涡轮叶片内流冷却通道中压力系数的研究  

Research on Pressure Coefficients of Turbine Blade Internal Cooling Passages

作　　者：倪萌[1] 朱惠人[2] 裘云[2] 许都纯[2] 刘松龄[2] 

机构地区：[1]香港大学机械工程系 [2]西北工业大学航空动力学院,陕西西安710072

出　　处：《燃气轮机技术》2004年第4期41-47,共7页Gas Turbine Technology

摘　　要：本文根据相似理论,采用几何放大的模型,在流动相似的条件下,详细研究了涡轮叶片内流冷却通道在同时带肋和气膜孔出流的情况下,各流动参数、几何参数对压力系数的影响。实验在内流通道进口雷诺数为20000-80000,通道总出流比为0.3,0.45和0.6的范围内,肋高/宽比分别为1.0和2.0,肋角度分别为45°,60°,90°和120°,不同的肋与气膜孔相对位置,以及不同的通道截面形状的条件下进行。结果显示,同时带肋和气膜孔出流的内流通道中压力系数受气膜孔出流的影响很大,肋的存在也改变了内流通道的流动结构,影响了压力系数的分布,此外,通道的截面形状也是压力系数的重要影响因素之一。文章的结果对于涡轮叶片内流冷却通道的设计具有参考意义。Based on similarity theory,experimental investigations of pressure coefficients of the gas turbine blade internal cooling passages with both rib turbulators and film hole suctions were carried out on proportionally enlarged model.The distributions of pressure coefficients were measured along the passage under the conditions as follows:Reynolds number:20000-80000;film hole suction ratios(SR):0.3-0.6;rib height/width ratio:1.0,2.0; rib attack angle:45°,60°,90°,120°and different internal passage configurations.Results indicate that the pressure coefficients are greatly influenced by film hole suction ratios and the configuration of rib turbulators and passage configurations.The results can contribute to turbine blade internal cooling designing.

关 键 词：涡轮叶片 内流冷却 压力系数 气膜孔 肋 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] V211.73