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Title:
Experimental Studies of Film Cooling in Supersonic Combustors
Author: Fan C(樊川); Wang J(王晶); Fan XJ(范学军)
Issued Date: 2017
Conference Name: 21st AIAA International Space Planes and Hypersonics Technologies Conference
Conference Date: 6-9 March 2017
Conference Place: Xiamen, China
Abstract: 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.
Keyword: Combustion ; Combustors ; Coolants ; Kerosene ; Spacecraft ; Supersonic aerodynamics
Indexed Type: EI
Related URLs: 查看原文
Source: 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Publisher: American Institute of Aeronautics and Astronautics Inc, AIAA
Publish Place: USA
Language: 英语
ISBN: 978-1-62410-463-3
Content Type: 会议论文
URI: http://dspace.imech.ac.cn/handle/311007/72186
Appears in Collections:高温气体动力学国家重点实验室_会议论文

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description.institution: 1. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beisihuanxilu NO.15, Beijing
2.100190, China

Recommended Citation:
Fan C,Wang J,Fan XJ. Experimental Studies of Film Cooling in Supersonic Combustors[C]. 见:21st AIAA International Space Planes and Hypersonics Technologies Conference. Xiamen, China. 6-9 March 2017.https://arc.aiaa.org/doi/book/10.2514/MHYP17
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