In order to reveal the influence of real damage on the aerodynamic performance after ice-shedding impact on transonic fan rotor blades, reverse modeling of the damaged blades was performed, and the effects of different bending directions and deformation degrees of the blade leading edge on aerodynamic performance were investigated. The results show that the stall margins of Case 1 and Case 2 with blade leading edges bending toward the suction surface are relatively reduced by 62% and 29%, and the stall margins of Case 4 and Case 5 with blade leading edges bending toward the pressure surface are relatively reduced by 11.9% and 19.5%. Bending of the lead? ing edge towards the pressure surface reduces blade passage flow capacity, decreases mass flow rate, increases suction surface curvature, and aggravates boundary layer separation.
Bending towards the suction surface improves passage flow capacity, increases mass flow rate, forms an S-shaped chordwise section at the damaged area, increases the total pressure ratio through pre-compression effect, and inhibits boundary layer separation due to the concave profile of the uncovered suction surface segment. At near-stall conditions, the blade incidence angle of Case 1 and Case 2 increases, and the high-speed zone outside the channel causes the airflow speed to change drasti? cally, inducing blade stall. For Case 4 and Case 5, the curvature of the blade suction surface increases, causing severe boundary layer separation and leading to blade stall. Leading-edge bending towards the suction surface forms an S-shaped chordwise section at the dam? aged area, which is conducive to suppressing boundary layer separation with minor impact on aerodynamic performance; however, the blade stall margin is significantly reduced, threatening flight safety; leading-edge bending towards the pressure surface significantly degrades aerodynamic performance but has a smaller impact on stall margin.