Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode

doi:10.1016/j.cja.2020.01.013

	Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode
	Wang Q(汪球)1 ; Luo K(罗凯)1,2 ; Li JW(栗继伟)1; Li JP(李进平)1 ; Zhao W(赵伟)1,2
发表期刊	CHINESE JOURNAL OF AERONAUTICS
	2020-05-01
卷号	33 期号:5 页码:1468-1475
ISSN	1000-9361
摘要	A detonation-driven shock tunnel is useful as a ground test facility for hypersonic flow research. The forward detonation driving mode is usually used to achieve high-enthalpy flows due to its strong driving capability. Unfortunately, the strong detonation wave front results in diaphragm fragments that disturb the test flow and scratch the nozzle or test models. In this study, a dual ignition system was developed to burst a metal diaphragm without fragmentation in the forward driving mode. A series of experiments were conducted to validate the proposed technique. The influences of the delay time setting on the test conditions were investigated in detail. Numerical simulations were also conducted to obtain a better understanding of the wave processes in the shock tube. The results showed that the dual ignition system solved the diaphragm issues in the forward driving mode. The test time was shortened due to the additional ignition close to the primary diaphragm; the smaller the delay time, the shorter the effective test time. However, a small amount of time loss is considered worthwhile because the severe diaphragm problems have been solved. (C) 2020 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.
关键词	Shock tunnel Detonation driver Diaphragm Dual ignition High-enthalpy flow
DOI	10.1016/j.cja.2020.01.013
收录类别	SCI ; EI ; CSCD
语种	英语
WOS记录号	WOS:000539256800001
关键词[WOS]	PERFORMANCE
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
项目资助者	National Natural Science Foundation of China[11402275] ; National Natural Science Foundation of China[11727901] ; National Natural Science Foundation of China[11472280]
论文分区	二类/Q1
力学所作者排名	1
RpAuthor	Li, Jiwei
引用统计	被引频次：8[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/84787
专题	高温气体动力学国家重点实验室
作者单位	1.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China; 2.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China
推荐引用方式 GB/T 7714	Wang Q,Luo K,Li JW,et al. Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode[J]. CHINESE JOURNAL OF AERONAUTICS,2020,33,5,:1468-1475.
APA	汪球,罗凯,栗继伟,李进平,&赵伟.(2020).Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode.CHINESE JOURNAL OF AERONAUTICS,33(5),1468-1475.
MLA	汪球,et al."Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode".CHINESE JOURNAL OF AERONAUTICS 33.5(2020):1468-1475.

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