Study on the propulsive performance of oblique detonation engine

doi:10.1016/j.energy.2024.130519

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

	Study on the propulsive performance of oblique detonation engine
	Liu YF(刘云峰)1; Han, Xin 2; Zhang, Zijian 3
刊名	ENERGY
	2024-04-01
卷号	292 页码:11
关键词	Oblique detonation engine ODE Propulsive performance Specific impulse
ISSN号	0360-5442
DOI	10.1016/j.energy.2024.130519
通讯作者	Liu, Yunfeng(liuyunfeng@imech.ac.cn)
英文摘要	The oblique detonation engine (ODE) has established a clear superiority for hypersonic flight because of its high thermal efficiency and compact structure. It has become the research hot spot all over the world in recent years. The aim of this study is to derive a criterion on the propulsive balance of ODE, from which we can find the key parameters governing the propulsive performance explicitly. A physical model of ODE is put forth, which consists of the inlet, the constant cross-section combustor and the divergent nozzle. The mathematical equations to calculate the thrust generated by the divergent nozzle and the pressure drag produced by the inlet are deduced. The net thrust of ODE is then obtained. The criterion shows clearly that the static temperature at the engine inlet exit is a very important parameter. The lower the inlet exit temperature is, the higher the specific impulse will be. The specific impulse of ODE with stoichiometric H2/air mixture and hydrocarbon/air mixture are calculated by using these equations. The results show that ODE can obtain positive net thrust from Ma8 to Ma15.
分类号	一类
资助项目	National Natural Science Foundation of China[11672312]
WOS关键词	SHOCK-INDUCED COMBUSTION ; INDUCED SUPERSONIC COMBUSTION ; WAVE
WOS研究方向	Thermodynamics ; Energy & Fuels
语种	英语
WOS记录号	WOS:001173971100001
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/311007/94613]
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.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China; 2.Xiamen Univ, Sch Aerosp Engn, Xiamen 361102, Peoples R China; 3.Hong Kong Polytech Univ, Dept Aeronaut & Aviat Engn, Hong Kong 999077, Peoples R China
推荐引用方式 GB/T 7714	Liu YF,Han, Xin,Zhang, Zijian. Study on the propulsive performance of oblique detonation engine[J]. ENERGY,2024,292:11.
APA	刘云峰,Han, Xin,&Zhang, Zijian.(2024).Study on the propulsive performance of oblique detonation engine.ENERGY,292,11.
MLA	刘云峰,et al."Study on the propulsive performance of oblique detonation engine".ENERGY 292(2024):11.