本文针对航空发动机双转子系统的碰摩故障进行了动力学仿真研究.对航空发动机双转子系统试验器的模型进行了简化,基于ADAMS平台,建立了双转子碰摩系统的多体动力学模型.分析获得了轻微碰摩、较重碰摩和严重碰摩三种碰摩状态下转子系统的时、频域振动响应和轴心轨迹.结果表明:在双转子碰摩系统中,随着转静件碰摩得从轻到重,其轴心轨迹和振动频谱成分发生了较大的变化;特别是在碰摩刚度和阻尼系数较大的条件下,振动响应的频谱变得越来越复杂,出现了高次谐波、组合谐波和次谐波成分.
This study investigates the rubbing fault of a double-rotor aeroengine system.First, based on a simplified double-rotor model test bench of an aeroengine, the dynamic model was established and analyzed using ADAMS simulation software.Second, the vibration responses in time and frequency domains, and the axis orbits of the rotor system were analyzed under three different rubbing states:slight rubbing, heavy rubbing, and severe rubbing.The simulation results show that the axle center orbits of the rotors and the vibration spectrum components significantly change with increased rubbing of the rotor-stator.In particular, with increased rubbing stiffness and damping coeffi-cients, the frequency spectrum of the vibration response becomes more complex and many frequencies appear, in-cluding higher harmonic, combination harmonic, and sub-harmonic frequencies.