气膜冷却涡轮叶栅气动损失数值计算
NUMERICAL ANALYSIS OF AERODYNAMIC LOSSES IN FILM-COOLED VANE CASCADE
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摘要: 在二维气膜冷却边界层流动和传热计算方法[1]基础上,引入边界层积分参数法[2],计算叶栅的气动损失。结果表明,这种方法较适用于低吹风比和边界层较厚处有气膜冷却的情况。作者将边界层积分参数法与叶栅损失计算的另一种方法进行数值计算的比较,表明两种方法各有长处与适用范围,实际应用中应考虑两者的结合使用。Abstract: Intergal Boun dary Layer Parameter" method based on a 2 dimensional film cooling flow and heat transfer prediction program STANCOOL is provided to pred ict the aerodynamic losses in the film cooled vane cascade.The comparison of the numerical analysis with the corresponding experimental data demonstrates that the present method is more suitable to the case when blowing rates are low or the film cooling is located at thick local boundary layer.Finally this method is compared with another loss predicting method,named "TOTLOS",and it is concluded that both methods have their own advantages and extent of application.In practice it is reasonable to use the two methods in combination.
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