航空发动机叶片颤振分析  

Flutter Analysis of Aeroengine Blades

作　　者：戴思成 DAI Sicheng(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2020年第6期66-69,共4页Machine Building & Automation

摘　　要：航空发动机的安全性和可靠性长期被叶片颤振问题所困扰。发生颤振时,由于剧烈的振动,在极短的时间内便可导致叶片断裂等严重后果。针对某型航空发动机压气机叶片,构造出两种叶片结构模型,运用MSC. Patran2008和MSC. Nastran2008,进行了模态分析和颤振分析。分别采用K-E法和P-K法计算两种叶片在亚声速内的临界颤振速度,分析了亚声速内马赫数(空气压缩性)对两种叶片临界颤振速度的影响,并基于计算结果比较了K-E法和P-K法的区别。The safety and reliability of aerospace engines are plagued with the blade flutter.This flutter results in severe vibration which can make the blade breaking in a very short period.The model of an aero-engine blade without or with torsion is established and its,modal analysis and flutter analysis are done by using MSC.Patran2008 and MSC.Nastran2008.The critical subsonic flutter frequency of the two blades is calculated by K-E method and P-K method respectively and the inflence of the subsonic Mach number(air compressibility)on the critical flutter frequency of two blades is analyzed,then,based on the calculation results,the K-E method is compared with P-K method.

关 键 词：气动弹性力学 叶片颤振 MSC.Nastran K-E法 P-K法 V-g图 

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]