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。
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.
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。
The experimental results are valuable reference for aero-engine turbine blade cooling designers.
本实验选取航空发动机涡轮叶片中段内部冷却通道为研究对象，对不同肋间距的横肋变截面U型通道的换热特性进行了研究。
The experiment has studied the heat transfer characteristic inside U shaped variable cross-section channels with different rib pitches, The channel is the middle part of a gas turbine blade.
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