带肋横流进气方式下气膜孔的流阻特性与机理研究  

Flow Resistance Characteristics and Mechanism of Film Cooling Holes with Ribbed Crossflow

作　　者：刘存良[1] 宋辉[1] 郭涛[1] 贾广森[1] 闫建坤[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：《推进技术》2016年第7期1320-1327,共8页Journal of Propulsion Technology

基　　金：航空科学基金(2014ZB53023);国家"九七三"基金(2013CB035702);霍英东教育基金会资助项目(141053);中央高校基本科研业务费专项资金(3102014JCQ01049)

摘　　要：为了更好地研究内冷结构对外部气膜孔流阻特性的影响,在带肋横流进气方式下,实验测得不同横流雷诺数（Rec=1×10^-5,5×10^-4）和吹风比（M=0.5,1,2）下的圆柱型气膜孔流量系数,并结合数值模拟分析了横流雷诺数、45°肋结构和吹风比对气膜孔流阻特性的影响机理。结果表明：带肋横流进气方式下,横流引起的孔内旋流是流量系数减小的主要因素,肋引起的进口堵塞使得流量系数进一步减小;横流雷诺数相同时,流量系数随吹风比的增大而增大,当吹风比增大至M=2时,流量系数趋于一定值;小吹风比（M=0.5-1）时,横流雷诺数越大流量系数越小,随吹风比的增大（M=1-2）,横流雷诺数对流量系数的影响逐渐减小。In order to find out the effects of internal cooling structures on outer film cooling performance,experimental measurements and numerical simulations have been carried out to investigate the flow resistance characteristics and mechanism of cylindrical holes with coolant crossflow in ribbed channel over a series of crossflow Reynolds number（Rec=1×10^-5,5×10^-4） and blowing ratio（M=0.5,1,2）. The results show that the swirl flow in the hole caused by the crossflow is the main reason for the decrease of discharge coefficient. Flow blockage at hole entrance caused by the rib can further reduce the discharge coefficient. Under the same crossflow Reynolds number,the discharge coefficient increases with the blowing ratio and approaches to a constant value when the blowing ratio increases to 2. Under low blowing ratios（M=0.5 - 1）,the discharge coefficient decreases with the increase of crossflow Reynolds number. However,the effects of crossflow Reynolds number on the discharge coefficient become smaller with the increase of blowing ratio（M=1 - 2）.

关 键 词：气膜冷却 带肋横流 流量系数 吹风比 横流雷诺数 

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]