轴流压气机端壁附面层的理论预测

从Ｎ－Ｓ方程出发，推导了轴流压气机端壁边界层动量积分方程，并提出了一种适用范围广泛的叶片力亏损模型，结合边界层的卷吸方程和速度分布表达式，可以方便的预测压气机环壁边界层的发展，与传统的叶片力亏损模型相比，该方法的计算准确性和适用范围均得到提高。

Investigations of an Axial Compressor End Wall Boundary Layer Prediction Method

A new model is presented for calculating the blade force defect and the end wall boundary layer within the passage of axial compressor cascades. The intergral equation of end wall boundary layer is infered from N S equation. The end wall boundary layer may be predicted easily by using intergral equation together with entrainment equation and flow velocity profile. Compared with experimental results and other methods, the predictions by this method show better agreement for two examples. The results of numericl calculations show that the blade force defect has a severe influence on the development of end wall boundary layer.