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。
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.
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；
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；
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.
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