The results show that the cooling effectiveness on concave side is better than suction side with laying film cooling holes in concave side at leading edges of turbine blade.

结果表明，叶片前缘压力面侧布置的气膜孔对叶片压力面有很好的冷却效果；

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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 with two flat side walls.

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。

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