The high pressure rotor of aero-engine has a typical bolted connection structure. In order to study the relationship between the assembly performance of bolted connection and the composite load

a multi-axial excitation test system with axial tension and transverse vibration excitation is developed. The experiments of the system stability and the bolt assembly deviation are both designed and tested. The experimental results show that the frequency response characteristics are stable and effective when the variation range of the front and rear axial loads is less than 0.003 kN. When bolt assembly deviations exist in different positions

both vibration response frequency and amplitude will be affected. Finally

XGBoost intelligent algorithm is established to effectively identify the location of bolt assembly deviation by using specific frequency response peak value and amplitude.