多斜孔冷却方式气动参数对壁温梯度和冷却效率的影响

许全宏; 徐剑; 林宇震; 刘高恩

多斜孔冷却方式气动参数对壁温梯度和冷却效率的影响

北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室, 北京 100083

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出版历程
- 收稿日期: 2007-03-28
- 修回日期: 2007-07-25
- 刊出日期: 2008-04-28

Influence of aerodynamic parameter on the temperature gradient and cooling efficiency for effusion wall cooling method

National Key Laboratory on Aero-engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083

摘要

摘要: 针对高温升燃烧室以延长其火焰筒使用寿命为目的,实验研究了多斜孔冷却方式气动参数,如加温比、速度比和主流速度变化对主燃烧室火焰筒壁温梯度和冷却效率的影响.实验结果表明:减小加温比或增大速度比都可以减小壁温梯度的绝对值,同时冷却效率也会增加;当主流进入了自模区后,随着主流速度的增加,壁温梯度的绝对值会减小,冷却效率会增大.
- 航空、航天推进系统 /
- 航空发动机 /
- 燃烧室 /
- 火焰筒 /
- 冷却 /
- 多斜孔 /
- 壁温梯度 /
- 冷却效率
Abstract: As one of the most important factors influencing the combustor life-span,the temperature gradient of the effusion wall,as well as the cooling efficiency were investigated experimentally under the guidance of similarity theory.The effects of the temperature ratio of the main flow to the cooling air,the speed ratio of the cooling air to the main flow and the speed of the main flow were analyzed and discussed.IRthermograph was used to perform local measurements of the surface temperature field.The results reveal that these parameters which are investigated in this paper have strong influence on the temperature gradient and the cooling efficiency.
- aerospace propulsion system /
- gas turbine engine /
- combustor /
- liner /
- cooling /
- effusion wall /
- temperature gradient /
- cooling efficiency

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参考文献(9)

[1]	林宇震,宋波,李斌,等.燃烧室多斜孔壁气膜冷却研究[D].北京;北京航空航天大学,1997.LIN Yuzhen,SONG Bo,LI Bing,et al.An investigation of the inclined multihole wall fil cooling combustion chamber[D].Beijing:Beijng University of Aeronautics and Astronautics,1997.
[2]	LIN Yuzhen,SONG Bo,LI Bin,et al.Measured film cooling effectiveness of three multihole patterns[J].Journal of Heat Transfer,2006,2(128):192-197.
[3]	李军,董志锐,林宇震,等.多斜孔气膜冷却壁表面换热系数实验研究[J].推进技术,2000,21(5):45-48.LI Jun,DONG Zhirui,LIN Yuzhen,et al.Experimental investigation of heat transfer coefficients on the inclined multihole film cooling wall[J].Journal of Propulsion Technology,2000,21(5):45-48.
[4]	Andrews G E,Metl A.Small diameter film cooling holes:Wall convection heat transfer[R].ASME 86-GT-225,1986.
[5]	Mayle R E,Camarata F J.Multihole cooling film effectiveness and heat transfer[J].Trans of the ASME,Journal of Heat Transfer,1975,97 (2):534-538.
[6]	Sasaki M,Takahara K,Kumagai T,et al.Film cooling effectiveness for injection from multirow holes[R].ASME Paper 78-GT-32,1978.
[7]	Crawford M E,Kays W M,Moffat R J.Full coverage film cooling,Part Ⅰ:Comparison of heat transfer data for three injection angles[R].ASME Paper 80-GT-43,1980.
[8]	Kumada M,Kasagi N,H irataM.Studies of full-coverage film cooling,Part 2:Measurement of local heat transfer coefficient[R].ASME Paper 81-GT-38,1981.
[9]	杨世铭,陶文铨.传热学[M].北京:高等教育出版社,1998.