The high-pressure rotor is the core component of the turbofan engine

and its vibration problem is always prominent. It is very important and urgent to research the complex relationship between the assembly process data

the final technical state

and the vibration response for the high-pressure rotor. In this paper

a certain type of aero-engine highpressure combined rotor has been selected as the analysis object

and it is composed of a high-pressure compressor rotor and a high-pressure turbine rotor. The typical geometric characteristics and unbalanced parameters are used

and taking vibration response as the evaluation target

the comparative analysis of three high-pressure rotor connection and assembly methods have been conducted based on the stacking mechanism and dynamic modeling method. The influences of flat runout and unbalance on the vibration response have also been studied. The presented work provides the theoretical support for assembly process optimization to a certain extent

and hopes to supply some reference or inspiration for vibration trouble shooting of the aero-engine.