Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection

doi:10.1016/j.ast.2020.106054

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

	Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection
	Zhang ZJ(张子健)1,2; Ma KF(马凯夫)1,2; Zhang WS(张文硕)1,2; Han X(韩鑫)1,2; Liu YF(刘云峰)1,2; Jiang ZL(姜宗林)1,2
刊名	AEROSPACE SCIENCE AND TECHNOLOGY
	2020-10-01
卷号	105 页码:9
关键词	Oblique detonation engine Pre-injection Detonative combustion Mixing Hydrogen
ISSN号	1270-9638
DOI	10.1016/j.ast.2020.106054
通讯作者	Liu, Yunfeng(liuyunfeng@imech.ac.cn)
英文摘要	In this study, the performances of a Mach 9 oblique detonation engine fueled by hydrogen are numerically investigated by solving the multi-species reactive Reynolds-averaged Navier-Stokes (RANS) equations with a detailed combustion mechanism. The fuel is perpendicularly pre-injected into the core airflow in the engine inlet by three parallel strut-injectors. It is demonstrated that mixing can be enhanced by the baroclinic effect of oblique shock waves, the incipient expansion of fuel jets and the intensive momentum exchange of vertical jets into the crossflow, resulting in a well-mixed fuel-air core flow before entering the combustor. Analyses of the two most dangerous zones that bear potential of pre-ignition suggest that no pre-combustion occurs in the inlet. Benefiting from the floor bleed structure, the upstream movement of the shock waves stops at the combustor's entrance and they remain stabilized in the combustor thereafter. Finally, the combustor is proved to work under the stable detonation mode of combustion, and the supersonic fuel-air mixture is fast burnt through the steady detonation waves generated in the combustor. The concept of the pre-injection oblique detonation engine has been numerically demonstrated, which provides a significant reference to further experimental studies and future engineering applications. (C) 2020 Elsevier Masson SAS. All rights reserved.
分类号	一类
资助项目	National Natural Science Foundation of China[11672312] ; National Natural Science Foundation of China[11532014]
WOS关键词	SHOCK-INDUCED COMBUSTION ; OXYGEN MIXTURES ; WAVES ; HYDROGEN ; WEDGE ; INITIATION ; SHCRAMJET ; PERFORMANCE ; TRANSITION ; SCRAMJET
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000573516700005
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/311007/85321]
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
推荐引用方式 GB/T 7714	Zhang ZJ,Ma KF,Zhang WS,et al. Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2020,105:9.
APA	张子健,马凯夫,张文硕,韩鑫,刘云峰,&姜宗林.(2020).Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection.AEROSPACE SCIENCE AND TECHNOLOGY,105,9.
MLA	张子健,et al."Numerical investigation of a Mach 9 oblique detonation engine with fuel pre-injection".AEROSPACE SCIENCE AND TECHNOLOGY 105(2020):9.