Abstract: A detail research has been completed for calculation of end wall boundary layers within an axial compressor cascade.A new calculation model for blade force defect is proposed,which is associated with development of primary flow and transverse flow.A unique feature of this method lies not only in capability to calculate the development of end wall boundary layers inside the cascade passage without any assumption about the exit of cascade,but also in ability to take into account the influecnce of its tip clearance.The calculational results of three heavily loaded cascades show that this model is superior to other existing models.