Effect of Squeeze Film Damper on Rotor System with Rub-impact Fault under Maneuvering Flight Conditions

doi:10.7652/xjtuxb201511011

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Effect of Squeeze Film Damper on Rotor System with Rub-impact Fault under Maneuvering Flight Conditions

更新时间：2025-07-09

- Effect of Squeeze Film Damper on Rotor System with Rub-impact Fault under Maneuvering Flight Conditions
- Vol. 49, Issue 11, Pages: 62-70+141(2015)
- 作者机构：
  
  1. 天津大学内燃机燃烧学国家重点实验室,天津,300072
  2. 天津大学仁爱学院,天津,300000
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb201511011
  CLC： TH133.3
- Online First：10 November 2015，
  
  Published：2015
- 稿件说明：
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Effect of Squeeze Film Damper on Rotor System with Rub-impact Fault under Maneuvering Flight Conditions[J]. 2015, 49(11): 62-70+141.
DOI：

Effect of Squeeze Film Damper on Rotor System with Rub-impact Fault under Maneuvering Flight Conditions[J]. 2015, 49(11): 62-70+141. DOI： 10.7652/xjtuxb201511011.

摘要

飞机飞行时

航空发动机的故障对于飞机的安全性有着重要影响。针对这个问题

基于Lagrange方程

建立了飞机在空间进行机动飞行时发动机转子系统的动力学模型; 同时基于库伦定律

建立了转子碰摩故障模型; 基于雷诺方程

建立了挤压油膜阻尼器的模型; 对模型进行综合建模

得到不同机动飞行条件下转子-滚动轴承-挤压油膜阻尼器(SFD)系统非线性动力学微分方程

通过龙格库塔数值解法进行求解得到不同机动飞行状态下碰摩故障状态的系统振动响应

得到了不同机动飞行状态下碰摩故障转子系统的运动分岔图

同时利用典型转速(1 400 rad/s

2 000 rad/s)下转子系统的频谱图、庞加莱图、时域图和轴心轨迹图研究系统的动力学特性。研究结果表明:在高转速下

SFD能够显著提高系统的稳定性

抑制系统的非线性特征

但是在低转速下可能损害系统稳定性; 不同机动飞行状态下

SFD对于转子系统非线性特征的影响大小也不同。

Abstract

Aeroengine faults have crucial effect on the safety of aircraft flying. A model of aeroengine rotor system was presented by using the Lagrange equation during maneuvering flight

a model of rub-impact faults was built according to the Coulomb's friction

and a model of squeeze film damper(SFD)was built according to the Reynolds equation. The dynamic responses of rotor-SFD-ball-bearing system during different maneuvering flights under rub-impact faults were studied. The system equations were numerically integrated to obtain the vibration responses by Runge-Kutta method. The Bifurcation diagrams of the rotor system with rub-impact faults in different maneuvering flights

as well as the time-domain diagram

Poincare map

spectrum diagram and orbit plot of rotor system under typical rotating speeds(1 400 rad/s

2 000 rad/s)

were obtained to analyze the dynamic characteristics. The results show that the stability of the rotor system can be improved by SFD at high speed

and the non-linear characteristics of the system are weakened

but SFD may reduce the stability at low speed. Suppression of the non-linear response of the system by SFD depends on maneuvering flight conditions.

关键词

Keywords

references

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