带肋的内流通道中气膜孔流量系数的研究  

Investigation of Film Hole Discharge Coefficients of the Internal Passage with Rib-turbulators

作　　者：倪萌[1] 朱惠人[2] 裘云[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与热力工程系,西安710072

出　　处：《燃气涡轮试验与研究》2004年第1期24-28,共5页Gas Turbine Experiment and Research

基　　金：西北工业大学博士论文创新基金资助项目(200114)

摘　　要：在根据相似理论放大的模型上,测量了带60°肋壁的内流通道中沿主流流向分布的各气膜孔的流量系数(Cd)。实验在内流通道进口雷诺数为20000～80000、通道总出流比为0.30～0.60的范围内进行,重点分析了带60°肋壁和不带肋的内流通道中来流雷诺数和总出流比对Cd的影响规律,分析了肋对气膜孔流量系数的影响,并且进行了相应的数值模拟研究。为涡轮叶片的冷却结构设计提供了依据。Measurements of film hole discharge coefficients (Cd) in an internal p assage with rib turbulators and film holes were presented. The internal passage was rectangular channel with two opposite ribbed wall, the aspect ratio was 1.0, and the rib turbulators were staggered arranged on the two wider walls. The cyl indrical film holes were 45° inclined and perpendicular oriented and were place d on one ribbed wall. Tests were run at rib tubulators′ orientation as 60°, Re ynolds numbers (Re) changing from20 000 to 80 000 and suction ratios (SR) changing from 0.30 to 0.60. Influences of rib tuburlators, main stream Reynolds number and suction ratio on Cd were stu died. Numerical simulation was also undertaken. This study can be useful in turb ine blade cooling design.

关 键 词：航空发动机 气膜孔 流量系数 内流通道 涡轮叶片 冷却技术 肋 实验装置 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]