Experimental Studies of Film Cooling in Supersonic Combustors

	Experimental Studies of Film Cooling in Supersonic Combustors
	Fan C(樊川); Wang J(王晶); Fan XJ(范学军)
会议录名称	21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
	2017
会议名称	21st AIAA International Space Planes and Hypersonics Technologies Conference
会议日期	6-9 March 2017
会议地点	Xiamen, China
摘要	The current work is an experimental investigation of the dependence of film-cooling effectiveness on the injection angle, mass flux and injection temperature in supersonic combustors. The mainstream Mach number is 2.5, and the coolant was injected with sonic speed. The total temperature of the mainstream is 1500K, and for the injection it ranges from 300K to 1060K. Three injection angle is respectively 00, 430, 1370. The coolant mass flux ranges from 1% to 6% of the mainstream mass flux, and the mainstream mass flux is 2.5kg/s. The results show that a smaller injection angle has a better performance in film cooling effectiveness and indicate that an increase in film-cooling effectiveness with the increase of the coolant mass flux. The influence of coolant temperature is more complex. The rising of coolant temperature reduces the film-cooling effectiveness without kerosene combustion, while has not significant difference with kerosene combustion. 漏 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
关键词	Combustion Combustors Coolants Kerosene Spacecraft Supersonic Aerodynamics
ISBN号	978-1-62410-463-3
URL	查看原文
收录类别	EI
语种	英语
文献类型	会议论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/72186
专题	高温气体动力学国家重点实验室
作者单位	1. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beisihuanxilu NO.15, Beijing 2.100190, China
推荐引用方式 GB/T 7714	Fan C,Wang J,Fan XJ. Experimental Studies of Film Cooling in Supersonic Combustors[C]21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017,2017.

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