A　rotating　pretwisted　cylindrical　shell　model　with　a　presetting　angle　is　established　to　investigate　nonlinear　dynamic　responses　of　the　aero-engine　compressor　blade.　The　centrifugal　force　and　the　Coriolis　force　are　considered　in　the　model.　The　aerodynamic　pressure　is　obtained　by　the　first-order　piston　theory.　The　strain-displacement　relationship　is　derived　by　the　Green　strain　tensor.　Based　on　the　first-order　shear　deformation　theory　and　the　isotropic　constitutive　law,　nonlinear　partial　differential　governing　equations　are　derived　by　using　the　Hamilton　principle.　Discarding　the　Coriolis　force　effect,　Galerkin　approach　is　utilized　to　reduce　nonlinear　partial　differential　governing　equations　into　a　two-degree-of-freedom　nonlinear　system.　According　to　nonlinear　ordinary　differential　equations,　numerical　simulations　are　performed　to　explore　nonlinear　transient　dynamic　responses　of　the　system　under　the　effect　of　the　single　point　excitation　and　nonlinear　steady-state　dynamic　responses　of　the　system　under　the　effect　of　the　uniform　distribution　excitation.　The　effects　of　the　excitation　parameter,　damping　coefficient,　rotating　speed,　presetting　angle　and　pretwist　angle　on　nonlinear　dynamic　responses　of　the　system　are　fully　discussed.