| Citation: | WANG Songbai, NIU Xiao, HUO Jiaxin, et al. Improved design for anti-bird impact of aero-engine fan rotor blades[J]. Journal of Aerospace Power, 2024, 39（2）：20230494 doi: 10.13224/j.cnki.jasp.20230494
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In order to improve the bird impact resistance of aero-engine fan rotor blades, the smoothed particle hydrodynamics (SPH) method and LS-DYNA software were used to evaluate the bird impact resistance of fan rotor blades, and the effects of key design parameters on aerodynamic performance and bird impact resistance were analyzed. The results indicated that the realistic bird impact mainly caused deformation, curling, and tearing of rotor blade leading edge. The aerodynamic performance decreased with the increase of the leading edge radius, the stability margin sharply decreased as the leading edge radius was larger than 0.25 mm. The maximum thickness position moving afterward was beneficial for aerodynamic performance, while the bird impact resistance decreased. By selecting reasonable design parameters to maintain the aerodynamic performance, the fan rotor blade design was improved. The anti-bird ability of fan rotor blade had been significantly increased from 30 g to 50 g.
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