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.