Tip deformation analysis of high pressure (HP) turbine rotor based on the HP rotor can improve the tip clearance numerical simulation precision. Due to the complex air cooling structure of HP turbine rotor blade

the number of finite element mesh is huge. The mortise structure analysis of HP turbine blade and disk belongs to nonlinear analysis

which also needs enough calculation time. A simplified method of complex air cooling blade model and mortise structure contact analysis model was presented

the calculation efficiency was improved under the premise of without affecting the calculation accuracy. Applying this method to an aero-engine turbine components deformation analysis

the results were compared with the deformation analysis results of the original complex blade model. The relative error of the largest turbine blade tip radial deformation was 0.47%

and the calculation time reduced 99%. Its proven that the simplified method and the calculation method are feasible.