Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.

根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。

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With the increase of the turbine inlet temperature of high performance aero-engine day by day, the turbine coating blade coating technology has been widely used.

随着高性能航空发动机涡轮进口温度日益提高，涂层技术在涡轮叶片上得以广泛应用。

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The experimental results are valuable reference for aero-engine turbine blade cooling designers.

本文的实验结果对于航空发动机涡轮叶片冷却结构设计具有参考价值。

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