吹风比对旋转涡轮叶片气膜冷却的影响

邓宏武; 肖俊; 李国庆; 薛航

吹风比对旋转涡轮叶片气膜冷却的影响

1.
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国家级重点实验室, 北京 100191
2.
中国航空技术进出口总公司民机市场部, 北京 100101

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出版历程
- 收稿日期: 2010-07-02
- 修回日期: 2010-11-02
- 刊出日期: 2011-07-28

Influence of blowing ratio on film cooling of rotating turbine blade

1.
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China
2.
Market Department of China National Aero-Technology Import and Export Corporation, Beijing 100101,China

摘要

摘要: 对1.5级涡轮叶片在旋转状态下不同吹风比时的气膜冷却特性进行了实验研究.实验中基于动叶弦长的涡轮进口主流雷诺数为1.6451×10⁵,冷却工质采用二氧化碳,对应主流射流密度比为1.57,实验涡轮转速为475 r/min,对应旋转数为1.901,吹风比为0.5~2.0.采用稳态液晶方法测温.结果表明:①压力面上,随吹风比的增大,气膜冷却效率升高,气膜覆盖区域增大,气膜轨迹的偏转程度减弱;②吸力面上,随吹风比的增大,气膜冷却效率先上升后下降,气膜覆盖区域亦先增加后减少,气膜轨迹的偏转程度不明显;③射流流动的曲率半径影响气膜对壁面的附着.
- 气膜冷却 /
- 旋转 /
- 吹风比 /
- 冷却效率 /
- 涡轮叶片 /
- 曲率半径
Abstract: Experimental investigations were carried out to study the rotating film cooling characteristics at different blowing ratios in a 1.5-turbine stage.The mainstream Reynolds number Re_g is 1.6451×10⁵ in the experiment.CO₂ acts as a coolant with mainstream jet density ratio of 1.57.Turbine speed is 475r/min,and the rotation number is 1.901.The blowing ratio varies from 0.5 to 2.0.By using steady-state liquid crystal method,the results show that: (1) On pressure side,the film cooling efficiency and the film coverage increase,the deflection angle of film trajectory decreases with the increasing blowing ratio. (2) On suction side,the film cooling efficiency and the film coverage first increase and then decrease,the film trajectory has no obvious deflection angle with the increasing blowing ratio. (3) The curvature radius of jet flow affects the adhesion of film on the wall.
- film cooling /
- rotation /
- blowing ratio /
- cooling efficiency /
- turbine blade /
- curvature radius

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参考文献(13)

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