采用放大的半圆柱状表面模拟涡轮叶片前缘的形状 ,对叶片前缘单排及两排圆柱形孔的气膜冷却效率进行了测量。试件表面交错地开有 6排孔 ,以驻点为起点 ,位置分别在± 1 5°,± 4 0°及± 60°处 ,各排孔的孔间距均为 3个孔径 ,孔轴线与表面在展向及流向的夹角分别为 30°及 90°,孔长与孔径比为 4。主要对比研究了 3种单排气膜孔不同孔排位、3种两排气膜孔不同孔排位及 1种三排气膜孔的布局对孔排下游冷却效率的影响。结果表明 :在同样二次流流量条件下 ,冷却效果好的单排孔位置依次为 60°,4 0°,1 5°,冷却效果最好的两排孔位置组合为 ( 40°,60°)。结果还表明 :在较大的二次流流量条件下 ,采用单排孔、两排孔或三排孔冷却方案对孔排下游的冷却效果影响不大 ;但在较小的二次流流量条件下 ,从冷却效果看 ,较好的孔排冷却方案依次为 :三排孔、两排孔及单排孔。实验参数范围是 :主流雷诺数 Re=4 2 0 0 0～ 1 2 70 0 0 ,平均吹风比 M =0 .5～ 2 .0 The magnified semi-cylindrical surface was used to simulate the shape of the leading edge of the turbine blade. The film cooling efficiency of the single row and two rows of cylindrical holes at the leading edge of the blade was measured. The specimen surface staggered to open a row of six rows of holes to stagnation as a starting point, the location of ± 15 °, ± 40 ° and ± 60 ° at the hole spacing of each row of holes are 3 holes, hole axis and The angle between the surface and the flow direction is 30 ° and 90 °, respectively. The ratio of aperture length to aperture is 4. The effects of layout of three kinds of single-hole film holes with different hole ranks, three kinds of holes with two two-row film holes and one type of three-row film holes on the cooling efficiency of the hole row were studied. The results show that under the same secondary flow rate, the single cooling holes with good cooling effect are 60 °, 40 ° and 15 ° in sequence, and the combination of the two cooling holes with the best cooling effect is (40 ° and 60 ° ). The results also show that under the condition of larger secondary flow, the cooling effect of the single row of holes, two rows of holes or three rows of holes is not affected by the cooling effect of the row of holes. However, Under the cooling effect, the better row of row cooling programs are: three rows of holes, two rows of holes and single row of holes. The experimental parameters range is: the mainstream Reynolds number Re = 4 0 0 0 ~ 1 2 70 0 0, the average blowing ratio M = 0.5 ~ 2 .0