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.　©　2019　Journal　of　Dynamics　and　Control.　All　rights　reserved.