| Criteria for hypersonic airbreathing propulsion and its experimental verification | |
Jiang ZL(姜宗林)1,2 ; Zhang ZJ(张子健)1,2; Liu YF(刘云峰)1,2; Wang C(王春)1,2; Luo ZT(罗长童)1,2
| |
| Corresponding Author | Jiang, Zonglin([email protected]) |
| Source Publication | CHINESE JOURNAL OF AERONAUTICS
 |
| 2021-03-01 | |
| Volume | 34Issue:3Pages:94-104 |
| ISSN | 1000-9361 |
| Abstract | Hypersonic airbreathing propulsion is one of the top techniques for future aerospace flight, but there are still no practical engines after seventy years? development. Two critical issues are identified to be the barriers for the ramjet-based engine that has been taken as the most potential concept of the hypersonic propulsion for decades. One issue is the upstream-traveling shock wave that develops from spontaneous waves resulting from continuous heat releases in combustors and can induce unsteady combustion that may lead to engine surging during scramjet engine operation. The other is the scramjet combustion mode that cannot satisfy thrust needs of hypersonic vehicles since its thermos-efficiency decreases as the flight Mach number increases. The two criteria are proposed for the ramjet-based hypersonic propulsion to identify combustion modes and avoid thermal choking. A standing oblique detonation ramjet (Sodramjet) engine concept is proposed based on the criteria by replacing diffusive combustion with an oblique detonation that is a unique pressure-gain phenomenon in nature. The Sodramjet engine model is developed with several flow control techniques, and tested successfully with the hypersonic flight-duplicated shock tunnel. The experimental data show that the Sodramjet engine model works steadily, and an oblique detonation can be made stationary in the engine combustor and is controllable. This research demonstrates the Sodramjet engine is a promising concept and can be operated stably with high thermal efficiency at hypersonic flow conditions. ? 2020 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). |
| Keyword | Concept demonstration Hypersonic propulsion Oblique detonation engine Scramjet Shock wave Supersonic combustion Wind tunnel test |
| DOI | 10.1016/j.cja.2020.11.0011000-9361 |
| Indexed By | SCI ; EI ; CSCD |
| Language | 英语 |
| WOS ID | WOS:000634376600004 |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Funding Project | National Natural Science Foundation of China[11532014] |
| Funding Organization | National Natural Science Foundation of China |
| Classification | 二类/Q1 |
| Ranking | 1 |
| Contributor | Jiang, Zonglin |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/86441 |
| Collection | 高温气体动力学国家重点实验室 |
| Affiliation | 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 |
| Recommended Citation GB/T 7714 | Jiang ZL,Zhang ZJ,Liu YF,et al. Criteria for hypersonic airbreathing propulsion and its experimental verification[J]. CHINESE JOURNAL OF AERONAUTICS,2021,34,3,:94-104.Rp_Au:Jiang, Zonglin |
| APA | 姜宗林,张子健,刘云峰,王春,&罗长童.(2021).Criteria for hypersonic airbreathing propulsion and its experimental verification.CHINESE JOURNAL OF AERONAUTICS,34(3),94-104. |
| MLA | 姜宗林,et al."Criteria for hypersonic airbreathing propulsion and its experimental verification".CHINESE JOURNAL OF AERONAUTICS 34.3(2021):94-104. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| Jp2021F179.pdf（1806KB） | 期刊论文 | 出版稿 | 开放获取 | CC BY-NC-SA | View Download | |
Items in the repository are protected by copyright, with all rights reserved, unless otherwise indicated.
Edit Comment