航空发动机叶片-机匣碰摩故障的机匣振动加速度 特征分析及验证

为了提取叶片机匣碰摩状态下的机匣振动加速度特征,利用航空发动机转子系统模型的试验器,进行了转子叶片-机匣的单点碰摩和偏摩试验,通过频谱分析和倒频谱分析方法,分析了机匣振动加速度信号的碰摩特征,结果表明:机匣振动加速度具有明显的周期冲击特征,其冲击频率为旋转频率与叶片数的积,在频谱上出现了该冲击频率及其倍频,冲击的大小受旋转频率调制,在频率上表现出冲击频率及其倍频两侧出现了以旋转频率为间隔的边频带族。从倒频谱图中可以明显看出转频及其倍频的倒频率成分,并用实际航空发动机试车数据验证了分析结果。

Study on Rub-impact Responses of Rotor Systems Based on Hysteretic Rub-impact Force Model

In order to extract the casing acceleration vibration characteristics under blade-casing rubbing, rotor blade-casing single- point rubbing and partial rubbing experiments were performed with aeroengine rotor test rig. By means of the frequency spectrum analysis and the cepstrum analysis methods, the casing vibration acceleration signals were analyzed in order to extract the rubbing faults＂ characteristics. The results show that the casing signals under rubbing have obvious impact characteristics; the impact frequency equals the product of rotating frequency and the number of blades; there is the impact frequency and its frequency doubling in the frequency spectrum; the size of impact is modulated by rotating frequency, so that there are families of side bands on impact frequency and both sides of frequency doubling, and the side bands＂ interval equals the rotating frequency. There are obvious frequency components of the rotating frequency and its frequency doubling in the Cepstrum. The analysis results are verified by using the actual aeroengine test data.