不同前缘气膜冷气流下某涡轮叶栅流场分析  

Turbine Cascade Flow Analysis with Different Leading Edge Film Cooling Air Quantity

作　　者：王瀚艺[1] 罗立[1] 魏永超 WANG Han-yi;LUO Li;WEI Yong-chao(Aviation Engineering Institute,Civil Aviation Flight University of China,Sichuan Guanghan 618300,China;Departement of Research,Civil Aviation Flight University of China,Sichuan Guanghan 618300,China)

机构地区：[1]中国民用航空飞行学院航空工程学院,四川广汉618300 [2]中国民用航空飞行学院科研处,四川广汉618300

出　　处：《机械设计与制造》2022年第5期15-19,共5页Machinery Design & Manufacture

基　　金：航空发动机叶片检测与性能分析关键技术研究(U1633127);航空发动机叶片冷却技术及其耦合性能研究(J2019-003)。

摘　　要：针对引入前缘气膜冷却的某高压涡轮转子叶片,运用NUMECA进行建模,对引入气膜冷却后的涡轮叶栅流场进行分析,得到了加入前缘气冷后温度、速度、总压等参数的变化。再改变前缘气膜冷气流量,得到了不同流量工况下涡轮叶栅流场的变化情况。通过计算得到结论,冷气流量增大,气膜与叶片壁面分离位置提前,整体流速更快到达最大值且沿着壁面下降更快。冷气流量减小,冷却效率降低;吹风比越大,不同冷气流下冷却效率的变化更为集中;但随着冷气流的改变,总压恢复系数没有发生本质变化。A typical engine turbine rotor model with leading edge film cooling is established,usingNUMECA. The turbine cascade with film cooling is analyzed. Different parameters are calculated like temperature,velocity and total pressure,etc. Under different flow quantities of cooling film,the flow field is obtained. The results show that increasing flow quantity,separation position of film and blade advances,the flow magnitude increases to the maximum and then decreases faster. The lower cooling air flow quantity becomes,the lower cooling efficiency is. The larger the blowing ratio is,the more concentrated the change of cooling efficiency is under different cooling air flow. Moreover,the total pressure recovery coefficient does not change much as air flow changes.

关 键 词：气膜冷却 冷却效率 数值模拟 叶栅流场 

分 类 号：TH16[机械工程—机械制造及自动化] V232[航空宇航科学与技术—航空宇航推进理论与工程]