The balancing process post-assembly of engine’s high-pressure turbine rotor is pivotal to ensuring the operational stability of the engine. Simulated balancing techniques are widely employed in the balancing of engine rotor

during which the rotor calibrator serves as a balancing fixture. To enhance the inherent stability of the high-pressure turbine rotor calibrator during the balancing process

a multi-objective planning approach for coaxiality and perpendicularity assembly adjustment has been proposed. An assembly error propagation model for the rotor calibrator has been established to regulate the coaxiality and perpendicularity of the rotor calibrator assembly in response to field application requirements. An analysis of the three components assembly process of the high-pressure turbine rotor calibrator reveals that optimizing the coaxiality and perpendicularity of the rotor calibrator can be achieved by altering the assembly angles of components at each level. Under the premise of meeting the specified criteria

the assembly angles can be selected based on the requirements of the application site to minimize either coaxiality or perpendicularity.