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Experimental Studies of Film Cooling in Supersonic Combustors
Fan C(樊川); Wang J(王晶); Fan XJ(范学军)
Source Publication21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Conference Name21st AIAA International Space Planes and Hypersonics Technologies Conference
Conference Date6-9 March 2017
Conference PlaceXiamen, China
AbstractThe 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.
KeywordCombustion Combustors Coolants Kerosene Spacecraft Supersonic Aerodynamics
Indexed ByEI
Document Type会议论文
Affiliation1. State Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beisihuanxilu NO.15, Beijing
2.100190, China
Recommended Citation
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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