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.
与等截面回转通道相比较，变截面通道更接近叶片内冷通道原型。
Compared to the channel with uniform section area, those with various section areas are much similar to the internal cooling structure of the turbine blade.
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