多管脉冲爆震发动机压力反传特性试验与数值研究

推进技术 ›› 2014, Vol. 35 ›› Issue (11): 1558-1565.

多管脉冲爆震发动机压力反传特性试验与数值研究

卢　杰,郑龙席,王治武,彭畅新,陈星谷

西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:卢　杰(1988—)，男，博士生，研究领域为爆震推进技术、发动机燃烧与流动。
基金资助:
国家自然科学基金(51306153)；陕西省自然科学基金(2010JQ7005)。

Experimental and Numerical Investigation on Propagation of Back-Pressure Waves of a Four-Tube Pulse Detonation Engine

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究多管脉冲爆震发动机的压力反传特性，采用数值模拟和试验相结合的方法对四管爆震室的压力反传特性进行研究，测量了四管爆震室同时点火和分时点火这两种工作模式下的压力反传规律，利用数值模拟对四管爆震室共用进气道进行研究，分析了共用进气道长度以及在共用进气道内加装分流板对压力反传的影响。试验结果表明，四管爆震室同时工作时，共用进气道产生一道很强的压力扰动波，其峰值压力接近0.12MPa；四管爆震室分时工作时，共用进气道在一个循环内出现四次压力扰动，但扰动波的峰值压力较小。数值模拟的结果表明，在两种工作模式下，爆震室产生的反传压力使发动机入口产生高速倒流，四管分时工作时倒流的速度较小。随着共用进气道的长度增大，反传压力的峰值降低，但发动机入口处仍然存在倒流现象，倒流的速度随着共用进气道的长度增大而减小。共用进气道内加装分流板对反传压力的峰值并没有削弱作用。

关键词: 多管脉冲爆震燃烧室；压力反传；试验；数值模拟；倒流；共用进气道

Abstract: In order to investigate the propagation characteristics of back-pressure waves in multi-tube pulse detonation engine，a series of experiments and numerical simulations were carried out. The propagation characteristics of back-pressure waves of four-tube pulse detonation combustors were measured when the combustors operated at two firing patterns: all tubes firing simultaneously and all tubes firing sequentially. Numerical simulations were carried out to investigate the flow characteristics in the air buffer chamber. The length of the air buffer chamber was varied and a splitter was installed in the air buffer chamber numerically to study their effects on the propagation of back-pressure waves. The experimental results show that a strong back-pressure wave was observed in the air buffer chamber when all tubes were fired simultaneously and the peak value was about 0.12MPa. However，when all tubes were fired sequentially，the air buffer chamber experienced four times pressure oscillation in a single cycle and the amplitude was smaller than that when all tubes were fired simultaneously. The numerical results indicate that there was a reverse flow in the engine inlet when the back-pressure wave propagated into the air inlet. The velocity of reverse flow was smaller when the tubes were operated at sequential firing pattern. The amplitude of the back-pressure waves was reduced when the length of air buffer chamber increased. The velocity of reverse flow was also reduced. No reduction of amplitude of the back-pressure waves was observed when the splitter was installed in the air buffer chamber.

Key words: Multi-tube pulse detonation combustor；Back-pressure wave；Experiment；Numerical simulation；Reverse flow；Air buffer chamber

卢　杰,郑龙席,王治武,彭畅新,陈星谷. 多管脉冲爆震发动机压力反传特性试验与数值研究[J]. 推进技术, 2014, 35(11): 1558-1565.

LU Jie,ZHENG Long-xi,WANG Zhi-wu,PENG Chang-xin,CHEN Xing-gu. Experimental and Numerical Investigation on Propagation of Back-Pressure Waves of a Four-Tube Pulse Detonation Engine[J]. Journal of Propulsion Technology, 2014, 35(11): 1558-1565.

参考文献

[1] Ma F M, Choi J Y, Vigor Y. Internal Flow Dynamics in a Valveless Airbreathing Pulse Detonation Engine [J]. Journal of Propulsion and Power, 2008, 24(3).
[2] Glaser A, Rasheed A, Dunton R, et al. Investigations of Thrust Generated by a Valved, Multi-Tube PDE with Exit Nozzles[R]. AIAA 2008-4692.
[3] Glaser A J, Rasheed A, Dunton R, et al. Measurement of Pressure-Rise in a Pulse Detonation Engine[R]. AIAA 2009-857.
[4] Jonas G, Venkata N, Corin S. Inlet/Engine Interaction in an Axisymmetric Pulse Detonation Engine System [J]. Journal of Propulsion and Power, 2003, 19(2).
[5] Brophy C M, Werner S, Sinibaldi J O. Performance Characterization of a Valveless Pulse Detonation Engine [R]. AIAA 2003-1344.
[6] Ma F H, Jeong Y C, Vigor Y. Numerical Modeling of Valveless Airbreathing Pulse Detonation Engine [R]. AIAA 2005-227.
[7] Rasheed A, Furman A, Dean A J. Experimental Investigations of an Axial Turbine Driven by a Multi-Tube Pulsed Detonation Combustor System [R]. AIAA 2005-4209.
[8] Adam R, Anthony H F, Anthony J D. Pressure Measurements and Attenuation in a Hybrid Multitube Pulse Detonation Turbine System [J]. Journal of Propulsion and Power, 2009, 25(1).
[9] Ripley R C, Harris P G, Farinaccio R. Multi-Tube Two-Dimensional Evaluation of a Pulse Detonation Engine as a Ramjet Replacement[R]. AIAA 2004-3745.
[10] 温玉芬, 谭慧俊, 李建中, 等. 某气动阀式脉冲爆震发动机进气道流动特性研究[J]. 航空学报, 2012, 33(1).
[11] 彭畅新, 王治武, 郑龙席.爆震室长度对反传影响的数值研究[J].航空学报, 2013, 34(5).
[12] 彭畅新, 王治武, 郑龙席, 等. 吸气式脉冲爆震发动机反压传播规律研究[J]. 推进技术, 2013 34(2).(PENG Chang-xin, WANG Zhi-wu, ZHENG Long-xi. et al. Investigation on Propagation of Back-Pressure in Air-Breathing Pulse Detonation Engine[J]. Journal of Propulsion Technology, 2013, 34(2).)
[13] 袁成, 范玮, 彭畅新, 等. 六管吸气式脉冲爆震发动机试验[J]. 航空动力学报, 2011, 26(9).
[14] 李建中, 王家骅, 唐豪, 等. 煤油/空气三管气动阀式脉冲爆震发动机[J]. 航空学报, 2009, 30(11).
[15] Peng C, Fan W, Zheng L, et al. Experimental Investigation on Valveless Air-Breathing Dual-Tube Pulse Detonation Engines[J].Applied Thermal Engineering, 2013,51(1-2).(编辑:梅瑛)　　　　　　　　　　　　　　收稿日期:2013-10-11；修订日期:2013-11-27。基金项目:国家自然科学基金(51306153)；陕西省自然科学基金(2010JQ7005)。作者简介:卢杰(1988—),男,博士生,研究领域为爆震推进技术、发动机燃烧与流动。E-mail:lujie2012@mail.nwpu.edu.cn