WorldWideScience

Sample records for afterburners

  1. Flow Field Calculations for Afterburner

    Institute of Scientific and Technical Information of China (English)

    ZhaoJianxing; LiuQuanzhong; 等

    1995-01-01

    In this paper a calculation procedure for simulating the coimbustion flow in the afterburner with the heat shield,flame stabilizer and the contracting nozzle is described and evaluated by comparison with experimental data.The modified two-equation κ-ε model is employed to consider the turbulence effects,and the κ-ε-g turbulent combustion model is used to determine the reaction rate.To take into accunt the influence of heat radiation on gas temperature distribution,heat flux model is applied to predictions of heat flux distributions,The solution domain spanned the entire region between centerline and afterburner wall ,with the heat shield represented as a blockage to the mesh.The enthalpy equation and wall boundary of the heat shield require special handling for two passages in the afterburner,In order to make the computer program suitable to engineering applications,a subregional scheme is developed for calculating flow fields of complex geometries.The computational grids employed are 100×100 and 333×100(non-uniformly distributed).The numerical results are compared with experimental data,Agreement between predictions and measurements shows that the numerical method and the computational program used in the study are fairly reasonable and appopriate for primary design of the afterburner.

  2. Simulating Afterburn with LLNL Hydrocodes

    Energy Technology Data Exchange (ETDEWEB)

    Daily, L D

    2004-06-11

    Presented here is a working methodology for adapting a Lawrence Livermore National Laboratory (LLNL) developed hydrocode, ALE3D, to simulate weapon damage effects when afterburn is a consideration in the blast propagation. Experiments have shown that afterburn is of great consequence in enclosed environments (i.e. bomb in tunnel scenario, penetrating conventional munition in a bunker, or satchel charge placed in a deep underground facility). This empirical energy deposition methodology simulates the anticipated addition of kinetic energy that has been demonstrated by experiment (Kuhl, et. al. 1998), without explicitly solving the chemistry, or resolving the mesh to capture small-scale vorticity. This effort is intended to complement the existing capability of either coupling ALE3D blast simulations with DYNA3D or performing fully coupled ALE3D simulations to predict building or component failure, for applications in National Security offensive strike planning as well as Homeland Defense infrastructure protection.

  3. Thermodynamic Model of Afterburning in Explosions

    Energy Technology Data Exchange (ETDEWEB)

    Kuhl, A L; Howard, M; Fried, L

    2003-04-23

    Thermodynamic states encountered during afterburning of explosion products gases in air were analyzed with the Cheetah code. Results are displayed in the form of Le Chatelier diagrams: the locus of states of specific internal energy versus temperature, for six different condensed explosives charges. Accuracy of the results was confirmed by comparing the fuel and products curves with the heats of detonation and combustion, and species composition as measured in bomb calorimeter experiments. Results were fit with analytic functions u = f ( T ) suitable for specifying the thermodynamic properties required for gas-dynamic models of afterburning in explosions.

  4. Modeling TeV Class Plasma Afterburners

    CERN Document Server

    Huang Cheng Kun; Clayton, Chris; Decker, Franz Josef; Deng, Suzhi; Hogan, Mark; Iverson, Richard; Johnson, Devon K; Joshi, Chandrashekhar; Katsouleas, Thomas C; Lu, Wei; Mori, Warren; Muggli, Patric; Oz, Erdem; Zhou, Miaomiao

    2005-01-01

    Plasma wakefield acceleration can sustain acceleration gradients three orders of magnitude larger than conventional RF accelerator. In the recent E164X experiment, substantial energy gain of about 3Gev has been observed. Thus, a plasma afterburner, which has been proposed to double the incoming beam energy for a future linear collider, is now of great interest. In an afterburner, a particle beam drives a plasma wave and generates a strong wakefield which has a phase velocity equal to the velocity of the beam. This wakefield can then be used to accelerate part of the drive beam or a trailing beam. Several issues such as the efficient transfer of energy and the stable propagation of both the drive and trailing beams in the plasma are critical to the afterburner concept. We investigate the nonlinear beam-plasma interaction in such scenario using the 3D computer modeling code QuickPIC. We will report the latest simulation results of both 50 GeV and 1 TeV plasma afterburner stages for electrons including the beam-...

  5. Building an Efficient Model for Afterburn Energy Release

    Energy Technology Data Exchange (ETDEWEB)

    Alves, S; Kuhl, A; Najjar, F; Tringe, J; McMichael, L; Glascoe, L

    2012-02-03

    Many explosives will release additional energy after detonation as the detonation products mix with the ambient environment. This additional energy release, referred to as afterburn, is due to combustion of undetonated fuel with ambient oxygen. While the detonation energy release occurs on a time scale of microseconds, the afterburn energy release occurs on a time scale of milliseconds with a potentially varying energy release rate depending upon the local temperature and pressure. This afterburn energy release is not accounted for in typical equations of state, such as the Jones-Wilkins-Lee (JWL) model, used for modeling the detonation of explosives. Here we construct a straightforward and efficient approach, based on experiments and theory, to account for this additional energy release in a way that is tractable for large finite element fluid-structure problems. Barometric calorimeter experiments have been executed in both nitrogen and air environments to investigate the characteristics of afterburn for C-4 and other materials. These tests, which provide pressure time histories, along with theoretical and analytical solutions provide an engineering basis for modeling afterburn with numerical hydrocodes. It is toward this end that we have constructed a modified JWL equation of state to account for afterburn effects on the response of structures to blast. The modified equation of state includes a two phase afterburn energy release to represent variations in the energy release rate and an afterburn energy cutoff to account for partial reaction of the undetonated fuel.

  6. MUSIC with the UrQMD Afterburner

    Energy Technology Data Exchange (ETDEWEB)

    Ryu, Sangwook; Jeon, Sangyong; Gale, Charles [McGill University, Montreal, QC (Canada); Schenke, Björn [Brookhaven National Laboratory, Upton, NY (United States); Young, Clint [McGill University, Montreal, QC (Canada); University of Minnesota, Minneaplis, MN (United States)

    2013-05-02

    As RHIC is entering the precision measurement era and the LHC is producing a copious amount of new data, the role of 3+1D event-by-event viscous hydrodynamics is more important than ever to understand the bulk data as well as providing the background for hard probes. For more meaningful comparison with the experimental data, it is also important that hydrodynamics be coupled to the hadronic afterburner. In this proceeding we report on preliminary results of coupling MUSIC with UrQMD.

  7. Altitude Performance of Modified J71 Afterburner with Revised Engine Operating Conditions

    Science.gov (United States)

    Useller, James W.; Russey, Robert E.

    1955-01-01

    An investigation was conducted in an altitude test chamber at the NACA Lewis laboratory to determine the effect of a revision of the rated engine operating conditions and modifications to the afterburner fue1 system, flameholder, and shell cooling on the augmented performance of the J71-A-2 (x-29) turbo jet engine operating at altitude . The afterburner modifications were made by the manufacturer to improve the endurance at sea-level, high-pressure conditions and to reduce the afterburner shell temperatures. The engine operating conditions of rated rotational speed and turbine-outlet gas temperature were increased. Data were obtained at conditions simulating flight at a Mach number of 0.9 and at altitudes from 40,000 to 60,000 feet. The afterburner modifications caused a reduction in afterburner combustion efficiency. The increase in rated engine speed and turbine-outlet temperature coupled with the afterburner modifications resulted in the over-all thrust of the engine and afterburner being unchanged at a given afterburner equivalence ratio, while the specific fuel consumption was increased slightly. A moderate shift in the range of equivalence ratios over which the afterburner would operate was encountered, but the maximum operable altitude remained unaltered. The afterburner-shell temperatures were also slightly reduced because of the modifications to the afterburner.

  8. Exergetic analysis of an aircraft turbojet engine with an afterburner

    Directory of Open Access Journals (Sweden)

    Ehyaei M.A.

    2013-01-01

    Full Text Available An exergy analysis is reported of a J85-GE-21 turbojet engine and its components for two altitudes: sea level and 11,000 meters. The turbojet engine with afterburning operates on the Brayton cycle and includes six main parts: diffuser, compressor, combustion chamber, turbine, afterburner and nozzle. Aircraft data are utilized in the analysis with simulation data. The highest component exergy efficiency at sea level is observed to be for the compressor, at 96.7%, followed by the nozzle and turbine with exergy efficiencies of 93.7 and 92.3%, respectively. At both considered heights, reducing of engine intake air speed leads to a reduction in the exergy efficiencies of all engine components and overall engine. The exergy efficiency of the turbojet engine is found to decrease by 0.45% for every 1°C increase in inlet air temperature.

  9. An Efficient Microwave Power Source: Free-electron Laser Afterburner

    Energy Technology Data Exchange (ETDEWEB)

    Wang, C.; Sessler, Andrew M.

    1993-03-04

    A kind of microwave power source, called a free-electron laser afterburner (FEL afterburner) which consists of a free-electron laser buncher and a slow-wave output structure sharing a magnetic wiggler field with the buncher, is proposed. The buncher and the slow-wave structure can operate in either a travelling-wave state or a standing-wave state. In the buncher, the wiggler field together with the radiation field makes an electron beam bunched, and in the slow-wave structure the wiggler field keeps the beam bunched while the bunched beam interacts strongly with the slow-wave structure and so produces rf power. The bunching process comes from the free-electron laser mechanism and the generating process of rf power is in a slow-wave structure. A three-dimensional, time-dependent code is used to simulate a particular standing-wave FEL afterburner and it is shown that rf power of up to 1.57 GW can be obtained, at 17.12 GHz, from a l-kA, 5-MeV electron beam.

  10. After-burning of nitropenta products in a calorimeter

    Energy Technology Data Exchange (ETDEWEB)

    Kuhl, A L; Neuwald, P; Reichenbach, H

    1999-06-18

    Explored here are the ''after-burning'' effects for explosions of Nitropenta (NP) charges in air. Detonation of the charge transforms the solid explosive ( C HNO 5 8412 , also known as PETN) into gaseous products that are rich in carbon and CO, which subsequently act as a fuel. When these hot ({approximately}3500 K) gases mix with air, rapid combustion (after-burning) takes place. The dynamics of this exothermic process was studied in ''pressure calorimeter'' experiments performed at EMI.

  11. Control of an afterburner in a diesel fuel cell power unit under variable load

    Science.gov (United States)

    Dolanc, Gregor; Pregelj, Boštjan; Petrovčič, Janko; Samsun, Remzi Can

    2017-01-01

    In this paper, the control system for a catalytic afterburner in a diesel fuel cell auxiliary power unit is presented. The catalytic afterburner is used to burn the non-utilised hydrogen and other possible combustible components of the fuel cell anode off-gas. To increase the energy efficiency of the auxiliary power unit, the thermal energy released in the catalytic afterburner is utilised to generate the steam for the fuel processor. For optimal operation of the power unit in all modes of operation including load change, stable steam generation is required and overall energy balance must be kept within design range. To achieve this, the reaction temperature of the catalytic afterburner must be stable in all modes of operation. Therefore, we propose the afterburner temperature control based on mass and thermal balances. Finally, we demonstrate the control system using the existing prototype of the diesel fuel cell auxiliary power unit.

  12. Heavy ion acceleration in the Breakout Afterburner regime

    CERN Document Server

    Petrov, G M; Thomas, A G R; Krushelnick, K; Beg, F N

    2015-01-01

    Theoretical study of heavy ion acceleration from an ultrathin (20 nm) gold foil irradiated by sub-picosecond lasers is presented. Using two dimensional particle-in-cell simulations we identified two highly efficient ion acceleration schemes. By varying the laser pulse duration we observed a transition from Radiation Pressure Acceleration to the Breakout Afterburner regime akin to light ions. The underlying physics and ion acceleration regimes are similar to that of light ions, however, nuances of the acceleration process make the acceleration of heavy ions more challenging. Two laser systems are studied in detail: the Texas Petawatt Laser and the Trident laser, the former having pulse duration 180 fs, intermediate between very short femtosecond pulses and picosecond pulses. Both laser systems generated directional gold ions beams (~10 degrees half-angle) with fluxes in excess of 1011 ion/sr and normalized energy >10 MeV/nucleon.

  13. Steam thermolysis of tire shreds: modernization in afterburning of accompanying gas with waste steam

    Science.gov (United States)

    Kalitko, V. A.

    2010-03-01

    On the basis of experience in the commercial operation of tire-shred steam thermolysis in EnresTec Inc. (Taiwan) producing high-grade commercial carbon, liquid pyrolysis fuel, and accompanying fuel gas by this method, we have proposed a number of engineering solutions and calculated-analytical substantiations for modernization and intensification of the process by afterburning the accompanying gas with waste steam condensable in the scrubber of water gas cleaning of afterburning products. The condensate is completely freed of the organic pyrolysis impurities and the necessity of separating it from the liquid fuel, as is the case with the active process, is excluded.

  14. Improving the Efficiency of an Ideal Heat Engine: The Quantum Afterburner

    OpenAIRE

    Scully, Marlan O.

    2001-01-01

    By using a laser and maser in tandem, it is possible to obtain laser action in the hot exhaust gases involved in heat engine operation. Such a "quantum afterburner" involves the internal quantum states of working gas atoms or molecules as well as the techniques of cavity quantum electrodynamics and is therefore in the domain of quantum thermodynamics. As an example, it is shown that Otto cycle engine performance can be improved beyond that of the "ideal" Otto heat engine.

  15. Effects of Nozzle Scale, Total Temperature and an Afterburner on Jet Noise from a Pre-Cooled Turbojet Engine

    Science.gov (United States)

    Araki, Mikiya; Sano, Takayuki; Fukuda, Masayuki; Kojima, Takayuki; Taguchi, Hideyuki; Nishida, Shunsuke; Imamura, Osamu; Shiga, Seiichi; Tsue, Mitsuhiro

    Effects of nozzle scale, total temperature, and an afterburner on jet noise characteristics from a pre-cooled turbojet engine are investigated experimentally. In JAXA (Japan Aerospace Exploration Agency), a pre-cooled turbojet engine for an HST (Hypersonic transport) is under development. In the present study, 1.0%- and 2.4%-scaled models of the rectangular plug nozzle (Nozzles I and II) are manufactured, and the jet noise characteristics are investigated under a wide range of total temperatures. For Nozzle I, no air-heater is utilized and the total temperature is 290K. For Nozzle II, a pebble heater and an afterburner (AB) are utilized upstream of the nozzle model, and the total temperature is varied from 520K (pebble heater) to 1540K (pebble heater + AB). The total pressure is set at 0.27 and 0.30MPa(a) for both nozzle models. Jet noise is measured using a high-frequency microphone set at 135 deg from the engine inlet, and normalized jet noise spectra are obtained based on AUjn law and Helmholtz number. For cases without afterburner, the normalized spectra agrees well regardless of the nozzle scale and total temperature where the velocity index lies from n = 7.7 to 9.2, and the correlation factor between the two facilities is shown to be about 1dB. For the case with afterburner, the normalized spectrum does not agree with other conditions where the velocity index n seems to be about 4.

  16. Turbulent mixing and afterburn in post-detonation flow with dense particle clouds

    Science.gov (United States)

    Gottiparthi, Kalyana C.; Menon, Suresh

    2017-01-01

    Augmentation of the impact of an explosive is routinely achieved by packing metal particles in the explosive charge. When detonated, the particles in the charge are ejected and dispersed. The ejecta influences the post-detonation combustion processes that bolster the blast wave and determines the total impact of the explosive. While the classical Eulerian-Lagrangian (EL) methods can accurately handle the post-detonation mixing zone in the dilute regime, the Eulerian-Eulerian (EE) method is preferred for the initial dense clustering. Here, we summarize the results obtained using both EL and EE methods as well as demonstrate a new hybrid EE-EL approach. The EL method, which is also developed to handle both dense and dilute flows using the discrete equation method, is used initially to study the dispersion of a relatively dense particle shell by blast waves. The results show distinct clustering of particles that later leads to the formation of jet-like structures as seen in experiments. Then, the hybrid EE-EL method is used to study the dispersion of dense clouds from explosives packed with aluminum (reactive) or steel (inert) particles. A transitioning criterion is used to smoothly transfer the initially dense Eulerian mass to Lagrangian particles when dilute. Results are presented to demonstrate that the approach is computationally efficient and accurate for certain ranges of particle sizes and loading. It is shown that mixing between the ambient and post-detonation products can be enhanced when particles are present in the flow. Furthermore, the afterburn of aluminum particles increases in the average gas-phase temperature by 100 K - 200 K when compared to a case with non-reacting particles. More studies are still needed to establish a robust strategy for wider applications.

  17. Helium-3 production from Pb+Pb collisions at SPS energies with the UrQMD model and the traditional coalescence afterburner

    CERN Document Server

    Li, Qingfeng; Wang, Xiaobao; Shen, Caiwan

    2016-01-01

    A potential version of the UrQMD (UrQMD/M) transport model and a traditional coalescence model are combined to calculate the production of $^3$He fragments in central Pb+Pb collisions at SPS energies 20-80 GeV/nucleon. It is found that the Lorentz transformation in the afterburner influences visibly the $^3$He yield and should be considered in calculations. The rapidity distribution of $^3$He multiplicities (including the concave shape) can be described well with UrQMD/M when it stops during t$_{\\rm cut}$=100$\\pm$25 fm$/c$ and the coalescence afterburner with one parameter set of ($R_0$,$P_0$)=(3.8 fm, 0.3 GeV$/$c) is taken into use afterwards.

  18. Surface temperature measurements from a stator vane doublet in a turbine afterburner flame using a YAG:Tm thermographic phosphor

    Science.gov (United States)

    Eldridge, Jeffrey I.; Allison, Stephen W.; Jenkins, Thomas P.; Gollub, Sarah L.; Hall, Carl A.; Walker, D. Greg

    2016-12-01

    Phosphor thermometry measurements in turbine engine environments can be difficult because of high background radiation levels. To address this challenge, luminescence lifetime-based phosphor thermometry measurements were obtained using thulium-doped Y3Al5O12 (YAG:Tm) to take advantage of the emission wavelengths at 365 nm (1D2  →  3H6 transition) and at 456 nm (1D2  →  3F4 transition). At these wavelengths, turbine engine radiation background is reduced compared with emission from longer wavelength phosphors. Temperature measurements of YAG:Tm coatings were demonstrated using decay of both the 365 and 456 nm emission bands in a furnace environment up to 1400 °C. To demonstrate that reliable surface temperatures based on short-wavelength YAG:Tm emission could be obtained from the surface of an actual engine component in a high gas velocity, highly radiative environment, measurements were obtained from a YAG:Tm-coated Honeywell stator vane doublet placed in the afterburner flame exhaust stream of the augmenter-equipped General Electric J85 turbojet test engine at the University of Tennessee Space Institute (UTSI). Using a probe designed for engine insertion, spot temperature measurements were obtained by measuring luminescence decay times over a range of steady state throttle settings as well as during an engine throttle acceleration. YAG:Tm phosphor thermometry measurements of the stator vane surface in the afterburner exhaust stream using the decay of the 456 nm emission band were successfully obtained at temperatures up to almost 1300 °C. Phosphor thermometry measurements acquired with the engine probe using the decay of the 365 nm emission band were not successful at usefully high temperatures because the probe design allowed transmission of intense unfiltered silica Raman scattering that produced photomultiplier tube saturation with extended recovery times. Recommendations are made for probe modifications that will enable

  19. Rapidity distribution of protons from the potential version of UrQMD model and the traditional coalescence afterburner

    CERN Document Server

    Li, Qingfeng; Wang, Xiaobao; Shen, Caiwan

    2016-01-01

    Rapidity distributions of both E895 proton data at AGS energies and NA49 net proton data at SPS energies can be described reasonably well with a potential version of the UrQMD in which mean-field potentials for both pre-formed hadrons and confined baryons are considered, with the help of a traditional coalescence afterburner in which one parameter set for both relative distance $R_0$ and relative momentum $P_0$, (3.8 fm, 0.3 GeV$/$c), is used. Because of the large cancellation between the expansion in $R_0$ and the shrinkage in $P_0$ through the Lorentz transformation, the relativistic effect in clusters has little effect on the rapidity distribution of free (net) protons. Using a Woods-Saxon-like function instead of a pure logarithmic function as seen by FOPI collaboration at SIS energies, one can fit well both the data at SIS energies and the UrQMD calculation results at AGS and SPS energies. Further, it is found that for central Au+Au or Pb+Pb collisions at top SIS, SPS and RHIC energies, the proton fracti...

  20. Experimental analysis on NOx generation and emission distribution off aviation afterburners%加力燃烧室NOx排放生成规律试验分析

    Institute of Scientific and Technical Information of China (English)

    王琦; 胡筱敏

    2012-01-01

    An afterburners was designed to get aviation engine extra thrust, but higher inlet temperature will generate higher NO. emission. One V style structure test facilities was adopted as an afterburners flow fields stabilizer, the section concentration of different NO. and 02 emission from the afterburners were analyzed in condition of inlet T 600 ℃ to outlet T 600 - 1 200 ℃ , the test was fulfilled at 4 experimental conditions of same flux and flow fields. The results show that the chamber combustion is of "higher temperature, rich oxy- gen, poor fuel" characteristics, most Oxygen consumption in an afterburner chamber is contributed to generate CO2 and in the emission temperature scope of 800 - 1 200 ℃, the NO thermal generation is restrained and af- fected by incomplete combustion product CO evidently.%实现航空发动机大推力通常采用加力燃烧室设计,燃烧室进气温度升高会同步导致排放尾气中NOx浓度提高.采用典型加力燃烧室主稳定器的V型结构试验件,测试加力燃烧前后(进口600℃,出口600~1200℃)燃烧室排放断面的NOx浓度分布,通过相同流场4种试验工况的NOx生成浓度组分和氧含量变化分析,验证了加力燃烧室NOx生成以热力型NO为主的"高温、富氧、贫油"燃烧特性.结果表明加力燃烧室燃烧过程中消耗的氧含量大多贡献于CO2增量,在800~1000℃燃气排放温度范围内,不完全燃烧产物CO对NO的热力生成有明显抑制作用.

  1. Development of integrated, zero-G pneumatic transporter/rotating paddle incinerator/catalytic afterburner subsystem for processing human wastes on board spacecraft

    Science.gov (United States)

    Fields, S. F.; Labak, L. J.; Honegger, R. J.

    1974-01-01

    A four component system was developed which consists of a particle size reduction mechanism, a pneumatic waste transport system, a rotating-paddle incinerator, and a catalytic afterburner to be integrated into a six-man, zero-g subsystem for processing human wastes on board spacecraft. The study included the development of different concepts or functions, the establishment of operational specifications, and a critical evaluation for each of the four components. A series of laboratory tests was run, and a baseline subsystem design was established. An operational specification was also written in preparation for detailed design and testing of this baseline subsystem.

  2. 近距离微型广角加力燃烧室点火过程观测系统%Micro and Wide-Angle Observation System Close to Aeroengine Afterburner for Ignition Process

    Institute of Scientific and Technical Information of China (English)

    胡智涌; 段发阶

    2016-01-01

    由于加力燃烧室尾喷口环境恶劣,难以近距离对其进行观测,传统方法采用远距离观测,成像效果不佳.本文提出一种用于可见光波段的微型广角观测系统方案,使用微型相机,与水冷保护管相结合,可直接在尾喷口后1~2 m位置对加力燃烧室点火过程进行观测.相机直径7 mm,水冷管直径可达20~30 mm,视场角最大可达50°.在模拟实验中,对靶标成像清晰,细节明显.通过视觉成像技术对航空发动机加力燃烧室内部区域工作过程进行观测,得到的观测结果可用于对点火、火焰稳定性和燃烧均匀性的定性评价.%Due to the severe environment near to the jet of the afterburner, it is hard to observe.Tradi-tional observation method is remote from the afterburner and the photos are not clear enough.In order to solve this problem, a micro and wide-angle observation system was proposed in this paper.Based on a micro camera and combined with a water-cooling tube, the system is useful for visible spectrum and can be set close to the jet with a distance of 1—2 m.The camera diameter is 7 mm and the water-cooling tube diameter reach to 20—30 mm, and the largest field angle is about 50°.Experimental results show that the images of the system for the target are clear and detailed.The result of vision observation to aero-engine afterburner inner aera is available for the evaluation of ignition and combustion stability and homo-geneity.

  3. Effects of Special Fuel-gas Jet on Mixing and Combustion in Afterburning Chamber%特型燃气喷口对补燃室掺混燃烧的影响∗

    Institute of Scientific and Technical Information of China (English)

    王同辉; 白涛涛; 莫展; 单睿子; 曹军伟

    2015-01-01

    Based on the N-S equation, k-ε turbulence models and no-premixed combustion simplified PDF models, numerical studies on the mixing and combustion of fuel-gas and air in the afterburning chamber of solid rocket ramjet were carried out fewer than three special fu-el-gas jets structures. The effects of the three special fuel-gas jets were analyzed and compared with simulation results of standard fuel-gas jets. The results show that, the mixing efficiency, full combustion extent and characteristic velocity in the afterburning chamber of solid rocket ramjet promoted when using special fuel-gas jets;mixing and combustion effects of 2# and 3# special fuel-gas jets better than that of 1# special fuel-gas jet, but they would bring more total pressure loss.%采用N-S方程、k-ε双方程和非预混燃烧简化PDF模型,对3种特型燃气喷口结构的固冲发动机补燃室掺混燃烧流场进行了数值研究。分析3种特型燃气喷口对补燃室中掺混燃烧的影响,并与常规型燃气喷口的仿真结果进行了对比分析。结果表明:特型燃气喷口可以有效增强补燃室中燃气与空气的掺混效果,提高燃气的完全燃烧程度,提升固冲发动机补燃室的特征速度;2#和3#特型喷口的补燃室掺混燃烧效果要比1#特型喷口更好,但是会带来更大的总压损失。

  4. Numerical study on the combustion characteristics of afterburner with chevron mixer%采用锯齿冠状混合器的加力燃烧室燃烧特性数值研究

    Institute of Scientific and Technical Information of China (English)

    王亚盟; 张靖周; 单勇; 高家春; 徐兴平

    2011-01-01

    Based on computational fluid dynamics(CFD),the process of three-dimension and two-phase chemical reaction flow of afterburner with confluent mixer and chevron mixer was simulated with introduction of eddy dissipation(ED) model.The results reveal that the temperature of bypass flow and the oxygen content of core flow are enhanced dramatically by chevron mixer,meanwhile,the combustion efficiency increases by 14.9% compared to confluent mixer under the same fuel supply scheme. 更多还原%基于计算流体动力学(CFD)技术,采用涡耗散燃烧模型对环形混合器和锯齿冠状混合器的加力燃烧进行三维两相化学反应流的数值模拟.计算结果表明:相对于环形混合器,锯齿冠状混合器能够显著提高外涵气流的温度和内涵的含氧量,在相同的供油方案下,使得燃烧效率提高14.9%.

  5. Numerical simulation on separation control by filleting casing tongue of after-burning fuel pump%加力燃油泵隔舌倒圆抑制分离的数值模拟

    Institute of Scientific and Technical Information of China (English)

    薛梅新; 朴英

    2012-01-01

    采用动态亚格子应力模型对加力燃油泵内非定常流场进行大涡模拟,探讨了原隔舌空蚀机理,并研究了不同倒圆半径下泵隔舌附近的瞬时流动规律及流量扬程特性.计算结果表明:小流量工况原隔舌处分离产生的强剪切涡会诱发空化,涡脱落形成的分离再附位置与空蚀破坏核心区域相符;小流量工况下,隔舌倒圆在扩散管内形成转向涡,消除了隔舌壁面分离绕流及附着剪切涡,4mm倒圆半径可以避免空化;设计流量范围内隔舌倒圆提高了泵出口扬程,流量越小扬程增幅越大,小流量工况时扬程增幅达3%.%Unsteady flow field inside an after-burning fuel pump was investigated by large eddy simulation method with the dynamic subgrid-scale stress model.The cavitation erosion mechanism of the original casing tongue was discussed,and then,the characteristics of transient flow around the casing tongue and pump performance were investigated under different filleting radius conditions.The results show that the flow separation at the original tongue under small flow-rate condition brings strong shearing vortex which induces cavitation.The separation attachment location formed by the vortex shedding agrees well with the real cavitation damage core region.Under small flow-rate condition,tongue filleting results in diversion vortex in the diffuser tube,which suppresses the flow separation around the tongue face as well as the attached shearing vortex,while the 4 mm filleting radius case can avoid tongue cavitation.Within the design flow-rate,tongue filleting raises the pump head,and the smaller the flow-rate,the larger the head increase amplitude,which reaches 3% under small flow-rate condition.

  6. Noise of High Performance Aircraft at Afterburner

    Science.gov (United States)

    2016-02-10

    aircraft carrier, navy personnel work in close proximity to high performance jets at takeoffs and landings. The noise level emitted by these jets is...any major differences between the dominant noise components of these jets and those of a standard high temperature laboratory supersonic jet . It is...noise. For the F18E aircraft, we find that its noise, at high engine power settings, also includes new noise components in addition to the usual fine

  7. Noise of High Performance Aircraft at Afterburner

    Science.gov (United States)

    2016-05-04

    Mathematics Florida State University Email: tam@math.fsu.edu Grant Monitor Dr. John Spyropoulous Email: John.Spyropoulous@jsf.mil...of equations (1) and (2). Obviously, the computed spectrum is unacceptable. It is overwhelmed by spurious high frequency oscillations. Figure 2...reasoning suggests that we may, as a first approximation, insert a boxcar window function in the integral of equation (4). That is, equation (4) is

  8. Numerical simulation on internal flow characteristics in the discharge chamber of an afterburning fuel pump under off-design conditions%加力燃油泵压出室非设计工况内流特征数值模拟

    Institute of Scientific and Technical Information of China (English)

    薛梅新; 吴迪; 朴英

    2012-01-01

    The unsteady flow in an afterburning oil pump on a certain type of aero-engine was simulated for the uneommon cavitation damage problem near its casing tongue, with arbitrary sliding mesh technology. The discharge chamber internal flow characteristics at off-design conditions were investigated to find out possible conditions causing the casing tongue cavitation. The results showed that. under large flow-rate condition, there are two separated vortices of different sizes located in the cone-shaped tube passage, while the fuel flowed past the casing wall without obvious separation in the annular chamber, which hardly trigger cavitation under small flow-rate condition, the two separated vortices extend to take up most part of the cone-shaped passage, incoming flow of the diffuser is choke up with a part of the fuel blocked at right side flowing back to the annular chamber around the tongue. As a result, serious flow separation is raised with a high pressure decrease, which is expected to generate cavitation and following damage on the casing tongue.%针对某型航空发动机加力燃油泵隔舌空蚀破坏,采用滑移网格技术模拟泵内非定常流场,揭示了压出室在典型非设计工况下的内流特征,研究了隔舌处的空化机理.计算结果表明:大流量工况,扩散管锥形段存在大小两个分离涡,而环形腔室隔舌段燃油以相切方式流经隔舌壁面,无明显流动分离,不会发生空化;而小流量工况,扩散管锥形段内两分离涡扩展到大部分区域,右半侧部分阻滞燃油在反向流向涡作用下,绕流隔舌上部,在隔舌下游形成了明显分离涡,导致隔舌壁面静压急剧降低,进而引发空化,产生空蚀破坏.

  9. Noise of High-Performance Aircraft at Afterburner

    Science.gov (United States)

    2015-07-11

    50 ft. from the jet exit by the inverse-square law. The data was acquired at four engine power settings. But only data at 3 power settings are found...8217 ’ ’ ’ ’ 10u f/f- J I 1 I I III, 10’ Figure 10. The two similarity spectra of turbulent mixing noise of high-speed jets . In a previous work ...Vibration, Vol. 352, 103-128, 2015), it was found that when the engine was operating at intermediate power, the jet noise of the engine consisted of

  10. Development of Emissions Measurement Techniques for Afterburning Turbine Engines. Supplement 2. Afterburner Plume Computer Program User’s Manual.

    Science.gov (United States)

    1975-10-01

    and total HC (as single- carbon-atom molecules) and total NO with sample water content as-sampled. ___— l B ’ ILllllpiM III... The composition and...hydrogen/carbon atom ratio. Absolute enthalpy of fuel, Btu/lbm. Water /air mass ratio in ambient air. Fan inlet total temperature, °R. Engine by-pass...IFtCQRE .>NO. C3RSTP) GO TO S IFISuPC .AND. SJPSIP) IFCMFR tANQ , HER3TP) GO TO 20 GU TO 5 GO TO JTCTRLOI JTCTRL02 JTCTRL03 JTXXRLM- RELÖCATE

  11. Modeling of Chemical Reactions in Afterburning for the Reduction of N2O

    DEFF Research Database (Denmark)

    Gustavsson, Lennart; Glarborg, Peter; Leckner, Bo

    1996-01-01

    Full scale tests in a 12 MW fluidized bed combustor on reduction of N2O by secondary fuel injection are analyzed in terms a model that involves a detailed reaction mechanism for the gas phase chemistry as well as a description of gas-solid reactions.......Full scale tests in a 12 MW fluidized bed combustor on reduction of N2O by secondary fuel injection are analyzed in terms a model that involves a detailed reaction mechanism for the gas phase chemistry as well as a description of gas-solid reactions....

  12. 含氢硅油的最新研究进展%Development of Silicone Rubber Insulation on Ramjet Afterburner

    Institute of Scientific and Technical Information of China (English)

    白雪; 李季; 赵晓璐; 张磊; 杨春晖

    2014-01-01

    This review analyzes the reasons for poor work conditions of heat insulation in ramjet,and dis-cusses the progress of the factors influencing the silicone rubber insulation,such as basic rubber,powder fill-er,fiber and other reagents.%综述了近20年来含氢硅油的研究成果,对全含氢硅油和部分含氢硅油的制备方法进行了分析及比较。展望了含氢硅油的发展方向。

  13. Development of an integrated, zero-G pneumatic transporter/rotating-paddle incinerator/catalytic afterburner subsystem for processing human waste on board spacecraft

    Science.gov (United States)

    Fields, S. F.; Labak, L. J.; Honegger, R. J.

    1974-01-01

    A baseline laboratory prototype of an integrated, six man, zero-g subsystem for processing human wastes onboard spacecraft was investigated, and included the development of an operational specification for the baseline subsystem, followed by design and fabrication. The program was concluded by performing a series of six tests over a period of two weeks to evaluate the performance of the subsystem. The results of the tests were satisfactory, however, several changes in the design of the subsystem are required before completely satisfactory performance can be achieved.

  14. Between designer drugs and afterburners: A Lexicographic-Semantic Study of Equivalence Tussen designer drugs (ontwerpersdwelms en afterburners (naverbranders: 'n leksikografies-semantiese studie van ekwivalensie.

    Directory of Open Access Journals (Sweden)

    Arleta Adamska-Sałaciak

    2012-01-01

    Full Text Available

    The lexicons of natural languages are not isomorphic. Reasons for the anisomorphism can be sought on three interrelated planes: language structure, extralinguistic reality, and conceptualisation. Simply put, the relevant differences may reside in the language, the world, the mind, or any combination of these. As a result, what goes under the name of lexicographic equivalence is a rather heterogeneous category. Growing awareness of this fact has resulted over the years in the creation of several tentative typologies of equivalence, one of which is presented below, together with a brief discussion of some strategies for dealing with imperfect equivalence.

    The remaining part of the article comprises a detailed analysis of a single problem encountered while preparing a new edition of a bilingual dictionary for Polish learners of English. The task at hand involved choosing a viable counterpart for a (Polish semantic neologism from among a few (English equivalence candidates. In the discussion, reference is made both to the metalexicographic categories introduced earlier and to such concepts developed by lexical (especially cognitive semantics which may prove helpful in capturing the meaning differences between the source-language item and its competing target-language renditions.

    This micro-scale dissection of a single specimen demonstrates that we are still some way from being able to classify, let alone deal with, all the instances of imperfect interlingual correspondence that come our way. Persisting in the efforts to advance our understanding of the complex issues covered by the blanket term lexicographic equivalence thus seems crucial for improving the treatment of meaning in bilingual dictionaries.

    Die leksikons van natuurlike tale is nie isomorf nie. Redes vir die gebrek aan isomorfie kom op drie onderling verwante vlakke voor: taalstruktuur, die buitetalige realiteit, en konseptualisasie. Anders gestel kan die tersaaklike verskille in die taal, die wêreld, die verstand, of enige kombinasie hiervan aangetref word. Gevolglik is dit wat as leksikografiese ekwivalensie bekend staan 'n nogal heterogene kategorie. 'n Groeiende bewuswording van hierdie feit het oor die jare daartoe gelei dat verskeie tentatiewe tipologieë van ekwivalensie geskep is, waarvan een hieronder aangebied word, saam met 'n kort bespreking van sommige strategieë om onvolledige ekwivalensie te hanteer.

    Die oorblywende deel van die artikel bevat 'n uitvoerige ontleding van 'n enkele probleem wat teëgekom is toe 'n nuwe uitgawe van 'n tweetalige woordeboek vir Poolse aanleerders van Engels saamgestel is. Die betrokke taak het behels dat 'n lewensvatbare teenhanger vir 'n (Poolse semantiese neologisme uit 'n paar ekwivalente (Engelse alternatiewe gekies word. In die bespreking word verwys na sowel die metaleksikografiese kategorieë wat vroeër geopper is, as na konsepte in die leksikale (veral die kognitiewe semantiek wat sou kon help om die betekenisverskil tussen die brontaalitem en sy kompeterende doeltaalvertalings vas te vang.

    Hierdie ontleding van 'n enkele voorbeeld op mikroskaal demonstreer dat ons nog ver daarvan is om al die gevalle van onvolledige intertalige ooreenstemming wat ons teëkom te kan klassifiseer, wat nog te sê van te hanteer. Om vol te hou met ons pogings om die komplekse vraagstukke te verstaan wat deur die oorkoepelende term leksikografiese ekwivalensie gedek word, is dit dus uiters belangrik om die hantering van betekenis in tweetalige woordeboeke te verbeter.

  15. High-efficiency high-energy Ka source for the critically-required maximum illumination of x-ray optics on Z using Z-petawatt-driven laser-breakout-afterburner accelerated ultrarelativistic electrons LDRD .

    Energy Technology Data Exchange (ETDEWEB)

    Sefkow, Adam B.; Bennett, Guy R.

    2010-09-01

    Under the auspices of the Science of Extreme Environments LDRD program, a <2 year theoretical- and computational-physics study was performed (LDRD Project 130805) by Guy R Bennett (formally in Center-01600) and Adam B. Sefkow (Center-01600): To investigate novel target designs by which a short-pulse, PW-class beam could create a brighter K{alpha} x-ray source than by simple, direct-laser-irradiation of a flat foil; Direct-Foil-Irradiation (DFI). The computational studies - which are still ongoing at this writing - were performed primarily on the RedStorm supercomputer at Sandia National Laboratories Albuquerque site. The motivation for a higher efficiency K{alpha} emitter was very clear: as the backlighter flux for any x-ray imaging technique on the Z accelerator increases, the signal-to-noise and signal-to-background ratios improve. This ultimately allows the imaging system to reach its full quantitative potential as a diagnostic. Depending on the particular application/experiment this would imply, for example, that the system would have reached its full design spatial resolution and thus the capability to see features that might otherwise be indiscernible with a traditional DFI-like x-ray source. This LDRD began FY09 and ended FY10.

  16. Application of after-burning between high and low turbines to improve performance of two-spool turbofan engine%用高低压涡轮间补燃提高双轴涡扇发动机性能

    Institute of Scientific and Technical Information of China (English)

    齐少军; 蔡元虎; 王占学; 葛爱学

    2002-01-01

    基于双轴涡扇发动机热力学模型,采用高低压涡轮间补燃的方法,实现了对发动机性能的改善.研究分析了高低压涡轮间补燃对发动机高度特性、速度特性以及转速特性的影响.计算结果表明采用高低压涡轮间补燃的热力循环后,发动机的推力明显提高,耗油率基本保持原来的水平或有所降低.

  17. Application of active disturbance rejection control method in aeroengines afterburning transition state control%自抗扰控制算法在发动机加力过渡态控制中的应用

    Institute of Scientific and Technical Information of China (English)

    张海波; 孙健国

    2010-01-01

    主要研究了航空发动机加力过渡态控制的新方法.在不改变原有发动机控制结构的基础上,提出了一种增广LQR法(Augmented Linear Quadratic regulator-ALQR)综合ADRC(Active Disturbance Rejection Control)干扰补偿控制的算法(简称ALQR+ADRC),该算法除了有原ALQR控制所具备的强的消除静差能力之外,还兼具ADRC优良的干扰补偿能力.通过模拟快速进入/退出发动机加力过渡态过程,验证了该算法具有理想的控制效果,能够较好地协调加力燃油供给和喷口开张,在整个过渡态过程中对核心机工作有较小的影响.

  18. 77 FR 8575 - National Emissions Standards for Hazardous Air Pollutants: Secondary Aluminum Production

    Science.gov (United States)

    2012-02-14

    ... scrap shredders, thermal chip dryers, scrap dryers/delacquering kilns/decoating kilns, group 1 furnaces... following affected sources: aluminum scrap shredders (subject to PM standards), thermal chip dryers (subject... scrap shredders; afterburners for control of THC and D/F from thermal chip dryers; afterburners...

  19. Eliminating air pollution from petrol engines

    Energy Technology Data Exchange (ETDEWEB)

    Gujral, I.S.; Dave, R.K.; Shende, S.; Saxena, L.M.

    1976-03-01

    A review is given of various methods of controlling nitrogen oxides emissions from automobile spark ignition engines. Methods discussed include exhaust gas recirculation, catalytic conversion, afterburning, burning of non-stoichiometric mixtures, and water injection. It is concluded that the combined use of a catalytic converter and an afterburner is the most feasible option for meeting pollution standards. (PMA)

  20. 40 CFR Appendix A to Part 20 - Guidelines for Certification

    Science.gov (United States)

    2010-07-01

    ... afterburners. (6) Catalytic afterburners. (7) Gas absorption equipment. (8) Vapor condensers. (9) Vapor recovery systems. (10) Floating roofs for storage tanks. (11) Fuel cleaning equipment. (12) Combinations of... from a coal-fired boiler and the addition of gas or oil burners. The purpose of the burners is...

  1. Effects of fuel-gas jetting modes on mixing effectiveness in the afterburning chamber of solid rocket ramjets%燃气喷射方式对冲压发动机补燃室掺混效果的影响

    Institute of Scientific and Technical Information of China (English)

    陈林泉; 毛根旺; 霍东兴; 刘霓生

    2005-01-01

    在空气进气参数不变情况下,分析了喷口布局、喷口形状、头部型面对冷流掺混效果的影响.结果表明,燃气喷射方式不同,掺混在补燃室中的发展过程也不同,提高补燃室内整体掺混度的方法,不一定能提高头部的掺混度;可提高头部掺混度的燃气喷射方式有5孔交汇喷射、5孔偏心喷射以及头部采用椭球型面.

  2. Parametric studies with an atmospheric diffusion model that assesses toxic fuel hazards due to the ground clouds generated by rocket launches

    Science.gov (United States)

    Stewart, R. B.; Grose, W. L.

    1975-01-01

    Parametric studies were made with a multilayer atmospheric diffusion model to place quantitative limits on the uncertainty of predicting ground-level toxic rocket-fuel concentrations. Exhaust distributions in the ground cloud, cloud stabilized geometry, atmospheric coefficients, the effects of exhaust plume afterburning of carbon monoxide CO, assumed surface mixing-layer division in the model, and model sensitivity to different meteorological regimes were studied. Large-scale differences in ground-level predictions are quantitatively described. Cloud alongwind growth for several meteorological conditions is shown to be in error because of incorrect application of previous diffusion theory. In addition, rocket-plume calculations indicate that almost all of the rocket-motor carbon monoxide is afterburned to carbon dioxide CO2, thus reducing toxic hazards due to CO. The afterburning is also shown to have a significant effect on cloud stabilization height and on ground-level concentrations of exhaust products.

  3. Bose-Einstein Correlations in a Space-Time Approach to $e^{+} e^{-}$ Annihilation into Hadrons

    CERN Document Server

    Kinder-Geiger, Klaus; Heinz, Ulrich W; Wiedemann, Urs Achim

    2000-01-01

    A new treatment of Bose-Einstein correlations is incorporated in a space-time parton-shower model for e+ e- annihilation into hadrons. Two alternative afterburners are discussed, and we use a simple calculable model to demonstrate that they reproduce successfully the size of the hadron emission region. One of the afterburners is used to calculate two-pion correlations in e+ e- -> Z^0 -> hadrons and e+ e- -> W+ W- -> hadrons. Results are shown with and without resonance decays, for correlations along and transverse to the thrust jet axis in these two classes of events.

  4. Exhaust emissions survey of a turbofan engine for flame holder swirl type augmentors at simulated altitude flight conditions

    Science.gov (United States)

    Moss, J. E., Jr.

    1981-01-01

    Emissions of carbon dioxide, total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from an F100 afterburning two spool turbofan engine at simulated flight conditions are reported. Tests were run at Mach 0.8 at altitudes of 10.97 and 13.71 km (36,000 and 45,000 ft), and at Mach 1.2 at 13.71 km (45,000 ft). Emission measurements were made from intermediate power (nonafterburning) through maximum afterburning, using a single point gas sample probe traversed across the horizontal diameter of the exhaust nozzle. The data show that emissions vary with flight speed, altitude, power level, and radial position across the nozzle. Carbon monoxide emissions were low for intermediate and partial afterburning power. Unburned hydrocarbons were near zero for most of the simulated flight conditions. At maximum afterburning, there were regions of NOx deficiency in regions of high CO. The results suggest that the low NOx levels observed in the tests are a result of interaction with high CO in the thermal converter. CO2 emissions were proportional to local fuel air ratio for all test conditions.

  5. Reproducibility Distinguishability and Correlation of Fireball and Shockwave Dynamics in Explosive Munitions Detonations

    Science.gov (United States)

    2006-03-01

    plots, heat of detonation (which follows the same correlation as the specific afterburn energy) initial mass in the lower plots. As all quantities...fireball area increases with the third power of the heat of detonation , neglecting the outliers...third power of the heat of detonation , neglecting the outliers. In all cases, correlation is higher than when C-4 was included

  6. Numerical simulation of long-duration blast wave evolution in confined facilities

    Science.gov (United States)

    Togashi, F.; Baum, J. D.; Mestreau, E.; Löhner, R.; Sunshine, D.

    2010-10-01

    The objective of this research effort was to investigate the quasi-steady flow field produced by explosives in confined facilities. In this effort we modeled tests in which a high explosive (HE) cylindrical charge was hung in the center of a room and detonated. The HEs used for the tests were C-4 and AFX 757. While C-4 is just slightly under-oxidized and is typically modeled as an ideal explosive, AFX 757 includes a significant percentage of aluminum particles, so long-time afterburning and energy release must be considered. The Lawrence Livermore National Laboratory (LLNL)-produced thermo-chemical equilibrium algorithm, “Cheetah”, was used to estimate the remaining burnable detonation products. From these remaining species, the afterburning energy was computed and added to the flow field. Computations of the detonation and afterburn of two HEs in the confined multi-room facility were performed. The results demonstrate excellent agreement with available experimental data in terms of blast wave time of arrival, peak shock amplitude, reverberation, and total impulse (and hence, total energy release, via either the detonation or afterburn processes.

  7. 76 FR 74014 - Approval and Promulgation of Implementation Plans; Illinois; Volatile Organic Compound Emission...

    Science.gov (United States)

    2011-11-30

    ... Compound Emission Control Measures for Chicago and Metro-East St. Louis Ozone Nonattainment Areas AGENCY... compound (VOC) rules for approval into its State Implementation Plan (SIP). The purpose of these rules is... does not exceed 8.00 millimeters of mercury (mmHg) or by use of add-on control (i.e., an afterburner...

  8. Simulation of underexpanded supersonic jet flows with chemical reactions

    Directory of Open Access Journals (Sweden)

    Fu Debin

    2014-06-01

    Full Text Available To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics (CFD method. A program based on a total variation diminishing (TVD methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navier–Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.

  9. Static internal performance including thrust vectoring and reversing of two-dimensional convergent-divergent nozzles

    Science.gov (United States)

    Re, R. J.; Leavitt, L. D.

    1984-01-01

    The effects of geometric design parameters on two dimensional convergent-divergent nozzles were investigated at nozzle pressure ratios up to 12 in the static test facility. Forward flight (dry and afterburning power settings), vectored-thrust (afterburning power setting), and reverse-thrust (dry power setting) nozzles were investigated. The nozzles had thrust vector angles from 0 deg to 20.26 deg, throat aspect ratios of 3.696 to 7.612, throat radii from sharp to 2.738 cm, expansion ratios from 1.089 to 1.797, and various sidewall lengths. The results indicate that unvectored two dimensional convergent-divergent nozzles have static internal performance comparable to axisymmetric nozzles with similar expansion ratios.

  10. Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft

    Science.gov (United States)

    Berrier, B. L.; Re, R. J.

    1980-01-01

    An investigation was conducted of isolated convergent-divergent nozzles to determine the effect of several design parameters on nozzle performance. Tests were conducted using high pressure air for propulsion simulation at Mach numbers from 0.60 to 2.86 at an angle of attack of 0 deg and at nozzle pressure ratios from jet off to 46.0. Three power settings (dry, partial afterburning, and maximum afterburning), three nozzle lengths, and nozzle expansion ratios from 1.22 to 2.24 were investigated. In addition, the effects of nozzle throat radius and a cusp in the external boattail geometry were studied. The results of this study indicate that, for nozzles operating near design conditions, increasing nozzle length increases nozzle thrust-minus-drag performance. Nozzle throat radius and an external boattail cusp had negligible effects on nozzle drag or internal performance.

  11. Simulation of underexpanded supersonic jet flows with chemical reactions

    Institute of Scientific and Technical Information of China (English)

    Fu Debin; Yu Yong; Niu Qinglin

    2014-01-01

    To achieve a detailed understanding of underexpanded supersonic jet structures influenced by afterburning and other flow conditions, the underexpanded turbulent supersonic jet with and without combustions are investigated by computational fluid dynamics (CFD) method. A program based on a total variation diminishing (TVD) methodology capable of predicting complex shocks is created to solve the axisymmetric expanded Navier-Stokes equations containing transport equations of species. The finite-rate ratio model is employed to handle species sources in chemical reactions. CFD solutions indicate that the structure of underexpanded jet is typically influenced by the pressure ratio and afterburning. The shock reflection distance and maximum value of Mach number in the first shock cell increase with pressure ratio. Chemical reactions for the rocket exhaust mostly exist in the mixing layer of supersonic jet flows. This tends to reduce the intensity of shocks existing in the jet, responding to the variation of thermal parameters.

  12. Combustion Technology for Incinerating Wastes from Air Force Industrial Processes.

    Science.gov (United States)

    1984-02-01

    waste for energy (not recycling cement kiln dust for clinker ) to be distinguishable from a commercial hazardous waste incinerator in -" its potential...ORGANIZATION NAME AND ADDRESS 10 PROGRAM ELEMENT . PROJECT, TASK . National Bureau of Standards AREA & WORK UNIT NUMBERS Washington D.C. 20234 PE 63723F JON...high temperature combustion zone transit time which significantly exceeds fuel droplet burnout and mixing times, and (4) employing afterburners

  13. Effect of von Karman Vortex Shedding on Regular and Open-slit V-gutter Stabilized Turbulent Premixed Flames

    Science.gov (United States)

    2012-04-01

    a trade-off between static and dynamic stability is evident. 1. Introduction Requirements for rapid increase in thrust for take-off and climb ...injected through spray bars and is atomized by shearing due to the turbine exhaust flow. It then evaporates and mixes with the available oxygen. The mixture...exit through a converging/diverging nozzle with extensive film cooling and a variable throat area located downstream of the afterburner exit. The

  14. HPC Insights, Fall 2011

    Science.gov (United States)

    2011-01-01

    thrust for takeoff and climb calls for additional thrust-producing devices. The afterburner concept is an auxiliary burner located behind the turbine...across the duct. The combustion products exit through a converging/diverging nozzle with extensive film cooling and a variable throat area located...of factors including flameholder geometry, fuel spray injection sites, blockage, non-uniformity of fuel/air ratio, evaporation rates, and ignition

  15. Effect of Riblets upon Flow Separation in a Subsonic Diffuser

    Science.gov (United States)

    1988-12-01

    Technology Air University In Partial Fulfillment of the Requirements for the Degree of Master of Science in Aeronautical Engineering Nathan W. Martens...afterburner where the flow leaving the turbine must be 4 slowed from a high subsonic Mach number to a Mach number of about 0.2" (8:305). Physicall ., a...Riblets," Proceedings of the AIAA 20th Aerospace Sciences Meeting. Paper No. 82-0169. New York: American Institute of Aeronautics and Astronautics

  16. Proceedings of the International Pyrotechnics Seminar (5th) Held 12-16 July 1976, Vail, Colorado.

    Science.gov (United States)

    1976-01-01

    measuring the maximum pressure (P max) obtained at a given propellant loading density. At low pressures the covolume effect is negligible and impetus...helium, hydrogen, and cartridge generated gas. Function times of less than 10 ms were achieved, depending on the gas source and pressure . The present...reduced as atmospheric pressure decreases and wind shear velocities increase. Flare plume afterburning is a complex process, depending on fundamental

  17. NACA Conference on Turbojet Engines for Supersonic Propulsion. A Compilation of Technical Material Presented

    Science.gov (United States)

    1953-10-01

    particular, in combination with a static-pressure rise across the rotor, have had low turbine efficiency. On the other hand, the gains w be realized by being...does not have the disadvantages associated itith compressor surge, compressor off-design- point operation, or low turbine -inlet temperatures at take...either the high turbine-inlet-temperature nonafterburning engines or low turbine -inlet-temperature afterburning engines. For this case where high turbine

  18. Multidisciplinary and Multiobjective Optimization in Conceptual Design for Mixed-Stream Turbofan Engines

    Science.gov (United States)

    1996-12-01

    AFIT/GAE/ENY/96D-6 Abstract Despite major advances in design tools such as engine cycle analysis software and computer-aided design, conceptual gas...Ratio of specific heat for turbine flow etaAB = =iAB Efficiency of afterburner etab = 1lb = Efficiency of burner etacprime = l, = Efficiency of fan...ABSTRACT (Maximum 200 words) Despite major advances in design tools such as engine cycle analysis software and computer-aided design, conceptual gas

  19. Classification of Battlespace Detonations from Temporally Resolved Multi-Band Imagery and Mid-Infrared Spectra

    Science.gov (United States)

    2005-03-01

    called the heat of detonation and includes only the combustion of the explosive reactants, not the heat associated with the secondary afterburn. This...32:24] 2. Basic Phenomenology As mentioned earlier, the heat of detonation ∆H is the heat (or energy) generated during the reaction and is...232, −++++= eTdTcTbTaTC ip , (5) where the coefficients a through e are defined in Table 2, the heat of detonation becomes an integral

  20. Aerothermodynamic analysis of a Coanda/Refraction jet engine test facility.

    OpenAIRE

    Maraoui, André

    1988-01-01

    Approved for public release; distribution is unlimited A computer model of the Coanda Refraction Jet Engine Test Cell facility was developed using the PHOENICS computer code. The PIIOENICS code was utilized to determine the steady state aerothermal characteristics of the test cell during the testing of an E404 gas turbine engine with afterburner in operation. Computer generated aerothermodynamic field variables of pressure, velocity and temperature parameters were compared t...

  1. Preliminary Design of a Tip-Jet-Driven Heavy Lift Helicopter Incorporating Circulation Control

    Science.gov (United States)

    1981-03-01

    helicopter size, and soon become limiting factors (Reference 1). 2 .i1 * ~ ~ ~ Fgr 1. XH-17qI¶ ,=---.- I~~~~Fgr ___.________________I 44 Figur 1. X-1...have not been practical in the past because of the limitations imposed by available engines and materials. For example, the afterburners at the blade...successive runs. An option was a-’ailable to optimize the main rotor automatically using iterative procedures. The funcions of the individual

  2. The QCD Phase Diagram, Equation of State, and Heavy Ion Collisions

    OpenAIRE

    2001-01-01

    After some historic remarks and a brief summary of recent theoretical news about the QCD phases, we turn to the issue of $freeze-out$ in heavy ion collisions. We argue that the chemical freeze-out line should actually consists of two crossing lines of different nature. We also consider some inelatic reactions which occure $after$ chemical freeze-out, emphasizing the role of overpopulation of pions. The $hydrodynamics$ (with or without hadronic afterburner) explaines SPS/RHIC data on radial an...

  3. Static internal performance of a thrust vectoring and reversing two-dimensional convergent-divergent nozzle with an aft flap

    Science.gov (United States)

    Re, R. J.; Leavitt, L. D.

    1986-01-01

    The static internal performance of a multifunction nozzle having some of the geometric characteristics of both two-dimensional convergent-divergent and single expansion ramp nozzles has been investigated in the static-test facility of the Langley 16-Foot Transonic Tunnel. The internal expansion portion of the nozzle consisted of two symmetrical flat surfaces of equal length, and the external expansion portion of the nozzle consisted of a single aft flap. The aft flap could be varied in angle independently of the upper internal expansion surface to which it was attached. The effects of internal expansion ratio, nozzle thrust-vector angle (-30 deg. to 30 deg., aft flap shape, aft flap angle, and sidewall containment were determined for dry and afterburning power settings. In addition, a partial afterburning power setting nozzle, a fully deployed thrust reverser, and four vertical takeoff or landing nozzle, configurations were investigated. Nozzle pressure ratio was varied up to 10 for the dry power nozzles and 7 for the afterburning power nozzles.

  4. On the fundamentals of thermal treatment for the cleanup of contaminated soils

    Energy Technology Data Exchange (ETDEWEB)

    Lighty, J.S.; Silcox, G.D.; Pershing, D.W. (Utah Univ., Salt Lake City, UT (USA)); Cundy, V.A. (Louisiana State Univ., Baton Rouge, LA (USA))

    1988-01-01

    Considerable research has focused on air emissions from the afterburner, mainly as a result of the regulations regarding destruction and removal efficiency of a principle organic hazardous constituent (POHC) -99.99% of the POHC must be destroyed in the system based on gas measurements from the afterburner. Research focusing on the primary desorber environment, the evolution of contaminants from solids and the resulting quality of the ash, is limited. The primary desorber is often operated at high temperatures which is costly, particularly for the cleanup of contaminated solid, due to high auxiliary fuel requirements. A more desirable option would be to desorb the contaminants from the soil at lower temperatures and then expose the off-gas to a high-temperature afterburner for decomposition of the hazardous compounds. In addition, the ability to predict the quality of the resulting soil is desirable for delisting purposes. To understand the desorption process, research must explore the rate controlling processes that are occurring. The overall goal of this research is to develop an understanding of the fundamental transport phenomena associated with the evolution of hazardous materials from soils in the primary desorber environment. As well, the rate information obtained can be used to model the thermal desorption of contaminants under a variety of experimental conditions; from these results large-scale operating parameters can be determined for optimum cleanup conditions.

  5. Analysis of gas turbine engines using water and oxygen injection to achieve high Mach numbers and high thrust

    Science.gov (United States)

    Henneberry, Hugh M.; Snyder, Christopher A.

    1993-01-01

    An analysis of gas turbine engines using water and oxygen injection to enhance performance by increasing Mach number capability and by increasing thrust is described. The liquids are injected, either separately or together, into the subsonic diffuser ahead of the engine compressor. A turbojet engine and a mixed-flow turbofan engine (MFTF) are examined, and in pursuit of maximum thrust, both engines are fitted with afterburners. The results indicate that water injection alone can extend the performance envelope of both engine types by one and one-half Mach numbers at which point water-air ratios reach 17 or 18 percent and liquid specific impulse is reduced to some 390 to 470 seconds, a level about equal to the impulse of a high energy rocket engine. The envelope can be further extended, but only with increasing sacrifices in liquid specific impulse. Oxygen-airflow ratios as high as 15 percent were investigated for increasing thrust. Using 15 percent oxygen in combination with water injection at high supersonic Mach numbers resulted in thrust augmentation as high as 76 percent without any significant decrease in liquid specific impulse. The stoichiometric afterburner exit temperature increased with increasing oxygen flow, reaching 4822 deg R in the turbojet engine at a Mach number of 3.5. At the transonic Mach number of 0.95 where no water injection is needed, an oxygen-air ratio of 15 percent increased thrust by some 55 percent in both engines, along with a decrease in liquid specific impulse of 62 percent. Afterburner temperature was approximately 4700 deg R at this high thrust condition. Water and/or oxygen injection are simple and straightforward strategies to improve engine performance and they will add little to engine weight. However, if large Mach number and thrust increases are required, liquid flows become significant, so that operation at these conditions will necessarily be of short duration.

  6. Solar thermal rocket engine (STRE) thrust characteristics at the change of engine operation mode and of the flight vehicle attitude in the solar system

    Science.gov (United States)

    Kudrin, O. I.

    1993-10-01

    Relationships are presented which describe changes in the thrust and specific impulse of a solar thermal rocket engine due to a change in the flow rate of the working fluid (hydrogen). Expressions are also presented which describe the variation of the STRE thrust and specific impulse with the distance between the flight vehicle and the sun. Results of calculations are presented for an STRE with afterburning of the working fluid (hydrogen + oxygen) using hydrogen heating by solar energy to a temperature of 2360 K.

  7. HBT Parameters and Space-Momentum Correlations in Relativistic Heavy-Ion Collisions

    Institute of Scientific and Technical Information of China (English)

    张景波; 霍雷; 张卫宁; 李新华; 许怒; 刘亦铭

    2001-01-01

    Using the relativistic quantum molecular dynamics approach, with a correlation after-burner, the physics of the transverse momentum dependence of the Hanbury-Brown and Twiss parameters is studied for Au t Au, Si + Si and p + p collisions at the centre-of-mass energy v s = 200 AGeV. The results indicate that the space-momentum correlations would affect such dependence in both heavy-ion and elementary collisions. The size parameters as a function of the transverse mass mt are sensitive to the degree of space-momentum correlations.

  8. The development and flight test of an electronic integrated propulsion control system

    Science.gov (United States)

    Johnson, H. J.; Painter, W. D.

    1976-01-01

    Advanced technical features of the electronic integrated propulsion control system (IPCS) and flight evaluation tests of IPCS (F-111E with TF30-P-9 engines as test vehicle) are described. Nine baseline flight tests and 15 IPCS flight tests were conducted. Instrumentation, data acquisition and data processing systems, software maintenance procedures, flight test procedures, flight safety criteria, flight test results, and ground and flight testing of the aircraft system are described. Advantages conferred by IPCS include: faster accelerations (both gas generator and afterburner performance), better thrust and flight control, reduced flight idle thrust, reduced engine ground trim, extended service ceiling, automatic stall detection, and stall recovery detection.

  9. Review of multi-dimensional large-scale kinetic simulation and physics validation of ion acceleration in relativistic laser-matter interaction

    Energy Technology Data Exchange (ETDEWEB)

    Wu, Hui-Chun [Los Alamos National Laboratory; Hegelich, B.M. [Los Alamos National Laboratory; Fernandez, J.C. [Los Alamos National Laboratory; Shah, R.C. [Los Alamos National Laboratory; Palaniyappan, S. [Los Alamos National Laboratory; Jung, D. [Los Alamos National Laboratory; Yin, L [Los Alamos National Laboratory; Albright, B.J. [Los Alamos National Laboratory; Bowers, K. [Guest Scientist of XCP-6; Huang, C. [Los Alamos National Laboratory; Kwan, T.J. [Los Alamos National Laboratory

    2012-06-19

    Two new experimental technologies enabled realization of Break-out afterburner (BOA) - High quality Trident laser and free-standing C nm-targets. VPIC is an powerful tool for fundamental research of relativistic laser-matter interaction. Predictions from VPIC are validated - Novel BOA and Solitary ion acceleration mechanisms. VPIC is a fully explicit Particle In Cell (PIC) code: models plasma as billions of macro-particles moving on a computational mesh. VPIC particle advance (which typically dominates computation) has been optimized extensively for many different supercomputers. Laser-driven ions lead to realization promising applications - Ion-based fast ignition; active interrogation, hadron therapy.

  10. Minimum fuel mode evaluation

    Science.gov (United States)

    Orme, John S.; Nobbs, Steven G.

    1995-01-01

    The minimum fuel mode of the NASA F-15 research aircraft is designed to minimize fuel flow while maintaining constant net propulsive force (FNP), effectively reducing thrust specific fuel consumption (TSFC), during cruise flight conditions. The test maneuvers were at stabilized flight conditions. The aircraft test engine was allowed to stabilize at the cruise conditions before data collection initiated; data were then recorded with performance seeking control (PSC) not-engaged, then data were recorded with the PSC system engaged. The maneuvers were flown back-to-back to allow for direct comparisons by minimizing the effects of variations in the test day conditions. The minimum fuel mode was evaluated at subsonic and supersonic Mach numbers and focused on three altitudes: 15,000; 30,000; and 45,000 feet. Flight data were collected for part, military, partial, and maximum afterburning power conditions. The TSFC savings at supersonic Mach numbers, ranging from approximately 4% to nearly 10%, are in general much larger than at subsonic Mach numbers because of PSC trims to the afterburner.

  11. Incineration of animal by-products--The impact of selected parameters on the flux of flue gas enthalpy.

    Science.gov (United States)

    Bujak, Janusz; Sitarz, Piotr

    2016-04-01

    This paper presents model analyses and tests of animal by-product waste thermal treatment plants. A schedule of tests was prepared, and 62,024 cases of system operation were analysed. A map/work field of the tested plant was drawn up on the basis thereof. Calculations were made following an algorithm described by Bujak (2015a) written in the VBA (Visual Basic for Application) language. The tests showed that when incinerating animal waste, the flux of physical enthalpy of the flue gas from the afterburner chamber depends on numerous design and operating parameters. The most important include the following: humidity and flux of the waste, concentration of oxygen in the flue gas in the afterburner chamber and loss of heat flux to the atmosphere through the external surfaces of the plant. Individual design and operating parameters can be selected so that the process of incineration is ensured without additional fuel. The performed analyses were verified against the actual object at the industrial scale using a meat plant that manufactures ham and processes beef, pork and poultry with a capacity of 150 tonnes/day. The production process waste included mainly bones and - in much smaller quantities - meat and bone meal, at 17 tonnes/day. The performed tests and analyses can be used to optimise the operation of the waste thermal treatment plant at the stages of design and operation.

  12. A detailed numerical simulation of a liquid-propellant rocket engine ground test experiment

    Science.gov (United States)

    Lankford, D. W.; Simmons, M. A.; Heikkinen, B. D.

    1992-07-01

    A computational simulation of a Liquid Rocket Engine (LRE) ground test experiment was performed using two modeling approaches. The results of the models were compared with selected data to assess the validity of state-of-the-art computational tools for predicting the flowfield and radiative transfer in complex flow environments. The data used for comparison consisted of in-band station radiation measurements obtained in the near-field portion of the plume exhaust. The test article was a subscale LRE with an afterbody, resulting in a large base region. The flight conditions were such that afterburning regions were observed in the plume flowfield. A conventional standard modeling approach underpredicted the extent of afterburning and the associated radiation levels. These results were attributed to the absence of the base flow region which is not accounted for in this model. To assess the effects of the base region a Navier-Stokes model was applied. The results of this calculation indicate that the base recirculation effects are dominant features in the immediate expansion region and resulted in a much improved comparison. However, the downstream in-band station radiation data remained underpredicted by this model.

  13. Interplay of parton and hadron cascades in nucleus-nucleus collisions at the CERN SPS and RHIC

    CERN Document Server

    Kinder-Geiger, Klaus; Geiger, Klaus; Longacre, Ronald

    1998-01-01

    We introduce a Monte Carlo space-time model for high-energy collisions with nuclei, involving the dynamical interplay of perturbative QCD parton production and evolution, with non-perturbative parton-cluster formation and `afterburner' cascading of formed pre-hadronic clusters plus hadron excitations. This approach allows us to trace the space-time history of parton and hadron degrees of freedom of nuclear collisions on the microscopical level of parton and hadron cascades in both position and momentum space, from the instant of nuclear overlap to the final yield of particles. In applying this approach, we analyze Pb+Pb collisions at the CERN SPS with beam energy 158 GeV (sqrt{s}/A = 17 GeV) and Au+Au collisions at RHIC with collider energy \\sqrt{s}/A = 200 GeV. We find that the perturbative QCD parton production and cascade development provides an important contribution to particle production at central rapidities, and that the `afterburner' cascading of pre-hadronic clusters and formed hadrons emerging from...

  14. Experimental/Analytical Characterization of the RBCC Rocket-Ejector Mode

    Science.gov (United States)

    Ruf, J. H.; Lehman, M.; Pal, S.; Santoro, R. J.

    2000-01-01

    The experimental/analytical research work described here addresses the rocket-ejector mode (Mach 0-2 operational range) of the RBCC engine. The experimental phase of the program includes studying the mixing and combustion characteristics of the rocket-ejector system utilizing state-of-the-art diagnostic techniques. A two-dimensional variable geometry rocket-ejector system with enhanced optical access was utilized as the experimental platform. The goals of the experimental phase of the research being conducted at Penn State are to: (a) systematically increase the range of rocket-ejector understanding over a wide range of flow/geometry parameters and (b) provide a comprehensive data base for evaluating and anchoring CFD codes. Concurrent with the experimental activities, a CFD code benchmarking effort at Marshall Space Flight Center is also being used to further investigate the RBCC rocket-ejector mode. Experiments involving the single rocket based optically-accessible rocket-ejector system have been conducted for Diffusion and Afterburning (DAB) as well as Simultaneous Mixing and Combustion configurations. For the DAB configuration, air is introduced (direct-connect) or ejected (sea-level static) into a constant area mixer section with a centrally located gaseous oxygen (GO2)/gaseous hydrogen (GH2) rocket combustor. The downstream flowpath for this configuration includes a diffuser, an afterburner and a final converging nozzle. For the SMC configuration, the rocket is centrally located in a slightly divergent duct. For all tested configurations, global measurements of the axial pressure and heat transfer profiles as well as the overall engine thrust were made. Detailed measurements include major species concentration (H2 O2 N2 and H2O) profiles at various mixer locations made using Raman spectroscopy. Complementary CFD calculations of the flowfield at the experimental conditions also provide additional information on the physics of the problem. These calculations

  15. Two-stage combustion of coal in a pressurized fluidized bed combustor for use in gas turbine processes; Zweistufige Verbrennung von Kohlen in einer Druckwirbelschichtanlage fuer den Einsatz in Gasturbinenprozessen

    Energy Technology Data Exchange (ETDEWEB)

    Mieden, M.; Bonn, B.; Baumann, H.

    1996-12-31

    The power raising efficiencies of PFBC-processes depend on the temperature of the flue-gas at the entrance of gas-turbines. In order to rise efficiencies, hybrid combined cycles have been suggested in which the gas temperature increased e.g. by firing natural gas in an afterburner at the entrance of the turbine. Alternatively a fuel gas can be produced by gasifying coal in a carboniser or gasifier. This fuel gas can be used to heat up the flue gas of the PFBC to a temperature that ensures an optimum gas-turbine efficiency. A process has been examined at DMT that provides a fuel gas with high CO concentration by substoichiometric combustion of coal in a PFBC. In order to increase the gas temperature the fuel gas is mixed with oxygen in an afterburner and then burns spontaneously. The experiments showed that it was possible to reach a temperature of about 1300 C in the afterburner. As the laboratory scale PFBC plant is provided with flue gas recirculation, equilibrium calculations have been made to examine the feasibility of the process for operation with air. (orig.) [Deutsch] Fuer die Erhoehung des Wirkungsgrades von druckwirbelschichtgefeuerten Kombiprozessen durch die Temperaturerhoehung im Eingang der Gasturbine wurde ein neuartiges Verfahren mit extrem gestufter Verbrennung der Kohle untersucht. Durch unterstoechiometrische Verbrennung von Kohle in einem Druckwirbelschichtreaktor (p=5 bar; T=900 C) wird zunaechst ein stark CO-haltiges Gas erzeugt, das nach der Entstaubung durch Vermischung mit Sauerstoff in einer zweiten Stufe, die als Nachbrennkammer diente, ausgebrannt wurde. Dabei erhoehte sich die Temperatur des Rauchgases, und es wurden Temperaturen von ueber 1300 C erreicht. Bei Sauerstoffzahlen von minimal {lambda}=0,75 betrugen die CO-Konzentrationen des Schwachgases der ersten Stufe bis zu 14%. Der Sauerstoffmangel fuehrte dazu, dass auch unverbrannter Kohlenstoff aus der Druckwirbelschicht ausgetragen wurde und in die Nachbrennkammer gelangte. Bei den

  16. Development of treatment process by pyrolysis of low level radioactive spent ion exchange resin

    Energy Technology Data Exchange (ETDEWEB)

    Nagahara, Satoshi; Kidoguchi, Akira; Ushikoshi, Juntaro; Kanda, Nobuyasu [Mitsui Shipbuilding and Engineering Co. Ltd., Tokyo (Japan)

    2001-03-01

    Mitsui Engineering and Shipbuilding Co., Ltd. has been successfully developing a continuous treatment process by pyrolysis under reduction condition for low level radioactive ion-exchange resin used in nuclear power plants, for the purpose of reducing its volume with excellent decontamination performance. Pyrolysis experiments with labo-scale and bench-scale test equipments were carried out, followed by the continuous pyrolysis treatment test in the full-scale test equipment with feed rate at 7 liter/hour which was composed of a rotary kiln pyrolysis drum and an after-burner. Results showed an excellent performance of pyrolysis for the treatment of the spent resin. The properties of cement immobilization of residue sufficiently meet the governmental regulations, and we are confident that the continuous treatment process of the disposal for the low level radioactive ion-exchange resin used in nuclear power plants is established. (author)

  17. Direct photons at FAIR

    Energy Technology Data Exchange (ETDEWEB)

    Baeuchle, Bjoern [Frankfurt Institute for Advanced Studies (FIAS), Ruth-Moufang-Str. 1, D-60438 Frankfurt am Main (Germany); Bleicher, Marcus; Grimm, Andreas [Frankfurt Institute for Advanced Studies (FIAS), Ruth-Moufang-Str. 1, D-60438 Frankfurt am Main (Germany); Frankfurt Univ. (Germany). Inst. fuer Theoretische Physik

    2013-07-01

    Photons, as all electromagnetic probes, can give direct access to the hot and dense phase of a heavy-ion reaction. We show calculations of direct photon emission at SiS100- and SiS-300 energies with the UrQMD-hybrid model. UrQMD is a full microscopic+macroscopic transport/fluid-dynamics hybrid model with hadron- and string-driven equilibration phase, a full (3+1)-dimensional fluiddynamic hot and dense phase and a hadronic after-burner. Unequilibrated matter at high rapidity is preserved during the fluid phase. A strong emphasis is set on the impact of viscosity and Equation of State at zero and non-zero baryon density to the spectra and flow patterns of thermal and non-thermal photons in A+A-collisions at the colliding systems relevant for FAIR.

  18. Generation of heavy ion beams using high-intensity short pulse lasers

    Science.gov (United States)

    Petrov, George; McGuffey, Chris; Thomas, Alec; Krushelnick, Karl; Beg, Farhat

    2016-10-01

    A theoretical study of ion acceleration from high-Z material irradiated by intense sub-picosecond lasers is presented. The underlying physics of beam formation and acceleration is similar for light and heavy ions, however, nuances of the acceleration process make the heavy ions more challenging. At least four technical hurdles have been identified: low charge-to-mass ratio, limited number of ions amenable to acceleration, delayed acceleration and poor energy coupling due to high reflectivity of the plasma. Using two dimensional particle-in-cell (PIC) simulations, we observed transitions from Radiation Pressure Acceleration (RPA) to the Breakout Afterburner regime (BoA) and to Target Normal Sheath Acceleration (TNSA) akin to light ions. The numerical simulations predict gold ions beams with high directionality (high fluxes (>1011 ions/sr) and energy (>10 MeV/nucleon) from laser systems delivering >20 J of energy on target.

  19. Circular polarization opportunities at the SASE3 undulator line of the European XFEL

    CERN Document Server

    Serkez, Svitozar; Kocharyan, Vitali; Saldin, Evgeni

    2016-01-01

    XFELs provide X-ray pulses with unprecedented peak brightness and ultrashort duration. They are usually driven by planar undulators, meaning that the output radiation is linearly polarized. For many experimental applications, however, polarization control is critical: besides the ability to produce linearly polarized radiation, one often needs the possibility of generating circularly polarized radiation with a high, stable degree of polarization. This may be achieved by using a first part of the XFEL undulator to produce bunching and then, by propagating the the bunched beam through an "afterburner" - a short undulator with tunable polarization, where only limited gain takes place. One of the issues that one needs to consider in this case is the separation of the circularly polarized radiation obtained in the radiator from the linearly polarized background produced in the first part of the FEL. In this article we review several methods to do so, including the inverse tapering technique. In particular, we use ...

  20. Process for production of wood charcoal from fine-particle lignocellulose wastes and installation for its accomplishment

    Energy Technology Data Exchange (ETDEWEB)

    Babicki, R.; Perzynski, B.

    1979-05-15

    For producing wood charcoal from sawdust, shells of nuts, and other lignin-containing wastes by drying, roasting, and cooling the obtainable carbon, a multizone kiln is used, consisting of zones for drying (DZ), low-temperature carbonization (SCZ), and cooling (CZ), each of which is divided by racks into two parts. Between the zones racks having openings for feedstock charging are also arranged. In the SCZ, air nozzles are mounted, above which there is a ceramic screen. Waste gases from the SCZ and CZ pass through the heat exchanger-afterburner and are admitted into the condenser, whence they are released into the atmosphere. The temperature in the DZ is 120-60/sup 0/, and in the SCZ -- 400-600/sup 0/.

  1. FDNS CFD Code Benchmark for RBCC Ejector Mode Operation: Continuing Toward Dual Rocket Effects

    Science.gov (United States)

    West, Jeff; Ruf, Joseph H.; Turner, James E. (Technical Monitor)

    2000-01-01

    Computational Fluid Dynamics (CFD) analysis results are compared with benchmark quality test data from the Propulsion Engineering Research Center's (PERC) Rocket Based Combined Cycle (RBCC) experiments to verify fluid dynamic code and application procedures. RBCC engine flowpath development will rely on CFD applications to capture the multi -dimensional fluid dynamic interactions and to quantify their effect on the RBCC system performance. Therefore, the accuracy of these CFD codes must be determined through detailed comparisons with test data. The PERC experiments build upon the well-known 1968 rocket-ejector experiments of Odegaard and Stroup by employing advanced optical and laser based diagnostics to evaluate mixing and secondary combustion. The Finite Difference Navier Stokes (FDNS) code [2] was used to model the fluid dynamics of the PERC RBCC ejector mode configuration. Analyses were performed for the Diffusion and Afterburning (DAB) test conditions at the 200-psia thruster operation point, Results with and without downstream fuel injection are presented.

  2. FDNS CFD Code Benchmark for RBCC Ejector Mode Operation

    Science.gov (United States)

    Holt, James B.; Ruf, Joe

    1999-01-01

    Computational Fluid Dynamics (CFD) analysis results are compared with benchmark quality test data from the Propulsion Engineering Research Center's (PERC) Rocket Based Combined Cycle (RBCC) experiments to verify fluid dynamic code and application procedures. RBCC engine flowpath development will rely on CFD applications to capture the multi-dimensional fluid dynamic interactions and to quantify their effect on the RBCC system performance. Therefore, the accuracy of these CFD codes must be determined through detailed comparisons with test data. The PERC experiments build upon the well-known 1968 rocket-ejector experiments of Odegaard and Stroup by employing advanced optical and laser based diagnostics to evaluate mixing and secondary combustion. The Finite Difference Navier Stokes (FDNS) code was used to model the fluid dynamics of the PERC RBCC ejector mode configuration. Analyses were performed for both Diffusion and Afterburning (DAB) and Simultaneous Mixing and Combustion (SMC) test conditions. Results from both the 2D and the 3D models are presented.

  3. Benchmark of FDNS CFD Code For Direct Connect RBCC Test Data

    Science.gov (United States)

    Ruf, J. H.

    2000-01-01

    Computational Fluid Dynamics (CFD) analysis results are compared with experimental data from the Pennsylvania State University's (PSU) Propulsion Engineering Research Center (PERC) rocket based combined cycle (RBCC) rocket-ejector experiments. The PERC RBCC experimental hardware was in a direct-connect configuration in diffusion and afterburning (DAB) operation. The objective of the present work was to validate the Finite Difference Navier Stokes (FDNS) CFD code for the rocket-ejector mode internal fluid mechanics and combustion phenomena. A second objective was determine the best application procedures to use FDNS as a predictive/engineering tool. Three-dimensional CFD analysis was performed. Solution methodology and grid requirements are discussed. CFD results are compared to experimental data for static pressure, Raman Spectroscopy species distribution data and RBCC net thrust and specified impulse.

  4. Recycling of metal bearing electronic scrap in a plasma furnace

    Science.gov (United States)

    Jarosz, Piotr; Małecki, Stanisław; Gargul, Krzysztof

    2011-12-01

    The recycling of electronic waste and the recovery of valuable components are large problems in the modern world economy. This paper presents the effects of melting sorted electronic scrap in a plasma furnace. Printed circuit boards, cables, and windings were processed separately. The characteristics of the obtained products (i.e., alloy metal, slag, dust, and gases) are presented. A method of their further processing in order to obtain commercial products is proposed. Because of the chemical composition and physical properties, the waste slag is environmentally inert and can be used for the production of abrasives. Process dusts containing large amounts of carbon and its compounds have a high calorific value. That makes it possible to use them for energy generation. The gas has a high calorific value, and its afterburning combined with energy recovery is necessary.

  5. Further Improvement and System Integration of High Temperature Polymer Electrolyte Membrane Fuel Cells

    DEFF Research Database (Denmark)

    Li, Qingfeng; Jensen, Jens Oluf

    The strategic developments of the FURIM are in three steps: (1) further improvement of the high temperature polymer membranes and related materials; (2) development of technological units including fuel cell stack, hydrocarbon reformer and afterburner, that are compatible with the HT-PEMFC; and (3......) integration of the HT-PEMFC stack with these compatible subunits. The main goal of the project is a 2kWel HT-PEMFC stack operating in a temperature range of 150-200°C, with a single cell performance target of 0.7 A/cm² at a cell voltage around 0.6 V. The target durability is more than 5,000 hours...

  6. Industrial burners with compact burner management system on industrial applications; Industriebrenner mit kompaktem Brenner-Management-System in verschiedenen industriellen Anwendungen

    Energy Technology Data Exchange (ETDEWEB)

    Saenger, P.; Bloess, H. [CRONE Waermetechnik GmbH (Germany)

    2008-07-15

    Industrial burners are the heart of every thermal process-based production line. The quality of the final product depends largely on the burner's reliability and performance. Small maintenance effort and maximum availability, high energy efficiency and seamless integration into existing automation systems are the key requirements placed on advanced industrial firing systems. Whether thermal after-burning, drying or assisted firing, the scope of industrial applications demands an extensive range of solutions. Depending on individual requirements, the LMV family of burner management systems from Siemens Building Technologies (SBT) offers complete high-end solutions for the control of thermal process-based production lines reaching from metalworking to the production of glass wool, ceramics or automobiles, textiles, paper, plastics and rubber. This paper describes various burner management systems that are used on a number of different applications. (orig.)

  7. Hollow screw like drill in plasma using an intense Laguerre Gaussian laser

    CERN Document Server

    Wang, Wenpeng; Zhang, Xiaomei; Zhang, Lingang; Shi, Yin; Xu, Zhizhan

    2014-01-01

    With the development of ultra intense laser technology, MeV ions from the laser foil interaction have been obtained by different mechanisms, such as target normal sheath acceleration, radiation pressure acceleration, collisionless shock acceleration, breakout afterburner, and a combination of different mechanisms. These energetic ion beams can be applied in fast ignition for inertial confinement fusion, medical therapy, and proton imaging. However, these ions are mainly accelerated in the laser propagation direction, and the ion acceleration in an azimuthal orientation is scarcely mentioned. Here, a doughnut Laguerre Gaussian LG laser is used for the first time to study the laser plasma interaction in the relativistic intensity regime in three dimensional particle in cell simulations. Studies have shown that a novel rotation of the plasma is produced from the hollow screw like drill of a LG mode laser. The angular momentum of the protons in the longitudinal direction produced by the LG laser is remarkably enh...

  8. Design and development of major balance of plant components in solid oxide fuel cell system

    Energy Technology Data Exchange (ETDEWEB)

    Hong, Wen-Tang; Huang, Cheng-Nan; Tan, Hsueh-I; Chao, Yu [Institute of Nuclear Energy Research Atomic Energy Council, Taoyuan County 32546 (Taiwan, Province of China); Yen, Tzu-Hsiang [Green Technology Research Institute, CPC Corporation, Chia-Yi City 60036 (Taiwan, Province of China)

    2013-07-01

    The balance of plant (BOP) of a Solid Oxide Fuel Cell (SOFC) system with a 2 kW stack and an electric efficiency of 40% is optimized using commercial GCTool software. The simulation results provide a detailed understanding of the optimal operating temperature, pressure and mass flow rate in all of the major BOP components, i.e., the gas distributor, the afterburner, the reformer and the heat exchanger. A series of experimental trials are performed to validate the simulation results. Overall, the results presented in this study not only indicate an appropriate set of operating conditions for the SOFC power system, but also suggest potential design improvements for several of the BOP components.

  9. Polycyclic aromatic hydrocarbon and particulate emissions from two-stage combustion of polystyrene: the effect of the primary furnace temperature.

    Science.gov (United States)

    Wang, J; Levendis, Y A; Richter, H; Howard, J B; Carlson, J

    2001-09-01

    A study is presented on laboratory-scale combustion of polystyrene (PS) to identify staged-combustion conditions that minimize emissions. Batch combustion of shredded PS was conducted in fixed beds placed in a bench-scale electrically heated horizontal muffle furnace. In most cases, combustion of the samples occurred by forming gaseous diffusion flames in atmospheric pressure air. The combustion effluent was mixed with additional air, and it was channeled to a second muffle furnace (afterburner) placed in series. Further reactions took place in the secondary furnace at a residence time of 0.7 s. The gas temperature of the primary furnace was varied in the range of 500-1,000 degrees C, while that of the secondary furnace was kept fixed at 1,000 degrees C. Sampling for CO, CO2, O2, soot, and unburned hydrocarbon emissions (volatile and semivolatile, by GC-MS) was performed at the exits of the two furnaces. Results showed that the temperature of the primary furnace, where PS gasifies, is of paramount importance to the formation and subsequent emissions of organic species and soot. Atthe lowesttemperatures explored, mostly styrene oligomers were identified at the outlet of the primary furnace, but they did not survive the treatment in the secondary furnace. The formation and emission of polycyclic aromatic hydrocarbons (PAH) and soot were suppressed. As the temperature in the first furnace was raised, increasing amounts of a wide range of both unsubstituted and substituted PAH containing up to at least seven condensed aromatic rings were detected. A similar trend was observed for total particulate yields. The secondary furnace treatment reduced the yields of total PAH, but it had an ambiguous effect on individual species. While most low molecular mass PAH were reduced in the secondary furnace, concentrations of some larger PAH increased under certain conditions. Thus, care in the selection of operating conditions of both the primary furnace (gasifier/ burner) and the

  10. Analysis of the turbojet engine for propulsion of supersonic fighter airplanes / David S. Gabriel, Richard P. Krebs, E.Clinton Wilcox, Stanley L.Koutz

    Science.gov (United States)

    Gabriel, David S; Krebs, Richard P; Wilcox, E Clinton; Koutz, Stanley L

    1953-01-01

    An analytical investigation was made of two supersonic interceptor type airplanes to determine the most desirable turbojet engine characteristics for this application The airplanes were designed differently primarily because of the amount of subsonic flight incorporated in the flight plan--one flight having none and the other, a cruise radius of 400 nautical miles. Several power plant design variables were varied independently to determine the effect of changes in each parameter on airplane performance. These parameters included compressor pressure ratio, compressor efficiency, turbine-inlet temperature, afterburner temperature, engine specific weight, and air-handling capacity. The effects of using a convergent-divergent exhaust nozzle and of changing the design flight Mach number were also investigated.

  11. Flight testing the Digital Electronic Engine Control (DEEC) A unique management experience

    Science.gov (United States)

    Putnam, T. W.; Burcham, F. W., Jr.; Kock, B. M.

    1983-01-01

    The concept for the DEEC had its origin in the early 1970s. At that time it was recognized that the F100 engine performance, operability, reliability, and cost could be substantially improved by replacing the original mechanical/supervisory electronic control system with a full-authority digital control system. By 1978, the engine manufacturer had designed and initiated the procurement of flight-qualified control system hardware. As a precursor to an integrated controls program, a flight evaluation of the DEEC system on the F-15 aircraft was proposed. Questions regarding the management of the DEEC flight evaluation program are discussed along with the program elements, the technical results of the F-15 evaluation, and the impact of the flight evaluation on after-burning turbofan controls technology and its use in and application to military aircraft. The lessons learned through the conduct of the program are discussed.

  12. High-Flux Femtosecond X-Ray Emission from Controlled Generation of Annular Electron Beams in a Laser Wakefield Accelerator.

    Science.gov (United States)

    Zhao, T Z; Behm, K; Dong, C F; Davoine, X; Kalmykov, S Y; Petrov, V; Chvykov, V; Cummings, P; Hou, B; Maksimchuk, A; Nees, J A; Yanovsky, V; Thomas, A G R; Krushelnick, K

    2016-08-26

    Annular quasimonoenergetic electron beams with a mean energy in the range 200-400 MeV and charge on the order of several picocoulombs were generated in a laser wakefield accelerator and subsequently accelerated using a plasma afterburner in a two-stage gas cell. Generation of these beams is associated with injection occurring on the density down ramp between the stages. This well-localized injection produces a bunch of electrons performing coherent betatron oscillations in the wakefield, resulting in a significant increase in the x-ray yield. Annular electron distributions are detected in 40% of shots under optimal conditions. Simultaneous control of the pulse duration and frequency chirp enables optimization of both the energy and the energy spread of the annular beam and boosts the radiant energy per unit charge by almost an order of magnitude. These well-defined annular distributions of electrons are a promising source of high-brightness laser plasma-based x rays.

  13. Auxiliary power unit based on a solid oxide fuel cell and fuelled with diesel

    Science.gov (United States)

    Lawrence, Jeremy; Boltze, Matthias

    An auxiliary power unit (APU) is presented that is fuelled with diesel, thermally self-sustaining, and based on a solid oxide fuel cell (SOFC). The APU is rated at 1 kW electrical, and can generate electrical power after a 3 h warm-up phase. System features include a "dry" catalytic partial oxidation (CPOX) diesel reformer, a 30 cell SOFC stack with an open cathode, and a porous-media afterburner. The APU does not require a supply of external water. The SOFC stack is an outcome of a development partnership with H.C. Starck GmbH and Fraunhofer IKTS, and is discussed in detail in an accompanying paper.

  14. 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.

  15. An Electron Bunch Compression Scheme for a Superconducting Radio Frequency Linear Accelerator Driven Light Source

    Energy Technology Data Exchange (ETDEWEB)

    C. Tennant, S.V. Benson, D. Douglas, P. Evtushenko, R.A. Legg

    2011-09-01

    We describe an electron bunch compression scheme suitable for use in a light source driven by a superconducting radio frequency (SRF) linac. The key feature is the use of a recirculating linac to perform the initial bunch compression. Phasing of the second pass beam through the linac is chosen to de-chirp the electron bunch prior to acceleration to the final energy in an SRF linac ('afterburner'). The final bunch compression is then done at maximum energy. This scheme has the potential to circumvent some of the most technically challenging aspects of current longitudinal matches; namely transporting a fully compressed, high peak current electron bunch through an extended SRF environment, the need for a RF harmonic linearizer and the need for a laser heater. Additional benefits include a substantial savings in capital and operational costs by efficiently using the available SRF gradient.

  16. Dioxins, furans and polycyclic aromatic hydrocarbons emissions from a hospital and cemetery waste incinerator

    Science.gov (United States)

    Mininni, Giuseppe; Sbrilli, Andrea; Maria Braguglia, Camilla; Guerriero, Ettore; Marani, Dario; Rotatori, Mauro

    An experimental campaign was carried out on a hospital and cemetery waste incineration plant in order to assess the emissions of polychlorinated dibenzo-p-dioxins (PCDDs), polychlorinated dibenzofurans (PCDFs) and polycyclic aromatic hydrocarbons (PAHs). Raw gases were sampled in the afterburning chamber, using a specifically designed device, after the heat recovery section and at the stack. Samples of slags from the combustion chamber and fly ashes from the bag filter were also collected and analyzed. PCDD/Fs and PAHs concentrations in exhaust gas after the heat exchanger (200-350 °C) decreased in comparison with the values detected in the afterburning chamber. Pollutant mass balance regarding the heat exchanger did not confirm literature findings about the de novo synthesis of PCDD/Fs in the heat exchange process. In spite of a consistent reduction of PCDD/Fs in the flue gas treatment system (from 77% up to 98%), the limit of 0.1 ng ITEQ Nm -3 at the stack was not accomplished. PCDD/Fs emission factors for air spanned from 2.3 up to 44 μg ITEQ t -1 of burned waste, whereas those through solid residues (mainly fly ashes) were in the range 41-3700 μg ITEQ t -1. Tests run with cemetery wastes generally showed lower PCDD/F emission factors than those with hospital wastes. PAH total emission factors (91-414 μg kg -1 of burned waste) were in the range of values reported for incineration of municipal and industrial wastes. In spite of the observed release from the scrubber, carcinogenic PAHs concentrations at the stack (0.018-0.5 μg Nm -3) were below the Italian limit of 10 μg Nm -3.

  17. Theoretical and experimental studies on emissions from wood combustion

    Energy Technology Data Exchange (ETDEWEB)

    Skreiberg, Oeyvind

    1997-12-31

    This thesis discusses experiments on emissions from wood log combustion and single wood particle combustion, both caused by incomplete combustion and emissions of nitric and nitrous oxide, together with empirical and kinetic NO{sub x} modelling. Experiments were performed in three different wood stoves: a traditional stove, a staged air stove and a stove equipped with a catalytic afterburner. Ideally, biomass fuel does not give a net contribution to the greenhouse effect. However, incomplete combustion was found to result in significant greenhouse gas emissions. Empirical modelling showed the excess air ratio and the combustion chamber temperature to be the most important input variables controlling the total fuel-N to NO{sub x} conversion factor. As the result of an international round robin test of a wood stove equipped with a catalytic afterburner, particle emission measurements were found to be the best method to evaluate the environmental acceptability of the tested stove, since the particle emission level was least dependent of the national standards, test procedures and calculation procedures used. In batch single wood particle combustion experiments on an electrically heated small-scale fixed bed reactor the fuel-N to NO conversion factor varied between 0.11-0.86 depending on wood species and operating conditions. A parameter study and homogeneous kinetic modelling on a plug flow reactor showed that, depending on the combustion compliance in question, there is an optimum combination of primary excess air ratio, temperature and residence time that gives a maximum conversion of fuel-N to N{sub 2}. 70 refs., 100 figs., 26 tabs.

  18. Computational Analyses in Support of Sub-scale Diffuser Testing for the A-3 Facility. Part 2; Unsteady Analyses and Risk Assessment

    Science.gov (United States)

    Ahuja, Vineet; Hosangadi, Ashvin; Allgood, Daniel

    2008-01-01

    Simulation technology can play an important role in rocket engine test facility design and development by assessing risks, providing analysis of dynamic pressure and thermal loads, identifying failure modes and predicting anomalous behavior of critical systems. This is especially true for facilities such as the proposed A-3 facility at NASA SSC because of a challenging operating envelope linked to variable throttle conditions at relatively low chamber pressures. Design Support of the feasibility of operating conditions and procedures is critical in such cases due to the possibility of startup/shutdown transients, moving shock structures, unsteady shock-boundary layer interactions and engine and diffuser unstart modes that can result in catastrophic failure. Analyses of such systems is difficult due to resolution requirements needed to accurately capture moving shock structures, shock-boundary layer interactions, two-phase flow regimes and engine unstart modes. In a companion paper, we will demonstrate with the use of CFD, steady analyses advanced capability to evaluate supersonic diffuser and steam ejector performance in the sub-scale A-3 facility. In this paper we will address transient issues with the operation of the facility especially at startup and shutdown, and assess risks related to afterburning due to the interaction of a fuel rich plume with oxygen that is a by-product of the steam ejectors. The primary areas that will be addressed in this paper are: (1) analyses of unstart modes due to flow transients especially during startup/ignition, (2) engine safety during the shutdown process (3) interaction of steam ejectors with the primary plume i.e. flow transients as well as probability of afterburning. In this abstract we discuss unsteady analyses of the engine shutdown process. However, the final paper will include analyses of a staged startup, drawdown of the engine test cell pressure, and risk assessment of potential afterburning in the facility. Unsteady

  19. A revolutionary lunar space transportation system architecture using extraterrestrial LOX-augmented NTR propulsion

    Science.gov (United States)

    Borowski, Stanley K.; Corban, Robert R.; Culver, Donald W.; Bulman, Melvin J.; McIlwain, Mel C.

    1994-08-01

    The concept of a liquid oxygen (LOX)-augmented nuclear thermal rocket (NTR) engine is introduced, and its potential for revolutionizing lunar space transportation system (LTS) performance using extraterrestrial 'lunar-derived' liquid oxygen (LUNOX) is outlined. The LOX-augmented NTR (LANTR) represents the marriage of conventional liquid hydrogen (LH2)-cooled NTR and airbreathing engine technologies. The large divergent section of the NTR nozzle functions as an 'afterburner' into which oxygen is injected and supersonically combusted with nuclear preheated hydrogen emerging from the NTR's choked sonic throat: 'scramjet propulsion in reverse.' By varying the oxygen-to-fuel mixture ratio (MR), the LANTR concept can provide variable thrust and specific impulse (Isp) capability with a LH2-cooled NTR operating at relatively constant power output. For example, at a MR = 3, the thrust per engine can be increased by a factor of 2.75 while the Isp decreases by only 30 percent. With this thrust augmentation option, smaller, 'easier to develop' NTR's become more acceptable from a mission performance standpoint (e.g., earth escape gravity losses are reduced and perigee propulsion requirements are eliminated). Hydrogen mass and volume is also reduced resulting in smaller space vehicles. An evolutionary NTR-based lunar architecture requiring only Shuttle C and/or 'in-line' shuttle-derived launch vehicles (SDV's) would operate initially in an 'expandable mode' with NTR lunar transfer vehicles (LTV's) delivering 80 percent more payload on piloted missions than their LOX/LH2 chemical propulsion counterparts. With the establishment of LUNOX production facilities on the lunar surface and 'fuel/oxidizer' depot in low lunar orbit (LLO), monopropellant NTR's would be outfitted with an oxygen propellant module, feed system, and afterburner nozzle for 'bipropellant' operation. The LANTR cislunar LTV now transitions to a reusable mode with smaller vehicle and payload doubling benefits on

  20. Effect of LiF Coating on the Thermal Oxidation Characteristics for Boron Powder%LiF包覆对硼粉热氧化特性的影响

    Institute of Scientific and Technical Information of China (English)

    陈涛; 张先瑞; 王园园; 黄凌; 肖金武

    2013-01-01

    In order to investigate the effect of LiF coating on the thermal oxidation characteristics for amorphous boron powder,the thermal analysis experiment of boron coated with LiF (BLiF) was conducted by DSC-TC. Propellant samples containing BLif were prepared. The heat of detonation and heat of combustion were determined by an oxygen bomb calorimeter. The effects of BLif on the energy release features in primary combustion and after-burning processes of the propellant were discussed. The results indicate that in comparison with amorphous boron, BLiF shows a fast oxidation reaction at 599 XL ,and a 39. 9% higher percentage of boron participated in B/O reaction. The propellant containing BLiF makes primary combustion and after-burning energy release efficiencies (ηc1 and ηc2) increased and combustion efficiencies of B enhanced significantly from 65.48% to 81 .57%. This is due to the consumption of B2O3 layer on the boron particle surface via endothermic reaction of LiF and B2O3 at high temperature and the acceleration of B/O reaction.%为考察LiF包覆对硼粉热氧化特性的影响,采用DSC-TG技术对LiF包覆硼(BLiF)进行热分析试验.制备了含BLiF的推进剂样品.采用氧弹量热计测试其爆热和热值.考察了BLiF对推进剂一次、二次燃烧过程中能量释放特性的影响.结果表明:与无定形硼相比,BLiF在599℃存在快速氧化反应,有39.9%(质量百分数)的B参与了B/O反应.含BLiF的推进剂使一次能量释放效率和二次能量释放效率明显提高,硼的燃烧效率从65.48%提高到81.57%.这是由高温下LiF通过吸热反应消耗硼粉表面B2O3氧化层,加速B/O反应所引起的.

  1. The QCD Phase Diagram, Equation of State, and Heavy Ion Collisions

    CERN Document Server

    Shuryak, E V

    2002-01-01

    After some historic remarks and a brief summary of recent theoretical news about the QCD phases, we turn to the issue of $freeze-out$ in heavy ion collisions. We argue that the chemical freeze-out line should actually consists of two crossing lines of different nature. We also consider some inelatic reactions which occure $after$ chemical freeze-out, emphasizing the role of overpopulation of pions. The $hydrodynamics$ (with or without hadronic afterburner) explaines SPS/RHIC data on radial and elliptic flow in unexpected details,for different particles, collision energies, and impact parameters. Apart of Equation of State (EoS), it has basically no free parameters. The EoS which describe these data best agrees quite well with the lattice predictions, with the QGP latent heat $\\Delta\\epsilon\\approx 800 Mev/fm^3$. Other phenomena at RHIC, such as ``jet quenching'' and huge ellipticity at large $p_t$, also point toward very rapid entropy production. Its mechanism remains an outstanding open problem: at the end w...

  2. Proton and Ion Acceleration on the Contrast Upgraded Texas Petawatt Laser

    Science.gov (United States)

    McCary, Edward; Roycroft, Rebecca; Jiao, Xuejing; Kupfer, Rotem; Tiwari, Ganesh; Wagner, Craig; Yandow, Andrew; Franke, Philip; Dyer, Gilliss; Gaul, Erhard; Toncian, Toma; Ditmire, Todd; Hegelich, Bjorn; CenterHigh Energy Density Science Team

    2016-10-01

    Recent upgrades to the Texas Petawatt (TPW) laser system have eliminated pre-pulses and reduced the laser pedestal, resulting in improved laser contrast. Previously unwanted pre-pulses and amplified spontaneous emission (ASE) would ionize targets thinner than 1 micron, leaving an under-dense plasma which was not capable of accelerating ions to high energies. After the upgrade the contrast was drastically improved allowing us to successfully shoot targets as thin as 20 nm without plasma mirrors. We have also observed evidence of relativistic transparency and Break-Out Afterburner (BOA) ion acceleration when shooting ultra-thin, nanometer scale targets. Data taken with a wide angle ion spectrometer (IWASP) showed the characteristic asymmetry of BOA in the plane orthogonal to the laser polarization on thin targets but not on micron scale targets. Thick micron scale targets saw improvement as well; shots on 2 μm thick gold targets saw ions with energies up to 100 MeV, which broke the former record proton energy on the TPW. Switching the focusing optic from an f/3 parabolic mirror to an f/40 spherical mirror showed improvement in the number of low energy protons created, and provided a source for hundreds of picosecond heating of aluminum foils for warm dense matter measurements.

  3. Infrared radiation signature of exhaust plume from solid propellants with different energy characteristics

    Institute of Scientific and Technical Information of China (English)

    Wang Weichen; Li Shipeng; Zhang Qiao; Wang Ningfei

    2013-01-01

    The infrared radiation signature of the plume from solid propellants with different energy characteristics is not the same.Three kinds of double-base propellants of different energy characteristics are chosen to measure the infrared spectral radiance from 1000cm-1 to 4500 cm-1 of their plumes.The radiative spectrum is obtained in the tests.The experimental results indicate that the infrared radiation of the plume is determined by the energy characteristics of the propellant.The radiative transfer calculation models of the exhaust plume for the solid propellants are established.By including the chemical reaction source term and the radiation source term into the energy equation,the plume field and the radiative transfer are solved in a coupled way.The calculated results are consistent with the experimental data,so the reliability of the models is confirmed.The temperature distribution and the extent of the afterburning of the plume are distinct for the propellants of different energy characteristics,therefore the plume radiation varies for different propellants.The temperature of the fluid cell in the plume will increase or decrease to some extent by the influence of the radiation term.

  4. Control of laser absorbing efficiency and proton quality by a specific double target

    Science.gov (United States)

    Yu, Q.; Gu, Y. J.; Li, X. F.; Qu, J. F.; Kong, Q.; Kawata, S.

    2016-08-01

    The micro-structured double-layer target is an efficient method to improve proton quality. However, the laser absorption efficiency is low due to strong reflection at the front surface of such targets. Moreover, the proton charge is limited by the driving laser radius. To overcome these shortcomings, a specific double-layer (SDL) target with a vacuum gap in the center of the heavy ion layer is proposed in this paper. In this specified target, the laser reflection effect is significantly weakened and the absorption and penetration efficiencies are greatly enhanced. The high-energy electrons from Breakout afterburner regime efficiently transfer their energy to the protons. Both the energy of the spectral peaks and maximum proton energy are greatly increased. The periodic structure of the longitudinal electric field makes the force applied on the protons becomes homogeneous in time average and therefore reduce the energy spread. In these SDL targets, the proton layer radius and the accelerated proton charge are not limited by the laser radius. With a larger-radius proton layer, the protons can be accelerated to high energy with small energy spread. When the proton layer radius is reduced to the laser radius, the SDL target is still an effective structure to improve the proton quality. The mechanism is proved by a series of particle-in-cell simulations.

  5. Analysis of Flowfields over Four-Engine DC-X Rockets

    Science.gov (United States)

    Wang, Ten-See; Cornelison, Joni

    1996-01-01

    The objective of this study is to validate a computational methodology for the aerodynamic performance of an advanced conical launch vehicle configuration. The computational methodology is based on a three-dimensional, viscous flow, pressure-based computational fluid dynamics formulation. Both wind-tunnel and ascent flight-test data are used for validation. Emphasis is placed on multiple-engine power-on effects. Computational characterization of the base drag in the critical subsonic regime is the focus of the validation effort; until recently, almost no multiple-engine data existed for a conical launch vehicle configuration. Parametric studies using high-order difference schemes are performed for the cold-flow tests, whereas grid studies are conducted for the flight tests. The computed vehicle axial force coefficients, forebody, aftbody, and base surface pressures compare favorably with those of tests. The results demonstrate that with adequate grid density and proper distribution, a high-order difference scheme, finite rate afterburning kinetics to model the plume chemistry, and a suitable turbulence model to describe separated flows, plume/air mixing, and boundary layers, computational fluid dynamics is a tool that can be used to predict the low-speed aerodynamic performance for rocket design and operations.

  6. Auxiliary lift propulsion system with oversized front fan

    Energy Technology Data Exchange (ETDEWEB)

    Castells, O.T.; Johnson, J.E.; Rundell, D.J.

    1980-09-16

    A propulsion system for use primarily in V/STOL aircraft is provided with a variable cycle, double bypass gas turbofan engine and a remote augmenter to produce auxiliary lift. The fan is oversized in air-pumping capability with respect to the cruise flight requirements of the remainder of the engine and a variable area, low pressure turbine is capable of supplying varying amounts of rotational energy to the oversized fan, thereby modulating its speed and pumping capability. During powered lift flight, the variable cycle engine is operated in the single bypass mode with the oversized fan at its maximum pumping capability. In this mode, substantially all of the bypass flow is routed as an auxiliary airstream to the remote augmenter where it is mixed with fuel, burned and exhausted through a vectorable nozzle to produce thrust for lifting. Additional lift is generated by the high energy products of combustion of the variable cycle engine which are further energized in an afterburner and exhausted through a thrust vectorable nozzle at the rear of the engine.

  7. Static investigation of two STOL nozzle concepts with pitch thrust-vectoring capability

    Science.gov (United States)

    Mason, M. L.; Burley, J. R., II

    1986-01-01

    A static investigation of the internal performance of two short take-off and landing (STOL) nozzle concepts with pitch thrust-vectoring capability has been conducted. An axisymmetric nozzle concept and a nonaxisymmetric nozzle concept were tested at dry and afterburning power settings. The axisymmetric concept consisted of a circular approach duct with a convergent-divergent nozzle. Pitch thrust vectoring was accomplished by vectoring the approach duct without changing the nozzle geometry. The nonaxisymmetric concept consisted of a two dimensional convergent-divergent nozzle. Pitch thrust vectoring was implemented by blocking the nozzle exit and deflecting a door in the lower nozzle flap. The test nozzle pressure ratio was varied up to 10.0, depending on model geometry. Results indicate that both pitch vectoring concepts produced resultant pitch vector angles which were nearly equal to the geometric pitch deflection angles. The axisymmetric nozzle concept had only small thrust losses at the largest pitch deflection angle of 70 deg., but the two-dimensional convergent-divergent nozzle concept had large performance losses at both of the two pitch deflection angles tested, 60 deg. and 70 deg.

  8. Static Thrust and Vectoring Performance of a Spherical Convergent Flap Nozzle with a Nonrectangular Divergent Duct

    Science.gov (United States)

    Wing, David J.

    1998-01-01

    The static internal performance of a multiaxis-thrust-vectoring, spherical convergent flap (SCF) nozzle with a non-rectangular divergent duct was obtained in the model preparation area of the Langley 16-Foot Transonic Tunnel. Duct cross sections of hexagonal and bowtie shapes were tested. Additional geometric parameters included throat area (power setting), pitch flap deflection angle, and yaw gimbal angle. Nozzle pressure ratio was varied from 2 to 12 for dry power configurations and from 2 to 6 for afterburning power configurations. Approximately a 1-percent loss in thrust efficiency from SCF nozzles with a rectangular divergent duct was incurred as a result of internal oblique shocks in the flow field. The internal oblique shocks were the result of cross flow generated by the vee-shaped geometric throat. The hexagonal and bowtie nozzles had mirror-imaged flow fields and therefore similar thrust performance. Thrust vectoring was not hampered by the three-dimensional internal geometry of the nozzles. Flow visualization indicates pitch thrust-vector angles larger than 10' may be achievable with minimal adverse effect on or a possible gain in resultant thrust efficiency as compared with the performance at a pitch thrust-vector angle of 10 deg.

  9. Static thrust-vectoring performance of nonaxisymmetric convergent-divergent nozzles with post-exit yaw vanes. M.S. Thesis - George Washington Univ., Aug. 1988

    Science.gov (United States)

    Foley, Robert J.; Pendergraft, Odis C., Jr.

    1991-01-01

    A static (wind-off) test was conducted in the Static Test Facility of the 16-ft transonic tunnel to determine the performance and turning effectiveness of post-exit yaw vanes installed on two-dimensional convergent-divergent nozzles. One nozzle design that was previously tested was used as a baseline, simulating dry power and afterburning power nozzles at both 0 and 20 degree pitch vectoring conditions. Vanes were installed on these four nozzle configurations to study the effects of vane deflection angle, longitudinal and lateral location, size, and camber. All vanes were hinged at the nozzle sidewall exit, and in addition, some were also hinged at the vane quarter chord (double-hinged). The vane concepts tested generally produced yaw thrust vectoring angles much less than the geometric vane angles, for (up to 8 percent) resultant thrust losses. When the nozzles were pitch vectored, yawing effectiveness decreased as the vanes were moved downstream. Thrust penalties and yawing effectiveness both decreased rapidly as the vanes were moved outboard (laterally). Vane length and height changes increased yawing effectiveness and thrust ratio losses, while using vane camber, and double-hinged vanes increased resultant yaw angles by 50 to 100 percent.

  10. Effect of nozzle lateral spacing on afterbody drag and performance of twin-jet afterbody models with convergent-divergent nozzles at Mach numbers up to 2.2

    Science.gov (United States)

    Pendergraft, O. C., Jr.; Schmeer, J. W.

    1972-01-01

    Twin-jet afterbody models were investigated by using two balances to measure the thrust-minus-total drag and the afterbody drag, separately, at static conditions and at Mach numbers up to 2.2 for an angle of attack of 0 deg. Hinged-flap convergent-divergent nozzles were tested at subsonic-cruise- and maximum-afterburning-power settings with a high-pressure air system used to provide jet-total-pressure ratios up to 20. Two nozzle lateral spacings were studied, using afterbodies with similar interfairing shapes but with different longitudinal cross-sectional area distributions. Alternate, blunter, interfairings with different shapes for the two spacings, which produced afterbodies having identical cross-sectional area progressions corresponding to an axisymmetric minimum wave-drag configuration, were also tested. The results indicate that the wide-spaced configurations improved the flow field around the nozzles, thereby reducing drag on the cruise nozzles; however, the increased surface and projected cross-sectional areas caused an increase in afterbody drag. Except for a slight advantage with cruise nozzles at subsonic speeds, the wide-spaced configurations had the higher total drag at all other test conditions.

  11. Further Improvement and System Integration of High Temperature Polymer Electrolyte Membrane Fuel Cells

    DEFF Research Database (Denmark)

    Li, Qingfeng; Jensen, Jens Oluf

    The new development in the field of polymer electrolyte membrane fuel cell (PEMFC) is high temperature PEMFC for operation above 100°C, which has been successfully demonstrated through the previous EC Joule III and the 5th framework programme. New challenges are encountered, bottlenecks for the new...... of the FURIM are in three steps: (1) further improvement of the high temperature polymer membranes and related materials; (2) development of technological units including fuel cell stack, hydrocarbon reformer and afterburner, that are compatible with the HT-PEMFC; and (3) integration of the HT-PEMFC stack...... with these compatible subunits. The main goal of the project is a 2kWel HT-PEMFC stack operating in a temperature range of 150-200°C, with a single cell performance target of 0.7 A/cm² at a cell voltage around 0.6 V. The target durability is more than 5,000 hours. A hydrocarbon reformer and a catalytic burner...

  12. Further Improvement and System Integration of High Temperature Polymer Electrolyte Membrane Fuel Cells

    DEFF Research Database (Denmark)

    Jensen, Jens Oluf; Li, Qingfeng

    Polymer electrolyte membrane fuel cell (PEMFC) technology based on Nafion membranes can operate at temperatures around 80°C. The new development in the field is high temperature PEMFC for operation above 100°C, which has been successfully demonstrated through the previous EC Joule III and the 5th......, and system integration of the high temperature PEMFC. The strategic developments of the FURIM are in three steps: (1) further improvement of the high temperature polymer membranes and related materials; (2) development of technological units including fuel cell stack, hydrocarbon reformer, afterburner...... and power management system, that are compatible with the HT-PEMFC; and (3) integration of the HT-PEMFC stack with these compatible subunits. The main goal of the project is a 2kWel HT-PEMFC stack operating in a temperature range of 120-220°C, with a single cell performance target of 0.7 A/cm² at a cell...

  13. Circular polarization control for the LCLS baseline in the soft X-ray regime

    CERN Document Server

    Geloni, Gianluca; Saldin, Evgeni

    2010-01-01

    The LCLS baseline includes a planar undulator system, producing linearly polarized light in the range 0.15-1.5 nm. Polarization control in the soft X-ray region from linear to circular is highly desirable. Several schemes using helical undulators have been discussed for the LCLS. One consists in replacing three of the last planar undulator segments by APPLE III. A second proposal, the 2nd harmonic helical afterburner, uses short, crossed undulators tuned to the second harmonic. This last scheme is expected to be the better one. Its advantages are a high and stable degree of circular polarization and a low cost. Its disadvantage is a small output power and a narrow wavelength range. We propose a novel method to generate 10 GW level power at the fundamental harmonic with 99% degree of circular polarization from the LCLS baseline. Its merits are low cost, simplicity and easy implementation. After the baseline undulator, the electron beam is sent through a 40 m long straight section, and subsequently passes throu...

  14. Chemical indices and methods of multivariate statistics as a tool for odor classification.

    Science.gov (United States)

    Mahlke, Ingo T; Thiesen, Peter H; Niemeyer, Bernd

    2007-04-01

    Industrial and agricultural off-gas streams are comprised of numerous volatile compounds, many of which have substantially different odorous properties. State-of-the-art waste-gas treatment includes the characterization of these molecules and is directed at, if possible, either the avoidance of such odorants during processing or the use of existing standardized air purification techniques like bioscrubbing or afterburning, which however, often show low efficiency under ecological and economical regards. Selective odor separation from the off-gas streams could ease many of these disadvantages but is not yet widely applicable. Thus, the aim of this paper is to identify possible model substances in selective odor separation research from 155 volatile molecules mainly originating from livestock facilities, fat refineries, and cocoa and coffee production by knowledge-based methods. All compounds are examined with regard to their structure and information-content using topological and information-theoretical indices. Resulting data are fitted in an observation matrix, and similarities between the substances are computed. Principal component analysis and k-means cluster analysis are conducted showing that clustering of indices data can depict odor information correlating well to molecular composition and molecular shape. Quantitative molecule describtion along with the application of such statistical means therefore provide a good classification tool of malodorant structure properties with no thermodynamic data needed. The approximate look-alike shape of odorous compounds within the clusters suggests a fair choice of possible model molecules.

  15. Concept development of a Mach 4 high-speed civil transport

    Science.gov (United States)

    Domack, Christopher S.; Dollyhigh, Samuel M.; Beissner, Fred L., Jr.; Geiselhart, Karl A.; Mcgraw, Marvin E., Jr.; Shields, Elwood W.; Swanson, Edward E.

    1990-01-01

    A study was conducted to configure and analyze a 250 passenger, Mach 4 High Speed Civil Transport with a design range of 6500 n.mi. The design mission assumed an all-supersonic cruise segment and no community noise or sonic boom constraints. The study airplane was developed in order to examine the technology requirements for such a vehicle and to provide an unconstrained baseline from which to assess changes in technology levels, sonic boom limits, or community noise constraints in future studies. The propulsion, structure, and materials technologies utilized in the sizing of the study aircraft were assumed to represent a technology availability date of 2015. The study airplane was a derivative of a previously developed Mach 3 concept and utilized advanced afterburning turbojet engines and passive airframe thermal protection. Details of the configuration development, aerodynamic design, propulsion system, mass properties, and mission performance are presented. The study airplane was estimated to weigh approx. 866,000 lbs. Although an aircraft of this size is a marginally acceptable candidate to fit into the world airport infrastructure, it was concluded that the inclusion of community noise or sonic boom constraints would quickly cause the aircraft to grow beyond acceptable limits using the assumed technology levels.

  16. Solid Oxide Fuel Cells coupled with a biomass gasification unit

    Directory of Open Access Journals (Sweden)

    Skrzypkiewicz Marek

    2016-01-01

    Full Text Available A possibility of fuelling a solid oxide fuel cell stack (SOFC with biomass fuels can be realized by coupling a SOFC system with a self-standing gasification unit. Such a solution enables multi-fuel operation, elasticity of the system as well as the increase of the efficiency of small-scale biomass-to-electricity conversion units. A system of this type, consisting of biomass gasification unit, gas purification unit, SOFC stack, anode off-gas afterburner and peripherals was constructed and operated successfully. During the process, biomass fuel (wood chips was gasified with air as gasification agent. The gasifier was capable of converting up to 30 kW of fuel to syngas with efficiencies up to 75%. Syngas leaving the gasification unit is delivered to a medium temperature adsorber for sulphur compounds removal. Steam is added to the purified fuel to maintain steam to carbon ratio higher than 2. The syngas then is passed to a SOFC stack through a fuel preheater. In such a configuration it was possible to operate a commercial 1.3 kW stack within its working regime. Conducted tests confirmed successful operation of a SOFC stack fuelled by biomass-sourced syngas.

  17. Co-combustion - a summary of technology

    Energy Technology Data Exchange (ETDEWEB)

    Bo Leckner [Chalmers University of Technology, Goeteborg (Sweden). Dept. of Energy and Environment

    2007-07-01

    Co-combustion of biomass or waste together with a base fuel in a boiler is a simple and economically suitable way to replace fossil fuels by biomass and to utilise waste. Co-combustion in a high-efficiency power station means utilisation of biomass and waste with a higher thermal efficiency than what otherwise had been possible. Due to transport limitations, the additional fuel will only supply a minor part (less than a few hundreds MW{sub fuel}) of the energy in a plant. There are several options: co-combustion with coal in pulverised or fluidised bed boilers, combustion on added grates inserted in pulverised coal boilers, combustors for added fuel coupled in parallel to the steam circuit of a power plant, external gas producers delivering its gas to replace an oil, gas or pulverised fuel burner. Furthermore biomass can be used for reburning in order to reduce NO emissions or for afterburning to reduce N{sub 2}O emissions in fluidised bed boilers. Combination of fuels can give rise to positive or negative synergy effects, of which the best known are the interactions between S, Cl, K, Al, and Si that may give rise to or prevent deposits on tubes or on catalyst surfaces, or that may have an influence on the formation of dioxins. With better knowledge of these effects the positive ones can be utilised and the negative ones can be avoided. 71 refs., 19 figs., 5 tabs.

  18. The path to visible extreme adaptive optics with MagAO-2K and MagAO-X

    Science.gov (United States)

    Males, Jared R.; Close, Laird M.; Guyon, Olivier; Morzinski, Katie M.; Hinz, Philip; Esposito, Simone; Pinna, Enrico; Xompero, Marco; Briguglio, Runa; Riccardi, Armando; Puglisi, Alfio; Mazin, Ben; Ireland, Michael J.; Weinberger, Alycia; Conrad, Al; Kenworthy, Matthew; Snik, Frans; Otten, Gilles; Jovanovic, Nemanja; Lozi, Julien

    2016-07-01

    The next generation of extremely large telescopes (ELTs) have the potential to image habitable rocky planets, if suitably optimized. This will require the development of fast high order "extreme" adaptive optics systems for the ELTs. Located near the excellent site of the future GMT, the Magellan AO system (MagAO) is an ideal on-sky testbed for high contrast imaging development. Here we discuss planned upgrades to MagAO. These include improvements in WFS sampling (enabling correction of more modes) and an increase in speed to 2000 Hz, as well as an H2RG detector upgrade for the Clio infrared camera. This NSF funded project, MagAO-2K, is planned to be on-sky in November 2016 and will significantly improve the performance of MagAO at short wavelengths. Finally, we describe MagAO-X, a visible-wavelength extreme-AO "afterburner" system under development. MagAO-X will deliver Strehl ratios of over 80% in the optical and is optimized for visible light coronagraphy.

  19. A micro-solid oxide fuel cell system as battery replacement

    Science.gov (United States)

    Bieberle-Hütter, Anja; Beckel, Daniel; Infortuna, Anna; Muecke, Ulrich P.; Rupp, Jennifer L. M.; Gauckler, Ludwig J.; Rey-Mermet, Samuel; Muralt, Paul; Bieri, Nicole R.; Hotz, Nico; Stutz, Michael J.; Poulikakos, Dimos; Heeb, Peter; Müller, Patrik; Bernard, André; Gmür, Roman; Hocker, Thomas

    The concept and the design of a micro-solid oxide fuel cell system is described and discussed. The system in this study is called the ONEBAT system and consists of the fuel cell PEN (positive electrode - electrolyte - negative electrode) element, a gas processing unit, and a thermal system. PEN elements of free-standing multi-layer membranes are fabricated on Foturan ® and on Si substrates using thin film deposition and microfabrication techniques. Open circuit voltages of up to 1.06 V and power of 150 mW cm -2 are achieved at 550 °C. The membranes are stable up to 600 °C. The gas processing unit allows butane conversion of 95% and hydrogen selectivity of 83% at 550 °C in the reformer and efficient after-burning of hydrogen, carbon monoxide, and lower hydrocarbons in the post-combustor. Thermal system simulations prove that a large thermal gradient of more than 500 °C between the hot module and its exterior are feasible. The correlation between electrical power output - system size and thermal conductivity - heat-transfer coefficient of the thermal insulation material are shown. The system design studies show that the single sub-systems can be integrated into a complete system and that the requirements for portable electronic devices can be achieved with a base unit of 2.5 W and a modular approach.

  20. Phased Array Noise Source Localization Measurements of an F404 Nozzle Plume at Both Full and Model Scale

    Science.gov (United States)

    Podboy, Gary G.; Bridges, James E.; Henderson, Brenda S.

    2010-01-01

    A 48-microphone planar phased array system was used to acquire jet noise source localization data on both a full-scale F404-GE-F400 engine and on a 1/4th scale model of a F400 series nozzle. The full-scale engine test data show the location of the dominant noise sources in the jet plume as a function of frequency for the engine in both baseline (no chevron) and chevron configurations. Data are presented for the engine operating both with and without afterburners. Based on lessons learned during this test, a set of recommendations are provided regarding how the phased array measurement system could be modified in order to obtain more useful acoustic source localization data on high-performance military engines in the future. The data obtained on the 1/4th scale F400 series nozzle provide useful insights regarding the full-scale engine jet noise source mechanisms, and document some of the differences associated with testing at model-scale versus fullscale.

  1. Removal of Unpleasant Odorous Substances from Smoke Produced by Smoke Curing Houses

    Directory of Open Access Journals (Sweden)

    Zygmunt Kowalski

    2010-01-01

    Full Text Available Problem statement: For purification of smoke in PPHU Duda-Bis Plant water washers, placed in the outlet channel of smoke chamber, have been applied, but the amount of the substances remaining in the air after passing through the washer were not acceptable by the standards and caused repulsive odor emitted into the atmosphere. Approach: To eliminate discomfort, caused by smoke emission unto the environment, PPHU Duda-Bis has been introduced a simple and effective method of thermal utilization of post-curing smoke by using heated with natural gas boiler. Before the smoke enters the boiler, water vapors undergo condensation and the water drops obtained are separated in steam drier. The smoke introduced into the boiler brings some excess of air. Results: After the new method of curing smoke after-burning had been put into practice in PPHU Duda-Bis, the unpleasant odorous and harmful to the environment compounds were eliminated. The content of the emitted components per year, after thermal utilization of the smoke, was 100 times lower in comparison to the wet-method. Conclusion: The thermal methods belong to the most efficient BAT techniques enabling removal of the unpleasant odorous substances from the gases generated by meat industry.

  2. Turbulent Combustion in SDF Explosions

    Energy Technology Data Exchange (ETDEWEB)

    Kuhl, A L; Bell, J B; Beckner, V E

    2009-11-12

    A heterogeneous continuum model is proposed to describe the dispersion and combustion of an aluminum particle cloud in an explosion. It combines the gas-dynamic conservation laws for the gas phase with a continuum model for the dispersed phase, as formulated by Nigmatulin. Inter-phase mass, momentum and energy exchange are prescribed by phenomenological models. It incorporates a combustion model based on the mass conservation laws for fuel, air and products; source/sink terms are treated in the fast-chemistry limit appropriate for such gasdynamic fields, along with a model for mass transfer from the particle phase to the gas. The model takes into account both the afterburning of the detonation products of the C-4 booster with air, and the combustion of the Al particles with air. The model equations were integrated by high-order Godunov schemes for both the gas and particle phases. Numerical simulations of the explosion fields from 1.5-g Shock-Dispersed-Fuel (SDF) charge in a 6.6 liter calorimeter were used to validate the combustion model. Then the model was applied to 10-kg Al-SDF explosions in a an unconfined height-of-burst explosion. Computed pressure histories are compared with measured waveforms. Differences are caused by physical-chemical kinetic effects of particle combustion which induce ignition delays in the initial reactive blast wave and quenching of reactions at late times. Current simulations give initial insights into such modeling issues.

  3. Thermodynamic States in Explosion Fields

    Energy Technology Data Exchange (ETDEWEB)

    Kuhl, A L

    2009-10-16

    Here we investigate the thermodynamic states occurring in explosion fields from the detonation of condensed explosives in air. In typical applications, the pressure of expanded detonation products gases is modeled by a Jones-Wilkins-Lee (JWL) function: P{sub JWL} = f(v,s{sub CJ}); constants in that function are fit to cylinder test data. This function provides a specification of pressure as a function of specific volume, v, along the expansion isentrope (s = constant = s{sub CJ}) starting at the Chapman-Jouguet (CJ) state. However, the JWL function is not a fundamental equation of thermodynamics, and therefore gives an incomplete specification of states. For example, explosions inherently involve shock reflections from surfaces; this changes the entropy of the products, and in such situations the JWL function provides no information on the products states. In addition, most explosives are not oxygen balanced, so if hot detonation products mix with air, they after-burn, releasing the heat of reaction via a turbulent combustion process. This raises the temperature of explosion products cloud to the adiabatic flame temperature ({approx}3,000K). Again, the JWL function provides no information on the combustion products states.

  4. HITEMP derived spectral database for the prediction of jet engine exhaust infrared emission using a statistical band model

    Science.gov (United States)

    Lindermeir, E.; Beier, K.

    2012-08-01

    The spectroscopic database HITEMP 2010 is used to upgrade the parameters of the statistical molecular band model which is part of the infrared signature prediction code NIRATAM (NATO InfraRed Air TArget Model). This band model was recommended by NASA and is applied in several codes that determine the infrared emission of combustion gases. The upgrade regards spectral absorption coefficients and line densities of the gases H2O, CO2, and CO in the spectral region 400-5000 cm-1 (2-25μm) with a spectral resolution of 5 cm-1. The temperature range 100-3000 K is covered. Two methods to update the database are presented: the usually applied method as provided in the literature and an alternative, more laborious procedure that employs least squares fitting. The achieved improvements resulting from both methods are demonstrated by comparisons of radiance spectra obtained from the band model to line-by-line results. The performance in a realistic scenario is investigated on the basis of measured and predicted spectra of a jet aircraft plume in afterburner mode.

  5. DRAGON: Monte Carlo Generator of Particle Production from a Fragmented Fireball in Ultrarelativistic Nuclear Collisions

    Science.gov (United States)

    Tomasik, Boris

    2010-11-01

    A Monte Carlo generator of the final state of hadrons emitted from an ultrarelativistic nuclear collision is introduced. An important feature of the generator is a possible fragmentation of the fireball and emission of the hadrons from fragments. Phase space distribution of the fragments is based on the blast wave model extended to azimuthally non-symmetric fireballs. Parameters of the model can be tuned and this allows to generate final states from various kinds of fireballs. A facultative output in the OSCAR1999A format allows for a comprehensive analysis of phase-space distributions and/or use as an input for an afterburner. DRAGON's purpose is to produce artificial data sets which resemble those coming from real nuclear collisions provided fragmentation occurs at hadronisation and hadrons are emitted from fragments without any further scattering. Its name, DRAGON, stands for DRoplet and hAdron GeneratOr for Nuclear collisions. In a way, the model is similar to THERMINATOR, with the crucial difference that emission from fragments is included.

  6. Neutron Source from Laser Plasma Acceleration

    Science.gov (United States)

    Jiao, Xuejing; Shaw, Joseph; McCary, Eddie; Downer, Mike; Hegelich, Bjorn

    2016-10-01

    Laser driven electron beams and ion beams were utilized to produce neutron sources via different mechanism. On the Texas Petawatt laser, deuterized plastic, gold and DLC foil targets of varying thickness were shot with 150 J , 150 fs laser pulses at a peak intensity of 2 ×1021W /cm2 . Ions were accelerated by either target normal sheath acceleration or Breakout Afterburner acceleration. Neutrons were produced via the 9Be(d,n) and 9Be(p,n) reactions when accelerated ions impinged on a Beryllium converter as well as by deuteron breakup reactions. We observed 2 ×1010 neutron per shot in average, corresponding to 5 ×1018n /s . The efficiencies for different targets are comparable. In another experiment, 38fs , 0.3 J UT3 laser pulse interacted with mixed gas target. Electrons with energy 40MeV were produced via laser wakefield acceleration. Neutron flux of 2 ×106 per shot was generated through bremsstrahlung and subsequent photoneutron reactions on a Copper converter.

  7. Modelling and Simulation of a Hybrid Solid Oxide Fuel Cell Coupled with a Gas Turbine Power Plant

    Directory of Open Access Journals (Sweden)

    Luca Andreassi

    2009-09-01

    Full Text Available

    The paper presents a simulation of a hybrid solid oxide fuel cell-gas turbine (SOFC-GT power generation system fueled by natural gas. In the system considered, the unreacted fuel from a topping solid oxide fuel cell is burnt in an afterburner to feed a bottoming gas turbine and produce additional power. Combustion gas expands in the gas turbine after having preheated the inlet air and fuel and it is used to generate steam required by the reforming reactions. A novel thermodynamic model has been developed for the fuel cell and implemented into the library of a modular object-oriented Process Simulator, CAMELPro™. The relevant plant performance indicators have been analyzed to evaluate the incremental increase in efficiency brought about by the introduction of the gas turbine and heat regeneration system. Simulations were performed for different values of the main plant parameters.

    • This paper is an updated version of a paper published in the ECOS'08 proceedings. 

  8. Supersonic Injection of Aerated Liquid Jet

    Science.gov (United States)

    Choudhari, Abhijit; Sallam, Khaled

    2016-11-01

    A computational study of the exit flow of an aerated two-dimensional jet from an under-expanded supersonic nozzle is presented. The liquid sheet is operating within the annular flow regime and the study is motivated by the application of supersonic nozzles in air-breathing propulsion systems, e.g. scramjet engines, ramjet engines and afterburners. The simulation was conducted using VOF model and SST k- ω turbulence model. The test conditions included: jet exit of 1 mm and mass flow rate of 1.8 kg/s. The results show that air reaches transonic condition at the injector exit due to the Fanno flow effects in the injector passage. The aerated liquid jet is alternately expanded by Prandtl-Meyer expansion fan and compressed by oblique shock waves due to the difference between the back (chamber) pressure and the flow pressure. The process then repeats itself and shock (Mach) diamonds are formed at downstream of injector exit similar to those typical of exhaust plumes of propulsion system. The present results, however, indicate that the flow field of supersonic aerated liquid jet is different from supersonic gas jets due to the effects of water evaporation from the liquid sheet. The contours of the Mach number, static pressure of both cases are compared to the theory of gas dynamics.

  9. Ultrasound assessed thickness of burn scars in association with laser Doppler imaging determined depth of burns in paediatric patients.

    Science.gov (United States)

    Wang, Xue-Qing; Mill, Julie; Kravchuk, Olena; Kimble, Roy M

    2010-12-01

    This study describes the ultrasound assessment of burn scars in paediatric patients and the association of these scar thickness with laser Doppler imaging (LDI) determined burn depth. A total of 60 ultrasound scar assessments were conducted on 33 scars from 21 paediatric burn patients at 3, 6 and 9 months after-burn. The mean of peak scar thickness was 0.39±0.032 cm, with the thickest at 6 months (0.40±0.036 cm). There were 17 scald burn scars (0.34±0.045 cm), 4 contact burn scars (0.61±0.092 cm), and 10 flame burn scars (0.42±0.058 cm). Each group of scars followed normal distributions. Twenty-three scars had original burns successfully scanned by LDI and various depths of burns were presented by different colours according to blood perfusion units (PU), with dark blue burns, with the thinnest scars for green coloured burns and the thickest for dark blue coloured burns. Within light blue burns, grafted burns healed with significantly thinner scars than non-grafted burns. This study indicates that LDI can be used for predicting the risk of hypertrophic scarring and for guiding burn care. To our knowledge, this is the first study to correlate the thickness of burns scars by ultrasound scan with burn depth determined by LDI.

  10. Apparatus for incinerating hazardous waste

    Science.gov (United States)

    Chang, R.C.W.

    1994-12-20

    An apparatus is described for incinerating wastes, including an incinerator having a combustion chamber, a fluid-tight shell enclosing the combustion chamber, an afterburner, an off-gas particulate removal system and an emergency off-gas cooling system. The region between the inner surface of the shell and the outer surface of the combustion chamber forms a cavity. Air is supplied to the cavity and heated as it passes over the outer surface of the combustion chamber. Heated air is drawn from the cavity and mixed with fuel for input into the combustion chamber. The pressure in the cavity is maintained at least approximately 2.5 cm WC higher than the pressure in the combustion chamber. Gases cannot leak from the combustion chamber since the pressure outside the chamber (inside the cavity) is higher than the pressure inside the chamber. The apparatus can be used to treat any combustible wastes, including biological wastes, toxic materials, low level radioactive wastes, and mixed hazardous and low level transuranic wastes. 1 figure.

  11. Cold start dynamics and temperature sliding observer design of an automotive SOFC APU

    Science.gov (United States)

    Lin, Po-Hsu; Hong, Che-Wun

    This paper presents a dynamic model for studying the cold start dynamics and observer design of an auxiliary power unit (APU) for automotive applications. The APU is embedded with a solid oxide fuel cell (SOFC) stack which is a quiet and pollutant-free electric generator; however, it suffers from slow start problem from ambient conditions. The SOFC APU system equips with an after-burner to accelerate the start-up transient in this research. The combustion chamber burns the residual fuel (and air) left from the SOFC to raise the exhaust temperature to preheat the SOFC stack through an energy recovery unit. Since thermal effect is the dominant factor that influences the SOFC transient and steady performance, a nonlinear real-time sliding observer for stack temperature was implemented into the system dynamics to monitor the temperature variation for future controller design. The simulation results show that a 100 W APU system in this research takes about 2 min (in theory) for start-up without considering the thermal limitation of the cell fracture.

  12. 含呋咱衍生物富燃料推进剂的能量性能%The Energy Properties of Fuel-rich Propellants Comprising Furazan Derivatives

    Institute of Scientific and Technical Information of China (English)

    张君启; 张炜; 朱慧; 张兴高

    2006-01-01

    Furazan is a kind of novel high energy material and has a good future application in propellants and explosives. This work studies the energy properties of Al/Mg/HTPB/AP fuel-rich propellants comprising furazan derivatives. The results reveal that the specific impulse (Is) of propellant comprising DAAzF is the largest with propellant comprising CL-20 at the same mass fraction(w). The mean relative molecular mass(Mg) of propellants comprising furazans is about 29, the flame temperature in after-burning chamber(Tc) is about 2200K, and the values of (-M)g and Tc increase with increasing the mass fraction of furazans.%采用最小自由能法,研究了含呋咱衍生物的Al/Mg/HTPB/AP富燃料推进剂的能量性能,结果表明,随着呋咱衍生物含量的增加,富燃料推进剂比冲明显增加,其中含质量分数为25%的DAAzF(4,4'-二氨基-3,3'-偶氮呋咱)的富燃料推进剂比冲可达7 522.9 N·s·kg-1,比相同质量含量下含CL-20富燃料推进剂比冲高260N·s·kg-1.含呋咱衍生物富燃料推进剂气相平均相对分子质量((-M)g)约为29,补燃室火焰温度(Tc)约为2 200K,且二者随着呋咱衍生物含量增加而略有增加.

  13. Human exploration and settlement of the Moon using LUNOX-augmented NTR propulsion

    Science.gov (United States)

    Borowski, Stanley K.; Culver, Donald W.; Bulman, Melvin J.

    1995-10-01

    An innovative trimodal nuclear thermal rocket (NTR) concept is described which combines conventional liquid hydrogen (LH2)-cooled NTR, Brayton cycle power generation and supersonic combustion ramjet (scramjet) technologies. Known as the liquid oxygen (LOX) augmented NTR (LANTR), this concept utilizes the large divergent section of the NTR nozzle as an 'afterburner' into which LOX is injected and supersonically combusted with nuclear preheated hydrogen emerging from the LANTR's choked sonic throat--'scramjet propulsion in reverse.' By varying the oxygen-to-hydrogen mixture ratio (MR), the LANTR can operate over a wide range of thrust and specific impulse (Isp) values while the reactor core power level remains relatively constant. As the MR varies from zero to seven, the thrust-to-weight ratio for a 15 thousand pound force (klbf) NTR increases by approximately 440%--from 3 to 13--while the Isp decreases by only approximately 45%--from 940 to 515 seconds. This thrust augmentation feature of the LANTR means that 'big engine' performance can be obtained using smaller more affordable, easier to test NTR engines. 'Reoxidizing' the bipropellant LANTR system in low lunar orbit (LLO) with high density 'lunar-derived' LOX (LUNOX) enables a reusable, reduced size and mass lunar transfer vehicle (LTV) which can be deployed and resupplied using two 66 t-class Shuttle-derived launch vehicles. The reusable LANTR can also transport 200 to 300% more payload on each piloted round trip mission than an expendable 'all LH2' NTR system. As initial outposts grow to eventual lunar settlements and LUNOX production capacity increases, the LANTR concept can also enable a rapid 'commuter' shuttle capable of 36 to 24 hour 'one way' trips to the Moon and back with reasonable size vehicles and initial mass in low Earth orbit (IMLEO) requirements.

  14. Wind-Tunnel Investigation of Subsonic Longitudinal Aerodynamic Characteristics of a Tiltable-Wing Vertical-Take-Off-and-Landing Supersonic Bomber Configuration Including Turbojet Power Effects

    Science.gov (United States)

    Thompson, Robert F.; Vogler, Raymond D.; Moseley, William C., Jr.

    1959-01-01

    Jet-powered model tests were made to determine the low-speed longitudinal aerodynamic characteristics of a vertical-take-off and-landing supersonic bomber configuration. The configuration has an unique engine-wing arrangement wherein six large turbojet engines (three on each side of the fuselage) are buried in a low-aspect-ratio wing which is tilted into the vertical plane for take-off. An essentially two-dimensional variable inlet, spanning the leading edge of each wing semispan, provides air for the engines. Jet flow conditions were simulated for a range of military (nonafterburner) and afterburner turbojet-powered flight at subsonic speeds. Three horizontal tails were tested at a station down-stream of the jet exit and at three heights above the jet axes. A semi-span model was used and test parameters covered wing-fuselage incidence angles from 0 deg to 15 deg, wing angles of attack from -4 deg to 36 deg, a variable range of horizontal-tail incidence angles, and some variations in power simulation conditions. Results show that, with all horizontal tails tested, there were large variations in static stability throughout the lift range. When the wing and fuselage were alined, the model was statically stable throughout the test range only with the largest tail tested (tail span of 1.25 wing span) and only when the tail was located in the low test position which placed the tail nearest to the undeflected jet. For transition flight conditions, none of the tail configurations provided satisfactory longitudinal stability or trim throughout the lift range. Jet flow was destabilizing for most of the test conditions, and varying the jet-exit flow conditions at a constant thrust coefficient had little effect on the stability of this model. Wing leading-edge simulation had some important effects on the longitudinal aerodynamic characteristics.

  15. Experimental assessment of film cooling performance of short cylindrical holes on a flat surface

    Science.gov (United States)

    Singh, Kuldeep; Premachandran, B.; Ravi, M. R.

    2016-03-01

    The present study is an experimental investigation of film-cooling over a flat surface from the short cylindrical holes. The film cooling holes used in the combustion chamber and the afterburner liner of an aero engine has length-to-diameter (L/D) typically in the range 1-2, while the cooling holes used in turbine blades has L/D > 3. Based on the classification given in the literature, cooling holes with L/D ≤ 3 are named as short holes and cooling holes with L/D > 3 are named as long holes. Short film cooling holes cause jetting of the secondary fluid whereas the secondary fluid emerging from long holes has characteristics similar to fully developed turbulent flow in pipe. In order to understand the difference in the film cooling performance of long and short cooling holes, experimental study is carried out for five values of L/D in the range 1-5, five injection angles, α = 15°-90° and five mainstream Reynolds number 1.25 × 105-6.25 × 105 and two blowing ratios, M = 0.5-1.0. The surface temperature of the test plate is monitored using infrared thermography. The results obtained from the present study showed that the film-cooling effectiveness is higher for the longest holes (L/D = 5) investigated in the present work in comparison to that for the shorter holes. Short holes are found to give better effectiveness at the lowest investigated injection angle i.e. α = 15° in the near cooling hole region, whereas film cooling effectiveness obtained at injection angle, α = 45° is found to be better than other injection angles for longest investigated holes, i.e. L/D = 5.

  16. Combustion of Shock-Dispersed Fuels in a Chamber

    Energy Technology Data Exchange (ETDEWEB)

    Neuwald, P; Reichenbach, H; Kuhl, A L

    2003-04-23

    In previous studies we have investigated after-burning effects of a fuel-rich explosive (TNT). In that case the detonation only releases about 30 % of the available energy, but generates a hot cloud of fuel that can burn in the ambient air, thus evoking an additional energy release that is distributed in space and time. The current series of small-scale experiments can be looked upon as a natural generalization of this mechanism: a booster charge disperses a (non-explosive) fuel, provides mixing with air and - by means of the hot detonation products - energy to ignite the fuel. The current version of our miniature Shock-Dispersed-Fuel (SDF) charges consists of a spherical booster charge of 0.5 g PETN, embedded in a paper cylinder of approximately 2.2 cm3, which is filled with powdered fuel compositions. The main compositions studied up to now contain aluminum powder, hydrocarbon powders like polyethylene or sucrose and/or carbon particles. These charges were studied in three different chambers of 4-1, 6.6-1 and 40.5-1 volume. In general, the booster charge was sufficient to initiate burning of the fuel. This modifies the pressure signatures measured with a number of wall gages and increases the quasi-static overpressure level obtained in the chambers. On the one hand the time-scale and the yield of the pressure rise depend on the fuel and its characteristics. On the other hand they also depend on the flow dynamics in the chamber, which is dominated by shock reverberations, and thus on the chamber geometry and volume. The paper gives a survey of the experimental results and discusses the possible influences of some basic parameters.

  17. Advanced air staging techniques to improve fuel flexibility, reliability and emissions in fluidized bed co-combustion

    Energy Technology Data Exchange (ETDEWEB)

    Aamand, Lars-Erik; Leckner, Bo [Chalmers Technical Univ., Goeteborg (Sweden); Luecke, Karsten; Werther, Joachim [Technical Univ. of Hamburg-Harburg (Germany)

    2001-12-01

    A joint research project between the Technical University of Hamburg-Harburg and Chalmers Technical University. For operation under co-combustion the following results should be considered: The high ash content of the sewage sludge results in significantly increased ash flows. Although high alkali metal concentrations are found in the sewage sludge ash, no critical concentrations were reached and tendencies to fouling were not observed. The trace metal input rises with increased sludge fraction. However, emissions of metal compounds were well below legal limits. The trace metals tend to accumulate on the fly ash. In general, very low fuel nitrogen conversions to NO and N{sub 2}O of 2 - 4 % are achievable. With coal as a base fuel alternative air staging with secondary air supply after solids separation attains even lower NO emissions than normal staging without strongly affecting CO and SO{sub 2} emissions. Alternative staging also reduces N{sub 2}O emissions. An optimum for the excess air ratio in the riser of 1.05 was found for a total excess air ratio of 1.2. The higher the volatile content of the fuel is, the less effective the NO reduction due to air staging becomes. The measurements suggest that the optimum gas residence time regarding the emissions in CFB combustors is around 6 to 7 s. These times are achieved in commercial scale plants due to their large cyclones that perhaps partly can replace a large afterburner chamber. The circulating fluidized bed boiler can be operated in a very flexible way with various fuel mixtures up to an energy fraction of sludge of 25% without exceeding legal emission limits.

  18. Experimental assessment of film cooling performance of short cylindrical holes on a flat surface

    Science.gov (United States)

    Singh, Kuldeep; Premachandran, B.; Ravi, M. R.

    2016-12-01

    The present study is an experimental investigation of film-cooling over a flat surface from the short cylindrical holes. The film cooling holes used in the combustion chamber and the afterburner liner of an aero engine has length-to-diameter (L/D) typically in the range 1-2, while the cooling holes used in turbine blades has L/D > 3. Based on the classification given in the literature, cooling holes with L/D ≤ 3 are named as short holes and cooling holes with L/D > 3 are named as long holes. Short film cooling holes cause jetting of the secondary fluid whereas the secondary fluid emerging from long holes has characteristics similar to fully developed turbulent flow in pipe. In order to understand the difference in the film cooling performance of long and short cooling holes, experimental study is carried out for five values of L/D in the range 1-5, five injection angles, α = 15°-90° and five mainstream Reynolds number 1.25 × 105-6.25 × 105 and two blowing ratios, M = 0.5-1.0. The surface temperature of the test plate is monitored using infrared thermography. The results obtained from the present study showed that the film-cooling effectiveness is higher for the longest holes (L/D = 5) investigated in the present work in comparison to that for the shorter holes. Short holes are found to give better effectiveness at the lowest investigated injection angle i.e. α = 15° in the near cooling hole region, whereas film cooling effectiveness obtained at injection angle, α = 45° is found to be better than other injection angles for longest investigated holes, i.e. L/D = 5.

  19. The correlation of in vivo burn scar contraction with the level of α-smooth muscle actin expression.

    Science.gov (United States)

    Wang, Xue-Qing; Kravchuk, Olena; Winterford, Clay; Kimble, Roy M

    2011-12-01

    This study describes the direct association of in vivo burn scar contraction with the level of α-smooth muscle actin (α-SMA) in scar tissue, in a porcine burn model. The expression of α-SMA was investigated in 100 biopsies from 44 6-week old burn scars and in 85 biopsies from 16 2-week old burn wounds. Statistical analysis showed that the levels of α-SMA in 6-week old scars were significantly negatively correlated to scar size (r=-0.68) and the higher levels of α-SMA were observed in smaller scars. Moreover, α-SMA was also found to be significantly positively correlated to re-epithelialisation time (r=0.57) and scar thickness (r=0.58) and higher levels of α-SMA were detected in thicker scars with delayed wound closure. Further statistical analysis revealed that scar contraction can be explained best by the level of α-SMA expression and partially by scar thickness. Other variables, such as different dressings and individual pig, may also partly contribute to scar contraction. At week 2 after-burn, the level of α-SMA expression in 16 burn wounds was significantly related to the depth of burns and wound healing outcome. To our knowledge, this is the first study to provide in vivo evidence of the association of α-SMA expression with scar contraction, scar thickness, re-epithelialisation time and the depth of burn in a large animal burn model with scars similar to human hypertrophic scar.

  20. INVESTIGATION OF FUEL CHEMISTRY AND BED PERFORMANCE IN A FLUIDIZED BED BLACK LIQUOR STEAM REFORMER

    Energy Technology Data Exchange (ETDEWEB)

    Kevin Whitty

    2003-12-01

    The University of Utah project ''Investigation of Fuel Chemistry and Bed Performance in a Fluidized Bed Black Liquor Steam Reformer'' (DOE award number DE-FC26-02NT41490) was developed in response to a solicitation for projects to provide technical support for black liquor and biomass gasification. The primary focus of the project is to provide support for a DOE-sponsored demonstration of MTCI's black liquor steam reforming technology at Georgia-Pacific's paper mill in Big Island, Virginia. A more overarching goal is to improve the understanding of phenomena that take place during low temperature black liquor gasification. This is achieved through five complementary technical tasks: (1) construction of a fluidized bed black liquor gasification test system, (2) investigation of bed performance, (3) evaluation of product gas quality, (4) black liquor conversion analysis and modeling and (5) computational modeling of the Big Island gasifier. Four experimental devices have been constructed under this project. The largest facility, which is the heart of the experimental effort, is a pressurized fluidized bed gasification test system. The system is designed to be able to reproduce conditions near the black liquor injectors in the Big Island steam reformer, so the behavior of black liquor pyrolysis and char gasification can be quantified in a representative environment. The gasification test system comprises five subsystems: steam generation and superheating, black liquor feed, fluidized bed reactor, afterburner for syngas combustion and a flue gas cooler/condenser. The three-story system is located at University of Utah's Industrial Combustion and Gasification Research Facility, and all resources there are available to support the research.

  1. MOA—The Magnetic Field Amplified Thruster, a Novel Concept for a Pulsed Plasma Accelerator

    Science.gov (United States)

    Frischauf, Norbert; Hettmer, Manfred; Grassauer, Andreas; Bartusch, Tobias; Koudelka, Otto

    2008-01-01

    More than 60 years after the later Nobel laureate Hannes Alfvén had published a letter stating that oscillating magnetic fields can accelerate ionised matter via magneto-hydrodynamic interactions in a wave like fashion, the technical implementation of Alfvén waves for propulsive purposes has been proposed, patented and examined for the first time by a group of inventors. The name of the concept is MOA—Magnetic field Oscillating Amplified thruster. Based on computer simulations, MOA is a highly flexible propulsion system, whose performance parameters might easily be adapted, by changing the mass flow and/or the power level. As such the system is capable to deliver a maximum specific impulse of 13116 s (12.87 mN) at a power level of 11.16 kW, using Xe as propellant, but can also be attuned to provide a thrust of 236.5 mN (2411 s) at 6.15 kW of power. While space propulsion is expected to be the prime application for MOA and is supported by numerous applications such as Solar and/or Nuclear Electric Propulsion or even as an `afterburner system' for Nuclear Thermal Propulsion, other terrestrial applications can be thought of as well, making the system highly suited for a common space-terrestrial application research and utilisation strategy. This paper presents the recent developments of the MOA Thruster R&D activities at QASAR (www.qasar.at), the company in Vienna, which has been set up to further develop and test the Alfvén wave technology and its applications.

  2. Development of nuclear fuel cycle technologies - bases of long-term provision of fuel and environmental safety of nuclear power

    Energy Technology Data Exchange (ETDEWEB)

    Solonin, M.I.; Polyakov, A.S.; Zakharkin, B.S.; Smelov, V.S.; Nenarokomov, E.A.; Mukhin, I.V. [SSC, RF, A.A. Bochvar ALL-Russia Research Institute of Inorganic Materials, Moscow (Russian Federation)

    2000-07-01

    To-day nuclear power is one of the options, however, to-morrow it may become the main source of the energy, thus, providing for the stable economic development for the long time to come. The availability of the large-scale nuclear power in the foreseeable future is governed by not only the safe operation of nuclear power plants (NPP) but also by the environmentally safe management of spent nuclear fuel, radioactive waste conditioning and long-term storage. More emphasis is to be placed to the closing of the fuel cycle in view of substantial quantities of spent nuclear fuel arisings. The once-through fuel cycle that is cost effective at the moment cannot be considered to be environmentally safe even for the middle term since the substantial build-up of spent nuclear fuel containing thousands of tons Pu will require the resolution of the safe management problem in the nearest future and is absolutely unjustified in terms of moral ethics as a transfer of the responsibility to future generations. The minimization of radioactive waste arisings and its radioactivity is only feasible with the closed fuel cycle put into practice and some actinides and long-lived fission radionuclides burnt out. The key issues in providing the environmentally safe fuel cycle are efficient processes of producing fuel for NPP, radionuclide after-burning included, a long-term spent nuclear fuel storage and reprocessing as well as radioactive waste management. The paper deals with the problems inherent in producing fuel for NPP with a view for the closed fuel cycle. Also discussed are options of the fuel cycle, its effectiveness and environmental safety with improvements in technologies of spent nuclear fuel reprocessing and long-lived radionuclide partitioning. (authors)

  3. Analysis Of The World Elite Men's Table Tennis Athletes Specialty Technology%世界优秀男子乒乓球运动员特长技术分析

    Institute of Scientific and Technical Information of China (English)

    王军

    2014-01-01

    采用文献资料等方法,对世界优秀男子乒乓球运动员特长技术进行研究,旨在提升我国乒乓球项目特长技术创新与发展。结果表明:世界优秀男子乒乓球运动员特长技术主要有8项,分别为,瓦尔德内尔横拍直握式发球技术和晃接技术、科贝尔反手侧拧技术、金泽洙步法技术、蒋澎龙加力推挡技术、格林卡反手横向拉球技术、马琳加转摆短技术和正手前冲弧圈球技术、朱世赫削中反攻技术、王皓直板横打技术。%Mainly using literature method, etc, making the research to the world elite men's table tennis athletes specialty technology, to continuously improve the development and innovation of table tennis specialty technology in China.The results show that: the world elite men's table tennis athletes specialty technology mainly have eight terms, respectively are, Waldner post-binge hold serve technology and sway technology, Gobel backhand side screw technology, Kim Taek Soo step technique, Jiang Penglong afterburner push technology, Glinka backhand transverse pull the ball technology, Ma Lin turned a short swing technology and forehand fast loop drive technique, Zhu Shihe offensive techniques, Wang Hao Straight horizontal techniques.

  4. Nonlinear hydrodynamic and thermoacoustic oscillations of a bluff-body stabilised turbulent premixed flame

    Science.gov (United States)

    Lee, Chin Yik; Li, Larry Kin Bong; Juniper, Matthew P.; Cant, Robert Stewart

    2016-01-01

    Turbulent premixed flames often experience thermoacoustic instabilities when the combustion heat release rate is in phase with acoustic pressure fluctuations. Linear methods often assume a priori that oscillations are periodic and occur at a dominant frequency with a fixed amplitude. Such assumptions are not made when using nonlinear analysis. When an oscillation is fully saturated, nonlinear analysis can serve as a useful avenue to reveal flame behaviour far more elaborate than period-one limit cycles, including quasi-periodicity and chaos in hydrodynamically or thermoacoustically self-excited system. In this paper, the behaviour of a bluff-body stabilised turbulent premixed propane/air flame in a model jet-engine afterburner configuration is investigated using computational fluid dynamics. For the frequencies of interest in this investigation, an unsteady Reynolds-averaged Navier-Stokes approach is found to be appropriate. Combustion is represented using a modified laminar flamelet approach with an algebraic closure for the flame surface density. The results are validated by comparison with existing experimental data and with large eddy simulation, and the observed self-excited oscillations in pressure and heat release are studied using methods derived from dynamical systems theory. A systematic analysis is carried out by increasing the equivalence ratio of the reactant stream supplied to the premixed flame. A strong variation in the global flame structure is observed. The flame exhibits a self-excited hydrodynamic oscillation at low equivalence ratios, becomes steady as the equivalence ratio is increased to intermediate values, and again exhibits a self-excited thermoacoustic oscillation at higher equivalence ratios. Rich nonlinear behaviour is observed and the investigation demonstrates that turbulent premixed flames can exhibit complex dynamical behaviour including quasiperiodicity, limit cycles and period-two limit cycles due to the interactions of various

  5. Mixing and reaction processes in rocket based combined cycle and conventional rocket engines

    Science.gov (United States)

    Lehman, Matthew Kurt

    Raman spectroscopy was used to make species measurements in two rocket engines. An airbreathing rocket, the rocket based combined cycle (RBCC) engine, and a conventional rocket were investigated. A supersonic rocket plume mixing with subsonic coflowing air characterizes the ejector mode of the RBCC engine. The mixing length required for the air and plume to become homogenous is a critical dimension. For the conventional rocket experiments, a gaseous oxygen/gaseous hydrogen single-element shear coaxial injector was used. Three chamber Mach number conditions, 0.1, 0.2 and 0.3, were chosen to assess the effect of Mach number on mixing. The flow within the chamber was entirely subsonic. For the RBCC experiments, vertical Raman line measurements were made at multiple axial locations downstream from the rocket nozzle plane. Species profiles assessed the mixing progress between the supersonic plume and subsonic air. For the conventional rocket, Raman line measurements were made downstream from the injector face. The goal was to evaluate the effect of increased chamber Mach number on injector mixing/reaction. For both engines, quantitative and qualitative information was collected for computational fluid dynamics (CFD development. The RBCC experiments were conducted for three distinct geometries. The primary flow path was a diffuse and afterburner design with a direct-connect air supply. A sea-level static (SLS) version and a thermally choked variant were also tested. The experimental results show that mixing length increases with additional coflow air in the DAB geometry. Operation of variable rocket mixture ratios at identical air flow rates did not significantly affect the mixing length. The thermally choked variant had a longer mixing length compared to the DAB geometry, and the SLS modification had a shorter mixing length due to a reduced air flow. The conventional rocket studies focused on the effect of chamber Mach number on primary injector mixing. Chamber Mach

  6. Investigations into the effects of the hybrid concepts on the performance of a pressurized fluidized bed combustion system; Untersuchungen zum Einfluss des Hybridkonzeptes auf den Betrieb einer Druckwirbelschichtfeuerung

    Energy Technology Data Exchange (ETDEWEB)

    Nagel, H.; Spliethoff, H.; Hein, K.R.G.

    1998-12-31

    Pressurized fluidized bed combustion has particular advantages as compared to conventional firing systems e.g. in-situ pollutant removal, high thermal efficiencies even in intermediate power ranges, and small reactor sizes. The widespread use of PFBC depends on rising the gasturbine inlet temperature in order to increase efficiencies. In a staged combustion process, which is a kind of a hybrid system, coal is burned substoichometrically in a pressuried fluidized bed producing a low calorific value gas. After hot gas cleanup (<700 C) the gas is afterburned allowing for gasturbine inlet temperatures of more than 1 200 C. At the IVD-PFBC test facility experiments were carried out with regard to composition of the produced gas, carbon-conversion and sulphur capture at various temperatures, pressures and air ratios. The results were compared to chemical equilibrium calculations. Based on experimental data the increase of thermal efficiency through staged combustion was studied using a process simulation program. In comparison with a standard combined cycle with a lignite fired PFBC, staged combustion led to an increase in thermal efficiency of up to 4,5% at equivalent operation conditions (thermal capacity, steam quality). (orig.) [Deutsch] Druckwirbelschichtfeuerungen (DWSF) weisen gegenueber konventionellen Feuerungen einige Vorteile auf wie z.B. in situ Schadstoffminderung, hohe thermische Wirkungsgrade auch im mittleren Leistungsbereich und geringes Bauvolumen. Die weitere Verbreitung der DWSF wird jedoch massgeblich davon abhaengen, inwieweit sich durch Erhoehung der Gasturbinen-Eintrittstemperatur ein weiteres Wirkungsgradpotential erschliessen laesst. Bei der gestuften Verbrennung, einem sog. Hybridprozess, wird Kohle in der Wirbelbrennkammer teiloxidiert. Das entstehende Schwachgas wird anschliessend gereinigt und in einer Nachbrennkammer vollstaendig umgesetzt, so dass Gasturbinen-Eintrittstemperaturen ueber 1 200 C erreicht werden koennen. An der IVD

  7. Nuclear Thermal Rocket (Ntr) Propulsion: A Proven Game-Changing Technology for Future Human Exploration Missions

    Science.gov (United States)

    Borowski, Stanley K.; McCurdy, David R.; Packard, Thomas W.

    2012-01-01

    The NTR represents the next evolutionary step in high performance rocket propulsion. It generates high thrust and has a specific impulse (Isp) of approx.900 seconds (s) or more V twice that of today s best chemical rockets. The technology is also proven. During the previous Rover and NERVA (Nuclear Engine for Rocket Vehicle Applications) nuclear rocket programs, 20 rocket reactors were designed, built and ground tested. These tests demonstrated: (1) a wide range of thrust; (2) high temperature carbide-based nuclear fuel; (3) sustained engine operation; (4) accumulated lifetime; and (5) restart capability V all the requirements needed for a human mission to Mars. Ceramic metal cermet fuel was also pursued, as a backup option. The NTR also has significant growth and evolution potential. Configured as a bimodal system, it can generate electrical power for the spacecraft. Adding an oxygen afterburner nozzle introduces a variable thrust and Isp capability and allows bipropellant operation. In NASA s recent Mars Design Reference Architecture (DRA) 5.0 study, the NTR was selected as the preferred propulsion option because of its proven technology, higher performance, lower launch mass, simple assembly and mission operations. In contrast to other advanced propulsion options, NTP requires no large technology scale-ups. In fact, the smallest engine tested during the Rover program V the 25,000 lbf (25 klbf) Pewee engine is sufficient for human Mars missions when used in a clustered engine arrangement. The Copernicus crewed spacecraft design developed in DRA 5.0 has significant capability and a human exploration strategy is outlined here that uses Copernicus and its key components for precursor near Earth asteroid (NEA) and Mars orbital missions prior to a Mars landing mission. Initially, the basic Copernicus vehicle can enable reusable 1-year round trip human missions to candidate NEAs like 1991 JW and Apophis in the late 2020 s to check out vehicle systems. Afterwards, the

  8. Nuclear Thermal Propulsion (NTP): A Proven Growth Technology for Human NEO/Mars Exploration Missions

    Science.gov (United States)

    Borowski, Stanley K.; McCurdy, David R.; Packard, Thomas W.

    2012-01-01

    The nuclear thermal rocket (NTR) represents the next "evolutionary step" in high performance rocket propulsion. Unlike conventional chemical rockets that produce their energy through combustion, the NTR derives its energy from fission of Uranium-235 atoms contained within fuel elements that comprise the engine s reactor core. Using an "expander" cycle for turbopump drive power, hydrogen propellant is raised to a high pressure and pumped through coolant channels in the fuel elements where it is superheated then expanded out a supersonic nozzle to generate high thrust. By using hydrogen for both the reactor coolant and propellant, the NTR can achieve specific impulse (Isp) values of 900 seconds (s) or more - twice that of today s best chemical rockets. From 1955 - 1972, twenty rocket reactors were designed, built and ground tested in the Rover and NERVA (Nuclear Engine for Rocket Vehicle Applications) programs. These programs demonstrated: (1) high temperature carbide-based nuclear fuels; (2) a wide range of thrust levels; (3) sustained engine operation; (4) accumulated lifetime at full power; and (5) restart capability - all the requirements needed for a human Mars mission. Ceramic metal "cermet" fuel was pursued as well, as a backup option. The NTR also has significant "evolution and growth" capability. Configured as a "bimodal" system, it can generate its own electrical power to support spacecraft operational needs. Adding an oxygen "afterburner" nozzle introduces a variable thrust and Isp capability and allows bipropellant operation. In NASA s recent Mars Design Reference Architecture (DRA) 5.0 study, the NTR was selected as the preferred propulsion option because of its proven technology, higher performance, lower launch mass, versatile vehicle design, simple assembly, and growth potential. In contrast to other advanced propulsion options, no large technology scale-ups are required for NTP either. In fact, the smallest engine tested during the Rover program

  9. Ion acceleration from relativistic laser nano-target

    Energy Technology Data Exchange (ETDEWEB)

    Jung, Daniel

    2012-01-06

    Laser-ion acceleration has been of particular interest over the last decade for fundamental as well as applied sciences. Remarkable progress has been made in realizing laser-driven accelerators that are cheap and very compact compared with conventional rf-accelerators. Proton and ion beams have been produced with particle energies of up to 50 MeV and several MeV/u, respectively, with outstanding properties in terms of transverse emittance and current. These beams typically exhibit an exponentially decaying energy distribution, but almost all advanced applications, such as oncology, proton imaging or fast ignition, require quasimonoenergetic beams with a low energy spread. The majority of the experiments investigated ion acceleration in the target normal sheath acceleration (TNSA) regime with comparably thick targets in the {mu}m range. In this thesis ion acceleration is investigated from nm-scaled targets, which are partially produced at the University of Munich with thickness as low as 3 nm. Experiments have been carried out at LANL's Trident high-power and high-contrast laser (80 J, 500 fs, {lambda}=1054 nm), where ion acceleration with these nano-targets occurs during the relativistic transparency of the target, in the so-called Breakout afterburner (BOA) regime. With a novel high resolution and high dispersion Thomson parabola and ion wide angle spectrometer, thickness dependencies of the ions angular distribution, particle number, average and maximum energy have been measured. Carbon C{sup 6+} energies reached 650 MeV and 1 GeV for unheated and heated targets, respectively, and proton energies peaked at 75 MeV and 120 MeV for diamond and CH{sub 2} targets. Experimental data is presented, where the conversion efficiency into carbon C{sup 6+} (protons) is investigated and found to have an up to 10fold (5fold) increase over the TNSA regime. With circularly polarized laser light, quasi-monoenergetic carbon ions have been generated from the same nm-scaled foil

  10. Combustion instability and active control: Alternative fuels, augmentors, and modeling heat release

    Science.gov (United States)

    Park, Sammy Ace

    Experimental and analytical studies were conducted to explore thermo-acoustic coupling during the onset of combustion instability in various air-breathing combustor configurations. These include a laboratory-scale 200-kW dump combustor and a 100-kW augmentor featuring a v-gutter flame holder. They were used to simulate main combustion chambers and afterburners in aero engines, respectively. The three primary themes of this work includes: 1) modeling heat release fluctuations for stability analysis, 2) conducting active combustion control with alternative fuels, and 3) demonstrating practical active control for augmentor instability suppression. The phenomenon of combustion instabilities remains an unsolved problem in propulsion engines, mainly because of the difficulty in predicting the fluctuating component of heat release without extensive testing. A hybrid model was developed to describe both the temporal and spatial variations in dynamic heat release, using a separation of variables approach that requires only a limited amount of experimental data. The use of sinusoidal basis functions further reduced the amount of data required. When the mean heat release behavior is known, the only experimental data needed for detailed stability analysis is one instantaneous picture of heat release at the peak pressure phase. This model was successfully tested in the dump combustor experiments, reproducing the correct sign of the overall Rayleigh index as well as the remarkably accurate spatial distribution pattern of fluctuating heat release. Active combustion control was explored for fuel-flexible combustor operation using twelve different jet fuels including bio-synthetic and Fischer-Tropsch types. Analysis done using an actuated spray combustion model revealed that the combustion response times of these fuels were similar. Combined with experimental spray characterizations, this suggested that controller performance should remain effective with various alternative fuels

  11. Recent activities in the development of the MOA thruster

    Science.gov (United States)

    Frischauf, Norbert; Hettmer, Manfred; Grassauer, Andreas; Bartusch, Tobias; Koudelka, Otto

    2008-07-01

    More than 60 years after the later Nobel laureate Hannes Alfvén had published a letter stating that oscillating magnetic fields can accelerate ionised matter via magneto-hydrodynamic interactions in a wave like fashion, the technical implementation of Alfvén waves for propulsive purposes has been proposed, patented and examined for the first time by a group of inventors. The name of the concept, utilising Alfvén waves to accelerate ionised matter for propulsive purposes, is MOA-magnetic field oscillating amplified thruster. Alfvén waves are generated by making use of two coils, one being permanently powered and serving also as magnetic nozzle, the other one being switched on and off in a cyclic way, deforming the field lines of the overall system. It is this deformation that generates Alfvén waves, which are in the next step used to transport and compress the propulsive medium, in theory leading to a propulsion system with a much higher performance than any other electric propulsion system. Based on computer simulations, which were conducted to get a first estimate on the performance of the system, MOA is a corrosion free and highly flexible propulsion system, whose performance parameters might easily be adapted in flight, by changing the mass flow and/or the power level. As such the system is capable to deliver a maximum specific impulse of 13 116 s (12.87 mN) at a power level of 11.16 kW, using Xe as propellant, but can also be attuned to provide a thrust of 236.5 mN (2411 s) at 6.15 kW of power. First tests-that are further described in this paper-have been conducted successfully and underline the feasibility of the concept. While space propulsion is expected to be the prime application for MOA and is supported by numerous applications such as Solar and/or Nuclear Electric Propulsion or even as an "afterburner system" for nuclear thermal propulsion, other terrestrial applications can be thought of as well, making the system highly suited for a common space

  12. 水/一氧化二氮组合式SteamJet发动机性能研究%Research on Performance of SteamJet with Water/Nitrous Oxide

    Institute of Scientific and Technical Information of China (English)

    王永文; 陈玉春; 周新新; 李舶; 徐杰

    2012-01-01

    为研究水/一氧化二氮组合式射流预冷却涡轮(SteamJet)发动机性能,在建立了射流预冷却的热交换系统计算、物性修正计算、发动机部件特性修正计算和含一氧化二氮的燃烧室计算的数学模型的基础上,建立了基于双轴混排加力式涡扇发动机的水/一氧化二氮组合式SteamJet发动机性能计算模型。在最大加力状态控制规律下,计算分析了SteamJet发动机在水与一氧化二氮不同配比下沿飞行轨道的特性,以及水/一氧化二氮组合式SteamJet发动机的高度速度特性;计算分析了进气系统特性对SteamJet发动机特性的影响。结果表明:与单喷水预冷却的SteamJet发动机相比,水/一氧化二氮组合式SteamJet发动机具有更好的燃烧稳定性和推力特性,能够满足高超声速飞行的需求。%For studying the turbine engine performance of SteamJet with Water/Nitrous Oxide,the mathematical models of the water injection precooling device,the corrected method of physical property,the engine component characteristics computation,and the model of combustion chamber with Nitrous Oxide are built.Based on the models above,the computation model of SteamJet with Water/Nitrous Oxide on basis of the two-spool mix-exhausted turbofan engine with afterburner is built.On the law of the maximum power of SteamJet,the engine characteristics of SteamJet with different proportion of Water/Nitrous Oxide when following flight-trace are calculated.The altitude and velocity characteristics of SteamJet with Water/Nitrous Oxide,and the effect of the inlet characteristics on the engine characteristics are calculated and analyzed as well.Compared with SteamJet without injected oxidizer,SteamJet with injected Water/Nitrous Oxide is of better combustion stability and thrust characteristics,and it can meet the needs of hypersonic flight.

  13. 大鼠正畸牙根吸收早期龈沟液中DPP的变化规律%Dentin phosphoprotein in gingival crevicular fluid during early orthodontic root resorption in rats.

    Institute of Scientific and Technical Information of China (English)

    李文星; 刘月华

    2011-01-01

    目的:构建大鼠正畸牙根吸收模型,检测龈沟液中牙本质磷蛋白(DPP)的浓度变化规律.方法:雌性12周龄SD大鼠46只,其中16只取上颌第一磨牙及牙周组织,通过HE和TRAP染色观察不同时间点根吸收程度;另30只随机分为2组,持续加力28 d(CF组)和加力14 d后停止加力(IF组),收集龈沟液并通过ELISA检测DPP浓度.结果:持续加力14 d,DPP浓度逐渐升高,CF组与IF组间无显著差异(P>0.05);第14 d到28 d,CF组DPP浓度逐渐降低,而IF组DPP浓度在第21 d仍升高,组间有显著差异(P<0.01).根吸收相对面积和DPP浓度显著相关(P<0.05).结论:DPP作为牙的特异性蛋白,与正畸牙根吸收的修复相关,可能是早期诊断正畸牙根吸收的指标.%Objective: This study aimed to establish the animal model of early orthodontic root resorption in rats, and determine whether dentin phosphoprotein (DPP) in gingival crevicular fluid (GFC) could serve as a prognostic factor for orthodontic root resorption. Method:46 12-week- old female SD rats were selected. The maxillary left first molar was drawn medially by applying an excess force. 16 rats were killed and the sections were treated with HE and TRAP histochemistry in the aim of observing the root resorption. The other 30 rats were randomly divided into continuous force group (CF) and the force suspended group (IF) and GFC was collected. The concentrasion of DPP were assayed by using the biochemistry techniques of ELISA. Result:From Od to 14d afterburner,concentration of DPP gradually increased, there were no significant differences between the two groups (P >O.05);from 14 d to 28 d, the concentration of DPP decreased in CF group,while it remained elevated on the 21th day,then reduced a little in IF group. The data between the two groups was statistically significant difference (P <0.01). The relative area of root resorption was correlated to the concentration of DPP,and the Pearson correlation coefficient was 0

  14. Source, Managemnt and Quantification of Unintentional POPs (PCDDD/Fs) in Nepal

    Science.gov (United States)

    Charitra Sah, Ram

    2010-05-01

    production, power generation and cooking using biomass, production of mineral products, transportation, uncontrolled combustion processes production of chemicals and consumer goods, disposal and land filling and miscellaneous. However, it does not account all the sources of the unintentional POPs emission. There are increasing amount of PCDD/Fs emission from other unidentified and/or under estimate sources. An another estimates just for medical waste incineration amount to be 57.37 g TEQ / year based on the current rate of medical waste generation, incineration proportion and considering small box-type batch incinerator with no afterburner as it is mostly adopted in all individual health care institutions. Toward management of POPs, earlier government is not found to be serious as there is still provision of waste incineration in its waste management guidelines including medical waste and has also given Environment Impact Assessment (EIA) clearance to some of the project with waste incineration components. It is important to make the highlight here that the waste incinerator no matter of its art of standards is the indentified major source of unintentional POPs such as PCDD/Fs the known human carcinogen. However, in the recent years, there was increasing concerned of the government as it has come up with the National Implementation Plan (NIP) for Stockholm Convention on Persistent Organic Pollutants with clear identification, prioritization as well as developed program of action linked with monitoring and reporting mechanism. Some of the recent development projects with FAO and GTZ towards realization of the few prioritized plan of action about the sound management of obsolete pesticides including POPs can be considered as remarkable positive progress towards overall development in this field which upon successful implementation will help to improve the country situation. Key words: unintentional POPs, source, management

  15. Comparaison de la performance environnementale de la production thermique d'electricite avec et sans sequestration geologique du dioxyde de carbone

    Science.gov (United States)

    Bellerive, Nathalie

    The research project hypothesis is that CO2 capture and sequestration technologies (CSC) leads to a significant decrease in global warming, but increases the impact of all other aspects of the study. This is because other processes used for CO2 capture and sequestration require additional quantities of raw materials and energy. Two other objectives are described in this project. The first is the modeling of an Integrated Gasification Combined Cycle power plant for which there is no known generic data. The second is to select the right hypothesis regarding electrical production technologies, CO2 capture, compression and transportation by pipeline and finally sequestration. "Life Cycle Assessment" (LCA) analyses were chosen for this research project. LCA is an exhaustive quantitative method used to evaluate potential environmental impacts associated with a product, a service or an activity from resource extraction to waste elimination. This tool is governed by ISO 14 040 through ISO 14 049 and is sustained by the Society of Environmental Toxicology and Chemistry (SETAC) and the United Nations Environment Program (UNEP). Two power plants were studied, the Integrated Gasification Combined Cycle (IGCC) power plant and the Natural Gas Combined Cycle (NGCC) power plant. In order to sequester CO2 in geological formation, it is necessary to extract CO2from emission flows. For the IGCC power plant, CO 2 was captured before the burning phase. For the NGCC power plant, the capture was done during the afterburning phase. Once the CO2 was isolated, it was compressed and directed through a transportation pipe 1 000 km in length on the ground surface and in the sea. It is hypothesized that the power plant is 300 km from the shore and the sequestration platform 700 km from France's shore, in the North Sea. The IGCC power plant modeling and data selection regarding CO2 capture and sequestration were done by using primary data from the industry and the Ecoinvent generic database

  16. Dynamic modelling and characterisation of a solid oxide fuel cell integrated in a gas turbine cycle

    Energy Technology Data Exchange (ETDEWEB)

    Thorud, Bjoern

    2005-07-01

    This thesis focuses on three main areas within the field of SOFC/GT-technology: 1) Development of a dynamic SOFC/GT model. 2) Model calibration and sensitivity study. 3) Assessment of the dynamic properties of a SOFC/GT power plant. The SOFC/GT model developed in this thesis describes a pressurised tubular Siemens Westinghouse-type SOFC, which is integrated in a gas turbine cycle. The process further includes a plate-fin recuperator for stack air preheating, a prereformer, an anode exhaust gas recycling loop for steam/carbon-ratio control, an afterburner and a shell-tube heat exchanger for air preheating. The fuel cell tube, the recuperator and the shell-tube heat exchanger are spatially distributed models. The SOFC model is further thermally integrated with the prereformer. The compressor and turbine models are based on performance maps as a general representation of the characteristics. In addition, a shaft model which incorporates moment of inertia is included to account for gas turbine transients. The SOFC model is calibrated against experimentally obtained data from a single-cell experiment performed on a Siemens Westinghouse tubular SOFC. The agreement between the model and the experimental results is good. The sensitivity study revealed that the degree of prereforming is of great importance with respect to the axial temperature distribution of the fuel cell. Types of malfunctions are discussed prior to the dynamic behaviour study. The dynamic study of the SOFC/GT process is performed by simulating small and large load changes according to three different strategies; 1) Load change at constant mean fuel cell temperature. 2) Load change at constant turbine inlet temperature. 3) Load change at constant shaft speed. Of these three strategies, the constant mean fuel cell temperature strategy appears to be the most rapid load change method. Furthermore, this strategy implies the lowest degree of thermal cycling, the smoothest fuel cell temperature distribution and

  17. Studies of Fission Fragment Rocket Engine Propelled Spacecraft

    Science.gov (United States)

    Werka, Robert O.; Clark, Rodney; Sheldon, Rob; Percy, Thomas K.

    2014-01-01

    The NASA Office of Chief Technologist has funded from FY11 through FY14 successive studies of the physics, design, and spacecraft integration of a Fission Fragment Rocket Engine (FFRE) that directly converts the momentum of fission fragments continuously into spacecraft momentum at a theoretical specific impulse above one million seconds. While others have promised future propulsion advances if only you have the patience, the FFRE requires no waiting, no advances in physics and no advances in manufacturing processes. Such an engine unequivocally can create a new era of space exploration that can change spacecraft operation. The NIAC (NASA Institute for Advanced Concepts) Program Phase 1 study of FY11 first investigated how the revolutionary FFRE technology could be integrated into an advanced spacecraft. The FFRE combines existent technologies of low density fissioning dust trapped electrostatically and high field strength superconducting magnets for beam management. By organizing the nuclear core material to permit sufficient mean free path for escape of the fission fragments and by collimating the beam, this study showed the FFRE could convert nuclear power to thrust directly and efficiently at a delivered specific impulse of 527,000 seconds. The FY13 study showed that, without increasing the reactor power, adding a neutral gas to the fission fragment beam significantly increased the FFRE thrust through in a manner analogous to a jet engine afterburner. This frictional interaction of gas and beam resulted in an engine that continuously produced 1000 pound force of thrust at a delivered impulse of 32,000 seconds, thereby reducing the currently studied DRM 5 round trip mission to Mars from 3 years to 260 days. By decreasing the gas addition, this same engine can be tailored for much lower thrust at much higher impulse to match missions to more distant destinations. These studies created host spacecraft concepts configured for manned round trip journeys. While the

  18. 烧伤后不同类型胶原在增生性瘢痕发生中的作用研究%The function of different collogens in hypertrophic scars

    Institute of Scientific and Technical Information of China (English)

    刘策励; 赵雄飞; 黎鳌; 李世荣

    2001-01-01

    Objective The aim of this study was toinvestigate the dynamic changes of collagen Ⅰ and Ⅲ in the formation of hypertrophic scar afterbum. Method The sirius red and polarizationmicroscopy was used to detected the collagen Ⅰ and Ⅲ fibers in scar tissues in vary periods. Radial immunology assay methods were used to evaluatethe contents of procollagen Ⅰ and Ⅲ in vary periodsin HS tissue. Result Collagen Ⅲ fiber is the main collagen in normalskin. There were no collagen fibers been found in granulation tissue. Collagen Ⅰ increased significantly in scar tissue 1 month after burn, increased much more in 3 months than in 1 month. The collagen were nearly thick collagen Iin HS tissue 1.5 year afterburn and only a little collagen Ⅲ were found. The RIA result showed that the ratio of procollagen Ⅰ/Ⅲ were increased gradually but the contents of collagen Ⅲ were much higher than normal skin. Conclusion In the process of HS forming after burn collagen Ⅰ increase and collagen Ⅲ decrease gradually and at last the collagens in HS were almost collagen Ⅰ. The zchanges of procollagcn can not reflect the changes of collagen fibers.%目的观察烧伤后瘢痕形成过程中Ⅰ、Ⅲ型胶原纤维的动态变化。方法采用苦味酸天狼猩红染色法对不同时期的瘢痕组织进行Ⅰ、Ⅲ型胶原纤维观察,RIA法对瘢痕组织中的Ⅰ、Ⅲ型前胶原进行检测。结果偏光观察正常皮肤中以Ⅲ型纤维为主,1月以后Ⅰ型纤维明显增加,1年以后的瘢痕组织中几乎全部为粗大的Ⅰ型纤维,极少Ⅲ型纤维。放免结果:Ⅰ/Ⅲ型前胶原比例逐渐增加,但Ⅲ型前胶原的含量仍然较高;晚期瘢痕中Ⅰ、Ⅲ型前胶原含量均显著降低。结论烧伤后瘢痕形成过程中Ⅰ型胶原逐渐增加,Ⅲ型胶原逐渐减少,后期几乎完全为Ⅰ型胶原纤维取代,前胶原的变化与胶原纤维的变化不吻合,不能反映胶原纤维的实际情况。

  19. Breakup characteristics of a liquid jet in subsonic crossflow

    Science.gov (United States)

    Gopala, Yogish

    This thesis describes an experimental investigation of the breakup processes involved in the formation of a spray created by a liquid jet injected into a gaseous crossflow. This work is motivated by the utilization of this method to inject fuel in combustors and afterburners of airplane engines. This study aims to develop a better understanding of the spray breakup processes and to provide better experimental inputs to improve the fidelity of numerical models. A review of the literature in this field identified the fundamental physical processes involved in the breakup of the spray and the dependence of spray properties on operating conditions. The time taken for the liquid column to break up into ligaments and droplets, the primary breakup time and the effect of injector geometry on the spray formation processes and spray properties as the key research areas in which research done so far has been inadequate. Determination of the location where the liquid column broke up was made difficult by the presence of a large number of droplets surrounding it. This study utilizes the liquid jet light guiding technique that enables accurate measurements of this location for a wide range of operating conditions. Prior to this study, the primary breakup time was thought to be a function the density ratio of the liquid and the gas, the diameter of the orifice and the air velocity. This study found that the time to breakup of the liquid column depends on the Reynolds number of the liquid jet. This suggests that the breakup of a turbulent liquid jet is influenced by both the aerodynamic breakup processes and the turbulent breakup processes. Observations of the phenomenon of the liquid jet splitting up into two or more jets were made at some operating conditions with the aid of the new visualization technique. Finally, this thesis investigates the effect of injector geometry on spray characteristics. One injector was a round edged orifice with a length to diameter ratio of 1 and a

  20. MOA2—an R&D paradigm buster enabling space propulsion by commercial applications

    Science.gov (United States)

    Frischauf, Norbert; Hettmer, Manfred; Koudelka, Otto; Löb, Horst

    2012-04-01

    More than 60 years after the late Nobel laureate Hannes Alfvén had published a letter stating that oscillating magnetic fields can accelerate ionised matter via magneto-hydrodynamic interactions in a wave like fashion, the technical implementation of Alfvén waves for propulsive purposes has been proposed, patented and examined for the first time by a group of inventors. Consequently improved since then, the name of the latest concept, relying on magneto-acoustic waves to accelerate electric conductive matter, is MOA2—Magnetic field Oscillating Amplified Accelerator. Based on computer simulations, which were undertaken to get a first estimate on the performance of the system, MOA2 is a corrosion free and highly flexible propulsion system, whose performance parameters might easily be adapted in operation, by changing the mass flow and/or the power level. As such the system is capable of delivering a maximum specific impulse of 13116 s (12.87 mN) at a power level of 11.16 kW, using Xe as propellant, but can also be attuned to provide a thrust of 236.5 mN (2411 s) at 6.15 kW of power. First tests—that are further described in this paper—have been conducted successfully with a 400 W prototype system at an ambient pressure of 0.20 Pa, delivered 9.24 mN of thrust at 1472 s ISP, thereby underlining the feasibility of the concept. Based on these results, space propulsion is expected to be a prime application for MOA2—a claim that is supported by numerous applications such as Solar and/or Nuclear Electric Propulsion or even as an 'afterburner system' for Nuclear Thermal Propulsion. However, MOA2 has so far seen most of its R&D impetus from terrestrial applications, like coating, semiconductor implantation and manufacturing as well as steel cutting. Based on this observation, MOA2 resembles an R&D paradigm buster, as it is the first space propulsion system, whose R&D is driven primarily by its terrestrial applications. Different terrestrial applications exist, but

  1. A Collaborative Analysis Tool for Integrated Hypersonic Aerodynamics, Thermal Protection Systems, and RBCC Engine Performance for Single Stage to Orbit Vehicles

    Science.gov (United States)

    Stanley, Thomas Troy; Alexander, Reginald; Landrum, Brian

    2000-01-01

    the process may be repeated altering the trajectory or some other input to reduce the TPS mass. E-PSURBCC is an "engine performance" model and requires the specification of inlet air static temperature and pressure as well as Mach number (which it pulls from the HYFIM and POST trajectory files), and calculates the corresponding stagnation properties. The engine air flow path geometry includes inlet, a constant area section where the rocket is positioned, a subsonic diffuser, a constant area afterburner, and either a converging nozzle or a converging-diverging nozzle. The current capabilities of E-PSURBCC ejector and ramjet mode treatment indicated that various complex flow phenomena including multiple choking and internal shocks can occur for combinations of geometry/flow conditions. For a given input deck defining geometry/flow conditions, the program first goes through a series of checks to establish whether the input parameters are sound in terms of a solution path. If the vehicle/engine performance fails mission goals, the engineer is able to collaboratively alter the vehicle moldline to change aerodynamics, or trajectory, or some other input to achieve orbit. The problem described is an example of the need for collaborative design and analysis. RECIPE is a cross-platform application capable of hosting a number of engineers and designers across the Internet for distributed and collaborative engineering environments. Such integrated system design environments allow for collaborative team design analysis for performing individual or reduced team studies. To facilitate the larger number of potential runs that may need to be made, RECIPE connects the computer codes that calculate the trajectory data, aerodynamic data based on vehicle geometry, heat rate data, TPS masses, and vehicle and engine performance, so that the output from each tool is easily transferred to the model input files that need it.

  2. Current Ground Test Options for Nuclear Thermal Propulsion (NTP)

    Science.gov (United States)

    Gerrish, Harold P., Jr.

    2014-01-01

    (approximately 1 GW) with a maximum burn time of 1 hour. The concept utilized lessons learned from NF-1. The strategy breaks down the exhaust into parallel paths to allow flexibility with engine size and mass flow of exhaust. Similar to NF-1, the exhaust is slowed down, cooled, filtered of particulates, filtered of noble gases, and then the clean hydrogen is flared to open air. Another concept proposed by Steve Howe (currently Director of the Center for Space Nuclear Research) to simplify the NTP exhaust filtering is to run the hydrogen exhaust into boreholes underground to filter the exhaust. The two borehole site locations proposed are at the NTS and at the Idaho National Laboratory (INL). At NTS, the boreholes are 8' diameter and 1200' deep. The permeability of hydrogen through the soil and its buoyancy will allow it to rise up through the soil and allow the filtering of noble gases and radioactive particulates. The exhaust needs to be cooled to 600C before entering the borehole to avoid soil glazing. Preliminary analysis shows a small buildup of back pressure with time which depends on permeability. Noble gases entering the borehole walls deep can take a long time before reaching the surface. Other factors affecting permeability include borehole pressure, water saturation, and turbulence. Also, a possible need to pump out contaminated water collected at the bottom of the borehole. At INL, the borehole concept is slightly different. The underground borehole has openings to the soil at special depths which have impermeable interbeds above the water table and below the surface to allow the exhaust to travel horizontal between the impermeable layers. Preliminary results indicate better permeability than at NTS. The last option is total containment of the exhaust during the test run. The concept involves slowing down the flow to subsonic in a water cooled diffuser. The hydrogen is burned off in an oxygen rich afterburner with the only products being steam, oxygen, and some noble