• CN:11-2187/TH
  • ISSN:0577-6686

机械工程学报 ›› 2019, Vol. 55 ›› Issue (13): 23-37.doi: 10.3901/JME.2019.13.023

• 特邀专栏:航空发动机健康监测与故障诊断 • 上一篇    下一篇

航空发动机叶片脱落的非线性瞬态动力学研究

刘阳, 李诚, 李富才, 李鸿光   

  1. 上海交通大学机械系统与振动国家重点实验室 上海 200240
  • 收稿日期:2018-07-15 修回日期:2018-12-13 出版日期:2019-07-05 发布日期:2019-07-05
  • 通讯作者: 李富才(通信作者),男,1976年出生,教授,博士研究生导师。主要研究方向为旋转机械故障诊断,机械设备的智能监测。E-mail:fcli@sjtu.edu.cn
  • 作者简介:刘阳,男,1991年出生。主要研究方向为转子非线性瞬态动力学。E-mail:liuyangsjtu@qq.com
  • 基金资助:
    国家科技支撑计划(2015BAF07B03)和上海市基础研究重点(15JC1402600)资助项目。

Non-linear Transient Rotor-dynamics Analysis of Fan Blade Out

LIU Yang, LI Cheng, LI Fucai, LI Hongguang   

  1. State Key Lab of Mechanical System and Vibration, Shanghai Jiao Tong University, Shanghai 200240
  • Received:2018-07-15 Revised:2018-12-13 Online:2019-07-05 Published:2019-07-05

摘要: 航空发动机叶片脱落(Fan blade out,FBO)的研究是在整机结构可靠性及安全性设计阶段必须解决的重要问题。涡扇叶片由于疲劳断裂或外物撞击而断裂,转子系统在巨大不平衡力作用下产生较大涡动,进而使得叶片的尖端与机匣发生碰撞及摩擦等。保留涡扇叶片进行瞬态动力学分析是创新点,具体思路是将FBO问题分成三部分进行分析,首先是研究多支撑变截面转轴的临界转速和瞬态不平衡响应,接下来是研究叶片尖端受到冲击载荷时叶片的瞬态响应及其根部载荷的变化,最后是将转轴与涡扇叶片连接在一起进行瞬态动力学分析,得到转子系统任意一点的瞬态响应及其减速曲线。通过对参数的修改可以针对不同型号的航空发动机和燃气轮机进行瞬态响应分析,最终形成通用的分析叶片与机匣碰摩的理论模型。

关键词: FBO, 非线性瞬态动力学, 叶片尖端与机匣碰摩

Abstract: The research of fan blade out is a significant issue on the phase of structural reliability and safety design. A FBO event may be caused by fatigue break or impact damage by foreign objects. Low-pressure rotor system would vibrate severely with huge unbalance force. Because of that, the tip of blades would rub with the containment. Innovative point of the research is to calculate transient response remaining fan blades. The analysis procedure is divided into three parts. Firstly, critical speed and transient unbalance response analysis of various cross-section shaft with multi-supports have been done. Secondly, non-linear dynamical equations of fan blades' tip subjected impact and load at root of blade are obtained. Finally, combine dynamical equations of shaft with fan blades subjected impact to analyze transient response and rotate speed after FBO. Transient response of different aero-engines and gas turbines can be analyzed by modifying parameters. Finally, general theoretical model of analyzing the rubbing between blades and case can be obtained.

Key words: contact-impact and rubbing, FBO, non-linear transient rotor-dynamics

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