Formation of stabilized oblique detonation waves in a combustor

doi:10.1016/j.combustflame.2020.09.034

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Formation of stabilized oblique detonation waves in a combustor
	Zhang ZJ(张子健)1,2; Wen, Chihyung 3,4; Zhang WS(张文硕)1,2; Liu YF(刘云峰)1,2; Jiang ZL(姜宗林)1,2
刊名	COMBUSTION AND FLAME
	2021
卷号	223 页码:423-436
关键词	Oblique detonation wave Combustor Oblique detonation engine Normal detonation wave Boundary layer separation
ISSN号	0010-2180
DOI	10.1016/j.combustflame.2020.09.034
通讯作者	Liu, Yunfeng(liuyunfeng@imech.ac.cn)
英文摘要	Initiation and stabilization of oblique detonation waves (ODWs) are important to the successful application of oblique detonation engines (ODEs), which, however, have been rarely studied under realistic combustor conditions. In this study, the flow structures, stabilization characteristics and potential thrust performance (under different combustor's geometries with different ODW reflection locations) in a typical hydrogen-fueled ODE combustor are numerically studied by solving the two-dimensional multi-species Reynolds-averaged conservation equations with a detailed hydrogen combustion mechanism. Results suggest that all the detonation waves/shock waves can be stabilized in the space-confined combustor, and the boundary layer separation induced by the ODW-boundary layer interaction is found crucial to determining the types of combustion mode in the combustor. Except for the expected ODW-induced combustion, fast combustion induced by a stabilized overdriven normal detonation wave (NDW) may exist in the combustor simultaneously (even up to a large extent, > 73.7%). It is demonstrated that the stabilization of the overdriven NDW in the combustor can be attributed to the formation of an effective aerodynamic convergent-divergent nozzle that quickly accelerates the subsonic flow behind the NDW to supersonic, preventing downstream disturbances from propagating upstream. Benefiting from the chemical equilibrium shift caused by the expansion effect of the flow, more heat is released to compensate for the compression loss and the simulated thrust performance is shown not deteriorate significantly even with a large percentage of NDW-induced combustion existing in the ODE combustor. This work would be beneficial to the future developments of the ODEs. (C) 2020 The Combustion Institute. Published by Elsevier Inc. All rights reserved.
分类号	一类/力学重要期刊
资助项目	National Natural Science Foundation of China[11672312] ; National Natural Science Foundation of China[11532014] ; National Natural Science Foundation of China[11772284]
WOS关键词	HOT JET ; ADAPTIVE SIMULATIONS ; NUMERICAL-SIMULATION ; OXYGEN MIXTURES ; MACH NUMBER ; WEDGE ; INITIATION ; SHCRAMJET ; SCRAMJET ; INLET
WOS研究方向	Thermodynamics ; Energy & Fuels ; Engineering
语种	英语
WOS记录号	WOS:000599705300004
资助机构	National Natural Science Foundation of China
其他责任者	Liu, Yunfeng
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/85888]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 2.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China; 3.Hong Kong Polytech Univ, Dept Mech Engn, Kowloon, Hong Kong, Peoples R China; 4.Hong Kong Polytech Univ, Interdisciplinary Div Aeronaut & Aviat Engn, Kowloon, Hong Kong, Peoples R China
推荐引用方式 GB/T 7714	Zhang ZJ,Wen, Chihyung,Zhang WS,et al. Formation of stabilized oblique detonation waves in a combustor[J]. COMBUSTION AND FLAME,2021,223:423-436.
APA	张子健,Wen, Chihyung,张文硕,刘云峰,&姜宗林.(2021).Formation of stabilized oblique detonation waves in a combustor.COMBUSTION AND FLAME,223,423-436.
MLA	张子健,et al."Formation of stabilized oblique detonation waves in a combustor".COMBUSTION AND FLAME 223(2021):423-436.