Abstract: In response to the problem of cracks appearing at the root of the blade during the partial intake turbine blade test of a liquid rocket engine, the quasi-static stress response and dynamic stress response of the turbine blade under the combined effects of centrifugal force field, temperature field, axial compression force, and aerodynamic field were analyzed using finite element method, and the service life of the turbine blade was evaluated; A frequency management method based on frequency density analysis of cyclic periodic structures is proposed to address the risk of high dynamic stress caused by high-frequency resonance of the structure, revealing the danger of highly concentrated frequency areas in turbine rotors; In response to the problem of cracks appearing at the root of the blades during the turbine rotor test run, the turbine rotor structure was optimized by adding shrouds at the blade crown. The positive effect of the shrouds on controlling blade vibration and reducing the dynamic stress response of the turbine rotor was demonstrated through finite element calculations.