某航空发动机压气机叶片振动分析  

Vibration analysis of aero-engine compressor blade

作　　者：付曦[1] 张俊红[1] 刘萌[1] 寇海军 林建生[1] FU Xi;ZHANG Jun-hong;LIU Meng;KOU Hai-jun;LIN Jian-sheng(State Key Laboratory of Engines, Tianjin University, Tianjin 30007)

机构地区：[1]天津大学内燃机燃烧学国家重点实验室,天津300072

出　　处：《机械设计》2018年第5期7-13,共7页Journal of Machine Design

基　　金：高等学校博士学科点专项科研基金资助项目(20130032130005);天津科技支撑计划重点资助项目(13ZCZDGX00200)

摘　　要：通过获取高精度点云数据实现高压压气机叶片数字化建模,采用不同方案拟合叶身曲面,建立了3种具有不同拟合精度的叶片实体模型,开展叶片振动试验验证模型可靠性。在叶片有限元振动研究中,进行叶片静频、动频和振动应力分析,得到典型工况下叶片的动态响应特性。分析发现,高转速工况下,3种模型高阶动频存在差异,模态振型及应力分布具有相对稳定性;开展叶片振动分析时,计算模型对叶片振动特性的还原度应作为数值研究的重要评价指标。研究结果为航空发动机叶片设计及其反求工程提供指导。The digital model of high pressure compressor blade was established by obtaining the high-precision point cloud data. In order to build various fitting precisions of three blade models, three modeling plans were proposed to fit the blade profile, conducted to verify the reliability of the model. In the research of blade vibration base on finite element method, the static, dynamic frequency and vibration stress of blade were calculated and analyzed. The dynamic response characteristics of the blade were obtained at different speed conditions. It is found that the high order modal frequency of three blade models has a large difference in high-speed conditions. The modal shapes and stress distributions of blade are relatively stable. For blade vibration numerical study, the restoration degree of blade vibration characteristic for the calculation model should become the important evaluating index. The results provide an academic foundation for designing and reverse engineering of aero-engine blade.

关 键 词：航空发动机 压气机叶片 数字化建模 振动分析 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]