考虑封严涂层的航空发动机叶片碰摩过程

为了分析封严涂层对航空发动机压气机叶片碰摩过程的影响，进行叶片-涂层/机匣碰摩过程的仿真模拟和实验研究.建立叶片-涂层/机匣碰摩动力学仿真模型，通过仿真分析获取一定转速下叶片-机匣碰摩和不同侵入深度下叶片-涂层碰摩时的叶尖应力和碰摩力；搭建叶片-涂层/机匣碰摩实验台，通过碰摩实验获取一定转速下叶片-机匣碰摩和不同侵入深度下叶片-涂层碰摩时的碰摩力和机匣上的加速度，分别进行对比分析.分析结果表明：封严涂层的存在有效降低了叶尖的应力和碰摩力以及峰值频率下的机匣振动加速度幅值；碰摩力具有周期性的脉冲特征，碰摩力随着侵入深度的增加而非线性增大；机匣振动加速度峰值频率为叶片通过频率及其倍频，峰值频率下的加速度幅值会随着侵入深度的增加而增大且高频下的增幅较大.
Abstract: The rubbing process between the blade and the coating/casing were analyzed through simulation and experiment approaches in order to analyze the effect of the seal coating on the rubbing process of aero-engine compressor blades. The dynamic model of blade-coating/casing rubbing was developed. The blade tip stress and the rubbing force under a certain speed with various invasion depths were obtained. The blade-coating/casing rubbing test bench was built and the rubbing force and the acceleration of the casing under the same speed were measured. Comparisons between the blade-casing rubbing and the blade-coated casing rubbing were conducted. Results show that the seal coating effectively reduces the blade tip stress, the rubbing force and the casing vibration acceleration amplitude at the peak frequency. The rubbing force is periodically pulsive and the magnitude increases nonlinearly with increasing invasion depth. The peak frequencies of the casing vibration are the blade-passing frequency and harmonics. The acceleration amplitudes under peak frequencies increase, with the increase of invasion depth and the acceleration amplitudes under high frequencies grow significantly.