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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。
An enlarged semi-cylindrical surface was used to simulate the shape of the leading edge of the turbine blade. The film cooling efficiency of multi-row cylindrical holes at the leading edge of the blade was experimentally studied. The local cooling efficiency of the hole row and its downstream was measured. The influence of the main Reynolds number and average blow ratio on the cooling efficiency and the outflow trajectory of secondary flow (cold air) was studied. The experimental parameters range is: Reynolds number Re = 42000 ~ 127000, the average hair blowing ratio M = 0.8 ~ 2.0, the measurement points 8 working conditions.