To　lighten　the　aircraft　engine　and　improve　its　propulsion　efficiency,　many　aero　engines　adopt　the　blisk　structure　comprising　both　the　rotor　disk　and　blades.　Since　the　disk　becomes　thinner,　the　stiffness　of　the　structure　decreased　apparently,　which　causes　the　occurrence　of　large　amplitude　vibration　in　the　blisk.　This　passage　utilizes　the　finite　element　analysis　(FEA)　and　computational　fluid　dynamics　(CFD)　simulation　software　to　investigate　the　coupled　vibration　characteristics　between　the　blades　and　the　disk　of　the　blisk　with　realistic　geometric　data,　in　which　the　aerodynamic　load　and　centrifugal　load　are　considered.　At　first,　the　CFD　and　finite　element　models　of　an　aero-turbine　compressor　blisk　are　built.　Then　the　pressure　load　data　under　some　critical　rotating　speeds　from　CFD　simulation　are　communicated　to　FEA　software　by　data　interpolating　method,　and　the　simulation　of　modal　characteristics　of　the　blisk　is　conducted　in　FEA.　At　last,　the　natural　modal　characteristics　of　the　blisk　structure　are　obtained,　including　the　resonance　speed　Campbell　diagram,　the　natural　frequencies　and　corresponding　mode　shapes.　According　to　the　Campbell　diagram,　it　indicates　that　the　most　critical　mode　is　the　fourth　order　mode.　It　is　found　that　the　mode　shape　of　the　fourth　order　in　the　blisk　is　the　coupling　of　the　disk　torsional　and　blades　first　bending　vibration.　It　is　easy　to　lead　to　vibration　failure　when　large　amplitude　vibration　of　the　fourth　mode　occurs　in　the　blisk.　Also,　it　could　also　conclude　that　the　modal　characteristics　of　the　coupled　vibration　in　the　rotating　blisk　are　very　sensitive　to　the　disk　stiffness.　These　results　provide　basic　data　for　the　further　research　in　nonlinear　vibration　and　structure　optimization　of　the　blisk,　and　also　a　simulating　method　to　investigate　coupled　vibration　between　the　blades　and　the　disk　of　the　blisk　considering　both　aerodynamic　and　centrifugal　load.　©　Published　under　licence　by　IOP　Publishing　Ltd.