部分充填下脉冲爆震发动机的热力循环性能分析

邱华; 严传俊; 范玮

部分充填下脉冲爆震发动机的热力循环性能分析

1.
西北工业大学力学与土木建筑学院, 西安 710072
2.
西北工业大学能源与动力学院, 西安 710072

基金项目: 国家自然科学基金项目(50106012,50336030)

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出版历程
- 收稿日期: 2007-04-02
- 修回日期: 2007-08-06
- 刊出日期: 2008-04-28

Analysis on thermodynamic performance of partially-fueled pulse detonation engine

1.
School of Mechanics, Civil Engineering and Architecture, Northwestern Polytechnical University, Xi'an 710072
2.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072

摘要

摘要: 在完全充填脉冲爆震发动机的Ficket-Jacobs热力循环的基础上,提出了用于分析部分充填下脉冲爆震发动机的热力循环性能的分析方法.结果表明,部分充填的工作方式会降低发动机总的热力循环效率,当爆震燃烧用于功率输出时,这种工作形式是应该避免的;但另一方面,由于部分充填的工作方式使爆震燃烧释放的能量在燃烧产物和隔离气体间重新分配,这种工作形式可以提高脉冲爆震发动机的总效率.
- 航空、航天推进系统 /
- 脉冲爆震发动机 /
- 部分充填 /
- 热力循环
Abstract: Ideal partially-fueled detonation cycle model was established based on FicketJacobs cycle.It is shown that partial fuel filling will cause decrease of total thermal efficiency,which means that this work mode is not adequate to the application of detonation for power output.However,as energy exchange between combustion products and purge gas occurs during the expansion of the detonation products under this mode,it can be used to enhance the propulsive efficiency of PDE.
- aerospace propulsion system /
- pulse detonation engine(PDE) /
- partially-fueled /
- thermodynamic cycle

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参考文献(14)

[1]	Zel'dovich YaB J.On the use of detonative combustion in power engineering[J].Journal of Technical Physics,1940,10(17):1455-1461.
[2]	Kentfield J A C.The thermodynamics of air-breathing pulse-detonation engines[R].AIAA 2001-3982.
[3]	Heiser W H.Thermodynamic cycle analysis of pulse detonation engines[J].Journal of Propulsion and Power,2002,18(1):68-76.
[4]	Dyer R S,Kaemming T A.The thermodynamic basis of pulsed detonation engine thrust production[R].AIAA 2002-4072.
[5]	Wintenberger E,Shepherd J E.Thermodynamic analysis of combustion processes for propulsion system[R].AIAA 2004-1033.
[6]	Fickett W,Davis W C.Detonation theory and experiment[M].New York:Dover Publications Inc.,Mineloa,2001.
[7]	Jacobs S J.The energy of detonation[R].NAVORD Report 4366,U.S.Naval Ordnance Laboratory,White Oak,MD.Available as NTIS AD113271-Old Series.
[8]	Zhdan S A,Mitrofanov V V,Sychev A I.Reactive impulse from the explosion of a gas mixture in a semi-infinite space[J].Combustion,Explosion and Shock Waves,1994,30(5):657-663.
[9]	Zitou R,Desbordes D.Propulsive performance of pulsed detonations[J].Comb.Sci.Tech,1999,144:93-114.
[10]	Cooper M,Jackson S,Austin J,et al.Direct experimental impulse measurements for deflagrations and detonations[R].AIAA 2001-3812.
[11]	Falempin F,Bouchaud D,Forrat B,et al.Pulsed detonation engine possible application to low cost tactical missile and to space laucher[R].AIAA 2001-3815.
[12]	Li C,Kailasanath K.Performance analysis of pulse detonation engines with partial fuel filling[J].Journal of Propulsion and Power,2003,19(5):908-916.
[13]	Endo T,Yatsufusa T,Taki S,et al.Homogeneous-dilution model of partiallly-fueled pulse detonation engines[R].AIAA 2004-1214.
[14]	邱华,严传俊,熊姹.自吸气脉冲爆震发动机热力循环及系统性能分析[C]//中国航空学会第十三届燃烧与传热传质专业学术讨论会论文集.昆明:中国航空学会,2005:76-83.