Nonlinear dynamic analysis and experiment verification of rubbing faults of rotor-ball bearing-support-stator coupling system for aero-engine

CHEN Guo; LI Cheng-gang; WANG De-you

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Nonlinear dynamic analysis and experiment verification of rubbing faults of rotor-ball bearing-support-stator coupling system for aero-engine

更新时间：2026-07-07

- Nonlinear dynamic analysis and experiment verification of rubbing faults of rotor-ball bearing-support-stator coupling system for aero-engine
- Vol. 23, Issue 7, (2008)
- 作者机构：
  
  1. 南京航空航天大学民航学院,南京,210016
  2. 沈阳航空发动机设计研究所强度振动技术中心,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2008
- 稿件说明：
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CHEN Guo, LI Cheng-gang, WANG De-you. Nonlinear dynamic analysis and experiment verification of rubbing faults of rotor-ball bearing-support-stator coupling system for aero-engine[J]. 2008, 23(7).
DOI：

CHEN Guo, LI Cheng-gang, WANG De-you. Nonlinear dynamic analysis and experiment verification of rubbing faults of rotor-ball bearing-support-stator coupling system for aero-engine[J]. 2008, 23(7). DOI：

摘要

针对实际的航空发动机转子系统

建立了含碰摩故障的转子-滚动轴承-支承-机匣耦合动力学模型.在模型中

考虑了机匣运动

弹性支承、挤压油膜阻尼

充分考虑了轴承间隙、滚珠与滚道的非线性赫兹接触力以及由滚动轴承支撑刚度变化而产生的变柔性(VaryingcomplianceVC)振动.运用数值积分方法获取了系统响应

并建立带机匣的航空发动机转子实验器进行碰摩故障实验

仿真结果与实验结果比较分析表明了模型的有效性.

Abstract

Anew rotor-ball bearing-support-stator coupling system dynamic model including rubbing fault was established for rotor-bearing system of practical aeroengine.In the model

the stator motion

the flexible support

squeeze film damper(SFD) were considered

and the nonlinear factors of ball bearing such as the clearance of bearing

nonlinear Hertzian contract force between balls and races

and the varying compliance vibration because of periodical variety of contact position between balls and races were modeled.The numerical integral method was employed to obtain system's responses

and an aeroengine tester with stator was established to carry out rubbing fault experiment.Finally

the simulation results from rotor-ball bearing-support-stator coupling model were compared with the experiment results in order to indicate the validity of the new model.

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Related Institution

Liaoning Key Laboratory of Advanced Test Technology for Aerospace Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University

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College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

Civil Aviation College, Nanjing University of Aeronautics and Astronautics

Micro-Engine and Distributed Energy System Research Center, School of Transportation Science and Engineering, Beijing University of Aeronautics and Astronautics

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