• CN:11-2187/TH
  • ISSN:0577-6686

机械工程学报 ›› 2019, Vol. 55 ›› Issue (13): 38-44.doi: 10.3901/JME.2019.13.038

• 特邀专栏:航空发动机健康监测与故障诊断 • 上一篇    下一篇

基于声模态的压气机/风扇气路故障诊断

程礼1,2, 杨武奎1,3, 梁涛1, 文璧4, 姚东野1   

  1. 1. 空军工程大学航空工程学院 西安 710038;
    2. 先进航空发动机协同创新中心 北京 100191;
    3. 航泰动力机器厂 襄阳 441002;
    4. 中国航发涡轮研究院航空发动机高空模拟技术重点实验室 绵阳 621700
  • 收稿日期:2018-07-20 修回日期:2018-11-23 出版日期:2019-07-05 发布日期:2019-07-05
  • 通讯作者: 程礼(通信作者),男,1963年出生,博士,教授,博士研究生导师。主要研究方向为航空发动机结构、强度、振动与故障诊断。E-mail:846141917@qq.com
  • 作者简介:杨武奎,男,1975年出生,博士研究生。主要研究方向为航空发动机结构、强度与振动。E-mail:yangwukui1975@163.com;梁涛,男,1993年出生,硕士研究生。主要研究方向为航空发动机结构、强度与振动。E-mail:1120094801@qq.com;文璧,男,1983年出生,硕士,高级工程师。主要研究方向为航空发动机特种测试技术,故障诊断测试技术。E-mail:85282053@qq.com;姚东野,男,1977年出生,硕士,讲师。主要研究方向为航空发动机结构、强度与振动。E-mail:349795572@qq.com
  • 基金资助:
    国家重点基础研究发展计划资助项目(973计划,2015CB057400)。

Failure Diagnosis on Gas Path of Fan/compressor Based on Acoustic Mode

CHENG Li1,2, YANG Wukui1,3, LIANG Tao1, WEN Bi4, YAO Dongye1   

  1. 1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038;
    2. Collaborative Innovation Center for Advanced Engine, Beijing 100191;
    3. Hangtai Power Machinery Factory, Xiangyang 441002;
    4. Key Lab. of Engine Altitude Simulation Technology, Gas Turbine Establishment of Aero Engine Corporation of China, Mianyang 621700
  • Received:2018-07-20 Revised:2018-11-23 Online:2019-07-05 Published:2019-07-05

摘要: 通过压气机/风扇流道中声模态产生机理分析,阐述了压气机/风扇效率与声模态之间的联系,探索基于声模态的航空发动机气路故障的诊断方法。基于奇异值分解理论,提出了一种声模态信号的提取方法,并通过某风扇试验器试验数据处理,成功绘制出了声模态时序图。根据声模态时序图的波峰、波谷分布,辨识出该风扇在亚音速工作范围内既有前行声模态,又有后行声模态。而当后行声模态居于主导地位时,风扇效率明显下降,偏离设计指标,与实际故障现象相吻合,验证了声模态诊断方法的可行性。

关键词: 故障诊断, 航空发动机, 奇异值分解, 声模态, 压气机/风扇

Abstract: The relation between efficiency of compressor/fan and acoustic mode is set forth by analysing generating mechanism of acoustic mode in the flow duct of fan/compressor, the failure diagnosis method of aero-engine's gas path based on acoustic mode is explored. On the basis of singular value decomposition(SVD) theory,a kind of taking-up method for acoustic mode sensor is put forward,and in accordance with test data processing of a type of fan tester,time sequence diagram of acoustic mode is successfully drawn, both forward acoustic mode and backward acoustic mode co-existence are distinguished during the subsonic work range of the fan by wave crest and valley distribution of acoustic mode's time sequence diagram, at the same time the fan efficiency obviously decreasing is found when backward acoustic mode is in the leading status, and design requirement is deviated, the calculation results are in good agreement with the practical failure mode, the diagnosis method of acoustic mode is feasible by verifying.

Key words: acoustic mode, aero-engine, compressorfan, failure diagnosis, singular value decomposition(SVD)

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