WorldWideScience

Sample records for automotive gas turbine

  1. An automotive transmission for automotive gas turbine power plants

    Science.gov (United States)

    Polak, J. C.

    1980-01-01

    A joint government-industry program was initiated to investigate the two-shaft gas turbine concept as an alternative to present-day automotive powerplants. Both were examined, compared and evaluated on the basis of the federal automotive driving cycle in terms of specific fuel/power/speed characteristics of the engine and the efficiency and performance of the transmission. The results showed that an optimum match of vehicle, gas turbine engine, and conventional automatic transmission is capable of a significant improvement in fuel economy. This system offers many advantages that should lead to its wide acceptance in future vehicles.

  2. AGT-102 automotive gas turbine

    Science.gov (United States)

    1981-01-01

    Development of a gas turbine powertrain with a 30% fuel economy improvement over a comparable S1 reciprocating engine, operation within 0.41 HC, 3.4 CO, and 0.40 NOx grams per mile emissions levels, and ability to use a variety of alternate fuels is summarized. The powertrain concept consists of a single-shaft engine with a ceramic inner shell for containment of hot gasses and support of twin regenerators. It uses a fixed-geometry, lean, premixed, prevaporized combustor, and a ceramic radial turbine rotor supported by an air-lubricated journal bearing. The engine is coupled to the vehicle through a widerange continuously variable transmission, which utilizes gearing and a variable-ratio metal compression belt. A response assist flywheel is used to achieve acceptable levels of engine response. The package offers a 100 lb weight advantage in a Chrysler K Car front-wheel-drive installation. Initial layout studies, preliminary transient thermal analysis, ceramic inner housing structural analysis, and detailed performance analysis were carried out for the basic engine.

  3. Automotive Gas Turbine Power System-Performance Analysis Code

    Science.gov (United States)

    Juhasz, Albert J.

    1997-01-01

    An open cycle gas turbine numerical modelling code suitable for thermodynamic performance analysis (i.e. thermal efficiency, specific fuel consumption, cycle state points, working fluid flowrates etc.) of automotive and aircraft powerplant applications has been generated at the NASA Lewis Research Center's Power Technology Division. The use this code can be made available to automotive gas turbine preliminary design efforts, either in its present version, or, assuming that resources can be obtained to incorporate empirical models for component weight and packaging volume, in later version that includes the weight-volume estimator feature. The paper contains a brief discussion of the capabilities of the presently operational version of the code, including a listing of input and output parameters and actual sample output listings.

  4. Air cooling of disk of a solid integrally cast turbine rotor for an automotive gas turbine

    Science.gov (United States)

    Gladden, H. J.

    1977-01-01

    A thermal analysis is made of surface cooling of a solid, integrally cast turbine rotor disk for an automotive gas turbine engine. Air purge and impingement cooling schemes are considered and compared with an uncooled reference case. Substantial reductions in blade temperature are predicted with each of the cooling schemes studied. It is shown that air cooling can result in a substantial gain in the stress-rupture life of the blade. Alternatively, increases in the turbine inlet temperature are possible.

  5. Fuel economy screening study of advanced automotive gas turbine engines

    Science.gov (United States)

    Klann, J. L.

    1980-01-01

    Fuel economy potentials were calculated and compared among ten turbomachinery configurations. All gas turbine engines were evaluated with a continuously variable transmission in a 1978 compact car. A reference fuel economy was calculated for the car with its conventional spark ignition piston engine and three speed automatic transmission. Two promising engine/transmission combinations, using gasoline, had 55 to 60 percent gains over the reference fuel economy. Fuel economy sensitivities to engine design parameter changes were also calculated for these two combinations.

  6. Advanced Gas Turbine (AGT) powertrain system development for automotive applications

    Science.gov (United States)

    1984-01-01

    Rotor dynamic instability investigations were conducted. Forward ball bearing hydraulic mount configurations were tested with little effect. Trial assembly of S/N 002 ceramic engine was initiated. Impeller design activities were completed on the straight line element (SLE) blade definition to address near-net-shape powder metal die forging. Performance characteristics of the Baseline Test 2A impeller were closely preserved. The modified blading design has been released for tooling procurement. Developmental testing of the diffusion flame combustor (DFC) for initial use in the S/N 002 2100 F ceramic structures engine was completed. A natural gas slave preheater was designed and fabricated. Preliminary regenerator static seal rig testing showed a significant reduction in leakage and sensitivity to stack height. Ceramic screening tests were completed and two complete sets of ceramic static structures were qualified for engine testing. Efforts on rotor dynamics development to resolve subsynchronous motion were continued.

  7. Aerodynamic design of a free power turbine for a 75 KW gas turbine automotive engine

    Science.gov (United States)

    Kofskey, M. G.; Katsanis, T.; Schumann, L. F.

    1975-01-01

    A single stage axial-flow turbine having a tip diameter of 15.41 centimeters was designed. The design specifications are given and the aerodynamic design procedure is described. The design includes the transition duct and the turbine exit diffuser. The aerodynamic information includes typical results of a parametric study, velocity diagrams, blade surface and wall velocities, and blade profile and wall coordinates.

  8. Splitter-bladed centrifugal compressor impeller designed for automotive gas turbine application. [at the Lewis Research Center

    Science.gov (United States)

    Pampreen, R. C.

    1977-01-01

    Mechanical design and fabrication of two splitter-bladed centrifugal compressor impellers were completed for rig testing at NASA Lewis Research Center. These impellers were designed for automotive gas turbine application. The mechanical design was based on NASA specifications for blade-shape and flowpath configurations. The contractor made engineering drawings and performed calculations for mass and center-of-gravity, for stress and vibration analyses, and for shaft critical speed analysis. One impeller was machined to print; the other had a blade height and exit radius of 2.54 mm larger than print dimensions.

  9. Development of low cost ceramic recuperator technology applicable to automotive gas turbine engines. Final report, April 1972--April 1977

    Energy Technology Data Exchange (ETDEWEB)

    Kormanyos, K.R.

    1978-02-01

    Oxide glass--ceramic recuperators for application to automotive gas turbine engines were investigated. Design data and fabrication feasibility were established. Evaluation of glass--ceramic recuperator structures was carried out on a series of experimental test specimens. Parametric design data for plate--fin type glass--ceramic recuperator configurations was developed over a range of engine operating conditions. Recuperator sizing procedures were developed to fit four conceptual recuperator designs to the DOE/Chrysler Baseline regenerated gas turbine engine. Assumed pressure drop and effectiveness value constraints on sizing yielded two design packages with acceptable dimensions to fit an automobile engine compartment. Four conceptual recuperator designs were fabricated as demonstration samples using CER-VIT C-132 glass--ceramic material. Single-pass cross-flow cores were fabricated using CER-VIT C-126 material for laboratory scale tests of cross-circuit leakage and hot-gas flow thermal cycling effects. The laboratory tests precipitated the development effect of a modified material system for test core fabrication. The modified material system proved successful in initial studies on small core sections; however, upon scale up to test core size unacceptably high cross-leakage resulted.

  10. Cold-air performance of free power turbine designed for 112-kilowatt automotive gas-turbine engine. 2: Effects of variable stator-vane-chord setting angle on turbine performance

    Science.gov (United States)

    Mclallin, K. L.; Kofskey, M. G.

    1979-01-01

    The cold-air performance of an axial-flow power turbine with a variable stator designed for a 112-kW automotive gas-turbine engine was determined at speeds from 30 to 110 percent of design and at pressure ratios from 1.11 to 2.67. Performance is presented in terms of equivalent mass flow, torque, power, and efficiency for stator-vane-chord setting angles of 26 degs, 30 degs, 35 degs (design), 40 degs, 45 degs, and 50 degs. Turbine braking performance at a nominal stator setting angle of 107 degs is also presented. Turbine efficiency increased with increasing stator setting angle. A 10-point efficiency increase was obtained by opening the stator from the design setting angle of 35 degs to a setting angle of 45 degs.

  11. Cold-air performance of free power turbine designed for 112-kilowatt automotive gas-turbine engine 3: Effect of stator vane end clearances on performance

    Science.gov (United States)

    Kofskey, M. G.; Mclallin, K. L.

    1978-01-01

    An experimental investigation of a free power turbine designed for a 112-kW, automotive, gas turbine engine was made to determine the penalty in performance due to the stator vane end clearances. Tests were made over a range of mean section stator vane angles from 26 deg to 50 deg (as measured from the plane of rotation) with the vane end clearances filled. These results were compared with test results of the same turbine with vane end clearances open. At design equivalent values of rotative speed and pressure ratio and at a vane angle of 35 deg, the mass flow with the vane and clearances filled was about 8 percent lower than mass flow with vane end clearances open. The decrease in mass flow was mitigated by increasing the vane angle. With the vane end clearances filled, there was about a 66 percent reduction in mass flow when the vane angle was decreased from 40 deg to 26 deg. For the same decrease in vane angle the stator throat area decreased by about 50 percent. This result indicates that the rotor losses were increasing with decreasing vane angle.

  12. Cold-air performance of free-power turbine designed for 112-kilowatt automotive gas-turbine engine. 1: Design Stator-vane-chord setting angle of 35 deg

    Science.gov (United States)

    Kofskey, M. G.; Nusbaum, W. J.

    1978-01-01

    A cold air experimental investigation of a free power turbine designed for a 112-kW automotive gas-turbine was made over a range of speeds from 0 to 130 percent of design equivalent speeds and over a range of pressure ratio from 1.11 to 2.45. Results are presented in terms of equivalent power, torque, mass flow, and efficiency for the design power point setting of the variable stator.

  13. The status of ceramic turbine component fabrication and quality assurance relevant to automotive turbine needs

    Energy Technology Data Exchange (ETDEWEB)

    Richerson, D.W.

    2000-02-01

    This report documents a study funded by the U.S. Department of Energy (DOE) Office of Transportation Technologies (OTT) with guidance from the Ceramics Division of the United States Automotive Materials Partnership (USAMP). DOE and the automotive companies have funded extensive development of ceramic materials for automotive gas turbine components, the most recent effort being under the Partnership for a New Generation of Vehicles (PNGV) program.

  14. Cold-air performance of a 15.41-cm-tip-diameter axial-flow power turbine with variable-area stator designed for a 75-kW automotive gas turbine engine

    Science.gov (United States)

    Mclallin, K. L.; Kofskey, M. G.; Wong, R. Y.

    1982-01-01

    An experimental evaluation of the aerodynamic performance of the axial flow, variable area stator power turbine stage for the Department of Energy upgraded automotive gas turbine engine was conducted in cold air. The interstage transition duct, the variable area stator, the rotor, and the exit diffuser were included in the evaluation of the turbine stage. The measured total blading efficiency was 0.096 less than the design value of 0.85. Large radial gradients in flow conditions were found at the exit of the interstage duct that adversely affected power turbine performance. Although power turbine efficiency was less than design, the turbine operating line corresponding to the steady state road load power curve was within 0.02 of the maximum available stage efficiency at any given speed.

  15. Gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Farahan, E.; Eudaly, J.P.

    1978-10-01

    This evaluation provides performance and cost data for commercially available simple- and regenerative-cycle gas turbines. Intercooled, reheat, and compound cycles are discussed from theoretical basis only, because actual units are not currently available, except on a special-order basis. Performance characteristics investigated include unit efficiency at full-load and off-design conditions, and at rated capacity. Costs are tabulated for both simple- and regenerative-cycle gas turbines. The output capacity of the gas turbines investigated ranges from 80 to 134,000 hp for simple units and from 12,000 to 50,000 hp for regenerative units.

  16. Effect of water injection and off scheduling of variable inlet guide vanes, gas generator speed and power turbine nozzle angle on the performance of an automotive gas turbine engine

    Science.gov (United States)

    Warren, E. L.

    1980-01-01

    The Chrysler/ERDA baseline automotive gas turbine engine was used to experimentally determine the power augmentation and emissions reductions achieved by the effect of variable compressor and power engine geometry, water injection downstream of the compressor, and increases in gas generator speed. Results were dependent on the mode of variable geometry utilization. Over 20 percent increase in power was accompanied by over 5 percent reduction in SFC. A fuel economy improvement of at least 6 percent was estimated for a vehicle with a 75 kW (100 hp) engine which could be augmented to 89 kW (120 hp) relative to an 89 Kw (120 hp) unaugmented engine.

  17. Automotive gas turbine ceramic regenerator design and reliability program. Final annual report, July 1, 1975--September 30, 1976

    Energy Technology Data Exchange (ETDEWEB)

    Cook, J.A.; Fucinari, C.A.; Lingscheit, J.N.; Rahnke, C.J.

    1976-10-01

    The primary objective of the ERDA/Ford Ceramic Regenerator Design and Reliability Program is to develop ceramic regenerator cores that can be used in passenger car gas turbine engines, Stirling engines, and industrial/truck gas turbine engines. Specific durability objectives are defined as achieving a B/sub 10/ life of 10,000 hours on a truck/industrial gas turbine engine duty cycle. Previous reports, under this program, summarized operating experience on lithium aluminum silicate (LAS) ceramic regenerator cores obtained at Ford Motor Company. The primary cause of failure of these regenerators was determined to be chemical attack of the LAS material. Improved materials and design concepts aimed at reducing or eliminating chemical attack were placed on durability test in Ford 707 industrial gas turbine engines late in 1974. A description is given of the results of 18,500 hours of turbine engine durability testing accumulated during the period from July 1, 1975 to Sept. 30, 1976. Two materials, aluminum silicate and magnesium aluminum silicate continue to show promise toward achieving the durability objectives of this program. Regenerator cores made from aluminum silicate show no evidence of chemical attack damage after 5600 hours of engine test.

  18. The Study of Automotive Exhaust Gas Turbine Power Generation Technology%汽车废气涡轮发电技术的研究

    Institute of Scientific and Technical Information of China (English)

    张勇斌

    2015-01-01

    汽车废气涡轮发电是利用汽车尾气能量推动涡轮转动并带动发电机发电的一项技术。基于汽车节能的思想,以东风EQ6100型内燃机为例设计了汽车废气回收利用装置,并从内燃机进气流量入手配合实际循环状态和排气状况,对热量的回收效益和涡轮机功率进行了计算,并对涡轮机结构进行了初步设计,发电机进行了选型匹配。计算得出了汽车废气涡轮发电涡轮机的功率和排气能量大小,证实了利用汽车废气驱动涡轮发电的可行性。%Automotive exhaust gas turbine power generation is a technology to use the car exhaust energy to rotate and drive a turbine generator to generate electricity. Based on the idea of energy-saving cars, taking Dongfeng EQ6100-type internal combustion engine as an example, a vehicle exhaust recycling system was designed. Combining the engine intake air flow rate and the actual cycling situation as well as the exhaust situation, the heat recovery efficiency and turbine power were calculated, turbine structure was preliminarily designed, and the selection of matching generators was carried out. Calculation of the automobile exhaust turbine generator turbine power and exhaust energy confirmed the feasibility of the use of motor vehicle exhaust to drive a turbine to generate electricity.

  19. On Mixed Flow Turbines for Automotive Turbocharger Applications

    OpenAIRE

    Bernhardt Lüddecke; Dietmar Filsinger; Jan Ehrhard

    2012-01-01

    Due to increased demands for improved fuel economy of passenger cars, low-end and part-load performance is of key importance for the design of automotive turbocharger turbines. In an automotive drive cycle, a turbine which can extract more energy at high pressure ratios and lower rotational speeds is desirable. In the literature it is typically found that radial turbines provide peak efficiency at speed ratios of 0.7, but at high pressure ratios and low rotational speeds the blade speed ratio...

  20. Gas turbine engine

    Science.gov (United States)

    Lawlor, Shawn P.; Roberts, II, William Byron

    2016-03-08

    A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.

  1. On Mixed Flow Turbines for Automotive Turbocharger Applications

    Directory of Open Access Journals (Sweden)

    Bernhardt Lüddecke

    2012-01-01

    Full Text Available Due to increased demands for improved fuel economy of passenger cars, low-end and part-load performance is of key importance for the design of automotive turbocharger turbines. In an automotive drive cycle, a turbine which can extract more energy at high pressure ratios and lower rotational speeds is desirable. In the literature it is typically found that radial turbines provide peak efficiency at speed ratios of 0.7, but at high pressure ratios and low rotational speeds the blade speed ratio will be low and the rotor will experience high values of positive incidence at the inlet. Based on fundamental considerations, it is shown that mixed flow turbines offer substantial advantages for such applications. Moreover, to prove these considerations an experimental assessment of mixed flow turbine efficiency and optimal blade speed ratio is presented. This has been achieved using a new semi-unsteady measurement approach. Finally, evidence of the benefits of mixed flow turbine behaviour in engine operation is given. Regarding turbocharged engine simulation, the benefit of wide-ranging turbine map measurement data as well as the need for reasonable turbine map extrapolation is illustrated.

  2. Gas turbine sealing apparatus

    Science.gov (United States)

    Wiebe, David J; Wessell, Brian J; Ebert, Todd; Beeck, Alexander; Liang, George; Marussich, Walter H

    2013-02-19

    A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine.

  3. Ceramic stationary gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Roode, M. van [Solar Turbines Inc., San Diego, CA (United States)

    1995-10-01

    The performance of current industrial gas turbines is limited by the temperature and strength capabilities of the metallic structural materials in the engine hot section. Because of their superior high-temperature strength and durability, ceramics can be used as structural materials for hot section components (blades, nozzles, combustor liners) in innovative designs at increased turbine firing temperatures. The benefits include the ability to increase the turbine inlet temperature (TIT) to about 1200{degrees}C ({approx}2200{degrees}F) or more with uncooled ceramics. It has been projected that fully optimized stationary gas turbines would have a {approx}20 percent gain in thermal efficiency and {approx}40 percent gain in output power in simple cycle compared to all metal-engines with air-cooled components. Annual fuel savings in cogeneration in the U.S. would be on the order of 0.2 Quad by 2010. Emissions reductions to under 10 ppmv NO{sub x} are also forecast. This paper describes the progress on a three-phase, 6-year program sponsored by the U.S. Department of Energy, Office of Industrial Technologies, to achieve significant performance improvements and emissions reductions in stationary gas turbines by replacing metallic hot section components with ceramic parts. Progress is being reported for the period September 1, 1994, through September 30, 1995.

  4. Ceramics technology for advanced industrial gas turbines

    International Nuclear Information System (INIS)

    Recent developments in the fabrication of high strength ceramic materials and in their application to automotive and aerospace gas turbine engines may lead also to significant improvements in the performance of industrial gas turbines. This paper presents a brief review of the improvements projected in a study initiated by the U.S. Department of Energy. The future costs of power generated by small gas turbines (up to 25 MW) are predicted, as well as the potential for fuel savings. Gas turbines in this size range are used extensively for gas compression and for cogeneration, as well as in a variety of more diverse applications. This paper includes results of analyses of the ways in which changes in gas turbine cost and performance are likely to affect market penetration. These results lead to predictions of future savings in U.S. fuel consumption in the industrial sector that would result. The paper also presents a brief overview of the scope of a suggested R and D program, with an appropriate schedule, which would provide a technical basis for achieving the projected results. Important parts of this program would cover ceramic design and fabrication technology, engine development and demonstration, and combustion technology

  5. Baseline Gas Turbine Development Program. Fourteenth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, F W; Wagner, C E

    1976-04-30

    Progress is reported for a Baseline Gas Turbine Development Program sponsored by the Heat Engine Systems Branch, Division of Transportation Energy Conservation (TEC) of the Energy Research and Development Administration (ERDA). Structurally, this program is made up of three parts: (1) documentation of the existing automotive gas turbine state-of-the-art; (2) conduction of an extensive component improvement program; and (3) utilization of the improvements in the design, and building of an Upgraded Engine capable of demonstrating program goals.

  6. Trends in gas turbine development

    Energy Technology Data Exchange (ETDEWEB)

    Day, W.H.

    1999-07-01

    This paper represents the Gas Turbine Association's view of the gas turbine industry's R and D needs following the Advanced Turbine Systems (ATS) Program which is funded by the U.S. Department of Energy (DOE). Some of this information was discussed at the workshop Next Generation Gas Turbine Power Systems, which was held in Austin, TX, February 9--10, 1999, sponsored by DOE-Federal Energy Technology Center (FETC), reference 1. The general idea is to establish public-private partnerships to reduce the risks involved in the development of new technologies which results in public benefits. The recommendations in this paper are focused on gas turbines > 30 MW output. Specific GTA recommendations on smaller systems are not addressed here. They will be addressed in conjunction with DOE-Energy Efficiency.

  7. Gas turbine combustor

    Science.gov (United States)

    Burd, Steven W. (Inventor); Cheung, Albert K. (Inventor); Dempsey, Dae K. (Inventor); Hoke, James B. (Inventor); Kramer, Stephen K. (Inventor); Ols, John T. (Inventor); Smith, Reid Dyer Curtis (Inventor); Sowa, William A. (Inventor)

    2011-01-01

    A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.

  8. Biomass combustion gas turbine CHP

    Energy Technology Data Exchange (ETDEWEB)

    Pritchard, D.

    2002-07-01

    This report summarises the results of a project to develop a small scale biomass combustor generating system using a biomass combustor and a micro-gas turbine indirectly fired via a high temperature heat exchanger. Details are given of the specification of commercially available micro-turbines, the manufacture of a biomass converter, the development of a mathematical model to predict the compatibility of the combustor and the heat exchanger with various compressors and turbines, and the utilisation of waste heat for the turbine exhaust.

  9. H gas turbine combined cycle

    Energy Technology Data Exchange (ETDEWEB)

    Corman, J. [General Electric Co., Schenectady, NY (United States)

    1995-10-01

    A major step has been taken in the development of the Next Power Generation System - {open_quotes}H{close_quotes} Technology Combined Cycle. This new gas turbine combined-cycle system increases thermal performance to the 60% level by increasing gas turbine operating temperature to 1430 C (2600 F) at a pressure ratio of 23 to 1. Although this represents a significant increase in operating temperature for the gas turbine, the potential for single digit NOx levels (based upon 15% O{sub 2}, in the exhaust) has been retained. The combined effect of performance increase and environmental control is achieved by an innovative closed loop steam cooling system which tightly integrates the gas turbine and steam turbine cycles. The {open_quotes}H{close_quotes} Gas Turbine Combined Cycle System meets the goals and objectives of the DOE Advanced Turbine System Program. The development and demonstration of this new system is being carried out as part of the Industrial/Government cooperative agreement under the ATS Program. This program will achieve first commercial operation of this new system before the end of the century.

  10. Influence of speed and frequency towards the automotive turbocharger turbine performance under pulsating flow conditions

    International Nuclear Information System (INIS)

    Highlights: • 3D CFD modeling of a turbocharger turbine with pulsating flow. • Characterization based on turbine speed and frequency. • Speed has higher influence on turbine performance compared to frequency. • Detailed localized flow behavior are shown for better understanding. - Abstract: The ever-increasing demand for low carbon applications in automotive industry has intensified the development of highly efficient engines and energy recovery devices. Even though there are significant developments in the alternative powertrains such as full electric, their full deployment is hindered by high costing and unattractive life-cycle energy and emission balance. Thus powertrain based on highly efficient internal combustion engines are still considered to be the mainstream for years to come. Traditionally, turbocharger has been an essential tool to boost the engine power, however in recent years it is seen as an enabling technology for engine downsizing. It is a well-known fact that a turbocharger turbine in an internal combustion engine operates in a highly pulsating exhaust flow. There are numerous studies looking into the complex interaction of the pulsating exhaust gas within the turbocharger turbine, however the phenomena is still not fully integrated into the design stage. Industry practice is still to design and match the turbine to an engine based on steady performance maps. The current work is undertaken with the mind to move one step closer towards fully integrating the pulsating flow performance into the turbocharger turbine design. This paper presents the development efforts and results from a full 3-D CFD model of a turbocharger turbine stage. The simulations were conducted at 30,000 rpm and 48,000 rpm (50% and 80% design speed respectively) for both 20 Hz and 80 Hz pulsating flow inlet conditions. Complete validation procedure using cold-flow experimental data is also described. The temporal and spatial resolutions of the incidence angle at the

  11. Calculation of gas turbine characteristic

    Science.gov (United States)

    Mamaev, B. I.; Murashko, V. L.

    2016-04-01

    The reasons and regularities of vapor flow and turbine parameter variation depending on the total pressure drop rate π* and rotor rotation frequency n are studied, as exemplified by a two-stage compressor turbine of a power-generating gas turbine installation. The turbine characteristic is calculated in a wide range of mode parameters using the method in which analytical dependences provide high accuracy for the calculated flow output angle and different types of gas dynamic losses are determined with account of the influence of blade row geometry, blade surface roughness, angles, compressibility, Reynolds number, and flow turbulence. The method provides satisfactory agreement of results of calculation and turbine testing. In the design mode, the operation conditions for the blade rows are favorable, the flow output velocities are close to the optimal ones, the angles of incidence are small, and the flow "choking" modes (with respect to consumption) in the rows are absent. High performance and a nearly axial flow behind the turbine are obtained. Reduction of the rotor rotation frequency and variation of the pressure drop change the flow parameters, the parameters of the stages and the turbine, as well as the form of the characteristic. In particular, for decreased n, nonmonotonic variation of the second stage reactivity with increasing π* is observed. It is demonstrated that the turbine characteristic is mainly determined by the influence of the angles of incidence and the velocity at the output of the rows on the losses and the flow output angle. The account of the growing flow output angle due to the positive angle of incidence for decreased rotation frequencies results in a considerable change of the characteristic: poorer performance, redistribution of the pressure drop at the stages, and change of reactivities, growth of the turbine capacity, and change of the angle and flow velocity behind the turbine.

  12. Modern low-pollutive industrial gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Marriott, A.

    1987-01-01

    As illustrated by aviation gas turbines, industrial gas-turbine engineering saw a rapid development towards light-weight compact units with enhanced efficiency. The Sulzer gas turbine type 10 is a most up-to-date machine which has not been derived simply from the aircraft engine but will also fully meet the requirements for stationary industrial operation.

  13. Electricity Cogeneration Using Open Gas Turbine

    OpenAIRE

    Kralj, Anita Kovac

    2010-01-01

    The inclusion of open gas turbine can increase the operating efficiency of the process. The gas turbine with its pressure and temperature drop can be included in the process cycle. The working fluid comes from the reactor and circulates through the process units: gas turbine, heat exchanger, separator (where the liquid product separates), and the compressor.

  14. ADVANCED GAS TURBINE SYSTEMS RESEARCH

    Energy Technology Data Exchange (ETDEWEB)

    Unknown

    2002-04-01

    The activities of the Advanced Gas Turbine Systems Research (AGTSR) program for this reporting period are described in this quarterly report. The report is divided into discussions of Membership, Administration, Technology Transfer (Workshop/Education), Research and Miscellaneous Related Activity. Items worthy of note are presented in extended bullet format following the appropriate heading.

  15. ADVANCED GAS TURBINE SYSTEMS RESEARCH

    Energy Technology Data Exchange (ETDEWEB)

    Unknown

    2002-02-01

    The activities of the Advanced Gas Turbine Systems Research (AGTSR) program for this reporting period are described in this quarterly report. The report is divided into discussions of Membership, Administration, Technology Transfer (Workshop/Education), Research and Miscellaneous Related Activity. Items worthy of note are presented in extended bullet format following the appropriate heading.

  16. Aeroderivative gas turbines for cogeneration

    International Nuclear Information System (INIS)

    Aircraft jet engine derivative gas turbines have gained acceptance for cogeneration applications through impressive advances in technology and especially in maintainability and reliability. The best advantages of heavy industrial turbines and of reliable commercial airline jet engines have been successfully joined to meet the requirements for industrial cogeneration service. The next generation is under development and offers improved thermal efficiencies, alternate fuel capabilities, low environmental emissions, flexibility of operation and improved competitive system economics. This paper summarizes the current aero-derivative engine features and advantages with various systems, and discusses advanced features under consideration at this time

  17. Advanced gas turbine systems program

    Energy Technology Data Exchange (ETDEWEB)

    Zeh, C.M.

    1995-06-01

    The U.S. Department of Energy (DOE) is sponsoring a program to develop fuel-efficient gas turbine-based power systems with low emissions. DOE`s Office of Fossil Energy (DOE/FE) and Office of Energy Efficiency and Renewable Energy (DOE/EE) have initiated an 8-year program to develop high-efficiency, natural gas-fired advanced gas turbine power systems. The Advanced Turbine Systems (ATS) Program will support full-scale prototype demonstration of both industrial- and utility-scale systems that will provide commercial marketplace entries by the year 2000. When the program targets are met, power system emissions will be lower than from the best technology in use today. Efficiency of the utility-scale units will be greater than 60 percent on a lower heating value basis, and emissions of carbon dioxide will be reduced inversely with this increase. Industrial systems will also see an improvement of at least 15 percent in efficiency. Nitrogen oxides will be reduced by at least 10 percent, and carbon monoxide and hydrocarbon emissions will each be kept below 20 parts per million, for both utility and industrial systems.

  18. GAS TURBINE ENGINES CONSUMING BIOGAS

    Directory of Open Access Journals (Sweden)

    Е. Ясиніцький

    2011-04-01

    Full Text Available A problem of implementation of biofuel for power plants of big capacity was considered in thisarticle. Up to date in the world practice a wide implementation of biogas plants of low and medialcapacity are integrated. It is explained by the big amount of enterprises in which relatively smallvolumes of organic sediment excrete in the process of its activity. An emphasis of article is on thatenterprises, which have big volumes of sediments for utilizing of which module system of medialcapacity biogas plants are non-effective. The possibility of using biogas and biomethane as a fuelfor gas turbine engine is described. The basic problems of this technology and ways of its solutionsare indicated. Approximate profitability of biogas due to example of compressor station locatednearby poultry factory was determined also. Such factors as process characteristics of engine withcapacity of 5 MW, approximate commercial price for natural gas and equipment costs due toofficial sources of “Zorg Ukraine” company was taken into consideration. The necessity forproviding researches on influence of biogas on the process characteristics of gas turbine engine andits reliability, constructing modern domestic purification system for biogas was shown.

  19. Combustion modeling in advanced gas turbine systems

    Energy Technology Data Exchange (ETDEWEB)

    Smoot, L.D.; Hedman, P.O.; Fletcher, T.H. [Brigham Young Univ., Provo, UT (United States)] [and others

    1995-10-01

    The goal of the U.S. Department of Energy`s Advanced Turbine Systems (ATS) program is to help develop and commercialize ultra-high efficiency, environmentally superior, and cost competitive gas turbine systems for base-load applications in the utility, independent power producer, and industrial markets. Combustion modeling, including emission characteristics, has been identified as a needed, high-priority technology by key professionals in the gas turbine industry.

  20. Advanced Gas Turbine (AGT) power-train system development

    Science.gov (United States)

    Helms, H. E.; Johnson, R. A.; Gibson, R. K.

    1982-01-01

    Technical work on the design and component testing of a 74.5 kW (100 hp) advanced automotive gas turbine is described. Selected component ceramic component design, and procurement were tested. Compressor tests of a modified rotor showed high speed performance improvement over previous rotor designs; efficiency improved by 2.5%, corrected flow by 4.6%, and pressure ratio by 11.6% at 100% speed. The aerodynamic design is completed for both the gasifier and power turbines. Ceramic (silicon carbide) gasifier rotors were spin tested to failure. Improving strengths is indicated by burst speeds and the group of five rotors failed at speeds between 104% and 116% of engine rated speed. The emission results from combustor testing showed NOx levels to be nearly one order of magnitude lower than with previous designs. A one piece ceramic exhaust duct/regenerator seal platform is designed with acceptable low stress levels.

  1. Integrated Turbine Tip Clearance and Gas Turbine Engine Simulation

    Science.gov (United States)

    Chapman, Jeffryes W.; Kratz, Jonathan; Guo, Ten-Huei; Litt, Jonathan

    2016-01-01

    Gas turbine compressor and turbine blade tip clearance (i.e., the radial distance between the blade tip of an axial compressor or turbine and the containment structure) is a major contributing factor to gas path sealing, and can significantly affect engine efficiency and operational temperature. This paper details the creation of a generic but realistic high pressure turbine tip clearance model that may be used to facilitate active tip clearance control system research. This model uses a first principles approach to approximate thermal and mechanical deformations of the turbine system, taking into account the rotor, shroud, and blade tip components. Validation of the tip clearance model shows that the results are realistic and reflect values found in literature. In addition, this model has been integrated with a gas turbine engine simulation, creating a platform to explore engine performance as tip clearance is adjusted. Results from the integrated model explore the effects of tip clearance on engine operation and highlight advantages of tip clearance management.

  2. Advanced IGCC/Hydrogen Gas Turbine Development

    Energy Technology Data Exchange (ETDEWEB)

    York, William [General Electric Company, Schenectady, NY (United States); Hughes, Michael [General Electric Company, Schenectady, NY (United States); Berry, Jonathan [General Electric Company, Schenectady, NY (United States); Russell, Tamara [General Electric Company, Schenectady, NY (United States); Lau, Y. C. [General Electric Company, Schenectady, NY (United States); Liu, Shan [General Electric Company, Schenectady, NY (United States); Arnett, Michael [General Electric Company, Schenectady, NY (United States); Peck, Arthur [General Electric Company, Schenectady, NY (United States); Tralshawala, Nilesh [General Electric Company, Schenectady, NY (United States); Weber, Joseph [General Electric Company, Schenectady, NY (United States); Benjamin, Marc [General Electric Company, Schenectady, NY (United States); Iduate, Michelle [General Electric Company, Schenectady, NY (United States); Kittleson, Jacob [General Electric Company, Schenectady, NY (United States); Garcia-Crespo, Andres [General Electric Company, Schenectady, NY (United States); Delvaux, John [General Electric Company, Schenectady, NY (United States); Casanova, Fernando [General Electric Company, Schenectady, NY (United States); Lacy, Ben [General Electric Company, Schenectady, NY (United States); Brzek, Brian [General Electric Company, Schenectady, NY (United States); Wolfe, Chris [General Electric Company, Schenectady, NY (United States); Palafox, Pepe [General Electric Company, Schenectady, NY (United States); Ding, Ben [General Electric Company, Schenectady, NY (United States); Badding, Bruce [General Electric Company, Schenectady, NY (United States); McDuffie, Dwayne [General Electric Company, Schenectady, NY (United States); Zemsky, Christine [General Electric Company, Schenectady, NY (United States)

    2015-07-30

    The objective of this program was to develop the technologies required for a fuel flexible (coal derived hydrogen or syngas) gas turbine for IGCC that met DOE turbine performance goals. The overall DOE Advanced Power System goal was to conduct the research and development (R&D) necessary to produce coal-based IGCC power systems with high efficiency, near-zero emissions, and competitive capital cost. To meet this goal, the DOE Fossil Energy Turbine Program had as an interim objective of 2 to 3 percentage points improvement in combined cycle (CC) efficiency. The final goal is 3 to 5 percentage points improvement in CC efficiency above the state of the art for CC turbines in IGCC applications at the time the program started. The efficiency goals were for NOx emissions of less than 2 ppm NOx (@15 % O2). As a result of the technologies developed under this program, the DOE goals were exceeded with a projected 8 point efficiency improvement. In addition, a new combustion technology was conceived of and developed to overcome the challenges of burning hydrogen and achieving the DOE’s NOx goal. This report also covers the developments under the ARRA-funded portion of the program that include gas turbine technology advancements for improvement in the efficiency, emissions, and cost performance of gas turbines for industrial applications with carbon capture and sequestration. Example applications could be cement plants, chemical plants, refineries, steel and aluminum plants, manufacturing facilities, etc. The DOE’s goal for more than 5 percentage point improvement in efficiency was met with cycle analyses performed for representative IGCC Steel Mill and IGCC Refinery applications. Technologies were developed in this program under the following areas: combustion, larger latter stage buckets, CMC and EBC, advanced materials and coatings, advanced configurations to reduce cooling, sealing and rotor purge flows, turbine aerodynamics, advanced sensors, advancements in first

  3. Advanced IGCC/Hydrogen Gas Turbine Development

    Energy Technology Data Exchange (ETDEWEB)

    York, William; Hughes, Michael; Berry, Jonathan; Russell, Tamara; Lau, Y. C.; Liu, Shan; Arnett, Michael; Peck, Arthur; Tralshawala, Nilesh; Weber, Joseph; Benjamin, Marc; Iduate, Michelle; Kittleson, Jacob; Garcia-Crespo, Andres; Delvaux, John; Casanova, Fernando; Lacy, Ben; Brzek, Brian; Wolfe, Chris; Palafox, Pepe; Ding, Ben; Badding, Bruce; McDuffie, Dwayne; Zemsky, Christine

    2015-04-30

    The objective of this program was to develop the technologies required for a fuel flexible (coal derived hydrogen or syngas) gas turbine for IGCC that met DOE turbine performance goals. The overall DOE Advanced Power System goal was to conduct the research and development (R&D) necessary to produce coal-based IGCC power systems with high efficiency, near-zero emissions, and competitive capital cost. To meet this goal, the DOE Fossil Energy Turbine Program had as an interim objective of 2 to 3 percentage points improvement in combined cycle (CC) efficiency. The final goal is 3 to 5 percentage points improvement in CC efficiency above the state of the art for CC turbines in IGCC applications at the time the program started. The efficiency goals were for NOx emissions of less than 2 ppm NOx (@15 % O2). As a result of the technologies developed under this program, the DOE goals were exceeded with a projected 8 point efficiency improvement. In addition, a new combustion technology was conceived of and developed to overcome the challenges of burning hydrogen and achieving the DOE’s NOx goal. This report also covers the developments under the ARRA-funded portion of the program that include gas turbine technology advancements for improvement in the efficiency, emissions, and cost performance of gas turbines for industrial applications with carbon capture and sequestration. Example applications could be cement plants, chemical plants, refineries, steel and aluminum plants, manufacturing facilities, etc. The DOE’s goal for more than 5 percentage point improvement in efficiency was met with cycle analyses performed for representative IGCC Steel Mill and IGCC Refinery applications. Technologies were developed in this program under the following areas: combustion, larger latter stage buckets, CMC and EBC, advanced materials and coatings, advanced configurations to reduce cooling, sealing and rotor purge flows, turbine aerodynamics, advanced sensors, advancements in first

  4. Gas Turbines: ''low NOx'' technologies at EGT

    International Nuclear Information System (INIS)

    For more than 15 years, European Gas Turbines (EGT - GEC Alsthom Group) has gained an important know-how culture and can use its rich feedback experience in the domain of gas turbine emissions. The EGT gas turbine units equipped with denitrogenation technologies cover the 4 to 226 MW power range and cumulate more than 1.7 hours of functioning in the different existing installations in the world. This paper describes the economical and environmental interests of gas turbines for power production and the combustion technologies developed by EGT to reduce the NOx emissions. The selective catalytic reduction technique is the only available secondary technique with can allow NOx and CO emissions lower than 10 ppm. Other technologies involving diluent injection (water, water-fuel mixture, vapor..) are also described and were developed in several countries to reduce the emission of these pollutants. (J.S.)

  5. Aircraft gas turbine materials and processes.

    Science.gov (United States)

    Kear, B H; Thompson, E R

    1980-05-23

    Materials and processing innovations that have been incorporated into the manufacture of critical components for high-performance aircraft gas turbine engines are described. The materials of interest are the nickel- and cobalt-base superalloys for turbine and burner sections of the engine, and titanium alloys and composites for compressor and fan sections of the engine. Advanced processing methods considered include directional solidification, hot isostatic pressing, superplastic foring, directional recrystallization, and diffusion brazing. Future trends in gas turbine technology are discussed in terms of materials availability, substitution, and further advances in air-cooled hardware.

  6. The marriage of gas turbines and coal

    International Nuclear Information System (INIS)

    This paper reports on developing gas turbine systems that can use coal or a coal-based fuel ensures that the United States will have cost-effective environmentally sound options for supplying future power generation needs. Power generation systems that marry coal or a coal-based fuel to a gas turbine? Some matchmakers would consider this an unlikely marriage. Historically, most gas turbines have been operated only on premium fuels, primarily natural gas or distillate oil. The perceived problems from using coal or coal-based fuels in turbines are: Erosion and deposition: Coal ash particles in the hot combustion gases passing through the expander turbine could erode or deposit on the turbine blades. Corrosion: Coal combustion will release alkali compounds form the coal ash. Alkali in the hot gases passing through the expander turbine can cause corrosion of high-temperature metallic surfaces. Emissions: coal contains higher levels of ash, fuel-bound sulfur and nitrogen compounds, and trace contaminants than premium fuels. Meeting stringent environmental regulations for particulates, sulfur dioxide (SO2), nitrogen oxides (NOx), and trace contaminants will be difficult. Economics: Coal-based systems are expensive to build. The difference in price between coal and premium fuels must be large enough to justify the higher capital cost

  7. Research and development of ceramic gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Suzuki, Kazuo [National Aerospace Laboratory, Chofu-shi, Tokyo (Japan)

    1993-12-31

    The CO{sub 2} caused by the consumption of hydrocarbon fuel is one of the main gases which affect the global climate. In order to reduce the formation of CO{sub 2}, it is necessary to conserve energy as effectively as possible. Therefore the heat energy provided by the fuel should be utilized in multi-cascades. The energy at the high temperature should be used for the generation of electric power and the energy at low temperature could be used for making the steam and the hot water. The gas turbine is preferable for this purpose. The heat energy of exhaust gas can be reused more easily. The two systems are proposed by using the gas turbine as the high temperature stage. One is the cogeneration system and the other is the combined cycle. The former generates electric power by the gas turbine and make steam or hot water in the exhaust gas. The latter employs the gas turbine as the high temperature cycle and the steam turbine as the low temperature cycle.

  8. Improved automobile gas turbine engine

    Science.gov (United States)

    Kofskey, M. G.; Katsanis, T.; Roelke, R. J.; Mclallin, K. L.; Wong, R. Y.; Schumann, L. F.; Galvas, M. R.

    1976-01-01

    Upgraded engine delivers 100 hp in 3500 lb vehicle. Improved fuel economy is due to combined effects of reduced weight, reduced power-to-weight ratio, increased turbine inlet pressure, and improved component efficiencies at part power.

  9. REGENERATIVE GAS TURBINES WITH DIVIDED EXPANSION

    DEFF Research Database (Denmark)

    Elmegaard, Brian; Qvale, Einar Bjørn

    2004-01-01

    divided expansion can be advantageous under certain circumstances. But, in order for todays micro gas turbines to be competitive, the thermodynamic efficiencies will have to be rather high. This requires that all component efficiencies including the recuperator effectiveness will have to be high....... The advantages of the divided expansion manifest themselves over a rather limited range of the operating parameters, that lies outside the range required to make modern micro turbines economically competitive....

  10. Gas turbine cleaning upgrade (compressor wash)

    Energy Technology Data Exchange (ETDEWEB)

    Asplund, P. [Gas Turbine Efficiency, Jarfalla (Sweden)

    1998-12-31

    The influence of gas turbine degradation on operating costs is high. Gas turbine cleaning is one of many actions taken for power recovery and is to consider as preventive maintenance. It is generally performed within the industrial field and occasionally within the aero sector. In order to meet the gas turbine development win high blade loads and ever-increasing temperatures, together with emission Aces and environmental regulations, more efficient and careful cleaning methods are needed. Following a survey about potentials for cost reduction in gas turbine operation a new man-hour and water saving cleaning method has been evaluated for a standard process. Compared with traditional cleaning methods, the new method is water,- cost,- weight and space saving due to a new washing technique. Traditional methods are based on using different nozzles for ON and OFF-line cleaning, which rise the demand for complicated systems. In the new method the same nozzle installation, same liquid flow and pressure is used for both ON and OFF-line cleaning. This gives a cost reduction of appr. 20.000 - 30.000 USD per gas turbine depending on installation and size. Evaluation of the new method shows significantly improved ON -line cleaning performance and thus OFF -line cleaning is required only during scheduled stops. (orig.) 10 refs.

  11. Exhaust gas energy recovery system of pneumatic driving automotive engine

    Institute of Scientific and Technical Information of China (English)

    Han Yongqiang; Sun Wenxu; Li Qinghua; Zhong Ming; Hao Wei; Du Wenchang

    2011-01-01

    Almost the same quantity to net output work of energy has been carried out and wasted by exhaust gas in typical automotive engine. Recovering the energy from exhaust gas and converting to mechanical energy will dramatically increase the heat efficiency and decrease the fuel consumption. With the increasing demand of fuel conservation, exhaust gas energy recovery technologies have been a hot topic. At present, many researches have been focused on heating or cooling the cab, mechanical energy using and thermo-electronic converting. Unfortunately, the complicated transmission of mechanical energy using and the depressed efficiency of thermo-electronic converting restrict their widely applying. In this paper, a kind of exhaust gas energy recovery system of pneumatic driving automotive engine, in which highly compressed air acts as energy storing and converting carrier, has been established. Pneumatic driving motor can produce moderate speed and high torque output, which is compatible for engine using. The feasibility has been certificated by GT-Power simulation and laboratory testes. The technologies about increasing recovery efficiency have been discussed in detail. The results demonstrated that the in parallel exhaust gas energy recovery system, which is similar to the compound turbo-charger structure can recovery 8 to 10 percent of rated power output. At last, a comprehensive system,which includes Rankine cycle based power wheel cycle unit etc. , has been introduced.

  12. Operating cost analysis aids gas turbine selection

    Energy Technology Data Exchange (ETDEWEB)

    Roy, G.K. [PT Indo-Rama Synthetics tbk., Purwakarta (Indonesia)

    1998-02-01

    If one considers the design life of a gas turbine to be 20 years, probably more than 70% of the plant operating costs will consist of fuel. And as fuel cost varies geographically, it is obvious that choosing a gas turbine, or for that matter any other prime mover, will depend on the fuel cost prevailing in that country. Spreadsheets make the analysis easier. A few options are presented to show the possible variations. The data taken for examples are typical. To illustrate the options, a typical requirement has been suggested for a plant--an electric power requirement of 50 MW and a process steam requirement of 70 tph. The selected gas/steam turbines, or diesel engine, will generate the electric power. When the equipment is down, the state electrical grid will provide the power.

  13. Gas turbine Type 10 - a modern, environmentally-compatible industrial turbine

    Energy Technology Data Exchange (ETDEWEB)

    Marriott, A.

    1987-01-01

    A rapid development to lighter, more compact units of higher efficiency has taken place in industrial gas turbine design, following the example set by aviation gas turbines. The Sulzer Type 10 gas turbine is an up-to-date machine, the design of which is not merely derived from that of jet engines, but also fully complies with the requirements of industrial service. The performance of this gas turbine is discussed.

  14. Advanced Coal-Fueled Gas Turbine Program

    Energy Technology Data Exchange (ETDEWEB)

    Horner, M.W.; Ekstedt, E.E.; Gal, E.; Jackson, M.R.; Kimura, S.G.; Lavigne, R.G.; Lucas, C.; Rairden, J.R.; Sabla, P.E.; Savelli, J.F.; Slaughter, D.M.; Spiro, C.L.; Staub, F.W.

    1989-02-01

    The objective of the original Request for Proposal was to establish the technological bases necessary for the subsequent commercial development and deployment of advanced coal-fueled gas turbine power systems by the private sector. The offeror was to identify the specific application or applications, toward which his development efforts would be directed; define and substantiate the technical, economic, and environmental criteria for the selected application; and conduct such component design, development, integration, and tests as deemed necessary to fulfill this objective. Specifically, the offeror was to choose a system through which ingenious methods of grouping subcomponents into integrated systems accomplishes the following: (1) Preserve the inherent power density and performance advantages of gas turbine systems. (2) System must be capable of meeting or exceeding existing and expected environmental regulations for the proposed application. (3) System must offer a considerable improvement over coal-fueled systems which are commercial, have been demonstrated, or are being demonstrated. (4) System proposed must be an integrated gas turbine concept, i.e., all fuel conditioning, all expansion gas conditioning, or post-expansion gas cleaning, must be integrated into the gas turbine system.

  15. Performance of nickel base superalloy components in gas turbines

    DEFF Research Database (Denmark)

    Dahl, Kristian Vinter

    2006-01-01

    The topic of this thesis is the microstructural behaviour of hot section components in the industrial gas turbine......The topic of this thesis is the microstructural behaviour of hot section components in the industrial gas turbine...

  16. Emissions control for ground power gas turbines

    Science.gov (United States)

    Rudney, R. A.; Priem, R. J.; Juhasz, A. J.; Anderson, D. N.; Mroz, T. S.; Mularz, E. J.

    1977-01-01

    The similarities and differences of emissions reduction technology for aircraft and ground power gas turbines is described. The capability of this technology to reduce ground power emissions to meet existing and proposed emissions standards is presented and discussed. Those areas where the developing aircraft gas turbine technology may have direct application to ground power and those areas where the needed technology may be unique to the ground power mission are pointed out. Emissions reduction technology varying from simple combustor modifications to the use of advanced combustor concepts, such as catalysis, is described and discussed.

  17. Performances of the Chemical Gas Turbine System and Comparison with Other Gas Turbine Based Cycles

    Directory of Open Access Journals (Sweden)

    Norio Arai

    2000-12-01

    Full Text Available

    This paper describes a novel combined cycle based on a “Chemical Gas Turbine” system. The system consists of fuel-rich and fuel-lean combustors with their gas turbines, recuperators, and a steam bottoming cycle. Important features of this system are the gas turbine with C/C composites blades and the fuel-rich combustion techniques. These techniques result in no cooling of turbine blades and much higher turbine inlet temperature, therefore, much higher thermal efficiency. This paper analyzes the energy, exergy, and heat exchanger sizes of the proposed system. Furthermore, optimizations from pressure ratio aspects are discussed. All results are compared with a simple gas turbine system and a conventional combined cycle. The following results were obtained: the chemical gas turbine system achieves a thermal efficiency of 64%, and low exergy loss in the combustion processes. In addition, characteristics of the system are similar to the simple gas turbine system.

    •  This paper was presented at the ECOS'00 Conference in Enschede, July 5-7, 2000

  18. Experience with unconventional gas turbine fuels

    Energy Technology Data Exchange (ETDEWEB)

    Mukherjee, D.K. [ABB Power Generation Ltd., Baden (Switzerland)

    1996-12-31

    Low grade fuels such as Blast Furnace Gas, biomass, residual oil, coke, and coal - if used in conjunction with appropriate combustion, gasification, and clean-up processes and in combination with a gas turbine combined cycle -offer attractive and environmentally sound power generation. Recently, the Bao Shan Iron and Steel Company in Shanghai placed an order with Kawasaki Heavy Industries, Japan, to supply a combined-cycle power plant. The plant is to employ ABB`s GT 11N2 with a combustor modified to burn blast furnace gas. Recent tests in Shanghai and at Kawasaki Steel, Japan, have confirmed the burner design. The same basic combustor concept can also be used for the low BTU gas derived from airblown gasification processes. ABB is also participating in the API project: A refinery-residual gasification combined-cycle plant in Italy. The GT 13E2 gas turbine employees MBTU EV burners that have been successfully tested under full operating conditions. These burners can also handle the MBTU gas produced in oxygenblown coal gasification processes. ABB`s vast experience in burning blast furnace gas (21 plants built during the 1950s and 1960s), residuals, crude, and coal in various gas turbine applications is an important asset for building such power plants. This presentation discusses some of the experience gained in such plants. (orig.) 6 refs.

  19. Sulzer's industrial gas turbine type 10

    Energy Technology Data Exchange (ETDEWEB)

    Marriott, A.C.

    1987-06-01

    A rapid development to lighter, compacter units of higher efficiency has taken place in industrial gas turbine design, following the example set by aviation gas turbines. The Sulzer Type 10 gas turbine is an up-to-date machine, the design of which is not merely derived from that of jet engines, but also fully complies with the requirements of industrial service.

  20. Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and with a Bypass

    Science.gov (United States)

    Suciu, Gabriel L. (Inventor); Chandler, Jesse M. (Inventor)

    2016-01-01

    A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.

  1. Airfoil for a turbine of a gas turbine engine

    Science.gov (United States)

    Liang, George

    2010-12-21

    An airfoil for a turbine of a gas turbine engine is provided. The airfoil comprises a main body comprising a wall structure defining an inner cavity adapted to receive a cooling air. The wall structure includes a first diffusion region and at least one first metering opening extending from the inner cavity to the first diffusion region. The wall structure further comprises at least one cooling circuit comprising a second diffusion region and at least one second metering opening extending from the first diffusion region to the second diffusion region. The at least one cooling circuit may further comprise at least one third metering opening, at least one third diffusion region and a fourth diffusion region.

  2. SMALL SCALE BIOMASS FUELED GAS TURBINE ENGINE

    Science.gov (United States)

    A new generation of small scale (less than 20 MWe) biomass fueled, power plants are being developed based on a gas turbine (Brayton cycle) prime mover. These power plants are expected to increase the efficiency and lower the cost of generating power from fuels such as wood. The n...

  3. Combined cycles with gas turbine engines

    Energy Technology Data Exchange (ETDEWEB)

    Najjar, Y.S.H.; Akyurt, M. (King Abdulaziz Univ., Jeddah (Saudi Arabia). Mechanical Engineering Dept.)

    1994-03-01

    Simple cycle gas turbine engines suffer from limited efficiencies and consequential dominance of fuel prices on generation costs. Combined cycles, however. exploit the waste heat from exhaust gases to boost power output, resulting in overall efficiencies around 50%, which are significantly above those of steam power plants. This paper reviews various types of combined cycles, including repowering, integrated gasification and other advanced systems. (author)

  4. Impingement jet cooling in gas turbines

    CERN Document Server

    Amano, R S

    2014-01-01

    Due to the requirement for enhanced cooling technologies on modern gas turbine engines, advanced research and development has had to take place in field of thermal engineering. Impingement jet cooling is one of the most effective in terms of cooling, manufacturability and cost. This is the first to book to focus on impingement cooling alone.

  5. Mixer Assembly for a Gas Turbine Engine

    Science.gov (United States)

    Dai, Zhongtao (Inventor); Cohen, Jeffrey M. (Inventor); Fotache, Catalin G. (Inventor); Smith, Lance L. (Inventor); Hautman, Donald J. (Inventor)

    2015-01-01

    A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.

  6. The gas turbine - a bundle of energy - requires tender care

    Energy Technology Data Exchange (ETDEWEB)

    Saarinen, J.; Uronen, J.; Leisio, C. [ed.

    1997-11-01

    The ability of a power plant to generate energy economically depends to a great extent on the functioning of the turbine. These days, an increasingly large number of these power plant `motors` are gas turbines. IVO`s expertise in the operation, maintenance and repair of gas turbines is based on long practical experience and the company`s own research. And IVO is also no stranger to the design and construction of new gas turbine plants

  7. Motor motives. Gas motors and gas turbines in cogeneration stations

    Energy Technology Data Exchange (ETDEWEB)

    Hein, K.

    1987-04-01

    Gas turbines' attractivity is increasing. But despite the impressive efficiency of 50% the gas motor is not yet beaten. A steam process installed downstream of a piston engine boosts its mechanic efficiency, in the lower performance range these engines are peerless anyway.

  8. Advanced Gas Turbine (AGT): Power-train system development

    Science.gov (United States)

    Helms, H. E.; Johnson, R. A.; Gibson, R. K.; Smith, L. B.

    1983-01-01

    Technical work on the design and effort leading to the testing of a 74.5 kW (100 hp) automotive gas turbine is described. The general effort was concentrated on building an engine for test starting in July. The buildup progressed with only routine problems and the engine was delivered to the test stand 9 July. In addition to the engine build effort, work continued in selected component areas. Ceramic turbine parts were built and tested. Burst tests of ceramic rotors show strengths are approaching that achieved in test bars; proof testing is required for acceptable strength ceramic vanes. Over 25 hours was accumulated on the combustor rig in three test modes: pilot nozzle only, start nozzle, and main nozzle operation. Satisfactory ignition was achieved for a wide range of starting speeds and the lean blowout limit was as low as 0.06 kg/b (0.14 lb/hr). Lean blowout was more a function of nozzle atomization than fuel/air ratio. A variety of cycle points were tested. Transition from start nozzle flow to main nozzle flow was done manually without difficulty. Regenerator parts were qualification tested without incident and the parts were assembled on schedule. Rig based performance matched first build requirements. Repeated failures in the harmonic drive gearbox during rig testing resulted in that concept being abandoned for an alternate scheme.

  9. Casing for a gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Wiebe, David J.; Little, David A.; Charron, Richard C.

    2016-07-12

    A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).

  10. Detonation wave compression in gas turbines

    Science.gov (United States)

    Wortman, A.

    1986-01-01

    A study was made of the concept of augmenting the performance of low pressure ratio gas turbines by detonation wave compression of part of the flow. The concept exploits the constant volume heat release of detonation waves to increase the efficiency of the Brayton cycle. In the models studied, a fraction of the compressor output was channeled into detonation ducts where it was processed by transient transverse detonation waves. Gas dynamic studies determined the maximum cycling frequency of detonation ducts, proved that upstream propagation of pressure pulses represented no problems and determined the variations of detonation duct output with time. Mixing and wave compression were used to recombine the combustor and detonation duct flows and a concept for a spiral collector to further smooth the pressure and temperature pulses was presented as an optional component. The best performance was obtained with a single firing of the ducts so that the flow could be re-established before the next detonation was initiated. At the optimum conditions of maximum frequency of the detonation ducts, the gas turbine efficiency was found to be 45 percent while that of a corresponding pressure ratio 5 conventional gas turbine was only 26%. Comparable improvements in specific fuel consumption data were found for gas turbines operating as jet engines, turbofans, and shaft output machines. Direct use of the detonation duct output for jet propulsion proved unsatisfactory. Careful analysis of the models of the fluid flow phenomena led to the conclusion that even more elaborate calculations would not diminish the uncertainties in the analysis of the system. Feasibility of the concept to work as an engine now requires validation in an engineering laboratory experiment.

  11. Performance-analysis-based gas turbine diagnostics: a review.

    OpenAIRE

    Li, Y.G.

    2002-01-01

    Gas turbine diagnostics has a history almost as long as gas turbine development itself. Early engine fault diagnosis was carried out based on manufacturer information supplied in a technical manual combined with maintenance experience. In the late 1960’s when Urban introduced Gas Path Analysis, gas turbine diagnostics made a big breakthrough. Since then different methods have been developed and used in both aero and industrial applications. Until now a substantial number of papers have been p...

  12. Internet operation of aero gas turbines

    OpenAIRE

    Diakostefanis, Michail

    2014-01-01

    Internet applications have been extended to various aspects of everyday life and offer services of high reliability and security. In the Academia, Internet applications offer useful tools for the remote creation of simulation models and real-time conduction of control experiments. The aim of this study was the design of a reliable, safe and secure software system for real time operation of a remote aero gas turbine, with the use of standard Internet technology at very low cost....

  13. Combustion heating value gas in a gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Kelsall, G. [CTDD, British Coal Corporation, Cheltenham (United Kingdom); Cannon, M. [European Gas Turbines Ltd., Lincoln (United Kingdom)

    1996-12-31

    Advanced coal and/or biomass based power generation systems offer the potential for high efficiency electricity generation with minimum environmental impact. An important component for many of these advanced power generation cycles is the gas turbine, for which development of a combustion system to burn low calorific value coal derived fuel gas, at turbine inlet temperatures of typically 1 100 - 1 260 deg C and with minimum pollutant emissions, is a key issue. A phased combustor development programme is under-way burning low calorific value fuel gas (3.6 - 4.1 MJ/m{sup 3}) with low emissions, particularly NO{sub x} derived from fuel-bound nitrogen. The first and second phases of the combustor development programme have been completed. The first phase used a generic tubo-annular, prototype combustor based on conventional design principles. Combustor performance for this first prototype combustor was encouraging. The second phase assessed five design variants of the prototype combustor, each variant achieving a progressive improvement in combustor performance. The operating conditions for this assessment were selected to represent a particular medium sized industrial gas turbine operating as part of an Air Blown Gasification Cycle (ABGC). The test conditions assessed therefore included the capability to operate the combustor using natural gas as a supplementary fuel, to suit one possible start-up procedure for the cycle. The paper presents a brief overview of the ABGC development initiative and discusses the general requirements for a gas turbine operating within such a cycle. In addition, it presents full combustor performance results for the second phase of turbine combustor development and discusses the rationale for the progressive design modifications made within that programme. The strategy for the further development of the combustor to burn low calorific value fuel gas with very low conversion of fuel-bound nitrogen to NO{sub x} is presented. (orig.) 6 refs.

  14. Upgrade of gas turbine cleaning technology

    Energy Technology Data Exchange (ETDEWEB)

    Asplund, P. [Gas Turbine Efficiency, Jarfalla (Sweden)

    2004-07-01

    Gas turbines used to be cleaned during times of engine shut down by spraying a jet of water into the compressor air intakes with a garden hose. Washing has become more sophisticated, with modern wash skids consisting of pumps, regulators, detergent tanks, rinsing water tanks, heaters, and wash cycle programs. High pressure wash systems were developed to improve both off-line and on-line cleaning of gas turbine compressors. The main feature of a high pressure system is its ability to use less liquid while minimizing risk for damage by erosion. A high pressure system was tested on the LM 2500 gas turbine at the Kvaerner Energy test facility at Agotnes, Norway. Both on-line washing and crank washing were tested. Engine performance was found to improve after washing. Laboratory tests have been validated by field experience with the high pressure system on North Sea platforms. The use of detergent can be eliminated with high pressure washing systems, thereby simplifying and reducing the cost of the washing procedure. The greatest advantage of pressure washing is that the interval for crank washes could be extended from 1500 hours to 4000 hours. 3 refs., 2 tabs., 9 figs.

  15. Flame Imaging of Gas-Turbine Relight

    DEFF Research Database (Denmark)

    Read, Robert; Rogerson, J.W.; Hochgreb, S.

    2010-01-01

    High-altitude relight inside a lean-direct-injection gas-turbine combustor is investigated experimentally by highspeed imaging. Realistic operating conditions are simulated in a ground-based test facility, with two conditions being studied: one inside and one outside the combustor ignition loop...... velocities of hot gas motion. Although the observed patterns of ignition failure are in broad agreement with results from laboratory-scale studies, other aspects of relight behavior are not reproduced in laboratory experiments employing simplified flow geometries and operating conditions. For example, when...

  16. Gas Path Sealing in Turbine Engines

    Science.gov (United States)

    Ludwig, L. P.

    1978-01-01

    A survey of gas path seals is presented with particular attention given to sealing clearance effects on engine component efficiency. The effects on compressor pressure ratio and stall margin are pointed out. Various case-rotor relative displacements, which affect gas path seal clearances, are identified. Forces produced by nonuniform sealing clearances and their effect on rotor stability are discussed qualitatively, and recent work on turbine-blade-tip sealing for high temperature is described. The need for active clearance control and for engine structural analysis is discussed. The functions of the internal-flow system and its seals are reviewed.

  17. Gas turbine applications in the drying industry

    Energy Technology Data Exchange (ETDEWEB)

    Tapper, R.C.

    2000-07-01

    The purpose of this report is to determine if it is feasible to utilize the hot exhaust gas discharged from gas turbines in direct applications. This report illustrates the technical feasibility and economic viability of using gas turbines in drying applications. The size of turbines in this investigation ranges from 2 MW to 10 MW. In addition, an implementation strategy has been developed to employ this new system. The method used to structure the scope of this undertaking is as follows: Step 1. Collecting information by contacting dryer manufacturer and companies drying different products. Information was also gathered by literature studies and the internet. Thomas register is a great tool when it comes to company and market searches. Step 2. Looking into if it is technically possible to use the exhaust gas directly into dryers. The parameters needed for these calculations were gathered in step 1, and some of the more important are temperature, mass flow, heat demand, and information about how the dryer works. The computer program Gatecycle is a great help when it comes to finding the right turbine for a dryer. Step 3. When it was obvious that it would work for some drying applications, the profitability was tested with the help of some spreadsheets. Step 4. The market was also evaluated as a last step. Market analysis was performed with the help of Porter's (Porter is one of the most famous strategy gurus) different models. The point of this is to find ways to be unique so that competitors will have a harder time copying the new system. It is shown in the report that for the right kind of projects, this new application for turbines is profitable. It is important to realize that this new system is not profitable for every drying plant. This is a general study with general input parameters. Every plant has its' own in-parameters and has to be evaluated individually. The most important factors determining if it is profitable or not are: Local electricity

  18. Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier

    Energy Technology Data Exchange (ETDEWEB)

    Wiebe, David J.; Charron, Richard C.; Morrison, Jay A.

    2016-10-18

    A gas turbine engine ducting arrangement (10), including: an annular chamber (14) configured to receive a plurality of discrete flows of combustion gases originating in respective can combustors and to deliver the discrete flows to a turbine inlet annulus, wherein the annular chamber includes an inner diameter (52) and an outer diameter (60); an outer diameter mounting arrangement (34) configured to permit relative radial movement and to prevent relative axial and circumferential movement between the outer diameter and a turbine vane carrier (20); and an inner diameter mounting arrangement (36) including a bracket (64) secured to the turbine vane carrier, wherein the bracket is configured to permit the inner diameter to move radially with the outer diameter and prevent axial deflection of the inner diameter with respect to the outer diameter.

  19. High temperature heat exchanger studies for applications to gas turbines

    Science.gov (United States)

    Min, June Kee; Jeong, Ji Hwan; Ha, Man Yeong; Kim, Kui Soon

    2009-12-01

    Growing demand for environmentally friendly aero gas-turbine engines with lower emissions and improved specific fuel consumption can be met by incorporating heat exchangers into gas turbines. Relevant researches in such areas as the design of a heat exchanger matrix, materials selection, manufacturing technology, and optimization by a variety of researchers have been reviewed in this paper. Based on results reported in previous studies, potential heat exchanger designs for an aero gas turbine recuperator, intercooler, and cooling-air cooler are suggested.

  20. Engineered Materials for Advanced Gas Turbine Engine Project

    Data.gov (United States)

    National Aeronautics and Space Administration — This project will develop innovative composite powders and composites that will surpass the properties of currently identified materials for advanced gas turbine...

  1. Variable geometry gas turbines for improving the part-load performance of marine combined cycles - Gas turbine performance

    DEFF Research Database (Denmark)

    Haglind, Fredrik

    2010-01-01

    The part-load performance of gas and steam turbine combined cycles intended for naval use is of great importance, and it is influenced by the gas turbine configuration and load control strategy. This paper is aimed at quantifying the effects of variable geometry on the gas turbine part......-load performance. Subsequently, in another paper, the effects of variable geometry on the part-load performance for combined cycles used for ship propulsion will be presented. Moreover, this paper is aimed at developing methodologies and deriving models for part-load simulations suitable for energy system analysis...... of various components within gas turbines. Two different gas turbine configurations are studied, a two-shaft aero-derivative configuration and a single-shaft industrial configuration. When both gas turbine configurations are running in part-load using fuel flow control, the results indicate better part...

  2. Gas sensing using porous materials for automotive applications.

    Science.gov (United States)

    Wales, Dominic J; Grand, Julien; Ting, Valeska P; Burke, Richard D; Edler, Karen J; Bowen, Chris R; Mintova, Svetlana; Burrows, Andrew D

    2015-07-01

    Improvements in the efficiency of combustion within a vehicle can lead to reductions in the emission of harmful pollutants and increased fuel efficiency. Gas sensors have a role to play in this process, since they can provide real time feedback to vehicular fuel and emissions management systems as well as reducing the discrepancy between emissions observed in factory tests and 'real world' scenarios. In this review we survey the current state-of-the-art in using porous materials for sensing the gases relevant to automotive emissions. Two broad classes of porous material - zeolites and metal-organic frameworks (MOFs) - are introduced, and their potential for gas sensing is discussed. The adsorptive, spectroscopic and electronic techniques for sensing gases using porous materials are summarised. Examples of the use of zeolites and MOFs in the sensing of water vapour, oxygen, NOx, carbon monoxide and carbon dioxide, hydrocarbons and volatile organic compounds, ammonia, hydrogen sulfide, sulfur dioxide and hydrogen are then detailed. Both types of porous material (zeolites and MOFs) reveal great promise for the fabrication of sensors for exhaust gases and vapours due to high selectivity and sensitivity. The size and shape selectivity of the zeolite and MOF materials are controlled by variation of pore dimensions, chemical composition (hydrophilicity/hydrophobicity), crystal size and orientation, thus enabling detection and differentiation between different gases and vapours. PMID:25982991

  3. Efficient, Low Pressure Ratio Propulsor for Gas Turbine Engines

    Science.gov (United States)

    Gallagher, Edward J. (Inventor); Monzon, Byron R. (Inventor)

    2015-01-01

    A gas turbine engine includes a spool, a turbine coupled to drive the spool, and a propulsor that is coupled to be driven by the turbine through the spool. A gear assembly is coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. The row includes no more than 20 of the propulsor blades.

  4. Feasibility of pulse combustion in micro gas turbines

    Science.gov (United States)

    Honkatukia, Juha; Saari, Esa; Knuuttila, Timo; Larjola, Jaakko; Backman, Jari

    2012-10-01

    In gas turbines, a fast decrease of efficiency appears when the output decreases; the efficiency of a large gas turbine (20...30 MW) is in the order of 40 %, the efficiency of a 30 kW gas turbine with a recuperator is in the order of 25 %, but the efficiency of a very small gas turbine (2...6 kW) in the order of 4...6 % (or 8...12 % with an optimal recuperator). This is mainly a result of the efficiency decrease in kinetic compressors, due to the Reynolds number effect. Losses in decelerating flow in a flow passage are sensitive to the Reynolds number effects. In contrary to the compression, the efficiency of expansion in turbines is not so sensitive to the Reynolds number; very small turbines are made with rather good efficiency because the flow acceleration stabilizes the boundary layer. This study presents a system where the kinetic compressor of a gas turbine is replaced with a pulse combustor. The combustor is filled with a combustible gas mixture, ignited, and the generated high pressure gas is expanded in the turbine. The process is repeated frequently, thus producing a pulsating flow to the turbine; or almost a uniform flow, if several parallel combustors are used and triggered alternately in a proper way. Almost all the compression work is made by the temperature increase from the combustion. This gas turbine type is investigated theoretically and its combustor also experimentally with the conclusion that in a 2 kW power size, the pulse flow gas turbine is not as attractive as expected due to the big size and weight of parallel combustors and due to the efficiency being in the order of 8 % to 10 %. However, in special applications having a very low power demand, below 1000 W, this solution has better properties when compared to the conventional gas turbine and it could be worth of a more detailed investigation.

  5. Turbine gas temperature measurement and control system

    Science.gov (United States)

    Webb, W. L.

    1973-01-01

    A fluidic Turbine Inlet Gas Temperature (TIGIT) Measurement and Control System was developed for use on a Pratt and Whitney Aircraft J58 engine. Based on engine operating requirements, criteria for high temperature materials selection, system design, and system performance were established. To minimize development and operational risk, the TIGT control system was designed to interface with an existing Exhaust Gas Temperature (EGT) Trim System and thereby modulate steady-state fuel flow to maintain a desired TIGT level. Extensive component and system testing was conducted including heated (2300F) vibration tests for the fluidic sensor and gas sampling probe, temperature and vibration tests on the system electronics, burner rig testing of the TIGT measurement system, and in excess of 100 hours of system testing on a J58 engine. (Modified author abstract)

  6. Gas turbine powerhouse the development of the power generation gas turbine at BBC - ABB - Alstom

    CERN Document Server

    Eckardt, Dietrich

    2014-01-01

    This book tells the story of the power generation gas turbine from the perspective of one of the leading companies in the field over a period of nearly 100 years, written by an engineer. Especially in times of imminent global economic crises it appears to be worthwhile to reflect on real economic values based on engineering ingenuity and enduring management of technological leadership.

  7. GAS TURBINE REHEAT USING IN SITU COMBUSTION

    Energy Technology Data Exchange (ETDEWEB)

    D.M. Bachovchin; T.E. Lippert; R.A. Newby P.G.A. Cizmas

    2004-05-17

    In situ reheat is an alternative to traditional gas turbine reheat design in which fuel is fed through airfoils rather than in a bulky discrete combustor separating HP and LP turbines. The goals are to achieve increased power output and/or efficiency without higher emissions. In this program the scientific basis for achieving burnout with low emissions has been explored. In Task 1, Blade Path Aerodynamics, design options were evaluated using CFD in terms of burnout, increase of power output, and possible hot streaking. It was concluded that Vane 1 injection in a conventional 4-stage turbine was preferred. Vane 2 injection after vane 1 injection was possible, but of marginal benefit. In Task 2, Combustion and Emissions, detailed chemical kinetics modeling, validated by Task 3, Sub-Scale Testing, experiments, resulted in the same conclusions, with the added conclusion that some increase in emissions was expected. In Task 4, Conceptual Design and Development Plan, Siemens Westinghouse power cycle analysis software was used to evaluate alternative in situ reheat design options. Only single stage reheat, via vane 1, was found to have merit, consistent with prior Tasks. Unifying the results of all the tasks, a conceptual design for single stage reheat utilizing 24 holes, 1.8 mm diameter, at the trailing edge of vane 1 is presented. A development plan is presented.

  8. Squeeze Film Damping for Aircraft Gas Turbines

    Directory of Open Access Journals (Sweden)

    R. W. Shende

    1988-10-01

    Full Text Available Modern aircraft gas turbine engines depend heavily on squeeze film damper supports at the bearings for abatement of vibrations caused by a number of probable excitation sources. This design ultimately results in light-weight construction together with higher efficiency and reliability of engines. Many investigations have been reported during past two decades concerning the functioning of the squeeze film damper, which is simple in construction yet complex in behaviour with its non-linearity and multiplicity of variables. These are reviewed in this article to throw light on the considerations involved in the design of rotor-bearing-casing systems incorporating squeeze film dampers.

  9. Gas Turbine Engine Inlet Wall Design

    Science.gov (United States)

    Florea, Razvan Virgil (Inventor); Matalanis, Claude G. (Inventor); Stucky, Mark B. (Inventor)

    2016-01-01

    A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than the first ellipse. The inlet duct has a surface defining the second ellipse which curves away from the first ellipse, such that the second ellipse is larger at an intermediate location. The second ellipse is even larger at a downstream end of the inlet duct leading into a fan.

  10. Durability Challenges for Next Generation of Gas Turbine Engine Materials

    Science.gov (United States)

    Misra, Ajay K.

    2012-01-01

    Aggressive fuel burn and carbon dioxide emission reduction goals for future gas turbine engines will require higher overall pressure ratio, and a significant increase in turbine inlet temperature. These goals can be achieved by increasing temperature capability of turbine engine hot section materials and decreasing weight of fan section of the engine. NASA is currently developing several advanced hot section materials for increasing temperature capability of future gas turbine engines. The materials of interest include ceramic matrix composites with 1482 - 1648 C temperature capability, advanced disk alloys with 815 C capability, and low conductivity thermal barrier coatings with erosion resistance. The presentation will provide an overview of durability challenges with emphasis on the environmental factors affecting durability for the next generation of gas turbine engine materials. The environmental factors include gaseous atmosphere in gas turbine engines, molten salt and glass deposits from airborne contaminants, impact from foreign object damage, and erosion from ingestion of small particles.

  11. Gas turbine heat transfer and cooling technology

    CERN Document Server

    Han, Je-Chin; Ekkad, Srinath

    2012-01-01

    FundamentalsNeed for Turbine Blade CoolingTurbine-Cooling TechnologyTurbine Heat Transfer and Cooling IssuesStructure of the BookReview Articles and Book Chapters on Turbine Cooling and Heat TransferNew Information from 2000 to 2010ReferencesTurbine Heat TransferIntroductionTurbine-Stage Heat TransferCascade Vane Heat-Transfer ExperimentsCascade Blade Heat TransferAirfoil Endwall Heat TransferTurbine Rotor Blade Tip Heat TransferLeading-Edge Region Heat TransferFlat-Surface Heat TransferNew Information from 2000 to 20102.10 ClosureReferencesTurbine Film CoolingIntroductionFilm Cooling on Rotat

  12. Thermodynamic analysis of turbine blade cooling on the performance of gas turbine cycle

    International Nuclear Information System (INIS)

    Turbine inlet temperature strongly affects gas turbine performance. Today blade cooling technologies facilitate the use of higher inlet temperatures. Of course blade cooling causes some thermodynamic penalties that destroys to some extent the positive effect of higher inlet temperatures. This research aims to model and evaluate the performance of gas turbine cycle with air cooled turbine. In this study internal and transpiration cooling methods has been investigated and the penalties as the result of gas flow friction, cooling air throttling, mixing of cooling air flow with hot gas flow, and irreversible heat transfer have been considered. In addition, it is attempted to consider any factor influencing actual conditions of system in the analysis. It is concluded that penalties due to blade cooling decrease as permissible temperature of the blade surface increases. Also it is observed that transpiration method leads to better performance of gas turbine comparing to internal cooling method

  13. Tilting pad gas bearing design for micro gas turbines

    Science.gov (United States)

    Nabuurs, M. J. H. W.; Al-Bender, F.; Reynaerts, D.

    2013-12-01

    This paper presents the results of a dynamic stability investigation of a micro gas turbine supported by two flexible tilting pad bearings. The pad flexibility allows centrifugal and thermal shaft growth of the rotor but can also introduce undesirable rotor instabilities. An eigenvalue analysis on the linearised rotor-bearing dynamics is performed to estimate the required pad stiffness and damping for stability. Results of the eigenvalue analysis are evaluated by fully nonlinear orbit simulations.

  14. Development of Compressor for Ultra Micro Gas Turbine

    Institute of Scientific and Technical Information of China (English)

    Shimpei MIZUKI

    2007-01-01

    The major problems for the development of an ultra micro gas turbine system were discussed briefly from the stand point of the internal flow and the performance characteristics. Following to these, the development of ultra micro centrifugal compression systems for the ultra micro gas turbine is explained with the design and the manufacturing processes. The measured results of ultra micro centrifugal compressors are shown.

  15. 46 CFR 58.10-15 - Gas turbine installations.

    Science.gov (United States)

    2010-10-01

    ... reference, see 46 CFR 58.03-1). (b) Materials. The materials used for gas turbine installations shall have...) Regenerator or recuperator. (3) Casing or piping conveying the gas from the combustion device to the...

  16. Mathematical modeling of gas turbine cooled elements

    Energy Technology Data Exchange (ETDEWEB)

    Pashayev, A.; Askerov, D.; Sadiqov, R.; Samedov, A. [Academy of Aviation, Baku (Azerbaijan). Dept. of Mathematical Modeling and Design of Gas Turbine Engines

    2007-07-01

    The profile section of a gas turbine blade with convective cooling was modelled. Converging quadrature processes were used to determine the stationary and quasi-stationary temperature field of the profile part of the blade. Profiles were visualized using the least squares method along with automatic conjecture, device spline, smooth replenishment, and neural nets. Heat exchange boundary conditions were characterized using the finite difference method; finite element analysis (FEA); the Monte Carlo method; and the boundary integral equations method (BIEM). Boundary conditions included the heat quantity assigned by convection of the cooler transmitted by heat conduction of the blade material to the surface of cooling channels. Errors were investigated using a quadratures method and Tikhonov regularization. A Kirchhoff permutation was used to linearize tasks. The developed equation was then transformed into a Laplace equation. The model was then compared with experimental investigations to validate heat and hydraulic characteristics, as well as the temperature field of the blade cross section. It was concluded that the model can be used to assess the reliability of gas turbine engine designs. 3 refs., 1 fig.

  17. Economics and Performance Forecast of Gas Turbine Combined Cycle

    Institute of Scientific and Technical Information of China (English)

    ZHANG Xiaotao; SUGISHITA Hideaki; NI Weidou; LI Zheng

    2005-01-01

    Forecasts of the economics and performance of gas turbine combined cycle (GTCC) with various types of gas turbines will help power plant designers to select the best type of gas turbine for future Chinese powerplants. The cost and performance of various designs were estimated using the commercial software GT PRO. Improved GTCC output will increase the system efficiency which may induce total investment and will certainly increase the cumulative cash which then will induce the cost and the payback period. The relative annual fuel output increases almost in proportion to the relative GTCC output. China should select the gas turbine that provides the most economical output according to its specific conditions. The analysis shows that a GTCC power plant with a medium-sized 100 to 200 MW output gas turbine is the most suitable for Chinese investors.

  18. Analysis of gas turbine integrated cogeneration plant: Process integration approach

    International Nuclear Information System (INIS)

    Cogeneration is defined as generation of two forms of energy viz. heat and work using single primary fuel. Cogeneration or combined heat and power (CHP) is important in improving energy efficiency of the overall plant and in reducing environmental pollution. A methodology, based on pinch analysis, is proposed in this paper to integrate gas turbine and regenerator with a process plant to minimize fuel consumption. Thermodynamic analysis of gas turbine integrated CHP plant is presented on gas turbine pressure ratio versus power to heat ratio diagram. On this novel diagram, limits of integration are identified and various regions of integration are represented. Additionally, contour plots of energy utilization factors and fuel energy saving ratios are represented on this diagram for optimal integration of gas turbine with a process plant. It is interesting to note that though the contour plots of energy utilization factors and fuel energy saving ratios differ significantly, loci of the maximal energy utilization factor and the maximal fuel energy saving ratio are identical. Optimum sizing of gas turbine integrated cogeneration plant for grassroots design and retrofitting are performed based on these diagrams. - Highlights: • Methodology for direct integration of gas turbine, regenerator, and process plant. • Integrated system analysis plotted on turbine pressure ratio vs. power to heat ratio. • Regions of integration are identified on this new diagram. • Variations of energy utilization factor and fuel energy saving ratio are indicated. • Optimal sizing of integrated gas turbine for retrofitting and grassroots design

  19. Update on DOE Advanced IGCC/H2 Gas Turbine

    Science.gov (United States)

    Chupp, Ray

    2009-01-01

    Cooling Flow Reduction: a) Focus on improving turbine hot gas path part cooling efficiency. b) Applicable to current metallic turbine components and synergistic with advanced materials. c) Address challenges of IGCC/hydrogen fuel environment (for example, possible cooling hole plugging). Leakage Flow Reduction: a) Focus on decreasing turbine parasitic leakages, i.e. between static-to-static, static-to-rotating turbine parts. b) Develop improved seal designs in a variety of important areas. Purge Flow Reduction: a) Focus on decreasing required flows to keep rotor disk cavities within temperature limits. b) Develop improved sealing at the cavity rims and modified flow geometries to minimize hot gas ingestion and aerodynamic impact.

  20. Miniature Gas-Turbine Power Generator

    Science.gov (United States)

    Wiberg, Dean; Vargo, Stephen; White, Victor; Shcheglov, Kirill

    2003-01-01

    A proposed microelectromechanical system (MEMS) containing a closed- Brayton-cycle turbine would serve as a prototype of electric-power generators for special applications in which high energy densities are required and in which, heretofore, batteries have been used. The system would have a volume of about 6 cm3 and would operate with a thermal efficiency >30 percent, generating up to 50 W of electrical power. The energy density of the proposed system would be about 10 times that of the best battery-based systems now available, and, as such, would be comparable to that of a fuel cell. The working gas for the turbine would be Xe containing small quantities of CO2, O2, and H2O as gaseous lubricants. The gas would be contained in an enclosed circulation system, within which the pressure would typically range between 5 and 50 atm (between 0.5 and 5 MPa). The heat for the Brayton cycle could be supplied by any of a number of sources, including a solar concentrator or a combustor burning a hydrocarbon or other fuel. The system would include novel heat-transfer and heat-management components. The turbine would be connected to an electric power generator/starter motor. The system would include a main rotor shaft with gas bearings; the bearing surfaces would be made of a ceramic material coated with nanocrystalline diamond. The shaft could withstand speed of 400,000 rpm or perhaps more, with bearing-wear rates less than 10(exp -)4 those of silicon bearings and 0.05 to 0.1 those of SiC bearings, and with a coefficient of friction about 0.1 that of Si or SiC bearings. The components of the system would be fabricated by a combination of (1) three-dimensional xray lithography and (2) highly precise injection molding of diamond-compatible metals and ceramic materials. The materials and fabrication techniques would be suitable for mass production. The disadvantages of the proposed system are that unlike a battery-based system, it could generate a perceptible amount of sound, and

  1. Blade Deterioration in a Gas Turbine Engine

    Directory of Open Access Journals (Sweden)

    W. Tabakoff

    1998-01-01

    Full Text Available A study has been conducted to predict blade erosion of gas turbine engines. The blade material erosion model is based on three dimensional particle trajectory simulation in the three-dimensional turbine flow field. The trajectories provide the special distribution of the particle impact parameters over the blade surface. A semi-empirical erosion model, derived from erosion tests of material samples at different particulate flow conditions, is used in the prediction of blade surface erosion based on the trajectory impact data. To improve the blade erosion resistance and to decrease the blade deterioration, the blades must be coated. For this purpose, an experimental study was conducted to investigate the behavior of rhodium platinum aluminide coating exposed to erosion by fly ash particles. New protective coatings are developed for erosion and thermal barrier. Chemical vapor deposition technique (CVD was used to apply the ceramic TiC coatings on INCO 718 and stainless steel 410. The erosive wear of the coated samples was investigated experimentally by exposing them to particle laden flow at velocities from 180 to 305m/s and temperatures from ambient to 538°C in a specially designed erosion wind tunnel. Both materials (INCO 718 and stainless steel 410 coated with CVD TiC showed one order of magnitude less erosion rate compared to some commercial coatings on the same substrates.

  2. Gas Turbine Blade Damper Optimization Methodology

    Directory of Open Access Journals (Sweden)

    R. K. Giridhar

    2012-01-01

    Full Text Available The friction damping concept is widely used to reduce resonance stresses in gas turbines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. This paper presents a methodology that combines three essential phases of friction damping optimization in turbo-machinery. The first phase is to develop an analytical model of blade damper system. The second phase is experimentation and model tuning necessary for response studies while the third phase is evaluating damper performance. The reduced model of blade is developed corresponding to the mode under investigation incorporating the friction damper then the simulations were carried out to arrive at an optimum design point of the damper. Bench tests were carried out in two phases. Phase-1 deals with characterization of the blade dynamically and the phase-2 deals with finding optimal normal load at which the blade resonating response is minimal for a given excitation. The test results are discussed, and are corroborated with simulated results, are in good agreement.

  3. Modular Coating for Flexible Gas Turbine Operation

    Science.gov (United States)

    Zimmermann, J. R. A.; Schab, J. C.; Stankowski, A.; Grasso, P. D.; Olliges, S.; Leyens, C.

    2016-01-01

    In heavy duty gas turbines, the loading boundary conditions of MCrAlY systems are differently weighted for different operation regimes as well as for each turbine component or even in individual part locations. For an overall optimized component protection it is therefore of interest to produce coatings with flexible and individually tailored properties. In this context, ALSTOM developed an Advanced Modular Coating Technology (AMCOTEC™), which is based on several powder constituents, each providing specific properties to the final coating, in combination with a new application method, allowing in-situ compositional changes. With this approach, coating properties, such as oxidation, corrosion, and cyclic lifetime, etc., can be modularly adjusted for individual component types and areas. For demonstration purpose, a MCrAlY coating with modular ductility increase was produced using the AMCOTEC™ methodology. The method was proven to be cost effective and a highly flexible solution, enabling fast compositional screening. A calculation method for final coating composition was defined and validated. The modular addition of ductility agent enabled increasing the coating ductility with up to factor 3 with only slight decrease of oxidation resistance. An optimum composition with respect to ductility is reached with addition of 20 wt.% of ductility agent.

  4. Computational thermo-fluid dynamics contributions to advanced gas turbine engine design

    Science.gov (United States)

    Graham, R. W.; Adamczyk, J. J.; Rohlik, H. E.

    1985-01-01

    The design practices for the gas turbine are traced throughout history with particular emphasis on the calculational or analytical methods. Three principal components of the gas turbine engine will be considered: namely, the compressor, the combustor and the turbine.

  5. Natural gas turbine topping for the iris reactor

    Energy Technology Data Exchange (ETDEWEB)

    Oriani, L.; Lombardi, C. [Politecnico di Milano, Milan (Italy); Paramonov, D. [Westinghouse Electric Corp., LLC, Pittsburgh, PA (United States)

    2001-07-01

    Nuclear power plant designs are typically characterized by high capital and low fuel costs, while the opposite is true for fossil power generation including the natural gas-fired gas turbine combined cycle currently favored by many utilities worldwide. This paper examines potential advantages of combining nuclear and fossil (natural gas) generation options in a single plant. Technical and economic feasibility and attractiveness of a gas turbine - nuclear reactor combined cycle where gas turbine exhaust is used to superheat saturated steam produced by a low power light water reactor are examined. It is shown that in a certain range of fuel and capital costs of nuclear and fossil options, the proposed cycle offers an immediate economic advantage over stand-alone plants resulting from higher efficiency of the nuclear plant. Additionally, the gas turbine topping will result in higher fuel flexibility without the economic penalty typically associated with nuclear power. (author)

  6. Natural gas turbine topping for the iris reactor

    International Nuclear Information System (INIS)

    Nuclear power plant designs are typically characterized by high capital and low fuel costs, while the opposite is true for fossil power generation including the natural gas-fired gas turbine combined cycle currently favored by many utilities worldwide. This paper examines potential advantages of combining nuclear and fossil (natural gas) generation options in a single plant. Technical and economic feasibility and attractiveness of a gas turbine - nuclear reactor combined cycle where gas turbine exhaust is used to superheat saturated steam produced by a low power light water reactor are examined. It is shown that in a certain range of fuel and capital costs of nuclear and fossil options, the proposed cycle offers an immediate economic advantage over stand-alone plants resulting from higher efficiency of the nuclear plant. Additionally, the gas turbine topping will result in higher fuel flexibility without the economic penalty typically associated with nuclear power. (author)

  7. Detonation wave augmentation of gas turbines

    Science.gov (United States)

    Wortman, A.

    1984-01-01

    The results of a feasibility study that examined the effects of using detonation waves to augment the performance of gas turbines are reported. The central ideas were to reduce compressor requirements and to maintain high performance in jet engines. Gasdynamic equations were used to model the flows associated with shock waves generated by the detonation of fuel in detonator tubes. Shock wave attenuation to the level of Mach waves was found possible, thus eliminating interference with the compressor and the necessity of valves and seals. A preliminary parametric study of the performance of a compressor working at a 4:1 ratio in a conceptual design of a detonation wave augmented jet engine in subsonic flight indicated a clear superiority over conventional designs in terms of fuel efficiency and thrust.

  8. Storage peak gas-turbine power unit

    Science.gov (United States)

    Tsinkotski, B.

    1980-01-01

    A storage gas-turbine power plant using a two-cylinder compressor with intermediate cooling is studied. On the basis of measured characteristics of a .25 Mw compressor computer calculations of the parameters of the loading process of a constant capacity storage unit (05.3 million cu m) were carried out. The required compressor power as a function of time with and without final cooling was computed. Parameters of maximum loading and discharging of the storage unit were calculated, and it was found that for the complete loading of a fully unloaded storage unit, a capacity of 1 to 1.5 million cubic meters is required, depending on the final cooling.

  9. Gas--steam turbine combined cycle power plants

    Energy Technology Data Exchange (ETDEWEB)

    Christian, J.E.

    1978-10-01

    The purpose of this technology evaluation is to provide performance and cost characteristics of the combined gas and steam turbine, cycle system applied to an Integrated Community Energy System (ICES). To date, most of the applications of combined cycles have been for electric power generation only. The basic gas--steam turbine combined cycle consists of: (1) a gas turbine-generator set, (2) a waste-heat recovery boiler in the gas turbine exhaust stream designed to produce steam, and (3) a steam turbine acting as a bottoming cycle. Because modification of the standard steam portion of the combined cycle would be necessary to recover waste heat at a useful temperature (> 212/sup 0/F), some sacrifice in the potential conversion efficiency is necessary at this temperature. The total energy efficiency ((electric power + recovered waste heat) divided by input fuel energy) varies from about 65 to 73% at full load to 34 to 49% at 20% rated electric power output. Two major factors that must be considered when installing a gas--steam turbine combines cycle are: the realiability of the gas turbine portion of the cycle, and the availability of liquid and gas fuels or the feasibility of hooking up with a coal gasification/liquefaction process.

  10. Off-Design Performance Prediction of Gas Turbines without the use of Compressor or Turbine Characteristics

    Science.gov (United States)

    Suraweera, Janitha Kanishka

    A new method of predicting gas turbine off-design performance is presented. This method, referred to as the core control method, is based on the idea that performance across a gas turbine depends on a single parameter that controls the energy input to the said gas turbine. It is shown that only the design-point performance of a gas turbine is needed to predict its off-design performance, and that neither compressor nor turbine characteristics are required. A thermodynamic model is developed for predicting the off-design performance of a single-spool turbojet and a two-spool gas generator with a free power turbine. This model is further developed to simulate the effects of handling bleed schedules, performance limiters and performance deterioration. The core control method is then used to predict the off-design performance of a Rolls-Royce Viper Mark 521 as a proof-of-concept, after which, the new and deteriorated off-design performance of three Rolls-Royce RB211-24GT gas turbines is predicted. In addition to the discussions on the involved theories and the performance predictions, the process by which the deteriorated RB211-24GT performance data was analyzed, and the sources and propagation of measurement uncertainties are also discussed.

  11. Thermodynamic Analysis of Supplementary-Fired Gas Turbine Cycles

    DEFF Research Database (Denmark)

    Elmegaard, Brian; Henriksen, Ulrik Birk; Qvale, Einar Bjørn

    2002-01-01

    demonstration of a two-stage gasification process through construction of several plants.} A preliminary analysis of the ideal recuperated Brayton cycle shows that for this cycle any supplementary firing will have a marginal efficiency of unity per extra unit of fuel. The same result is obtained...... for the indirectly fired gas turbine (IFGT) and for the supplementary-fired IFGT. Both results show that the combination of external firing and internal firing have the potential of reducing or solving some problems with the use of biomass both in the recuperated and the indirectly fired gas turbine: The former...... to be independent of temperature ratio and lower than for the recuperated gas turbine....

  12. Diagnostics of gas turbines based on changes in thermodynamics parameters

    Directory of Open Access Journals (Sweden)

    Hocko Marián

    2016-01-01

    Full Text Available This article is focused on solving the problems of determining the true state of gas turbine based on measured changes in thermodynamic parameters. Dependence between the real individual parts for gas turbines and changing the thermodynamic parameters were experimentally verified and confirmed on a small jet engine MPM-20 in the laboratory of the Department of Aviation Engineering at Technical University in Košice. The results of experiments confirm that the wear and tear of basic parts for gas turbines (turbo-compressor engines to effect the change of thermodynamic parameters of the engine.

  13. Diagnostics of gas turbines based on changes in thermodynamics parameters

    Science.gov (United States)

    Hocko, Marián; Klimko, Marek

    2016-03-01

    This article is focused on solving the problems of determining the true state of gas turbine based on measured changes in thermodynamic parameters. Dependence between the real individual parts for gas turbines and changing the thermodynamic parameters were experimentally verified and confirmed on a small jet engine MPM-20 in the laboratory of the Department of Aviation Engineering at Technical University in Košice. The results of experiments confirm that the wear and tear of basic parts for gas turbines (turbo-compressor engines) to effect the change of thermodynamic parameters of the engine.

  14. Ceramic stationary gas turbine development. Final report, Phase 1

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1994-09-01

    This report summarizes work performed by Solar Turbines Inc. and its subcontractors during the period September 25, 1992 through April 30, 1993. The objective of the work is to improve the performance of stationary gas turbines in cogeneration through implementation of selected ceramic components.

  15. Hydrogen turbines for space power systems: A simplified axial flow gas turbine model

    Science.gov (United States)

    Hudson, Steven L.

    1988-01-01

    Hydrogen cooled, turbine powered space weapon systems require a relatively simple, but reasonably accurate hydrogen gas expansion turbine model. Such a simplified turbine model would require little computational time and allow incorporation into system level computer programs while providing reasonably accurate volume/mass estimates. This model would then allow optimization studies to be performed on multiparameter space power systems and provide improved turbine mass and size estimates for the various operating conditions (when compared to empirical and power law approaches). An axial flow gas expansion turbine model was developed for these reasons and is in use as a comparative bench mark in space power system studies at Sandia. The turbine model is based on fluid dynamic, thermodynamic, and material strength considerations, but is considered simplified because it does not account for design details such as boundary layer effects, shock waves, turbulence, stress concentrations, and seal leakage. Although the basic principles presented here apply to any gas or vapor axial flow turbine, hydrogen turbines are discussed because of their immense importance on space burst power platforms.

  16. Thermodynamic Analysis of Supplementary-Fired Gas Turbine Cycles

    DEFF Research Database (Denmark)

    Elmegaard, Brian; Henriksen, Ulrik Birk; Qvale, Einar Bjørn

    2003-01-01

    for the indirectly fired gas turbine (IFGT) and for the supplementary-fired IFGT. These results show that the combination of external firing and internal firing have the potential of reducing or solving some problems associated with the use of biomass both in the recuperated and the indirectly fired gas turbine......This paper presents an analysis of the possibilities for improving the efficiency of an indi-rectly biomass-fired gas turbine (IBFGT) by supplementary direct gas-firing. The supple-mentary firing may be based on natural gas, biogas or pyrolysis gas. Intuitively, sup-plementary firing is expected...... to result in a high marginal efficiency. The paper shows that depending on the application, this is not always the case. The interest in this cycle arises from a recent demonstration of the feasibility of a two-stage gasification process through construction of several plants. The gas from this process...

  17. The gas turbine: Present technology and future developments

    International Nuclear Information System (INIS)

    The gas turbine is the most widely used prime mover all over the world for either power generation or mechanical drive applications. The above fact is due to the recent great improvements that have been done especially in terms of efficiency, availability and reliability. The future for gas turbine technological development looks very promising. In fact, although tremendous growth has already taken place, there is still the potential for dramatic improvements in performance. Compared with the competitive prime movers (conventional steam power plants and reciprocating piston engines) the gas turbine technology is younger and still following a strong growth curve. The coming decades will witness the continued increasing in turbine inlet temperature, the development of new materials and refrigeration systems and the commercialization of inter cooled system and steam cooled turbines. With the very soon introduction of the G and H technology, expected single and combined cycle efficiencies for heavy duty machines are respectively 40% and 60%, while maintaining 'single digit' levels in pollutant emissions. In this report are given wide information on gas turbine present technology (Thermodynamics, features, design, performances, emission control, applications) and are discussed the main lines for the future developments. Finally are presented the research and technological development activities on gas turbine of Italian National Agency for new Technology Energy and the Environment Energy Department

  18. Humid Air Turbine as a Primary Link PRIVATE of a Conventional Gas Turbine Set

    Directory of Open Access Journals (Sweden)

    Jan T. Szargut

    2002-06-01

    Full Text Available The effectiveness of the primary link of a conventional gas turbine set has been expressed by means of the incremental energy efficiency, defined as the ratio of the attained increase of power to the increase of chemical energy consumption. The calculations performed for the humid air turbine (HAT applied as a primary link indicate a high effectiveness of the utilization of the additionally consumed fuel. The compression ratio in both parts of the considered gas turbine set has been optimized in order to attain maximum energy efficiency.

  19. Application of LES in the study of inlet flow field in marine gas turbine

    Institute of Scientific and Technical Information of China (English)

    SHI Bao-long; SUN Hai-ou; SUN Tao; HU Yan-yong

    2005-01-01

    The structure and aerodynamics performance of gas turbine inlet system is an important part of technology of gas turbine installed on naval vessels. The design and numerical simulations of gas turbine inlet system are conducted and reliable foundation for design and manufacture of marine gas turbine inlet system of high performance is provided. Numerical simulations and experiments of two inlet system models of gas turbine are conducted with satisfactory results and are of significance to the actual application of the inlet system.

  20. Reflection error correction of gas turbine blade temperature

    Science.gov (United States)

    Kipngetich, Ketui Daniel; Feng, Chi; Gao, Shan

    2016-03-01

    Accurate measurement of gas turbine blades' temperature is one of the greatest challenges encountered in gas turbine temperature measurements. Within an enclosed gas turbine environment with surfaces of varying temperature and low emissivities, a new challenge is introduced into the use of radiation thermometers due to the problem of reflection error. A method for correcting this error has been proposed and demonstrated in this work through computer simulation and experiment. The method assumed that emissivities of all surfaces exchanging thermal radiation are known. Simulations were carried out considering targets with low and high emissivities of 0.3 and 0.8 respectively while experimental measurements were carried out on blades with emissivity of 0.76. Simulated results showed possibility of achieving error less than 1% while experimental result corrected the error to 1.1%. It was thus concluded that the method is appropriate for correcting reflection error commonly encountered in temperature measurement of gas turbine blades.

  1. Gas turbines: gas cleaning requirements for biomass-fired systems

    Directory of Open Access Journals (Sweden)

    Oakey John

    2004-01-01

    Full Text Available Increased interest in the development of renewable energy technologies has been hencouraged by the introduction of legislative measures in Europe to reduce CO2 emissions from power generation in response to the potential threat of global warming. Of these technologies, biomass-firing represents a high priority because of the modest risk involved and the availability of waste biomass in many countries. Options based on farmed biomass are also under development. This paper reviews the challenges facing these technologies if they are to be cost competitive while delivering the supposed environmental benefits. In particular, it focuses on the use of biomass in gasification-based systems using gas turbines to deliver increased efficiencies. Results from recent studies in a European programme are presented. For these technologies to be successful, an optimal balance has to be achieved between the high cost of cleaning fuel gases, the reliability of the gas turbine and the fuel flexibility of the overall system. Such optimisation is necessary on a case-by-case basis, as local considerations can play a significant part.

  2. Intercooler flow path for gas turbines: CFD design and experiments

    Energy Technology Data Exchange (ETDEWEB)

    Agrawal, A.K.; Gollahalli, S.R.; Carter, F.L. [Univ. of Oklahoma, Norman, OK (United States)] [and others

    1995-10-01

    The Advanced Turbine Systems (ATS) program was created by the U.S. Department of Energy to develop ultra-high efficiency, environmentally superior, and cost competitive gas turbine systems for generating electricity. Intercooling or cooling of air between compressor stages is a feature under consideration in advanced cycles for the ATS. Intercooling entails cooling of air between the low pressure (LP) and high pressure (BP) compressor sections of the gas turbine. Lower air temperature entering the HP compressor decreases the air volume flow rate and hence, the compression work. Intercooling also lowers temperature at the HP discharge, thus allowing for more effective use of cooling air in the hot gas flow path. The thermodynamic analyses of gas turbine cycles with modifications such as intercooling, recuperating, and reheating have shown that intercooling is important to achieving high efficiency gas turbines. The gas turbine industry has considerable interest in adopting intercooling to advanced gas turbines of different capacities. This observation is reinforced by the US Navys Intercooled-Recuperative (ICR) gas turbine development program to power the surface ships. In an intercooler system, the air exiting the LP compressor must be decelerated to provide the necessary residence time in the heat exchanger. The cooler air must subsequently be accelerated towards the inlet of the HP compressor. The circumferential flow nonuniformities inevitably introduced by the heat exchanger, if not isolated, could lead to rotating stall in the compressors, and reduce the overall system performance and efficiency. Also, the pressure losses in the intercooler flow path adversely affect the system efficiency and hence, must be minimized. Thus, implementing intercooling requires fluid dynamically efficient flow path with minimum flow nonuniformities and consequent pressure losses.

  3. Creep-Fatigue Interactions of Gas Turbine Materials

    OpenAIRE

    Tarun Goswami

    1988-01-01

    The military aircraft gas turbine engines are often required to undergo a complex set of.operating conditions where the load varies considerably with respect to time. The temperature range for performing such requirements also increases as the thrust increases.The modern design of gas turbine demands very high thrust-to-weight ratio. In order to achieve this, the design is limited in the low cycle regime. The low cycle regime necessarily has the plasticity effect because of fatigue and inelas...

  4. Note: thermal imaging enhancement algorithm for gas turbine aerothermal characterization.

    Science.gov (United States)

    Beer, S K; Lawson, S A

    2013-08-01

    An algorithm was developed to convert radiation intensity images acquired using a black and white CCD camera to thermal images without requiring knowledge of incident background radiation. This unique infrared (IR) thermography method was developed to determine aerothermal characteristics of advanced cooling concepts for gas turbine cooling application. Compared to IR imaging systems traditionally used for gas turbine temperature monitoring, the system developed for the current study is relatively inexpensive and does not require calibration with surface mounted thermocouples. PMID:24007128

  5. Fluid and structural measurements to advance gas turbine technology

    Science.gov (United States)

    Hartmann, M. J.

    1980-01-01

    In the present paper, the current status of fluid and structural measurements is reviewed, and some potential improvements in gas turbine machinery, directly associated with the new measuring capability are discussed. Some considerations concerning the impact of the new capability on the methods and approaches that will be used in the further development of advanced technology, in general, and to aeropropulsion gas turbine machinery, in particular, are presented.

  6. Availability Analysis of Gas Turbines Used in Power Plants

    OpenAIRE

    Gilberto Francisco Martha de Souza; Fernando Jesus Guevara Carazas

    2009-01-01

    The availability of a complex system, such as a gas turbine, is strongly associated with its parts reliability and maintenance policy. That policy not only has influence on the parts’ repair time but also on the parts’ reliability affecting the system degradation and availability. This study presents a method for reliability and availability evaluation of gas turbines installed in an electric power station. The method is based on system reliability concepts, such as functi...

  7. Availability Analysis of Gas Turbines Used in Power Plants

    OpenAIRE

    de Souza, Gilberto Francisco Martha; Carazas, Fernando Jesus Guevara

    2009-01-01

    The availability of a complex system, such as a gas turbine, is strongly associated with its parts reliability and maintenance policy. That policy not only has influence on the parts’ repair time but also on the parts’ reliability affecting the system degradation and availability. This study presents a method for reliability and availability evaluation of gas turbines installed in an electric power station. The method is based on system reliability concepts, such as functional tre...

  8. Note: thermal imaging enhancement algorithm for gas turbine aerothermal characterization.

    Science.gov (United States)

    Beer, S K; Lawson, S A

    2013-08-01

    An algorithm was developed to convert radiation intensity images acquired using a black and white CCD camera to thermal images without requiring knowledge of incident background radiation. This unique infrared (IR) thermography method was developed to determine aerothermal characteristics of advanced cooling concepts for gas turbine cooling application. Compared to IR imaging systems traditionally used for gas turbine temperature monitoring, the system developed for the current study is relatively inexpensive and does not require calibration with surface mounted thermocouples.

  9. Flashback mechanisms in lean premixed gas turbine combustion

    CERN Document Server

    Benim, Ali Cemal

    2014-01-01

    Blending fuels with hydrogen offers the potential to reduce NOx and CO2 emissions in gas turbines, but doing so introduces potential new problems such as flashback.  Flashback can lead to thermal overload and destruction of hardware in the turbine engine, with potentially expensive consequences. The little research on flashback that is available is fragmented. Flashback Mechanisms in Lean Premixed Gas Turbine Combustion by Ali Cemal Benim will address not only the overall issue of the flashback phenomenon, but also the issue of fragmented and incomplete research.Presents a coherent review of f

  10. Gas turbine control for islanding operation of distribution systems

    DEFF Research Database (Denmark)

    Mahat, Pukar; Chen, Zhe; Bak-Jensen, Birgitte

    2009-01-01

    Danish distribution systems are characterized by a significant penetration of small gas turbine generators (GTGs) and fixed speed wind turbine generators (WTGs). Island operation of these distribution systems are becoming a viable option for economical and technical reasons. However, stabilizing...... frequency in an islanded system is one of the major challenges. This paper presents three different gas turbine governors for possible operation of distribution systems in an islanding mode. Simulation results are presented to show the performance of these governors in grid connected and islanding mode....

  11. High-temperature turbine technology program. Turbine subsystem design report: Low-Btu gas

    Energy Technology Data Exchange (ETDEWEB)

    Horner, M.W.

    1980-12-01

    The objective of the US Department of Energy High-Temperature Turbine Technology (DOE-HTTT) program is to bring to technology readiness a high-temperature (2600/sup 0/F to 3000/sup 0/F firing temperature) turbine within a 6- to 10-year duration, Phase II has addressed the performance of component design and technology testing in critical areas to confirm the design concepts identified in the earlier Phase I program. Based on the testing and support studies completed under Phase II, this report describes the updated turbine subsystem design for a coal-derived gas fuel (low-Btu gas) operation at 2600/sup 0/F turbine firing temperature. A commercial IGCC plant configuration would contain four gas turbines. These gas turbines utilize an existing axial flow compressor from the GE product line MS6001 machine. A complete description of the Primary Reference Design-Overall Plant Design Description has been developed and has been documented. Trends in overall plant performance improvement at higher pressure ratio and higher firing temperature are shown. It should be noted that the effect of pressure ratio on efficiency is significally enhanced at higher firing temperatures. It is shown that any improvement in overall plant thermal efficiency reflects about the same level of gain in Cost of Electricity (COE). The IGCC concepts are shown to be competitive in both performance and cost at current and near-term gas turbine firing temperatures of 1985/sup 0/F to 2100/sup 0/F. The savings that can be accumulated over a thirty-year plant life for a water-cooled gas turbine in an IGCC plant as compared to a state-of-the-art coal-fired steam plant are estimated. A total of $500 million over the life of a 1000 MW plant is projected. Also, this IGCC power plant has significant environmental advantages over equivalent coal-fired steam power plants.

  12. Numerical Modeling and Analysis of Small Gas Turbine Engine : Part I: Analytical Model and Compressor CFD

    OpenAIRE

    Nawaz AHMAD

    2009-01-01

    The thesis work aims at devising analytical thermodynamic model and numerical modeling of the compressor of a small gas turbine to be operated on producer gas with lower heating contents. The turbine will serve as a component of “EXPLORE-Biomass Based Polygeneration” project to meet the internal electrical power requirements of 2-5 KW. The gas turbine engine is of radial type (one stage radial compressor, one stage radial turbine). Small gas turbines give less electrical efficiencies especial...

  13. Generation of synthesis gas by partial oxidation of natural gas in a gas turbine

    NARCIS (Netherlands)

    Cornelissen, R.; Tober, E.; Kok, J.B.W.; Meer, van der T.H.

    2006-01-01

    The application of partial oxidation in a gas turbine (PO-GT) in the production of synthesis gas for methanol production is explored. In PO-GT, methane is compressed, preheated, partial oxidized and expanded. For the methanol synthesis a 12% gain in thermal efficiency has been calculated for the PO-

  14. Proceedings of the flexible, midsize gas turbine program planning workshop

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1997-03-01

    The US Department of Energy (DOE) and the California Energy Commission (CEC) held a program planning workshop on March 4--5, 1997 in Sacramento, California on the subject of a flexible, midsize gas turbine (FMGT). The workshop was also co-sponsored by the Electric Power Research Institute (EPRI), the Gas Research Institute (GRI), the Gas Turbine Association (GTA), and the Collaborative Advanced Gas Turbine Program (CAGT). The purpose of the workshop was to bring together a broad cross section of knowledgeable people to discuss the potential benefits, markets, technical attributes, development costs, and development funding approaches associated with making this new technology available in the commercial marketplace. The participants in the workshop included representatives from the sponsoring organizations, electric utilities, gas utilities, independent power producers, gas turbine manufacturers, gas turbine packagers, and consultants knowledgeable in the power generation field. Thirteen presentations were given on the technical and commercial aspects of the subject, followed by informal breakout sessions that dealt with sets of questions on markets, technology requirements, funding sources and cost sharing, and links to other programs.

  15. Test Program for High Efficiency Gas Turbine Exhaust Diffuser

    Energy Technology Data Exchange (ETDEWEB)

    Norris, Thomas R.

    2009-12-31

    This research relates to improving the efficiency of flow in a turbine exhaust, and thus, that of the turbine and power plant. The Phase I SBIR project demonstrated the technical viability of “strutlets” to control stalls on a model diffuser strut. Strutlets are a novel flow-improving vane concept intended to improve the efficiency of flow in turbine exhausts. Strutlets can help reduce turbine back pressure, and incrementally improve turbine efficiency, increase power, and reduce greenhouse gas emmission. The long-term goal is a 0.5 percent improvement of each item, averaged over the US gas turbine fleet. The strutlets were tested in a physical scale model of a gas turbine exhaust diffuser. The test flow passage is a straight, annular diffuser with three sets of struts. At the end of Phase 1, the ability of strutlets to keep flow attached to struts was demonstrated, but the strutlet drag was too high for a net efficiency advantage. An independently sponsored followup project did develop a highly-modified low-drag strutlet. In combination with other flow improving vanes, complicance to the stated goals was demonstrated for for simple cycle power plants, and to most of the goals for combined cycle power plants using this particular exhaust geometry. Importantly, low frequency diffuser noise was reduced by 5 dB or more, compared to the baseline. Appolicability to other diffuser geometries is yet to be demonstrated.

  16. A Review of Materials for Gas Turbines Firing Syngas Fuels

    Energy Technology Data Exchange (ETDEWEB)

    Gibbons, Thomas [ORNL; Wright, Ian G [ORNL

    2009-05-01

    Following the extensive development work carried out in the 1990's, gas turbine combined-cycle (GTCC) systems burning natural gas represent a reliable and efficient power generation technology widely used in many parts of the world. A critical factor was that, in order to operate at the high turbine entry temperatures required for high efficiency operation, aero-engine technology, i.e., single-crystal blades, thermal barrier coatings, and sophisticated cooling techniques had to be rapidly scaled up and introduced into these large gas turbines. The problems with reliability that resulted have been largely overcome, so that the high-efficiency GTCC power generation system is now a mature technology, capable of achieving high levels of availability. The high price of natural gas and concern about emission of greenhouse gases has focused attention on the desirability of replacing natural gas with gas derived from coal (syngas) in these gas turbine systems, since typical systems analyses indicate that IGCC plants have some potential to fulfil the requirement for a zero-emissions power generation system. In this review, the current status of materials for the critical hot gas path parts in large gas turbines is briefly considered in the context of the need to burn syngas. A critical factor is that the syngas is a low-Btu fuel, and the higher mass flow compared to natural gas will tend to increase the power output of the engine. However, modifications to the turbine and to the combustion system also will be necessary. It will be shown that many of the materials used in current engines will also be applicable to units burning syngas but, since the combustion environment will contain a greater level of impurities (especially sulfur, water vapor, and particulates), the durability of some components may be prejudiced. Consequently, some effort will be needed to develop improved coatings to resist attack by sulfur-containing compounds, and also erosion.

  17. A numerical study of automotive turbocharger mixed flow turbine inlet geometry for off design performance

    International Nuclear Information System (INIS)

    Mixed flow turbines represent a potential solution to the increasing requirement for high pressure, low velocity ratio operation in turbocharger applications. While literature exists for the use of these turbines at such operating conditions, there is a lack of detailed design guidance for defining the basic geometry of the turbine, in particular, the cone angle – the angle at which the inlet of the mixed flow turbine is inclined to the axis. This investigates the effect and interaction of such mixed flow turbine design parameters. Computational Fluids Dynamics was initially used to investigate the performance of a modern radial turbine to create a baseline for subsequent mixed flow designs. Existing experimental data was used to validate this model. Using the CFD model, a number of mixed flow turbine designs were investigated. These included studies varying the cone angle and the associated inlet blade angle. The results of this analysis provide insight into the performance of a mixed flow turbine with respect to cone and inlet blade angle

  18. A numerical study of automotive turbocharger mixed flow turbine inlet geometry for off design performance

    Science.gov (United States)

    Leonard, T.; Spence, S.; Early, J.; Filsinger, D.

    2013-12-01

    Mixed flow turbines represent a potential solution to the increasing requirement for high pressure, low velocity ratio operation in turbocharger applications. While literature exists for the use of these turbines at such operating conditions, there is a lack of detailed design guidance for defining the basic geometry of the turbine, in particular, the cone angle - the angle at which the inlet of the mixed flow turbine is inclined to the axis. This investigates the effect and interaction of such mixed flow turbine design parameters. Computational Fluids Dynamics was initially used to investigate the performance of a modern radial turbine to create a baseline for subsequent mixed flow designs. Existing experimental data was used to validate this model. Using the CFD model, a number of mixed flow turbine designs were investigated. These included studies varying the cone angle and the associated inlet blade angle. The results of this analysis provide insight into the performance of a mixed flow turbine with respect to cone and inlet blade angle.

  19. Compatibility of gas turbine materials with steam cooling

    Energy Technology Data Exchange (ETDEWEB)

    Desai, V.; Tamboli, D.; Patel, Y. [Univ. of Central Florida, Orlando, FL (United States)

    1995-10-01

    Gas turbines had been traditionally used for peak load plants and remote locations as they offer advantage of low installation costs and quick start up time. Their use as a base load generator had not been feasible owing to their poor efficiency. However, with the advent of gas turbines based combined cycle plants (CCPs), continued advances in efficiency are being made. Coupled with ultra low NO{sub x} emissions, coal compatibility and higher unit output, gas turbines are now competing with conventional power plants for base load power generation. Currently, the turbines are designed with TIT of 2300{degrees}F and metal temperatures are maintained around 1700{degrees}F by using air cooling. New higher efficiency ATS turbines will have TIT as high as 2700{degrees}F. To withstand this high temperature improved materials, coatings, and advances in cooling system and design are warranted. Development of advanced materials with better capabilities specifically for land base applications are time consuming and may not be available by ATS time frame or may prove costly for the first generation ATS gas turbines. Therefore improvement in the cooling system of hot components, which can take place in a relatively shorter time frame, is important. One way to improve cooling efficiency is to use better cooling agent. Steam as an alternate cooling agent offers attractive advantages because of its higher specific heat (almost twice that of air) and lower viscosity.

  20. Biomass & Natural Gas Based Hydrogen Fuel For Gas Turbine (Power Generation)

    Science.gov (United States)

    Significant progress has been made by major power generation equipment manufacturers in the development of market applications for hydrogen fuel use in gas turbines in recent years. Development of a new application using gas turbines for significant reduction of power plant CO2 e...

  1. Development of gas turbines simplified mathematical models; Desenvolvimento de modelos matematicos simplificados das turbinas a gas

    Energy Technology Data Exchange (ETDEWEB)

    Gomes, Leonardo Vinicius; Mendes, Pedro Paulo C. [Escola Federal de Engenharia de Itajuba, MG (Brazil). Dept. de Eletrotecnica; Ferreira, Claudio [Agencia Nacional de Energia Eletrica (ANEEL), Brasilia, DF (Brazil)

    1999-07-01

    This paper presents the development and analysis of various mathematical models for gas turbine which can be incorporated to dynamic stability or to electric power systems. The work provides answers for questions such as: the dynamic behaviour of gas turbine driven generator unities, the influence of those equipment in the other elements and the best operational conditions for the equipment.

  2. Gas turbine engine with radial diffuser and shortened mid section

    Science.gov (United States)

    Charron, Richard C.; Montgomery, Matthew D.

    2015-09-08

    An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.

  3. Banshan Gas-Fired Turbine Generator Set Put into Operation

    Institute of Scientific and Technical Information of China (English)

    2005-01-01

    @@ No.1 generator set of Banshan gas-fired power generation project, which is the first 9 FA heavy-duty gas turbine generator set in China that has drawn much attention, was successfully put into operation and merged into power grid at 21:30 in June 2, three months ahead of schedule.

  4. Full hoop casing for midframe of industrial gas turbine engine

    Science.gov (United States)

    Myers, Gerald A.; Charron, Richard C.

    2015-12-01

    A can annular industrial gas turbine engine, including: a single-piece rotor shaft spanning a compressor section (82), a combustion section (84), a turbine section (86); and a combustion section casing (10) having a section (28) configured as a full hoop. When the combustion section casing is detached from the engine and moved to a maintenance position to allow access to an interior of the engine, a positioning jig (98) is used to support the compressor section casing (83) and turbine section casing (87).

  5. Hot section components life usage analyses for industrial gas turbines

    OpenAIRE

    Saturday, Egbigenibo Genuine

    2015-01-01

    Industrial gas turbines generally operate at a bit stable power levels and the hot section critical components, especially high pressure turbine blades are prone to failure due to creep. In some cases, plants are frequently shut down, thus, in addition to creep low cycle fatigue failure equally sets in. Avoiding failure calls for proper monitoring of how the lives of these components are being consumed. Efforts are thus being made to estimate the life of the critical components...

  6. Development of a low swirl injector concept for gas turbines

    OpenAIRE

    Cheng, R. K.; Fable, S.A.; D. Schmidt; L. Arellano; Smith, K O

    2000-01-01

    This paper presents a demonstration of a novel lean premixed low-swirl injector (LSI) concept for ultra-low NOx gas turbines. Low-swirl flame stabilization method is a recent discovery that is being applied to atmospheric heating equipment. Low-swirl burners are simple and support ultra-lean premixed flames that are less susceptible to combustion instabilities than conventional high-swirl designs. As a first step towards transferring this method to turbines, an injector modeled after th...

  7. Low-pressure-ratio regenerative exhaust-heated gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Tampe, L.A.; Frenkel, R.G.; Kowalick, D.J.; Nahatis, H.M.; Silverstein, S.M.; Wilson, D.G.

    1991-01-01

    A design study of coal-burning gas-turbine engines using the exhaust-heated cycle and state-of-the-art components has been completed. In addition, some initial experiments on a type of rotary ceramic-matrix regenerator that would be used to transfer heat from the products of coal combustion in the hot turbine exhaust to the cool compressed air have been conducted. Highly favorable results have been obtained on all aspects on which definite conclusions could be drawn.

  8. Generation of synthesis gas by partial oxidation of natural gas in a gas turbine

    International Nuclear Information System (INIS)

    The application of partial oxidation in a gas turbine (PO-GT) in the production of synthesis gas for methanol production is explored. In PO-GT, methane is compressed, preheated, partial oxidized and expanded. For the methanol synthesis a 12% gain in thermal efficiency has been calculated for the PO-GT process, while the product cost decrease with 7%. For DME synthesis simular results are achieved. More development on the reactor and turbine are needed to implement this process in the industry

  9. High temperature gas-cooled reactor: gas turbine application study

    International Nuclear Information System (INIS)

    The high-temperature capability of the High-Temperature Gas-Cooled Reactor (HTGR) is a distinguishing characteristic which has long been recognized as significant both within the US and within foreign nuclear energy programs. This high-temperature capability of the HTGR concept leads to increased efficiency in conventional applications and, in addition, makes possible a number of unique applications in both electrical generation and industrial process heat. In particular, coupling the HTGR nuclear heat source to the Brayton (gas turbine) Cycle offers significant potential benefits to operating utilities. This HTGR-GT Application Study documents the effort to evaluate the appropriateness of the HTGR-GT as an HTGR Lead Project. The scope of this effort included evaluation of the HTGR-GT technology, evaluation of potential HTGR-GT markets, assessment of the economics of commercial HTGR-GT plants, and evaluation of the program and expenditures necessary to establish HTGR-GT technology through the completion of the Lead Project

  10. High temperature gas-cooled reactor: gas turbine application study

    Energy Technology Data Exchange (ETDEWEB)

    1980-12-01

    The high-temperature capability of the High-Temperature Gas-Cooled Reactor (HTGR) is a distinguishing characteristic which has long been recognized as significant both within the US and within foreign nuclear energy programs. This high-temperature capability of the HTGR concept leads to increased efficiency in conventional applications and, in addition, makes possible a number of unique applications in both electrical generation and industrial process heat. In particular, coupling the HTGR nuclear heat source to the Brayton (gas turbine) Cycle offers significant potential benefits to operating utilities. This HTGR-GT Application Study documents the effort to evaluate the appropriateness of the HTGR-GT as an HTGR Lead Project. The scope of this effort included evaluation of the HTGR-GT technology, evaluation of potential HTGR-GT markets, assessment of the economics of commercial HTGR-GT plants, and evaluation of the program and expenditures necessary to establish HTGR-GT technology through the completion of the Lead Project.

  11. AGT 101: Ceramic component development: Advanced Gas Turbine Program: Topical report, October 1979-July 1987

    Energy Technology Data Exchange (ETDEWEB)

    Ten Eyck, M.O.; MacBeth, J.W.; Sweeting, T.B.

    1987-11-01

    This topical report summarizes the ceramic component technology development activity conducted by Standard Oil Engineered Materials Company. Standard Oil, acting as a principal subcontractor and supplier of ceramic components, directed its efforts toward the development of ceramic materials in the silicon-carbide family. Various shape forming and fabrication methods, and non-destructive evaluation techniques were explored to produce the static structural components for the ceramic engine. This enabled engine testing to proceed without program slippage, and developed the approaches for producing low-cost, production quantity processes. Standard Oil contributed to the acceptance of ceramics as a viable approach for automotive gas turbine engines and to the advancement of this vital ceramic technology. 174 figs., 33 tabs.

  12. Flow Integrating Section for a Gas Turbine Engine in Which Turbine Blades are Cooled by Full Compressor Flow

    Energy Technology Data Exchange (ETDEWEB)

    Steward, W. Gene

    1999-11-14

    Routing of full compressor flow through hollow turbine blades achieves unusually effective blade cooling and allows a significant increase in turbine inlet gas temperature and, hence, engine efficiency. The invention, ''flow integrating section'' alleviates the turbine dissipation of kinetic energy of air jets leaving the hollow blades as they enter the compressor diffuser.

  13. Methods of Si based ceramic components volatilization control in a gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Garcia-Crespo, Andres Jose; Delvaux, John; Dion Ouellet, Noemie

    2016-09-06

    A method of controlling volatilization of silicon based components in a gas turbine engine includes measuring, estimating and/or predicting a variable related to operation of the gas turbine engine; correlating the variable to determine an amount of silicon to control volatilization of the silicon based components in the gas turbine engine; and injecting silicon into the gas turbine engine to control volatilization of the silicon based components. A gas turbine with a compressor, combustion system, turbine section and silicon injection system may be controlled by a controller that implements the control method.

  14. Development of Micromachine Gas Turbine for Portable Power Generation

    Science.gov (United States)

    Isomura, Kousuke; Tanaka, Shuji; Togo, Shinichi; Kanebako, Hideki; Murayama, Motohide; Saji, Nobuyoshi; Sato, Fumihiro; Esashi, Masayoshi

    Micromachine gas turbine with centrifugal impellers of 10mm diameter fabricated by 5-axis micro-milling is under development at Tohoku University, in conjunction with Ishikawajima-Harima Heavy Industries Co., Ltd. (IHI), Tohoku-Gakuin University, and Sankyo Seiki Mfg. Co., Ltd. The development is currently at the stage of proving the feasibility of the gas turbine cycle by component tests. Micro-combustors have been developed for both hydrogen and methane fuel. Over 99.9% of the combustion efficiency has been realized in both combustors and the baseline configuration of the combustor for the gas turbine is set. A compressor of 10mm diameter has been developed as a micromachined turbocharger. The performance test of the micromachined turbocharger has been started, and ran up to 566000rpm, which is approximately 65% of the design speed. Compressor performance has been successfully measured along a constant speed line at 55% of the design speed.

  15. Experimental study on the heavy-duty gas turbine combustor

    International Nuclear Information System (INIS)

    The results of stand and field testing of a combustion chamber for a heavy-duty 150 MW gas turbine are discussed. The model represented one of 14 identical segments of a tubular multican combustor constructed in the scale 1:1. The model experiments were executed at a pressure smaller than in the real gas turbine. The combustion efficiency, pressure loss factor, pattern factor, liner wall temperature, flame radiation, fluctuating pressure, and NOx emission were measured at partial and full load for both model and on-site testing. The comparison of these items of information, received on similar modes in the stand and field tests, has allowed the development of a method of calculation and the improvement of gas turbine combustors

  16. Advanced coal-fueled industrial cogeneration gas turbine system

    Energy Technology Data Exchange (ETDEWEB)

    LeCren, R.T.; Cowell, L.H.; Galica, M.A.; Stephenson, M.D.; Wen, C.S.

    1991-07-01

    Advances in coal-fueled gas turbine technology over the past few years, together with recent DOE-METC sponsored studies, have served to provide new optimism that the problems demonstrated in the past can be economically resolved and that the coal-fueled gas turbine can ultimately be the preferred system in appropriate market application sectors. The objective of the Solar/METC program is to prove the technical, economic, and environmental feasibility of a coal-fired gas turbine for cogeneration applications through tests of a Centaur Type H engine system operated on coal fuel throughout the engine design operating range. The five-year program consists of three phases, namely: (1) system description; (2) component development; (3) prototype system verification. A successful conclusion to the program will initiate a continuation of the commercialization plan through extended field demonstration runs.

  17. Segmented inlet nozzle for gas turbine, and methods of installation

    Science.gov (United States)

    Klompas, Nicholas

    1985-01-01

    A gas turbine nozzle guide vane assembly is formed of individual arcuate nozzle segments. The arcuate nozzle segments are elastically joined to each other to form a complete ring, with edges abutted to prevent leakage. The resultant nozzle ring is included within the overall gas turbine stationary structure and secured by a mounting arrangement which permits relative radial movement at both the inner and outer mountings. A spline-type outer mounting provides circumferential retention. A complete rigid nozzle ring with freedom to "float" radially results. Specific structures are disclosed for the inner and outer mounting arrangements. A specific tie-rod structure is also disclosed for elastically joining the individual nozzle segments. Also disclosed is a method of assembling the nozzle ring subassembly-by-subassembly into a gas turbine employing temporary jacks.

  18. PRESSURIZED SOLID OXIDE FUEL CELL/GAS TURBINE POWER SYSTEM

    Energy Technology Data Exchange (ETDEWEB)

    W.L. Lundberg; G.A. Israelson; R.R. Moritz(Rolls-Royce Allison); S.E. Veyo; R.A. Holmes; P.R. Zafred; J.E. King; R.E. Kothmann (Consultant)

    2000-02-01

    Power systems based on the simplest direct integration of a pressurized solid oxide fuel cell (SOFC) generator and a gas turbine (GT) are capable of converting natural gas fuel energy to electric power with efficiencies of approximately 60% (net AC/LHV), and more complex SOFC and gas turbine arrangements can be devised for achieving even higher efficiencies. The results of a project are discussed that focused on the development of a conceptual design for a pressurized SOFC/GT power system that was intended to generate 20 MWe with at least 70% efficiency. The power system operates baseloaded in a distributed-generation application. To achieve high efficiency, the system integrates an intercooled, recuperated, reheated gas turbine with two SOFC generator stages--one operating at high pressure, and generating power, as well as providing all heat needed by the high-pressure turbine, while the second SOFC generator operates at a lower pressure, generates power, and provides all heat for the low-pressure reheat turbine. The system cycle is described, major system components are sized, the system installed-cost is estimated, and the physical arrangement of system components is discussed. Estimates of system power output, efficiency, and emissions at the design point are also presented, and the system cost of electricity estimate is developed.

  19. Investigating factors affecting the efficiency of gas turbine power cycle

    Directory of Open Access Journals (Sweden)

    R. Ghaderi

    2014-05-01

    Full Text Available Today, the use of gas turbines in power generation cycles has been growing. Small size, easy installation, high power-to-mass ratio and the ability to load and unload the cycle quickly are the advantages of such systems. Low efficiency is considered as one of the major disadvantages of such power plants. Thus providing a way to increase cycle efficiency can be very effective in making the cycle more efficient and thus saving fuel consumed in such systems. In this paper the thermal efficiency of the cycle is introduced through describing the mechanism of gas turbine in power generation cycle. Then we will examine the factors affecting the efficiency of the cycle and finally practical solutions such as increasing the inlet temperature, recovery, internal cooling of the compressor and heat recovery for increasing efficiency will be explained. Evaluating the polytropic efficiency of cycles shows that increasing the inlet gas temperature has little effect on turbine efficiency and is limited at high levels of ηpoly. Water or steam injection into the gas turbines will not only lead to increased efficiency of the cycle, but also increases the flexibility of the turbine, too.

  20. Analysis of gas turbine systems for sustainable energy conversion

    Energy Technology Data Exchange (ETDEWEB)

    Anheden, Marie

    2000-02-01

    Increased energy demands and fear of global warming due to the emission of greenhouse gases call for development of new efficient power generation systems with low or no carbon dioxide (CO{sub 2}) emissions. In this thesis, two different gas turbine power generation systems, which are designed with these issues in mind, are theoretically investigated and analyzed. In the first gas turbine system, the fuel is combusted using a metal oxide as an oxidant instead of oxygen in the air. This process is known as Chemical Looping Combustion (CLC). CLC is claimed to decrease combustion exergy destruction and increase the power generation efficiency. Another advantage is the possibility to separate CO{sub 2} without a costly and energy demanding gas separation process. The system analysis presented includes computer-based simulations of CLC gas turbine systems with different metal oxides as oxygen carriers and different fuels. An exergy analysis comparing the exergy destruction of the gas turbine system with CLC and conventional combustion is also presented. The results show that it is theoretically possible to increase the power generation efficiency of a simple gas turbine system by introducing CLC. A combined gas/steam turbine cycle system with CLC is, however, estimated to reach a similar efficiency as the conventional combined cycle system. If the benefit of easy and energy-efficient CO{sub 2} separation is accounted for, a CLC combined cycle system has a potential to be favorable compared to a combined cycle system with CO{sub 2} separation. In the second investigation, a solid, CO{sub 2}-neutral biomass fuel is used in a small-scale externally fired gas turbine system for cogeneration of power and district heating. Both open and closed gas turbines with different working fluids are simulated and analyzed regarding thermodynamic performance, equipment size, and economics. The results show that it is possible to reach high power generation efficiency and total (power

  1. Helium gas turbine conceptual design by genetic/gradient optimization

    International Nuclear Information System (INIS)

    Helium gas turbine is the key component of the power conversion system for direct cycle High Temperature Gas-cooled Reactors (HTGR), of which an optimal design is essential for high efficiency. Gas turbine design currently is a multidisciplinary process in which the relationships between constraints, objective functions and variables are very noisy. Due to the ever-increasing complexity of the process, it has becomes very hard for the engineering designer to foresee the consequences of changing certain parts. With classic design procedures which depend on adaptation to baseline design, this problem is usually averted by choosing a large number of design variables based on the engineer's judgment or experience in advance, then reaching a solution through iterative computation and modification. This, in fact, leads to a reduction of the degree of freedom of the design problem, and therefore to a suboptimal design. Furthermore, helium is very different in thermal properties from normal gases; it is uncertain whether the operation experiences of a normal gas turbine could be used in the conceptual design of a helium gas turbine. Therefore, it is difficult to produce an optimal design with the general method of adaptation to baseline. Since their appearance in the 1970s, Genetic algorithms (GAs) have been broadly used in many research fields due to their robustness. GAs have also been used recently in the design and optimization of turbo-machines. Researchers at the General Electronic Company (GE) developed an optimization software called Engineous, and used GAs in the basic design and optimization of turbines. The ITOP study group from Xi'an Transportation University also did some work on optimization of transonic turbine blades. However, since GAs do not have a rigorous theory base, many problems in utilities have arisen, such as premature convergence and uncertainty; the GA doesn't know how to locate the optimal design, and doesn't even know if the optimal solution

  2. Advanced Coal-Fueled Gas Turbine Program. Final report

    Energy Technology Data Exchange (ETDEWEB)

    Horner, M.W.; Ekstedt, E.E.; Gal, E.; Jackson, M.R.; Kimura, S.G.; Lavigne, R.G.; Lucas, C.; Rairden, J.R.; Sabla, P.E.; Savelli, J.F.; Slaughter, D.M.; Spiro, C.L.; Staub, F.W.

    1989-02-01

    The objective of the original Request for Proposal was to establish the technological bases necessary for the subsequent commercial development and deployment of advanced coal-fueled gas turbine power systems by the private sector. The offeror was to identify the specific application or applications, toward which his development efforts would be directed; define and substantiate the technical, economic, and environmental criteria for the selected application; and conduct such component design, development, integration, and tests as deemed necessary to fulfill this objective. Specifically, the offeror was to choose a system through which ingenious methods of grouping subcomponents into integrated systems accomplishes the following: (1) Preserve the inherent power density and performance advantages of gas turbine systems. (2) System must be capable of meeting or exceeding existing and expected environmental regulations for the proposed application. (3) System must offer a considerable improvement over coal-fueled systems which are commercial, have been demonstrated, or are being demonstrated. (4) System proposed must be an integrated gas turbine concept, i.e., all fuel conditioning, all expansion gas conditioning, or post-expansion gas cleaning, must be integrated into the gas turbine system.

  3. Erosion-Resistant Nanocoatings for Improved Energy Efficiency in Gas Turbine Engines

    Energy Technology Data Exchange (ETDEWEB)

    None

    2009-06-01

    This factsheet describes a research project whose goal is to test and substantiate erosion-resistant (ER) nanocoatings for application on compressor airfoils for gas turbine engines in both industrial gas turbines and commercial aviation.

  4. Thermal barrier coatings for gas turbine and diesel engines

    Science.gov (United States)

    Miller, Robert A.; Brindley, William J.; Bailey, M. Murray

    1989-01-01

    The present state of development of thin thermal barrier coatings for aircraft gas turbine engines and thick thermal barrier coatings for truck diesel engines is assessed. Although current thermal barrier coatings are flying in certain gas turbine engines, additional advances will be needed for future engines. Thick thermal barrier coatings for truck diesel engines have advanced to the point where they are being seriously considered for the next generation of engine. Since coatings for truck engines is a young field of inquiry, continued research and development efforts will be required to help bring this technology to commercialization.

  5. Overview of zirconia with respect to gas turbine applications

    Science.gov (United States)

    Cawley, J. D.

    1984-01-01

    Phase relationships and the mechanical properties of zirconia are examined as well as the thermal conductivity, deformation, diffusion, and chemical reactivity of this refractory material. Observations from the literature particular to plasma-sprayed material and implications for gas turbine engine applications are discussed. The literature review indicates that Mg-PSZ (partially stabilized zirconia) and Ca-PSZ are unsuitable for advanced gas turbine applications; a thorough characterization of the microstructure of plasma-sprayed zirconia is needed. Transformation-toughened zirconia may be suitable for use in monolithic components.

  6. Improvements in Aircraft Gas Turbine Engines for the 90s

    Directory of Open Access Journals (Sweden)

    Arun Prasad

    1993-10-01

    Full Text Available The gas turbine propulsion system has been playing the most significant role in the evolution and development of present-day aircraft, and has become the limiting technology for developing most new aircraft. However, the jet engine still remains the preferred propulsion choice. Aircraft gas turbines in one form or the other, viz. turbojet, turbofan, turboprop or turboshaft, have been used in commercial passenger aircraft, high performance military aircraft and in rotary wing aircraft (helicopters. The emphasis in engine development programmes world over seems to be in reducing fuel consumption, increasing thrust and in reducing weight.

  7. Gas turbine installations in nuclear power plants in Sweden

    International Nuclear Information System (INIS)

    At each of the four nuclear power stations in Sweden (Ringhals, Forsmark, Oskarshamn, Barsebaeck) gas turbine generating sets have been installed. These units are normally used for peak load operation dictated of grid and System requirements but they are also connected to supply the electrical auxiliary load of the nuclear plant as reserve power sources. The gas turbines have automatic start capability under certain abnormal conditions (such as reactor trips, low frequency grid etc) but they can also be started manually from several different locations. Starting time is approximately 2- 3 minutes from start up to full load. (author)

  8. The Optimal Operation Criteria for a Gas Turbine Cogeneration System

    Directory of Open Access Journals (Sweden)

    Atsushi Akisawa

    2009-04-01

    Full Text Available The study demonstrated the optimal operation criteria of a gas turbine cogeneration system based on the analytical solution of a linear programming model. The optimal operation criteria gave the combination of equipment to supply electricity and steam with the minimum energy cost using the energy prices and the performance of equipment. By the comparison with a detailed optimization result of an existing cogeneration plant, it was shown that the optimal operation criteria successfully provided a direction for the system operation under the condition where the electric power output of the gas turbine was less than the capacity

  9. Heat transfer and flow characteristics on a gas turbine shroud.

    Science.gov (United States)

    Obata, M; Kumada, M; Ijichi, N

    2001-05-01

    The work described in this paper is an experimental investigation of the heat transfer from the main flow to a turbine shroud surface, which may be applicable to ceramic gas turbines. Three kinds of turbine shrouds are considered with a flat surface, a taper surface and a spiral groove surface opposite to the blades in an axial flow turbine of actual turbo-charger. Heat transfer measurements were performed for the experimental conditions of a uniform heat flux or a uniform wall temperature. The effects of the inlet flow angle, rotational speed, and tip clearance on the heat transfer coefficient were clarified under on- and off-design flow conditions. The mean heat transfer coefficient was correlated to the blade Reynolds number and tip clearance, and compared with an experimental correlation and measurements of a flat surface. A comparison was also made for the measurement of static pressure distributions.

  10. An Innovative Solution for Suburban Railroad Transportation: The Gas Turbine-Hybrid Train

    Directory of Open Access Journals (Sweden)

    Enrico Sciubba

    2005-03-01

    Full Text Available

    The paper reports the latest results of a study conducted on a hybrid train in which a gas turbine, operating in several alternative control modes (fixed point, on-off or load-following, generates the electrical energy for recharging a battery package and for driving the electric motors of a suburban train. The model, originally developed for automotive applications, has been validated by experimental tests performed on an ELLIOTT TA-45 GT group in the ENEA-Casaccia Research Center.

    This paper describes the preliminary design of the traction system and the choice of the energy flow control strategy. Numerical simulations have been carried out, based on an actual train mission (the Norwegian railroad track between Asker and Lillehammer and on industrial data for the single components. Following two different approaches, separate optimizations of the gas turbine set and battery package are performed, in which the objective function is the monetary cost per mission or, which is equivalent, the kWh/(t·km for a given mission profile.

  11. Fuel cell/gas turbine integration

    Energy Technology Data Exchange (ETDEWEB)

    Knickerbocker, T. [Allison Engine Company, Indianapolis, IN (United States)

    1995-10-19

    The Allison Engine Company`s very high efficiency fuel cell/advanced turbine power cycle program is discussed. The power cycle has the following advantages: high system efficiency potential, reduced emissions inherent to fuel cells, unmanned operation(no boiler) particularly suited for distributed power, and existing product line matches fuel cell operating environment. Cost effectiveness, estimates, and projections are given.

  12. Preliminary design of 600 MWt HTGR-gas turbine plant

    Energy Technology Data Exchange (ETDEWEB)

    Muto, Yasushi; Miyamoto, Yoshiaki; Shiozawa, Shusaku [Japan Atomic Energy Research Inst., Oarai, Ibaraki (Japan). Oarai Research Establishment

    1999-07-01

    In JAERI a feasibility study of the High Temperature Gas-cooled Reactor - Gas Turbine (HTGR-GT) system has been carried out since January, 1997 as an assigned work by the Science and Technology Agency. This paper describes a result of a preliminary design for a direct cycle plant of 600 MWt carried out in 1997 fiscal year within the framework of this feasibility study. A reactor inlet gas temperature of 460degC, a reactor outlet gas temperature of 850degC and a helium gas pressure of 6 MPa were selected. A power density of 6 MW/m{sup 3} and the maximum burnup of 10{sup 5} MWD/ton were achieved. A single-shaft horizontal turbomachine of 3600 rpm was selected and placed in a turbine vessel. A net thermal efficiency of 45.7% is expected to be achieved. (author)

  13. Technical and financial analysis of combined cycle gas turbine

    Directory of Open Access Journals (Sweden)

    Khan Arshad Muhammad

    2013-01-01

    Full Text Available This paper presents technical and financial models which were developed in this study to predict the overall performance of combined cycle gas turbine plant in line with the needs of independent power producers in the liberalized market of power sector. Three similar sizes of combined cycle gas turbine power projects up to 200 Megawatt of independent power producers in Pakistan were selected in-order to develop and drive the basic assumptions for the inputs of the models in view of prevailing Government of Pakistan’s two components of electricity purchasing tariff that is energy purchase price and capacity purchase price at higher voltage grid station terminal from independent power producers. The levelized electricity purchasing tariff over life of plant on gaseous fuel at 60 percent plant load factor was 6.47 cent per kilowatt hour with energy purchase price and capacity purchase prices of 3.54 and 2.93 cents per kilowatt hour respectively. The outcome of technical models of gas turbine, steam turbine and combined cycle gas turbine power were found in close agreement with the projects under consideration and provides opportunity of evaluation of technical and financial aspects of combined cycle power plant in a more simplified manner with relatively accurate results. At 105 Celsius exit temperature of heat recovery steam generator flue gases the net efficiency of combined cycle gas turbine was 48.8 percent whereas at 125 Celsius exit temperature of heat recovery steam generator flue gases it was 48.0 percent. Sensitivity analysis of selected influential components of electricity tariff was also carried out.

  14. Availability Analysis of Gas Turbines Used in Power Plants

    Directory of Open Access Journals (Sweden)

    Gilberto Francisco Martha de Souza

    2009-03-01

    Full Text Available The availability of a complex system, such as a gas turbine, is strongly associated with its parts reliability and maintenance policy. That policy not only has influence on the parts’ repair time but also on the parts’ reliability affecting the system degradation and availability. This study presents a method for reliability and availability evaluation of gas turbines installed in an electric power station. The method is based on system reliability concepts, such as functional tree development, application of failure mode and effects analysis to identify critical components for improvement of system reliability, and reliability and maintainability evaluation based on a historical failure database. The method also proposes the application of Reliability Centered Maintenance concepts to improve complex system maintenance policies aimed at the reduction of unexpected failure occurrences in critical components. The method is applied to the analysis of two F series gas turbines, each with an output of 150 MW, installed in a 500 MW combined cycle power plant. The reliability and availability of the turbines are simulated based on a five-year failure database. The availability analysis shows different results for each turbine, one presenting 99% and the other 96% availability, indicating differences in their systems installation and operation.

  15. 40 CFR 1042.670 - Special provisions for gas turbine engines.

    Science.gov (United States)

    2010-07-01

    ... provisions of 40 CFR part 1068 also do not apply for gas turbine engines produced in these earlier model... 40 Protection of Environment 32 2010-07-01 2010-07-01 false Special provisions for gas turbine... AND VESSELS Special Compliance Provisions § 1042.670 Special provisions for gas turbine engines....

  16. 46 CFR 112.20-10 - Diesel or gas turbine driven emergency power source.

    Science.gov (United States)

    2010-10-01

    ... 46 Shipping 4 2010-10-01 2010-10-01 false Diesel or gas turbine driven emergency power source. 112... Power Source § 112.20-10 Diesel or gas turbine driven emergency power source. Simultaneously with the operation of the transfer means under § 112.20-5, the diesel engine or gas turbine driving the...

  17. The impact of alternate fuels on future candidate automotive engines

    Energy Technology Data Exchange (ETDEWEB)

    Rahnke, C.J.; Nichols, R.J.

    1982-06-01

    The thermal efficiency that could occur in the future for a variety of automotive engine candidates operating on conventional and alternate fuels is projected based on current automotive engine development trends and the special characteristics of the various alternate fuels. The multi-fuel engine candidates include mixture cycle and direct injection reciprocating engines, as well as adiabatic turbocompound engines and advanced gas turbine and Stirling engines. The alternate fuels considered are propane, methanol, ethanol, diesel and methane.

  18. Creep-Fatigue Interactions of Gas Turbine Materials

    Directory of Open Access Journals (Sweden)

    Tarun Goswami

    1988-10-01

    Full Text Available The military aircraft gas turbine engines are often required to undergo a complex set of.operating conditions where the load varies considerably with respect to time. The temperature range for performing such requirements also increases as the thrust increases.The modern design of gas turbine demands very high thrust-to-weight ratio. In order to achieve this, the design is limited in the low cycle regime. The low cycle regime necessarily has the plasticity effect because of fatigue and inelastic time dependent permanent deformation because of creep. Fatigue and creep interaction studies are very important for the safe life design of critical components such as turbine discs and blades.

  19. Gas turbine cooling modeling - Thermodynamic analysis and cycle simulations

    Energy Technology Data Exchange (ETDEWEB)

    Jordal, Kristin

    1999-02-01

    Considering that blade and vane cooling are a vital point in the studies of modern gas turbines, there are many ways to include cooling in gas turbine models. Thermodynamic methods for doing this are reviewed in this report, and, based on some of these methods, a number of model requirements are set up and a Cooled Gas Turbine Model (CGTM) for design-point calculations of cooled gas turbines is established. Thereafter, it is shown that it is possible to simulate existing gas turbines with the CGTM. Knowledge of at least one temperature in the hot part of the turbine (TET, TRIT or possibly TIT) is found to be vital for a complete heat balance over the turbine. The losses, which are caused by the mixing of coolant and main flow, are in the CGTM considered through a polytropic efficiency reduction factor S. Through the study of S, it can be demonstrated that there is more to gain from coolant reduction in a small and/or old turbine with poor aerodynamics, than there is to gain in a large, modern turbine, where the losses due to interaction between coolant and main flow are, relatively speaking, small. It is demonstrated, at the design point (TET=1360 deg C, {pi}=20) for the simple-cycle gas turbine, that heat exchanging between coolant and fuel proves to have a large positive impact on cycle efficiency, with an increase of 0.9 percentage points if all of the coolant passes through the heat exchanger. The corresponding improvement for humidified coolant is 0.8 percentage points. A design-point study for the HAT cycle shows that if all of the coolant is extracted after the humidification tower, there is a decrease in coolant requirements of 7.16 percentage points, from 19.58% to 12.52% of the compressed air, and an increase in thermal efficiency of 0.46 percentage points, from 53.46% to 53.92%. Furthermore, it is demonstrated with a TET-parameter variation, that the cooling of a simple-cycle gas turbine with humid air can have a positive effect on thermal efficiency

  20. Bio-fuels for the gas turbine: A review

    Energy Technology Data Exchange (ETDEWEB)

    Gupta, K.K. [Mechanical Engineering Department, Medi-Caps Institute of Technology and Management, Pigdamber, Rau, Indore (M.P.) (India); Rehman, A.; Sarviya, R.M. [Department of Mechanical Engineering, MANIT, Bhopal (M.P.) (India)

    2010-12-15

    Due to depletion of fossil fuel, bio-fuels have generated a significant interest as an alternative fuel for the future. The use of bio-fuels to fuel gas turbine seems a viable solution for the problems of decreasing fossil-fuel reserves and environmental concerns. Bio-fuels are alternative fuels, made from renewable sources and having environmental benefit. In recent years, the desire for energy independence, foreseen depletion of nonrenewable fuel resources, fluctuating petroleum fuel costs, the necessity of stimulating agriculture based economy, and the reality of climate change have created an interest in the development of bio-fuels. The application of bio-fuels in automobiles and heating applications is increasing day by day. Therefore the use of these fuels in gas turbines would extend this application to aviation field. The impact of costly petroleum-based aviation fuel on the environment is harmful. So the development of alternative fuels in aviation is important and useful. The use of liquid and gaseous fuels from biomass will help to fulfill the Kyoto targets concerning global warming emissions. In addition, to reduce exhaust emission waste gases and syngas, etc., could be used as a potential gas turbine fuel. The term bio-fuel is referred to alternative fuel which is produced from biomass. Such fuels include bio-diesel, bio-ethanol, bio-methanol, pyrolysis oil, biogas, synthetic gas (dimethyl ether), hydrogen, etc. The bio-ethanol and bio-methanol are petrol additive/substitute. Bio-diesel is an environment friendly alternative liquid fuel for the diesel/aviation fuel. The gas turbine develops steady flame during its combustion; this feature gives a flexibility to use alternative fuels. Therefore so the use of different bio-fuels in gas turbine has been investigated by a good number of researchers. The suitability and modifications in the existing systems are also recommended. (author)

  1. Bio-fuels for the gas turbine: A review

    International Nuclear Information System (INIS)

    Due to depletion of fossil fuel, bio-fuels have generated a significant interest as an alternative fuel for the future. The use of bio-fuels to fuel gas turbine seems a viable solution for the problems of decreasing fossil-fuel reserves and environmental concerns. Bio-fuels are alternative fuels, made from renewable sources and having environmental benefit. In recent years, the desire for energy independence, foreseen depletion of nonrenewable fuel resources, fluctuating petroleum fuel costs, the necessity of stimulating agriculture based economy, and the reality of climate change have created an interest in the development of bio-fuels. The application of bio-fuels in automobiles and heating applications is increasing day by day. Therefore the use of these fuels in gas turbines would extend this application to aviation field. The impact of costly petroleum-based aviation fuel on the environment is harmful. So the development of alternative fuels in aviation is important and useful. The use of liquid and gaseous fuels from biomass will help to fulfill the Kyoto targets concerning global warming emissions. In addition, to reduce exhaust emission waste gases and syngas, etc., could be used as a potential gas turbine fuel. The term bio-fuel is referred to alternative fuel which is produced from biomass. Such fuels include bio-diesel, bio-ethanol, bio-methanol, pyrolysis oil, biogas, synthetic gas (dimethyl ether), hydrogen, etc. The bio-ethanol and bio-methanol are petrol additive/substitute. Bio-diesel is an environment friendly alternative liquid fuel for the diesel/aviation fuel. The gas turbine develops steady flame during its combustion; this feature gives a flexibility to use alternative fuels. Therefore so the use of different bio-fuels in gas turbine has been investigated by a good number of researchers. The suitability and modifications in the existing systems are also recommended. (author)

  2. Real time model based diagnosis of gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Trave-Massuyes, L. [Centre National de la Recherche Scientifique (CNRS), 31 - Toulouse (France); Milne, R.

    1995-12-31

    Exxon petrochemical plant in Scotland requires continuous ethylene supply from offshore site in North Sea. The supply is achieved thanks to compressors driven by a 28 MW gas turbine, whose monitoring is of major importance. The TIGER fault diagnostic system is a knowledge base system containing a prediction model. (D.L.)

  3. BIOMASS COMBUSTION IN GAS-TURBINE-BASED SYSTEMS

    Science.gov (United States)

    The paper gives results of a comparative evaluation of a range of biomass power generation systems. he objective was to identify systems most suitable for unique properties of biomass. he characteristics of biomass fuels were reviewed, and the performance of several gas-turbine-b...

  4. GE Wins Bid for Gas Turbines in China

    Institute of Scientific and Technical Information of China (English)

    2003-01-01

    The United States-based General Electric Power Systems has won a bid to build gas turbines for a key power plant program in China's 10th Five-Year Plan (2001-05). Agreements on equipment purchases and technology transfers for the project were signed in Beijing in early March. GE Power Systems. in

  5. Solid Oxide Fuel Cell – Gas Turbine Hybrid Power Plant

    OpenAIRE

    Henke, Moritz; Willich, Caroline; Steilen, Mike; Kallo, Josef; Friedrich, K. Andreas

    2013-01-01

    A model of a hybrid power plant consisting of SOFC and a gas turbine is presented. Simulations are carried out for a different number of SOFC stacks while keeping the output power of the SOFC constant. Results show that the effect of stack number on system performance is only marginal within the investigated range. Operating conditions of the SOFC, however, are strongly influenced.

  6. Pyrolysis oil utilization in 50KWE gas turbine

    NARCIS (Netherlands)

    Pozarlik, Artur; Bijl, Anton; Alst, van Niek; Bramer, Eddy; Brem, Gerrit

    2015-01-01

    The concept of using pyrolysis oil (PO) derived from biomass via a fast pyrolysis route for power and heat generation encounters problems due to an incompatibility between properties (physical and chemical) of bio-oil and gas turbines designed for fossil fuels. An extensive research has been perform

  7. Development of new thermal barrier coating materials for gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Cao, X.

    2004-04-01

    New thermal barrier coating (TBC) materials for gas turbines were studied in this work. Two of the most important properties of the material for TBCs, thermal expansion coefficient and phase stability, and the powder preparation by spray-drying are investigated.

  8. Possibilities for gas turbine and waste incinerator integration

    NARCIS (Netherlands)

    Korobitsyn, M.A.; Jellema, P.; Hirs, G.G.

    1999-01-01

    The aggressive nature of the flue gases in municipal waste incinerators does not allow the temperature of steam in the boiler to rise above 400°C. An increase in steam temperature can be achieved by external superheating in a heat recovery steam generator positioned behind a gas turbine, so that ste

  9. Parameters controlling nitric oxide emissions from gas turbine combustors

    Science.gov (United States)

    Heywood, J. B.; Mikus, T.

    1973-01-01

    Nitric oxide forms in the primary zone of gas turbine combustors where the burnt gas composition is close to stoichiometric and gas temperatures are highest. It was found that combustor air inlet conditions, mean primary zone fuel-air ratio, residence time, and the uniformity of the primary zone are the most important variables affecting nitric oxide emissions. Relatively simple models of the flow in a gas turbine combustor, coupled with a rate equation for nitric oxide formation via the Zeldovich mechanism are shown to correlate the variation in measured NOx emissions. Data from a number of different combustor concepts are analyzed and shown to be in reasonable agreement with predictions. The NOx formation model is used to assess the extent to which an advanced combustor concept, the NASA swirl can, has produced a lean well-mixed primary zone generally believed to be the best low NOx emissions burner type.

  10. Gas turbine combustion performance test of hydrogen and carbon monoxide synthetic gas

    Energy Technology Data Exchange (ETDEWEB)

    Min Chul Lee; Seok Bin Seo; Jae Hwa Chung; Si Moon Kim; Yong Jin Joo; Dal Hong Ahn [Korea Electric Power Corporation, Daejeon (Republic of Korea). Green Growth Laboratory

    2010-07-15

    The development of coal IGCC (Integrated Gasification Combined Cycle) technology has made it possible to exploit electricity generated from coal at a low cost. Furthermore, IGCC is a pre-requisite for the development of CCS (Carbon Capture and Storage) technology and hydrogen generated from coal. To achieve the need to reduce CO{sub 2} emissions, Korea's 300 MW IGCC RDD&D (Research Development, Demonstration and Dissemination) project was launched in December 2006 under the leadership of the Korea Electric Power Corporation (KEPCO), with the support of the Korea Ministry of Knowledge Economy. When a new fuel is adapted to a gas turbine (such as syngas for IGCC), it is necessary to study the gas turbine combustion characteristics of the fuel, because gas turbines are very sensitive to its physical and chemical properties. This experimental study was conducted by investigating the combustion performance of synthetic gas, which is composed chiefly of hydrogen and carbon monoxide. The results of a test on synthetic gas combustion performance were compared with the results of methane combustion, which is a major component of natural gas. The results of the combustion test of both gases were examined in terms of the turbine's inlet temperature, combustion dynamics, emission characteristics, and flame structure. From the results of this experimental study, we were able to understand the combustion characteristics of synthetic gas and anticipate the problems when synthetic gas rather than natural gas is fuelled to a gas turbine. 21 refs., 11 figs., 1 tab.

  11. Automotive exhaust gas flow control for an ammonia–water absorption refrigeration system

    International Nuclear Information System (INIS)

    A considerable part of the energy generated by an automotive internal combustion engine is wasted as heat in the exhaust system. This wasted heat could be recovered and applied to power auxiliary systems in a vehicle, contributing to its overall energy efficiency. In the present work, the experimental analysis of an absorption refrigeration system was performed. The exhaust system of an automotive internal combustion engine was connected to the generator element of an absorption refrigeration system. The performance of the absorption refrigerator was evaluated as a function of the supplied heat. The use of a control strategy for the engine exhaust gas mass flow rate was implemented to optimize the system. Exhaust gas flow was controlled by step-motor actuated valves commanded by a microcontroller in which a proportional-integral control scheme was implemented. Information such as engine torque, speed, key temperatures in the absorption cycle, as well as internal temperatures of the refrigerator was measured in a transient regime. The results indicated that the refrigeration system exhibited better performance when the amount of input heat is controlled based on the temperature of the absorption cycle generator. It was possible to conclude that, by dynamically controlling the amount of input heat, the utilisation range of the absorption refrigeration system powered by exhaust gas heat could be expanded in order to incorporate high engine speed operating conditions. - Highlights: •An absorption refrigerator was driven by automotive exhaust gas heat. •A system for controlling the refrigeration system heat input was developed. •Excessive exhaust gas heat leads to ineffective operation of the refrigerator. •Control of refrigerator's generator temperature led to better performance. •The use of exhaust gas was possible for high engine speeds

  12. Hydrogen-air energy storage gas-turbine system

    Science.gov (United States)

    Schastlivtsev, A. I.; Nazarova, O. V.

    2016-02-01

    A hydrogen-air energy storage gas-turbine unit is considered that can be used in both nuclear and centralized power industries. However, it is the most promising when used for power-generating plants based on renewable energy sources (RES). The basic feature of the energy storage system in question is combination of storing the energy in compressed air and hydrogen and oxygen produced by the water electrolysis. Such a process makes the energy storage more flexible, in particular, when applied to RES-based power-generating plants whose generation of power may considerably vary during the course of a day, and also reduces the specific cost of the system by decreasing the required volume of the reservoir. This will allow construction of such systems in any areas independent of the local topography in contrast to the compressed-air energy storage gas-turbine plants, which require large-sized underground reservoirs. It should be noted that, during the energy recovery, the air that arrives from the reservoir is heated by combustion of hydrogen in oxygen, which results in the gas-turbine exhaust gases practically free of substances hazardous to the health and the environment. The results of analysis of a hydrogen-air energy storage gas-turbine system are presented. Its layout and the principle of its operation are described and the basic parameters are computed. The units of the system are analyzed and their costs are assessed; the recovery factor is estimated at more than 60%. According to the obtained results, almost all main components of the hydrogen-air energy storage gas-turbine system are well known at present; therefore, no considerable R&D costs are required. A new component of the system is the H2-O2 combustion chamber; a difficulty in manufacturing it is the necessity of ensuring the combustion of hydrogen in oxygen as complete as possible and preventing formation of nitric oxides.

  13. Automotive gasoline quality analysis by gas chromatography: study of adulteration

    Energy Technology Data Exchange (ETDEWEB)

    Moreira, L.S.; Azevedo, D.A. [Dept. de Quimica Organica, Univ. Federal do Rio de Janeiro, Ilha do Fundao, Rio de Janeiro, RJ (Brazil); d' Avila, L.A. [Dept. de Processos Organicos, Univ. Federal do Rio de Janeiro, Ilha do Fundao, Rio de Janeiro, RJ (Brazil)

    2003-10-01

    The addition of organic solvents (light aliphatic, heavy aliphatic and aromatic hydrocarbons) in Brazilian gasoline is unfortunately very frequent, and this illicit practice impares gasoline quality. Gas chromatography (GC) and gas chromatography coupled to mass spectrometry (GC-MS) analyses can be used as a procedure to improve the detection of adulterated gasoline. The results showed that adulterated samples and also the type of organic solvent used in adulteration can be detected by comparison of chromatographic profiles (standard samples versus adulterated samples). However, a single GC analysis can detect an adulterated gasoline, and so decrease the number of adulterated samples approved as presenting good quality. (orig.)

  14. A novel algorithm for the simulation of an automotive turbocharger turbine

    OpenAIRE

    Katrašnik, Tomaž

    2015-01-01

    Predstavljen je inovativni algoritem za simulacijo delovanja turbine turbopolnilnika z metodo karakteristik, ki omogoča simulacijo spremenljivega izstopnega oz. vstopnega tlaka na robnem elementu in spremenljivih fizikalnih lastnosti plina. Teorija metode karakteristik sloni na predpostavki idealnega plina z nespremenljivimi fizikalnimi lastnostmi - lastnosti plina se ne spreminjajo s temperaturo in koncentracijo. Zato so, za doseganje natančnejših in resničnejših rezultatov, izpeljane izpopo...

  15. Ztek`s ultra high efficiency fuel cell/gas turbine combination

    Energy Technology Data Exchange (ETDEWEB)

    Hsu, M.; Nathanson, D. [Ztek Corp., Waltham, MA (United States)

    1995-10-19

    Ztek is proceeding on development of an ultra-high efficiency hybrid system of its Planar SOFC with a gas turbine, realizing shared cost and performance benefits. The gas turbine as the Balance-of-Plant was a logical selection from a fuel cell system perspective because of (1) the high-power-density energy conversion of gas turbines; (2) the unique compatibility of the Ztek Planar SOFC with gas turbines, and (3) the availability of low-cost commercial gas turbine systems. A Tennessee Valley Authority/Ztek program is ongoing, which addresses operation of the advanced Planar SOFC stacks and design scale-up for utility power generation applications.

  16. Low Cost Gas Turbine Off-Design Prediction Technique

    Science.gov (United States)

    Martinjako, Jeremy

    This thesis seeks to further explore off-design point operation of gas turbines and to examine the capabilities of GasTurb 12 as a tool for off-design analysis. It is a continuation of previous thesis work which initially explored the capabilities of GasTurb 12. The research is conducted in order to: 1) validate GasTurb 12 and, 2) predict off-design performance of the Garrett GTCP85-98D located at the Arizona State University Tempe campus. GasTurb 12 is validated as an off-design point tool by using the program to predict performance of an LM2500+ marine gas turbine. Haglind and Elmegaard (2009) published a paper detailing a second off-design point method and it includes the manufacturer's off-design point data for the LM2500+. GasTurb 12 is used to predict off-design point performance of the LM2500+ and compared to the manufacturer's data. The GasTurb 12 predictions show good correlation. Garrett has published specification data for the GTCP85-98D. This specification data is analyzed to determine the design point and to comment on off-design trends. Arizona State University GTCP85-98D off-design experimental data is evaluated. Trends presented in the data are commented on and explained. The trends match the expected behavior demonstrated in the specification data for the same gas turbine system. It was originally intended that a model of the GTCP85-98D be constructed in GasTurb 12 and used to predict off-design performance. The prediction would be compared to collected experimental data. This is not possible because the free version of GasTurb 12 used in this research does not have a module to model a single spool turboshaft. This module needs to be purchased for this analysis.

  17. The effects of solarization on the performance of a gas turbine

    Science.gov (United States)

    Homann, Christiaan; van der Spuy, Johan; von Backström, Theodor

    2016-05-01

    Various hybrid solar gas turbine configurations exist. The Stellenbosch University Solar Power Thermodynamic (SUNSPOT) cycle consists of a heliostat field, solar receiver, primary Brayton gas turbine cycle, thermal storage and secondary Rankine steam cycle. This study investigates the effect of the solarization of a gas turbine on its performance and details the integration of a gas turbine into a solar power plant. A Rover 1S60 gas turbine was modelled in Flownex, a thermal-fluid system simulation and design code, and validated against a one-dimensional thermodynamic model at design input conditions. The performance map of a newly designed centrifugal compressor was created and implemented in Flownex. The effect of the improved compressor on the performance of the gas turbine was evident. The gas turbine cycle was expanded to incorporate different components of a CSP plant, such as a solar receiver and heliostat field. The solarized gas turbine model simulates the gas turbine performance when subjected to a typical variation in solar resource. Site conditions at the Helio100 solar field were investigated and the possibility of integrating a gas turbine within this system evaluated. Heat addition due to solar irradiation resulted in a decreased fuel consumption rate. The influence of the additional pressure drop over the solar receiver was evident as it leads to decreased net power output. The new compressor increased the overall performance of the gas turbine and compensated for pressure losses incurred by the addition of solar components. The simulated integration of the solarized gas turbine at Helio100 showed potential, although the solar irradiation is too little to run the gas turbine on solar heat alone. The simulation evaluates the feasibility of solarizing a gas turbine and predicts plant performance for such a turbine cycle.

  18. Generic Analysis Methods for Gas Turbine Engine Performance: The development of the gas turbine simulation program GSP

    NARCIS (Netherlands)

    Visser, W.P.J.

    2015-01-01

    Numerical modelling and simulation have played a critical role in the research and development towards today’s powerful and efficient gas turbine engines for both aviation and power generation. The simultaneous progress in modelling methods, numerical methods, software development tools and methods,

  19. Comparison between externally fired gas turbine and gasifier-gas turbine system for the olive oil industry

    International Nuclear Information System (INIS)

    The olive oil industry generates during the extraction process several solid wastes as olive tree leaves and prunings, exhausted pomace and olive pits. These renewable wastes could be used for power and heat applications. The aim of this paper is to compare the performance of two small-scale CHP systems: a gasification- gas turbine system and an EFGT (externally fired gas turbine system). For this reason, several parameters have been calculated: generated heat and power, electric and overall efficiencies, biomass consumption, exergy efficiency, optimum pressure ratio, etc. These systems provide 30 kWe and about 60kWth. Simulation results show that the electrical and overall efficiencies achieved in EFGT system (19.1% and 59.3%, respectively) are significantly higher than those obtained in the gasification plant (12.3% and 45.4%). The proposed CHP systems have been modeled using Cycle-Tempo® software. -- Highlights: ► Comparison between externally fired gas turbine and gasifier-gas turbine system. ► Olive oil industry generates several solid wastes as olive tree leaves and prunings. ► Thermodynamic parameters have been calculated. ► Systems have been modeled using Cycle-Tempo® software. ► Simulation results show electrical and overall efficiencies achieved in the systems.

  20. Determination of Remaining Useful Life of Gas Turbine Blade

    OpenAIRE

    Meor Said Mior Azman; Osman Muhammad Hafizuddin; Megat Yusoff Puteri Sri Melor; Sulaiman Shaharin Anwar; Syed Ahmad Ghazali Syed M Afdhal

    2016-01-01

    The aim of this research is to determine the remaining useful life of gas turbine blade, using service-exposed turbine blades. This task is performed using Stress Rupture Test (SRT) under accelerated test conditions where the applied stresses to the specimen is between 400 MPa to 600 MPa and the test temperature is 850°C. The study will focus on the creep behaviour of the 52000 hours service-exposed blades, complemented with creep-rupture modelling using JMatPro software and microstructure ex...

  1. Development of a low swirl injector concept for gas turbines

    International Nuclear Information System (INIS)

    This paper presents a demonstration of a novel lean premixed low-swirl injector (LSI) concept for ultra-low NOx gas turbines. Low-swirl flame stabilization method is a recent discovery that is being applied to atmospheric heating equipment. Low-swirl burners are simple and support ultra-lean premixed flames that are less susceptible to combustion instabilities than conventional high-swirl designs. As a first step towards transferring this method to turbines, an injector modeled after the design of atmospheric low-swirl burner has been tested up to T=646 F and 10 atm and shows good promise for future development

  2. Development of a low swirl injector concept for gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Cheng, R.K.; Fable, S.A.; Schmidt, D; Arellano, L.; Smith, K.O.

    2000-09-01

    This paper presents a demonstration of a novel lean premixed low-swirl injector (LSI) concept for ultra-low NOx gas turbines. Low-swirl flame stabilization method is a recent discovery that is being applied to atmospheric heating equipment. Low-swirl burners are simple and support ultra-lean premixed flames that are less susceptible to combustion instabilities than conventional high-swirl designs. As a first step towards transferring this method to turbines, an injector modeled after the design of atmospheric low-swirl burner has been tested up to T=646 F and 10 atm and shows good promise for future development.

  3. Collaborative Advanced Gas Turbine Program: Phase 1. Final report

    Energy Technology Data Exchange (ETDEWEB)

    Hollenbacher, R.; Kesser, K.; Beishon, D.

    1994-12-01

    The Collaborative Advanced Gas Turbine (CAGT) Program is an advanced gas turbine research and development program whose goal is to accelerate the commercial availability, to within the turn of the century, of high efficiency aeroderivative gas turbines for electric power generating applications. In the first project phase, research was conducted to prove or disprove the research hypothesis that advanced aeroderivative gas turbine systems can provide a promising technology alternative, offering high efficiency and good environmental performance characteristics in modular sizes, for utility applications. This $5 million, Phase 1 research effort reflects the collaborative efforts of a broad and international coalition of industries and organizations, both public and private, that have pooled their resources to assist in this research. Included in this coalition are: electric and gas utilities, the Electric Power Research Institute, the Gas Research Institute and the principal aircraft engine manufacturers. Additionally, the US Department of Energy (DOE) and the California Energy Commission have interacted with the CAGT on both technical and executive levels as observers and sources of funding. The three aircraft engine manufacturer-led research teams participating in this research include: Rolls-Royce, Inc., and Bechtel; the Turbo Power and Marine Division of United Technologies and Fluor Daniel; and General Electric Power Generation, Stewart and Stevenson, and Bechtel. Each team has investigated advanced electric power generating systems based on their high-thrust (60,000 to 100,000 pounds) aircraft engines. The ultimate goal of the CAGT program is that the community of stakeholders in the growing market for natural-gas-fueled, electric power generation can collectively provide the right combination of market-pull and technology-push to substantially accelerate the commercialization of advanced, high efficiency aeroderivative technologies.

  4. Exergy and Environmental Impact Assessment between Solar Powered Gas Turbine and Conventional Gas Turbine Power Plant

    Directory of Open Access Journals (Sweden)

    Ali Rajaei

    2016-01-01

    Full Text Available Recuperator is a heat exchanger that is used in gas turbine power plants to recover energy from outlet hot gases to heat up the air entering the combustion chamber. Similarly, the combustion chamber inlet air can be heated up to temperatures up to 1000 (°C by solar power tower (SPT as a renewable and environmentally benign energy source. In this study, comprehensive comparison between these two systems in terms of energy, exergy, and environmental impacts is carried out. Thermodynamic simulation of both cycles is conducted using a developed program in MATLAB environment. Exergetic performances of both cycles and their emissions are compared and parametric study is carried out. A new parameter (renewable factor is proposed to evaluate resources quality and measure how green an exergy loss or destruction or a system as a whole is. Nonrenewable exergy destruction and loss are reduced compared to GT with recuperator cycle by 34.89% and 47.41%, respectively. Reductions in CO2, NOx, and CO compared to GT with recuperator cycle by 49.92%, 66.14%, and 39.77%, respectively, are in line with renewable factor value of around 55.7 which proves the ability of the proposed green measure to evaluate and compare the cycles performances.

  5. The Combination of Internal-Combustion Engine and Gas Turbine

    Science.gov (United States)

    Zinner, K.

    1947-01-01

    While the gas turbine by itself has been applied in particular cases for power generation and is in a state of promising development in this field, it has already met with considerable success in two cases when used as an exhaust turbine in connection with a centrifugal compressor, namely, in the supercharging of combustion engines and in the Velox process, which is of particular application for furnaces. In the present paper the most important possibilities of combining a combustion engine with a gas turbine are considered. These "combination engines " are compared with the simple gas turbine on whose state of development a brief review will first be given. The critical evaluation of the possibilities of development and fields of application of the various combustion engine systems, wherever it is not clearly expressed in the publications referred to, represents the opinion of the author. The state of development of the internal-combustion engine is in its main features generally known. It is used predominantly at the present time for the propulsion of aircraft and road vehicles and, except for certain restrictions due to war conditions, has been used to an increasing extent in ships and rail cars and in some fields applied as stationary power generators. In the Diesel engine a most economical heat engine with a useful efficiency of about 40 percent exists and in the Otto aircraft engine a heat engine of greatest power per unit weight of about 0.5 kilogram per horsepower.

  6. Baseline Gas Turbine Development Program. Eleventh quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, F.W.; Wagner, C.E.

    1975-07-31

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1978 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. NASA completed initial heat balance testing of a baseline engine. An additional 450 hours were run on ceramic regenerators and seals. Seal wear rates are very good, and the elastomeric mounting system was satisfactory. An engine/control oil supply system based on the power steering pump is successfully operating in baseline vehicles. The design of the upgraded engine power turbine nozzle actuator was finalized, and layouts of the inlet guide vane actuator are in process. A lock-up torque converter was installed in the free rotor vehicle. Baseline engine and vehicle testing of water injection and variable inlet guide vanes was completed. A thermal analysis of the gas generator is in process. A steady-state, full power analysis was made. A three-dimensional stress analysis of the compressor cover was made. The power turbine nozzle actuating system layout was completed. The analytical studies of the power turbine rotor bearings were completed. MTI completed the design of the gas generator rotor simulation fixture and is starting to build it. Optimized reduction gears were successfully tested in a baseline engine.

  7. Analysis of Maisotsenko open gas turbine power cycle with a detailed air saturator model

    International Nuclear Information System (INIS)

    Highlights: • Developed an accurate air saturator model. • Performed sensitivity analysis for Maisotsenko gas turbine cycle (MGTC). • Performed comparative analysis for MGTC and simple gas turbine with reheat (SGTR) and humid air turbine (HAT). • MGTC has higher efficiency and specific work output with at high compressor pressure ratio. • Optimum air saturator water mass flow rate is calculated. - Abstract: With ever increasing cost of fossil fuels and natural gas, the improvement in gas turbine power cycle efficiency is needed due to the tremendous savings in fuel consumption. Water/steam injection is considered as one of the most popular power augmentation techniques because of its significant impact on the gas turbine performance. One of the recently suggested evaporative gas turbine cycles is the Maisotsenko open cycle for gas turbine power generation. In this paper, detailed thermodynamic analysis of this cycle is investigated with a thorough air saturator model. A comparative analysis is carried out to signify the advantages and disadvantages of Maisotsenko gas turbine cycle (MGTC) as compared with humid air gas turbine cycles. MGTC performance is evaluated based on a simple recuperated gas turbine cycle. In addition, sensitivity analysis is performed to investigate the effect of different operating parameters on the overall cycle performance. Finally, integrating an air saturator instead of a conventional heat exchanger in recuperated gas turbine cycles enhances the power plant performance such that an efficiency enhancement of 7% points and net specific work output augmentation of 44.4% are obtained

  8. Operability of an Ejector Enhanced Pulse Combustor in a Gas Turbine Environment

    Science.gov (United States)

    Paxson, Daniel E.; Dougherty, Kevin

    2008-01-01

    A pressure-gain combustor comprised of a mechanically valved, liquid fueled pulsejet, an ejector, and an enclosing shroud, was coupled to a small automotive turbocharger to form a self-aspirating, thrust producing gas turbine engine. The system was constructed in order to investigate issues associated with the interaction of pulsed combustion devices and turbomachinery. Installed instrumentation allowed for sensing of distributed low frequency pressure and temperature, high frequency pressure in the shroud, fuel flow rate, rotational speed, thrust, and laboratory noise. The engine ran successfully and reliably, achieving a sustained thrust of 5 to 6 lbf, and maintaining a rotor speed of approximately 90,000 rpm, with a combustor pressure gain of approximately 4 percent. Numerical simulations of the system without pressure-gain combustion indicated that the turbocharger would not operate. Thus, the new combustor represented a substantial improvement in system performance. Acoustic measurements in the shroud and laboratory indicated turbine stage sound pressure level attenuation of 20 dB. This is consistent with published results from detonative combustion experiments. As expected, the mechanical reed valves suffered considerable damage under the higher pressure and thermal loading characteristics of this system. This result underscores the need for development of more robust valve systems for this application. The efficiency of the turbomachinery components did not appear to be significantly affected by unsteadiness associated with pulsed combustion, though the steady component efficiencies were already low, and thus not expected to be particularly sensitive.

  9. Gas turbine combustor exit piece with hinged connections

    Energy Technology Data Exchange (ETDEWEB)

    Charron, Richard C.; Pankey, William W.

    2016-04-26

    An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.

  10. Long run of wood powder fired gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Salman, Hassan [Energitekniskt Centrum, Piteaa (Sweden)

    2004-05-01

    Tests have been carried out on a biomass gasification test facility at Energy Technology Center in Piteaa (ETC). It was planned to run the facility batchwise for 100 hours. The main aim of these tests was to study the effects of the impurities in the product gas on the blades of a gas turbine. The impurities are the ash particles carried by the product gas and the vaporised metals from the fuel especially the alkali metals. Six successful tests could be done before a breakdown of the gas turbine due to a fouling of the blade tips and the turbine passage resulting in seizing of the turbine. However the runs were sufficient to give new experiences in the running of the plant. The atmospheric preheating by gas combustion in the cyclone appeared to be more reliable than the pressurised preheating with an oil burner. It is also observed that the gasification could be started when the cyclone temperature is 550-600 deg C instead of higher than 700 deg C that was used earlier. The reliability of the feeding system was improved and the plugging of the downcomers was eliminated. It was also observed that the flame stability in the modified combustion chamber of the turbine depends not only on the gas composition but also on the temperature of the gas. A gas temperature that is over 650 deg C gave stable combustion. The effects of the impurities in the gas were studied. Steel cylinders were placed at the inlet of the turbine and the deposits on them were analysed. The turbine wheel was disassembled after the last run and blades were cut and the deposits were analysed too. The analysis was done on the deposits by using scanning electron microscopy. The thickness of deposits was 30-60 {mu}m on the pressure side of the turbineblades while they were too thin to be resolved with the optical microscope on the suction side. Deposits were observed also on the blade-tips and on the turbine case. It was observed that the content of K in the deposits was higher than that in the fuel

  11. Thermodynamic Analysis of Supplementary-Fired Gas Turbine Cycles

    Directory of Open Access Journals (Sweden)

    Bjørn Qvale

    2003-06-01

    Full Text Available

    This paper presents an analysis of the possibilities for improving the efficiency of an indi-rectly biomass-fired gas turbine (IBFGT by supplementary direct gas-firing. The supplementary firing may be based on natural gas, biogas or pyrolysis gas. Intuitively, supplementary firing is expected to result in a high marginal efficiency. The paper shows that depending on the application, this is not always the case.

    The interest in this cycle arises from a recent demonstration of the feasibility of a two-stage gasification process through construction of several plants. The gas from this process could be divided into two streams, one for primary and one for supplementary firing. A preliminary analysis of the ideal, recuperated Brayton cycle shows that for this cycle any supplementary firing will have a marginal efficiency of unity per extra unit of fuel. The same result is obtained for the indirectly fired gas turbine (IFGT and for the supplementary-fired IFGT. These results show that the combination of external firing and internal firing have the potential of reducing or solving some problems associated with the use of biomass both in the recuperated and the indirectly fired gas turbine: The former requires a clean, expensive fuel. The latter is limited in efficiency due to limitations in material temperature of the heat exchanger. Thus, in the case of an IBFGT, it would appear be very appropriate to use a cheap biomass or waste fuel for low temperature combustion and external firing and use natural gas at a high marginal efficiency for high temperature heating. However, it is shown that this is not the case for a simple IBFGT supplementary-fired with natural gas. The marginal efficiency of the natural gas is in this case found to be independent of temperature ratio and lower than for the recuperated gas turbine. Instead, other process changes may be considered in order to obtain a high marginal efficiency on natural gas. Two possibilities

  12. Cost Benefit Analysis of Using Clean Energy Supplies to Reduce Greenhouse Gas Emissions of Global Automotive Manufacturing

    OpenAIRE

    Xiang Zhao; Chris Yuan; Huajun Cao; Qiang Zhai

    2011-01-01

    Automotive manufacturing is energy-intensive. The consumed energy contributes to the generation of significant amounts of greenhouse gas (GHG) emissions by the automotive manufacturing industry. In this paper, a study is conducted on assessing the application potential of such clean energy power systems as solar PV, wind and fuel cells in reducing the GHG emissions of the global auto manufacturing industry. The study is conducted on the representative solar PV, wind and fuel cell clean energy...

  13. Advanced solidification processing of an industrial gas turbine engine component

    Science.gov (United States)

    Clemens, Mei Ling; Price, Allen; Bellows, Richard S.

    2003-03-01

    This paper will describe the efforts of the Advanced Turbine Airfoil Manufacturing Technology Program sponsored by the U.S. Department of Energy through the Oak Ridge National Laboratory and Howmet Research Corporation. The purpose of the program is to develop single-crystal and directionally solidified casting technologies to benefit Advanced Turbine Systems (ATS) industrial and utility gas turbine engines. The focus is on defining and implementing advanced Vacuum Induction Melting (VIM) furnace enhancements that provide precise control of mold temperatures during solidification. Emphasis was placed on increasing the total magnitude of thermal gradients while minimizing the difference in maximum and minimum gradients produced during the solidification process. Advanced VIM casting techniques were applied to Solar Turbines Incorporated’s Titan 130 First Stage High Pressure Turbine Blade under the ATS program. A comparison of the advanced VIM casting process to the conventional Bridgeman casting process will be presented as it pertains to the thermal gradients achieved during solidification, microstructure, elemental partitioning characterization, and solution heat treat response.

  14. Chaotic gas turbine subject to augmented Lorenz equations.

    Science.gov (United States)

    Cho, Kenichiro; Miyano, Takaya; Toriyama, Toshiyuki

    2012-09-01

    Inspired by the chaotic waterwheel invented by Malkus and Howard about 40 years ago, we have developed a gas turbine that randomly switches the sense of rotation between clockwise and counterclockwise. The nondimensionalized expressions for the equations of motion of our turbine are represented as a starlike network of many Lorenz subsystems sharing the angular velocity of the turbine rotor as the central node, referred to as augmented Lorenz equations. We show qualitative similarities between the statistical properties of the angular velocity of the turbine rotor and the velocity field of large-scale wind in turbulent Rayleigh-Bénard convection reported by Sreenivasan et al. [Phys. Rev. E 65, 056306 (2002)]. Our equations of motion achieve the random reversal of the turbine rotor through the stochastic resonance of the angular velocity in a double-well potential and the force applied by rapidly oscillating fields. These results suggest that the augmented Lorenz model is applicable as a dynamical model for the random reversal of turbulent large-scale wind through cessation. PMID:23031014

  15. Chaotic gas turbine subject to augmented Lorenz equations.

    Science.gov (United States)

    Cho, Kenichiro; Miyano, Takaya; Toriyama, Toshiyuki

    2012-09-01

    Inspired by the chaotic waterwheel invented by Malkus and Howard about 40 years ago, we have developed a gas turbine that randomly switches the sense of rotation between clockwise and counterclockwise. The nondimensionalized expressions for the equations of motion of our turbine are represented as a starlike network of many Lorenz subsystems sharing the angular velocity of the turbine rotor as the central node, referred to as augmented Lorenz equations. We show qualitative similarities between the statistical properties of the angular velocity of the turbine rotor and the velocity field of large-scale wind in turbulent Rayleigh-Bénard convection reported by Sreenivasan et al. [Phys. Rev. E 65, 056306 (2002)]. Our equations of motion achieve the random reversal of the turbine rotor through the stochastic resonance of the angular velocity in a double-well potential and the force applied by rapidly oscillating fields. These results suggest that the augmented Lorenz model is applicable as a dynamical model for the random reversal of turbulent large-scale wind through cessation.

  16. Temperature detection in a gas turbine

    Science.gov (United States)

    Lacy, Benjamin; Kraemer, Gilbert; Stevenson, Christian

    2012-12-18

    A temperature detector includes a first metal and a second metal different from the first metal. The first metal includes a plurality of wires and the second metal includes a wire. The plurality of wires of the first metal are connected to the wire of the second metal in parallel junctions. Another temperature detector includes a plurality of resistance temperature detectors. The plurality of resistance temperature detectors are connected at a plurality of junctions. A method of detecting a temperature change of a component of a turbine includes providing a temperature detector include ing a first metal and a second metal different from the first metal connected to each other at a plurality of junctions in contact with the component; and detecting any voltage change at any junction.

  17. Evaluation of the Gas Turbine Modular Helium Reactor

    International Nuclear Information System (INIS)

    Recent advances in gas-turbine and heat exchanger technology have enhanced the potential for a Modular Helium Reactor (MHR) incorporating a direct gas turbine (Brayton) cycle for power conversion. The resulting Gas Turbine Modular Helium Reactor (GT-MHR) power plant combines the high temperature capabilities of the MHR with the efficiency and reliability of modern gas turbines. While the passive safety features of the steam cycle MHR (SC-MHR) are retained, generation efficiencies are projected to be in the range of 48% and steam power conversion systems, with their attendant complexities, are eliminated. Power costs are projected to be reduced by about 20%, relative to the SC-MHR or coal. This report documents the second, and final, phase of a two-part evaluation that concluded with a unanimous recommendation that the direct cycle (DC) variant of the GT-MHR be established as the commercial objective of the US Gas-Cooled Reactor Program. This recommendation has been endorsed by industrial and utility participants and accepted by the US Department of Energy (DOE). The Phase II effort, documented herein, concluded that the DC GT-MHR offers substantial technical and economic advantages over both the IDC and SC systems. Both the DC and IDC were found to offer safety advantages, relative to the SC, due to elimination of the potential for water ingress during power operations. This is the dominant consequence event for the SC. The IDC was judged to require somewhat less development than the direct cycle, while the SC, which has the greatest technology base, incurs the least development cost and risk. While the technical and licensing requirements for the DC were more demanding, they were judged to be incremental and feasible. Moreover, the DC offers significant performance and cost improvements over the other two concepts. Overall, the latter were found to justify the additional development needs

  18. Evaluation of the Gas Turbine Modular Helium Reactor

    Energy Technology Data Exchange (ETDEWEB)

    1994-02-01

    Recent advances in gas-turbine and heat exchanger technology have enhanced the potential for a Modular Helium Reactor (MHR) incorporating a direct gas turbine (Brayton) cycle for power conversion. The resulting Gas Turbine Modular Helium Reactor (GT-MHR) power plant combines the high temperature capabilities of the MHR with the efficiency and reliability of modern gas turbines. While the passive safety features of the steam cycle MHR (SC-MHR) are retained, generation efficiencies are projected to be in the range of 48% and steam power conversion systems, with their attendant complexities, are eliminated. Power costs are projected to be reduced by about 20%, relative to the SC-MHR or coal. This report documents the second, and final, phase of a two-part evaluation that concluded with a unanimous recommendation that the direct cycle (DC) variant of the GT-MHR be established as the commercial objective of the US Gas-Cooled Reactor Program. This recommendation has been endorsed by industrial and utility participants and accepted by the US Department of Energy (DOE). The Phase II effort, documented herein, concluded that the DC GT-MHR offers substantial technical and economic advantages over both the IDC and SC systems. Both the DC and IDC were found to offer safety advantages, relative to the SC, due to elimination of the potential for water ingress during power operations. This is the dominant consequence event for the SC. The IDC was judged to require somewhat less development than the direct cycle, while the SC, which has the greatest technology base, incurs the least development cost and risk. While the technical and licensing requirements for the DC were more demanding, they were judged to be incremental and feasible. Moreover, the DC offers significant performance and cost improvements over the other two concepts. Overall, the latter were found to justify the additional development needs.

  19. A liquid turbine generator as a high-temperature attachment to a gas turbine

    Science.gov (United States)

    Shershnev, N. A.; Sinenkov, A. N.; Gorin, A. I.

    1984-11-01

    A vortex chamber working with gaseous combustion products effectively retains injected liquid metal in the form of a rotating annular layer, and this is considered as a possible basic component in a liquid generator constituting a high-temperature attachment to a gas-turbine system. It is shown that copper or nickel should be used as the working metal. Model cold experiments have given efficencies for the chamber working with water and air at a level of 0.4-0.45.

  20. Turbines. NO{sub x} processing on Solar gas turbines; Turbines. Traitement des NO{sub x} sur les turbines a gaz solar

    Energy Technology Data Exchange (ETDEWEB)

    Chausse, X. [Spie-Trindel, 95 - Cergy (France)

    1997-12-31

    This paper presents the SoLoNOx process developed by the Solar Turbines Incorporated company for the prevention of NO{sub x} production in his gas turbines. The formation of combustion products, by-products and NO{sub x} are recalled first and then the different existing processes for the reduction of pollutants are reviewed: water or steam injection, and purification of exhaust gases. The SoLoNOx process uses a dry, weak and pre-mixed mixture and allows better NO{sub x} and CO reductions than the water injection process. (J.S.)

  1. Current status and future prospects of gas-turbine development in the USSR

    Science.gov (United States)

    Liulka, A. M.

    1981-06-01

    It is noted that gas turbine engines are widely used in the USSR in the gas industry as main drives for superchargers in main stations. In addition, gas turbine engines are widely used in the chemical industry as well as in the iron and steel industries; a series of standard units with output up to 100 MW operate in electric power engineering under base and peak load. Gas turbine engines are also used in shipbuilding and civil aviation.

  2. Railcar mounted gas turbines serve Chinese power needs

    Energy Technology Data Exchange (ETDEWEB)

    1975-03-01

    The Orenda Division of Hawker Siddeley Canada Ltd. has just completed an order by the China National Technical Import Corp., Peking, for 2 railcar-mounted 9000-kW mobile generating sets. The gas-turbine-powered units, spares, etc., made up a package valued at approximately $4 million. The overall design concept called for a 2-car unit with the gas turbine and generator in one car and the switch gear, control panels, and an auxiliary power unit in the other. At the operating site, the cars are separated by distances of 10 ft (3 m), and the power car is leveled using mechanically operated leveling jacks and a system of liquid-level sight glasses located along the walls of the car. Cable connections between the control and power cars are made through drop-down doors at the facing car ends.

  3. Gas-turbine critical research and advanced technology support project

    Science.gov (United States)

    Clark, J. S.; Hodge, P. E.; Lowell, C. E.; Anderson, D. N.; Schultz, D. F.

    1981-01-01

    A technology data base for utility gas turbine systems capable of burning coal derived fuels was developed. The following areas are investigated: combustion; materials; and system studies. A two stage test rig is designed to study the conversion of fuel bound nitrogen to NOx. The feasibility of using heavy fuels in catalytic combustors is evaluated. A statistically designed series of hot corrosion burner rig tests was conducted to measure the corrosion rates of typical gas turbine alloys with several fuel contaminants. Fuel additives and several advanced thermal barrier coatings are tested. Thermal barrier coatings used in conjunction with low critical alloys and those used in a combined cycle system in which the stack temperature was maintained above the acid corrosion temperature are also studied.

  4. Flow and Combustion in Advanced Gas Turbine Combustors

    CERN Document Server

    Janicka, Johannes; Schäfer, Michael; Heeger, Christof

    2013-01-01

    With regard to both the environmental sustainability and operating efficiency demands, modern combustion research has to face two main objectives, the optimization of combustion efficiency and the reduction of pollutants. This book reports on the combustion research activities carried out within the Collaborative Research Center (SFB) 568 “Flow and Combustion in Future Gas Turbine Combustion Chambers” funded by the German Research Foundation (DFG). This aimed at designing a completely integrated modeling and numerical simulation of the occurring very complex, coupled and interacting physico-chemical processes, such as turbulent heat and mass transport, single or multi-phase flows phenomena, chemical reactions/combustion and radiation, able to support the development of advanced gas turbine chamber concepts.

  5. Exergy Analysis of Overspray Process in Gas Turbine Systems

    Directory of Open Access Journals (Sweden)

    Kyoung Hoon Kim

    2012-07-01

    Full Text Available Gas turbine power can be augmented by overspray process which consists of inlet fogging and wet compression. In this study exergy analysis of the overspray process in gas turbine system is carried out with a non-equilibrium analytical modeling based on droplet evaporation and the second law of thermodynamics. This work focuses on the effects of system parameters such as pressure ratio, water injection ratio, and initial droplet diameter on exergetical performances including irreversibility and exergy efficiency of the process. The process performances are also estimated under the condition of saturated water injection ratio above which complete evaporation of injected water droplets within a compressor is not possible. The results show that the irreversibility increases but the saturated irreversibility decreases with increasing initial droplet diameter for a specified pressure ratio.

  6. Bimetallic Palladium Catalysts for Methane Combustion in Gas Turbines

    OpenAIRE

    Persson, Katarina

    2006-01-01

    Catalytic combustion is a promising combustion technology for gas turbines, which results in ultra low emission levels of nitrogen oxides (NOx), carbon monoxide (CO) and unburned hydrocarbons (UHC). Due to the low temperature achieved in catalytic combustion almost no thermal NOx is formed. This thesis is concentrated on the first stage in a catalytic combustion chamber, i.e. the ignition catalyst. The catalyst used for this application is often a supported palladium based catalyst due to its...

  7. Development of gas turbine fuels and combustion. An overview

    Energy Technology Data Exchange (ETDEWEB)

    Fejer, A. A.

    1979-01-01

    This overview is triggered by the rapidly changing role of the gas turbine in the spectrum of medium and large prime movers for industrial service. It describes the characteristic features of these engines, contrasting them with their chief competitor, the steam cycle. The focus is on the aerodynamic processes in the combustion chambers of traditional engines and includes an outline of the changes that are to be expected with the introduction of the synthetic and coal derived fuels.

  8. Optimal Discrete Event Supervisory Control of Aircraft Gas Turbine Engines

    Science.gov (United States)

    Litt, Jonathan (Technical Monitor); Ray, Asok

    2004-01-01

    This report presents an application of the recently developed theory of optimal Discrete Event Supervisory (DES) control that is based on a signed real measure of regular languages. The DES control techniques are validated on an aircraft gas turbine engine simulation test bed. The test bed is implemented on a networked computer system in which two computers operate in the client-server mode. Several DES controllers have been tested for engine performance and reliability.

  9. Fundamental heat transfer research for gas turbine engines

    Science.gov (United States)

    Metzger, D. E. (Editor)

    1980-01-01

    Thirty-seven experts from industry and the universities joined 24 NASA Lewis staff members in an exchange of ideas on trends in aeropropulsion research and technology, basic analyses, computational analyses, basic experiments, near-engine environment experiments, fundamental fluid mechanics and heat transfer, and hot technology as related to gas turbine engines. The workshop proceedings described include pre-workshop input from participants, presentations of current activity by the Lewis staff, reports of the four working groups, and a workshop summary.

  10. Needs assessment for manufacturing ceramic gas turbine components

    Energy Technology Data Exchange (ETDEWEB)

    Johnson, D.R.; McSpadden, S.B.; Morris, T.O.; Pasto, A.E.

    1995-11-01

    An assessment of needs for the manufacturing of ceramic gas turbine components was undertaken to provide a technical basis for planning R&D activities to support DOE`s gas turbine programs. The manufacturing processes for ceramic turbine engine components were examined from design through final inspection and testing. The following technology needs were identified: Concurrent engineering early in the design phase to develop ceramic components that are more readily manufacturable. Additional effort in determining the boundaries of acceptable design dimensions and tolerances through experimental and/or analytical means. Provision, by the designer, of a CAD based model of the component early in the design cycle. Standardization in the way turbine components are dimensioned and toleranced, and in the way component datum features are defined. Rapid means of fabricating hard tooling, including intelligent systems for design of tooling and rapid prototyping of tooling. Determination of process capabilities by manufacturing significant numbers of parts. Development of more robust ceramic manufacturing processes which are tolerant of process variations. Development of intelligent processing as a means of controlling yield and quality of components. Development of computer models of key manufacturing steps, such as green forming to reduce the number of iterations required to manufacture intolerance components. Development of creep feed or other low-damage precision grinding for finish machining of components. Improved means of fixturing components for finish machining. Fewer and lower-cost final inspection requirements. Standard procedures, including consistent terminology and analytical software for dimensional inspection of components. Uniform data requirements from the US turbine engine companies. An agreed-upon system of naming ceramic materials and updating the name when changes have been made.

  11. Conceptual design of helium gas turbine for MHTGR-GT

    International Nuclear Information System (INIS)

    Conceptual designs of the direct-cycle helium gas turbine for a practical unit (450 MWt) and an experimental unit (1200kWt) of MHTGR were conducted and the results as shown below were obtained. The power conversion vessel for this practical unit can further be downsized to an outside diameter of 7.4m and a height of 22m as compared with the conventional design examples. Comparison of the conceptual designs of helium gas turbines using single-shaft type employing the axial-flow compressor and twin-shaft type employing the centrifugal compressor shows that the former provides advantages in terms of structure and control designs whereas the latter offers a higher efficiency. In order to determine which of them should be selected, a further study to investigate various aspects of safety features and startup characteristics will be needed. Either of the two types can provide a cycle efficiency of 46 to 48%. The third mode natural frequencies of the twin-shart type's low-pressure rotational shaft and the single shaft type are below the designed rotational speed, but their vibrational controls are made available using the magnetic bearing system. Elevation of the natural frequency for the twin-shaft type would be possible by altering the arrangements of its shafting configuration. As compared with the earlier conceptual designs, the overall systems configuration can be made simpler and more compact; five stages of turbines for the single-shaft type and seven stages of turbines for the twin-shaft type employing one shaft for the low-pressure compressor and the power turbine and; 26 stages of compressors for the axial-flow type with the single shaft system and five stages of compressors for the centrifugal type with the twin-shaft system. 9 refs, 12 figs, 4 tabs

  12. Fuel property effects on USN gas turbine combustors

    Science.gov (United States)

    Masters, A. I.; Mosier, S. A.; Nowack, C. J.

    1984-01-01

    For several years the Department of Defense has been sponsoring fuel accommodation investigations with gas turbine engine manufacturers and supporting organizations to quantify the effect of changes in fuel properties and characteristics on the operation and performance of military engine components and systems. Inasmuch as there are many differences in hardware between the operational engines in the military inventories, due to differences in design philosophy and requirements, efforts were initially expended to acquire fuel effects data from rigs simulating the hot sections of these different engines. Correlations were then sought using the data acquired to produce more general, generic relationships that could be applied to all military gas turbine engines regardless of their origin. Finally, models could be developed from these correlations that could predict the effect of fuel property changes on current and future engines. This presentation describes some of the work performed by Pratt and Whitney Aircraft, under Naval Air Propulsion Center sponsorship, to determine the effect of fuel properties on the hot section and fuel system of the Navy's TF30-P-414 gas turbine engine.

  13. Externally Fired micro-Gas Turbine: Modelling and experimental performance

    Energy Technology Data Exchange (ETDEWEB)

    Traverso, Alberto; Massardo, Aristide F. [Thermochemical Power Group, Dipartimento di Macchine, Sistemi Energetici e Trasporti, Universita di Genova, Genova (Italy); Scarpellini, Riccardo [Ansaldo Ricerche s.r.l., Genova (Italy)

    2006-11-15

    This work presents the steady-state and transient performance obtained by an Externally Fired micro-Gas Turbine (EFmGT) demonstration plant. The plant was designed by Ansaldo Ricerche (ARI) s.r.l. and the Thermochemical Power Group (TPG) of the Universita di Genova, using the in-house TPG codes TEMP (Thermoeconomic Modular Program) and TRANSEO. The plant was based on a recuperated 80kW micro-gas turbine (Elliott TA-80R), which was integrated with the externally fired cycle at the ARI laboratory. The first goal of the plant construction was the demonstration of the EFmGT control system. The performance obtained in the field can be improved in the near future using high-temperature heat exchangers and apt external combustors, which should allow the system to operate at the actual micro-gas turbine inlet temperature (900-950{sup o}C). This paper presents the plant layout and the control system employed for regulating the microturbine power and rotational speed. The experimental results obtained by the pilot plant in early 2004 are shown: the feasibility of such a plant configuration has been demonstrated, and the control system has successfully regulated the shaft speed in all the tests performed. Finally, the plant model in TRANSEO, which was formerly used to design the control system, is shown to accurately simulate the plant behaviour both at steady-state and transient conditions. (author)

  14. Melt Infiltrated Ceramic Composites (Hipercomp) for Gas Turbine Engine Applications

    Energy Technology Data Exchange (ETDEWEB)

    Gregory Corman; Krishan Luthra

    2005-09-30

    This report covers work performed under the Continuous Fiber Ceramic Composites (CFCC) program by GE Global Research and its partners from 1994 through 2005. The processing of prepreg-derived, melt infiltrated (MI) composite systems based on monofilament and multifilament tow SiC fibers is described. Extensive mechanical and environmental exposure characterizations were performed on these systems, as well as on competing Ceramic Matrix Composite (CMC) systems. Although current monofilament SiC fibers have inherent oxidative stability limitations due to their carbon surface coatings, the MI CMC system based on multifilament tow (Hi-Nicalon ) proved to have excellent mechanical, thermal and time-dependent properties. The materials database generated from the material testing was used to design turbine hot gas path components, namely the shroud and combustor liner, utilizing the CMC materials. The feasibility of using such MI CMC materials in gas turbine engines was demonstrated via combustion rig testing of turbine shrouds and combustor liners, and through field engine tests of shrouds in a 2MW engine for >1000 hours. A unique combustion test facility was also developed that allowed coupons of the CMC materials to be exposed to high-pressure, high-velocity combustion gas environments for times up to {approx}4000 hours.

  15. Fuzzy Computing for Control of Aero Gas Turbine Engines .

    Directory of Open Access Journals (Sweden)

    S. R. Balakrishnan

    1994-10-01

    Full Text Available Many methods, techniques and procedures available for designing the control system of plants and processes, are applied only after knowing accurately the plant or process to be controlled. However, in some complex situations where plants/processes cannot be accurately modelled, and especially where their control has human interaction, controller design may not be completely satisfactory. In such cases, it has been found that control decisions can be made on the basis of heuristic/linguistic measures or fuzzy algorithms. Fuzzy set principles have been used in controlling various plants/processes ranging from a laboratory steam engine to an autopilot, including an aero gas turbine engine engine for which the response of the engine speed for a fuzzy input of fuel flow has been studied. In this paper, certain stipulations and logic are suggested for the control of the total gas turbine engine. A case study of a single spool aero gas turbine engine with one of its state variables varied by heuristic logic is presented.

  16. Analysis on using biomass lean syngas in micro gas turbines

    Science.gov (United States)

    Mărculescu, C.; Cenuşă, V. E.; Alexe, F. N.

    2016-08-01

    The paper presents an analysis on small systems for converting biomass/wastes into power using Micro Gas Turbines (MGT) fed with gaseous bio-fuels produced by air- gasification. The MGT is designed for burning various fossil liquid and gas fuels, having catalogue data related to natural gas use. Fuel switch changes their performances. The present work is focused on adapting the MGT for burning alternative low quality gas fuel produced by biomass air gasification. The heating values of these gas fuels are 3 to 5 times lower than the methane ones, leading to different air demand for the stoichiometric burning. Validated numerical computation procedures were used to model the MGT thermodynamic process. Our purpose was to analyze the influence of fuel change on thermodynamic cycle performances.

  17. Development of Granular Catalysts and Natural Gas Combustion Technology for Small Gas Turbine Power Plants

    OpenAIRE

    Ismagilov, Z. R.; Kerzhentsev, M.A.; Yashnik, S.A.; N. V. Shikina; Zagoruiko, A.N.; Parmon, V.N.; Zakharov, V.M.; Braynin, B.I.; Favorski, O.N.

    2010-01-01

    Granular catalysts for natural gas combustion in gas turbine power plants were developed: Pd-Ce-Al2O3 catalyst for initiation of methane combustion at low temperatures and the catalysts based on oxides of Mn, hexaaluminates of Mn and La for high temperature

  18. Computer-Aided System of Virtual Testing of Gas Turbine Engines

    Directory of Open Access Journals (Sweden)

    Rybakov Viktor N.

    2016-01-01

    Full Text Available The article describes the concept of a virtual lab that includes subsystem of gas turbine engine simulation, subsystem of experiment planning, subsystem of measurement errors simulation, subsystem of simulator identification and others. The basis for virtual lab development is the computer-aided system of thermogasdynamic research and analysis “ASTRA”. The features of gas turbine engine transient modes simulator are described. The principal difference between the simulators of transient and stationary modes of gas turbine engines is that the energy balance of the compressor and turbine becomes not applicable. The computer-aided system of virtual gas turbine engine testing was created using the developed transient modes simulator. This system solves the tasks of operational (throttling, speed, climatic, altitude characteristics calculation, analysis of transient dynamics and selection of optimal control laws. Besides, the system of virtual gas turbine engine testing is a clear demonstration of gas turbine engine working process and the regularities of engine elements collaboration. The interface of the system of virtual gas turbine engine testing is described in the article and some screenshots of the interface elements are provided. The developed system of virtual gas turbine engine testing provides means for reducing the laboriousness of gas turbine engines testing. Besides, the implementation of this system in the learning process allows the diversification of lab works and therefore improve the quality of training.

  19. Gas turbines for polygeneration? A thermodynamic investigation of a fuel rich gas turbine cycle

    Directory of Open Access Journals (Sweden)

    Burak Atakan

    2011-11-01

    " SemiHidden="false" UnhideWhenUsed="false" QFormat="true" Name="Subtle Emphasis" />

    Gas turbines as used nowadays are working far in the fuel lean regime, which is most reasonable for mobile applications, since the formation of pollutants and soot are avoided while the temperatures remain low enough to avoid damage of the turbine. However, from a thermodynamic point of view the exergy utilization is far from optimum at such conditions.

  20. Baseline gas turbine development program. Eighteenth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, F W; Wagner, C E [comps.

    1977-04-30

    Progress is reported for a program whose goals are to demonstrate an experimental upgraded gas turbine powered automobile which meets the 1978 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, compact-size American automobile. Initial running of the upgraded engine took place on July 13, 1976. The engine proved to be mechanically sound, but was also 43% deficient in power. A continuing corrective development effort has to date reduced the power deficiency to 32%. Compressor efficiency was increased 2 points by changing to a 28-channel diffuser and tandem deswirl vanes; improved processing of seals has reduced regenerator leakage from about 5 to 2.5% of engine flow; a new compressor turbine nozzle has increased compressor turbine stage efficiency by about 1 point; and adjustments to burner mixing ports has reduced pressure drop from 2.8 to 2.1% of engine pressure. Key compressor turbine component improvements are scheduled for test during the next quarterly period. During the quarter, progress was also made on development of the Upgraded Vehicle control system; and instrumentation of the fourth program engine was completed by NASA. The engine will be used for development efforts at NASA LeRC.

  1. Life assessment of gas turbine blades after long term service

    Energy Technology Data Exchange (ETDEWEB)

    Auerkari, Pertti; Salonen, Jorma [VTT, Espoo (Finland); Maekinen, Sari [Helsingin Energia, Helsinki (Finland); Karvonen, Ikka; Tanttari, Heikki [Lappeenrannan Laempoevoima, Lappeenranta (Finland); Kangas, Pekka [Neste Oil, Kilpilahti (Finland); Scholz, Alfred [Technische Univ. Darmstadt (Germany); Vacchieri, Erica [Ansaldo Richerche, Genoa (Italy)

    2010-07-01

    Turbine blade samples from three land based gas turbines have been subjected to systematic condition and life assessment after long term service (88000 - 109000 equivalent operating hours, eoh), when approaching the nominal or suggested life limits. The blades represent different machine types, materials and design generations, and uncooled blading outside the hottest front end of the turbine, i.e. blades with relatively large size and considerable expected life. For a reasonable assessment, a range of damage mechanisms need to be addressed and evaluated for the impact in the residual life. The results suggested significant additional safe life for all three blade sets. In some cases this could warrant yet another life cycle comparable to that of new blades, even after approaching the nominal end of life in terms of recommended equivalent operating hours. This is thought to be partly because of base load combined cycle operation and natural gas fuel, or modest operational loading if the design also accounted for more intensive cycling operation and more corrosive oil firing. In any case, long term life extension is only appropriate if not intervened by events of overloading, overheating or other sudden events such as foreign object damage (FOD), and if supported by the regular inspection and maintenance program to control in-service damage. Condition based assessment therefore remains an important part of the blade life management after the decision of accepted life extension. (orig.)

  2. Numerical prediction of combustion induced vibro-acoustical instabilities in a gas turbine combustor

    NARCIS (Netherlands)

    Pozarlik, Artur; Kok, Jim

    2009-01-01

    Introduction of lean premixed combustion to gas turbine technology reduced the emission of harmful exhaust gas species, but due to the high sensitivity of lean flames to acoustic perturbations, the average life time of gas turbine engines was decreased significantly. Very dangerous to the integrity

  3. Design considerations: gas turbines for electric power generation

    International Nuclear Information System (INIS)

    The gas turbine represents one of the most sophisticated designs from the standpoint of time dependent deformation behavior. The large size of the equipment, which limits the amount of full scale testing, together with the demanding performance requirements and high level of reliability desired places a high degree of emphasis on the high temperature deformation design process. As an example of the various design considerations used in this equipment, a brief overview of the turbine will be given, highlighting the materials, stress, temperatures, and load history experienced by the major components. Particular attention will then be focused on the vane segment design considerations. This component is not only structurally complicated, but experiences steep temperature gradients imposed by internal cooling and large temperature transients during cyclic duty operation which have to be addressed in the design procedure. Based on this discussion the limitations of the current design procedures will be highlighted and the areas requiring additional research inputs will be discussed

  4. Application of artificial neural networks to micro gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Bartolini, C.M.; Caresana, F.; Comodi, G.; Pelagalli, L.; Renzi, M.; Vagni, S. [Dipartimento di Energetica, Facolta di Ingegneria, Universita Politecnica delle Marche, via Brecce Bianche, 60131 Ancona (Italy)

    2011-01-15

    In this work, artificial neural networks (ANNs) were applied to describe the performance of a micro gas turbine (MGT). In particular, they were used (i) to complete performance diagrams for unavailable experimental data; (ii) to assess the influence of ambient parameters on performance; and (iii) to analyze and predict emissions of pollutants in the exhausts. The experimental data used to feed the ANNs were acquired from a manufacturer's test bed. Though large, the data set did not cover the whole working range of the turbine; ANNs and an artificial neural fuzzy interference system (ANFIS) were therefore applied to fill information gaps. The results of this investigation were also used for sensitivity analysis of the machine's behavior in different ambient conditions. ANNs can effectively evaluate both MGT performance and emissions in real installations in any climate, the worst R{sup 2} in the validation set being 0.9962. (author)

  5. Advanced gas turbine cycles a brief review of power generation thermodynamics

    CERN Document Server

    Horlock, JH

    2003-01-01

    Primarily this book describes the thermodynamics of gas turbine cycles. The search for high gas turbine efficiency has produced many variations on the simple ""open circuit"" plant, involving the use of heat exchangers, reheating and intercooling, water and steam injection, cogeneration and combined cycle plants. These are described fully in the text. A review of recent proposals for a number of novel gas turbine cycles is also included. In the past few years work has been directed towards developing gas turbines which produce less carbon dioxide, or plants from which the CO2 can be d

  6. SiC/SiC Leading Edge Turbine Airfoil Tested Under Simulated Gas Turbine Conditions

    Science.gov (United States)

    Robinson, R. Craig; Hatton, Kenneth S.

    1999-01-01

    Silicon-based ceramics have been proposed as component materials for use in gas turbine engine hot-sections. A high pressure burner rig was used to expose both a baseline metal airfoil and ceramic matrix composite leading edge airfoil to typical gas turbine conditions to comparatively evaluate the material response at high temperatures. To eliminate many of the concerns related to an entirely ceramic, rotating airfoil, this study has focused on equipping a stationary metal airfoil with a ceramic leading edge insert to demonstrate the feasibility and benefits of such a configuration. Here, the idea was to allow the SiC/SiC composite to be integrated as the airfoil's leading edge, operating in a "free-floating" or unrestrained manner. and provide temperature relief to the metal blade underneath. The test included cycling the airfoils between simulated idle, lift, and cruise flight conditions. In addition, the airfoils were air-cooled, uniquely instrumented, and exposed to the same internal and external conditions, which included gas temperatures in excess of 1370 C (2500 F). Results show the leading edge insert remained structurally intact after 200 simulated flight cycles with only a slightly oxidized surface. The instrumentation clearly suggested a significant reduction (approximately 600 F) in internal metal temperatures as a result of the ceramic leading edge. The object of this testing was to validate the design and analysis done by Materials Research and Design of Rosemont, PA and to determine the feasibility of this design for the intended application.

  7. Axial Turbine Aerodynamic Design of Small Heavy-Duty Gas Turbines

    Energy Technology Data Exchange (ETDEWEB)

    Kim, Joung Seok; Lee, Wu Sang; Ryu, Je Wook [Doosan Heavy Industries and Construction, Seoul (Korea, Republic of)

    2013-04-15

    This study describes the aerodynamic design procedure for the axial turbines of a small heavy-duty gas turbine engine being developed by Docosan Heavy Industries. The design procedure mainly consists of three parts: namely, flow path design, airfoil design, and 3a performance calculation. To design the optimized flow path, through flow calculations as well as the loss estimation are widely used to evaluate the effect of geometric variables, for example, shape of meridional plane, mean radius, blades axial gap, and had angle. During the airfoil design procedure, the optimum number of blades is calculated by empirical correlations based on the in/outlet flow angles, and then 2a airfoil planar sections are designed carefully, followed by 2a B2 NS calculations. The designed planar sections are stacked along the span wise direction, leading to a 3a surfaced airfoil shape. To consider the 3a effect on turbine performance, 3a multistage Euler calculation, single row, and multistage NS calculations are performed.

  8. Axial Turbine Aerodynamic Design of Small Heavy-Duty Gas Turbines

    International Nuclear Information System (INIS)

    This study describes the aerodynamic design procedure for the axial turbines of a small heavy-duty gas turbine engine being developed by Docosan Heavy Industries. The design procedure mainly consists of three parts: namely, flow path design, airfoil design, and 3a performance calculation. To design the optimized flow path, through flow calculations as well as the loss estimation are widely used to evaluate the effect of geometric variables, for example, shape of meridional plane, mean radius, blades axial gap, and had angle. During the airfoil design procedure, the optimum number of blades is calculated by empirical correlations based on the in/outlet flow angles, and then 2a airfoil planar sections are designed carefully, followed by 2a B2 NS calculations. The designed planar sections are stacked along the span wise direction, leading to a 3a surfaced airfoil shape. To consider the 3a effect on turbine performance, 3a multistage Euler calculation, single row, and multistage NS calculations are performed

  9. Gas turbine efficiency enhancement using waste heat powered absorption chillers in the oil and gas industry

    International Nuclear Information System (INIS)

    In hot climates, the efficiency of energy-intensive industrial facilities utilizing gas turbines for power generation, such as oil refineries and natural gas processing plants (NGPPs), can be enhanced by reducing gas turbine compressor inlet air temperature. This is typically achieved using either evaporative media coolers or electrically-driven mechanical vapor-compression chillers. However, the performance of evaporative media coolers is constrained in high relative humidity (RH) conditions, such as encountered in the Middle East and tropical regions, and such coolers require demineralized water supply, while electrically-driven mechanical vapor-compression chillers consume a significant amount of electric power. In this study, the use of gas turbine exhaust gas waste-heat powered, single-effect water–lithium bromide (H2O–LiBr) absorption chillers is thermo-economically evaluated for gas turbine compressor inlet air cooling scheme, with particular applicability to Middle East NGPPs. The thermodynamic performance of the proposed scheme, integrated in a NGPP, is compared with that of conventional evaporative coolers and mechanical vapor-compression chillers, in terms of key operating parameters, and either demineralized water or electricity consumption, respectively. The results show that in extreme ambient conditions representative of summer in the Persian Gulf (i.e., 55 °C, 80% RH), three steam-fired, single-effect H2O–LiBr absorption chillers utilizing 17 MW of gas turbine exhaust heat, could provide 12.3 MW of cooling to cool compressor inlet air to 10 °C. In the same ambient conditions, evaporative coolers would only provide 2.3 MW cooling capacity, and necessitate consumption of approximately 0.8 kg/s of demineralized water to be vaporized. In addition, mechanical vapor-compression chillers would require an additional 2.7 MW of electric energy to provide the same amount of cooling as H2O–LiBr absorption chillers. The additional electricity generated

  10. Baseline Gas Turbine Development Program seventh quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, F.W.

    1974-07-30

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1976 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. All of the baseline vehicles are now operational and are performing Program tests. Vehicle tests completed in this quarter include noise reduction, heater, air conditioning, and underhood temperature evaluations. Testing was completed on the original endurance engine. Test cell evaluation of the government furnished combustor (Solar) has commenced. Vendor A and Vendor B ceramic regenerator cores were rig tested with an improved elastomeric drive. Vendor A cores with the elastomeric drive are being engine tested. Ceramic regenerator seal wear test rig results are showing promise of achieving a low friction, non-nickel-oxide rubbing surface. The first preprototype integrated control system was delivered and placed in operation on a baseline engine in a test cell. Six ribbed compressor turbine wheels made of IN 792/Hf by the AiResearch Airefrac process were received. Rig testing of the variable inlet guide Vanes was completed and engine testing initiated. Vehicle evaluations of the torque converter lock-up were completed . Specifications for the Upgraded Engine aerodymanic components were made. A subcontract is currently being arranged with Mechanical Technology Inc. (MTI) for design and development of the upgraded engine gas generator bearings and shaft system. An initial feasibility study for gas bearings was completed. Analytical design of the upgraded engine power turbine reduction gears and bearings has commenced. Engine and vehicle accessory drive studies for the upgraded engine are well underway.

  11. Forty-fourth ASME International Gas Turbine and Aeroengine Technical Congress, Exposition and Users Symposium. Pt. 2. Aircraft gas turbine; 1999 nen dai 44 kai ASME kokusai gas turbine kaigi. kokuyo gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Ikeyama, M. [Ishikawajima-Harima Heavy Industries Co. Ltd., Tokyo (Japan)

    1999-09-20

    This paper reports aircraft gas turbine presented at the 44th ASME International Gas Turbine and Aeroengine Technical Congress 1999. What has drawn the strongest interest was the session related to the numerical propulsion system simulation (NPSS) being developed by NASA. The simulation links into a network about 1000 computers possessed by aero-industry related companies, research institutes and universities. The network uses common models to perform analysis under parallel processing on aerodynamics, heat transfer and structures, while taking interactions into consideration. It is planned that the whole jet engines will be subjected to non-steady calculation using three-dimensional models by the year 2007. The cost will be 8% or less of that when large super computers are used. The keys to realization of a supersonic passenger aircraft are noise, exhaust gas and impulse wave, whereas there would be no market unless a method for absorbing the impulse wave is developed and the aircraft can fly over the ground. Presentations were made on a wind tunnel testing equipment for jet engines and studies on turbo-fan engines for civilian aircraft. (NEDO)

  12. Determination of Remaining Useful Life of Gas Turbine Blade

    Directory of Open Access Journals (Sweden)

    Meor Said Mior Azman

    2016-01-01

    Full Text Available The aim of this research is to determine the remaining useful life of gas turbine blade, using service-exposed turbine blades. This task is performed using Stress Rupture Test (SRT under accelerated test conditions where the applied stresses to the specimen is between 400 MPa to 600 MPa and the test temperature is 850°C. The study will focus on the creep behaviour of the 52000 hours service-exposed blades, complemented with creep-rupture modelling using JMatPro software and microstructure examination using optical microscope. The test specimens, made up of Ni-based superalloy of the first stage turbine blades, are machined based on International Standard (ISO 24. The results from the SRT will be analyzed using these two main equations – Larson-Miller Parameter and Life Fraction Rule. Based on the results of the remaining useful life analysis, the 52000h service-exposed blade has the condition to operate in the range of another 4751 hr to 18362 hr. The microstructure examinations shows traces of carbide precipitation that deteriorate the grain boundaries that occurs during creep process. Creep-rupture life modelling using JMatPro software has shown good agreement with the accelerated creep rupture test with minimal error.

  13. An air bearing system for small high speed gas turbines

    Science.gov (United States)

    Turner, A. B.; Davies, S. J.; Nimir, Y. L.

    1994-03-01

    This paper describes the second phase of an experimental program concerning the application of air bearings to small turbomachinery test rigs and small gas turbines. The first phase examined externally pressurized (EP) journal bearings, with a novel EP thrust bearing, for application to 'warm air' test rigs, and was entirely successful at rotational speeds in excess of 100,000 rpm. This second phase examined several designs of tilting pad-spiring journal bearings, one with a novel form of externally pressurized pad, but all using the original EP thrust bearing. The designs tested are described, including some oscillogram traces, for tests up to a maximum of 70,000 rpm; the most successful using a carbon pad-titanium beam spring arrangement. The thrust bearing which gave trouble-free operation throughout, is also described. The results of an original experiment to measure the 'runway speed' of a radial inflow turbine are also presented, which show that overspeeds of 58 percent above the design speed can result from free-power turbine coupling failure.

  14. A High Efficiency PSOFC/ATS-Gas Turbine Power System

    Energy Technology Data Exchange (ETDEWEB)

    W.L. Lundberg; G.A. Israelson; M.D. Moeckel; S.E. Veyo; R.A. Holmes; P.R. Zafred; J.E. King; R.E. Kothmann

    2001-02-01

    A study is described in which the conceptual design of a hybrid power system integrating a pressurized Siemens Westinghouse solid oxide fuel cell generator and the Mercury{trademark} 50 gas turbine was developed. The Mercury{trademark} 50 was designed by Solar Turbines as part of the US. Department of Energy Advanced Turbine Systems program. The focus of the study was to develop the hybrid power system concept that principally would exhibit an attractively-low cost of electricity (COE). The inherently-high efficiency of the hybrid cycle contributes directly to achieving this objective, and by employing the efficient, power-intensive Mercury{trademark} 50, with its relatively-low installed cost, the higher-cost SOFC generator can be optimally sized such that the minimum-COE objective is achieved. The system cycle is described, major system components are specified, the system installed cost and COE are estimated, and the physical arrangement of the major system components is discussed. Estimates of system power output, efficiency, and emissions at the system design point are also presented. In addition, two bottoming cycle options are described, and estimates of their effects on overall-system performance, cost, and COE are provided.

  15. Gas turbine blade with intra-span snubber

    Science.gov (United States)

    Merrill, Gary B.; Mayer, Clinton

    2014-07-29

    A gas turbine blade (10) including a hollow mid-span snubber (16). The snubber is affixed to the airfoil portion (14) of the blade by a fastener (20) passing through an opening (24) cast into the surface (22) of the blade. The opening is defined during an investment casting process by a ceramic pedestal (38) which is positioned between a ceramic core (32) and a surrounding ceramic casting shell (48). The pedestal provides mechanical support for the ceramic core during both wax and molten metal injection steps of the investment casting process.

  16. Power Plants, Steam and Gas Turbines WebQuest

    OpenAIRE

    Carlos Ulloa; Rey, Guillermo D.; Ángel Sánchez; Ángeles Cancela

    2012-01-01

    A WebQuest is an Internet-based and inquiry-oriented learning activity. The aim of this work is to outline the creation of a WebQuest entitled “Power Generation Plants: Steam and Gas Turbines.” This is one of the topics covered in the course “Thermodynamics and Heat Transfer,” which is offered in the second year of Mechanical Engineering at the Defense University Center at the Naval Academy in Vigo, Spain. While participating in the activity, students will be divided into groups of no more th...

  17. Gas-turbine critical research and advanced technology support project

    Science.gov (United States)

    Clark, J. S.; Lowell, C. E.; Niedzwiecki, R. W.; Nainiger, J. J.

    1979-01-01

    The technical progress made during the first 15 months of a planned 40-month project to provide a critical-technology data base for utility gas-turbine systems capable of burning coal-derived fuels is summarized. Tasks were included in the following areas: (1) combustion, to study the combustion of coal-derived fuels and conversion of fuel-bound nitrogen to NOx; (2) materials, to understand and prevent hot corrosion; and (3) system studies, to integrate and guide the other technologies. Significant progress was made.

  18. Cogeneration power plant concepts using advanced gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Huettenhofer, K.; Lezuo, A. [Siemens Power Generation, Erlangen (Germany)

    2001-07-01

    Cogeneration of heat and power (CHP) is undeniably the environmentally most favourable way of making efficient use of energy in the power generation industry. Cogeneration is also particularly appreciated by political decision makers because of its high yield from primary energy sources, and thus its contribution to the protection of the environment and the conservation of resources. Advanced gas turbines, along with an intelligent power plant design consisting of pre-engineered, modular power plant items, will help cogeneration to play an important role in future energy markets also from an economic point of view. (orig.)

  19. Interface ring for gas turbine fuel nozzle assemblies

    Science.gov (United States)

    Fox, Timothy A.; Schilp, Reinhard

    2016-03-22

    A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.

  20. Fuel nozzle for a combustor of a gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Belsom, Keith Cletus; McMahan, Kevin Weston; Thomas, Larry Lou

    2016-03-22

    A fuel nozzle for a gas turbine generally includes a main body having an upstream end axially separated from a downstream end. The main body at least partially defines a fuel supply passage that extends through the upstream end and at least partially through the main body. A fuel distribution manifold is disposed at the downstream end of the main body. The fuel distribution manifold includes a plurality of axially extending passages that extend through the fuel distribution manifold. A plurality of fuel injection ports defines a flow path between the fuel supply passage and each of the plurality of axially extending passages.

  1. Counter-Rotatable Fan Gas Turbine Engine with Axial Flow Positive Displacement Worm Gas Generator

    Science.gov (United States)

    Giffin, Rollin George (Inventor); Murrow, Kurt David (Inventor); Fakunle, Oladapo (Inventor)

    2014-01-01

    A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section through a gearbox. The gas generator has inner and outer bodies having offset inner and outer axes extending through first, second, and third sections of a core assembly. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. A combustor section extends through at least a portion of the second section.

  2. Modelling internal air systems in gas turbine engines

    Institute of Scientific and Technical Information of China (English)

    J Michael Owen

    2007-01-01

    Rotating-disc systems can be used to model,experimentally and computationally,the flow and heat transfer that occur inside the internal cooling-air systems of gas turbine engines.These rotating-disc systems have been used successfully to simplify and understand some of the complex flows that occur in internal-air systems,and designers have used this insight to improve the cooling effectiveness,thereby increasing the engine efficiency and reducing the emissions.In this review paper,three important cases are considered:hot-gas ingress;the pre-swirl system;and buoyancy-induced flow.Ingress,or ingestion,occurs when hot gas from the mainstream gas path is ingested into the wheel-space between the turbine disc and its adjacent casing.Rim seals are fitted at the periphery of the system,and sealing flow is used to reduce or prevent ingress.However,too much sealing air reduces the engine efficiency,and too little can cause serious overheating,resulting in damage to the turbine rim and blade roots.Although the flow is three-dimensional and unsteady,there are encouraging signs that simple 'orifice models' could be used to estimate the amount of ingress into the wheel-space.In a pre-swirl system,the cooling air for the gas-turbine blades is swirled by stationary nozzles,and the air is delivered to the blades via receiver holes in the rotating turbine disc.Swirling the air reduces its temperature relative to the rotating blades,and the designer needs to calculate the air temperature and pressure drop in the system.The designer also needs to calculate the effect of this swirling flow on the heat transfer from the turbine disc to the air,as this has a significant effect on the temperature distribution and stresses in the disc.Recent experimental and computational studies have given a better understanding of the flow and heat transfer in these systems.Buoyancy-induced flow occurs in the cavity between two co-rotating compressor discs when the temperature of the discs is higher

  3. Materials Selection in Gas Turbine Engine Design and the Role of Low Thermal Expansion Materials

    Science.gov (United States)

    Lagow, Benjamin W.

    2016-08-01

    Materials selection criteria in gas turbine engine design are reviewed, and several design challenges are introduced where selection of low coefficient of thermal expansion (CTE) materials can help improve engine performance and operability. This is followed by a review of the types of low CTE materials that are suitable for gas turbine engine applications, and discussion of their advantages and disadvantages. The primary limitation of low CTE materials is their maximum use temperature; if higher temperature materials could be developed, this could result in novel turbine system designs for gas turbine engines.

  4. Developments in advanced high temperature disc and blade materials for aero-engine gas turbine applications

    OpenAIRE

    Everitt, S

    2012-01-01

    The research carried out as part of this EngD is aimed at understanding the high temperature materials used in modern gas turbine applications and providing QinetiQ with the information required to assess component performance in new propulsion systems. Performance gains are achieved through increased turbine gas temperatures which lead to hotter turbine disc rims and blades. The work has focussed on two key areas: (1) Disc Alloy Assessment of High Temperature Properties; and (2) Thermal Barr...

  5. Analytical investigation of thermal barrier coatings on advanced power generation gas turbines

    Science.gov (United States)

    Amos, D. J.

    1977-01-01

    An analytical investigation of present and advanced gas turbine power generation cycles incorporating thermal barrier turbine component coatings was performed. Approximately 50 parametric points considering simple, recuperated, and combined cycles (including gasification) with gas turbine inlet temperatures from current levels through 1644K (2500 F) were evaluated. The results indicated that thermal barriers would be an attractive means to improve performance and reduce cost of electricity for these cycles. A recommended thermal barrier development program has been defined.

  6. Advanced Materials for Mercury 50 Gas Turbine Combustion System

    Energy Technology Data Exchange (ETDEWEB)

    Price, Jeffrey

    2008-09-30

    Solar Turbines Incorporated (Solar), under cooperative agreement number DE-FC26-0CH11049, has conducted development activities to improve the durability of the Mercury 50 combustion system to 30,000 hours life and reduced life cycle costs. This project is part of Advanced Materials in the Advanced Industrial Gas Turbines program in DOE's Office of Distributed Energy. The targeted development engine was the Mercury{trademark} 50 gas turbine, which was developed by Solar under the DOE Advanced Turbine Systems program (DOE contract number DE-FC21-95MC31173). As a generator set, the Mercury 50 is used for distributed power and combined heat and power generation and is designed to achieve 38.5% electrical efficiency, reduced cost of electricity, and single digit emissions. The original program goal was 20,000 hours life, however, this goal was increased to be consistent with Solar's standard 30,000 hour time before overhaul for production engines. Through changes to the combustor design to incorporate effusion cooling in the Generation 3 Mercury 50 engine, which resulted in a drop in the combustor wall temperature, the current standard thermal barrier coated liner was predicted to have 18,000 hours life. With the addition of the advanced materials technology being evaluated under this program, the combustor life is predicted to be over 30,000 hours. The ultimate goal of the program was to demonstrate a fully integrated Mercury 50 combustion system, modified with advanced materials technologies, at a host site for a minimum of 4,000 hours. Solar was the Prime Contractor on the program team, which includes participation of other gas turbine manufacturers, various advanced material and coating suppliers, nationally recognized test laboratories, and multiple industrial end-user field demonstration sites. The program focused on a dual path development route to define an optimum mix of technologies for the Mercury 50 and future gas turbine products. For liner and

  7. Catalysts as Sensors—A Promising Novel Approach in Automotive Exhaust Gas Aftertreatment

    Directory of Open Access Journals (Sweden)

    Ralf Moos

    2010-07-01

    Full Text Available Sensors that detect directly and in situ the status of automotive exhaust gas catalysts by monitoring the electrical properties of the catalyst coating itself are overviewed. Examples included in this review are the in-situ determination of the electrical impedance of three-way catalysts based on ceria-zirconia solutions and of lean NOx traps of earth-alkaline based coatings, as well as approaches to determine the ammonia loading in Fe-SCR-zeolites with electrical ac measurements. Even more sophisticated approaches based on interactions with electromagnetic waves are also reviewed. For that purpose, metallic stick-like antennas are inserted into the exhaust pipe. The catalyst properties are measured in a contactless manner, directly indicating the catalyst status. The radio frequency probes gauge the oxygen loading degree of three-way catalysts, the NOx-loading of lean NOx traps, and the soot loading of Diesel particulate filters

  8. Catalysts as sensors--a promising novel approach in automotive exhaust gas aftertreatment.

    Science.gov (United States)

    Moos, Ralf

    2010-01-01

    Sensors that detect directly and in situ the status of automotive exhaust gas catalysts by monitoring the electrical properties of the catalyst coating itself are overviewed. Examples included in this review are the in-situ determination of the electrical impedance of three-way catalysts based on ceria-zirconia solutions and of lean NO(x) traps of earth-alkaline based coatings, as well as approaches to determine the ammonia loading in Fe-SCR-zeolites with electrical ac measurements. Even more sophisticated approaches based on interactions with electromagnetic waves are also reviewed. For that purpose, metallic stick-like antennas are inserted into the exhaust pipe. The catalyst properties are measured in a contactless manner, directly indicating the catalyst status. The radio frequency probes gauge the oxygen loading degree of three-way catalysts, the NO(x)-loading of lean NO(x) traps, and the soot loading of Diesel particulate filters. PMID:22163575

  9. Condition Based Monitoring of Gas Turbine Combustion Components

    Energy Technology Data Exchange (ETDEWEB)

    Ulerich, Nancy; Kidane, Getnet; Spiegelberg, Christine; Tevs, Nikolai

    2012-09-30

    The objective of this program is to develop sensors that allow condition based monitoring of critical combustion parts of gas turbines. Siemens teamed with innovative, small companies that were developing sensor concepts that could monitor wearing and cracking of hot turbine parts. A magnetic crack monitoring sensor concept developed by JENTEK Sensors, Inc. was evaluated in laboratory tests. Designs for engine application were evaluated. The inability to develop a robust lead wire to transmit the signal long distances resulted in a discontinuation of this concept. An optical wear sensor concept proposed by K Sciences GP, LLC was tested in proof-of concept testing. The sensor concept depended, however, on optical fiber tips wearing with the loaded part. The fiber tip wear resulted in too much optical input variability; the sensor could not provide adequate stability for measurement. Siemens developed an alternative optical wear sensor approach that used a commercial PHILTEC, Inc. optical gap sensor with an optical spacer to remove fibers from the wearing surface. The gap sensor measured the length of the wearing spacer to follow loaded part wear. This optical wear sensor was developed to a Technology Readiness Level (TRL) of 5. It was validated in lab tests and installed on a floating transition seal in an F-Class gas turbine. Laboratory tests indicate that the concept can measure wear on loaded parts at temperatures up to 800{degrees}C with uncertainty of < 0.3 mm. Testing in an F-Class engine installation showed that the optical spacer wore with the wearing part. The electro-optics box located outside the engine enclosure survived the engine enclosure environment. The fiber optic cable and the optical spacer, however, both degraded after about 100 operating hours, impacting the signal analysis.

  10. Construction of power-generating gas turbine units with the use of efficient thermal schemes

    Science.gov (United States)

    Ermolenko, D. I.; Gusev, A. A.; Zhuravlev, Yu. I.; Lesnichenko, A. Ya.; Tsai, S. S.

    2008-08-01

    The design features of GTE-30 and GTE-50 power-generating gas turbines, the basic thermal circuit of a PGU-90 (150) combined-cycle plant, and a layout solution for a cogeneration station built around a gas-turbine unit are considered.

  11. Ceramic Stationary Gas Turbine Development. Technical progress report, April 1, 1993--October 31, 1994

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1994-12-01

    This report summarizes work performed by Solar Technologies Inc. and its subcontractors, during the period April 1, 1993 through October 31, 1994 under Phase II of the DOE Ceramic Stationary Gas Turbine Development program. The objective of the program is to improve the performance of stationary gas turbines in cogeneration through the implementation of selected ceramic components.

  12. Comparative Exergoeconomic Analyses of Gas Turbine Steam Injection Cycles with and without Fogging Inlet Cooling

    Directory of Open Access Journals (Sweden)

    Hassan Athari

    2015-09-01

    Full Text Available The results are reported of exergoeconomic analyses of a simple gas turbine cycle without a fogging system (SGT, a simple steam injection gas turbine cycle (STIG, and a steam injection gas turbine cycle with inlet fogging cooler (FSTIG. The results show that (1 a gas-turbine cycle with steam injection and simultaneous cooling has a higher power output than the other considered cycle; (2 at maximum energy efficiency conditions the gas turbine has the highest exergy efficiency of the cycle components and the lowest value of exergy efficiency is calculated for the fog cooler, where the mixing of air and water at greatly different temperatures causes the high exergy destruction; and (3 utilization of the fogging cooler in the steam injection cycle increases the exergy destruction in the combustion chamber. Furthermore, the simple gas turbine cycle is found to be more economic as its relative cost difference, total unit product cost, and exergoeconomic factors are less than those for the two other configurations. However, its efficiency and net power output are notably lower than for the gas turbine with steam injection and/or fog cooling. The total unit product cost is highest for the simple gas turbine with steam injection.

  13. Method for Making Measurements of the Post-Combustion Residence Time in a Gas Turbine Engine

    Science.gov (United States)

    Miles, Jeffrey H (Inventor)

    2015-01-01

    A system and method of measuring a residence time in a gas-turbine engine is provided, whereby the method includes placing pressure sensors at a combustor entrance and at a turbine exit of the gas-turbine engine and measuring a combustor pressure at the combustor entrance and a turbine exit pressure at the turbine exit. The method further includes computing cross-spectrum functions between a combustor pressure sensor signal from the measured combustor pressure and a turbine exit pressure sensor signal from the measured turbine exit pressure, applying a linear curve fit to the cross-spectrum functions, and computing a post-combustion residence time from the linear curve fit.

  14. Thermodynamic Analysis of Alternative Marine Fuels for Marine Gas Turbine Power Plants

    Institute of Scientific and Technical Information of China (English)

    Mohamed M El Gohary; Nader R Ammar

    2016-01-01

    The marine shipping industry faces challenges to reduce engine exhaust emissions and greenhouse gases (GHGs) from ships, and in particular, carbon dioxide. International regulatory bodies such as the International Maritime Organization and National Environmental Agencies of many countries have issued rules and regulations to drastically reduce GHG and emissions emanating from marine sources. This study investigates the possibility of using natural gas and hydrogen as alternative fuels to diesel oil for marine gas turbines and uses a mathematical model to assess the effect of these alternative fuels on gas turbine thermodynamic performance. Results show that since natural gas is categorized as a hydrocarbon fuel, the thermodynamic performance of the gas turbine cycle using natural gas was close to that of the diesel case. However, the gas turbine thermal efficiency was found to be slightly lower for natural gas and hydrogen fuels compared to diesel fuel.

  15. Thermodynamic analysis of alternative marine fuels for marine gas turbine power plants

    Science.gov (United States)

    El Gohary, Mohamed M.; Ammar, Nader R.

    2016-03-01

    The marine shipping industry faces challenges to reduce engine exhaust emissions and greenhouse gases (GHGs) from ships, and in particular, carbon dioxide. International regulatory bodies such as the International Maritime Organization and National Environmental Agencies of many countries have issued rules and regulations to drastically reduce GHG and emissions emanating from marine sources. This study investigates the possibility of using natural gas and hydrogen as alternative fuels to diesel oil for marine gas turbines and uses a mathematical model to assess the effect of these alternative fuels on gas turbine thermodynamic performance. Results show that since natural gas is categorized as a hydrocarbon fuel, the thermodynamic performance of the gas turbine cycle using natural gas was close to that of the diesel case. However, the gas turbine thermal efficiency was found to be slightly lower for natural gas and hydrogen fuels compared to diesel fuel.

  16. LES of an ignition sequence in a gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Boileau, M.; Staffelbach, G.; Cuenot, B. [CERFACS, Toulouse (France); Poinsot, T. [IMFT - CNRS, Toulouse (France); Berat, C. [Turbomeca (SAFRAN group), Bordes (France)

    2008-07-15

    Being able to ignite or reignite a gas turbine engine in a cold and rarefied atmosphere is a critical issue for many manufacturers. From a fundamental point of view, the ignition of the first burner and the flame propagation from one burner to another are phenomena that are usually not studied. The present work is a large eddy simulation (LES) of these phenomena. To simulate a complete ignition sequence in an annular chamber, LES has been applied to the full 360 geometry, including 18 burners. This geometry corresponds to a real gas turbine chamber. Massively parallel computing (700 processors on a Cray XT3 machine) was essential to perform such a large calculation. Results show that liquid fuel injection has a strong influence on the ignition times. Moreover, the rate of flame progress from burner to burner is much higher than the turbulent flame speed due to a major effect of thermal expansion. This flame speed is also strongly modified by the main burner aerodynamics due to the swirled injection. Finally, the variability of the combustor sectors and quadrant ignition times is highlighted. (author)

  17. Sensor and Actuator Needs for More Intelligent Gas Turbine Engines

    Science.gov (United States)

    Garg, Sanjay; Schadow, Klaus; Horn, Wolfgang; Pfoertner, Hugo; Stiharu, Ion

    2010-01-01

    This paper provides an overview of the controls and diagnostics technologies, that are seen as critical for more intelligent gas turbine engines (GTE), with an emphasis on the sensor and actuator technologies that need to be developed for the controls and diagnostics implementation. The objective of the paper is to help the "Customers" of advanced technologies, defense acquisition and aerospace research agencies, understand the state-of-the-art of intelligent GTE technologies, and help the "Researchers" and "Technology Developers" for GTE sensors and actuators identify what technologies need to be developed to enable the "Intelligent GTE" concepts and focus their research efforts on closing the technology gap. To keep the effort manageable, the focus of the paper is on "On-Board Intelligence" to enable safe and efficient operation of the engine over its life time, with an emphasis on gas path performance

  18. Analisa Pengaruh Water Wash Terhadap Performansi Turbin Gas Pada PLTG Unit 7 Paya Pasir PT.PLN Sektor Pembangkitan Medan

    OpenAIRE

    Perangin Angin, Febri Dwi Senjaya

    2015-01-01

    Turbin gas adalah mesin Pembakaran luar (eksternal Combustion Engine) dimana energi kinetik dari gas panas memutar sudu – sudu turbin menjadi energi mekanik. Pada saat ini instalasi turbin gas ditambah dengan cara baru yang disebut Water Wash. Water Wash adalah suatu cara yang digunakan untuk membersihkan kompresor sehingga daya keluaran turbin gas lebih besar. Proses penggunaan Water Wash beroperasi menggunakan pola semprotan air dari nozzle yang sangat dirancang untuk benar-benar masuk ...

  19. Dynamic Simulation of Carbonate Fuel Cell-Gas Turbine Hybrid Systems

    Energy Technology Data Exchange (ETDEWEB)

    Roberts, R.A. (U. of California, Irvine, CA); Brouwer, J. (U. of California, Irvine, CA); Liese, E.A.; Gemmen, R.S.

    2006-04-01

    Hybrid fuel cell/gas turbine systems provide an efficient means of producing electricity from fossil fuels with ultra low emissions. However, there are many significant challenges involved in integrating the fuel cell with the gas turbine and other components of this type of system. The fuel cell and the gas turbine must maintain efficient operation and electricity production while protecting equipment during perturbations that may occur when the system is connected to the utility grid or in stand-alone mode. This paper presents recent dynamic simulation results from two laboratories focused on developing tools to aid in the design and dynamic analyses of hybrid fuel cell systems. The simulation results present the response of a carbonate fuel cell/gas turbine, or molten carbonate fuel cell/gas turbine, (MCFC/GT) hybrid system to a load demand perturbation. Initial results suggest that creative control strategies will be needed to ensure a flexible system with wide turndown and robust dynamic operation.

  20. Assessment of coal gasification/hot gas cleanup based advanced gas turbine systems

    Energy Technology Data Exchange (ETDEWEB)

    1990-12-01

    The major objectives of the joint SCS/DOE study of air-blown gasification power plants with hot gas cleanup are to: (1) Evaluate various power plant configurations to determine if an air-blown gasification-based power plant with hot gas cleanup can compete against pulverized coal with flue gas desulfurization for baseload expansion at Georgia Power Company's Plant Wansley; (2) determine if air-blown gasification with hot gas cleanup is more cost effective than oxygen-blown IGCC with cold gas cleanup; (3) perform Second-Law/Thermoeconomic Analysis of air-blown IGCC with hot gas cleanup and oxygen-blown IGCC with cold gas cleanup; (4) compare cost, performance, and reliability of IGCC based on industrial gas turbines and ISTIG power island configurations based on aeroderivative gas turbines; (5) compare cost, performance, and reliability of large (400 MW) and small (100 to 200 MW) gasification power plants; and (6) compare cost, performance, and reliability of air-blown gasification power plants using fluidized-bed gasifiers to air-blown IGCC using transport gasification and pressurized combustion.

  1. Developing compressed natural gas as an automotive fuel in Nigeria: Lessons from international markets

    International Nuclear Information System (INIS)

    The Nigerian government proposed the use of compressed natural gas (CNG) as an automotive fuel in 1997 as part of the initiatives to harness natural gas (NG) resources but progress has been slow. This paper examines the natural gas vehicle (NGV) implementation approaches and outcomes in seven countries with diverse experiences in order to gain an understanding of the barriers to the NGV market development in Nigeria. The analysis employs hermeneutic principles to secondary data derived from academic literature, published reports from a variety of international agencies, grey literature, and text from online sources and identifies eight success factors for NGV market development namely: strategic intent, legal backing, learning and adaptation, assignment of responsibilities, financial incentives, NG pricing, consumer confidence, and NG infrastructure. The paper concludes that the principal impediment to NGV market development in Nigeria is the uncoordinated implementation approach and that greater government involvement is required in setting strategic goals, developing the legal and regulatory frameworks, setting of clear standards for vehicles and refuelling stations as well as assigning responsibilities to specific agencies. Short-term low cost policy interventions identified include widening the existing NG and gasoline price gap and offering limited support for refuelling and retrofitting facilities. - Highlights: • We examined the NGV policies and implementation strategies in selected countries. • The use of legislative mandates help deepen NGV penetration. • Aligning stakeholder interest is critical to NGV adoption. • Making national interest a priority ahead of regional infrastructure is a critical success factor. • Government support drives participation

  2. Non-intrusive measurement of hot gas temperature in a gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    DeSilva, Upul P.; Claussen, Heiko; Yan, Michelle Xiaohong; Rosca, Justinian; Ulerich, Nancy H.

    2016-09-27

    A method and apparatus for operating a gas turbine engine including determining a temperature of a working gas at a predetermined axial location within the engine. An acoustic signal is encoded with a distinct signature defined by a set of predetermined frequencies transmitted as a non-broadband signal. Acoustic signals are transmitted from an acoustic transmitter located at a predetermined axial location along the flow path of the gas turbine engine. A received signal is compared to one or more transmitted signals to identify a similarity of the received signal to a transmitted signal to identify a transmission time for the received signal. A time-of-flight is determined for the signal and the time-of-flight for the signal is processed to determine a temperature in a region of the predetermined axial location.

  3. Small turbines in distributed utility application: Natural gas pressure supply requirements

    Energy Technology Data Exchange (ETDEWEB)

    Goldstein, H.L.

    1996-05-01

    Implementing distributed utility can strengthen the local distribution system and help avoid or delay the expense of upgrading transformers and feeders. The gas turbine-generator set is an attractive option based on its low front-end capital cost, reliable performance at unmanned stations, and environmental performance characteristics. This report assesses gas turbine utilization issues from a perspective of fuel supply pressure requirements and discusses both cost and operational factors. A primary operational consideration for siting gas turbines on the electric distribution system is whether the local gas distribution company can supply gas at the required pressure. Currently available gas turbine engines require gas supply pressures of at least 150 pounds per square inch gauge, more typically, 250 to 350 psig. Few LDCs maintain line pressure in excess of 125 psig. One option for meeting the gas pressure requirements is to upgrade or extend an existing pipeline and connect that pipeline to a high-pressure supply source, such as an interstate transmission line. However, constructing new pipeline is expensive, and the small volume of gas required by the turbine for the application offers little incentive for the LDC to provide this service. Another way to meet gas pressure requirements is to boost the compression of the fuel gas at the gas turbine site. Fuel gas booster compressors are readily available as stand-alone units and can satisfactorily increase the supply pressure to meet the turbine engine requirement. However, the life-cycle costs of this equipment are not inconsequential, and maintenance and reliability issues for boosters in this application are questionable and require further study. These factors may make the gas turbine option a less attractive solution in DU applications than first indicated by just the $/kW capital cost. On the other hand, for some applications other DU technologies, such as photovoltaics, may be the more attractive option.

  4. Technical development give industrial gas turbines a new edge in offshore applications

    Energy Technology Data Exchange (ETDEWEB)

    Hellberg, Anders; Thom, Dorian [Demag Delaval Industrial Turbines, Lincoln, Lincolnshire (United Kingdom)

    2004-07-01

    Gas turbines have been used as compressor and alternator drivers for many years, but over the last decade gas turbines have been subject to considerable technological development spurred on by economic changes and increased environmental concerns. Industrial types of gas turbines have been specifically designed and developed for mechanical drive and general industrial power applications. However, during the last decade, gas turbine manufacturers have concentrated their developments on the lucrative aircraft market, with some subsequent benefit for the aero derivative type gas turbines. Since the pre selection of a particular characteristic (e.g. emissions, fuel consumption, maintenance method, etc) will automatically preclude one or other type of gas turbine, by virtue of the turbine design, this has resulted in a more restrictive choice for end users. We will show in this paper how the new generation of industrial gas turbines (with specific focus on the GT10C) will redress this balance. It will be shown that the new generation of machines maintain all the benefits of the industrial design (maintenance, reliability, operability) but also inherit higher efficiency, lower weight, low emissions, higher power output and speed to address present market requirements. While the weight of an industrial gas turbine core engine is somewhat higher than that of an aero derivative, today's package design is more focused to the offshore needs and as such that the core engine does not have any significant effect on overall package weight or layout. The maintenance methods that have been developed are more suitable to demands of low downtime and faster maintenance activities. The impression of most customers has been that 'industrial' type gas turbines are not suitable for the high demands of the offshore market. However, recent developments have changed the technology and the aim of the paper is to change the image. (author)

  5. Metallic and Ceramic Thin Film Thermocouples for Gas Turbine Engines

    Directory of Open Access Journals (Sweden)

    Otto J. Gregory

    2013-11-01

    Full Text Available Temperatures of hot section components in today’s gas turbine engines reach as high as 1,500 °C, making in situ monitoring of the severe temperature gradients within the engine rather difficult. Therefore, there is a need to develop instrumentation (i.e., thermocouples and strain gauges for these turbine engines that can survive these harsh environments. Refractory metal and ceramic thin film thermocouples are well suited for this task since they have excellent chemical and electrical stability at high temperatures in oxidizing atmospheres, they are compatible with thermal barrier coatings commonly employed in today’s engines, they have greater sensitivity than conventional wire thermocouples, and they are non-invasive to combustion aerodynamics in the engine. Thin film thermocouples based on platinum:palladium and indium oxynitride:indium tin oxynitride as well as their oxide counterparts have been developed for this purpose and have proven to be more stable than conventional type-S and type-K thin film thermocouples. The metallic and ceramic thin film thermocouples described within this paper exhibited remarkable stability and drift rates similar to bulk (wire thermocouples.

  6. Performance review: PBMR closed cycle gas turbine power plant

    International Nuclear Information System (INIS)

    Helium is considered as one of the ideal working fluid for closed cycle using nuclear heat source due to its low neutron absorption as well as high thermodynamic properties. The commercial viability of the Helium turbo machinery depends on operational success. The past attempts failed due to poor performances manifested in the form of drop in efficiency, inability to reach maximum load, slow response to the transients etc. Radical changes in the basic design were suggested in some instances as possible solutions. A better understanding of the operational performance is necessary for the detailed design of the plant and the control systems. This paper describes the theory behind the off design and transient modelling of a closed cycle gas turbine plant. A computer simulation model has been created specifically for this cycle. The model has been tested for various turbine entry temperatures along the steady state and its replications at various locations were observed. The paper also looks at the various control methods available for a closed cycle and some of the options were simulated. (author)

  7. Life assessment and extension for gas turbine blades

    Energy Technology Data Exchange (ETDEWEB)

    Auerkari, P.; Salonen, J.; Rantala, J. (VTT Technical Research Centre of Finland, Espoo (Finland)); Maekinen, S. (Helsingin Energia, Helsinki (Finland)); Karvonen, I.; Tanttari, H. (Lappeenrannan Energia, Lappeenranta (Finland)); Kangas, P. (Neste Oil, Porvoo (Finland)); Taattola, J. (FIAF, Tampere (Finland))

    2010-05-15

    Gas turbine blades operate under severe loading conditions, and for satisfactory service must be designed to withstand multiple damage mechanisms. On the other hand, if the assumptions on the future service are sufficiently conservative or actual service conditions more benign than foreseen, there is potential for blade life extension. This generally does not justify fully omitting intermediate inspections, as intervening damage by e.g. overheating or foreign objects is not excluded, and restoring coatings or other repairs could be needed. Nevertheless, a significant extension to the time of final replacement can be possible. In this work, example cases are used to highlight the technical challenges and results of blade life extension. Such aspects include assessment of in-service stress and temperature histories, interpretation of condition assessment, and materials performance. The example cases refer to ex-service blade samples extracted at the time approximately corresponding to the nominal blade life as defined by the engine supplier. Both land based and aircraft turbines are considered, and in spite of the differences in design and service profiles, similarities can be pointed out. The results for the example cases generally suggest significant potential for life extension, for reasons related to the case-specific service histories. (orig.)

  8. Saturator analysis for an evaporative gas turbine cycle

    Energy Technology Data Exchange (ETDEWEB)

    Parente, Joao O.S.; Traverso, Alberto; Massardo, Aristide F. [Universita di Genova, Thermo-Chemical Power Group (TPG), Genova (Italy)

    2003-07-01

    In this paper a thermodynamic assessment and a preliminary cost evaluation are given for an evaporative gas turbine (EvGT) cycle packed humidifier. Both background theory and simulation results are included. Two different approaches were used for the humidifier system modelling: the full integration of the mass-energy balance and mass transfer equations (called SAT model), and an atmospheric cooling tower-based model (called CT model). Both approaches were used to perform component thermodynamic analyses and to determine the humidifier packing design. Within these approaches, two simulation cases are discussed: a test case, with experimental results from the pilot-plant of the University of Lund, and a case study of the saturators for the optimised HAT (humid air turbine) cycles of a plant with a 50 MW power output. The two cases presented consider two different operating conditions for the saturator: the first being a 'non-optimised' saturator, and the second the 'optimal' configuration with reduced exergetic losses. For the case study, the saturator design and cost evaluation are also included. (Author)

  9. Metallic and ceramic thin film thermocouples for gas turbine engines.

    Science.gov (United States)

    Tougas, Ian M; Amani, Matin; Gregory, Otto J

    2013-01-01

    Temperatures of hot section components in today's gas turbine engines reach as high as 1,500 °C, making in situ monitoring of the severe temperature gradients within the engine rather difficult. Therefore, there is a need to develop instrumentation (i.e., thermocouples and strain gauges) for these turbine engines that can survive these harsh environments. Refractory metal and ceramic thin film thermocouples are well suited for this task since they have excellent chemical and electrical stability at high temperatures in oxidizing atmospheres, they are compatible with thermal barrier coatings commonly employed in today's engines, they have greater sensitivity than conventional wire thermocouples, and they are non-invasive to combustion aerodynamics in the engine. Thin film thermocouples based on platinum:palladium and indium oxynitride:indium tin oxynitride as well as their oxide counterparts have been developed for this purpose and have proven to be more stable than conventional type-S and type-K thin film thermocouples. The metallic and ceramic thin film thermocouples described within this paper exhibited remarkable stability and drift rates similar to bulk (wire) thermocouples. PMID:24217356

  10. Power Plants, Steam and Gas Turbines WebQuest

    Directory of Open Access Journals (Sweden)

    Carlos Ulloa

    2012-10-01

    Full Text Available A WebQuest is an Internet-based and inquiry-oriented learning activity. The aim of this work is to outline the creation of a WebQuest entitled “Power Generation Plants: Steam and Gas Turbines.” This is one of the topics covered in the course “Thermodynamics and Heat Transfer,” which is offered in the second year of Mechanical Engineering at the Defense University Center at the Naval Academy in Vigo, Spain. While participating in the activity, students will be divided into groups of no more than 10 for seminars. The groups will create PowerPoint presentations that include all of the analyzed aspects. The topics to be discussed during the workshop on power plant turbines are the: (1 principles of operation; (2 processes involved; (3 advantages and disadvantages; (4 efficiency; (5 combined cycle; and (6 transversal competences, such as teamwork, oral and written presentations, and analysis and synthesis of information. This paper presents the use of Google Sites as a guide to the WebQuest so that students can access all information online, including instructions, summaries, resources, and information on qualifications.

  11. Metallic and ceramic thin film thermocouples for gas turbine engines.

    Science.gov (United States)

    Tougas, Ian M; Amani, Matin; Gregory, Otto J

    2013-11-08

    Temperatures of hot section components in today's gas turbine engines reach as high as 1,500 °C, making in situ monitoring of the severe temperature gradients within the engine rather difficult. Therefore, there is a need to develop instrumentation (i.e., thermocouples and strain gauges) for these turbine engines that can survive these harsh environments. Refractory metal and ceramic thin film thermocouples are well suited for this task since they have excellent chemical and electrical stability at high temperatures in oxidizing atmospheres, they are compatible with thermal barrier coatings commonly employed in today's engines, they have greater sensitivity than conventional wire thermocouples, and they are non-invasive to combustion aerodynamics in the engine. Thin film thermocouples based on platinum:palladium and indium oxynitride:indium tin oxynitride as well as their oxide counterparts have been developed for this purpose and have proven to be more stable than conventional type-S and type-K thin film thermocouples. The metallic and ceramic thin film thermocouples described within this paper exhibited remarkable stability and drift rates similar to bulk (wire) thermocouples.

  12. Welding metallurgy of nickel alloys in gas turbine components

    Energy Technology Data Exchange (ETDEWEB)

    Lingenfelter, A. C., LLNL

    1997-05-21

    Materials for gas turbine engines are required to meet a wide range of temperature and stress application requirements. These alloys exhibit a combination of creep resistance, creep rupture strength, yield and tensile strength over a wide temperature range, resistance to environmental attack (including oxidation, nitridation, sulphidation and carburization), fatigue and thermal fatigue resistance, metallurgical stability and useful thermal expansion characteristics. These properties are exhibited by a series of solid-solution-strengthened and precipitation-hardened nickel, iron and cobalt alloys. The properties needed to meet the turbine engine requirements have been achieved by specific alloy additions, by heat treatment and by thermal mechanical processing. A thorough understanding of the metallurgy and metallurgical processing of these materials is imperative in order to successfully fusion weld them. This same basic understanding is required for repair of a component with the added dimension of the potential effects of thermal cycling and environmental exposure the component will have endured in service. This article will explore the potential problems in joining and repair welding these materials.

  13. Baseline Gas Turbine Development Program ninth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, C.E.

    1975-01-31

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1978 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. NASA completed the first phase of their baseline engine heat balance tests, and an upgraded engine compressor is being scaled for test. EPA completed their report on vehicle tests including emissions and vehicle performance, and a new endurance engine is on test. Significant development progress was made on both fixed and variable geometry combustors. After 45 hours of engine operation with Vendor A ceramic regenerator, no significant deterioration of the matrix, seals, or elastomeric mount was encountered. Ceramic regenerator stress analysis has commenced. Additional developments in non-nickel oxide regenerator rubbing seals are encouraging. The first preprototype integrated control system is in vehicle operation. Control adaptation for variable inlet guide vanes and water injection is progressing. AiRefrac turbine wheels were verified dimensionally and are being processed for engine testing. Water injection tests with a four nozzle system were run, and additional performance documentation of variable inlet guide vanes was obtained. Linerless insulation is on test in the free rotor engine, the new endurance engine, and a performance engine. The free rotor engine completed test cell checkout and was installed in a vehicle. Vehicle checkout, including a preprototype integrated control, is underway. Detailed specifications of the upgraded engine were written.

  14. Baseline Gas Turbine Development Program. Tenth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, F.W.; Wagner, C.E.

    1975-04-30

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1978 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. A fuel control system is being developed to allow program evaluation of a very promising low emissions, single stage, fixed geometry proprietary burner. Ceramic regenerators are under test in the free-rotor vehicle, and some have completed 30 hours of performance evaluation. Three-dimensional ceramic regenerator transient thermal and structural analysis programs are operational. Initial friction and wear test fixture results show that zirconium oxide fully stabilized by yttrium oxide is an effective substitute for nickel oxide in a plasma sprayed seal. A preprototype control system was adapted for variable inlet guide vane control in a vehicle installation. An evaluation of the free-rotor accessory drive concept in a vehicle showed no serious mechanical integrity problems. Simplifications are being made to the water injection system; significant metallurgical analysis of observed erosion/corrosion problems was accomplished. Variable inlet guide vane aerodynamic loss characteristics were determined. Generally satisfactory results with linerless insulation are resulting in extended use and application. Pattern work for the upgraded engine housing and the power turbine wheel castings are in process. A computer design analysis of the regenerator drive gears was made, and an analysis was completed of a three peripheral roller regenerator support and drive proposal for the upgraded engine.

  15. Demonstration of Enabling Spar-Shell Cooling Technology in Gas Turbines

    Energy Technology Data Exchange (ETDEWEB)

    Downs, James [Florida Turbine Technologies Inc., Jupiter, FL (United States)

    2014-12-29

    In this Advanced Turbine Program-funded Phase III project, Florida Turbine Technologies, Inc. (FTT) has developed and tested, at a pre-commercial prototypescale, spar-shell turbine airfoils in a commercial gas turbine. The airfoil development is based upon FTT’s research and development to date in Phases I and II of Small Business Innovative Research (SBIR) grants. During this program, FTT has partnered with an Original Equipment Manufacturer (OEM), Siemens Energy, to produce sparshell turbine components for the first pre-commercial prototype test in an F-Class industrial gas turbine engine and has successfully completed validation testing. This project will further the commercialization of this new technology in F-frame and other highly cooled turbine airfoil applications. FTT, in cooperation with Siemens, intends to offer the spar-shell vane as a first-tier supplier for retrofit applications and new large frame industrial gas turbines. The market for the spar-shell vane for these machines is huge. According to Forecast International, 3,211 new gas turbines units (in the >50MW capacity size range) will be ordered in ten years from 2007 to 2016. FTT intends to enter the market in a low rate initial production. After one year of successful extended use, FTT will quickly ramp up production and sales, with a target to capture 1% of the market within the first year and 10% within 5 years (2020).

  16. Gas Turbine Combustion and Ammonia Removal Technology of Gasified Fuels

    Directory of Open Access Journals (Sweden)

    Takeharu Hasegawa

    2010-03-01

    Full Text Available From the viewpoints of securing a stable supply of energy and protecting our global environment in the future, the integrated gasification combined cycle (IGCC power generation of various gasifying methods has been introduced in the world. Gasified fuels are chiefly characterized by the gasifying agents and the synthetic gas cleanup methods and can be divided into four types. The calorific value of the gasified fuel varies according to the gasifying agents and feedstocks of various resources, and ammonia originating from nitrogenous compounds in the feedstocks depends on the synthetic gas clean-up methods. In particular, air-blown gasified fuels provide low calorific fuel of 4 MJ/m3 and it is necessary to stabilize combustion. In contrast, the flame temperature of oxygen-blown gasified fuel of medium calorie between approximately 9–13 MJ/m3 is much higher, so control of thermal-NOx emissions is necessary. Moreover, to improve the thermal efficiency of IGCC, hot/dry type synthetic gas clean-up is needed. However, ammonia in the fuel is not removed and is supplied into the gas turbine where fuel-NOx is formed in the combustor. For these reasons, suitable combustion technology for each gasified fuel is important. This paper outlines combustion technologies and combustor designs of the high temperature gas turbine for various IGCCs. Additionally, this paper confirms that further decreases in fuel-NOx emissions can be achieved by removing ammonia from gasified fuels through the application of selective, non-catalytic denitration. From these basic considerations, the performance of specifically designed combustors for each IGCC proved the proposed methods to be sufficiently effective. The combustors were able to achieve strong results, decreasing thermal-NOx emissions to 10 ppm (corrected at 16% oxygen or less, and fuel-NOx emissions by 60% or more, under conditions where ammonia concentration per fuel heating value in unit volume was 2.4 × 102 ppm

  17. Comparison of damping treatments for gas turbine blades

    Science.gov (United States)

    Gordon, Robert W.; Hollkamp, Joseph J.

    1996-05-01

    High frequency vibration of gas turbine fan blades is a high cycle fatigue concern. Friction damping devices are ineffective in suppressing high frequency vibration modes and external damping treatments are plagued by creep concerns. An alternative approach is to apply viscoelastic material internally in the blades. In this paper, an analytical comparison of internal damping treatments for fan blades is presented. The fan blade is modeled as a solid, flat, cantilevered titanium plate. Internal portions are removed producing cavities that are filled with viscoelastic material. Configurations with one, two, and three cavities are modeled using the modal strain energy method in conjunction with finite element analysis to estimate damping. Results show that appreciable damping levels for high frequency modes are possible with stiff viscoelastic material. Other design criteria are also considered. Results indicate that the hydrostatic load from the viscoelastic material on the cavity walls may be a concern.

  18. Ceramics in gas turbines - Powder and process characterization

    Science.gov (United States)

    Dutta, S.

    1977-01-01

    The role of powder and process characterization in producing high quality silicon nitride and silicon carbide components, for gas turbine applications, is described. Some of the intrinsic properties of various forms of Si3N4 and SiC are listed and limitations of such materials' availability have been pointed out. The essential features/parameters to characterize a batch of powder have been discussed including the standard techniques for such characterization. In process characterization, parameters in sintering, reaction sintering, and hot pressing processes are discussed including the factors responsible for strength limitations in ceramic bodies. It is inevitable that significant improvements in material properties can be achieved by reducing or eliminating the strength limiting factors with consistent powder and process characterization along with process control.

  19. Degradation of gas turbine coatings and life assessment

    Energy Technology Data Exchange (ETDEWEB)

    Cheruvu, N.S. [Southwest Research Institute, San Antonio, TX (United States)

    1998-12-31

    MCrAlY coatings are widely used on hot section components of gas turbines to provide hot corrosion and/or oxidation protection by formation of an oxide layer on the surface. As the protective oxide scale exfoliates during service, aluminum from the coating diffuses outward for reformation of the protective scale. Aluminum may also diffuse inward due to the differences in composition between the coating and the substrate. Thus, the coatings degrade due to oxidation, oxide scale spallation, and inward and outward diffusion of aluminum. Service life of these coatings is controlled by the aluminum content in the coating, operating temperature and start- shutdown cycles. In-service degradation of CoCrAlY and CoNiCrAlY coatings is presented. A procedure to predict the remaining service life of coatings under oxidizing conditions is discussed. (orig.) 12 refs.

  20. Recuperated atmosphere SOFC/gas turbine hybrid cycle

    Science.gov (United States)

    Lundberg, Wayne

    2010-08-24

    A method of operating an atmospheric-pressure solid oxide fuel cell generator (6) in combination with a gas turbine comprising a compressor (1) and expander (2) where an inlet oxidant (20) is passed through the compressor (1) and exits as a first stream (60) and a second stream (62) the first stream passing through a flow control valve (56) to control flow and then through a heat exchanger (54) followed by mixing with the second stream (62) where the mixed streams are passed through a combustor (8) and expander (2) and the first heat exchanger for temperature control before entry into the solid oxide fuel cell generator (6), which generator (6) is also supplied with fuel (40).

  1. NDE of titanium alloy MMC rings for gas turbine engines

    Energy Technology Data Exchange (ETDEWEB)

    Baaklini, G.Y.; Percival, L.D.; Yancey, R.N.; Kautz, H.E.

    1993-09-01

    Progress in the processing and fabrication of metal matrix composites (MMC's) requires appropriate mechanical and nondestructive testing methods. These methods are needed to characterize properties, assess integrity, and predict the life of engine components such as compressor rotors, blades, and vanes. Capabilities and limitations of several state-of-the-art nondestructive evaluation (NDE) technologies are investigated for characterizing titanium MMC rings for gas turbine engines. The use of NDE technologies such as x-ray computed tomography, radiography, and ultrasonics in identifying fabrication-related problems that caused defects in components is examined. Acousto-ultrasonics was explored to assess degradation of material mechanical properties by using stress wave factor and ultrasonic velocity measurements before and after the burst testing of the rings.

  2. NDE of titanium alloy MMC rings for gas turbine engines

    Science.gov (United States)

    Baaklini, George Y.; Percival, Larry D.; Yancey, Robert N.; Kautz, Harold E.

    1993-01-01

    Progress in the processing and fabrication of metal matrix composites (MMC's) requires appropriate mechanical and nondestructive testing methods. These methods are needed to characterize properties, assess integrity, and predict the life of engine components such as compressor rotors, blades, and vanes. Capabilities and limitations of several state-of-the-art nondestructive evaluation (NDE) technologies are investigated for characterizing titanium MMC rings for gas turbine engines. The use of NDE technologies such as x-ray computed tomography, radiography, and ultrasonics in identifying fabrication-related problems that caused defects in components is examined. Acousto-ultrasonics was explored to assess degradation of material mechanical properties by using stress wave factor and ultrasonic velocity measurements before and after the burst testing of the rings.

  3. Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing

    Energy Technology Data Exchange (ETDEWEB)

    Etemad, Shahrokh [Precision Combustion, Inc., North Haven, CT (United States); Baird, Benjamin [Precision Combustion, Inc., North Haven, CT (United States); Alavandi, Sandeep [Precision Combustion, Inc., North Haven, CT (United States); Pfefferle, William [Precision Combustion, Inc., North Haven, CT (United States)

    2010-04-01

    PCI has developed and demonstrated its Rich Catalytic Lean-burn (RCL®) technology for industrial and utility gas turbines to meet DOE's goals of low single digit emissions. The technology offers stable combustion with extended turndown allowing ultra-low emissions without the cost of exhaust after-treatment and further increasing overall efficiency (avoidance of after-treatment losses). The objective of the work was to develop and demonstrate emission benefits of the catalytic technology to meet strict emissions regulations. Two different applications of the RCL® concept were demonstrated: RCL® catalytic pilot and Full RCL®. The RCL® catalytic pilot was designed to replace the existing pilot (a typical source of high NOx production) in the existing Dry Low NOx (DLN) injector, providing benefit of catalytic combustion while minimizing engine modification. This report discusses the development and single injector and engine testing of a set of T70 injectors equipped with RCL® pilots for natural gas applications. The overall (catalytic pilot plus main injector) program NOx target of less than 5 ppm (corrected to 15% oxygen) was achieved in the T70 engine for the complete set of conditions with engine CO emissions less than 10 ppm. Combustor acoustics were low (at or below 0.1 psi RMS) during testing. The RCL® catalytic pilot supported engine startup and shutdown process without major modification of existing engine controls. During high pressure testing, the catalytic pilot showed no incidence of flashback or autoignition while operating over a wide range of flame temperatures. In applications where lower NOx production is required (i.e. less than 3 ppm), in parallel, a Full RCL® combustor was developed that replaces the existing DLN injector providing potential for maximum emissions reduction. This concept was tested at industrial gas turbine conditions in a Solar Turbines, Incorporated high-pressure (17 atm.) combustion rig and in a modified Solar

  4. Power boost of gas turbines by inlet air cooling

    Energy Technology Data Exchange (ETDEWEB)

    White, C.; Raghu, S. [State Univ. of New York, Stony Brook, NY (United States). Dept. of Mechanical Engineering; Giannotti, G.; Giannotti, H. [Giannotti Associates, Bellport, NY (United States)

    1996-12-31

    The design of a power boost system for an existing gas turbine unit using a direct spray evaporative spray cooling method is described in this paper. Experiments were conducted to determine the extent of cooling possible by this method, droplet size requirements and spray water requirements. Although up to 4.9% of power boost is theoretically possible at the design conditions of 32.2 C (90 F) and 60% relative humidity, various other constraints limit the actual power boost to about 3.8% of the nominal power. For small values of the wet-bulb depression (less than about 5 C or 10 F), the required droplet sizes for complete evaporation become so small (of the order of 5--10 microns with high flow rates) that production of them at the required flow rates is a challenging task.

  5. Thermal barrier coating on high temperature industrial gas turbine engines

    Science.gov (United States)

    Carlson, N.; Stoner, B. L.

    1977-01-01

    The thermal barrier coating used was a yttria stabilized zirconia material with a NiCrAlY undercoat, and the base engine used to establish improvements was the P&WA FT50A-4 industrial gas turbine engine. The design benefits of thermal barrier coatings include simplified cooling schemes and the use of conventional alloys in the engine hot section. Cooling flow reductions and improved heating rates achieved with thermal barrier coating result in improved performance. Economic benefits include reduced power production costs and reduced fuel consumption. Over the 30,000 hour life of the thermal barrier coated parts, fuel savings equivalent to $5 million are projected and specific power (megawatts/mass of engine airflow) improvements on the order of 13% are estimated.

  6. Apparatus and method for gas turbine active combustion control system

    Science.gov (United States)

    Umeh, Chukwueloka (Inventor); Kammer, Leonardo C. (Inventor); Shah, Minesh (Inventor); Fortin, Jeffrey B. (Inventor); Knobloch, Aaron (Inventor); Myers, William J. (Inventor); Mancini, Alfred Albert (Inventor)

    2011-01-01

    An Active Combustion Control System and method provides for monitoring combustor pressure and modulating fuel to a gas turbine combustor to prevent combustion dynamics and/or flame extinguishments. The system includes an actuator, wherein the actuator periodically injects pulsed fuel into the combustor. The apparatus also includes a sensor connected to the combustion chamber down stream from an inlet, where the sensor generates a signal detecting the pressure oscillations in the combustor. The apparatus controls the actuator in response to the sensor. The apparatus prompts the actuator to periodically inject pulsed fuel into the combustor at a predetermined sympathetic frequency and magnitude, thereby controlling the amplitude of the pressure oscillations in the combustor by modulating the natural oscillations.

  7. Turbofan gas turbine engine with variable fan outlet guide vanes

    Science.gov (United States)

    Wood, Peter John (Inventor); Zenon, Ruby Lasandra (Inventor); LaChapelle, Donald George (Inventor); Mielke, Mark Joseph (Inventor); Grant, Carl (Inventor)

    2010-01-01

    A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.

  8. Development of impact design methods for ceramic gas turbine components

    Science.gov (United States)

    Song, J.; Cuccio, J.; Kington, H.

    1990-01-01

    Impact damage prediction methods are being developed to aid in the design of ceramic gas turbine engine components with improved impact resistance. Two impact damage modes were characterized: local, near the impact site, and structural, usually fast fracture away from the impact site. Local damage to Si3N4 impacted by Si3N4 spherical projectiles consists of ring and/or radial cracks around the impact point. In a mechanistic model being developed, impact damage is characterized as microcrack nucleation and propagation. The extent of damage is measured as volume fraction of microcracks. Model capability is demonstrated by simulating late impact tests. Structural failure is caused by tensile stress during impact exceeding material strength. The EPIC3 code was successfully used to predict blade structural failures in different size particle impacts on radial and axial blades.

  9. Gas Turbine Engine Component Development : An Integrated Approach

    Directory of Open Access Journals (Sweden)

    Willem Jansen

    1988-10-01

    Full Text Available Computer - aided engineering methods have made a significant impact in the design technologies of advanced machinery. These methods have been applied in several areas such as aerodynamics and fluid dynamic theory for high efficiency, stress and vibration theory for reliability, and manufacturing strategies to produce machined components at low cost and with short time schedules. The integration of these various design technologies offer the opportunity for even greater productivity in the engineering design and manufacturing process. This paper addresses the application of various engineering disciplines to the demand of producing a reliable, efficient design and the subsequent manufacture of components with short lead times through the interaction of these computer - aided engineering technologies. The concept is further illustrated by simple cases for a centrifugal compressor and a gas turbine.

  10. Gas turbine nozzle vane insert and methods of installation

    Science.gov (United States)

    Miller, William John; Predmore, Daniel Ross; Placko, James Michael

    2002-01-01

    A pair of hollow elongated insert bodies are disposed in one or more of the nozzle vane cavities of a nozzle stage of a gas turbine. Each insert body has an outer wall portion with apertures for impingement-cooling of nozzle wall portions in registration with the outer wall portion. The insert bodies are installed into the cavity separately and spreaders flex the bodies toward and to engage standoffs against wall portions of the nozzle whereby the designed impingement gap between the outer wall portions of the insert bodies and the nozzle wall portions is achieved. The spreaders are secured to the inner wall portions of the insert bodies and the bodies are secured to one another and to the nozzle vane by welding or brazing.

  11. The ISO 9001 combined cycle gas turbine power station

    Energy Technology Data Exchange (ETDEWEB)

    Copeland, C. [Enron Power Operations Ltd., Middlesborough (United Kingdom)

    2000-07-01

    Enron Power Operations Limited is believed to be one of the first organisations to achieve BS EN ISO9001: 1994 for an Operational Combined Cycle Gas Turbine Power Station. In 1997 the Power Station decided to re-create policies and procedures to fill in the unknown gaps in its array of policies and procedures. The creation of the Quality Management System was expected to take six months utilising limited resources and the experiences of operational staff. Initial checks and internal audits created a wealth of information and highlighted some significant short falls, once certification was gained further issues have been noted. This paper concerns the development, implementation and certification of the Quality Management System at Teesside Power Station showing some benefits noted during this period and the short period after certification. Any other improvements and benefits will come in the future during continued development of the system. (author)

  12. Corrosion-resistant nickel-base alloys for gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Schultz, J.W.; Hulsizer, W.R.

    1976-08-01

    Laboratory corrosion screening procedures used during the past ten years in developing nickel-base superalloys for gas turbine applications are described. Hot salt corrosion tests have included crucible and salt shower exposures. Reproducible techniques were established and alloy composition effects defined, leading to development of M313, IN-587, a IN-792. Correlations have been made with corrosion results in burner rigs, and engine experience confirming anticipated behavior is now becoming available. During this work a number of limitations of these accelerated laboratory tests were uncovered; these are discussed. Finally, brief descriptions of the states of development of alloy MA 755E (an oxide dispersion-strengthened superalloy) and IN-939 (a cast 23 percent chromium superalloy) are outlined as examples of advanced corrosion resistant, high strength materials of the future.

  13. Final report on EURAMET.QM-S10/1274: supplementary comparison of preparative capabilities for automotive gas mixtures

    Science.gov (United States)

    Val'ková, M.; Ďurišová, Z.; Szilágyi, Z. N.; Büki, T.; Fükű, J.

    2016-01-01

    This bilateral supplementary preparative comparison involves standard gas mixtures of automotive gas containing carbon monoxide, carbon dioxide and propane in nitrogen. Two laboratories (SMU, Slovakia and MKEH, Hungary) participated in this supplementary comparison. SMU was the coordinating laboratory, responsible for collecting and reporting measurement results. The participants have established facilities for automotive gas gravimetric preparation and analysis. The agreement of the results in this supplementary comparison is good. All the results with their reported uncertainties are in agreement with the reference values for the participants. SMU participated and obtained good results in the previous preparative comparison organised within EURAMET in this field. Both laboratories have existing claims for their Calibration and Measurement Capabilities (CMCs) for automotive gas mixtures. Main text To reach the main text of this paper, click on Final Report. Note that this text is that which appears in Appendix B of the BIPM key comparison database kcdb.bipm.org/. The final report has been peer-reviewed and approved for publication by the CCQM, according to the provisions of the CIPM Mutual Recognition Arrangement (CIPM MRA).

  14. Investigation into the thermodynamic suitability of a commercial turbocharger for use in a micro gas-turbine / David Tertius Landsberg

    OpenAIRE

    Landsberg, David Tertius

    2006-01-01

    Micro gas-turbines are expanding to be much more prevalent in the power generating market. They are merely scaled down versions of their larger siblings, gas-turbines powering commercial airplanes on generating megawatts of electrical energy throughout the world. The basic components of a micro gas-turbine and that of a turbocharger unit on internal combustion engines are quite similar. Both have a compressor, a heat source and a turbine. This study investigates the possibility...

  15. Parametric Analysis of a Two-Shaft Aeroderivate Gas Turbine of 11.86 MW

    Directory of Open Access Journals (Sweden)

    R. Lugo-Leyte

    2015-08-01

    Full Text Available The aeroderivate gas turbines are widely used for power generation in the oil and gas industry. In offshore marine platforms, the aeroderivative gas turbines provide the energy required to drive mechanically compressors, pumps and electric generators. Therefore, the study of the performance of aeroderivate gas turbines based on a parametric analysis is relevant to carry out a diagnostic of the engine, which can lead to operational as well as predictive and/or corrective maintenance actions. This work presents a methodology based on the exergetic analysis to estimate the irrevesibilities and exergetic efficiencies of the main components of a two-shaft aeroderivate gas turbine. The studied engine is the Solar Turbine Mars 100, which is rated to provide 11.86 MW. In this engine, the air is compressed in an axial compressor achieving a pressure ratio of 17.7 relative to ambient conditions and a high pressure turbine inlet temperature of 1220 °C. Even if the thermal efficiency associated to the pressure ratio of 17.7 is 1% lower than the maximum thermal efficiency, the irreversibilities related to this pressure ratio decrease approximately 1 GW with respect to irreversibilities of the optimal pressure ratio for the thermal efficiency. In addition, this paper contributes to develop a mathematical model to estimate the high turbine inlet temperature as well as the pressure ratio of the low and high pressure turbines.

  16. Topping gas turbines improve steam power plant efficiency

    Energy Technology Data Exchange (ETDEWEB)

    Lezuo, A. (Siemens AG, Erlangen (Germany, F.R.). KWU Group)

    An interesting option for improving the efficiency and output of an existing conventional steam power plant is to convert it into a combined steam-and-gas cycle power plant by adding a topping gas turbine. The investment involved is relatively low, the payback period is short, and the low specific fuel consumption makes it possible to save on overall running costs. At the same time, the amount of residue for disposal and also pollutant emissions are drastically reduced. This article describes the configuration of a fully-fired combined-cycle power plant and discusses thermodynamic design and efficiency, operational aspects, emissions and residues and investment and economic viability. Both coal-fired and gas or oil-fired steam power plants can be converted by adding a topping cycle and the investment cost is about 20% of the cost of a new plant with the same output rating as the plant to be converted. Conversion reduces pollutant emission and residues produced (SO{sub 2}, NO{sub x}, CO{sub 2}, dust, ash, gypsum, waste heat). 4 figs.

  17. Design analysis and development of a high temperature actuaror for gas turbine blade tip clearance control

    OpenAIRE

    Coşkun, Mustafa Bulut; Coskun, Mustafa Bulut

    2011-01-01

    During a typical startup cycle industrial gas turbine blades experience rapid radial thermal expansion while bulky shroud structure with larger thermal inertia requires much longer period to reach its operating temperature. Turbine designers have to leave a safe radial distance in order to prevent contact of blades to the surrounding annular casing. However, when thermal steady state in the turbine stage is achieved, shroud and casing grow and excessive amount of blade-shroud clearance remain...

  18. Optimization of micro combined heat and power gas turbine by genetic algorithm

    OpenAIRE

    Yazdi Behnam Ahrar; Yazdi Behdad Ahrar; Ehyaei Mehdi Ali; Ahmadi Abolfazl

    2015-01-01

    In this paper, a comprehensive thermodynamic modeling and multi-objective optimization of a micro turbine cycle in combined heat and power generation, which provides 100KW of electric power. This CHP System is composed of air compressor, combustion chamber (CC), Air Preheater, Gas Turbine (GT) and a Heat Recovery Heat Exchanger. In this paper, at the first stage, the each part of the micro turbine cycle is modeled using thermodynamic laws. Next, with using ...

  19. Design and Analysis of Gas Turbine Blade by Potential Flow Approach

    OpenAIRE

    V. Vijaya Kumar,; R. Lalitha Narayana

    2014-01-01

    The design features of the turbine segment of the gas turbine have been taken from the “preliminary design of a power turbine for maximization of an existing turbojet engine”. It was observed that in the above design, after the rotor blades being designed they were analyzed only for the mechanical stresses. As the temperature has a significant effect on the overall stress in the rotor blades, a detailed study is carried out on the temperature effects to have a clear understand...

  20. Artificial neural networks for monitoring the gas turbine; Artificiella neuronnaet foer gasturbinoevervakning

    Energy Technology Data Exchange (ETDEWEB)

    Fast, Magnus; Thern, Marcus [Inst. foer Energivetenskaper, Lunds Univ. (Sweden)

    2011-10-15

    Through available historical operational data from gas turbines, fast, accurate, easy to use and reliable models can be developed. These models can be used for monitoring of gas turbines and assist in the transition from today's time-based maintenance to condition based maintenance. For the end user this means that, because only operational data is needed, they can easily develop their own tools independent of the manufacturer. Traditionally these types of models are constructed with physical relations for e.g., mass, energy and momentum. To develop a model with physical relations is often laborious and requires classified information which the end user does not have access to. Research has shown that by producing models using operational data a very high model precision can be achieved. When implementing these models in a power plant computer system the gas turbine's performance can be monitored in real time. This can facilitate fault detection at an early stage, and if necessary, stop the gas turbine before major damage occurs. For the power plant owner, this means that the gas turbine reliability is increased since the need for maintenance is minimized and the downtime is reduced. It also means that a measure of the gas turbine's overall status is continuously available, with respect to e.g. degradation, which helps in the planning of service intervals. The tool used is called artificial neural networks (ANN), a collective name for a number of algorithms for information processing that attempts to mimic the nerve cell function. Just like real networks of neurons in a brain, these artificial neural networks have the ability to learn. In this case, neural networks are trained to mimic the behavior of gas turbines by introducing them to data from real gas turbines. After a neural network is trained it represents a very accurate model of the gas turbine that it is trained to emulate.

  1. Performance of gas turbines in Russia under the changing climatic conditions

    Science.gov (United States)

    Klimenko, V. V.; Klimenko, A. V.; Kasilova, E. V.; Rekunenko, E. S.; Tereshin, A. G.

    2016-10-01

    The impact of the expected climatic changes on the performance of gas turbine units (GTU) as part of the power industry and gas pipeline network in Russia is considered. Long-term estimates of changes in the average annual air temperature throughout the country are made based on the authors' model. The calculations using the efficiency value of gas turbine units as a function of the ambient air temperature show that climatic changes will significantly deteriorate the operational efficiency of gas-turbine equipment in practically all of Russia's regions. Based on publicly available statistical data, we assessed the installed capacity of gas-turbine power stations (including combined-cycle power plants) and gas-turbine drive of gas pipeline network. Three development scenarios have been considered for gas turbine power in the national electric power industry, differing in the rates of new facilities' commissioning. Integrated estimates have been made of the increase in gas consumption in Russia's gas pipeline network and power industry resulting from climatic changes by 2030 and 2050. It is shown that the total increase in the annual gas consumption associated with a reduction in the efficiency of gas turbine units due to climate warming by 2030 could reach approximately 130000 tce (of which approximately 90000 tce in the gas pipeline network and 40000 tce in the electric power industry) and more than 170000 tce (120000 and 50000 tce, respectively) by 2050. Should more optimistic scenarios be implemented for the development of the electric power industry, this effect will increase 1.5-2.0 times by 2050. Despite high absolute values, the increase in GTU fuel expenditures due to higher ambient temperatures resulting from climate change in Russia will only amount to a fraction of a percent of the total gas consumption and will be two orders of magnitude lower than the savings in space heating.

  2. Thermodynamic analysis for a regenerative gas turbine cycle in coking process

    OpenAIRE

    Zelong Zhang, Lingen Chen, Fengrui Sun

    2014-01-01

    A regenerative gas turbine cycle driven by residual coke oven gas is proposed in this paper. The thermal efficiency and the work output (per ton of coke) of the system are analyzed based on thermodynamics and the theory of gas turbine cycle. The influences of the gas release rate, the residual gas rate and the effectiveness of regenerator on the performance of the cycle are analyzed by using numerical examples. It is found that the work output increases with the increase of the residual gas r...

  3. Lean-rich axial stage combustion in a can-annular gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Laster, Walter R.; Szedlacsek, Peter

    2016-06-14

    An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.

  4. Gas turbine modular helium reactor in cogeneration; Turbina de gas reactor modular con helio en cogeneracion

    Energy Technology Data Exchange (ETDEWEB)

    Leon de los Santos, G. [UNAM, Facultad de Ingenieria, Division de Ingenieria Electrica, Departamento de Sistemas Energeticos, Ciudad Universitaria, 04510 Mexico, D. F. (Mexico)], e-mail: tesgleon@gmail.com

    2009-10-15

    This work carries out the thermal evaluation from the conversion of nuclear energy to electric power and process heat, through to implement an outline gas turbine modular helium reactor in cogeneration. Modeling and simulating with software Thermo flex of Thermo flow the performance parameters, based on a nuclear power plant constituted by an helium cooled reactor and helium gas turbine with three compression stages, two of inter cooling and one regeneration stage; more four heat recovery process, generating two pressure levels of overheat vapor, a pressure level of saturated vapor and one of hot water, with energetic characteristics to be able to give supply to a very wide gamma of industrial processes. Obtaining a relationship heat electricity of 0.52 and efficiency of net cogeneration of 54.28%, 70.2 MW net electric, 36.6 MW net thermal with 35% of condensed return to 30 C; for a supplied power by reactor of 196.7 MW; and with conditions in advanced gas turbine of 850 C and 7.06 Mpa, assembly in a shaft, inter cooling and heat recovery in cogeneration. (Author)

  5. Analysis on Service Life of Hot-end Components of Gas Turbine Using Equivalent Operation

    Directory of Open Access Journals (Sweden)

    Taixing Wang

    2013-01-01

    Full Text Available The reliability of the gas turbine depends on the technical status and the maintenance level of the hot-end components in a large part.The three main factors influencing on the service life of the hot-end components of the gas turbine were analyzed first.On this basis,various common service life assessment methods for gas turbine were discussed in detail.Aiming at the features of the M701F gas-steam combined cycle unit in Huizhou LNG power plant,a gas turbine life assessment method based on equivalent operation time analysis was put forward.The calculation result of an example shows that the equivalent operation time analysis method is a simple and practical assessment method.

  6. Development of superalloys for 1700 C ultra-efficient gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Harada, Hiroshi [National Institute for Materials Science, Tsukuba, Ibaraki (Japan). High Temperature Materials Center

    2010-07-01

    Mitigation of global warming is one of the most outstanding issues for the humankind. The Japanese government announced that it will reduce its greenhouse gas emissions by 25% from the 1990 level by 2020 as a medium-term goal. One of the promising approaches to achieving this is to improve the efficiency of thermal power plants emitting one-third of total CO{sub 2} gas in Japan. The key to improving the thermal efficiency is high temperature materials with excellent temperature capabilities allowing higher inlet gas temperatures. In this context, new single crystal superalloys for turbine blades and vanes, new coatings and turbine disk superalloys have been successfully developed for various gas turbine applications, typically 1700 C ultra-efficient gas turbines for next generation combine cycle power plants. (orig.)

  7. Fuel flexibility via real-time Raman fuel-gas analysis for turbine system control

    Science.gov (United States)

    Buric, M.; Woodruff, S.; Chorpening, B.; Tucker, D.

    2015-06-01

    The modern energy production base in the U.S. is increasingly incorporating opportunity fuels such as biogas, coalbed methane, coal syngas, solar-derived hydrogen, and others. In many cases, suppliers operate turbine-based generation systems to efficiently utilize these diverse fuels. Unfortunately, turbine engines are difficult to control given the varying energy content of these fuels, combined with the need for a backup natural gas supply to provide continuous operation. Here, we study the use of a specially designed Raman Gas Analyzer based on capillary waveguide technology with sub-second response time for turbine control applications. The NETL Raman Gas Analyzer utilizes a low-power visible pump laser, and a capillary waveguide gas-cell to integrate large spontaneous Raman signals, and fast gas-transfer piping to facilitate quick measurements of fuel-gas components. A U.S. Department of Energy turbine facility known as HYPER (hybrid performance system) serves as a platform for apriori fuel composition measurements for turbine speed or power control. A fuel-dilution system is used to simulate a compositional upset while simultaneously measuring the resultant fuel composition and turbine response functions in real-time. The feasibility and efficacy of system control using the spontaneous Raman-based measurement system is then explored with the goal of illustrating the ability to control a turbine system using available fuel composition as an input process variable.

  8. Prospective gas turbine and combined-cycle units for power engineering (a Review)

    Science.gov (United States)

    Ol'khovskii, G. G.

    2013-02-01

    The modern state of technology for making gas turbines around the world and heat-recovery combined-cycle units constructed on their basis are considered. The progress achieved in this field by Siemens, Mitsubishi, General Electric, and Alstom is analyzed, and the objectives these companies set forth for themselves for the near and more distant future are discussed. The 375-MW gas turbine unit with an efficiency of 40% produced by Siemens, which is presently the largest one, is subjected to a detailed analysis. The main specific features of this turbine are that the gas turbine unit's hot-path components have purely air cooling, due to which the installation has enhanced maneuverability. The single-shaft combined-cycle plant constructed on the basis of this turbine has a capacity of 570 MW and efficiency higher than 60%. Programs adopted by different companies for development of new-generation gas turbine units firing synthesis gas and fitted with low-emission combustion chambers and new cooling systems are considered. Concepts of rotor blades for new gas turbine units with improved thermal barrier coatings and composite blades different parts of which are made of materials selected in accordance with the conditions of their operation are discussed.

  9. Maintenance optimization of a gas turbine power plant; Optimisation de la maintenance d'une tranche turbine a combustion

    Energy Technology Data Exchange (ETDEWEB)

    Despujols, A. [Electricite de France (EDF), 93 - Saint-Denis (France). Dept. Surveillance, Diagnostic, Maintenance; Meillant, J.P. [Electricite de France (EDF), 93 - Saint-Denis (France). Div. Productions Thermiques et Hydrauliques

    1999-10-01

    A Reliability Centred Maintenance (RCM) analysis has been applied by EDF to 123 MW gas turbines. This study enabled to define a complete preventive maintenance programme adapted to the specific operating conditions of these plants to ensure a high availability level at the lower cost. (author)

  10. Proven reliability of the gas-turbine engine. BIPS Phase 1

    Energy Technology Data Exchange (ETDEWEB)

    1976-11-01

    The background, capabilities and experience of the Garrett Corp. in designing, developing, manufacturing and testing gas turbines and related systems are described, and the requirements for and components of the Brayton Isotope Power System (BIPS) for space vehicles are outlined. Data on the compressor and turbine, alternator, bearings, recuperator, radiator, heat source assembly, and control systems are presented. (LCL)

  11. The gas turbine: Present technology and future developments; La turbina a gas: Tecnologie attuali e gli sviluppi futuri

    Energy Technology Data Exchange (ETDEWEB)

    Minghetti, E. [ENEA, Centro Ricerche Casaccia, Rome (Italy)

    1997-03-01

    The gas turbine is the most widely used prime mover all over the world for either power generation or mechanical drive applications. The above fact is due to the recent great improvements that have been done especially in terms of efficiency, availability and reliability. The future for gas turbine technological development looks very promising. In fact, although tremendous growth has already taken place, there is still the potential for dramatic improvements in performance. Compared with the competitive prime movers (conventional steam power plants and reciprocating piston engines) the gas turbine technology is younger and still following a strong growth curve. The coming decades will witness the continued increasing in turbine inlet temperature, the development of new materials and refrigeration systems and the commercialization of inter cooled system and steam cooled turbines. With the very soon introduction of the {sup G }and {sup H }technology, expected single and combined cycle efficiencies for heavy duty machines are respectively 40% and 60%, while maintaining single digit levels in pollutant emissions. In this report are given wide information on gas turbine present technology (Thermodynamics, features, design, performances, emission control, applications) and are discussed the main lines for the future developments. Finally are presented the research and technological development activities on gas turbine of Italian National Agency for new Technology Energy and the Environment Energy Department.

  12. BIOMASS GASIFICATION AND POWER GENERATION USING ADVANCED GAS TURBINE SYSTEMS

    Energy Technology Data Exchange (ETDEWEB)

    David Liscinsky

    2002-10-20

    A multidisciplined team led by the United Technologies Research Center (UTRC) and consisting of Pratt & Whitney Power Systems (PWPS), the University of North Dakota Energy & Environmental Research Center (EERC), KraftWork Systems, Inc. (kWS), and the Connecticut Resource Recovery Authority (CRRA) has evaluated a variety of gasified biomass fuels, integrated into advanced gas turbine-based power systems. The team has concluded that a biomass integrated gasification combined-cycle (BIGCC) plant with an overall integrated system efficiency of 45% (HHV) at emission levels of less than half of New Source Performance Standards (NSPS) is technically and economically feasible. The higher process efficiency in itself reduces consumption of premium fuels currently used for power generation including those from foreign sources. In addition, the advanced gasification process can be used to generate fuels and chemicals, such as low-cost hydrogen and syngas for chemical synthesis, as well as baseload power. The conceptual design of the plant consists of an air-blown circulating fluidized-bed Advanced Transport Gasifier and a PWPS FT8 TwinPac{trademark} aeroderivative gas turbine operated in combined cycle to produce {approx}80 MWe. This system uses advanced technology commercial products in combination with components in advanced development or demonstration stages, thereby maximizing the opportunity for early implementation. The biofueled power system was found to have a levelized cost of electricity competitive with other new power system alternatives including larger scale natural gas combined cycles. The key elements are: (1) An Advanced Transport Gasifier (ATG) circulating fluid-bed gasifier having wide fuel flexibility and high gasification efficiency; (2) An FT8 TwinPac{trademark}-based combined cycle of approximately 80 MWe; (3) Sustainable biomass primary fuel source at low cost and potentially widespread availability-refuse-derived fuel (RDF); (4) An overall integrated

  13. Baseline Gas Turbine Development Program sixth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Wagner, C.E.

    1974-04-30

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1976 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. Engines were built to replace those originally loaned to the Program. Efforts to identify and correct a general power deficiency were generally successful. The third baseline vehicle was built and checked out. Baseline vehicle emissions, performance, fuel consumption, and noise tests were run. Chrysler's proprietary linerless insulation showed no significant distress following 300 hours of engine endurance testing. An improved elastomeric drive for ceramic regenerators was developed on the regenerator rig. Preparations are being made for engine testing. The Ai Research engine simulation model is operational and control system concepts are being studied. Operation of the preprototype fuel system was verified on an engine. All other key preprototype system elements were bench checked. Variable inlet guide vane testing and development and torque converter lock-up evaluation tests are in process. A free rotor engine arrangement for vehicle evaluation and development is being built. Initial specifications were completed for a 122 horsepower, compact vehicle upgraded engine. NASA completed initial specifications for the gas generator aerodynamics. Overall engine and engine housing layout studies are being made.

  14. Pyrolysis of automotive shredder residue for the production of fuel-grade gas

    International Nuclear Information System (INIS)

    Every year eight to ten million cars and trucks are disposed of by shredding at one of the 200 auto shredders located in the United States. Automotive shredder residue (ASR) is a by-product created in the dismantling of automobiles. Figure 1 illustrates the process by which ASR is generated. An automobile is stripped of useful and/or hazardous items, such as the gas tank, battery, tires, and radiator. Although it is beneficial to have these items removed for safety and environmental concerns, this is not always accomplished. After removal of some or all of these items, the automobile is shredded to provide a material less than 4 inches in size and composed of approximately 50% organic and 50% inorganic fractions. Ferrous scrap is then separated out magnetically. This ferrous scrap supplies the steel industry with 12 to 14 million tons per year for electric arc furnace feedstock. Air cyclone separators isolate a low density open-quotes fluffclose quotes from the nonferrous fraction (aluminum, copper, etc.). This fluff (shredder residue) is composed of a variety of plastics, fabrics, foams, glass, rubber, and an assortment of contaminants. Fluff bulk density is approximately 20 lb/ft

  15. Baseline Gas Turbine Development Program eighth quarterly progress report

    Energy Technology Data Exchange (ETDEWEB)

    Schmidt, C.E.

    1974-10-31

    Progress is reported for a program to demonstrate by 1976 an experimental gas turbine powered automobile which meets the 1978 Federal Emissions Standards, has significantly improved fuel economy, and is competitive in performance, reliability, and potential manufacturing cost with the conventional piston engine powered, standard size American automobile. Major preparations for engine heat balance tests by NASA were completed. EPA laboratories completed Baseline vehicle emissions, noise, and odor tests. Assembly of the program endurance engine is nearing completion. Test cell evaluation of the government furnished combustor (Solar) verified steady state emissions to be extremely low. Initial engine tests of Vendor A ceramic regenerator cores with an elastomeric drive verified performance predictions. Efforts towards developing a non-nickel oxide regenerator seal show extreme sensitivity to porosity differences between cores of different suppliers. All three preprototype integrated control systems were built. Modifications are being worked out to achieve a stable low speed operation. Two prototype compressor turbine wheels made from the reuseable pattern process are being inspected and processed for testing. The engine housing modified for operation at higher cycle temperatures and pressures was received. The baseline engine converted to free rotor is completing test cell check out. The modified vehicle is ready for engine installation. The upgraded engine characterization was updated to include the latest information on V.I.G.V., rotors, and bearings. The upgraded engine housing is being modeled physically and analytically for design and stress studies. An accessory drive system for the upgraded engine was selected, and a final layout is in process.

  16. Performance of a Line Loss Correction Method for Gas Turbine Emission Measurements

    Science.gov (United States)

    Hagen, D. E.; Whitefield, P. D.; Lobo, P.

    2015-12-01

    International concern for the environmental impact of jet engine exhaust emissions in the atmosphere has led to increased attention on gas turbine engine emission testing. The Society of Automotive Engineers Aircraft Exhaust Emissions Measurement Committee (E-31) has published an Aerospace Information Report (AIR) 6241 detailing the sampling system for the measurement of non-volatile particulate matter from aircraft engines, and is developing an Aerospace Recommended Practice (ARP) for methodology and system specification. The Missouri University of Science and Technology (MST) Center for Excellence for Aerospace Particulate Emissions Reduction Research has led numerous jet engine exhaust sampling campaigns to characterize emissions at different locations in the expanding exhaust plume. Particle loss, due to various mechanisms, occurs in the sampling train that transports the exhaust sample from the engine exit plane to the measurement instruments. To account for the losses, both the size dependent penetration functions and the size distribution of the emitted particles need to be known. However in the proposed ARP, particle number and mass are measured, but size is not. Here we present a methodology to generate number and mass correction factors for line loss, without using direct size measurement. A lognormal size distribution is used to represent the exhaust aerosol at the engine exit plane and is defined by the measured number and mass at the downstream end of the sample train. The performance of this line loss correction is compared to corrections based on direct size measurements using data taken by MST during numerous engine test campaigns. The experimental uncertainty in these correction factors is estimated. Average differences between the line loss correction method and size based corrections are found to be on the order of 10% for number and 2.5% for mass.

  17. Technical and economic analysis of steam-injected gas-turbine cogeneration

    Science.gov (United States)

    Larson, Eric D.; Williams, Robert H.

    1985-11-01

    Industrial cogeneration is gaining popularity as an energy and money saving alternative to separate steam and electricity generation. Among cogeneration technologies, gas-turbine systems are attractive largely because of their lower capital cost and high thermodynamic efficiency. However, at industrial plants where steam and electricity loads vary daily, seasonally, or unpredictably, the economics of conventional gas turbines are often unfavorable due to low capacity utilization. Steam-injected gas-turbine cogeneration overcomes the part-load problem by providing for excess steam to be injected back into the turbine to raise electrical output and generating efficiency. Under provisions of the Public Utilities Regulatory Policies Act, any excess electricity can be sold to the local grid at the prevailing avoided cost of electricity. Steam-injected gas-turbine cogeneration can result in a consistently high rate of return on investment over a wide range of variation in process steam loads. Moreover, this technology can also give rise to greater annual electricity production and fuel savings per unit of process steam generated, compared to simple-cycle cogeneration, making the technology attractive from the perspective of society, as well as that of the user. Steam-injected gas-turbines may soon find applications in electric utility base-load generation, as well, since it appears that electrical generating efficiencies in excess of 50% can be obtained from turbines producing of the order of 100 MW of electricity at a fully-installed capital cost as low as 500/kW.

  18. Making aerospace technology work for the automotive industry - Introduction

    Science.gov (United States)

    Olson, W. T.

    1978-01-01

    In many cases it has been found that advances made in one technical field can contribute to other fields. An investigation is in this connection conducted concerning subjects from contemporary NASA programs and projects which might have relevance and potential usefulness to the automotive industry. Examples regarding aerospace developments which have been utilized by the automotive industry are related to electronic design, computer systems, quality control experience, a NASA combustion scanner and television display, exhaust gas analyzers, and a device for suppressing noise propagated through ducts. Projects undertaken by NASA's center for propulsion and power research are examined with respect to their value for the automotive industry. As a result of some of these projects, a gas turbine engine and a Stirling engine might each become a possible alternative to the conventional spark ignition engine.

  19. Cooling of Gas Turbines. 6; Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

    Science.gov (United States)

    Livingood, John N. B.; Sams, Eldon W.

    1947-01-01

    A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to -metal heat transfer coefficient, and of the effect of changing the thermal conductivity of the blade metal for a constant cross sectional area blade with two quarter inch diameter coolant passages.

  20. A Physics-Based Starting Model for Gas Turbine Engines Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The objective of this proposal is to demonstrate the feasibility of producing an integrated starting model for gas turbine engines using a new physics-based...

  1. Development of technology of nitride films manufacture for blades of gas turbine engines

    Directory of Open Access Journals (Sweden)

    С.Р. Ігнатович

    2004-02-01

    Full Text Available  Films of TiN on compressor blades of gas turbine engines are considered. Films are obtained with using plasma jet coater of capillary pulse-periodical plasmatrone. Diagnostics of films surface are performed.

  2. Robust High Fidelity Large Eddy Simulation Tool for Gas Turbine Combustors Project

    Data.gov (United States)

    National Aeronautics and Space Administration — The objective is to develop and demonstrate the use of Large Eddy Simulation (LES) for computations of gas turbine combustor flow and transport processes, using the...

  3. Study of an exhaust gas recirculation equipped micro gas turbine supplied with bio-fuels

    International Nuclear Information System (INIS)

    The authors discuss in this paper some aspects related to the employment of liquid and gaseous bio-fuels in a micro-gas turbine. Besides the purpose of checking the effectiveness of methods for supplying the micro-turbine with fuels from renewable sources, the attention is focused on the need of controlling the pollutant emission. To this aim, several solutions are experienced and numerically tested. For the liquid fuel supply, a new shape and location of the main fuel injector is combined with a modified position of the pilot injector. In the case of the biogas fuelling, an external EGR option is considered as activated. Both methods aim at the reduction of the thermal and prompt NO formation by approaching the flameless combustion concept. -- Highlights: • External and internal EGR concepts applied to NOx control from micro gas turbines. • For gaseous fuels: internal EGR is obtained by a proper location of the pilot injector. • For liquid fuels: replacing the original radial injectors with a pressure swirl atomizer. • We apply a CFD based method, after validation with experimental data. • Blends of bio-fuels with fossil fuels promise noticeable benefits

  4. Effective energy management by combining gas turbine cycles and forward osmosis desalination process

    International Nuclear Information System (INIS)

    Highlights: • Innovative gas turbine system and FO integrated system was proposed. • The feasibility of the integrated system was analyzed thermodynamically. • GOR of the FO–gas turbine system is 17% higher than those of MED and MSF. • Waste heat utilization of the suggested system is 85.7%. • Water production capacity of the suggested system is 3.5 times higher than the MSF–gas turbine system. - Abstract: In the recent years, attempts to improve the thermal efficiency of the gas turbine cycles have been made. In order to enhance the energy management of the gas turbine cycle, a new integration concept has been proposed; integration of gas turbine cycle and forward osmosis desalination process. The combination of the gas turbine cycle and the forward osmosis (FO) desalination process basically implies the coupling of the waste heat from the gas turbine cycle to the draw solute recovery system in the FO process which is the most energy consuming part of the whole FO process. By doing this, a strong system that is capable of producing water and electricity with very little waste heat can be achieved. The feasibility of this newly proposed system was analyzed using UNISIM program and the OLI property package. For the analysis, the thermolytic draw solutes which has been suggested by other research groups have been selected and studied. Sensitivity analysis was conducted on the integration system in order to understand and identify the key parameters of the integrated system. And the integrated system was further evaluated by comparing the gain output ratio (GOR) values with the conventional desalination technologies such as multi stage flash (MSF) and multi effect distillation (MED). The suggested integrated system was calculated to have a GOR of 14.8, while the MSF and MED when integrated to the gas turbine cycle showed GOR value of 12. It should also be noted that the energy utilization of the suggested integrated system is significantly higher by 27

  5. Dual-fuelling of a direct-injection automotive diesel engine by diesel and compressed natural gas

    International Nuclear Information System (INIS)

    Application of Compressed Natural Gas in diesel engines has always been important, especially in the field of automotive engineering. This is due to easy accessibility, better mixing quality and good combustion characteristics of the Compressed Natural Gas fuel. In this study the application of Compressed Natural Gas fuel along with diesel oil in a heavy duty direct-injection automotive diesel engine is experimentally investigated. In order to convert a diesel engine into a diesel-gas one, the so called mixed diesel-gasapproach has been used and for this purpose a carbureted Compressed Natural Gas fuel system has been designed and manufactured. For controlling quantity of Compressed Natural Gas, the gas valve is linked to the diesel fuel injection system by means of a set of rods. Then, the dual-fuel system is adjusted so that, at full load conditions, the quantity of diesel fuel is reduced to 20% and 80% of its equivalent energy is substituted by Compressed Natural Gas fuel. Also injection pressure of pilot jet is increased by 11.4%. Performance and emission tests are conducted under variation of load and speed on both diesel and diesel-gas engines. Results show that, with equal power and torque, the diesel-gas engine has the potential to improve overall engine performance and emission. For example, at rated power and speed, fuel economy increases by 5.48%, the amount of smoke decreases by 78%, amount of CO decreases by 64.3% and mean exhaust gas temperature decreases by 6.4%

  6. A Silicon-Based Micro Gas Turbine Engine for Power Generation

    CERN Document Server

    Shan, X -C; Maeda, R; Sun, Y F; Wu, M; Hua, J S

    2007-01-01

    This paper reports on our research in developing a micro power generation system based on gas turbine engine and piezoelectric converter. The micro gas turbine engine consists of a micro combustor, a turbine and a centrifugal compressor. Comprehensive simulation has been implemented to optimal the component design. We have successfully demonstrated a silicon-based micro combustor, which consists of seven layers of silicon structures. A hairpin-shaped design is applied to the fuel/air recirculation channel. The micro combustor can sustain a stable combustion with an exit temperature as high as 1600 K. We have also successfully developed a micro turbine device, which is equipped with enhanced micro air-bearings and driven by compressed air. A rotation speed of 15,000 rpm has been demonstrated during lab test. In this paper, we will introduce our research results major in the development of micro combustor and micro turbine test device.

  7. Application of Laser-based Diagnostics to a Prototype Gas Turbine Burner at Selected Pressures

    OpenAIRE

    Whiddon, Ronald

    2014-01-01

    The matured laser-diagnostic techniques of planar laser-induced fluorescence (PLIF) and particle image velocimetry (PIV) were applied to a prototype gas turbine burner operating on various fuels. The work was performed to provide verification of computational fluid dynamic (CFD) models of the combustion of atypical fuels in a gas turbine combustor. The burner was operated using methane and three synthesized fuels of interest- one with hydrogen as the principle component and two with a low hea...

  8. Upgrading existing coal-fired power plants through heavy-duty and aeroderivative gas turbines

    International Nuclear Information System (INIS)

    Highlights: • The feedwater repowering of an existing coal-fired power plant is examined. • Repowering is operated by adding heavy duty and aeroderivative gas turbines. • A characteristic plane allows to compare benefits of different repowering options. • Regenerative gas turbines yield the greatest increase in steam plant performances. • Aeroderivative gas turbine allows to implement a more flexible part-load strategy. - Abstract: The need to meet future changes in power demand and current environmental regulations are considered the main driving forces for upgrading existing coal-fired power plants. In this context, repowering by gas-turbine integration is a well-established technique to increase power plant capacity and operational flexibility. Non-negligible benefits are also improvements in efficiency and a decrease in greenhouse gases emissions promoted by the shift to low carbon fuels. This paper aims to investigate the impact of feedwater heater repowering on a 300 MW coal-fired power plant. Marginal efficiency and power increase, as well as the performance of integrated steam-gas power plants, are evaluated by varying the steam section operating conditions and gas turbine technology. Three main cases are investigated, assuming integration with simple or regenerative heavy-duty gas turbines and aeroderivative gas turbines. As part of this investigation, a performance plane is defined, allowing to compare repowering options based on different steam turbine overloads and boiler modes of operation. Focusing on repowering configurations with the maximum power increase, the analysis also examines the plant capability to follow potential load variations and their impact on energy and economic performance parameters

  9. Experimental and Numerical Research of a Novel Combustion Chamber for Small Gas Turbine Engines

    OpenAIRE

    Hybl R.; Betak V.; Kubata J.; Tuma J.

    2013-01-01

    New combustion chamber concept (based on burner JETIS-JET Induced Swirl) for small gas turbine engine (up to 200kW) is presented in this article. The combustion chamber concept is based on the flame stabilization by the generated swirl swirl generated by two opposite tangentially arranged jet tubes in the intermediate zone, this arrangement replaces air swirler, which is very complicated and expensive part in the scope of small gas turbines with annular combustion chamber. The mixing primary ...

  10. Multi-dimensional modelling of gas turbine combustion using a flame sheet model in KIVA II

    Science.gov (United States)

    Cheng, W. K.; Lai, M.-C.; Chue, T.-H.

    1991-01-01

    A flame sheet model for heat release is incorporated into a multi-dimensional fluid mechanical simulation for gas turbine application. The model assumes that the chemical reaction takes place in thin sheets compared to the length scale of mixing, which is valid for the primary combustion zone in a gas turbine combustor. In this paper, the details of the model are described and computational results are discussed.

  11. Evaluation of Methods for the Determination of Black Carbon Emissions from an Aircraft Gas Turbine Engine

    Science.gov (United States)

    The emissions from aircraft gas turbine engines consist of nanometer size black carbon (BC) particles plus gas-phase sulfur and organic compounds which undergo gas-to-particle conversion downstream of the engine as the plume cools and dilutes. In this study, four BC measurement ...

  12. Mechanical support of a ceramic gas turbine vane ring

    Science.gov (United States)

    Shi, Jun; Green, Kevin E.; Mosher, Daniel A.; Holowczak, John E.; Reinhardt, Gregory E.

    2010-07-27

    An assembly for mounting a ceramic turbine vane ring onto a turbine support casing comprises a first metal clamping ring and a second metal clamping ring. The first metal clamping ring is configured to engage with a first side of a tab member of the ceramic turbine vane ring. The second metal clamping ring is configured to engage with a second side of the tab member such that the tab member is disposed between the first and second metal clamping rings.

  13. Laboratory Studies of the Effects of Pressure and Dissolved Gas Supersaturation on Turbine-Passed Fish

    Energy Technology Data Exchange (ETDEWEB)

    Neitzel, Duane A.

    2009-09-14

    Migratory and resident fish in the Columbia River Basin are exposed to stresses associated with hydroelectric power production, including changes in pressure as they pass through turbines and dissolved gas supersaturation (resulting from the release of water from the spillway). To examine pressure changes as a source of turbine-passage injury and mortality, Pacific Northwest National Laboratory scientists conducted specific tests using a hyperbaric chamber. Tests were designed to simulate Kaplan turbine passage conditions and to quantify the response of fish to rapid pressure changes, with and without the complication of fish being acclimated to gas-supersaturated water.

  14. Integration of A Solid Oxide Fuel Cell into A 10 MW Gas Turbine Power Plant

    Directory of Open Access Journals (Sweden)

    Denver F. Cheddie

    2010-04-01

    Full Text Available Power generation using gas turbine power plants operating on the Brayton cycle suffers from low efficiencies. In this work, a solid oxide fuel cell (SOFC is proposed for integration into a 10 MW gas turbine power plant, operating at 30% efficiency. The SOFC system utilizes four heat exchangers for heat recovery from both the turbine outlet and the fuel cell outlet to ensure a sufficiently high SOFC temperature. The power output of the hybrid plant is 37 MW at 66.2% efficiency. A thermo-economic model predicts a payback period of less than four years, based on future projected SOFC cost estimates.

  15. Alternative Liquid Fuel Effects on Cooled Silicon Nitride Marine Gas Turbine Airfoils

    Energy Technology Data Exchange (ETDEWEB)

    Holowczak, J.

    2002-03-01

    With prior support from the Office of Naval Research, DARPA, and U.S. Department of Energy, United Technologies is developing and engine environment testing what we believe to be the first internally cooled silicon nitride ceramic turbine vane in the United States. The vanes are being developed for the FT8, an aeroderivative stationary/marine gas turbine. The current effort resulted in further manufacturing and development and prototyping by two U.S. based gas turbine grade silicon nitride component manufacturers, preliminary development of both alumina, and YTRIA based environmental barrier coatings (EBC's) and testing or ceramic vanes with an EBC coating.

  16. Thermodynamic modeling and Exergy Analysis of Gas Turbine Cycle for Different Boundary conditions

    Directory of Open Access Journals (Sweden)

    Lalatendu Pattanayak

    2015-06-01

    Full Text Available In this study an exergy analysis of 88.71 MW 13D2 gas turbine (GT topping cycle is carried out. Exergy analysis based on second law was applied to the gas cycle and individual components through a modeling approach. The analysis shows that the highest exergy destruction occurs in the combustion chamber (CC. In addition, the effects of the gas turbine load and performance variations with ambient temperature, compression ratio and turbine inlet temperature (TIT are investigated to analyse the change in system behavior. The analysis shows that the gas turbine is significantly affected by the ambient temperature which leads to a decrease in power output. The results of the load variation of the gas turbine show that a reduction in gas turbine load results in a decrease in the exergy efficiency of the cycle as well as all the components. The compressor has the largest exergy efficiency of 92.84% compared to the other component of the GT and combustion chamber is the highest source of exergy destruction of 109.89 MW at 100 % load condition. With increase in ambient temperature both exergy destruction rate and exergy efficiency decreases.

  17. 40 CFR 60.4325 - What emission limits must I meet for NOX if my turbine burns both natural gas and distillate oil...

    Science.gov (United States)

    2010-07-01

    ... NOX if my turbine burns both natural gas and distillate oil (or some other combination of fuels)? 60... percent natural gas, you must meet the corresponding limit for a natural gas-fired turbine when you are... Combustion Turbines Emission Limits § 60.4325 What emission limits must I meet for NOX if my turbine...

  18. An evaluation of thermal energy storage options for precooling gas turbine inlet air

    Science.gov (United States)

    Antoniak, Z. I.; Brown, D. R.; Drost, M. K.

    1992-12-01

    Several approaches have been used to reduce the temperature of gas turbine inlet air. One of the most successful uses off-peak electric power to drive vapor-compression-cycle ice makers. The ice is stored until the next time high ambient temperature is encountered, when the ice is used in a heat exchanger to cool the gas turbine inlet air. An alternative concept would use seasonal thermal energy storage to store winter chill for inlet air cooling. The objective of this study was to compare the performance and economics of seasonal thermal energy storage in aquifers with diurnal ice thermal energy storage for gas turbine inlet air cooling. The investigation consisted of developing computer codes to model the performance of a gas turbine, energy storage system, heat exchangers, and ancillary equipment. The performance models were combined with cost models to calculate unit capital costs and levelized energy costs for each concept. The levelized energy cost was calculated for three technologies in two locations (Minneapolis, Minnesota and Birmingham, Alabama). Precooling gas turbine inlet air with cold water supplied by an aquifer thermal energy storage system provided lower cost electricity than simply increasing the size of the turbine for meteorological and geological conditions existing in the Minneapolis vicinity. A 15 to 20 percent cost reduction resulted for both 0.05 and 0.2 annual operating factors. In contrast, ice storage precooling was found to be between 5 and 20 percent more expensive than larger gas turbines for the Minneapolis location. In Birmingham, aquifer thermal energy storage precooling was preferred at the higher capacity factor and ice storage precooling was the best option at the lower capacity factor. In both cases, the levelized cost was reduced by approximately 5 percent when compared to larger gas turbines.

  19. Turbine Airfoil With CMC Leading-Edge Concept Tested Under Simulated Gas Turbine Conditions

    Science.gov (United States)

    Robinson, R. Craig; Hatton, Kenneth S.

    2000-01-01

    Silicon-based ceramics have been proposed as component materials for gas turbine engine hot-sections. When the Navy s Harrier fighter experienced engine (Pegasus F402) failure because of leading-edge durability problems on the second-stage high-pressure turbine vane, the Office of Naval Research came to the NASA Glenn Research Center at Lewis Field for test support in evaluating a concept for eliminating the vane-edge degradation. The High Pressure Burner Rig (HPBR) was selected for testing since it could provide temperature, pressure, velocity, and combustion gas compositions that closely simulate the engine environment. The study focused on equipping the stationary metal airfoil (Pegasus F402) with a ceramic matrix composite (CMC) leading-edge insert and evaluating the feasibility and benefits of such a configuration. The test exposed the component, with and without the CMC insert, to the harsh engine environment in an unloaded condition, with cooling to provide temperature relief to the metal blade underneath. The insert was made using an AlliedSignal Composites, Inc., enhanced HiNicalon (Nippon Carbon Co. LTD., Yokohama, Japan) fiber-reinforced silicon carbide composite (SiC/SiC CMC) material fabricated via chemical vapor infiltration. This insert was 45-mils thick and occupied a recessed area in the leading edge and shroud of the vane. It was designed to be free floating with an end cap design. The HPBR tests provided a comparative evaluation of the temperature response and leading-edge durability and included cycling the airfoils between simulated idle, lift, and cruise flight conditions. In addition, the airfoils were aircooled, uniquely instrumented, and exposed to the exact set of internal and external conditions, which included gas temperatures in excess of 1370 C (2500 F). In addition to documenting the temperature response of the metal vane for comparison with the CMC, a demonstration of improved leading-edge durability was a primary goal. First, the

  20. Development and validation of a full-range performance analysis model for a three-spool gas turbine with turbine cooling

    International Nuclear Information System (INIS)

    The performance analysis of a gas turbine is important for both its design and its operation. For modern gas turbines, the cooling flow introduces a noteworthy thermodynamic loss; thus, the determination of the cooling flow rate will clearly influence the accuracy of performance calculations. In this paper, a full-range performance analysis model is established for a three-spool gas turbine with an open-circuit convective blade cooling system. A hybrid turbine cooling model is embedded in the analysis to predict the amount of cooling air accurately and thus to remove the errors induced by the relatively arbitrary value of cooling air requirements in the previous research. The model is subsequently used to calculate the gas turbine performance; the calculation results are validated with detailed test data. Furthermore, multistage conjugate heat transfer analysis is performed for the turbine section. The results indicate that with the same coolant condition and flow rate as those in the performance analysis, the blade metal has been effectively cooled; in addition, the maximum temperature predicted by conjugate heat transfer analysis is close to the corresponding value in the cooling model. Hence, the present model provides an effective tool for analyzing the performance of a gas turbine with cooling. - Highlights: • We established a performance model for a gas turbine with convective cooling. • A hybrid turbine cooling model is embedded in the performance analysis. • The accuracy of the model is validated with detailed test data of the gas turbine. • Conjugate heat transfer analysis is performed for the turbine for verification

  1. Fuel Flexible Combustion Systems for High-Efficiency Utilization of Opportunity Fuels in Gas Turbines

    Energy Technology Data Exchange (ETDEWEB)

    Venkatesan, Krishna

    2011-11-30

    The purpose of this program was to develop low-emissions, efficient fuel-flexible combustion technology which enables operation of a given gas turbine on a wider range of opportunity fuels that lie outside of current natural gas-centered fuel specifications. The program encompasses a selection of important, representative fuels of opportunity for gas turbines with widely varying fundamental properties of combustion. The research program covers conceptual and detailed combustor design, fabrication, and testing of retrofitable and/or novel fuel-flexible gas turbine combustor hardware, specifically advanced fuel nozzle technology, at full-scale gas turbine combustor conditions. This project was performed over the period of October 2008 through September 2011 under Cooperative Agreement DE-FC26-08NT05868 for the U.S. Department of Energy/National Energy Technology Laboratory (USDOE/NETL) entitled "Fuel Flexible Combustion Systems for High-Efficiency Utilization of Opportunity Fuels in Gas Turbines". The overall objective of this program was met with great success. GE was able to successfully demonstrate the operability of two fuel-flexible combustion nozzles over a wide range of opportunity fuels at heavy-duty gas turbine conditions while meeting emissions goals. The GE MS6000B ("6B") gas turbine engine was chosen as the target platform for new fuel-flexible premixer development. Comprehensive conceptual design and analysis of new fuel-flexible premixing nozzles were undertaken. Gas turbine cycle models and detailed flow network models of the combustor provide the premixer conditions (temperature, pressure, pressure drops, velocities, and air flow splits) and illustrate the impact of widely varying fuel flow rates on the combustor. Detailed chemical kinetic mechanisms were employed to compare some fundamental combustion characteristics of the target fuels, including flame speeds and lean blow-out behavior. Perfectly premixed combustion experiments were conducted to

  2. Advanced Gas Turbine (AGT) Technology Development Project, ceramic component developments

    Science.gov (United States)

    Teneyck, M. O.; Macbeth, J. W.; Sweeting, T. B.

    1987-01-01

    The ceramic component technology development activity conducted by Standard Oil Engineered Materials Company while performing as a principal subcontractor to the Garrett Auxiliary Power Division for the Advanced Gas Turbine (AGT) Technology Development Project (NASA Contract DEN3-167) is summarized. The report covers the period October 1979 through July 1987, and includes information concerning ceramic technology work categorized as common and unique. The former pertains to ceramic development applicable to two parallel AGT projects established by NASA contracts DEN3-168 (AGT100) and DEN3-167 (AGT101), whereas the unique work solely pertains to Garrett directed activity under the latter contract. The AGT101 Technology Development Project is sponsored by DOE and administered by NASA-Lewis. Standard Oil directed its efforts toward the development of ceramic materials in the silicon-carbide family. Various shape forming and fabrication methods, and nondestructive evaluation techniques were explored to produce the static structural components for the ceramic engine. This permitted engine testing to proceed without program slippage.

  3. Investigation of azimuthal staging concepts in annular gas turbines

    Science.gov (United States)

    Noiray, Nicolas; Bothien, Mirko; Schuermans, Bruno

    2011-10-01

    In this work, the influence of azimuthal staging concepts on the thermoacoustic behavior of annular combustion chambers is assessed theoretically and numerically. Staging is a well-known and effective method to abate thermoacoustic pulsations in combustion chambers. However, in the case of, for example, fuel staging the associated inhomogeneity of equivalence ratio may result in increased levels of NOx emissions. In order to minimize this unwanted effect a staging concept is required in which the transfer functions of the burners are changed while affecting the equivalence ratio as little as possible. In order to achieve this goal, a theoretical framework for predicting the influence of staging concepts on pulsations has been developed. Both linear and nonlinear analytical approaches are presented and it is shown that the dynamics of azimuthal modes can be described by coupled Van der Pol oscillators. A criterion based on the thermoacoustic coupling strength and on the asymmetry degree provides the modal behavior in the annular combustor, i.e. standing or traveling waves. The model predictions have been verified by numerical simulations of a heavy-duty gas turbine using an in-house thermoacoustic network-modeling tool. The interaction between the heat release of the flame and the acoustic field was modeled using measured transfer functions and source terms. These numerical simulations confirmed the original theoretical considerations.

  4. Analysis of Internal Cooling Geometry Variations in Gas Turbine Blades

    Institute of Scientific and Technical Information of China (English)

    M. Eifel; V. Caspary; H. H(o)nen; P. Jeschke

    2009-01-01

    The present investigation analyzes the effects of major geometrical modifications to the interior of a convection cooled gas turbine rotor blade. The main focus lies on the flow of the leading edge channels and the impact on the heat transfer. An experimental approach is performed with flow visualization via paint injection into water. Also numerical calculations are carried out in two sets, on the one hand water calculations accompanying the experi-ments and on the other hand conjugate heat transfer calculations under realistic engine conditions. The latter cal-culations are still ongoing delivering preliminary results. Five geometry configurations are investigated, three of them with differing turbulator arrangements in the leading edge channels. The operating point of the base configuration is set to Re = 50,000 at the inlet while for the modi-fied geometries the pressure ratio is held constant compared to the base. Among several investigated configurations one could be identified that leads to a heat transfer enhancement in one leading edge channel 7 % larger compared to the base.

  5. Thermo-economic optimization of whole gas turbine plant (GTPOM)

    International Nuclear Information System (INIS)

    This paper describes the GTPOM project that focused on the development and implementation of an integrated through-life economic performance optimization tool for gas turbine whole plant analysis, funded in part through the European Commission's Fifth Framework Programme.PSEconomy, the software tool developed in GTPOM, is primarily intended for use at the preliminary design stage to enable the down-selection of potentially attractive new cycle configurations based on calculated through-life economic performance. However, its flexibility also enables the re-appraisal of existing power generation system design to improve economic, thermodynamic or emissions performance.PSEconomy comprises three key areas of functionality:thermodynamic process modelling capability,economic analysis capability,optimization capability.This paper summarises the key objectives of the project, the structure of the software tool, and the functionality it offers the User. It also briefly describes an example case study performed with the tool to demonstrate the through-life economic optimization capabilities of the system, and suggests potential application areas for the software

  6. Gas-liquid dispersion with dual Rushton turbine impellers.

    Science.gov (United States)

    Hudcova, V; Machon, V; Nienow, A W

    1989-08-20

    Aerated and unaerated power consumption and flow patterns in a 0.56 m diameter agitated vessel containing water with dual Rushton turbines have been studied. Under unaerated conditions with a liquid height-to-diameter ratio of 2, an impeller spacing of 2 to 3 times the impeller is required for each to draw an amount of power equal to a single impeller. For aerated conditions, if a similar spacing is used, equations for the flooding-loading transition and for power consumption for a single Rushton impeller can be extended relatively easily to dual systems. All results for this spacing are explained by reference to bulk flow patterns and gassed-filled cavity structures and the proportion of sparged gas flowing through the upper impeller is also estimated. Such a spacing is generally recommended since it maximizes the power draw and hence the potential for oxygen mass transfer. Data are presented for other spacings but the results do not fit in easily with single agitator studies because strong impeller-impeller flow pattern interactions occur.

  7. Methodology for Structural Integrity Analysis of Gas Turbine Blades

    Directory of Open Access Journals (Sweden)

    Tiago de Oliveira Vale

    2012-03-01

    Full Text Available One of the major sources of stress arising in turbomachinery blades are the centrifugal loads acting at any section of the airfoil. Accounting for this phenomenon stress evaluation of the blade attachment region in the disc has to be performed in order to avoid blade failure. Turbomachinery blades are generally twisted, and the cross section area varies from the root of the blade to the tip. The blade root shape at the attachment region is of great concern. Stress concentrations are predictable at this contact region. In this paper, a finite element model has been created for the purpose of assessing stress at the joint region connecting the blade to the disc slot. Particular attention was paid to the geometric modeling of the "fir-tree" fixing, which is now used in the majority of gas turbine engines. This study has been performed using the commercial software ANSYS 13.0. The disc and blade assembly are forced to move with a certain rotational velocity. Contact connections are predicted on the common faces of the blade and on the disc at the root. Solutions can be obtained to allow the evaluation of stresses. Results can be compared with the mechanical properties of the adopted material.

  8. High temperature strain gage technology for gas turbine engines

    Science.gov (United States)

    Fichtel, Edward J.; McDaniel, Amos D.

    1994-08-01

    This report summarizes the results of a six month study that addressed specific issues to transfer the Pd-13Cr static strain sensor to a gas turbine engine environment. The application issues that were addressed include: (1) evaluation of a miniature, variable potentiometer for use as the ballast resistor, in conjunction with a conventional strain gage signal conditioning unit; (2) evaluation of a metal sheathed, platinum conductor leadwire assembly for use with the three-wire sensor; and (3) subjecting the sensor to dynamic strain cyclic testing to determine fatigue characteristics. Results indicate a useful static strain gage system at all temperature levels up to 1350 F. The fatigue characteristics also appear to be very promising, indicating a potential use in dynamic strain measurement applications. The procedure, set-up, and data for all tests are presented in this report. This report also discusses the specific strain gage installation technique for the Pd-13Cr gage because of its potential impact on the quality of the output data.

  9. Integrated Approach to Design and Manufacture of Gas Turbine Components Based on Group Theory

    Directory of Open Access Journals (Sweden)

    M. Jawaharlal

    1988-10-01

    Full Text Available This paper deals with a new method that provides an integrated approach to design and manufacture of gas turbine components by using the group theory and customising standard computer aided design and manufacturing system. With this approach time consuming and iterative design procedure and process planning are automated and become more efficient. Due to the intricate and diverse nature of gas turbine components, grouping them is not easy as in other industries. A possible way of grouping the gas turbine components based on design and manufacturing attributes on a broad basis is presented. A case study of high pressure turbine disc is included with illustrations for design and process planning of this component. The proposed system is implemented on a personal computer and offers an alternate solution to sophisticated and expensive main frame based systems.

  10. Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR)

    Science.gov (United States)

    Snyder, Christopher A.; Thurman, Douglas R.

    2010-01-01

    In support of the Fundamental Aeronautics Program, Subsonic Rotary Wing Project; an engine system study has been undertaken to help define and understand some of the major gas turbine engine parameters required to meet performance and weight requirements as defined by earlier vehicle system studies. These previous vehicle studies will be reviewed to help define gas turbine performance goals. Assumptions and analysis methods used will be described. Performance and weight estimates for a few conceptual gas turbine engines meeting these requirements will be given and discussed. Estimated performance for these conceptual engines over a wide speed variation (down to 50 percent power turbine rpm at high torque) will be presented. Finally, areas needing further effort will be suggested and discussed.

  11. Effective utilization of fossil fuels for low carbon world -- IGCC and high performance gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Ishii, Hiromi; Hashimoto, Takao; Sakamoto, Koichi; Komori, Toyoaki; Kishine, Takashi; Shiozaki, Shigehiro

    2010-09-15

    The reduction of greenhouse-gas emissions is required to minimize the effect of hydrocarbon based power generation on global warming. In pursue of this objective, Mitsubishi Heavy Industries is dedicating considerable efforts on two different ways to reduce the environmental impact. The first one involves gas turbine performance improvement by raising firing temperature for Natural-gas and LNG applications. In this regard, the latest J class gas turbine was designed to operate at 1600 deg C and expected combined cycle efficiency in excess of 60%. The other approach involves the use of Integrated Gasification Combined Cycle (IGCC) plants to burn solid fuel like coal.

  12. Turbine bucket for use in gas turbine engines and methods for fabricating the same

    Science.gov (United States)

    Garcia-Crespo, Andres

    2014-06-03

    A turbine bucket for use with a turbine engine. The turbine bucket includes an airfoil that extends between a root end and a tip end. The airfoil includes an outer wall that defines a cavity that extends from the root end to the tip end. The outer wall includes a first ceramic matrix composite (CMC) substrate that extends a first distance from the root end to the tip end. An inner wall is positioned within the cavity. The inner wall includes a second CMC substrate that extends a second distance from the root end towards the tip end that is different than the first distance.

  13. Design and Analysis of Gas Turbine Blade by Potential Flow Approach

    Directory of Open Access Journals (Sweden)

    V. Vijaya Kumar,

    2014-01-01

    Full Text Available The design features of the turbine segment of the gas turbine have been taken from the “preliminary design of a power turbine for maximization of an existing turbojet engine”. It was observed that in the above design, after the rotor blades being designed they were analyzed only for the mechanical stresses. As the temperature has a significant effect on the overall stress in the rotor blades, a detailed study is carried out on the temperature effects to have a clear understanding of the combined mechanical and the thermal stresses. The first stage rotor blade of the gas turbine is analyzed for the mechanical axial and centrifugal forces. Knowing the fluid conditions at exit of the gas turbines, a value of static pressure was assumed at the turbine outlet. From this the corresponding enthalpy drop required in the power turbine is calculated. The peripheral speed of rotor and flows velocities is kept in the reasonable range so to minimize losses. In which the base profiles available and is analyzed later for flow conditions through any of the theoretical flow analysis methods such as “Potential flow Approach”

  14. Exergy costing analysis and performance evaluation of selected gas turbine power plants

    Directory of Open Access Journals (Sweden)

    S.O. Oyedepo

    2015-12-01

    Full Text Available In this study, exergy costing analysis and performance evaluation of selected gas turbine power plants in Nigeria are carried out. The results of exergy analysis confirmed that the combustion chamber is the most exergy destructive component compared to other cycle components. The exergetic efficiency of the plants was found to depend significantly on a change in gas turbine inlet temperature (GTIT. The increase in exergetic efficiency with the increase in turbine inlet temperature is limited by turbine material temperature limit. This was observed from the plant efficiency defect curve. As the turbine inlet temperature increases, the plant efficiency defect decreases to minimum value at certain GTIT (1,200 K, after which it increases with GTIT. This shows degradation in performance of gas turbine plant at high turbine inlet temperature. Exergy costing analysis shows that the combustion chamber has the greatest cost of exergy destruction compared to other components. Increasing the GTIT, both the exergy destruction and the cost of exergy destruction of this component are found to decrease. Also, from exergy costing analysis, the unit cost of electricity produced in the power plants varies from cents 1.99/kWh (N3.16/kWh to cents 5.65/kWh (N8.98/kWh.

  15. Thermodynamic analysis for a regenerative gas turbine cycle in coking process

    Directory of Open Access Journals (Sweden)

    Zelong Zhang, Lingen Chen, Yanlin Ge, Fengrui Sun

    2014-01-01

    Full Text Available A regenerative gas turbine cycle driven by residual coke oven gas is proposed in this paper. The thermal efficiency and the work output (per ton of coke of the system are analyzed based on thermodynamics and the theory of gas turbine cycle. The influences of the gas release rate, the residual gas rate and the effectiveness of regenerator on the performance of the cycle are analyzed by using numerical examples. It is found that the work output increases with the increase of the residual gas rate while decreases with the increase of the gas release rate. The cycle with regenerator can reach higher thermal efficiency and bigger work output, which means that the coke oven gas is used more effectively. Moreover, there exist two optimal pressure ratios of compressor which lead the maximum thermal efficiency and the maximum specific work, respectively.

  16. Effects of Propane/Natural Gas Blended Fuels on Gas Turbine Pollutant Emissions

    Energy Technology Data Exchange (ETDEWEB)

    Straub, D.L.; Ferguson, D.H.; Casleton, K.H.; Richards, G.A.

    2007-03-01

    Liquefied natural gas (LNG) imports to the U.S. are expected to grow significantly over the next 10-15 years. Likewise, it is expected that changes to the domestic gas supply may also introduce changes in natural gas composition. As a result of these anticipated changes, the composition of fuel sources may vary significantly from conventional domestic natural gas supplies. This paper will examine the effects of fuel variability on pollutant emissions for premixed gas turbine conditions. The experimental data presented in this paper have been collected from a pressurized single injector combustion test rig at the National Energy Technology Laboratory (NETL). The tests are conducted at 7.5 atm with a 588 K air preheat. A propane blending facility is used to vary the Wobbe Index of the site natural gas. The results indicate that propane addition of about five (vol.) percent does not lead to a significant change in the observed NOx or CO emissions. These results are different from data collected on some engine applications and potential reasons for these differences will be described.

  17. Aerodynamic design study on HTGR helium gas turbines. Investigation on the effect of design conditions

    International Nuclear Information System (INIS)

    Performance prediction codes for an axial turbine and an axial compressor were prepared based on the loss models of Craig, Cox and Wilson and of Koch, Smith and Wilson respectively. Using those codes, preliminary design of 3600 rpm single-shaft HTGR helium gas turbines were carried out. Influences of changing system mass flow rate and pressure on turbine and compressor design and performance were surveyed. Possible conditions of these parameters were found in which 3600 rpm single-shaft gas turbines could be properly designed. Feasibility of magnetic bearings and rotor dynamic design, which were not taken into account in this investigation, should be considered in future studies. A small power, high pressure HTGR gas turbine is difficult to design in a single-shaft configuration. As an alternative plan, a preliminary design of a 2-shaft gas turbine with an electrical output of 100 MWe and an inlet pressure of 6 MPa was carried out. High practicability and performance were expected. Probably, in this particular case, magnetic bearings now on the market can be used. (author). 65 refs

  18. Evaluation and application of data sources for assessing operating costs for mechanical drive gas turbines in pipeline service

    Energy Technology Data Exchange (ETDEWEB)

    Smalley, A.J.; Mauney, D.A. [Southwest Research Inst., San Antonio, TX (United States); Ash, D.I. [Conoco Inc., Ponca City, OK (United States)

    1999-07-01

    The use of regression analysis of public domain data provided by interstate pipeline companies to the Federal Energy Regulatory Commission (FERC), combined with individual company equipment lists to generate information on cost of operations, maintenance, fuel gas used and the cost of fuel and power, is demonstrated. Methods of analysis and limitations are identified, and results of such regression analysis as average and variance of cost and fuel usage for industrial gas turbines and aeroderivative gas turbines are discussed. Comparison between gas turbine prime movers, reciprocating engine prime movers and electric motor drives are made, and annual costs per installed horsepower as a function of turbine size are calculated. 1 ref., 6 figs.

  19. NEXT GENERATION GAS TURBINE (NGGT) SYSTEMS STUDY; FINAL

    International Nuclear Information System (INIS)

    Building upon the 1999 AD Little Study, an expanded market analysis was performed by GE Power Systems in 2001 to quantify the potential demand for an NGGT product. This analysis concluded that improvements to the US energy situation might be best served in the near/mid term (2002-2009) by a ''Technology-Focused'' program rather than a specific ''Product-Focused'' program. Within this new program focus, GEPS performed a parametric screening study of options in the three broad candidate categories of gas turbines: aero-derivative, heavy duty, and a potential hybrid combining components of the other two categories. GEPS's goal was to determine the best candidate systems that could achieve the DOE PRDA expectations and GEPS's internal design criteria in the period specified for initial product introduction, circa 2005. Performance feasibility studies were conducted on candidate systems selected in the screening task, and critical technology areas were identified where further development would be required to meet the program goals. DOE PRDA operating parameters were found to be achievable by 2005 through evolutionary technology. As a result, the study was re-directed toward technology enhancements for interim product introductions and advanced/revolutionary technology for potential NGGT product configurations. Candidate technologies were identified, both evolutionary and revolutionary, with a potential for possible development products via growth step improvements. Benefits were analyzed from two perspectives: (1) What would be the attributes of the top candidate system assuming the relevant technologies were developed and available for an NGGT market opportunity in 2009/2010; and (2) What would be the expected level of public benefit, assuming relevant technologies were incorporated into existing new and current field products as they became available. Candidate systems incorporating these technologies were assessed as to how they could serve multiple applications

  20. Optical measurement of gas turbine engine soot particle effluents

    Energy Technology Data Exchange (ETDEWEB)

    Litchford, R.J.; Sun, F. [ERC Inc., Tullahoma, TN (United States); Few, J.D.; Lewis, J.W.L. [Univ. of Tennessee Space Inst., Tullahoma, TN (United States). Center for Laser Applications

    1998-01-01

    This paper addresses optical-based techniques for measuring soot particulate loading in the exhaust stream of gas turbine engines. The multi-angle scattering and multi-wavelength extinction of light beams by ensembles of submicrometer soot particles was investigated as a diagnostic means of inferring particle field characteristics. That is, the particle size distribution function and particle number density were deduced using an innovative downhill simplex inversion algorithm for fitting the deconvolved Mie-based scattering/extinction integral to the measured scattering/extinction signals. In this work, the particle size distribution was characterized by the widely accepted two-parameter log-normal distribution function, which is fully defined with the specification of the mean particle diameter and the standard deviation of the distribution. The accuracy and precision of the algorithm were evaluated for soot particle applications by applying the technique to noise-perturbed synthetic data in which the signal noise component is obtained by Monte Carlo sampling of Gaussian distributed experimental errors of 4, 6, and 10%. The algorithm was shown to yield results having an inaccuracy of less than 10% for the highest noise levels and an imprecision equal to or less than the experimental error. Multi-wavelength extinction experiments with a laboratory bench-top burner yielded a mean particle diameter of 0.039 {micro}m and indicated that molecular absorption by organic vapor-phase molecules in the ultraviolet region should not significantly influence the measurements. A field demonstration test was conducted on one of the JT-12D engines of a Sabre Liner jet aircraft. This experiment yielded mean diameters of 0.040 {micro}m and 0.036 {micro}m and standard deviations of 0.032 {micro}m for scattering and extinction methods, respectively. The total particulate mass flow rate at idle was estimated to be 0.54 kg/h.

  1. Life prediction of advanced materials for gas turbine application

    Energy Technology Data Exchange (ETDEWEB)

    Zamrik, S.Y.; Ray, A.; Koss, D.A. [Pennsylvania State Univ., University Park, PA (United States)

    1995-10-01

    Most of the studies on the low cycle fatigue life prediction have been reported under isothermal conditions where the deformation of the material is strain dependent. In the development of gas turbines, components such as blades and vanes are exposed to temperature variations in addition to strain cycling. As a result, the deformation process becomes temperature and strain dependent. Therefore, the life of the component becomes sensitive to temperature-strain cycling which produces a process known as {open_quotes}thermomechanical fatigue, or TMF{close_quotes}. The TMF fatigue failure phenomenon has been modeled using conventional fatigue life prediction methods, which are not sufficiently accurate to quantitatively establish an allowable design procedure. To add to the complexity of TMF life prediction, blade and vane substrates are normally coated with aluminide, overlay or thermal barrier type coatings (TBC) where the durability of the component is dominated by the coating/substrate constitutive response and by the fatigue behavior of the coating. A number of issues arise from TMF depending on the type of temperature/strain phase cycle: (1) time-dependent inelastic behavior can significantly affect the stress response. For example, creep relaxation during a tensile or compressive loading at elevated temperatures leads to a progressive increase in the mean stress level under cyclic loading. (2) the mismatch in elastic and thermal expansion properties between the coating and the substrate can lead to significant deviations in the coating stress levels due to changes in the elastic modulii. (3) the {open_quotes}dry{close_quotes} corrosion resistance coatings applied to the substrate may act as primary crack initiation sites. Crack initiation in the coating is a function of the coating composition, its mechanical properties, creep relaxation behavior, thermal strain range and the strain/temperature phase relationship.

  2. Biogas and sewage gas in Stirling engines and micro gas turbines. Results of a field study; Bio- und Klaergas in Stirlingmotoren und Mikrogasturbinen. Ergebnisse einer Feldstudie

    Energy Technology Data Exchange (ETDEWEB)

    Thomas, Bernd; Wyndorps, Agnes [Hochschule Reutlingen (Germany); Bekker, Marina; Oechsner, Hans [Hohenheim Univ., Landesanstalt fuer Agrartechnik und Bioenergie, Stuttgart (Germany); Kelm, Tobias [Zentrum fuer Sonnenenergie- und Wasserstoff-Forschung, Stuttgart (Germany)

    2010-07-01

    In decentral heat and power generation from biogas, sewage gas, landfill gas and methane in systems with a capacity below 100 kWe, Stirling engines and micro gas turbines may have advantages over gas engines, gasoline engines, and diesel engines. This was proved in a research project in which the operation of a Stirling engine with sewage gas and a micro gas turbine with biogas were investigated. (orig.)

  3. Alternative systems for fuel gas boosters for small gas turbine engines

    Science.gov (United States)

    Faulkner, Henry B.

    1992-04-01

    The study was done to investigate alternative technologies for fuel gas boosters for gas turbine engines under 5 MW output. The goal was to identify concepts which would significantly reduce the overall life cycle cost of these boosters. In a broad review of alternative systems, centrifugal compressors were found to be most promising. Electrically driven centrifugals, either direct drive or gear driven, were found to be quite limited in speed. Therefore they require many stages for these applications, and no cost advantage was indicated. Considerable promise was indicated for centrifugals driven by bleed air from the engine compressor, using turbocompressor units which are conversions of existing turbochargers for internal combustion engines. A first cost advantage of 30 to 80 percent was indicated for applications with an annual market size of at least ten units. Considerable savings in installation and maintenance costs are expected in addition.

  4. Laboratory studies of the effects of pressure and dissolved gas supersaturation on turbine-passed fish

    Energy Technology Data Exchange (ETDEWEB)

    Abernethy, C. S. [Pacific Northwest National Lab. (PNNL), Richland, WA (United States); Amidan, B. G. [Pacific Northwest National Lab. (PNNL), Richland, WA (United States); Cada, G. F. [Oak Ridge National Lab. (ORNL), Oak Ridge, TN (United States)

    2001-03-01

    Designing advanced turbine systems requires knowledge of environmental conditions that injure or kill fish such as the stresses associated with hydroelectric power production, including pressure changes fish experience during turbine passage and dissolved gas supersaturation (resulting from the release of water from the spillway). The objective of this study was to examine the relative importance of pressure changes as a source of turbine-passage injury and mortality. Specific tests were designed to quantify the response of fish to rapid pressure changes typical of turbine passage, with and without the complication of the fish being acclimated to gas supersaturated water. The study investigated the responses of rainbow trout (Oncorhynchus mykiss), chinook salmon (O. tshawytscha), and bluegill sunfish (Lepomis macrochirus) to these two stresses, both singly and in combination.

  5. Experimental Investigation of A Twin Shaft Micro Gas-Turbine System

    Science.gov (United States)

    Sadig, Hussain; Sulaiman, Shaharin Anwar; Ibrahim, Idris

    2013-06-01

    Due to the fast depletion of fossil fuels and its negative impact on the environment, more attention has been concentrated to find new resources, policies and technologies, which meet the global needs with regard to fuel sustainability and emissions. In this paper, as a step to study the effect of burning low calorific value fuels on gas-turbine performance; a 50 kW slightly pressurized non-premixed tubular combustor along with turbocharger based twin shaft micro gas-turbine was designed and fabricated. A series of tests were conducted to characterize the system using LPG fuel. The tests include the analysis of the temperature profile, pressure and combustor efficiency as well as air fuel ratio and speed of the second turbine. The tests showed a stable operation with acceptable efficiency, air fuel ratio, and temperature gradient for the single and twin shaft turbines.

  6. Methodologies for predicting the part-load performance of aero-derivative gas turbines

    DEFF Research Database (Denmark)

    Haglind, Fredrik; Elmegaard, Brian

    2009-01-01

    Prediction of the part-load performance of gas turbines is advantageous in various applications. Sometimes reasonable part-load performance is sufficient, while in other cases complete agreement with the performance of an existing machine is desirable. This paper is aimed at providing some guidance...... on methodologies for predicting part-load performance of aero-derivative gas turbines. Two different design models – one simple and one more complex – are created. Subsequently, for each of these models, the part-load performance is predicted using component maps and turbine constants, respectively. Comparisons...... with manufacturer data are made. With respect to the design models, the simple model, featuring a compressor, combustor and turbines, results in equally good performance prediction in terms of thermal efficiency and exhaust temperature as does a more complex model. As for part-load predictions, the results suggest...

  7. 3000 MW(t) HTGR - gas turbine non-intercoolel. Technical evaluation report

    International Nuclear Information System (INIS)

    This report summarizes all the technical work performed on the 3000-MW(t) 3-loop High-Temperature Gas-Cooled Reactor Gas Turbine design as of June 1979. Although the plant configuration has changed to a 2000-MW(t) 2-loop plant, most of the technical assessments described in this report are still applicable to the 2000-MW(t) plant. The report covers the criteria under which the plant was designed, the technical feasibility problems associated with the plant and their potential solutions, and other potential applications and improvements which could make the gas turbine concept more attractive economically

  8. Integration of a municipal solid waste gasification plant with solid oxide fuel cell and gas turbine

    DEFF Research Database (Denmark)

    Bellomare, Filippo; Rokni, Masoud

    2013-01-01

    it reacts with air and produces electricity. The exhausted gases out of the SOFC enter a burner for further fuel combusting and finally the off-gases are sent to a gas turbine to produce additional electricity. Different plant configurations have been studied and the best one found to be a regenerative gas...... in landfills. A Municipal Solid Waste Gasification Plant Integrated with Solid Oxide Fuel Cell (SOFC) and Gas Turbine (GT) has been studied and the plant is called IGSG (Integrated Gasification SOFC and GT). Gasification plant is fed by MSW to produce syngas by which the anode side of an SOFC is fed wherein...

  9. Biomass-gasifier steam-injected gas turbine cogeneration for the cane sugar industry

    International Nuclear Information System (INIS)

    Steam injection for power and efficiency augmentation in aeroderivative gas turbines has been commercially established for natural gas-fired cogeneration since 1980. Steam-injected gas turbines fired with coal and biomass are being developed. A performance and economic assessment of biomass integrated-gasifier steam-injected gas turbine (BIG/STIG) cogeneration systems is carried out here. A detailed economic case study is presented for the second largest sugar factory in Jamaica, with cane residues as the fuel. BIG/STIG cogeneration units would be attractive investments for sugar producers, who could sell large quantities of excess electricity to the utility, or for the utility, as a low-cost generating option. Worldwide, the cane sugar industry could support some 50,000 MW of BIG/STIG electric generation capacity. The relatively modest development effort required to commercialize the BIG/STIG technology is discussed in a companion paper prepared for this conference

  10. Low pressure cooling seal system for a gas turbine engine

    Science.gov (United States)

    Marra, John J

    2014-04-01

    A low pressure cooling system for a turbine engine for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel and into a cooling fluid mixing chamber positioned immediately downstream from a row of turbine blades extending radially outward from a rotor assembly to prevent ingestion of hot gases into internal aspects of the rotor assembly. The low pressure cooling system may also include at least one bleed channel that may extend through the rotor assembly and exhaust cooling fluids into the cooling fluid mixing chamber to seal a gap between rotational turbine blades and a downstream, stationary turbine component. Use of ambient pressure cooling fluids by the low pressure cooling system results in tremendous efficiencies by eliminating the need for pressurized cooling fluids for sealing this gap.

  11. Composite hubs for low cost gas turbine engines

    Science.gov (United States)

    Chamis, C. C.

    1977-01-01

    A detailed stress analysis was performed using NASTRAN to demonstrate theoretically the adequacy of composite hubs for low cost turbine engine applications. Composite hubs are adequate for this application from the steady state stress view point.

  12. HTGR gas-turbine program. Semiannual progress report for period ending March 31, 1980

    Energy Technology Data Exchange (ETDEWEB)

    1982-01-01

    This report describes the conceptual design and analysis performed by General Atomic Company and its subcontractors for the US Department of Energy on the direct cycle gas turbine high-temperature gas-cooled reactor. The primary accomplishments for this period were cost reduction studies, turbomachinery failure analysis, and alternate plant concept evaluation.

  13. Thermodynamic Performance Study of Biomass Gasification, Solid Oxide Fuel Cell and Micro Gas Turbine Hybrid Systems

    DEFF Research Database (Denmark)

    Bang-Møller, Christian; Rokni, Masoud

    2010-01-01

    A system level modelling study of three combined heat and power systems based on biomass gasification is presented. Product gas is converted in a micro gas turbine (MGT) in the first system, in a solid oxide fuel cell (SOFC) in the second system and in a combined SOFC–MGT arrangement in the third...

  14. HTGR gas-turbine program. Semiannual progress report for period ending March 31, 1980

    International Nuclear Information System (INIS)

    This report describes the conceptual design and analysis performed by General Atomic Company and its subcontractors for the US Department of Energy on the direct cycle gas turbine high-temperature gas-cooled reactor. The primary accomplishments for this period were cost reduction studies, turbomachinery failure analysis, and alternate plant concept evaluation

  15. Potential benefits of a ceramic thermal barrier coating on large power generation gas turbine

    Science.gov (United States)

    Clark, J. S.; Nainiger, J. J.

    1977-01-01

    Thermal barrier coating design option offers benefit in terms of reduced electricity costs when used in utility gas turbines. Options considered include: increased firing temperature, increased component life, reduced cooling air requirements, and increased corrosion resistance (resulting in increased tolerance for dirty fuels). Performance and cost data were obtained. Simple, recuperated and combined cycle applications were considered, and distillate and residual fuels were assumed. The results indicate that thermal barrier coatings could produce large electricity cost savings if these coatings permit turbine operation with residual fuels at distillate-rated firing temperatures. The results also show that increased turbine inlet temperature can result in substantial savings in fuel and capital costs.

  16. Thermodynamic modeling of a hybrid solar gas-turbine power plant

    International Nuclear Information System (INIS)

    Highlights: • A complete analytical model for a hybrid solar driven gas-turbine plant is presented. • Each subsystem is modeled: combustion chamber, solar collector, and gas turbine. • Main irreversibility losses for the subsystems are accounted. • The model validation by comparing with real prototype plants is very satisfactory. • The output records are analyzed with respect the main losses parameters, and the temperature and pressure ratios. - Abstract: A thermodynamic model for a hybrid solar gas-turbine power plant is presented. All the subsystems of the plant are modeled, taking into account the most important losses sources: those coming from heat losses in the solar subsystem, those in the combustion chamber, those associated to the Brayton cycle, and those heat losses in the heat exchangers connecting subsystems. Analytical expressions for the overall plant efficiency and its power output are obtained in a general form, for whichever solar share: from the pure combustion mode when solar irradiance is null or small, to the eventual case in which only solar heat input would be enough to ensure that the working fluid reaches the turbine inlet temperature. The gas-turbine model is validated by direct comparison of the model predictions with the output parameters of a commercial turbine. Results are very promising. The real parameters of an existing experimental thermosolar plant are considered and its performance records in stationary irradiance conditions are obtained. A sensitivity analysis of the influence of several turbine losses is performed: recuperator, turbine, compressor, and pressure losses. Finally, the influence of the pressure and temperature ratios on the overall plant efficiency and the fuel conversion rate is discussed. This kind of thermodynamic analysis is necessary in order to design efficient as well as commercially interesting new generations of plants of this type

  17. Design features of the GTD 8000 and GTD 15000 marine gas turbine engines

    Science.gov (United States)

    Romanov, Viktor I.

    1992-06-01

    An account is given of the design features and performance of the GTD 8000 and GTD 15000 marine gas turbines, whose simple-cycle thermodynamic efficiencyis of the order of 34-35 percent. A development history is presented for the component design improvements through which such performance levels were achieved. Attention is given to the counterflow combustor, bearings, and high pressure compressor/turbine spool rotor joint assembly features. These powerplants are suitable for hydrofoil and hovercraft applications.

  18. Integrated Method of the Computation of Cooling Systems for Gas Turbine Rotors

    OpenAIRE

    Тарасов, Александр Иванович; Чан, Конг Шанг; Литвиненко, Оксана Алексеевна; Михайлова, Ирина Александровна

    2015-01-01

    The integrated method allows for the simplification of the CFD analysis of the cooling of turbine rotors through the replacement of small-size elements (slots, labyrinth sealing, etc.) by virtual channels that provide the passage of air from one cavity to the next one. This computation method of the cooling of gas turbines was based on the combination of the method of computation of hydraulic networks and the method of computation of the flow and heat exchange of the viscous compressed liquid...

  19. Low-pressure-ratio regenerative exhaust-heated gas turbine. Final report

    Energy Technology Data Exchange (ETDEWEB)

    Tampe, L.A.; Frenkel, R.G.; Kowalick, D.J.; Nahatis, H.M.; Silverstein, S.M.; Wilson, D.G.

    1991-01-01

    A design study of coal-burning gas-turbine engines using the exhaust-heated cycle and state-of-the-art components has been completed. In addition, some initial experiments on a type of rotary ceramic-matrix regenerator that would be used to transfer heat from the products of coal combustion in the hot turbine exhaust to the cool compressed air have been conducted. Highly favorable results have been obtained on all aspects on which definite conclusions could be drawn.

  20. Development of a high temperature cooled fast response probe for gas turbine applications

    OpenAIRE

    Mersinligil, Mehmet

    2014-01-01

    The measurement of unsteady pressures within the hot components of gas turbine engines still remains a true challenge for test engineers. Several high temperature pressure sensors have been developed but so far their applications are restricted to unsteady wall static pressure measurements. Because of the severe flow conditions such as turbine inlet temperatures of 1700°C and pressures of 50 bar or more in the most advanced aero-engine designs; few (if any) experimental techniques exist to me...

  1. Energy and economic effects of CHP with combined technologies of corn cobs gasification and gas turbines

    Directory of Open Access Journals (Sweden)

    Guteša Milana M.

    2016-01-01

    Full Text Available This paper presents the performance and economic analysis of the gas turbine with co-firing gas from corn cob gasification and natural gas. Adiabatic and non-adiabatic expansion in the turbine is considered. The analysis is performed parametrically with corn cob gasification gas and natural gas ratio. The volumetric energy content of fuels with different share of gas from the corn cob gasification therefore, with different calorific values, is compared by means of the Wobbe Index. In energy and economic analyses, the following configurations are dealt with: single manifold, dual manifold and separate gas systems. [Projekat Ministarstva nauke Republike Srbije, br. 33049: The Development of CHP Demonstration Plant with Biomass Gasification

  2. Evaluation of Soya Bio-Diesel as a Gas Turbine Fuel

    Directory of Open Access Journals (Sweden)

    K.K. Gupta

    2010-07-01

    Full Text Available In the recent past, the crude oil prices have increased immensely as the fossil fuels are depleting, biodiesel has emerged as an alternative fuel for the petroleum. In this context the use of bio-diesel in the gas turbine seems a solution for power generation problems and their environmental concerns. Vegetable oils, due to their agricultural origin, are able to reduce net carbon dioxide emissions to the atmosphere. However, there are several operational and durability problems which may arise in using straight vegetable oils, which are because of their higher viscosity and low volatility compared to mineral diesel fuel. Bio-fuels, an alternative fuels are having environmental benefit as; they are made from renewable sources. It can be blended in any proportion with mineral Diesel. Many performance and emission tests are being carried out in reciprocating diesel engines that use bio fuel but there are very few tests has been done on gas turbine engines. The gas turbine combustion is steady flame combustion. This feature creates the wide range for the different alternative fuels for clean combustion in the gas turbine, such as natural gas, petroleum distillates, pyrolysis wood gas, biogas of methanisation, bio-diesel etc. The present work is an analysis of the Soya bio-diesel productionprocess i.e. trans-esterification, the different parameters affecting on trans-esterification. The different physical and chemical properties of this bio-diesel and diesel has been determined and compared to establish the suitability of the bio-diesel in the gas turbine. An analysis on High Performance Liquid Chromatography (HPLC has been done to find out the composition of the different fatty acid esters. The effect of these fatty acids onthe property of the bio-diesel has also been explained such as viscosity, heat of combustion, cetane No, cold flow properties, lubricity and oxidative stability etc. This will also help us to select best suited bio-diesel for the

  3. Comparative Analysis of a Power Plant Comprising One Gas and One Steam Turbine with respect to Two Types of Inspection

    Directory of Open Access Journals (Sweden)

    Dalip Singh

    2014-06-01

    Full Text Available Comparative analysis between two models is made with respect to two types of inspection in the present paper. The two models (Model 1 and Model 2 considered are on a gas turbine power plant comprising one gas turbine and one steam turbine with the difference in the type of inspection. Model 1 considers the scheduled inspection whereas random inspection is considered in Model 2. Initially, both the units i.e. the gas turbine as well as the steam turbine are operating. On failure of the gas turbine, system goes to down state, whereas on failure of the steam turbine, the system may be kept in the up state with only gas turbine working if the buyer of the power so generated is ready to pay higher amount or otherwise put to down state. When only the gas turbine is operative and the steam turbine is failed, this type of working of the system is called working in the Single Cycle; whereas when both the units are operative then it is called the Combined Cycle. Expressions for various measures of system effectiveness and cost-benefit analysis for Model 1 were obtained by [1] but with no computational work. Here the computational work has been done for Model 1 and with interesting conclusions. Also, this model has been compared with the model wherein the random inspection is carried out. System is analyzed by making use of semi - Markov processes and regenerative point technique.

  4. Interaction between Struts and Swirl Flow in Gas Turbine Exhaust Diffusers

    Institute of Scientific and Technical Information of China (English)

    Roman Z.PIETRASCH; Joerg R. SEUME

    2005-01-01

    The increasing use of gas turbines in combined cycle power plants together with the high amount of kinetic energy in modem gas turbine exhaust flows focuses attention on the design of gas turbine diffusers as the connecting part between the Brayton/Joule and the Rankine parts of the combined cycle. A scale model of a typical gas turbine exhaust diffuser is investigated experimentally. The test rig consists of a radial type, variable swirl generator which provides the exhaust flow corresponding to different gas turbine operating conditions.Static pressure measurements are carried out along the outer diffuser walls and along the hub of the annular part and along the centerline of the conical diffuser. Velocity distributions at several axial positions in the annular and conical diffuser have been measured using a Laser Doppler Velocimeter (LDV). Pressure recovery coefficients and velocity profiles are depicted as a function of diffuser length for several combinations of swirl strength, tip flow and strut geometries. The diffuser without struts achieved a higher pressure recovery than the diffuser with struts at all swirl angle settings. The diffuser with cylindrical struts achieved a higher pressure recovery than the diffuser with profiled struts at all swirl angle settings. Inlet flows with swirl angles over 18° affected the pressure recovery negatively for all strut configurations.

  5. Development of interactive design system, KAIT by computer-analysis for gas turbine blade

    Energy Technology Data Exchange (ETDEWEB)

    Tsuta, Toshio; Yamaji, Seiichi; Tanizawa, Tadashi; Isozaki, Toshiaki; Hamabe, Kenji; Hoshino, Akifumi; Sugimoto, Takao; Miyaji, Hiroshi; Take, Koji; Yoshigane, Masaru

    1987-08-20

    Upon development of various gas turbines, design of the turbine power generating portion provides the dominating influences over the turbine performance and durability. Heretofore, such design has been coped with by the accumulation of the technologies required during the design stage which had been programed individually, but due to the recent increase of development projects which contents have been upgraded, difficulties have arisen in coping with the performance design of blade profile, etc. which requires a time-consuming trial and error approach. Accordingly, Kawasaki Heavy Industries Co. has developed the Kawasaki Interactive Axial Gas Turbine Blade Design System (KAIT) which does the design and development of turbine blades, the most labor and time consuming work in designing a gas turbine, through the computer dialoguing on examination and analysis in each different specific field such as fluid dynamics, thermodynamics, structural mechanics, fatigue and high temperature strength etc.. This article explains the outline of this system. Thanks for this system, a blade with well balanced performance and durability can be designed in a short time. (13 figs, 12 refs)

  6. Energy Conversion Alternatives Study (ECAS), General Electric Phase 1. Volume 2: Advanced energy conversion systems. Part 1: Open-cycle gas turbines

    Science.gov (United States)

    Brown, D. H.; Corman, J. C.

    1976-01-01

    Ten energy conversion systems are defined and analyzed in terms of efficiency. These include: open-cycle gas turbine recuperative; open-cycle gas turbine; closed-cycle gas turbine; supercritical CO2 cycle; advanced steam cycle; liquid metal topping cycle; open-cycle MHD; closed-cycle inert gas MHD; closed-cycle liquid metal MHD; and fuel cells. Results are presented.

  7. Mini gas turbines. Study related to energy efficient cogeneration applications for new cogeneration markets. Appendix; Mini gasturbiner. Udredning vedr. energieffektive kraftvarmeapplikationer til nye kraftvarmemarkeder. Appendix

    Energy Technology Data Exchange (ETDEWEB)

    Mikkelsen, J.B.; Weel Hansen, M.; Astrupgaard, N.P.

    2000-12-01

    The aim of the project is to investigate, design and increase the energy efficiency in new cogeneration/cooling systems, which are based on new developed mini gas turbines. Hereby cogeneration can primarily based on natural gas and bio-fuels be spread to new market segments. The appendix presents further details related to gas turbine as burner; cogeneration with recuperation gas turbine; gas turbine for cogeneration/absorption refrigerator; the economic and operational basis used in the study. (EHS)

  8. AN INVESTIGATION INTO THE MECHANICS OF SINGLE CRYSTAL TURBINE BLADES WITH A VIEW TOWARDS ENHANCING GAS TURBINE EFFICIENCY

    Energy Technology Data Exchange (ETDEWEB)

    K.R. Rajagopal; I.J. Rao

    2006-05-05

    The demand for increased efficiency of gas turbines used in power generation and aircraft applications has fueled research into advanced materials for gas turbine blades that can withstand higher temperatures in that they have excellent resistance to creep. The term ''Superalloys'' describes a group of alloys developed for applications that require high performance at elevated temperatures. Superalloys have a load bearing capacity up to 0.9 times their melting temperature. The objective of the investigation was to develop a thermodynamic model that can be used to describe the response of single crystal superalloys that takes into account the microstructure of the alloy within the context of a continuum model. Having developed the model, its efficacy was to be tested by corroborating the predictions of the model with available experimental data. Such a model was developed and it is implemented in the finite element software ABAQUS/STANDARD through a user subroutine (UMAT) so that the model can be used in realistic geometries that correspond to turbine blades.

  9. CFD Modeling of Syngas Combustion and Emissions for Marine Gas Turbine Applications

    Directory of Open Access Journals (Sweden)

    Ammar Nader R.

    2016-09-01

    Full Text Available Strong restrictions on emissions from marine power plants will probably be adopted in the near future. One of the measures which can be considered to reduce exhaust gases emissions is the use of alternative fuels. Synthesis gases are considered competitive renewable gaseous fuels which can be used in marine gas turbines for both propulsion and electric power generation on ships. The paper analyses combustion and emission characteristics of syngas fuel in marine gas turbines. Syngas fuel is burned in a gas turbine can combustor. The gas turbine can combustor with swirl is designed to burn the fuel efficiently and reduce the emissions. The analysis is performed numerically using the computational fluid dynamics code ANSYS FLUENT. Different operating conditions are considered within the numerical runs. The obtained numerical results are compared with experimental data and satisfactory agreement is obtained. The effect of syngas fuel composition and the swirl number values on temperature contours, and exhaust gas species concentrations are presented in this paper. The results show an increase of peak flame temperature for the syngas compared to natural gas fuel combustion at the same operating conditions while the NO emission becomes lower. In addition, lower CO2 emissions and increased CO emissions at the combustor exit are obtained for the syngas, compared to the natural gas fuel.

  10. Impact of inlet fogging and fuels on power and efficiency of gas turbine plants

    Directory of Open Access Journals (Sweden)

    Basha Mehaboob

    2013-01-01

    Full Text Available A computational study to assess the performance of different gas turbine power plant configurations is presented in this paper. The work includes the effect of humidity, ambient inlet air temperature and types of fuels on gas turbine plant configurations with and without fogger unit. Investigation also covers economic analysis and effect of fuels on emissions. GT frames of various sizes/ratings are being used in gas turbine power plants in Saudi Arabia. 20 MWe GE 5271RA, 40 MWe GE-6561B and 70 MWe GE-6101FA frames are selected for the present study. Fogger units with maximum mass flow rate of 2 kg/s are considered for the present analysis. Reverse Osmosis unit of capacity 4 kg/s supplies required water to the fogger units. GT PRO software has been used for carrying out the analysis including; net plant output and net efficiency, break even electricity price and break even fuel LHV price etc., for a given location of Saudi Arabia. The relative humidity and temperature have been varied from 30 to 45 % and from 80 to 100° F, respectively. Fuels considered in the study are natural gas, diesel and heavy bunker oil. Simulated gas turbine plant output from GT PRO has been validated against an existing gas turbine plant output. It has been observed that the simulated plant output is less than the existing gas turbine plant output by 5%. Results show that variation of humidity does not affect the gas turbine performance appreciably for all types of fuels. For a decrease of inlet air temperature by 10 °F, net plant output and efficiency have been found to increase by 5 and 2 %, respectively for all fuels, for GT only situation. However, for GT with Fogger scenario, for a decrease of inlet air temperature by 10 °F, net plant output and efficiency have been found to further increase by 3.2 and 1.2 %, respectively for all fuels. For all GT frames with fogger, the net plant output and efficiency are relatively higher as compared to GT only case for all

  11. Modification and testing of an engine and fuel control system for a hydrogen fuelled gas turbine

    Science.gov (United States)

    Funke, H. H.-W.; Börner, S.; Hendrick, P.; Recker, E.

    2011-10-01

    The control of pollutant emissions has become more and more important by the development of new gas turbines. The use of hydrogen produced by renewable energy sources could be an alternative. Besides the reduction of NOx emissions emerged during the combustion process, another major question is how a hydrogen fuelled gas turbine including the metering unit can be controlled and operated. This paper presents a first insight in modifications on an Auxiliary Power Unit (APU) GTCP 36300 for using gaseous hydrogen as a gas turbine fuel. For safe operation with hydrogen, the metering of hydrogen has to be fast, precise, and secure. So, the quality of the metering unit's control loop has an important influence on this topic. The paper documents the empiric determination of the proportional integral derivative (PID) control parameters for the metering unit.

  12. Advanced coal-fueled industrial cogeneration gas turbine system. Annual report, June 1990--June 1991

    Energy Technology Data Exchange (ETDEWEB)

    LeCren, R.T.; Cowell, L.H.; Galica, M.A.; Stephenson, M.D.; Wen, C.S.

    1991-07-01

    Advances in coal-fueled gas turbine technology over the past few years, together with recent DOE-METC sponsored studies, have served to provide new optimism that the problems demonstrated in the past can be economically resolved and that the coal-fueled gas turbine can ultimately be the preferred system in appropriate market application sectors. The objective of the Solar/METC program is to prove the technical, economic, and environmental feasibility of a coal-fired gas turbine for cogeneration applications through tests of a Centaur Type H engine system operated on coal fuel throughout the engine design operating range. The five-year program consists of three phases, namely: (1) system description; (2) component development; (3) prototype system verification. A successful conclusion to the program will initiate a continuation of the commercialization plan through extended field demonstration runs.

  13. Robust control of speed and temperature in a power plant gas turbine.

    Science.gov (United States)

    Najimi, Ebrahim; Ramezani, Mohammad Hossein

    2012-03-01

    In this paper, an H(∞) robust controller has been designed for an identified model of MONTAZER GHAEM power plant gas turbine (GE9001E). In design phase, a linear model (ARX model) which is obtained using real data has been applied. Since the turbine has been used in a combined cycle power plant, its speed and also the exhaust gas temperature should be adjusted simultaneously by controlling fuel signals and compressor inlet guide vane (IGV) position. Considering the limitations on the system inputs, the aim of the control is to maintain the turbine speed and the exhaust gas temperature within desired interval under uncertainties and load demand disturbances. Simulation results of applying the proposed robust controller on the nonlinear model of the system (NARX model), fairly fulfilled the predefined aims. Simulations also show the improvement in the performance compared to MPC and PID controllers for the same conditions.

  14. Support and power plant documentation for the gas turbine powered bus demonstration program

    Science.gov (United States)

    Nigro, D. N.; Stewart, R. G.; Apple, S. A.

    1982-01-01

    The operational experience obtained for the GT404-4 gas turbine engines in the intercity and intracity Bus Demonstration Programs is described for the period January 1980 through September 1981. Support for the engines and automatic transmissions involved in this program provided engineering and field service, spare parts and tools, training, and factory overhauls. the Greyhound (intercity) coaches accumulated 183,054 mi (294,595 km) and 5154 hr of total operation. The Baltimore Transit (intracity) coaches accumulated 40,567 mi (65,285 km) and 1840 hr of total operation. In service, the turbine powered Greyhound and Transit coaches achieved approximately 25% and 40% lower fuel mileage, respectively, than did the production diesel powered coaches. The gas turbine engine will require the advanced ceramic development currently being sponsored by the DOE and NASA to achieve fuel economy equivalent not only to that of today's diesel engines but also to the projected fuel economy of the advanced diesel engines of the 1990s. Sufficient experience was not achieved with the coaches prior to the start of service to identify and eliminate many of the problems associated with the startup of new equipment. Because of these problems, the mean miles between incident were unacceptably low. The future gas turbine system should be developed sufficiently to establish satisfactory durability prior to evaluation in revenue service. Commercialization of the gas turbine bus engine remains a viable goal for the future.

  15. Advanced combustion technologies for gas turbine power plants

    Energy Technology Data Exchange (ETDEWEB)

    Vandsburger, U.; Desu, S.B. [Virginia Tech, Blacksburg, VA (United States); Roe, L.A.

    1995-10-01

    During the second half of fiscal year 1995 progress was made in all three funded subject areas of the project as well as in a new area. Work in the area of mixing and combustion management through flow actuation was transferred into an enclosed facility. Jet mixing in a ducted co-flow was examined. The same jets were also subjected to a strong acoustic field established in the duct. Excitation of the jet with static spatial modes was shown to be effective even in the presence of co-flow and the acoustic field. Only when a wall is placed at the jet exit plane did the acoustic field dominate the jet dispersion (as expected due to reflective boundary conditions and the jet shear layer receptivity). This case is, however, not the most relevant to gas turbine combustors since it precludes co-flow. In the area of combustor testing, the design, fabrication, and assembly of a modular combustor test rig for project has been completed at the University of Arkansas. In the area of high temperature piezoceramic actuator materials development, Sr{sub 2}(Nb{sub x}Ta{sub 1-x}){sub 2}O{sub 7} powders have been synthesized, and bulk samples and thick films sintered. These materials have a curie temperature of about 1400{degrees}C compared with 300{degrees}C for the commercially available PZT. While at room temperature the new materials show a piezoelectric constant (d{sub 33}) which is a factor of 100 lower than PZT, at high temperatures they can exhibit significant action. A new area of non-linear, neural-net based, controllers for mixing and combustion control has been added during the second contract year. This work is not funded by the contract. Significant progress was made in this area. Neural nets with up to 15 neurons in the hidden layer were trained with experimental data and also with data generated using linear stability theory. System ID was performed successfully. The network was then used to predict the behavior of jets excited at other modes not used for the training.

  16. Magnetogasdynamic Power Extraction and Flow Conditioning for a Gas Turbine

    Science.gov (United States)

    Adamovich, Igor V.; Rich, J. William; Schneider, Steven; Blankson, Isaiah

    2003-01-01

    An extension of the Russian AJAX concept to a turbojet is being explored. This magnetohydrodynamic (MHD) energy bypass engine cycle incorporating conventional gas turbine technology has MHD flow conditioning at the inlet to electromagnetically extract part of the inlet air kinetic energy. The electrical power generated can be used for various on-board vehicle requirements including plasma flow control around the vehicle or it may be used for augmenting the expanding flow in the high speed nozzle by MHD forces to generate more thrust. In order to achieve this interaction, the air needs to be ionized by an external means even up to fairly high flight speeds, and the leading candidates may be classified as electrical discharge devices. The present kinetic modeling calculations suggest that the use of electron beams with characteristics close to the commercially available e-beam systems (electron energy approx. 60 keV, beam current approx. 0.2 mA/sq cm) to sustain ionization in intermediate pressure, low-temperature (P = 0.1 atm, T = 300 K) supersonic air flows allows considerable reduction of the flow kinetic energy (up to 10 to 20 percent in M = 3 flows). The calculations also suggest that this can be achieved at a reasonable electron beam efficiency (eta approx. 5), even if the e-beam window losses are taken into account. At these conditions, the exit NO and O atom concentrations due to e-beam initiated chemical reactions do not exceed 30 ppm. Increasing the beam current up to approx. 2 mA/sq cm, which corresponds to a maximum electrical conductivity of sigma(sub max) approx. 0.8 mho/m at the loading parameter of K = 0.5, would result in a much greater reduction of the flow kinetic energy (up to 30 to 40 percent). The MHD channel efficiency at these conditions would be greatly reduced (to eta approx. 1) due to increased electron recombination losses in the channel. At these conditions, partial energy conversion from kinetic energy to heat would result in a

  17. Advanced Turbine Technology Applications Project (ATTAP) and Hybrid Vehicle Turbine Engine Technology Support project (HVTE-TS): Final summary report

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1998-12-01

    This final technical report was prepared by Rolls-Royce Allison summarizing the multiyear activities of the Advanced Turbine Technology Applications Project (ATTAP) and the Hybrid Vehicle Turbine Engine Technology Support (HVTE-TS) project. The ATTAP program was initiated in October 1987 and continued through 1993 under sponsorship of the US Department of Energy (DOE), Energy Conservation and Renewable Energy, Office of Transportation Technologies, Propulsion Systems, Advanced Propulsion Division. ATTAP was intended to advance the technological readiness of the automotive ceramic gas turbine engine. The target application was the prime power unit coupled to conventional transmissions and powertrains. During the early 1990s, hybrid electric powered automotive propulsion systems became the focus of development and demonstration efforts by the US auto industry and the Department of energy. Thus in 1994, the original ATTAP technology focus was redirected to meet the needs of advanced gas turbine electric generator sets. As a result, the program was restructured to provide the required hybrid vehicle turbine engine technology support and the project renamed HVTE-TS. The overall objective of the combined ATTAP and HVTE-TS projects was to develop and demonstrate structural ceramic components that have the potential for competitive automotive engine life cycle cost and for operating 3,500 hr in an advanced high temperature turbine engine environment. This report describes materials characterization and ceramic component development, ceramic components, hot gasifier rig testing, test-bed engine testing, combustion development, insulation development, and regenerator system development. 130 figs., 12 tabs.

  18. Gas-Dynamic Foil Bearings Application in High-Speed Turbines

    OpenAIRE

    Giemza Bolesław; Nowiński Emil; Domański Marek

    2015-01-01

    Authors present the general characteristics of the gas-dynamic foil bearings in the paper. The short analysis of the application and possibilities of using gas-dynamic bearings in turbo machinery, especially in the aspect of aviation technology were described. Authors also pointed out possible directions of development and gas-dynamic foil bearings application in high-speed turbines, especially working in high temperature.

  19. The future of gas turbine compliance monitoring: The integration of PEMS and CEMS for regulatory compliance

    Energy Technology Data Exchange (ETDEWEB)

    Macak, J.J. III

    1999-07-01

    When the New Source Performance Standards (NSPS) for Stationary Gas Turbines were first promulgated in 1979 (40 CFR 60, Subpart GG), continuous compliance monitoring for gas turbines was simply a parametric monitoring approach where a unit was tested at four load conditions. For those units where water or steam injection was used for NO{sub x} control, testing consisted of establishing a water (or steam injection) versus fuel flow curve to achieve permitted NO{sub x} emission levels across the load range. Since 1979, the growth in gas turbine popularity has encouraged the development of Predictive Emissions Monitoring Systems (PEMS) where gas turbine operating parameters and ambient conditions are fed into a prediction algorithm to predict, rather than monitor, emissions. However, permitting requirements and technological advances now have gas turbines emitting NO{sub x} in the single digits while the overall combined-cycle thermal efficiency has improved dramatically. The combination of supplemental duct-firing in heat recovery steam generators, pollution prevention technology, post-combustion emission controls, and EPA Continuous Emissions Monitoring System (CEMS) regulations for the power industry, resulted in a shift towards CEMS due to the complexity of the overall process. Yet, CEMS are often considered to be a maintenance nightmare with significant amounts of downtime. CEMS and PEMS have their own advantages and disadvantages. Thus evolved the need to find the optimum balance between CEMS and PEMS for gas turbine projects. To justify the cost of both PEMS and CEMS in the same installation, there must be an economic incentive to do so. This paper presents the application of a PEMS/CEMS monitoring system that integrates both PEMS and CEMS in order to meet, and exceed, all emissions monitoring requirements.

  20. An integrated framework for gas turbine based power plant operational modeling and optimization

    Science.gov (United States)

    Zhao, Yongjun

    The deregulation of the electric power market introduced a strong element of competition. Power plant operators strive to develop advanced operational strategies to maximize the profitability in the dynamic electric power market. New methodologies for gas turbine power plant operational modeling and optimization are needed for power plant operation to enhance operational decision making, and therefore to maximize power plant profitability by reducing operations and maintenance cost and increasing revenue. In this study, a profit based, lifecycle oriented, and unit specific methodology for gas turbine based power plant operational modeling was developed, with the power plant performance, reliability, maintenance, and market dynamics considered simultaneously. The generic methodology is applicable for a variety of optimization problems, and several applications were implemented using this method. A multiple time-scale method was developed for gas turbine power plants long term generation scheduling. This multiple time-scale approach allows combining the detailed granularity of the day-to-day operations with global (seasonal) trends, while keeping the resulting optimization model relatively compact. Using the multiple time-scale optimization method, a profit based outage planning method was developed, and the key factors for this profit based approach include power plant aging, performance degradation, reliability degradation, and, importantly, the energy market dynamics. Also a novel approach for gas turbine based power plant sequential preventive maintenance scheduling was introduced, and a profit based sequential preventive maintenance scheduling was developed for more effective maintenance scheduling. Methods to evaluate the impact of upgrade packages on gas turbine power plant performance, reliability, and economics were developed, and TIES methodology was applied for effective evaluation and selection of gas turbine power plant upgrade packages.

  1. A Fully Non-metallic Gas Turbine Engine Enabled by Additive Manufacturing

    Science.gov (United States)

    Grady, Joseph E.

    2014-01-01

    The Non-Metallic Gas Turbine Engine project, funded by NASA Aeronautics Research Institute (NARI), represents the first comprehensive evaluation of emerging materials and manufacturing technologies that will enable fully nonmetallic gas turbine engines. This will be achieved by assessing the feasibility of using additive manufacturing technologies for fabricating polymer matrix composite (PMC) and ceramic matrix composite (CMC) gas turbine engine components. The benefits of the proposed effort include: 50 weight reduction compared to metallic parts, reduced manufacturing costs due to less machining and no tooling requirements, reduced part count due to net shape single component fabrication, and rapid design change and production iterations. Two high payoff metallic components have been identified for replacement with PMCs and will be fabricated using fused deposition modeling (FDM) with high temperature capable polymer filaments. The first component is an acoustic panel treatment with a honeycomb structure with an integrated back sheet and perforated front sheet. The second component is a compressor inlet guide vane. The CMC effort, which is starting at a lower technology readiness level, will use a binder jet process to fabricate silicon carbide test coupons and demonstration articles. The polymer and ceramic additive manufacturing efforts will advance from monolithic materials toward silicon carbide and carbon fiber reinforced composites for improved properties. Microstructural analysis and mechanical testing will be conducted on the PMC and CMC materials. System studies will assess the benefits of fully nonmetallic gas turbine engine in terms of fuel burn, emissions, reduction of part count, and cost. The proposed effort will be focused on a small 7000 lbf gas turbine engine. However, the concepts are equally applicable to large gas turbine engines. The proposed effort includes a multidisciplinary, multiorganization NASA - industry team that includes experts in

  2. CMC Technology Advancements for Gas Turbine Engine Applications

    Science.gov (United States)

    Grady, Joseph E.

    2013-01-01

    CMC research at NASA Glenn is focused on aircraft propulsion applications. The objective is to enable reduced engine emissions and fuel consumption for more environmentally friendly aircraft. Engine system studies show that incorporation of ceramic composites into turbine engines will enable significant reductions in emissions and fuel burn due to increased engine efficiency resulting from reduced cooling requirements for hot section components. This presentation will describe recent progress and challenges in developing fiber and matrix constituents for 2700 F CMC turbine applications. In addition, ongoing research in the development of durable environmental barrier coatings, ceramic joining integration technologies and life prediction methods for CMC engine components will be reviewed.

  3. Development of an axial microturbine for a portable gas turbine generator

    Science.gov (United States)

    Peirs, Jan; Reynaerts, Dominiek; Verplaetsen, Filip

    2003-07-01

    A miniature gas turbine is under development with the aim of generating electrical energy from fuel. This system consists of a compressor, combustion chamber, turbine and generator. The turbine is a single-stage axial impulse turbine (Laval turbine) with a rotor diameter of 10 mm, made of stainless steel using die-sinking electro-discharge machining. It has been tested with compressed air to speeds up to 160 000 rpm and generates a maximum mechanical power of 28 W with an efficiency of 18.4%. When coupled to a small generator, it generates 16 W of electrical power, which corresponds to an efficiency for the total system of 10.5%. The power density is mainly limited by the maximal speed of the ball bearings. The main losses are the blade profile losses and the exit losses. Higher speeds can considerably reduce the exit losses and therefore increase efficiency and power density. An improved turbine has been tested at temperatures up to 360 °C and generates up to 44 W of electrical energy with a total efficiency of 16%. A 20 mm diameter centrifugal compressor matching the pressure and flow characteristics of the turbine has been designed and is currently under construction.

  4. Non-Uniformity of the Combustor Exit Flow Temperature in Front of the Gas Turbine

    Directory of Open Access Journals (Sweden)

    Błachnio Józef

    2014-12-01

    Full Text Available Various types of damages to gas-turbine components, in particular to turbine blades, may occur in the course of gas turbine operation. The paper has been intended to discuss different forms of damages to the blades due to non-uniformity of the exit flow temperature. It has been shown that the overheating of blade material and thermal fatigue are the most common reasons for these damages. The paper presents results from numerical experiments with use of the computer model of the aero jet engine designed for simulations. The model has been purposefully modified to take account of the assumed non-homogeneity of the temperature field within the working agent at the turbine intake. It turned out that such non-homogeneity substantially affects dynamic and static properties of the engine considered as an object of control since it leads to a lag of the acceleration time and to increase in fuel consumption. The summarized simulation results demonstrate that the foregoing properties of a jet engine are subject to considerable deterioration in pace with gradual increase of the assumed non-homogeneity of the temperature field. The simulations made it possible to find out that variations of the temperature field nonhomogeneity within the working agent at the turbine intake lead to huge fluctuation of the turbine rpm for the idle run.

  5. Advanced coal-fueled gas turbine systems: Subscale combustion testing. Topical report, Task 3.1

    Energy Technology Data Exchange (ETDEWEB)

    1993-05-01

    This is the final report on the Subscale Combustor Testing performed at Textron Defense Systems` (TDS) Haverhill Combustion Laboratories for the Advanced Coal-Fueled Gas Turbine System Program of the Westinghouse Electric Corp. This program was initiated by the Department of Energy in 1986 as an R&D effort to establish the technology base for the commercial application of direct coal-fired gas turbines. The combustion system under consideration incorporates a modular staged, rich-lean-quench, Toroidal Vortex Slogging Combustor (TVC) concept. Fuel-rich conditions in the first stage inhibit NO{sub x} formation from fuel-bound nitrogen; molten coal ash and sulfated sorbent are removed, tapped and quenched from the combustion gases by inertial separation in the second stage. Final oxidation of the fuel-rich gases, and dilution to achieve the desired turbine inlet conditions are accomplished in the third stage, which is maintained sufficiently lean so that here, too, NO{sub x} formation is inhibited. The primary objective of this work was to verify the feasibility of a direct coal-fueled combustion system for combustion turbine applications. This has been accomplished by the design, fabrication, testing and operation of a subscale development-type coal-fired combustor. Because this was a complete departure from present-day turbine combustors and fuels, it was considered necessary to make a thorough evaluation of this design, and its operation in subscale, before applying it in commercial combustion turbine power systems.

  6. On the atomization and combustion of liquid biofuels in gas turbines: towards the application of biomass-derived pyrolysis oil

    NARCIS (Netherlands)

    Sallevelt, Johan Leonard Hendrik Pieter

    2015-01-01

    The combustion of liquid biofuels in gas turbines is an efficient way of generating heat and power from biomass. Gas turbines play a major role in the global energy supply and are suitable for a wide range of applications. However, biofuels generally have different properties compared to conventiona

  7. Fabrication and test of digital output interface devices for gas turbine electronic controls

    Science.gov (United States)

    Newirth, D. M.; Koenig, E. W.

    1978-01-01

    A program was conducted to develop an innovative digital output interface device, a digital effector with optical feedback of the fuel metering valve position, for future electronic controls for gas turbine engines. A digital effector (on-off solenoids driven directly by on-off signals from a digital electronic controller) with optical position feedback was fabricated, coupled with the fuel metering valve, and tested under simulated engine operating conditions. The testing indicated that a digital effector with optical position feedback is a suitable candidate, with proper development for future digital electronic gas turbine controls. The testing also identified several problem areas which would have to be overcome in a final production configuration.

  8. Energy optimization model for a CCHP system with available gas turbines

    Energy Technology Data Exchange (ETDEWEB)

    Kong, X.Q.; Wang, R.Z.; Huang, X.H. [Shanghai Jiao Tong Univ., Inst. of Refrigeration and Cryogenics, Shanghai (China)

    2005-02-01

    This paper deals with the problem of optimal energy management of cogeneration system for combined cooling, heating and power production (CCHP). The energy system consists of a gas turbine, an absorption chiller and a heat recovery boiler. A simple linear programming model is presented to determine the optimal strategies that minimize the overall cost of energy for the CCHP system. It is shown that the optimal operation of this system is dependent upon load conditions to be satisfied. In view of energy cost, it is shown that sometimes it may not be optimal to operate the turbine. This is the case when the electric-to-gas cost ratio is very low. (Author)

  9. Dynamic properties of combustion instability in a lean premixed gas-turbine combustor.

    Science.gov (United States)

    Gotoda, Hiroshi; Nikimoto, Hiroyuki; Miyano, Takaya; Tachibana, Shigeru

    2011-03-01

    We experimentally investigate the dynamic behavior of the combustion instability in a lean premixed gas-turbine combustor from the viewpoint of nonlinear dynamics. A nonlinear time series analysis in combination with a surrogate data method clearly reveals that as the equivalence ratio increases, the dynamic behavior of the combustion instability undergoes a significant transition from stochastic fluctuation to periodic oscillation through low-dimensional chaotic oscillation. We also show that a nonlinear forecasting method is useful for predicting the short-term dynamic behavior of the combustion instability in a lean premixed gas-turbine combustor, which has not been addressed in the fields of combustion science and physics.

  10. Aeroderivative Pratt & Whitney FT8-3 gas turbine – an interesting solution for power generation

    Directory of Open Access Journals (Sweden)

    Sorinel-Gicu TALIF

    2011-03-01

    Full Text Available The intermediate load electric power stations become more and more interesting for theelectric power market in Romania. In this context, the Combined Cycle Power Plants came as a veryattractive solution. This paper presents the results of a study regarding the use of the aeroderivativePratt & Whitney FT8-3 gas turbine, available in Romania, for the electric power generation in aCombined Cycle Power Plant. It is also analyzed the Combined Heat in Power generation with FT8-3gas turbine when saturated steam or hot water are required.

  11. Systems and methods for detecting a flame in a fuel nozzle of a gas turbine

    Science.gov (United States)

    Kraemer, Gilbert Otto; Storey, James Michael; Lipinski, John; Mestroni, Julio Enrique; Williamson, David Lee; Marshall, Jason Randolph; Krull, Anthony

    2013-05-07

    A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.

  12. Life cycle analysis and choice of natural gas-based automotive alternative fuels in Chongqing Municipality,China

    Institute of Scientific and Technical Information of China (English)

    WU Rui; LI Guangyi; ZHANG Zongyi; REN Yulong; HAN Weijian

    2007-01-01

    Road transport produces significant amounts of emissions by using crude oil as the primary energy source.A reduction of emissions can be achieved by implementing alternative fuel chains.The objective of this study is to carry out an economic,environmental and energy (EEE) life cycle study on natural gas-based automotive fuels with conventional gasoline in an abundant region of China.A set of indices of four fuels/vehicle systems on the basis of life cycle are assessed in terms of impact of EEE,in which natural gas produces compressed natural gas (CNG),methanol,dimethylether (DME) and Fischer Tropsch diesel (FTD).The study included fuel production,vehicle production,vehicle operation,infrastructure and vehicle end of life as a system for each fuel/vehicle system.A generic gasoline fueled car is used as a baseline.Data have been reviewed and modified based on the best knowledge available to Chongqing local sources.Results indicated that when we could not change electric and hydrogen fuel cell vehicles into commercial vehicles on a large scale,direct use of CNG in a dedicated or bi-fuel vehicle is an economical choice for the region which is most energy efficient and more environmental friendly.The study can be used to support decisions on how natural gas resources can best be utilized as a fuel/energy resource for automobiles,and what issues need to be resolved in Chongqing.The models and approaches for this study can be applied to other regions of China as long as all the assumptions are well defined and modified to find a substitute automotive energy source and establish an energy policy in a specific region.

  13. Thermodynamic modeling of a gas micro turbine power system; Modelagem termodinamica de uma microturbina a gas

    Energy Technology Data Exchange (ETDEWEB)

    Venson, Giuliano Gardolinski [Universidade Federal de Minas Gerais (UFMG), Belo Horizonte, MG (Brazil). Dept. de Engenharia Mecanica], e-mail: venson@ufmg.br; Barros, Jose Eduardo Mautone; Pereira, Josemar Figueiredo [Centro Federal de Educacao Tecnologica de Minas Gerais (CEFET-MG), Belo Horizonte, MG (Brazil)], e-mail: mautone@des.cefetmg.br, e-mail: josemar_cefet@yahoo.com.br

    2006-07-01

    This work presents the modeling of a gas microturbine power generator. The microturbine consists in a small thermo-electrical power unit, design for combined heat and power generation. The unit has an electric generator, coaxially connected with a turbocharger, which one is driven by a fuel burner. The system also incorporates an air regenerator, used for pre-heat the combustion air, and a heat exchanger, used for water heating. The objective of the modeling is the attainment of the electrical performance and the operational limits for the microturbine in function of the subsystems operational conditions. The modeling is based on the first law of the thermodynamic, using specific models for each component. In the combustion chamber is used a model that takes the fuel injection properties, as absolute pressure and temperature. A semi-empirical model, based in the modified Euler equation, is used in the turbocharger. In the air regenerator and heat exchanger, the method of mean logarithmic temperature difference is used. Through the modeling of a commercial microturbine, reference values obtained were used in some subsystems of a new microturbine. The results for this new microturbine in development, based in automotive turbochargers, indicate a nominal electrical power of 38 kW with electrical efficiency of 33% and global efficiency of 73%. (author)

  14. Impact design methods for ceramic components in gas turbine engines

    Science.gov (United States)

    Song, J.; Cuccio, J.; Kington, H.

    1991-01-01

    Methods currently under development to design ceramic turbine components with improved impact resistance are presented. Two different modes of impact damage are identified and characterized, i.e., structural damage and local damage. The entire computation is incorporated into the EPIC computer code. Model capability is demonstrated by simulating instrumented plate impact and particle impact tests.

  15. Cooling of gas turbines IX : cooling effects from use of ceramic coatings on water-cooled turbine blades

    Science.gov (United States)

    Brown, W Byron; Livingood, John N B

    1948-01-01

    The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the trailing part of such narrow blades, a theoretical study has been made of the cooling effect of a ceramic coating on: (1) the blade-metal temperature when the gas temperature is unchanged, and (2) the gas temperature when the metal temperature is unchanged. Comparison is also made between the changes in the blade or gas temperatures produced by ceramic coatings and the changes produced by moving the cooling passages nearer the trailing edge. This comparison was made to provide a standard for evaluating the gains obtainable with ceramic coatings as compared to those obtainable by constructing the turbine blade in such a manner that water passages could be located very near the trailing edge.

  16. Influence of Residence Time on Fuel Spray Sauter Mean Diameter (SMD) and emissions using Biodiesel and its Blends in a Low NOx Gas Turbine Combustor

    OpenAIRE

    Altaher, MA; Li, H.; Andrews, GE

    2016-01-01

    Biodiesels have advantages of low carbon footprint, reduced toxic emissions, improved energy supply security and sustainability and therefore attracted attentions in both industrial and aero gas turbines sectors. Industrial gas turbine applications are more practical biodiesels due to low temperature waxing and flow problems at altitude for aero gas turbine applications. This paper investigated the use of biodiesels in a low NOx radial swirler, as used in some industrial low NOx gas turbines....

  17. Modeling and simulation of combined gas turbine engine and heat pipe system for waste heat recovery and utilization

    Energy Technology Data Exchange (ETDEWEB)

    Lamfon, N.J. [Saudi Aramco Jeddah Refinery, Jeddah (Saudi Arabia); Najjar, Y.S.H.; Akyurt, M. [King Abdulaziz Univ., Mechanical Engineering Dept., Jeddah (Saudi Arabia)

    1998-12-01

    The results of a modeling and simulation study are presented for a combined system consisting of a gas turbine engine, a heat pipe recovery system and an inlet-air cooling system. The presentation covers performance data related to the gas turbine engine with precooled air intake as coupled to the water-in-copper heat pipe recovery system. This is done by matching the two mathematical models. The net power output is improved by 11% when the gas turbine engine is supplied with cold air produced by the heat-pipe recovery and utilization system. It is further concluded from the results produced by the combined mathematical model that the thermal efficiency of the gas turbine engine rises to 6% at 75% part load. It is to be anticipated that this rising trend in increases of thermal efficiency of the gas turbine engine would continue for operations at other (lower) part load conditions. (author)

  18. Variable geometry gas turbines for improving the part-load performance of marine combined cycles - Combined cycle performance

    DEFF Research Database (Denmark)

    Haglind, Fredrik

    2011-01-01

    The part-load performance of combined cycles intended for naval use is of great importance, and it is influenced by the gas turbine configuration and load control strategy. This paper is aimed at quantifying the effects of variable geometry gas turbines on the part-load efficiency for combined...... cycles used for ship propulsion. Moreover, the paper is aimed at developing methodologies and deriving models for part-load simulations suitable for energy system analysis of various components within combined cycle power plants. Two different gas turbine configurations are studied, a two-shaft aero......-derivative configuration and a single-shaft industrial configuration. The results suggest that by the use of variable geometry gas turbines, the combined cycle part-load performance can be improved. In order to minimise the voyage fuel consumption, a combined cycle featuring two-shaft gas turbines with VAN control...

  19. A review of potential turbine technology options for improving the off-design performance of direct coal-fired gas turbines in base load service. Second topical report

    Energy Technology Data Exchange (ETDEWEB)

    Thomas, R.L.

    1988-03-01

    The January, 1988 draft topical report, entitled ``An Assessment of Off-Design Particle Control Performance on Direct Coal-Fired Gas Turbine Systems`` [Ref.1.1], identified the need to assess potential trade-offs in turbine aerodynamic and thermodynamic design which may offer improvements in the performance, operational and maintenance characteristics of open-cycle, direct coal-fired, combustion gas turbines. In this second of a series of three topical reports, an assessment of the technical options posed by the above trade-offs is presented. The assessment is based on the current status of gas turbine technology. Several industry and university experts were contacted to contribute to the study. Literature sources and theoretical considerations are used only to provide additional background and insight to the technology involved.

  20. A review of potential turbine technology options for improving the off-design performance of direct coal-fired gas turbines in base load service

    Energy Technology Data Exchange (ETDEWEB)

    Thomas, R.L.

    1988-03-01

    The January, 1988 draft topical report, entitled An Assessment of Off-Design Particle Control Performance on Direct Coal-Fired Gas Turbine Systems'' (Ref.1.1), identified the need to assess potential trade-offs in turbine aerodynamic and thermodynamic design which may offer improvements in the performance, operational and maintenance characteristics of open-cycle, direct coal-fired, combustion gas turbines. In this second of a series of three topical reports, an assessment of the technical options posed by the above trade-offs is presented. The assessment is based on the current status of gas turbine technology. Several industry and university experts were contacted to contribute to the study. Literature sources and theoretical considerations are used only to provide additional background and insight to the technology involved.

  1. Feasibility of Ericsson type isothermal expansion/compression gas turbine cycle for nuclear energy use

    International Nuclear Information System (INIS)

    A gas turbine with potential demand for the next generation nuclear energy use such as HTGR power plants, a gas cooled FBR, a gas cooled nuclear fusion reactor uses helium as working gas and with a closed cycle. Materials constituting a cycle must be set lower than allowable temperature in terms of mechanical strength and radioactivity containment performance and so expansion inlet temperature is remarkably limited. For thermal efficiency improvement, isothermal expansion/isothermal compression Ericsson type gas turbine cycle should be developed using wet surface of an expansion/compressor casing and a duct between stators without depending on an outside heat exchanger performing multistage re-heat/multistage intermediate cooling. Feasibility of an Ericsson cycle in comparison with a Brayton cycle and multi-stage compression/expansion cycle was studied and technologies to be developed were clarified. (author)

  2. FY 1998 annual report. Research and development on ceramic gas turbine (300kW class)

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1999-04-01

    Research and development have been made on a small ceramic gas turbine which is high in efficiency, low in pollutant emission, capable of corresponding to different fuels, and can be utilized in cogeneration and/or movable electric power generation systems. Fundamental researches in developing and researching heat resistant ceramic parts have been carried out on a method for fabricating turbine nozzles using heat resistant silicon nitride, improvement in accuracy in fabricating combustors using the heat resistant silicon nitride, and casting of turbine blades made from sialon. In developing the devices, researches were made on reliability of bond between a ceramic blade and a metallic disk, air-fuel ratio in a combustor, distribution of fuel concentrations, fuel injection methods, reduction of loss in a diffuser in a compressor, and matching of the diffuser with an impeller. In addition, research and development were performed on a single shaft ceramic gas turbine for cogeneration and a double shaft ceramic gas turbine. Researches were executed on reliability of ceramic materials. (NEDO)

  3. Effects of Gas Turbine Component Performance on Engine and Rotary Wing Vehicle Size and Performance

    Science.gov (United States)

    Snyder, Christopher A.; Thurman, Douglas R.

    2010-01-01

    In support of the Fundamental Aeronautics Program, Subsonic Rotary Wing Project, further gas turbine engine studies have been performed to quantify the effects of advanced gas turbine technologies on engine weight and fuel efficiency and the subsequent effects on a civilian rotary wing vehicle size and mission fuel. The Large Civil Tiltrotor (LCTR) vehicle and mission and a previous gas turbine engine study will be discussed as a starting point for this effort. Methodology used to assess effects of different compressor and turbine component performance on engine size, weight and fuel efficiency will be presented. A process to relate engine performance to overall LCTR vehicle size and fuel use will also be given. Technology assumptions and levels of performance used in this analysis for the compressor and turbine components performances will be discussed. Optimum cycles (in terms of power specific fuel consumption) will be determined with subsequent engine weight analysis. The combination of engine weight and specific fuel consumption will be used to estimate their effect on the overall LCTR vehicle size and mission fuel usage. All results will be summarized to help suggest which component performance areas have the most effect on the overall mission.

  4. Comparative numerical investigation of a wood residues indirectly fired gas turbine

    Energy Technology Data Exchange (ETDEWEB)

    Ngoma, G. [Quebec Univ., Abitibi-Temiscaminque, PQ (Canada). Dept. of Applied Sciences

    2005-07-01

    Two models of an indirectly fired gas turbine that used both wood residues and natural gas combustors were presented. A Brayton cycle concept was used for the modelling calculations. The first model used wood residues burned in a combustor, where the resulting flue gases were used to preheat the air from a regenerator. In the second model, flue gases were used to preheat the air from the compressor. A computer program was developed from separate thermodynamic models of the compressor, regenerator, wood combustor, natural gas combustor, and gas turbine. The program was then used to calculate the mass and energy balances for each component. Irreversibilities within the compressor and the turbine were accounted for by using isentropic efficiencies. Numerical simulations were then performed to predict the static behaviour of the combustors. Results showed the effects of regenerator effectiveness, mass flow rate, compressor pressure ratio and gas turbine inlet temperature on the overall thermal efficiency. The results of both models were then compared. It was concluded that the model that preheated air from the compressor was more efficient than the model that preheated air from the regenerator. 6 refs., 11 figs.

  5. Cost Benefit Analysis of Using Clean Energy Supplies to Reduce Greenhouse Gas Emissions of Global Automotive Manufacturing

    Directory of Open Access Journals (Sweden)

    Xiang Zhao

    2011-09-01

    Full Text Available Automotive manufacturing is energy-intensive. The consumed energy contributes to the generation of significant amounts of greenhouse gas (GHG emissions by the automotive manufacturing industry. In this paper, a study is conducted on assessing the application potential of such clean energy power systems as solar PV, wind and fuel cells in reducing the GHG emissions of the global auto manufacturing industry. The study is conducted on the representative solar PV, wind and fuel cell clean energy systems available on the commercial market in six representative locations of GM’s global facilities, including the United States, Mexico, Brazil, China, Egypt and Germany. The results demonstrate that wind power is superior to other two clean energy technologies in the economic performance of the GHG mitigation effect. Among these six selected countries, the highest GHG emission mitigation potential is in China, through wind power supply. The maximum GHG reduction could be up to 60 tons per $1,000 economic investment on wind energy supply in China. The application of wind power systems in the United States and Germany could also obtain relatively high GHG reductions of between 40–50 tons per $1,000 economic input. When compared with wind energy, the use of solar and fuel cell power systems have much less potential for GHG mitigation in the six countries selected. The range of median GHG mitigation values resulting from solar and wind power supply are almost at the same level.

  6. Analysis of characteristics of different working fluids for gas turbine cycle with high temperature gas-cooled reactor

    International Nuclear Information System (INIS)

    Gas turbine cycle with high temperature gas-cooled reactor is the main direction of nuclear energy generation, which is with the advantages in terms of the safety and economy. The thermal and physical properties of helium, nitrogen, carbon dioxide and the mixtures were compared and analyzed in this paper. Further more, the heat transfer coefficient, pressure loss and the stage number of turbo-machines have been also compared. Results indicate that taking the mixture of helium and carbon dioxide as the working fluid of gas turbine cycle with high temperature gas-cooled reactor can not only improve the heat transfer coefficient and decrease the stage number of turbo-machinery, but also can limit the pressure loss to a certain level. (authors)

  7. Practical problems relating to the hovercraft application of marine gas turbines

    Science.gov (United States)

    Jin-Zhang, Z.

    Design specifications of the marine gas turbine in a hovercraft application are discussed, in addition to the requirements for load distribution of the turbine power in this application. The effective load of the gas turbine is found to be about 57 percent higher than that of the air-cooled diesel engine, and a comparison between the two engines indicates that the effective load of the diesel-driven boat becomes advantageous only when the endurance is more than 26 hours. A multistage filter for air-water separation could reduce the salt content to less than 0.01 ppm where the pressure loss is less than 100 mm water head, and a low profile-resistance ejector without a mixing section could be developed to reduce the engine room pressure to the 45-50 C range.

  8. Ion beam analysis of gas turbine blades: evaluation of refurbishment quality

    Indian Academy of Sciences (India)

    O Kakuee; V Fathollahi; P Oliaiy; D Agha-Aligol; M Lamehi-Rachti

    2015-04-01

    Refurbishment of hot components of gas turbines damaged in the harsh working environments is necessary to increase their lifetime. Scanning proton microscopy was employed to evaluate the quality of refurbishment process of gas turbine blades. Distribution patterns of different elements were observed in the polished cross-sections of turbine blade samples by proton microbeam. In the cross-sections of refurbished and used samples, distinct regions were identified corresponding to the base superalloy, original protection layer and applied coating for refurbishment. The elemental composition of each of these regions was measured by Micro-PIXE analysis. Inhomogeneous and high content of Si as well as undesired light elements were observed in the cross-sections of refurbished samples, indicating imperfections in the refurbishment process.

  9. A Plan for Revolutionary Change in Gas Turbine Engine Control System Architecture

    Science.gov (United States)

    Culley, Dennis E.

    2011-01-01

    The implementation of Distributed Engine Control technology on the gas turbine engine has been a vexing challenge for the controls community. A successful implementation requires the resolution of multiple technical issues in areas such as network communications, power distribution, and system integration, but especially in the area of high temperature electronics. Impeding the achievement has been the lack of a clearly articulated message about the importance of the distributed control technology to future turbine engine system goals and objectives. To resolve these issues and bring the technology to fruition has, and will continue to require, a broad coalition of resources from government, industry, and academia. This presentation will describe the broad challenges facing the next generation of advanced control systems and the plan which is being put into action to successfully implement the technology on the next generation of gas turbine engine systems.

  10. Power plant including an exhaust gas recirculation system for injecting recirculated exhaust gases in the fuel and compressed air of a gas turbine engine

    Science.gov (United States)

    Anand, Ashok Kumar; Nagarjuna Reddy, Thirumala Reddy; Shaffer, Jason Brian; York, William David

    2014-05-13

    A power plant is provided and includes a gas turbine engine having a combustor in which compressed gas and fuel are mixed and combusted, first and second supply lines respectively coupled to the combustor and respectively configured to supply the compressed gas and the fuel to the combustor and an exhaust gas recirculation (EGR) system to re-circulate exhaust gas produced by the gas turbine engine toward the combustor. The EGR system is coupled to the first and second supply lines and configured to combine first and second portions of the re-circulated exhaust gas with the compressed gas and the fuel at the first and second supply lines, respectively.

  11. The design of modern gas turbine design : beyond CFD

    Energy Technology Data Exchange (ETDEWEB)

    Kenny, D.P. [Pratt and Whitney Canada, Longueuil, PQ (Canada)

    1998-09-01

    The progress that has been made in recent years of applying computational fluid dynamics (CFD) to the design of advanced turbine engines was discussed. Pratt and Whitney has successfully transitioned the design of the company`s advanced turbine engines from a five-year design cycle based on a succession of design-test-redesign cycles to a three-year design cycle based on an analytical design methodology. The development of 3-D viscous CFD and computational structural mechanics (CSM) codes as primary design tools and a multi-disciplinary approach to applications have been major factors in achieving this success. The company also made significant progress in the development of a fully implicit unsteady stage scheme, with marked impact on performance and durability. Improvements also have been made in the life of the hot end components and in aero-acoustics. 9 figs.

  12. Some advantages of methane in an aircraft gas turbine

    Science.gov (United States)

    Graham, R. W.; Glassman, A. J.

    1980-01-01

    Liquid methane, which can be manufactured from any of the hydrocarbon sources such as coal, shale biomass, and organic waste considered as a petroleum replacement for aircraft fuels. A simple cycle analysis is carried out for a turboprop engine flying a Mach 0.8 and 10, 688 meters (35,000 ft.) altitude. Cycle performance comparisions are rendered for four cases in which the turbine cooling air is cooled or not cooled by the methane fuel. The advantages and disadvantages of involving the fuel in the turbine cooling system are discussed. Methane combustion characteristics are appreciably different from Jet A and will require different combustor designs. Although a number of similar difficult technical problems exist, a highly fuel efficient turboprop engine burning methane appear to be feasible.

  13. Enabling Technology for Monitoring & Predicting Gas Turbine Health & Performance in COAL IGCC Powerplants

    Energy Technology Data Exchange (ETDEWEB)

    Kenneth A. Yackly

    2004-09-30

    The ''Enabling & Information Technology To Increase RAM for Advanced Powerplants'' program, by DOE request, has been re-directed, de-scoped to two tasks, shortened to a 2-year period of performance, and refocused to develop, validate and accelerate the commercial use of enabling materials technologies and sensors for Coal IGCC powerplants. The new program has been re-titled as ''Enabling Technology for Monitoring & Predicting Gas Turbine Health & Performance in IGCC Powerplants'' to better match the new scope. This technical progress report summarizes the work accomplished in the reporting period April 1, 2004 to August 31, 2004 on the revised Re-Directed and De-Scoped program activity. The program Tasks are: Task 1--IGCC Environmental Impact on high Temperature Materials: This first materials task has been refocused to address Coal IGCC environmental impacts on high temperature materials use in gas turbines and remains in the program. This task will screen material performance and quantify the effects of high temperature erosion and corrosion of hot gas path materials in Coal IGCC applications. The materials of interest will include those in current service as well as advanced, high-performance alloys and coatings. Task 2--Material In-Service Health Monitoring: This second task develops and demonstrates new sensor technologies to determine the in-service health of advanced technology Coal IGCC powerplants, and remains in the program with a reduced scope. Its focus is now on only two critical sensor need areas for advanced Coal IGCC gas turbines: (1) Fuel Quality Sensor for detection of fuel impurities that could lead to rapid component degradation, and a Fuel Heating Value Sensor to rapidly determine the fuel heating value for more precise control of the gas turbine, and (2) Infra-Red Pyrometer to continuously measure the temperature of gas turbine buckets, nozzles, and combustor hardware.

  14. Numerical simulation of oxy-fuel combustion for gas turbine applications

    International Nuclear Information System (INIS)

    Relevant reduction on worldwide greenhouse gases emissions shall be based on more efficient power generation systems linked to a carbon capture and storage technology (CCS). Integrated gasification combined cycle and natural gas combined cycle (IGCC) would play an effective role to these objectives. To that, oxy-fuel combustion is an important alternative for the implementation of CCS technology, claiming, however, modifications to the conventional operation of gas turbines combustors. This work presents CFD simulations of oxy-fuel combustion in a can-type model gas turbine combustor. Equilibrium combustion model for non-premixed flames was used to model chemical reactions and turbulence was accounted for by Reynolds Stress Model (RSM). Numerical predictions were carried out after validating the numerical schemes and turbulence model. In addition to the baseline (propane/air combustion) four oxy-fuel cases were studied: propane and syngas oxy-fuel combustion with two different O2/CO2 ratios. The predictions showed that the propane/oxy-fuel flame (O2/CO2 = 1) resembles the baseline case (propane/air) though, with much higher temperature levels in the central core of the combustor, resulting in a poor gas turbine combustor pattern factor. The oxy-syngas flames showed intense reactions in the primary zone, before the first dilution holes, leading to a very good patter factor. The numerical model proposed for this study can be considered a relevant tool in the preliminary design phase of gas turbine combustors applied to CCS technology. - Highlights: • A gas turbine combustion chamber model was numerically simulated. • The numerical model was validated against experimental data for isothermal flow. • CCS technology based on oxy-fuel combustion for propane and syngas were studied. • The syngas cases showed improved pattern factors compared to the Propane/Air case. • The oxy-fuel combustion based on syngas seemed adequate for CCS technology

  15. Stress analysis and life prediction of gas turbine blade

    Science.gov (United States)

    Hsiung, H. C.; Dunn, A. J.; Woodling, D. R.; Loh, D. L.

    1988-01-01

    A stress analysis procedure is presented for a redesign of the Space Shuttle Main Engine high pressure fuel turbopump turbine blades. The analysis consists of the one-dimensional scoping analysis to support the design layout and the follow-on three-dimensional finite element analysis to confirm the blade design at operating loading conditions. Blade life is evaluated based on high-cycle fatigue and low-cycle fatigue.

  16. Impact of Dissociation and Sensible Heat Release on Pulse Detonation and Gas Turbine Engine Performance

    Science.gov (United States)

    Povinelli, Louis A.

    2001-01-01

    A thermodynamic cycle analysis of the effect of sensible heat release on the relative performance of pulse detonation and gas turbine engines is presented. Dissociation losses in the PDE (Pulse Detonation Engine) are found to cause a substantial decrease in engine performance parameters.

  17. Testing of a Hydrogen Diffusion Flame Array Injector at Gas Turbine Conditions

    Energy Technology Data Exchange (ETDEWEB)

    Weiland, Nathan T.; Sidwell, Todd G.; Strakey, Peter A.

    2013-07-03

    High-hydrogen gas turbines enable integration of carbon sequestration into coal-gasifying power plants, though NO{sub x} emissions are often high. This work explores nitrogen dilution of hydrogen diffusion flames to reduce thermal NO{sub x} emissions and avoid problems with premixing hydrogen at gas turbine pressures and temperatures. The burner design includes an array of high-velocity coaxial fuel and air injectors, which balances stability and ignition performance, combustor pressure drop, and flame residence time. Testing of this array injector at representative gas turbine conditions (16 atm and 1750 K firing temperature) yields 4.4 ppmv NO{sub x} at 15% O{sub 2} equivalent. NO{sub x} emissions are proportional to flame residence times, though these deviate from expected scaling due to active combustor cooling and merged flame behavior. The results demonstrate that nitrogen dilution in combination with high velocities can provide low NO{sub x} hydrogen combustion at gas turbine conditions, with significant potential for further NO{sub x} reductions via suggested design changes.

  18. 77 FR 52553 - Standards of Performance for Stationary Gas Turbines; Standards of Performance for Stationary...

    Science.gov (United States)

    2012-08-29

    ... significantly impact the emissions rate since typical low NO X natural gas-fired duct burners contribute between... duct burner. Therefore, we are proposing that the NO X standard be based on the type of fuel being... gases to generate electricity in stationary combustion turbines (see 74 FR 11858, March 20, 2009)....

  19. Bioethanol combustion in an industrial gas turbine combustor: simulations and experiments

    NARCIS (Netherlands)

    Sallevelt, J.L.H.P.; Pozarlik, A.K.; Beran, Martin; Axelsson, L.; Brem, G.

    2014-01-01

    Combustion tests with bioethanol and diesel as a reference have been performed in OPRA's 2 MWe class OP16 gas turbine combustor. The main purposes of this work are to investigate the combustion quality of ethanol with respect to diesel and to validate the developed CFD model for ethanol spray combus

  20. COMBINED CYCLE GAS TURBINE FOR THERMAL POWER STATIONS: EXPERIENCE IN DESIGNING AND OPERATION, PROSPECTS IN APPLICATION

    Directory of Open Access Journals (Sweden)

    N. V. Karnitsky

    2014-01-01

    Full Text Available The paper has reviewed main world tendencies in power consumption and power system structure. Main schemes of combined cycle gas turbines have been considered in the paper. The paper contains an operational analysis of CCGT blocks that are operating within the Belarusian energy system. The analysis results have been given in tables showing main operational indices of power blocks

  1. Advanced biomass power generation: The biomass-integrated gasifier/gas turbine and beyond

    International Nuclear Information System (INIS)

    The most promising initial strategy for modernizing bioenergy is the production of electricity or the cogeneration of electricity and heat using advanced gas turbines fired by gasified biomass. The major advances that have been made in coal gasification technology, to marry the gas turbine to coal, are readily adaptable to biomass applications. integrating biomass gasifiers with aeroderivative gas turbines in particular makes it possible to achieve high efficiencies and low unit capital costs at the modest scales required with bioenergy systems. Beyond the turn of the century fuel cells operated on gasified biomass offer the promise of even higher performance levels. For the near term, electricity produced with biomass-integrated gasifier/gas turbine (BIG/GT) power systems not only offers major environmental benefits but also would be competitive with electricity produced from fossil fuels and nuclear energy in a wide range of circumstances. It is reasonable to expect that biomass could be providing 25-35% of total global power generation in the second quarter of the next century, helping make it possible to substantially reduce CO2 emissions from the power sector relative to present levels in that time frame

  2. 77 FR 76842 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Science.gov (United States)

    2012-12-31

    ... Aircraft Gas Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation... Environmental Protection Agency (EPA) proposed new aircraft engine emission standards for oxides of nitrogen (NO... turbojet engines with rated thrusts greater than 26.7 kilonewtons (kN) (76 FR 45012, July 27, 2011)....

  3. 78 FR 63015 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Science.gov (United States)

    2013-10-23

    ... Aircraft Gas Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation... aircraft engines which, in the EPA Administrator's judgment, causes or contributes to air pollution that... aircraft engine emission standards for oxides of nitrogen (NO X ), compliance flexibilities, and...

  4. 78 FR 63017 - Exhaust Emissions Standards for New Aircraft Gas Turbine Engines and Identification Plate for...

    Science.gov (United States)

    2013-10-23

    ... Aircraft Gas Turbine Engines and Identification Plate for Aircraft Engines AGENCY: Federal Aviation... emission of any air pollutant from classes of aircraft engines which, in the EPA Administrator's judgment... standards. On July 27, 2011, the EPA proposed new aircraft engine emission standards for oxides of...

  5. Advanced gas turbine systems research. Technical quarterly progress report, January 1--March 31, 1998

    Energy Technology Data Exchange (ETDEWEB)

    NONE

    1998-08-01

    Major accomplishments by AGTSR during this reporting period are highlighted and then amplified in later sections of this report. Main areas of research are combustion, heat transfer, and materials. Gas turbines are used for power generation by utilities and industry and for propulsion.

  6. Review of some energy and environmental aspects of the gas turbine engine

    Energy Technology Data Exchange (ETDEWEB)

    Najjar, Y.S.H.; Akyurt, M.; Al-Rabghi, O.M.; Alp, T. (King Abdulaziz Univ., Jeddah (Saudi Arabia). College of Engineering)

    1994-01-01

    Gas turbine engine technology has been developed continuously in diverse areas such as cycle analysis, including novel cycles and second-law analyses; design, development and economic maintenance; combustion and environment; in addition to modeling, simulation and performance of engine components. A brief review of these areas is presented to highlight future trends. (author)

  7. Analysis and design of digital output interface devices for gas turbine electronic controls

    Science.gov (United States)

    Newirth, D. M.; Koenig, E. W.

    1976-01-01

    A trade study was performed on twenty-one digital output interface schemes for gas turbine electronic controls to select the most promising scheme based on criteria of reliability, performance, cost, and sampling requirements. The most promising scheme, a digital effector with optical feedback of the fuel metering valve position, was designed.

  8. The generation of electricity by gas turbines using the catalytic combustion of low-Btu gases

    DEFF Research Database (Denmark)

    Frederiksen, O.P.; Qvale, Einar Bjørn

    1989-01-01

    Various systems for the generation of electricity by gas turbines using catalytic combustion of low-Btu gases have been investigated. Parametric studies of three configurations that are deemed to be practically feasible have been completed. It is shown that thermodynamic efficiency of these systems...

  9. Vibro-acoustical instabilities induced by combustion dynamics in gas turbine combustors

    NARCIS (Netherlands)

    Pozarlik, Artur

    2010-01-01

    The lean premixed combustion suffers from a high sensitivity to thermo-acoustic instabilities which may occur in a combustion chamber of a gas turbine. The high level of acoustic excitation is hazardous to the combustion chamber walls (liner). The situation is even worse when mutual interaction betw

  10. Power Enhancement of Gas Turbine Plant by Intake Air Fog Cooling

    Directory of Open Access Journals (Sweden)

    J. P. Yadav

    2012-08-01

    Full Text Available Performance of gas turbine significantly depends upon the ambient air temperature and mass flow rate. During summer season the density of the air decreases which affects the mass flow rate and ultimately the power output of a gas turbine is reduced. In order to overcome this situation several techniques are already in the practice and one of the most effective and economical is adopting the inlet fog cooling which basically enhances the power output of the machine. The cooling of ambient air by fog cooling up to wet bulb temperature increases the mass flow rate on account of increase in air density, as a result it ultimately increases the power output of a gas turbine. Fogging is applied with consideration of relative humidity of ambient air not only during summer season but also during dry days of summer season in order to increase the power output of gas turbine. This paper describes the effect on percentage enhancement of power output adopting various fuel options with low and high humidity ambient conditions. The results indicate the potential increase in the power output up to 14�20It is also observed that the total cost of power production increases due to increase in fuel consumption on account of enhanced power output. Thus, the optimum operating parameters are required for taking advantage of power augmentation ensuring that it does not lead to excessive increase in fuel cost.

  11. Planar laser-induced fluorescence fuel imaging during gas-turbine relight

    DEFF Research Database (Denmark)

    Read, Robert; Rogerson, J.W.; Hochgreb, S.

    2013-01-01

    This experimental study investigates the influence of fuel distribution on ignition outcome during high-altitude relight of a gas turbine. Planar laser-induced fluorescence is used to image fuel inside a lean direct-injection combustor under realistic conditions. A novel apparatus is developed...

  12. Gas Turbine Engine Staged Fuel Injection Using Adjacent Bluff Body and Swirler Fuel Injectors

    Science.gov (United States)

    Snyder, Timothy S. (Inventor)

    2015-01-01

    A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.

  13. The Gas Turbine: Technical Terminology Bulletin. Terminotech, Vol. 2, No. 5.

    Science.gov (United States)

    General Electric Co. of Canada, Ltd., Montreal, Quebec.

    This issue of a bulletin of technological terminology is devoted to the gas turbine. A brief narrative on the subject is presented in both French and English. An English-French dictionary of terms comprises the bulk of the document. Explanatory illustrations are appended. (JB)

  14. Development of sprayed ceramic seal systems for turbine gas path sealing

    Science.gov (United States)

    Bill, R. C.; Shiembob, L. T.; Stewart, O. L.

    1978-01-01

    A ceramic seal system is reported that employs plasma-sprayed graded metal/ceramic yttria stabilized zirconium oxide (YSZ). The performance characteristics of several YSZ configurations were determined through rig testing for thermal shock resistance, abradability, and erosion resistance. Results indicate that this type of sealing system offers the potential to meet operating requirements of future gas turbine engines.

  15. Performance and economic enhancement of cogeneration gas turbines through compressor inlet air cooling

    Science.gov (United States)

    Delucia, M.; Bronconi, R.; Carnevale, E.

    1994-04-01

    Gas turbine air cooling systems serve to raise performance to peak power levels during the hot months when high atmospheric temperatures cause reductions in net power output. This work describes the technical and economic advantages of providing a compressor inlet air cooling system to increase the gas turbine's power rating and reduce its heat rate. The pros and cons of state-of-the-art cooling technologies, i.e., absorption and compression refrigeration, with and without thermal energy storage, were examined in order to select the most suitable cooling solution. Heavy-duty gas turbine cogeneration systems with and without absorption units were modeled, as well as various industrial sectors, i.e., paper and pulp, pharmaceuticals, food processing, textiles, tanning, and building materials. The ambient temperature variations were modeled so the effects of climate could be accounted for in the simulation. The results validated the advantages of gas turbine cogeneration with absorption air cooling as compared to other systems without air cooling.

  16. A framework with nonlinear system model and nonparametric noise for gas turbine degradation state estimation

    International Nuclear Information System (INIS)

    Modern health management approaches for gas turbine engines (GTEs) aim to precisely estimate the health state of the GTE components to optimize maintenance decisions with respect to both economy and safety. In this research, we propose an advanced framework to identify the most likely degradation state of the turbine section in a GTE for prognostics and health management (PHM) applications. A novel nonlinear thermodynamic model is used to predict the performance parameters of the GTE given the measurements. The ratio between real efficiency of the GTE and simulated efficiency in the newly installed condition is defined as the health indicator and provided at each sequence. The symptom of nonrecoverable degradations in the turbine section, i.e. loss of turbine efficiency, is assumed to be the internal degradation state. A regularized auxiliary particle filter (RAPF) is developed to sequentially estimate the internal degradation state in nonuniform time sequences upon receiving sets of new measurements. The effectiveness of the technique is examined using the operating data over an entire time-between-overhaul cycle of a simple-cycle industrial GTE. The results clearly show the trend of degradation in the turbine section and the occasional fluctuations, which are well supported by the service history of the GTE. The research also suggests the efficacy of the proposed technique to monitor the health state of the turbine section of a GTE by implementing model-based PHM without the need for additional instrumentation. (paper)

  17. Thermal Impact of Operating Conditions on the Performance of a Combined Cycle Gas Turbine

    Directory of Open Access Journals (Sweden)

    Thamir K. Ibrahim

    2012-08-01

    Full Text Available The combined cycle gas-turbine (CCGT power plant is a highly developed technology which generates electricalpower at high efficiencies. The first law of thermodynamics is used for energy analysis of the performance of theCCGT plant. The effects of varying the operating conditions (ambient temperature, compression ratio, turbine inlettemperature, isentropic compressor and turbine efficiencies, and mass flow rate of steam on the performance of theCCGT (overall efficiency and total output power were investigated. The programming of the performance model forCCGT was developed utilizing MATLAB software. The simulation results for CCGT show that the overall efficiencyincreases with increases in the compression ratio and turbine inlet temperature and with decreases in ambienttemperature. The total power output increases with increases in the compression ratio, ambient temperature, andturbine inlet temperature. The peak overall efficiency was reached with a higher compression ratio and low ambienttemperature. The overall efficiencies for CCGT were very high compared to the thermal efficiency of GT plants. Theoverall thermal efficiency of the CCGT quoted was around 57%; hence, the compression ratios, ambient temperature,turbine inlet temperature, isentropic compressor and turbine efficiencies, and mass flow rate of steam have a stronginfluence on the overall performance of the CCGT cycle.

  18. Fundamental mechanisms that influence the estimate of heat transfer to gas turbine blades

    Science.gov (United States)

    Graham, R. W.

    1979-01-01

    Estimates of the heat transfer from the gas to stationary (vanes) or rotating blades poses a major uncertainty due to the complexity of the heat transfer processes. The gas flow through these blade rows is three dimensional with complex secondary viscous flow patterns that interact with the endwalls and blade surfaces. In addition, upstream disturbances, stagnation flow, curvature effects, and flow acceleration complicate the thermal transport mechanisms in the boundary layers. Some of these fundamental heat transfer effects are discussed. The chief purpose of the discussion is to acquaint those in the heat transfer community, not directly involved in gas turbines, of the seriousness of the problem and to recommend some basic research that would improve the capability for predicting gas-side heat transfer on turbine blades and vanes.

  19. Analysis of the behaviour of biofuel-fired gas turbine power plants

    Directory of Open Access Journals (Sweden)

    Escudero Marcos

    2012-01-01

    Full Text Available The utilisation of biofuels in gas turbines is a promising alternative to fossil fuels for power generation. It would lead to a significant reduction of CO2 emissions using an existing combustion technology, although considerable changes appear to be required and further technological development is necessary. The goal of this work is to conduct energy and exergy analyses of the behaviour of gas turbines fired with biogas, ethanol and synthesis gas (bio-syngas, compared with natural gas. The global energy transformation process (i.e., from biomass to electricity also has been studied. Furthermore, the potential reduction of CO2 emissions attained by the use of biofuels has been determined, after considering the restrictions regarding biomass availability. Two different simulation tools have been used to accomplish this work. The results suggest a high interest in, and the technical viability of, the use of Biomass Integrated Gasification Combined Cycle (BioIGCC systems for large scale power generation.

  20. Schemes and New Developments in Combinations of Gasification with Fuel Gas Cleaning for Power Generation in Piston Gas Engines and Gas Turbines

    OpenAIRE

    Skoblia, S.

    2013-01-01

    In the contribution, possibilities are presented and discussed in details, how to employ the internal combustion engines and gas (combustion) turbines or their suitable combination for producing the electric power and heat from the gas produced by the partial oxidation (gasification) of biomass and alternative solid fuels.

  1. Fuel cell-gas turbine hybrid system design part I: Steady state performance

    Science.gov (United States)

    McLarty, Dustin; Brouwer, Jack; Samuelsen, Scott

    2014-07-01

    The hybridization of gas turbine technology with high temperature fuel cells represents an ultra-high efficiency, ultra-low emission, fuel flexible power generation platform. The performance of past prototypes has been limited by marginal compatibility of the two primary sub-systems. This paper addresses the challenge of selecting compatible hardware by presenting a simple and robust method for bespoke hybrid system design and off-the-shelf component integration. This is the first application of detailed, spatially resolved, physical models capable of resolving off-design performance to the integration analysis of FC-GT hybrids. Static maps are produced for both turbine and fuel cell sub-systems that readily evaluate the compatibility and hybrid performance. Molten carbonate and solid oxide fuel cells are considered for hybridization with recuperated micro-turbines and larger axial flow gas turbine systems. Current state-of-the-art molten carbonate technology is shown to pair well with present micro-turbine technology in an FC bottoming cycle design achieving 74.4% LHV efficiency. Solid oxide technology demonstrates remarkable potential for integration with larger scale axial turbo-machinery to achieve greater than 75% LHV efficiency. This performance map technique closely matches results from detailed integrated hybrid system analyses, and enables quick determination of performance requirements for balance of plant design and optimization.

  2. Fuzzy logic controller to improve parameters affecting gas turbines power generation

    Energy Technology Data Exchange (ETDEWEB)

    Mamlook, Rustom; Almazyad, Abdulaziz S.; Eldos, Taisir [Al-Kharj University, Department of Computer Engineering, College of Computer Engineering and Sciences, Al-Kharj (Saudi Arabia); Badran, Omar; Abdulhadi, Emad [Al-Balqa Applied University, Department of Mechatronics Engineering, Faculty of Engineering Technology, Amman (Jordan); Aljumah, Abdullah [Al-Kharj University, Department of Computer Engineering, College of Computer Engineering and Sciences, Al-Kharj (Saudi Arabia); Al-Balqa Applied University, Department of Mechatronics Engineering, Faculty of Engineering Technology, Amman (Jordan)

    2011-12-15

    In order to improve the performance of the gas turbine power plant and to generate electricity at the best cost, a fuzzy logic controller model was used to show the effect of different parameters on the power generation output of gas turbines. The proposed methodology was applied to certain parameter values collected from Rehab power station in Jordan - as a case study - for validation purposes. Relative weights were used, i.e., very very low power generation ''extremely low power generation,'' very low power generation, low power generation, normal power generation, high power generation, and very high power generation. The study reveals that the major factors that affect yield are ambient temperature (T{sub 1}), compressor's exit temperature (T{sub 2}), turbine's inlet temperature (T{sub 3}), turbine exit temperature (T{sub 4}), pressure ratio (R{sub p}), mass of fuel (M{sub f}), relative humidity (H), turbine efficiency ({eta}{sub t}), and compressor efficiency ({eta}{sub c}). Based on the increase of productivity, the results show that different factors are found to affect the yield of a power generator. Therefore, using fuzzy logic controller model has lead the researchers to focus on the highest priority parameters that should be enhanced and developed to increase the power output productivity. (orig.)

  3. High-temperature turbine technology program hot-gas path development test. Part II. Testing

    Energy Technology Data Exchange (ETDEWEB)

    Horner, M.W.

    1982-03-01

    This topical report of the US Department of Energy High-Temperature Turbine Technology (DOE-HTTT) Phase II program presents the results of testing full-scale water-cooled first-stage and second-stage turbine nozzles at design temperature and pressure to verify that the designs are adequate for operation in a full-scale turbine environment. Low-cycle fatigue life of the nozzles was demonstrated by subjecting cascade assemblies to several hundred simulated startup/shutdown turbine cycles. This testing was accomplished in the Hot-Gas Path Development Test Stand (HGPDTS), which is capable of evaluating full-scale combustion and turbine nozzle components. A three-throat cascade of the first-stage turbine nozzle was successfully tested at a nozzle inlet gas temperature of 2630/sup 0/F and a nozzle inlet pressure of 11.3 atmospheres. In addition to steady-state operation at the design firing temperature, the nozzle cascade was exposed to a simulated startup/shutdown turbine cycle by varying the firing temperature. A total of 42 h at the design point and 617 thermal cycles were accumulated during the test periods. First-stage nozzle test results show that measured metal and coolant temperatures correspond well to the predicted design values. This nozzle design has been shown to be fully satisfactory for the application (2600/sup 0/F), with growth capability to 3000/sup 0/F firing temperature. A post-test metallurgical examination of sectioned portions of the tested nozzles shows a totally bonded structure, confirming the test results and attesting to the successful performance of water-cooled composite nozzle hardware.

  4. Reduction of NOx Emissions from the Gas Turbines for Skarv Idun

    OpenAIRE

    Alne, Kristin Sundsbø

    2007-01-01

    Nitrogen oxides (NOx) are formed by oxidation of nitrogen during the combustion process, and production rate is highly affected by flame temperature. NOx is regarded as a local pollutant causing smog, acid rain and health complaints, and strictest emission regulations are found in urban areas. Reduction of NOx emissions from gas turbines can be achieved by modifying the combustion process or by exhaust gas clean up. Several technologies are already commercial available, but there are still a ...

  5. An ensemble of dynamic neural network identifiers for fault detection and isolation of gas turbine engines.

    Science.gov (United States)

    Amozegar, M; Khorasani, K

    2016-04-01

    In this paper, a new approach for Fault Detection and Isolation (FDI) of gas turbine engines is proposed by developing an ensemble of dynamic neural network identifiers. For health monitoring of the gas turbine engine, its dynamics is first identified by constructing three separate or individual dynamic neural network architectures. Specifically, a dynamic multi-layer perceptron (MLP), a dynamic radial-basis function (RBF) neural network, and a dynamic support vector machine (SVM) are trained to individually identify and represent the gas turbine engine dynamics. Next, three ensemble-based techniques are developed to represent the gas turbine engine dynamics, namely, two heterogeneous ensemble models and one homogeneous ensemble model. It is first shown that all ensemble approaches do significantly improve the overall performance and accuracy of the developed system identification scheme when compared to each of the stand-alone solutions. The best selected stand-alone model (i.e., the dynamic RBF network) and the best selected ensemble architecture (i.e., the heterogeneous ensemble) in terms of their performances in achieving an accurate system identification are then selected for solving the FDI task. The required residual signals are generated by using both a single model-based solution and an ensemble-based solution under various gas turbine engine health conditions. Our extensive simulation studies demonstrate that the fault detection and isolation task achieved by using the residuals that are obtained from the dynamic ensemble scheme results in a significantly more accurate and reliable performance as illustrated through detailed quantitative confusion matrix analysis and comparative studies. PMID:26881999

  6. An ensemble of dynamic neural network identifiers for fault detection and isolation of gas turbine engines.

    Science.gov (United States)

    Amozegar, M; Khorasani, K

    2016-04-01

    In this paper, a new approach for Fault Detection and Isolation (FDI) of gas turbine engines is proposed by developing an ensemble of dynamic neural network identifiers. For health monitoring of the gas turbine engine, its dynamics is first identified by constructing three separate or individual dynamic neural network architectures. Specifically, a dynamic multi-layer perceptron (MLP), a dynamic radial-basis function (RBF) neural network, and a dynamic support vector machine (SVM) are trained to individually identify and represent the gas turbine engine dynamics. Next, three ensemble-based techniques are developed to represent the gas turbine engine dynamics, namely, two heterogeneous ensemble models and one homogeneous ensemble model. It is first shown that all ensemble approaches do significantly improve the overall performance and accuracy of the developed system identification scheme when compared to each of the stand-alone solutions. The best selected stand-alone model (i.e., the dynamic RBF network) and the best selected ensemble architecture (i.e., the heterogeneous ensemble) in terms of their performances in achieving an accurate system identification are then selected for solving the FDI task. The required residual signals are generated by using both a single model-based solution and an ensemble-based solution under various gas turbine engine health conditions. Our extensive simulation studies demonstrate that the fault detection and isolation task achieved by using the residuals that are obtained from the dynamic ensemble scheme results in a significantly more accurate and reliable performance as illustrated through detailed quantitative confusion matrix analysis and comparative studies.

  7. Numeric Design and Performance Analysis of Solid Oxide Fuel Cell -- Gas Turbine Hybrids on Aircraft

    Science.gov (United States)

    Hovakimyan, Gevorg

    The aircraft industry benefits greatly from small improvements in aircraft component design. One possible area of improvement is in the Auxiliary Power Unit (APU). Modern aircraft APUs are gas turbines located in the tail section of the aircraft that generate additional power when needed. Unfortunately the efficiency of modern aircraft APUs is low. Solid Oxide Fuel Cell/Gas Turbine (SOFC/GT) hybrids are one possible alternative for replacing modern gas turbine APUs. This thesis investigates the feasibility of replacing conventional gas turbine APUs with SOFC/GT APUs on aircraft. An SOFC/GT design algorithm was created in order to determine the specifications of an SOFC/GT APU. The design algorithm is comprised of several integrated modules which together model the characteristics of each component of the SOFC/GT system. Given certain overall inputs, through numerical analysis, the algorithm produces an SOFC/GT APU, optimized for specific power and efficiency, capable of performing to the required specifications. The SOFC/GT design is then input into a previously developed quasi-dynamic SOFC/GT model to determine its load following capabilities over an aircraft flight cycle. Finally an aircraft range study is conducted to determine the feasibility of the SOFC/GT APU as a replacement for the conventional gas turbine APU. The design results show that SOFC/GT APUs have lower specific power than GT systems, but have much higher efficiencies. Moreover, the dynamic simulation results show that SOFC/GT APUs are capable of following modern flight loads. Finally, the range study determined that SOFC/GT APUs are more attractive over conventional APUs for longer range aircraft.

  8. Design and development of gas cooled reactors with closed cycle gas turbines. Proceedings of a technical committee meeting

    International Nuclear Information System (INIS)

    Technological advances over the past fifteen years in the design of turbomachinery, recuperators and magnetic bearings provide the potential for a quantum improvement in nuclear power generation economics through the use of the HTGR with a closed cycle gas turbine. Enhanced international co-operation among national gas cooled reactor programmes in these common technology areas could facilitate the development of this nuclear power concept thereby achieving safety, environmental and economic benefits with overall reduced development costs. This TCM and Workshop was convened to provide the opportunity to review and examine the status of design activities and technology development in national HTGR programmes with specific emphasis on the closed cycle gas turbine, and to identify pathways which take advantage of the opportunity for international co-operation in the development of this concept. Refs, figs, tabs

  9. The start-up of a gas turbine engine using compressed air tangentially fed onto the blades of the basic turbine

    Science.gov (United States)

    Slobodyanyuk, L. K.; Dayneko, V. I.

    1983-01-01

    The use of compressed air was suggested to increase the reliability and motor lifetime of a gas turbine engine. Experiments were carried out and the results are shown in the form of the variation in circumferential force as a function of the entry angle of the working jet onto the turbine blade. The described start-up method is recommended for use with massive rotors.

  10. Electricity cogeneration evaluation from cane bagasse in gasifier systems/gas turbine; Avaliacao da cogeracao de eletricidade a partir de bagaco de cana em sistemas de gaseificador/turbina a gas

    Energy Technology Data Exchange (ETDEWEB)

    Coelho, Suani Teixeira

    1992-07-01

    Before the beginning of PROALCOOL in 1975, the first effective program in the world using biomass in large scale as an automotive fuel, sugar/alcohol industries already used sugar cane bagasse - a by-product of sugar/alcohol production - to generate energy for sugar production. Currently, besides the fact that they are self-sufficient in thermal/electrical energy, sugar/alcohol industries produce small electricity excess which is exported to local utilities. Gasifier/gas turbine systems are more advanced technologies which are being developed and shall be commercialized in eight to ten years approximately, presenting much higher efficiency, at low cost and inducing more exportable electricity. In this study, possibilities of gasifier/gas turbine systems are evaluated and projections of bagasse based electricity production are presented, until year 2010, for Sao Paulo state and Brazil. Generation costs of gasified bagasse based electricity are calculated: they shall be lower than electricity cost from fossil origin. Influence of electricity sale on the reduction of alcohol production cost are also evaluated for several opportunity costs of bagasse. Environmental and social impacts are analyzed, including evaluation of the cost of avoided carbon, related to the substitution of fossil fuel by sugar cane bagasse in thermoelectric power plants. (author)

  11. Cooling system having reduced mass pin fins for components in a gas turbine engine

    Science.gov (United States)

    Lee, Ching-Pang; Jiang, Nan; Marra, John J

    2014-03-11

    A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.

  12. Improvement Results of TK-32 Turbocompressor Turbine with Gas- Dynamics And Strength CAE-Systems

    OpenAIRE

    Grigorii M. Popov; Oleg V. Baturin; Daria A. Kolmakova; Alexander V. Krivcov

    2014-01-01

    The results of strength and gas dynamic improvement of turbocharger TK-32 axial turbine are presented. Turbocharger was manufactured by LLC “Penzadieselmash” (Penza, Russian) and is used as unit boost for diesel locomotive. The goal of this work was to ensure turbine work capacity when rotor speed is increased by 10% without efficiency reduction. The strain-stress state analysis indicated the region of high stresses on rotor blade body at the level of 2/3 of root. These stresses exceed allowa...

  13. Blade loss transient dynamics analysis, volume 1. Task 1: Survey and perspective. [aircraft gas turbine engines

    Science.gov (United States)

    Gallardo, V. C.; Gaffney, E. F.; Bach, L. J.; Stallone, M. J.

    1981-01-01

    An analytical technique was developed to predict the behavior of a rotor system subjected to sudden unbalance. The technique is implemented in the Turbine Engine Transient Rotor Analysis (TETRA) computer program using the component element method. The analysis was particularly aimed toward blade-loss phenomena in gas turbine engines. A dual-rotor, casing, and pylon structure can be modeled by the computer program. Blade tip rubs, Coriolis forces, and mechanical clearances are included. The analytical system was verified by modeling and simulating actual test conditions for a rig test as well as a full-engine, blade-release demonstration.

  14. History of Thermal Barrier Coatings for Gas Turbine Engines: Emphasizing NASA's Role from 1942 to 1990

    Science.gov (United States)

    Miller, Robert A.

    2009-01-01

    NASA has played a central role in the development of thermal barrier coatings (TBCs) for gas turbine applications. This report discusses the history of TBCs emphasizing the role NASA has played beginning with (1) frit coatings in the 1940s and 1950s; (2) thermally sprayed coatings for rocket application in the 1960s and early 1970s; (3) the beginnings of the modern era of turbine section coatings in the mid 1970s; and (4) failure mechanism and life prediction studies in the 1980s and 1990s. More recent efforts are also briefly discussed.

  15. System study of an MHD/gas turbine combined-cycle baseload power plant. HTGL report No. 134

    Energy Technology Data Exchange (ETDEWEB)

    Annen, K.D.

    1981-08-01

    The MHD/gas turbine combined-cycle system has been designed specifically for applications where the availability of cooling water is very limited. The base case systems which were studied consisted of an MHD plant with a gas turbine bottoming plant, and required no cooling water. The gas turbine plant uses only air as its working fluid and receives its energy input from the MHD exhaust gases by means of metal tube heat exchangers. In addition to the base case systems, vapor cycle variation systems were considered which included the addition of a vapor cycle bottoming plant to improve the thermal efficiency. These systems required a small amount of cooling water. The MHD/gas turbine systems were modeled with sufficient detail, using realistic component specifications and costs, so that the thermal and economic performance of the system could be accurately determined. Three cases of MHD/gas turbine systems were studied, with Case I being similar to an MHD/steam system so that a direct comparison of the performances could be made, with Case II being representative of a second generation MHD system, and with Case III considering oxygen enrichment for early commercial applications. The systems are nominally 800 MW/sub e/ to 1000 MW/sub e/ in size. The results show that the MHD/gas turbine system has very good thermal and economic performances while requiring either little or no cooling water. Compared to the MHD/steam system which has a cooling tower heat load of 720 MW, the Base Case I MHD/gas turbine system has a heat rate which is 13% higher and a cost of electricity which is only 7% higher while requiring no cooling water. Case II results show that an improved performance can be expected from second generation MHD/gas turbine systems. Case III results show that an oxygen enriched MHD/gas turbine system may be attractive for early commercial applications in dry regions of the country.

  16. Performance Evaluation of Hybrid Gas Turbine Engine Embedded with Pulse Detonation Combustor

    Science.gov (United States)

    Deng, Jun-Xiang; Yan, Chuan-Jun; Zheng, Long-Xi; Huang, Xi-Qiao

    2011-09-01

    The numerical investigations of performance evaluation of a hybrid gas turbine engine embedded with a pulse detonation combustor (PDC) were performed to examine the improvement of the performance of the hybrid propulsion system. The calculation model and method were described. The architecture, configuration and size of detonation tubes were investigated in the calculation. Two models of detonation tube exit temperature were utilized. Eight configuration choices for the PDC based on the calculation model were designed. Specific fuel consumption of a hybrid gas turbine engine was compared with that of the baseline engine at the condition of the same engine net thrust. The experimental research of a PDC interacted with a radial flow turbine of a turbocharger was conducted. The numerical results show that if the net thrust of hybrid PDC engine is matched to that of baseline engine, specific fuel consumption of hybrid PDC engine is 20-25% less than that of baseline engine. The total volume of the hybrid engine combustor is reduced. The incorporation of PDC into gas turbine engine can improve the performance of hybrid PDC engine, decrease the combustor weight, and increase the thrust-weight ratio. The experimental results show that the fully developed detonation waves are achieved in the experimental apparatus.

  17. Melt Infiltrated Ceramic Matrix Composites for Shrouds and Combustor Liners of Advanced Industrial Gas Turbines

    Energy Technology Data Exchange (ETDEWEB)

    Gregory Corman; Krishan Luthra; Jill Jonkowski; Joseph Mavec; Paul Bakke; Debbie Haught; Merrill Smith

    2011-01-07

    This report covers work performed under the Advanced Materials for Advanced Industrial Gas Turbines (AMAIGT) program by GE Global Research and its collaborators from 2000 through 2010. A first stage shroud for a 7FA-class gas turbine engine utilizing HiPerComp{reg_sign}* ceramic matrix composite (CMC) material was developed. The design, fabrication, rig testing and engine testing of this shroud system are described. Through two field engine tests, the latter of which is still in progress at a Jacksonville Electric Authority generating station, the robustness of the CMC material and the shroud system in general were demonstrated, with shrouds having accumulated nearly 7,000 hours of field engine testing at the conclusion of the program. During the latter test the engine performance benefits from utilizing CMC shrouds were verified. Similar development of a CMC combustor liner design for a 7FA-class engine is also described. The feasibility of using the HiPerComp{reg_sign} CMC material for combustor liner applications was demonstrated in a Solar Turbines Ceramic Stationary Gas Turbine (CSGT) engine test where the liner performed without incident for 12,822 hours. The deposition processes for applying environmental barrier coatings to the CMC components were also developed, and the performance of the coatings in the rig and engine tests is described.

  18. A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing

    Science.gov (United States)

    Grady, Joseph E.; Halbig, Michael C.; Singh, Mrityunjay

    2015-01-01

    In a NASA Aeronautics Research Institute (NARI) sponsored program entitled "A Fully Non-Metallic Gas Turbine Engine Enabled by Additive Manufacturing", evaluation of emerging materials and additive manufacturing technologies was carried out. These technologies may enable fully non-metallic gas turbine engines in the future. This paper highlights the results of engine system trade studies which were carried out to estimate reduction in engine emissions and fuel burn enabled due to advanced materials and manufacturing processes. A number of key engine components were identified in which advanced materials and additive manufacturing processes would provide the most significant benefits to engine operation. In addition, feasibility of using additive manufacturing technologies to fabricate gas turbine engine components from polymer and ceramic matrix composite were demonstrated. A wide variety of prototype components (inlet guide vanes (IGV), acoustic liners, engine access door) were additively manufactured using high temperature polymer materials. Ceramic matrix composite components included first stage nozzle segments and high pressure turbine nozzle segments for a cooled doublet vane. In addition, IGVs and acoustic liners were tested in simulated engine conditions in test rigs. The test results are reported and discussed in detail.

  19. Advanced Turbine Technology Applications Project (ATTAP). Annual report 1992

    Energy Technology Data Exchange (ETDEWEB)

    1993-03-01

    This report summarizes work performed by Garrett Auxiliary Power Division (GAPD), a unit of Allied-Signal Aerospace Company, during calendar year 1992, toward development and demonstration of structural ceramic technology for automotive gas turbine engines. This work was performed for the US Department of Energy (DOE) under National Aeronautics and Space Administration (NASA) Contract DEN3-335, Advanced Turbine Technology Applications Project (ATTAP). GAPD utilized the AGT101 regenerated gas turbine engine developed under the previous DOE/NASA Advanced Gas Turbine (AGT) program as the ATTAP test bed for ceramic engine technology demonstration. ATTAP focussed on improving AGT101 test bed reliability, development of ceramic design methodologies, and improvement of fabrication and materials processing technology by domestic US ceramics fabricators. A series of durability tests was conducted to verify technology advancements. This is the fifth in a series of technical summary reports published annually over the course of the five-year contract.

  20. Gas turbine HTGR plant: economical dry cooling or a wet-cooled high-efficiency binary configuration

    International Nuclear Information System (INIS)

    The dry-cooled gas turbine HTGR plant offers the means whereby power plant siting flexibility can be substantially increased without efficiency penalty or cost disadvantage. With other advantages of the basic HTGR, the result is a nearly environmentally neutral plant. Optionally, the binary-cycle gas turbine HTGR maximizes electrical output from available cooling water and nuclear fuel resources because of the very high efficiency achievable by combining the closed-cycle gas turbine with a vapor secondary-power cycle. For either option, the resulting power plant offers the highest available nuclear efficiencies with lower generating costs and with minimum environmental impact