IMECH-IR  > 高温气体动力学国家重点实验室
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
Source PublicationCHINESE JOURNAL OF AERONAUTICS
2020-05-01
Volume33Issue:5Pages:1468-1475
ISSN1000-9361
AbstractA 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.
KeywordShock tunnel Detonation driver Diaphragm Dual ignition High-enthalpy flow
DOI10.1016/j.cja.2020.01.013
Indexed BySCI ; EI ; CSCD
Language英语
WOS IDWOS:000539256800001
WOS KeywordPERFORMANCE
WOS Research AreaEngineering
WOS SubjectEngineering, Aerospace
Funding OrganizationNational Natural Science Foundation of China[11402275] ; National Natural Science Foundation of China[11727901] ; National Natural Science Foundation of China[11472280]
Classification二类/Q1
Ranking1
ContributorLi, Jiwei
Citation statistics
Document Type期刊论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/84787
Collection高温气体动力学国家重点实验室
Affiliation1.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
Recommended Citation
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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