高温超声速流中爆震波特性数值研究

推进技术 ›› 2012, Vol. 33 ›› Issue (4): 541-546.

高温超声速流中爆震波特性数值研究

黄思源,桂业伟,白菡尘

中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,四川绵阳 621000; 中国空气动力研究与发展中心,四川绵阳 621000;中国空气动力研究与发展中心,四川绵阳 621000;中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,四川绵阳 621000; 中国空气动力研究与发展中心,四川绵阳 621000

发布日期:2021-08-15
作者简介:黄思源(1981—),男,博士,研究领域为湍流模式与燃烧。E-mail:huangsiyuan@tsinghua.org.cn

Numerical Research on Detonation Wave Characteristic in HighTemperature Supersonic Flow

Science and Technology on Scramjet Laboratory,China Aerodynamics Research and Development Center, Mianyang 621000,China ; China Aerdynamics Research and Development Center, Mianyang 621000,China;China Aerdynamics Research and Development Center, Mianyang 621000,China;Science and Technology on Scramjet Laboratory,China Aerodynamics Research and Development Center, Mianyang 621000,China ; China Aerdynamics Research and Development Center, Mianyang 621000,China

Published:2021-08-15

摘要/Abstract

摘要： 通过对高温超声速流中爆震波性质的研究,评估其在高超声速冲压发动机燃烧室的燃烧组织中应用的可行性,并通过数值模拟对分析结论进行了验证。提出了一种新的爆震波起爆机制,注入高温超声速流中的燃料混气可通过自身缓慢的释热使流动进入局域热壅塞状态,进而借助局域热壅塞产生的激波实现爆震波的起爆。计算结果表明在适宜的温度与马赫数条件下,注入高温超声速流中的燃料可通过新的起爆机制在超声速流中形成一道稳定的驻定爆震波。表明在高超声速冲压发动机燃烧室中存在着通过驻定爆震波实现火焰稳定的可能性。

关键词: 热壅塞;爆震波;起爆机制

Abstract: To evaluate the feasibility for utilizing the detonation wave to stabilize flame in scramjet combustor,the detonation wave characteristic in high temperature environment was studied by numerical simulations. A new initiation mechanism of detonation was presented. The premixed gas injected into high temperature supersonic flow can reach local thermal choking state through the heat released by slow reaction of premixed fuel gas and then a detonation wave can be initiated by shock produced in thermal choking state. The numerical results show that the fuel injected into high temperature supersonic flow can form a standing detonation wave by the new mechanism in some special temperature and Mach number flow conditions. The research shows that it is possible utilizing the standing detonation wave to stabilize flame in scramjet combustor. 

Key words: Thermal choking; Detonation wave; Initiation mechanism

黄思源,桂业伟,白菡尘. 高温超声速流中爆震波特性数值研究[J]. 推进技术, 2012, 33(4): 541-546.

参考文献

[2] Rubins P M,Bauer R C.Review of Shock-Induced Supersonic Combustion Research and Hypersonic Applications[J].Journal of Propulsion and Power,4,0(5):593-601.
[3] Eidelman S,Grossmann W.Pulsed Detonation Engine:Experimental and Theoretical Review[R]. AIAA 92-3168.
[4] Carrier G F, Fendell F, McGregor D,et al.Laser-Initiated Conical Detonation Wave for Supersonic Combustion[R].AIAA 91-0578.
[5] Fendell F E,Mitchell J,McGregor R,et al.Laser-Initiated Conical Detonation Wave for Supersonic Combustion.II[R].AIAA 92-0088.
[6] Seiler F, Patz G, Smeets G,et al.Influence of Projectile Material and Gas Composition on Superdetonative Combustion in ISL’s RAMAC30[R].AIAA 98-3445.
[7] Humphrey J W.Parametric Study of an ODW Scramaccelerator for Hypersonic Test Facilities[R].AIAA 90-2470.
[8] Li C, Kailasanath K, Oran E S,et al.Numerical Simulations of Transient Flows in Ram Accelerators[R].AIAA 93-1916.
[9] Choi J Y, Jeung I S, Yoon Y.Numerical Study of Scram Accelerator Starting Characteristics[J].AIAA Journal,8,6(6):1029-1038.
[10] Ting J M, Bussing T R A,Hinkey J B.Experimental Characterization of the Detonation Properties of Hydrocarbon Fuels for the Development of a Pulse Detonation Engine[R].AIAA 95-3154.
[11] Sterling J, Ghorbanian K,Sobota T.Enhanced Combustion Pulsejet Engines for Mach 0 to 3 Applications[R]. AIAA 96-2687.
[12] Eidelman S,Yang X.Analysis of the Pulse Detonation Engine Efficiency[R].AIAA 98-3877.
[13] Ciccarelli G,Dubocage P.Flame Acceleration in Fuel-air Mixtures at Elevated Initial Temperatures[R]. AIAA 2002-4020.
[14] Chapin D M, Tangirala V E, Dean A J.Ignition and Detonation of Moving Hydrogen-air Mixtures at Elevated Temperature and Pressure[R].AIAA 2007-236.
[15] Lin Z Y.Investigation of Detached Detonation Induced by Oblique Shock in Premixed Supersonic flow[J].Journal of Aerospace Power, 9,4(1).