冲击+逆向对流+气膜冷却传热特性的研究

宋双文; 杨卫华; 胡好生; 张靖周

冲击+逆向对流+气膜冷却传热特性的研究

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国航空动力机械研究所, 株洲 421002
3.
南京航空航天大学能源与动力学院, 南京 210016

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出版历程
- 收稿日期: 2007-03-26
- 修回日期: 2007-06-22
- 刊出日期: 2007-09-28

Experimental study of the heat transfer characteristics of combined cooling of impingement+reversed convection+film

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Aviatio n Powerplant Research Instit ute, Zhuzho u 412002, China
3.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为了研究火焰筒壁面冲击+逆向对流+气膜复合冷却方式的传热特性, 设计了6种不同几何结构的实验件, 搭建了实验台, 采用红外热像仪对其传热特性进行了研究.结果表明, 冷却效率随吹风比的增大而增大;在气膜出口与冲击位置之间, 气膜冷却效率沿主流方向不断增加, 在相同的冷却壁面处, 冷却效率随冲击位置距气膜出口的增加而减小;越过冲击位置, 冷却效率随壁面位置的增加而减小.在冷却壁面的任一位置, 冷却效果随冲击间距的减小而增大.
- 航空、航天推进系统 /
- 航空发动机 /
- 火焰筒 /
- 冲击冷却 /
- 气膜冷却 /
- 对流换热 /
- 实验研究
Abstract: In order to study the heat transfer characteristics of combined cooling of impingement +reversed convection +film on a flame tube wall,6 test pieces of different geometry were designed.The heat transfer characteristics of the combined cooling were studied by the experimental method using infrared cameras.The experimental results shows that the cooling effectiveness increases with the increase of blowing ratio;between the impingement position and film exit,the cooling effectiveness increases in the direction of main flow,and at a given position the cooling effectiveness decreases with the increase of distance between impingement position and the film exit;beyond the impingement position,the cooling effectiveness decreases in the direction of main flow.At the same wall position,the cooling effectiveness increases with the decrease of the impingement distance.
- aerospace propulsion system /
- aeroengine /
- flame tube /
- impinging cooling /
- film cooling /
- convective heat transfer /
- experimental study

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参考文献(7)

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