航空发动机双转子系统叶片-机匣碰摩故障模拟

doi:10.7527/S1000-6893.2021.25072

材料工程与机械制造

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航空发动机双转子系统叶片-机匣碰摩故障模拟

靳玉林^1,2, 刘治汶¹, 陈予恕³

1. 电子科技大学自动化工程学院, 成都 611731;
2. 西南交通大学机械工程学院, 成都 610031;
3. 哈尔滨工业大学航天学院, 哈尔滨 150001

收稿日期:2020-12-07 修回日期:2020-12-30 发布日期:2021-04-29
通讯作者: 刘治汶,E-mail:lzw1682007@126.com E-mail:lzw1682007@126.com
基金资助:
国家自然科学基金（52075080，12102084）；航空科学基金（20173319003）

Fault simulation of blade-casing rubbing for dual-rotor system of aero-engines

JIN Yulin^1,2, LIU Zhiwen¹, CHEN Yushu³

1. School of Automation Engineering, University of Electronic Science and Technology of China, Chengdu 611731, China;
2. School of Mechanical Engineering, Southwest Jiaotong University, Chengdu 610031, China;
3. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China

Received:2020-12-07 Revised:2020-12-30 Published:2021-04-29
Supported by:
National Natural Science Foundation of China (52075080, 12102084); Aeronautical Science Foundation of China (20173319003)

摘要/Abstract

摘要： 叶片-机匣碰摩严重影响航空发动机的性能、可靠性及安全性。考虑叶片-机匣碰摩、轴承非线性、联轴器不对中及高低压转子不平衡，利用有限元法建立双转子系统的非线性动力学模型；然后利用模态综合法缩减系统自由度，数值求解降阶模型的非线性振动响应，分析叶片-机匣碰摩故障响应特征。数值与实验结果表明：航空发动机双转子系统为多激励非线性系统，系统振动响应频率成分复杂，包括高低压转轴频率、多倍频、组合频率及其他复杂频率；当叶尖间隙较大时，叶片-机匣碰摩可能为局部碰摩，故障特征频率为叶片通过频率及其倍频，并在叶片通过频率两侧存在高低压转轴频率的调制边频带；当叶尖间隙较小时，叶片-机匣碰摩可能发生全周碰摩，呈现出由干摩擦引起的强烈自激振动。研究结果可为航空发动机双转子系统的叶片-机匣碰摩故障诊断及叶尖间隙设计提供一定参考。

关键词: 航空发动机, 双转子系统, 叶片-机匣碰摩, 有限元法, 模态综合法

Abstract: Blade-casing rubbing have very important effect on the performance, reliability and safety of the aero-engine. A dynamic model of the dual rotor-bearing system of the aero-engine is established based on the Finite Element Method (FEM) by taking into account blade-casing rubbing, misalignment and nonlinearities of the rolling element bearings. The Component Mode Synthesis (CMS) method is applied to reduce the high-degrees of freedom of the dynamic model, and the nonlinear vibration responses of the reduced order model are analyzed by the numerical method to reveal the features of blade-casing rubbing. The results of simulation and experiment show that the dual rotor-bearing system of the aero-engine is a multi-excitation nonlinear system, which presents complex frequency components for the vibration response, such as the rotation frequencies, multiple frequency components and combined frequencies of the high-pressure rotor and low-pressure rotor. For a wide blade-tip clearance, the blade-casing rubbing may be local rub-impact, where the fault feature frequency is manifested as the pass frequency of the blade and the corresponding doubling frequency, and there are a cluster of side bands on feature frequencies which are modulated by rotating frequencies of the dual rotor. For a small blade-tip clearance, the blade-casing rubbing may be full annular rub-impact, where a strong self-excited vibration is induced by dry friction. The results can provide references to fault diagnosis of blade-casing rubbing and blade-tip clearance design for the dual rotor system of aero-engine.

Key words: aero-engine, dual rotor-bearing system, blade-casing rubbing, finite element method, component mode synthesis (CMS) method

中图分类号:

V231.9

靳玉林, 刘治汶, 陈予恕. 航空发动机双转子系统叶片-机匣碰摩故障模拟[J]. 航空学报, 2022, 43(12): 425072-425072.

JIN Yulin, LIU Zhiwen, CHEN Yushu. Fault simulation of blade-casing rubbing for dual-rotor system of aero-engines[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 425072-425072.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

航空发动机双转子系统叶片-机匣碰摩故障模拟

Fault simulation of blade-casing rubbing for dual-rotor system of aero-engines

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