Reduction of surface friction drag in scramjet engine by boundary layer combustion

doi:10.1016/j.ast.2021.106788

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Reduction of surface friction drag in scramjet engine by boundary layer combustion
	Xue, Rui 4,5; Zheng, Xing ; Yue LJ(岳连捷); Zhang, Qian ; He, Xin ; Yang, Jing 4; Weng, Chao 3,4; Li, Zhihao 2
刊名	AEROSPACE SCIENCE AND TECHNOLOGY
	2021-08
卷号	115 页码:106788
关键词	Boundary layer combustion Skin-friction reduction Supersonic combustion Scramjet engine
ISSN号	1270-9638
DOI	10.1016/j.ast.2021.106788
英文摘要	This study investigates the effects of boundary layer combustion on skin friction reduction in a model scramjet combustor. The 4-equation RANS model (Transition SST model) is employed as the turbulence model and one experimental case which involves supersonic turbulent boundary layer combustion is used for validating the numerical simulation method. Then a wall jet device which can be used to inject hydrogen into boundary layer is designed and added to the lower wall of the combustor in the model scramjet engine. The numerical results showed that the optimal ratio between the primary fuel, producing thrust, and the wall jet fuel, used for drag reduction, for getting the largest skin-friction drag reduction when installing the wall jet device in the combustor, is 3:1. The study of modifying the location of the wall jet device showed that setting the wall jet position too close to the upstream or downstream could not get the maximum overall drag reduction. The installation position in the flow path depends on the coupling of primary fuel and wall jet fuel combustion. In practical scramjet design, the distribution ratio of primary to wall jet fuel and the location of wall jet device should be weighed to improve skin friction reduction efficiency and overall engine performance. (C) 2021 Elsevier Masson SAS. All rights reserved.
学科主题	Engineering, Aerospace
分类号	一类
语种	英语
WOS记录号	WOS:000663681800007
资助机构	National Natural Science Foundation of China [51706170] ; China Postdoctoral Science Foundation [2019TQ0246, 2019M663734] ; Shaanxi Provincial Postdoctoral Science Foundation [2018BSHEDZZ03] ; Foundation of State Key Laboratory of Coal Combustion [FSKLCCA2004] ; Foundation of State Key Laboratory of High Temperature Gas Dynamics ; Fundamental Research Funds for the Central Universities [xzy012019053]
其他责任者	Xue, R (corresponding author), Xi An Jiao Tong Univ, Sch Aerosp, State Key Lab Strength & Vibrat Mech Struct, Shaanxi Engn Lab Vibrat Control Aerosp Struct, Xian 710049, Peoples R China.
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/90255]
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.Xian Modern Control Technol Res Inst, Xian 710065, Peoples R China 2.Tongji Univ, Shanghai 200092, Peoples R China 3.YuelaiYH Co, Guiyang 550000, Peoples R China 4.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China 5.Xi An Jiao Tong Univ, Sch Aerosp, State Key Lab Strength & Vibrat Mech Struct, Shaanxi Engn Lab Vibrat Control Aerosp Struct, Xian 710049, Peoples R China
推荐引用方式 GB/T 7714	Xue, Rui,Zheng, Xing,Yue LJ,et al. Reduction of surface friction drag in scramjet engine by boundary layer combustion[J]. AEROSPACE SCIENCE AND TECHNOLOGY,2021,115:106788.
APA	Xue, Rui.,Zheng, Xing.,岳连捷.,Zhang, Qian.,He, Xin.,...&Li, Zhihao.(2021).Reduction of surface friction drag in scramjet engine by boundary layer combustion.AEROSPACE SCIENCE AND TECHNOLOGY,115,106788.
MLA	Xue, Rui,et al."Reduction of surface friction drag in scramjet engine by boundary layer combustion".AEROSPACE SCIENCE AND TECHNOLOGY 115(2021):106788.