This　paper　focuses　on　the　nonlinear　oscillations　and　the　steady-state　responses　of　a　thin-walled　compressor　blade　of　gas　turbine　engines　with　varying　rotating　speed　under　high-temperature　supersonic　gas　flow.　The　rotating　compressor　blade　is　modeled　as　a　pre-twisted,　presetting,　thin-walled　rotating　cantilever　beam.　The　model　involves　the　geometric　nonlinearity,　the　centrifugal　force,　the　aerodynamic　load　and　the　perturbed　angular　speed　due　to　periodically　varying　air　velocity.　Using　Hamilton＇s　principle,　the　nonlinear　partial　differential　governing　equation　of　motion　is　derived　for　the　pre-twisted,　presetting,　thin-walled　rotating　beam.　The　Galerkin＇s　approach　is　utilized　to　discretize　the　partial　differential　governing　equation　of　motion　to　a　two-degree-of-freedom　nonlinear　system.　The　method　of　multiple　scales　is　applied　to　obtain　the　four-dimensional　nonlinear　averaged　equation　for　the　resonant　case　of　2:1　internal　resonance　and　primary　resonance.　Numerical　simulations　are　presented　to　investigate　nonlinear　oscillations　and　the　steady-state　responses　of　the　rotating　blade　under　combined　parametric　and　forcing　excitations.　The　results　of　numerical　simulation,　which　include　the　phase　portrait,　waveform　and　power　spectrum,　illustrate　that　there　exist　both　periodic　and　chaotic　motions　of　the　rotating　blade.　In　addition,　the　frequency　response　curves　are　also　presented.　Based　on　these　curves,　we　give　a　detailed　discussion　on　the　contributions　of　some　factors,　including　the　nonlinearity,　damping　and　rotating　speed,　to　the　steady-state　nonlinear　responses　of　the　rotating　blade.