A　rotating　cantilever　sandwich-plate　model　with　a　pre-twisted　and　pre-set　angle　has　been　developed　to　investigate　the　vibrational　behavior　of　an　aero-engine　turbine　blade　with　thermal　barrier　coating　(TBC)　layers.　The　classic　von　Karman　plate　theory　and　the　first-order　shear　deformation　theory　are　applied　to　derive　the　energy　equations　of　the　rotating　TBC　blade,　in　which　the　geometric　shapes,　the　work　ambient　temperature,　and　the　TBC　material　properties　are　considered.　The　Chebyshev-Ritz　method　is　used　to　obtain　the　nature　frequency　of　the　rotating　TBC　blade.　For　static　frequency　and　modal　analysis,　the　finite-element　method　(FEM)　is　also　applied　to　compare　and　validate　the　results　from　the　Chebyshev-Ritz　method.　A　good　agreement　is　found　among　these　kinds　of　methods.　For　dynamic　frequency,　the　results　are　analyzed　in　detail　concerning　the　influence　of　system　parameters　such　as　the　thickness　of　the　TBC　layer,　the　working　temperature,　and　the　pre-twisted　and　pre-set　angle.　Finally,　the　Campbell　diagram　is　demonstrated　to　analyze　the　resonance　property　of　the　cantilever　sandwich　TBC　blade　model.