This　paper　investigates　the　steady-state　responses　of　the　rotating　thin-walled　blade　with　varying　rotating　speed　under　high　temperature　supersonic　gas　flow.　The　rotating　blade　is　considered　as　a　pre-twist,　presetting,　thin-walled　rotating　cantilever　beam.　The　model　involves　in　nonlinearity　of　deformation,　incorporates　centrifugal　force,　aerodynamic　load　and　perturbed　angular　speed　due　to　the　inconstant　air　velocity.　By　using　Hamilton＇s　principle,　the　nonlinear　partial　differential　governing　equation　of　motion　for　the　pre-twist,　presetting,　thin-walled　rotating　blade　is　derived.　Galerkin＇s　approach　is　used　to　discretize　the　partial　differential　governing　equation,　and　a　two-degree-of-freedom　nonlinear　system　is　obtained.　For　further　analysis,　the　method　of　multiple　scales　is　applied　to　obtain　four-dimensional　nonlinear　averaged　equations　under　the　case　of　primary　resonance　and　2:1　internal　resonance.　Finally,　numerical　simulations　are　conducted　to　study　the　steady-state　responses　of　the　rotating　blade.　The　frequency-response　curves　are　presented.　Based　on　these　curves,　the　paper　gives　a　detail　discussion　of　the　contributions　of　some　important　factors,　such　as　damping　and　rotating　speed,　to　the　steady-state　responses　of　the　rotating　blade.