涡轮叶片内冷却通道的流阻与换热研究

INVESTIGATION ON FLOW RESISTANCE AND HEAT TRANSFER IN COOLING PASSAGES OF GAS TURBINE BLADE

用实验方法研究了冷却气流在放大１倍模型涡轮叶片内通道的压力、冷热态流阻及局部换热系数分布。得出了相应的经验公式。冷却空气径向进入前缘冷却通道，到顶端折而向下在两隔板间流动，大部分空气经隔板５个穿孔弦向流入带三排扰流柱的收缩通道，并弦向排出叶片尾部。

An enlarged test blade of gas turbine has been investigated experimentally for flow resistance and heat transfer in its cooling passages.Air entered the radial cooling channel inside the leading part of the blade and contrary flowed downward into the passage between two plates while the air flow reached to the top.The bulk of the air stream flowed through five holes on the plate into the chordwise wedged passage with three pin-fin rows and exhausted to the atmosphere.The experimental results of the pressure distribution,the flow resistance under heating and without heating,and the distribution of the local heat transfer coefficient in the cooling passages of a gas turbine blade are presented.Therefrom an emperic formula is obtained.