后台阶三维缝隙冷却效率的数值模拟  

Numerical investigation of back-step three dimensional slots on film cooling effectiveness

作　　者：原和朋[1] 朱惠人[1] 孔满昭[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《燃气轮机技术》2006年第4期38-42,共5页Gas Turbine Technology

摘　　要：针对涡轮叶片尾缘冷却结构特点，建立了后台阶三维缝隙结构气膜冷却特性计算模型，计算了冷却效率在出口壁面的分布，研究了不同雷诺数（5000，15000）与吹风比（0．5—2．0）影响，计算结果表明：在缝后壁面冷却效率是单调递减的，而肋后冷却效率是先增大后减少的分布规律；二次流出口壁面冷却效率受吹风比影响较大，冷却效率随吹风比增大而减小；壁面缝后冷却效率受雷诺数的影响较小。Film cooling efectiveness of back-step three dimensional slots injection on wall protile was calculated which was used to model the trailing edge cooling of turbine blade. The numerical simulation was conducted under different secondary flow Reynolds number and blowing ratio to show the effects of aerodynamic parameters on film cooling effectiveness. The secondary flow Reynolds number based on slot high changed from 5 000 to 15 000 and blowing ratio changed from 0.5 to 2.0.The important calculated results show that the profile of film coooling effectiveness at slot center line is different form that of rib center line. Blowing ratio have evident influence on film cooling efectivenss. Film cooling effectiveness decrease with the increasing of blowing ratio, when Reynolds number show little influence on the film cooling effectiveness.

关 键 词：涡轮叶片 三维缝隙 气膜冷却 掺混流 

分 类 号：O242.1[理学—计算数学]