摘要
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.
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 aeroengine 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.
作者
张俊红
王杰
鲁鑫
戴胡伟
马梁
ZHANG Jun-hong;WANG Jie;LU Xin;DAI Hu-wei;MA Liang(State Key Laboratory of Engine,Tianjin University,Tianjin 300072,China;Ren＇ai College,Tianjin University,Tianjin 300000,China)
出处
《浙江大学学报（工学版）》
EI
CAS
CSCD
北大核心
2018年第5期980-987,共8页
Journal of Zhejiang University：Engineering Science
基金
国家自然科学基金资助项目(51501222)
中国民航局重大专项资助项目(MHRD20160106)
