The nonlinear vibration responses of the aeroengine blade were investigated. Considering the effects of the presetting and pretwisted angles, the blade was modeled as a rotating conical shell . Using Hamilton′s principle, the governing partial differential equations of motion under different excitations were established. Both Galerkin′s approach and numerical method were applied to analyze the nonlinear dynamics of the blade. Numerical simulations were performed to investigate the responses of the blade under different rotating speeds and excitations. The results show that both the rotating speed and excitation have effects on the nonlinear dynamics of the blade.