Abstract: A new model is presented for calculating the end-wall boundary layer and its blade force defect inside the axial compressor cascade, based on theoretical analysis. The model can consider the influence of tip clearence. The predictions for three different loaded compressor cascades agree well with experimental results. It is found that the development of end-wall boundary layer has a severe influence on the blade force defect from the results of numerical calculations. The calculated results of three different cascades show that the skewed degree of end-wall boundary layer is related to the transverse blade force defect and the relationship between the changed ratio of axial momentum thickness of end-wall boundary layer and axial blade force defect is rather close.

Key words: axial compressor, cascade, end-wall boundary layer, blade force defect