航空发动机复杂叶片碰摩仿真方法与动力学特性分析

  • 陶玄君 ,
  • 于平超 ,
  • 靳祎泽 ,
  • 向振洋 ,
  • 张大义
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  • 1. 南京航空航天大学
    2. 南京航空航天大学民航学院
    3. 北京航空航天大学,能源与动力工程学院

收稿日期: 2025-04-01

  修回日期: 2025-05-30

  网络出版日期: 2025-06-05

基金资助

国家自然科学基金;博士后科学基金面上项目;民航飞机健康监测与智能维护重点实验室自主基金专项资金;南京航空航天大学研究生科研与实践创新计划项目;国家科技重大专项

Simulation method and dynamic characteristics analysis of complex blade rubbing in aero-engines

  • TAO Xuan-Jun ,
  • YU Ping-Chao ,
  • JIN Yi-Ze ,
  • XIANG Zhen-Yang ,
  • ZHANG Da-Yi
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Received date: 2025-04-01

  Revised date: 2025-05-30

  Online published: 2025-06-05

Supported by

National Natural Science Foundation of China;China Postdoctoral Science Foundation;Open Funds for Key Laboratory of Civil Aircraft Health Monitoring and Intelligent Maintenance;Postgraduate Research & Practice Innovation Program of NUAA;National Science and Technology Major Project of the Ministry of Science and Technology of China

摘要

本文针对发动机复杂叶片开展碰摩仿真方法和动力学特性研究,考虑叶片局部接触与转子涡动影响,通过空间运动关系建立三维碰摩载荷与叶片惯性载荷模型;将上述载荷模型与降维后的叶片有限元模型进行组集,获得碰摩动力学方程;结合数值求解技术最终建立了发动机复杂叶片碰摩仿真方法。应用所提仿真方法开展某发动机压气机叶片碰摩分析,结果表明:叶尖碰摩可激发两种碰摩状态,其与碰摩位置有关,叶尖前缘碰摩时容易激发叶片间歇碰摩,此时叶片与机匣重复性的接触-分离,叶片呈现8000Hz的高频高幅模态振动;而叶尖尾缘碰摩则容易激发全周碰摩,此时叶片发生静变形。转子的非同步涡动则显著增加叶片碰摩行为的非线性程度,叶片振动频率将存在与涡动频率fe,fn相关的复杂组合频率。降低碰摩刚度、摩擦系数,能够有效抑制叶尖碰摩下叶片整体振动。本文研究可为航空发动机叶片动力学分析与间隙设计提供必要的理论方法支撑。

本文引用格式

陶玄君 , 于平超 , 靳祎泽 , 向振洋 , 张大义 . 航空发动机复杂叶片碰摩仿真方法与动力学特性分析[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32058

Abstract

This paper focuses on the research of the rubbing simulation method and dynamic characteristics of complex engine blades. Consid-ering the influence of local blade contact and rotor whirl, a three-dimensional rubbing load and blade inertial load model is estab-lished through the spatial motion relationship. The above load model is assembled with the reduced-dimensional finite element model of the blade to obtain the rubbing dynamic equation. Combined with numerical solution techniques, a rubbing simulation method for complex engine blades is finally established. The proposed simulation method is applied to conduct a rubbing analysis of the com-pressor blades of a certain engine. The results show that: Tip rubbing can excite two rubbing states, which are related to the rubbing position. When the leading edge of the blade tip rubs, it is easy to excite the intermittent rubbing of the blade. At this time, the blade repeatedly contacts and separates from the casing, and the blade exhibits high-frequency and high-amplitude modal vibration at 8000 Hz. When the trailing edge of the blade tip rub, it is likely to excite full circumferential rubbing, and the blade undergoes static de-formation at this time The non-synchronous whirl of the rotor significantly increases the nonlinearity of the blade rubbing behavior. The vibration frequency of the blade will have complex combined frequencies related to the whirl frequencies fe and fn. Reducing the rubbing stiffness and friction coefficient can effectively suppress the overall vibration of the blade under tip rubbing. The research of this paper can provide necessary theoretical method support for the dynamic analysis of aero-engine blades and clearance design.

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