双层壳型冲击/气膜复合冷却效果的实验

刘震雄; 毛军逵; 郭文; 江和甫

双层壳型冲击/气膜复合冷却效果的实验

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国燃气涡轮研究院南京 210016

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出版历程
- 收稿日期: 2006-02-09
- 修回日期: 2006-05-03
- 刊出日期: 2007-02-28

Experimental investigation of a double-decker jet impingement/film structure's cooling coefficient

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Gas Turbine Establishment, Chengdu 610500, China

摘要

摘要: 以双层壳型冲击/气膜复合冷却结构的平壁模型作为研究对象, 进行了该种冷却结构的复合冷却效果实验研究.研究中改变冷热气流吹风比M, 冲击距H/d, 冲击孔和气膜孔间距与冲击孔直径之比P/d等参数, 利用红外热像仪拍摄实验件的温度分布.研究结果表明:上述参数均影响双层壳型冲击/气膜复合冷却效果, 而且影响规律表现出较强的关联性.随着吹风比的增加, 复合冷却效果逐步增强;在实验工况条件下, 存在一个最佳冲击距H/d范围使得复合冷却效果最佳;同时在冲击孔和气膜孔之间也存在一个最佳的P/d范围, 使得复合冷却效果达到最大.当H/d=0.5和P/d=4时, 双层壳型冲击/气膜复合冷却结构能达到最佳的冷却效果.
- 航空、航天推进系统 /
- 双层 /
- 冲击 /
- 气膜 /
- 冷却效果
Abstract: Experiments were conducted out to investigate cooling coefficient of a lamellar double-decker jet impingement/film structure.Blowing rate M,the ratio of the jet impingement distance to the diameter of the jet hole H/d,and the ratio of the distance between the jet hole and film hole to the diameter of the jet hole P/d were changed to study the rules of local cooling coefficient varying with these parameters.All the results show that higher cooling coefficient was achieved under larger blowing rate conditions.And there exists a proper range of H/d and P/d,which can result in a maximum cooling coefficient.It is verified that when H/d=0.5 and P/d=4,the maximum cooling coefficient can be achieved.
- aerospace propulsion system /
- double-decker structure /
- jet impingement /
- film cooling /
- cooling coefficient

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参考文献(6)

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