局部剥落故障对滚动轴承接触与振动特性的影响

为了研究局部剥落故障对滚子与故障周边区域之间的接触特性以及轴承振动响应特征的影响规律,基于圆柱滚子与轴承滚道局部剥落故障之间接触关系,建立滚子与滚道接触等效有限元模型和考虑故障过渡区的圆柱滚子轴承动力学模型,研究故障宽度对滚子与滚道之间接触变形、应力、宽度和刚度以及轴承振动响应的影响规律。研究结果表明:随着局部剥落故障宽度的增大,接触宽度减小,接触应力与接触变形量增大;考虑局部剥落故障过渡区的轴承振动加速度大于不考虑局部剥落故障过渡区的轴承振动加速度。

轴承-轴承座系统振动特征与局部故障尺寸的关联

轴承-轴承座系统振动特征与局部故障尺寸的关联关系是轴承内部故障精确定量诊断的重要依据。针对不同尺寸局部故障诱发的轴承-轴承座系统振动特征的问题,采用显示动力学有限元算法,综合考虑其各部件的弹性变形、重力和轴承元件之间的接触与摩擦的影响,建立含局部故障的轴承-轴承座系统有限元动力学模型,研究不同尺寸局部故障诱发的轴承-轴承座系统的振动特征。分析局部故障尺寸变化对其振动特征的影响规律,揭示局部故障尺寸与轴承-轴承座系统振动特征之间关联关系,为获取其准确的振动特征提供了一种可行的手段,也为轴承-轴承座系统内部轴承早期局部故障的准确定量诊断提供了有效参考。

Optimization Method of Bearing Support Positions in a High-Speed Flexible Rotor System

Bearing support position is one of main factors affecting vibration characteristics of rotor systems. To optimize the bearing support positions in a high-speed flexible rotor system (HSFRS) based on the vibration characteristics, an optimization method of bearing support positions in the HSFRS is proposed. In this method, a finite element (FE) model of a high-speed flexible rotor (HSFR) was established. The natural frequencies and mode shapes of the HSFRS were used to obtain the initial design scheme of the bearing support positions. A frequency characteristic equation of the HSFRS was established to obtain the critical speeds of the HSFRS. And a dynamic model of the HSFRS was established to analyze the vibration characteristics for different bearing support position cases. The problem of optimizing bearing support positions in the HSFRS was solved by the developed method. The results showed that vibration amplitudes of the HSFRS were more stable when the bearing support positions were optimized. This study can provide a new method for optimizing bearing support positions of rotor systems.

航空发动机传动轴承多支承台架试验失效机理分析

作为航空发动机的关键部件之一,传动系统的工作性能直接决定整机的运行状态与可靠性。传动系统的支承轴承因工作环境恶劣,在其工作过程中极易出现早期失效故障。针对某航空发动机传动系统支承球轴承台架试验中出现早期失效的问题,采用有限元方法,建立了多点支撑柔性传动系统动力学模型,分析了转速和轴承游隙对系统各支承轴承的动态载荷与弹性变形的影响规律,确定了支承轴承发生失效的位置及其原因;采用Lundberg和Palmgre的疲劳寿命计算方法,基于多点支撑柔性传动系统动力学模型获得的轴承内部动态载荷,计算了台架系统中出现早期失效的支承球轴承的疲劳寿命。结果表明,支承轴承的游隙匹配会导致各轴承内部载荷存在较大差异,该差异是导致其疲劳失效的主要原因,该仿真结果与实际情况基本一致。论文的研究可为该型航空发动机传动系统支承轴承的优化设计提供新的思路和理论支撑。