Experimental Studies of Film Cooling in Supersonic Combustors
文献类型：会议论文
| 作者 | Fan C(樊川); Wang J(王晶) ; Fan XJ(范学军)
|
| 出版日期 | 2017 |
| 会议日期 | 6-9 March 2017 |
| 会议地点 | Xiamen, China |
| 关键词 | Combustion Combustors Coolants Kerosene Spacecraft Supersonic Aerodynamics |
| 英文摘要 | 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. |
| 会议录 | 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
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| 会议录出版者 | American Institute of Aeronautics and Astronautics Inc, AIAA |
| 会议录出版地 | USA |
| 语种 | 英语 |
| URL标识 | 查看原文 |
| ISBN号 | 978-1-62410-463-3 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/72186]  |
| 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.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]. 见:. Xiamen, China. 6-9 March 2017. |
入库方式： OAI收割
来源：力学研究所
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