Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner

doi:10.1017/jfm.2022.226

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

	Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner
	Zhang, Zijian 3; Liu YF(刘云峰)1,2; Wen, Chihyung 3
刊名	JOURNAL OF FLUID MECHANICS
	2022-04-11
卷号	940 页码:39
关键词	detonation waves
ISSN号	0022-1120
DOI	10.1017/jfm.2022.226
通讯作者	Wen, Chihyung(cywen@polyu.edu.hk)
英文摘要	The stabilization of oblique detonation waves (ODWs) in an engine combustor is important for the successful applications of oblique detonation engines, and comprehensively understanding the effects of the inviscid reflection of ODWs on their stabilization and the relevant mechanisms is imperative to overall combustor design. In this study, the flow fields of ODW reflections in a space-confined combustor are numerically studied by solving the two-dimensional time-dependent multispecies Euler equations in combination with a detailed hydrogen combustion mechanism. The inviscid Mach reflections of ODWs before an expansion corner are emphasized with different flight Mach numbers, Ma, and different dimensionless reflection locations, zeta >= 0 (zeta = 0: the ODW reflects precisely at the expansion corner; zeta > 0: the ODW reflects off the wall before the expansion corner). Two kinds of destabilization phenomena of the inviscid Mach reflection of an ODW induced by different mechanisms are found, namely wave-induced destabilization at large zeta > 0 for moderate (not very low) Ma and inherent destabilization at any zeta > 0 for low Ma. Wave-induced destabilization is attributed to the incompatibility between the pressure ratio across the Mach stem and its relative propagation speed, which is triggered by the action of the secondary reflected shock wave or the transmitted Mach stem on the subsonic zone behind the Mach stem. Inherent destabilization is demonstrated through an in-depth theoretical analysis and is attributed to geometric choking of the flow behind the Mach stem.
分类号	一类/力学重要期刊
资助项目	National Natural Science Foundation of China[11772284] ; National Natural Science Foundation of China[11672312] ; National Natural Science Foundation of China[11532014]
WOS关键词	ACETYLENE-OXYGEN MIXTURES ; SUPERSONIC COMBUSTION ; ADAPTIVE SIMULATIONS ; INITIATION ; PROPULSION ; TRANSITION ; WEDGE ; FLOW ; STABILIZATION ; CHALLENGES
WOS研究方向	Mechanics ; Physics
语种	英语
WOS记录号	WOS:000780390900001
资助机构	National Natural Science Foundation of China
其他责任者	Wen, Chihyung
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/88832]
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 Aeronaut & Aviat Engn, Kowloon, Hong Kong, Peoples R China;
推荐引用方式 GB/T 7714	Zhang, Zijian,Liu YF,Wen, Chihyung. Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner[J]. JOURNAL OF FLUID MECHANICS,2022,940:39.
APA	Zhang, Zijian,刘云峰,&Wen, Chihyung.(2022).Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner.JOURNAL OF FLUID MECHANICS,940,39.
MLA	Zhang, Zijian,et al."Mechanisms of the destabilized Mach reflection of inviscid oblique detonation waves before an expansion corner".JOURNAL OF FLUID MECHANICS 940(2022):39.