摘要
采用放大的半圆柱状表面模拟涡轮叶片前缘的形状，对叶片前缘多排圆柱形孔的气膜冷却效率进行了实验研究。测出了孔排区及其下游的局部冷却效率。研究了主流雷诺数及平均吹风比对冷却效率及二次流（冷气）出流轨迹的影响。实验参数范围是：主流雷诺数Ｒｅ＝４２０００～１２７０００，平均吹风比Ｍ＝０．８～２．０，测量分８个工况进行。
Film cooling effectiveness of hole-rows on leading edge of turbine blade has been studied experimentally.The model is a blunt body with a half-cylinder leading edge and two flat side-walls.Six rows of round holes were ungradationally located at and from stagnation on the half-cylinder leading edge.The holes in each row were spaced three hole-diameters apart at angles to the surface spanwise and streamwise respectively.The length of hole is of four hole-diameters.Spanwise and streamwise distributions of film cooling effectiveness in the leading edge and on the flat side-wall were measured in the range of mainstream Reynolds number (based on leading edge diameter) from 42000 to 127000 and blowing ratio (average secondary to mainstream mass flux ratio) from 0 8 to 2 0.The results indicate that the film cooling effectiveness decreases with increasing blowing ratio but does not depend too much on the mainstream Reynolds number.The secondary flow locus is depedent on blowing ratio but also does not depend on mainstream Reynolds number too much.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
1999年第2期205-208,共4页
Journal of Aerospace Power
