爆震频率对脉冲爆震发动机引射性能影响的实验

黄希桥; 严传俊; 王治武; 范玮; 蒋波

爆震频率对脉冲爆震发动机引射性能影响的实验

西北工业大学动力与能源学院, 西安 710072

基金项目: 国家自然科学基金(5033603050106012);教育部优秀青年教师资助计划和新世纪优秀人才计划(NCET-04-0960)

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出版历程
- 收稿日期: 2007-03-12
- 修回日期: 2007-07-23
- 刊出日期: 2008-03-28

Effect of operating frequency on performance of pulse detonation engine driven ejector

School of Power and EnergyNorthwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 采用汽油为燃料,空气为氧化剂,对多循环脉冲爆震发动机(PDE)加圆直形引射器的增推性能进行了实验研究.实验采用力传感器法对爆震发动机加引射器前后不同爆震频率以及不同引射器长度下的平均推力进行了测量.结果表明:脉冲爆震发动机非稳态引射器可以提高系统的平均推力,当爆震频率为2Hz时平均推力增益最大,可达64.4%.在一定频率下,对直径一定的圆直管引射器存在着一个最佳长径比4.8,此时对应推力增益性能最好.
- 航空、航天推进系统 /
- 脉冲爆震发动机(PDE) /
- 爆震频率 /
- 推力增益 /
- 实验研究
Abstract: A preliminary experimental investigation of the thrust augmentation performance of a round,straight ejector on a multi-cycle pulse detonation engine(PDE) was performed while using gasoline as fuel and air as oxidizers.The average thrusts of the PDEwith ejector and without ejector were measured with thrust transducer at different detonation frequencies and different length-to-diameter ratios of the ejector.The experimental results indicate that ejector system alone can augment the average thrust obtained from the pulse detonation engine.The maximum value of the average thrust augmentation is found to be about 64.4% when the detonation frequency is 25 Hz.The optimal value of the ejector length-to-diameter ratio is 4.58 when the ejector inner diameter and the operation frequency are constant,which corresponds to the best thrust augmentation performance.
- aerospace propulsion system /
- pulse detonation engine(PDE) /
- detonation frequency /
- thrust augmentation /
- experimental study

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参考文献(9)

[1]	Kailasanath K.Recent developments in the research on pulse detonation engines[R].AIAA Paper,2002-0470.
[2]	Porter J L.A summary/overview of ejector augmentor theory and performance[R].ATC Report No.R-91100/9CR-47A,Sept,1979.
[3]	Lockwood R.Interim summary report on investigation of the process of energy transfer from an intermittent jet to secondary fluid in an ejector-type thrust augmenter[R].Hiller Aircraft Report No.ARD-286,March 1961.
[4]	Paxson D E,Wilson J,Dougherty K T.Unsteady ejector performance:An experimental investigation using a pulsejet driver[R].AIAA Paper 2002-3915,July,2002.
[5]	Shehadeh R,Saretto S,Lee S Y,et al.Experimental study of a pulse detonation engine driven ejector[R].AIAA Paper,2003-4972,July 2003.
[6]	Luis G,Robort J,George L,et al.Experimental study of rounded ejector inlets for pulse detonation engines[R].AIAA Paper,2004-14342.
[7]	Shehadeh R,serreto S,Lee S Y,et al.Thrust augmentation measurements for a pulse detonation engine driven ejector[R].AIAA Paper,2004-3398,July 2004.
[8]	黄希桥.改善脉冲爆震发动机性能的实验研究[D].西安:西北工业大学,2006.HUANG Xiqiao.Exploratory investigation on improvingthe performance of pulse detonation engine[DJ.Xi' an:Northwestern Polytechnical University,2006.
[9]	李牧,严传俊,郑龙席,等.脉冲爆震发动机喷管实验研究[J].实验流体力学,2006,20(3):13-17.LI Mu,YAN Chuanjun,ZHENG Longxi,et al.Experimental investigation on pulse detonation engine nozzles[J].Journal of Experiments in Fluid Mechanics,2006,20(3):13-17.