航空发动机叶片掉角故障疲劳机理试验方法研究

doi:10.3901/JME.2019.13.072

机械工程学报 ›› 2019, Vol. 55 ›› Issue (13): 72-79.doi: 10.3901/JME.2019.13.072

• 特邀专栏：航空发动机健康监测与故障诊断 • 上一篇下一篇

航空发动机叶片掉角故障疲劳机理试验方法研究

程礼^1,2, 陈礼顺^1,3, 李思路¹, 刘景元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. 南昌航空大学飞行器工程学院南昌 330063

收稿日期:2018-07-13 修回日期:2018-11-28 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,教授,博士研究生导师。主要研究方向为航空发动机故障监控与诊断,转子动力学。E-mail:846141917@qq.com
作者简介:陈礼顺,男,1973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:Lishun_chen@126.com;李思路,男,1994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:slli2016@163.com;刘景元,男,1993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:firdsh@sina.com
基金资助:
国家重点基础研究发展计划（973计划，2015CB057400）。

Fatigue Mechanism Experiment Method of Blade Fracture Failure in Aero-engine

CHENG Li^1,2, CHEN Lishun^1,3, LI Silu¹, LIU Jingyuan¹

1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038;
2. Co-Innovation Center for Advanced Aero-Engine, Beijing 100191;
3. Aircraft Engineering College, Nanchang Hangkong University, Nanchang 330063

Received:2018-07-13 Revised:2018-11-28 Online:2019-07-05 Published:2019-07-05

摘要/Abstract

摘要： 针对航空发动机叶片掉角故障，提出了一种采用叶片模拟试件进行高阶弯扭复合共振开展疲劳机理试验研究的方法。通过有限元模态分析，优化设计了一种方形平板叶片模拟试件，开展了高阶弯扭复合共振疲劳试验研究，验证了试件模拟叶片掉角故障的可行性。结果表明：模拟试件在"双扭弯曲复合"振型下进行共振试验可模拟引起掉角故障的高阶弯扭复合振型。在开展共振疲劳试验时，发现试件存在复杂的非线性振动特性，该特性对进行共振疲劳试验有重要影响。制定的疲劳裂纹判定方法可准确有效获得共振疲劳试验数据。

关键词: 裂纹判定标准, 疲劳强度, 弯扭复合共振, 叶片掉角故障, 叶片模拟试件

Abstract: Aiming at the blade fracture failure of the aero-engine, a testing methodology for researching the fatigue mechanism is proposed, in which the square plate specimen is designed by FEM (finite element modal) analysis, as the simulation of the blade, is driven into the high order composite bending-torsional mode by base excitation. The results show that the high order composite bending-torsional mode which causes the blade fracture failure can be effectively simulated by the composite double-torsional and bending mode of the specimen in the resonant test. At the resonant fatigue test, complex nonlinearity is appeared in the vibration of the specimen, which significantly affects the progress of the experiment. The data of the resonant fatigue experiment results can be accurately determined by the crack criterion developed for the specimen, which confirms that it's feasible to simulate the blade fracture failure with the specimen.

Key words: blade fracture failure, composited bending-torsion resonance, crack criterion, fatigue strength, specimen simulating blade

中图分类号:

V232

程礼, 陈礼顺, 李思路, 刘景元. 航空发动机叶片掉角故障疲劳机理试验方法研究[J]. 机械工程学报, 2019, 55(13): 72-79.

CHENG Li, CHEN Lishun, LI Silu, LIU Jingyuan. Fatigue Mechanism Experiment Method of Blade Fracture Failure in Aero-engine[J]. Journal of Mechanical Engineering, 2019, 55(13): 72-79.

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航空发动机叶片掉角故障疲劳机理试验方法研究

Fatigue Mechanism Experiment Method of Blade Fracture Failure in Aero-engine

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