航空发动机转子在冲击载荷下的振动响应分析与试验

Considering the nonlinear squeezed film damping (SFD) oil film force, the differential equation of motion of an aero-engine rotor was established. The vibration response of die rotor under impact load was decomposed into harmonic response and impact response. The finite element models for harmonic response and impact response were established respectively, and die vibration responses were calculated and analyzed. Experimental studies on the vibration characteristics of the aero-engine rotor under vertical impact load with different pulse width were carried out on a vibration table. The instantaneous vibration response of the rotor under impact load was obtained and compared with the calculated results. The study shows that in a certain rang of pulse width, the vibration response of the rotor decreases with the increase of pulse widtii. In addition, compared with die test results, the calculation error of vibration responses is between 10.44% -20.00%. The study provides a method for vibration response analysis and test of tlie rotor under impact load, and has important engineering application value.