突加不平衡下GTF发动机转子系统瞬态响应分析

针对GTF发动机低压转子系统突加不平衡瞬态响应问题，基于有限元法建立了考虑啮合单元、行星架单元、膜盘联轴器单元的多体接触、多转子耦合动力学模型，介绍了考虑非线性因素下突加不平衡瞬态响应计算方法，求解了低压转子系统的突加不平衡瞬态响应，并分析了关键部件刚度对突加不平衡的影响规律。结果表明：当风扇转子发生突加不平衡时，各部件均表现为振动幅值突增，后迅速趋于稳定，低压涡轮转子发生明显拍振，突加不平衡载荷主要由行星架结构和第1.5支点刚性支承承担；行星架刚度主要影响风扇转子突加不平衡响应、第1.5支点和行星架处的外传力；膜盘联轴器刚度主要影响增压级突加不平衡响应、转子在突加不平衡之后稳定运转情况。

Transient Response Analysis of GTF Engine Rotor System Under Sudden Unbalance

In response to the transient response problem of a GTF engine low-pressure rotor system under sudden unbalance, a multi- body contact and multi-rotor coupling dynamic model considering meshing elements, planet carrier elements, and diaphragm coupling ele? ments was established based on the finite element method. The method considering nonlinear factors to calculate the transient response was introduced. The transient response of the low-pressure rotor system under sudden unbalance was solved, and the influences of stiffness of key components on sudden unbalance were analyzed. The results show that when the fan rotor experiences sudden unbalance, the vibration amplitude of each component increases suddenly and then stabilizes rapidly, and the low-pressure turbine rotor undergoes significant beat vibrations. The load due to the sudden unbalance is mainly borne by the planet carrier structure and the 1.5th rigid support; The stiffness of the planetary carrier mainly affects the sudden unbalance response of the fan rotor and the outward-transmitting forces at the 1.5th support and the planet carrier. The diaphragm coupling stiffness mainly affects the sudden unbalance response of the booster stage and the stable operation of the rotor after sudden unbalance.