总焓模拟含水实验介质对双模态燃烧室过程与性能的影响分析
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摘要
为评估燃烧加热设备对冲压发动机地面结果的影响,采用经典准一维方法,考虑燃烧可能存在的化学平衡过程,结合所发展的工作过程物理模型,研究了地面模拟飞行马赫数4~7实验中、氢气-空气加热器采用总焓模拟标准时,含水实验介质对发动机释热与面积匹配、性能潜力的影响规律。结果表明,在模拟总焓条件下,使用略大的燃烧室,燃料比冲数据和纯空气条件较为接近,Ma4~6条件下偏差不超过±1%,Ma7时不超过+3.1%,最大比冲对应的特征马赫数也和纯空气条件相同;但燃烧室所需扩张比、燃烧效率、空气比冲均大于纯空气条件,其中Ma4~7时空气比冲的最大偏差分别达到+2.2%,+4.5%,+8.3%,+14.4%,燃烧效率的偏差分别为+0.7%,+1.9%,+4.2%,+9.4%。这些数据的巧合与矛盾说明,需要在理解实验介质影响规律的基础上,建立纯空气应用时释热工作过程的再设计能力。
To study the effects of vitiated facility on dual-mode scramjet experiment,the difference of dual-mode combustor gasdynamic process and the resulting performance in a water-vitiated test air and pure air is studied. A classical quasi-one dimensional method is used with consideration of possible chemical equilibrium process in combustion and with a self-developed dual-mode combustor gasdynamic process model. It is proposed a H2-air combustion heater provides an enthalpy-simulated test medium by considering the flight Mach number from 4 to 7. The results relate to heat release in different combustor section,the needed combustor dilatation,the possible maximum thrust and specific impulse of fuel. This study show equivalent specific impulse of fuel may be obtained under iso-enthalpy conditions with a little bigger combustors when some special gasdynamic process is realized. The disperse between the two media of fuel specific impulse is no more than 1% for flight Mach number from 4 to 6,and no more than +3.1% for flight Mach number of 7. The corresponding characteristic Mach number in the combustor may be the same for the two media. But the combustor dilatation,combustion efficiency and specific impulse of air are different from pure air condition. The disperse of air specific impulse is+2.2%,+4.5%,+8.3%,+14.4% when flight Mach number varying from 4 to 7,and the disperse of combustion efficiency is +0.7%,+1.9%,+4.2%,+9.4%,respectively. The coincidence and contradiction of the resulting performance values indicate an intense need to establish a fuel-combustor matching design ability with well understanding of test medium effect on the dual-mode ramjet performance and gasdynamic process.
To study the effects of vitiated facility on dual-mode scramjet experiment,the difference of dual-mode combustor gasdynamic process and the resulting performance in a water-vitiated test air and pure air is studied. A classical quasi-one dimensional method is used with consideration of possible chemical equilibrium process in combustion and with a self-developed dual-mode combustor gasdynamic process model. It is proposed a H2-air combustion heater provides an enthalpy-simulated test medium by considering the flight Mach number from 4 to 7. The results relate to heat release in different combustor section,the needed combustor dilatation,the possible maximum thrust and specific impulse of fuel. This study show equivalent specific impulse of fuel may be obtained under iso-enthalpy conditions with a little bigger combustors when some special gasdynamic process is realized. The disperse between the two media of fuel specific impulse is no more than 1% for flight Mach number from 4 to 6,and no more than +3.1% for flight Mach number of 7. The corresponding characteristic Mach number in the combustor may be the same for the two media. But the combustor dilatation,combustion efficiency and specific impulse of air are different from pure air condition. The disperse of air specific impulse is+2.2%,+4.5%,+8.3%,+14.4% when flight Mach number varying from 4 to 7,and the disperse of combustion efficiency is +0.7%,+1.9%,+4.2%,+9.4%,respectively. The coincidence and contradiction of the resulting performance values indicate an intense need to establish a fuel-combustor matching design ability with well understanding of test medium effect on the dual-mode ramjet performance and gasdynamic process.
引文
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[2]John I Erdos.On the Bridge from Hypersonic Aeropropulsion Ground Test Data to Flight Performance[R].AIAA 98-2494.
[3]Ajay Kumar,J Philip Drummond,Charles R Mc Clinton,et al.Research in Hypersonic Airbreathing Propulsion at the NASA Langley Research Center[R].ISABE2001-1007.
[4]Raymond B Edelman,Louis J Spadaccini.Theoretical Effects of Vitiated Air Contamination on Ground Testing of Hypersonic Airbreathing Engines[J].Journal of Spacecraft and Rocket,1969,6(12).
[5]G L Pellett,C Bruno,W Chinitz.Review of Air Vitiation Effects on Scramjet Ignition and Flameholding Combustion Processes[R].AIAA 2002-3880.
[6]RTO Technical Report.Technologies for Propelled Hypersonic Flight,Vol.2-Subgroup 2:Scram Propulsion[R].TR-AVT-007-V2,2006.
[7]Antonella Ingenito,A Moretto,Antonio Agresta.Air Vitiation Effects in Scramjet Engines[R].AIAA 2013-3701.
[8]Junji Noda.Evaluation of Dual-Mode Combustor Characteristics with Vitiated and Non-Vitiated Inflow[R].AIAA 2013-3746.
[9]James C Mc Daniel,Roland H Krauss,W Brad Whitehurst,et al.Test Gas Vitiation Effects in a Dual-Mode Combustor[R].AIAA 2003-6960.
[10]Sadatake Tomioka,Shuuichi Ueda,Kohichiro Tani,et al.Scramjet Engine Tests at Ramjet Engine Test Facility in JAXA-KSPC[R].AIAA 2007-1040.
[11]罗飞腾,宋文艳,刘昊.污染空气对氢燃料超声速燃烧室性能的影响[J].推进技术,2010,31(4).(LUO Fei-teng,SONG Wen-yan,LIU Hao.Experimental Investigation for Vitiated Air Effects on Hydrogen-Fueled Supersonic Combustor Performance[J].Journal of Propulsion Technology,2010,31(4).)
[12]刘昊,宋文艳,罗飞腾.污染空气对乙烯燃料超声速燃烧影响的实验[J].推进技术,2011,32(1).(LIU Hao,SONG Wen-yan,LUO Fei-teng.Experiments on Vitiated Air Effects of Ethylene-Fueled Supersonic Combustion[J].Journal of Propulsion Technology,2011,32(1).)
[13]白菡尘,王泽江,高超声速冲压发动机—飞行器计力体系讨论[J].推进技术,2012,33(1):1-6.(BAI Hanchen,WANG Ze-jiang.Discussion on Force-Accounting System for Airbreathing Hypersonic Vehicle[J].Journal of Propulsion Technology,2012,33(1):1-6.)
[14]李大鹏.煤油双模态冲压发动机燃烧室工作过程研究[D].长沙:国防科技大学,2006.
[15]Chen Jun,Bai Hanchen.Study of the Combustion Organization Method’s Effects on Performance of Ramjet[C].Shanghai:Sino-Russia Hypersonic Flow Conference,2011.
[16]陈军,白菡尘,柳森.化学平衡效应对冲压燃烧室性能潜力与工作过程关系的影响分析[J].推进技术,2013,34(10).(CHEN Jun,BAI Han-chen,LIU Sen.Effects of Chemical Equilibrium on Relation Between Performance and Process for Scramjet Combustor[J].Journal of Propulsion Technology,2013,34(10).)
[17]陈军,白菡尘,柳森.燃烧室工作过程对冲压发动机性能潜力的影响研究[J].实验流体力学,2013,27(3).
[18]Ajay P Kothari,John W Livingston,Christopher Tarpley,et al.Rocket Based Combined Cycle Hypersonic Vehicle Design for Orbital Access[R].AIAA 2011-2338.
[19]Laurent Serre,Sébastien Defoort.Lapcat II:Towardsa Mach8 Civil Aircraft Concept,Using Advanced Rocket/DualMode Ramjet Propulsion System[R].AIAA 2009-7328.
[20]S Weingartner,Sanger.Reference Concept of the German Hypersonic Technology Program[R].AIAA 93-5161.
[21]Ernst Heinrich Hirschel.Basics of Aerothermodynamics[M].Berlin:Springer-Verlag Berlin Heidelberg,2005.