流体力学与飞行力学

爆震室长度对反传影响的数值研究

  • 彭畅新 ,
  • 王治武 ,
  • 郑龙席
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  • 西北工业大学 动力与能源学院, 陕西 西安 710072
彭畅新 男, 博士研究生。主要研究方向: 燃烧学和新概念脉冲爆震发动机应用基础研究。 Tel: 029-88460756 E-mail: mingyueqingxi@163.com;王治武 男, 博士, 副教授, 硕士生导师。主要研究方向: 燃烧学, 流体力学。 Tel: 029-88460756 E-mail: malsoo@mail.nwpu.edu.cn;郑龙席 男, 博士, 教授, 博士生导师。主要研究方向: 航空发动机结构与振动。 Tel: 029-88460756 E-mail: zhenglx@nwpu.edu.cn

收稿日期: 2012-06-19

  修回日期: 2012-12-02

  网络出版日期: 2012-12-05

基金资助

高等学校博士学科点专项科研基金(20116102120027);陕西省自然科学基金(S2010JC3660)

Numerical Investigation of Effect of Detonation Chamber Length on Back-propagation

  • PENG Changxin ,
  • WANG Zhiwu ,
  • ZHENG Longxi
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  • School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2012-06-19

  Revised date: 2012-12-02

  Online published: 2012-12-05

Supported by

Research Fund for the Doctoral Program of Higher Education of China (20116102120027);Natural Science Foundation of Shaanxi Province of China (S2010JC3660)

摘要

对吸气式脉冲爆震发动机(APDE)的反传进行了数值研究,分析了反传的形成及传播特性,得到了爆震室长度对反传的影响。结果表明:反压能够影响整个进气道,缩短爆震室长度有利于降低反压强度。要使反压强度大幅下降,爆震室长度需要大幅缩短。爆震室长度较长时,增长爆震室长度对反压强度影响不大,但会延长进气道的泄压时间。反压会造成进气道内流动反向,反流速度随着爆震室长度增长而增大,爆震室较短时这个趋势更加明显。反传燃气的影响区域明显小于反传压力,当爆震室长度缩短到一定程度时,燃气不会传入进气道。爆震室长度较长时,爆震室上游与进气道下游之间的流道内会出现燃气分布不连续的现象。

本文引用格式

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) : 1001 -1008 . DOI: 10.7527/S1000-6893.2013.0189

Abstract

The phenomenon of back-propagation of an air-breathing pulse detonation engine (APDE) is numerically investigated. The formation and propagation characteristics of the back-propagation phenomenon are analyzed. The effect of the detonation chamber length on back-propagation is analyzed. The results show that the back pressure can influence the whole inlet. Shortening the length of the detonation chamber has the benefit of reducing the back pressure intensity; a substantial decline of back pressure intensity depends on a significant reduction of the detonation chamber length. However, increasing the detonation chamber length has little effect on back pressure intensity when the chamber is relatively long, but it prolongs the pressure release time. The back pressure will cause the flow to reverse in the inlet. The velocity of the reversed flow increases with increasing chamber length, which is more obvious when the chamber length is relatively short. The hot gas covers a much smaller region than the back pressure. The hot gas will not travel into the inlet when the chamber length is short enough. The distribution of the hot gas will be discontinuous in the region between the upstream chamber and downstream inlet.

参考文献

[1] Yan C J, Fan W. Principle and key technologies of pulse detonation engine. Xi'an: Northwestern Polytechnical University Press, 2005. (in Chinese) 严传俊, 范玮. 脉冲爆震发动机原理及关键技术. 西安: 西北工业大学出版社, 2005.
[2] Kailasanath K. Research on pulse detonation combustion systems-a status report. AIAA-2009-631, 2009.
[3] Gustavsson J, Nori V, Segal C. Inlet/engine interaction in an axisymmetric pulse detonation engine system. Journal of Propulsion and Power, 2003, 19(2): 282-286.
[4] Nori V, Lerma N, Gustavsson J, et al. Forced oscillations in a mixed-compression inlet at Mach 3.5 for pulse detonation engine systems. Journal of Fluids Engineering, 2006, 128(3): 494-506.
[5] Cooper M, Jewell J, Shepherd J E. The effect of a porous thrust surface on detonation tube impulse. AIAA-2003-4822, 2003.
[6] Ma F H, Choi J Y, Yang V. Numerical modeling of valveless airbreathing pulse detonation engine. AIAA-2005-227, 2005.
[7] Brophy C M, Werner L S, Sinibaldi J O. Performance characterization of a valveless pulse detonation engine. AIAA-2003-1344, 2003.
[8] Ma F M, Choi J Y, Yang V. Internal flow dynamics in a valveless airbreathing pulse detonation engine. Journal of Propulsion and Power, 2008, 24(3): 479-489.
[9] Rasheed A, Furman A H, Dean A J. Pressure measurements and attenuation in a hybrid multitube pulse detonation turbine system. Journal of Propulsion and Power, 2009, 25(1): 148-161.
[10] Ripley R C, Harris P G, Farinaccio R. Multi-tube two-dimensional evaluation of a pulse detonation engine as a ramjet replacement. AIAA-2004-3745, 2004.
[11] Li J Z, Wang J H, Tang H, et al. Kerosene/air triple-tube aero-valve pulse detonation engine. Acta Aeronautica et Astronautica Sinica, 2009, 30(11): 2052-2058. (in Chinese) 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. 航空学报, 2009, 30(11): 2052-2058.
[12] Yuan C, Fan W, Peng C X, et al. Experimental investigation on a six-tube air-breathing pulse detonation engine. Journal of Aerospace Power, 2011, 26(9): 1981-1985. (in Chinese) 袁成, 范玮, 彭畅新, 等. 六管吸气式脉冲爆震发动机试验. 航空动力学报, 2011, 26(9): 1981-1985.
[13] Li J Z, Wang J H. Aerovalves of kerosene/air pulse detonation engine. Journal of Nanjing University of Aeronautics & Astronautics, 2008, 40(3): 279-283. (in Chinese) 李建中, 王家骅. 煤油/空气脉冲爆震发动机气动阀研究. 南京航空航天大学学报, 2008, 40(3): 279-283.
[14] Zheng D F, Yang Y Y, Wang J H. Design and experimental study whirl aero-valve for pulse detonation engine. Journal of Aerospace and Power, 2010, 25(7): 1471-1477. (in Chinese) 郑殿峰, 杨义勇, 王家骅, 等. 脉冲爆震发动机旋流式气动阀的设计与实验. 航空动力学报, 2010, 25(7): 1471-1477.
[15] Wen Y F, Tan H J, Li J Z, et al. Investigation on the inlet flow characteristics of a pulse detonation engine with aerodynamic valve. Acta Aeronautica et Astronautica Sinica, 2012, 33(1): 44-53. (in Chinese) 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. 航空学报, 2012, 33(1): 44-53.
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