SHANG Deguang multiaxial fatigue damage model was used to amend Manson-Coffin equation of multiaxial fatigue prediction and SWT(Smith-Waston-Topper) formula

based on working condition of turbine rotor blade in aviation engine.A new method of fatigue life prediction of turbine blade was presented

which was adapted for non-proportional loading of turbine blade fatigue damage at high temperature.A case of turbine blade was calculated for fatigue life and the total damage of 1000 hours flying

in well agreement with the fact of blade fatigue damage.So the model of multiaxial fatigue prediction is rational and feasible.