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Effect of combustion mode on thrust performance in a symmetrical tandem-cavity scramjet combustor

文献类型：期刊论文

作者Liu, Mingjiang4; Sun, Mingbo4; Zhao, Guoyan4; Meng Y(孟宇)2,3; Huang, Yuhui1; Ma, Guangwei4; Wang, Hongbo4
刊名AEROSPACE SCIENCE AND TECHNOLOGY
出版日期2022-11-01
卷号130页码:11
ISSN号1270-9638
关键词Tandem-cavity Scramjet combustor Combustion mode Thrust performance
DOI10.1016/j.ast.2022.107904
通讯作者Sun, Mingbo(sunmingbo@nudt.edu.cn) ; Zhao, Guoyan(zhaoguoyan09@nudt.edu.cn)
英文摘要To investigate the relationship between the thrust performance and combustion mode in a scramjet combustor, the acceleration process of a symmetrical tandem-cavity combustor is numerically investigated based on previous experiments. The numerical results are essentially in agreement with the experimental results through high-speed photography and wall pressure comparisons, which verifies the reliability of the numerical method. Then, three groups of simulations with different equivalent ratios are designed under the condition of inlet flow Mach numbers 2.4, 2.5, 2.6, 2.7, and 2.9. Complete combustion efficiency and specific section thrust are defined to measure the combustion efficiency of kerosene and thrust performance. Four combustion modes are defined and observed in simulations, i.e. strong ram mode, weak ram mode, dual-mode ram mode, and scram mode. The simulation results show that the combustion modes in the former and the later cavities for this tandem-cavity scramjet combustor are related to each other. Combustion modes have a significant impact on the thrust performance of the combustor and the specific section thrust mutation is caused by mode transition. Under different inlet Mach numbers, appropriate equivalent ratio settings can improve thrust performance for this tandem -cavity supersonic combustor. Two ideal combustion modes realized by different injection schemes are proposed for better thrust performance of symmetrical tandem-cavity supersonic combustor.(c) 2022 Elsevier Masson SAS. All rights reserved.
分类号一类
WOS关键词FLAME STABILIZATION ; TRANSITION ; OSCILLATIONS ; MECHANISM ; FLOW
资助项目National Natural Science Foundation of China[11925207] ; National Natural Science Foundation of China[12002381] ; Scientific Research Plan of National University of Defense Technology[ZK19-02] ; Science and Technology Foundation of State Key Laboratory[6142703200311]
WOS研究方向Engineering
语种英语
WOS记录号WOS:000882419600001
资助机构National Natural Science Foundation of China ; Scientific Research Plan of National University of Defense Technology ; Science and Technology Foundation of State Key Laboratory
其他责任者Sun, Mingbo ; Zhao, Guoyan
源URL[http://dspace.imech.ac.cn/handle/311007/90804]  
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.Equipment Project Management Ctr, Equipment Dev Dept, Beijing 100089, Peoples R China
2.Chinese Acad Sci, Inst Mech, Beijing 100190, Peoples R China;
3.Shanghai Jiao Tong Univ, Sch Aeronaut & Astronaut, Shanghai 200240, Peoples R China;
4.Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;
推荐引用方式
GB/T 7714		 Liu, Mingjiang,Sun, Mingbo,Zhao, Guoyan,et al. Effect of combustion mode on thrust performance in a symmetrical tandem-cavity scramjet combustor[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2022,130:11.
APA Liu, Mingjiang.,Sun, Mingbo.,Zhao, Guoyan.,孟宇.,Huang, Yuhui.,...&Wang, Hongbo.(2022).Effect of combustion mode on thrust performance in a symmetrical tandem-cavity scramjet combustor.AEROSPACE SCIENCE AND TECHNOLOGY,130,11.
MLA Liu, Mingjiang,et al."Effect of combustion mode on thrust performance in a symmetrical tandem-cavity scramjet combustor".AEROSPACE SCIENCE AND TECHNOLOGY 130(2022):11.

入库方式： OAI收割

来源：力学研究所

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