| 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
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| Corresponding Author | Liu, Yunfeng(liuyunfeng@imech.ac.cn) |
| Source Publication | AEROSPACE SCIENCE AND TECHNOLOGY
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| 2020-10-01 | |
| Volume | 105Pages:9 |
| ISSN | 1270-9638 |
| Abstract | 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. |
| Keyword | Oblique detonation engine Pre-injection Detonative combustion Mixing Hydrogen |
| DOI | 10.1016/j.ast.2020.106054 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000573516700005 |
| WOS Keyword | SHOCK-INDUCED COMBUSTION ; OXYGEN MIXTURES ; WAVES ; HYDROGEN ; WEDGE ; INITIATION ; SHCRAMJET ; PERFORMANCE ; TRANSITION ; SCRAMJET |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Natural Science Foundation of China[11672312] ; National Natural Science Foundation of China[11532014] |
| Funding Organization | National Natural Science Foundation of China |
| Classification | 一类 |
| Ranking | 1 |
| Contributor | Liu, Yunfeng |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/85322 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China; 2.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China |
| Recommended Citation 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. |
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| Jp2020321.pdf（2608KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
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