In this paper, a small large bypass ratio turbofan engine fan rotor is taken as the research target. The aerodynamic characteristics decay of the aero-engine fan rotor blades during the flight process are numerically studied, laying a theoretical foundation for the subsequent refined maintenance. After the fan rotor blade is eroded, the leading-edge of the blade will gradually become blunt-headed with pronounced surface roughness. To simplify the research, this paper assumes that the roughness of the leading-edge of the rotor blade after erosion is evenly distributed, and the rotor characteristics of the leading-edge roughness with 120 μm and 250 μm are calculated. The results show that the peak efficiency of the fan rotor is reduced by 1.63% and 2.39% compared with the prototype blade. When the leading-edge roughness is 250 μm, there is a separation trace on the near-wall limit streamlines of the front edge of the fan rotor blade suction, and the average Mach number of the outlet decreases by 2.03%.
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