In order to investigate the effect of end-wall modeling on the aerodynamic performance and flow field characteristics of turbine blades,the effect of non-axisymmetric end-wall modeling on the differential pressure of turbine rotor blades was analyzed,and the theoretical study was carried out based on non-axisymmetric end-wall modeling.A modeling scheme with upper convex and lower concave hub of turbine blades was proposed,and the effect of non-axisymmetric end- wall modeling on the secondary flow loss of turbine flow field was studied.The numerical simulation results show that non-axisymmetric end wall shaping method plays an important role in reducing lateral pressure difference,and the non-axisymmetric end wall shaping at the saddle point of the rotor hub is better than the shaping in the channel.Different interval shaping of the lower end wall of the turbine can effectively reduce the secondary flow loss in the turbine lobe channel,and the use of non-axisymmetric end wall shaping method can effectively reduce the total pressure loss coefficient of 0.132 2% at the outlet of the turbine lobe.