某型航空发动机双转子系统碰摩分析及挠度抑制方法研究  

Rub Impact Analysis and Deflection Suppression Method Study of Double Rotor System of An Engine

作　　者：魏林章 WEI Linzhang(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》2024年第4期134-139,150,共7页Machine Building & Automation

摘　　要：针对航空发动机的碰摩故障,建立某型航空发动机转子系统三维有限元模型,进行临界转速计算、低压转子瞬态响应和双转子系统碰摩风险分析;进行双转子系统碰摩响应计算,得出双转子系统碰摩工况和位置识别;采用限位轴承进行挠度抑制。结果表明:双转子系统碰摩工况与位置符合低压转子瞬态响应与临界特性,低压转子的2、3阶临界特性受到了抑制。To deal with the rub impact failures of aeroengines,a three-dimensional finite element model of an engine rotor system is established to calculate the critical speed,and carry out the risk analysis of the transient response of low-pressure rotor and the rub impact of the dual rotor system.The rub impact response of the dual rotor system is calculated to abtain the rub impact condition and position identification of the dual rotor system.Limit bearing is used to restrain the deflection.The results show that the rub impact condition and position of the dual rotor system conform to the transient response and critical characteristics of the low-pressure rotor,and the second and third order critical characteristics of the low pressure rotor are restrained.

关 键 词：航空发动机 双转子系统 碰摩分析 临界转速 瞬态响应 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]