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.
本文以航空发动机涡轮叶片冷却为应用背景，对一种基于彻体力场下热驱动理论的新型冷却技术展开了首次研究，并从机理上验证了此新型冷却技术的强化冷却效果。
In this thesis, a new cooling technique, which is based on the theory of thermally driven, was studied at the background of turbine blade's cooling design in aero-engine.
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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