气膜孔形状对排孔下游换热的影响  

Effects of Film Cooling Hole Shape on Heat Transfer

作　　者：朱惠人[1] 许都纯[1] 郭涛[1] 刘松龄[1] 

机构地区：[1]西北工业大学706教研室,陕西西安710072

出　　处：《航空动力学报》2001年第4期360-364,共5页Journal of Aerospace Power

摘　　要：实验研究了气膜孔几何形状、二次流雷诺数及吹风比对孔排下游的局部换热系数的影响。所用孔形是簸箕形孔、圆锥形孔及圆柱形孔 ;实验的参数范围为二次流孔径雷诺数 Re=1 0 0 0 0～ 2 5 0 0 0 ,二次流吹风比 M=0 .3～ 2 .0 ,在上述范围选取了 2 6个工况分别对 3种孔形进行了实验。The Effects of hole shapes,secondary flow Reynolds numbers,and blowing ratio on the heat transfer downstream of film cooling holes have been investigated.Experiments on dust-pan shaped holes,cone-shaped holes and round holes have been conducted with secondary flow Reynolds number ranging from 10,000 to 25,000 and blowing rate ranging from 0 3 to 2 0.Measurements are taken for 26 conditions.Results show that the critical blowing ratio is 1 3 for the dust-pan shaped holes and cone-shaped holes,0 7 for the round holes.The turbulence provided by jet from round holes is greater than that from dust-pan shaped holes and cone-shaped holes.

关 键 词：簸箕形孔 圆锥形孔 换热系数 气膜冷却 航空发动机 

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]