高压压气机转子叶片振动特性分析  

Vibration Characteristics Analysis of High-Pressure Compressor Rotor Blade

作　　者：魏武国[1] 侯宽新[2] 尚永锋[1] 

机构地区：[1]中国民航飞行学院航空工程学院,广汉618307 [2]中国民航飞行学院广汉分院,广汉618307

出　　处：《机械设计与制造》2012年第9期207-209,共3页Machinery Design & Manufacture

基　　金：中国民航飞行学院科研基金青年基金项目(Q2010-90)

摘　　要：基于ANSYS软件对某型航空发动机高压压气机第一级转子叶片的振动特性进行了分析研究,建立了叶片的三维有限元模型,采用分块Lanczos法,计算得到了叶片在发动机常用工况转速下的各阶自振频率、相应振型及振动应力分布,找出了应力较大的薄弱区域。最后考虑了高压压气机进口导流叶片后形成的气流尾迹对此级转子叶片的激振影响,得到该级转子叶片的共振图,结果证明该转子叶片在常用工况转速下,不会因为进口导流叶片后的气流尾迹引发共振。为叶片的后续结构分析、实验及振动排故提供了必要的数值依据。Based on the FEA software ANSYS,the vibration characteristics of an aero-engine＇s HPC rotor blades of the first level was analyzed.At first,a three dimension finite element model of the blade was established in ANSYS.Then,the vibration frequencies, vibration model and vibration stress distribution of the blade under the aero-engine＇s common rotating speeds were calculated by Block Lanczos method,and the area whose stress was larger than the other on the blade was also found out.At last,the wake influence caused by airflow behind the IGV of the HPC was considered,and the campbell curve was figured out.The results showed that the rotor blade will not cause resonance under the air exciting force caused by IGV trailing wake ,providing the necessary numerical basis for the subsequent structural analysis ,experiment and vibration troubleshooting of the blade.

关 键 词：压气机转子叶片 振动特性 气流尾迹 有限元 

分 类 号：TH16[机械工程—机械制造及自动化] V232.4[航空宇航科学与技术—航空宇航推进理论与工程]