气膜孔与肋的相对位置及通道截面形状对气膜孔流量系数的影响  

Effects of relative position of film hole to rib turbulators and passage geometry on film hole discharge coefficient

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,西安710072

出　　处：《燃气轮机技术》2005年第1期52-56,共5页Gas Turbine Technology

摘　　要：本文基于航空发动机涡轮叶片的放大模型,研究了在同时带肋和气膜孔出流的内流通道中气膜孔与肋的相对位置以及通道截面形状对流量系数Cd的影响情况。实验在内流通道进口雷诺数Re为20000～80000、通道总出流比SR为0.30～0.60以及肋角为60°、120°的范围进行,分析了肋与气膜孔的相对位置及通道截面形状对气膜孔流量系数的影响情况,发现肋的存在明显改变了气膜孔的流量系数。由于肋所导致的回流区的影响,位于肋下游的气膜孔流量系数低于中间孔和肋上游孔,而通道截面的不同则影响了气膜孔里的雷诺数大小,从而影响了气膜孔的流量系数。本文的实验结果对于航空发动机涡轮叶片冷却结构设计具有参考价值。Experiments on effects of relative position of film hole to rib turbulators and passage geometry on film hole discharge coefficients are carried out in an enlarged aero-engine turbine blade internal cooling passage model.This research is conducted under Re:20000-80000;film hole suction ratio:0.3-0.6;and tib orientation 60°,120°. The results indicate that the existence of rib turbulators alters film hole discharge coefficients. Due to the strong circulations caused by rib turbulators,the discharge coefficients of the hole after the rib are always lower than those at the middle of the rib or at the upstream of the ribs. Film hole discharge coefficients of different passage geometry are also different, as the Re numbers in the film holes are different. The experimental results are valuable reference for aero-engine turbine blade cooling designers.

关 键 词：航空发动机 涡轮叶片 气膜冷却 内流冷却 流量系数 

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]