Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode
文献类型：期刊论文
| 作者 | Wang Q(汪球)2 ; Luo K(罗凯)1,2; Li JW(栗继伟)2; Li JP(李进平)2; Zhao W(赵伟)1,2
|
| 刊名 | CHINESE JOURNAL OF AERONAUTICS
 |
| 出版日期 | 2020-05-01 |
| 卷号 | 33期号:5页码:1468-1475 |
| 关键词 | Shock tunnel Detonation driver Diaphragm Dual ignition High-enthalpy flow |
| ISSN号 | 1000-9361 |
| DOI | 10.1016/j.cja.2020.01.013 |
| 英文摘要 | 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. |
| 分类号 | 二类/Q1 |
| WOS关键词 | PERFORMANCE |
| WOS研究方向 | Engineering |
| 语种 | 英语 |
| WOS记录号 | WOS:000539256800001 |
| 资助机构 | National Natural Science Foundation of China[11402275] ; National Natural Science Foundation of China[11727901] ; National Natural Science Foundation of China[11472280] |
| 其他责任者 | Li, Jiwei |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/84787]  |
| 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, State Key Lab High Temp Gas Dynam, Beijing 100190, 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. |
入库方式： OAI收割
来源：力学研究所
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