Research on Vibration Response of Aero-Engine Rotor with SFD Under Vertical Impact Load

Considering the squeeze film damper (SFD) nonlinear oil film force, the differential equation of motion of an aero-engine rotor was established. The vibration response of rotor under impact load was decomposed into harmonic response and impact response. The finite element models of harmonic response and impact response were established respectively, and the vibration response was calculated and analyzed. Experimental study on the vibration characteristics of aero-engine rotor under vertical impact load with different pulse width was carried out on the vibration table. The instantaneous vibration response of the rotor under impact load was obtained and compared with the test results. Besides, the main frequency components of vibration response of aeroengine rotor with squeeze film damper under impact load were studied. The research results show that in a certain range of pulse width, the vibration response of rotor decreases with the increase of pulse width. In addition, compared with the test results, the calculation error of vibration response is between 10.44 and 20.00%. At the instant of impact, the fundamental frequency of rotor vibration response remains unchanged, but there are other complex frequency components. This study provides a method for vibration response analysis and test of rotor under impact load, and has important engineering application value.