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ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2025 , Vol. 46 >Issue 24: 232058 - 232058

DOI: https://doi.org/10.7527/S1000-6893.2025.32058

Solid Mechanics and Vehicle Conceptual Design

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

  • Xuanjun TAO ,
  • Pingchao YU ,
  • Yize JIN ,
  • Zhenyang XIANG ,
  • Dayi ZHANG
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  • 1.College of Civil Aviation，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
    2.Key Laboratory of Civil Aircraft Health Monitoring and Intelligent Maintenance，Nanjing University of Aeronautics and Astronautics，Nanjing 211106，China
    3.School of Energy and Power Engineering，Beihang University，Beijing 100191，China
    4.Beijing Key Laboratory of Aero-Engine Structure and Strength，Beihang University，Beijing 100191，China
E-mail： yupingchao@nuaa.edu.cn

Received date: 2025-04-01

  Revised date: 2025-04-15

  Accepted date: 2025-05-26

  Online published: 2025-06-05

Supported by

National Natural Science Foundation of China(52372387);Open Funds for Key Laboratory of Civil Aircraft Health Monitoring and Intelligent Maintenance(NJ2024022);China Postdoctoral Science Foundation(2022M711615);Postgraduate Research & Practice Innovation Program of NUAA(xcxjh20240722);National Science and Technology Major Project of China （J2022-Ⅳ-0005-0022）

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Abstract

This paper focuses on the research of the rubbing simulation method and dynamic characteristics of complex engine blades. Considering the influence of local blade contact and rotor whirl， a three-dimensional rubbing load and blade inertial load model is established 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 ultimately proposed. The proposed method is applied to conduct a rubbing analysis of the compressor blades of a certain aero-engine. The results show that tip rubbing can excite two rubbing states， which are related to the rubbing position. During the leading edge of the blade tip rubbing， the intermittent rubbing of the blade is easily to be excited. At this time， the blade repeatedly contacts and separates from the casing， and the blade exhibits high-frequency and high-amplitude modal vibration at 8 000 Hz. During the trailing edge of the blade tip rubbing， the full circumferential rubbing is more likely to be excited， and the blade undergoes static deformation 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. This paper can provide necessary theoretical method support for the dynamic analysis of aero-engine blades and clearance design.

Key words： aero-engine; rubbing; three-dimensional blade; vibration characteristics; dynamic model

Cite this article

Xuanjun TAO , Pingchao YU , Yize JIN , Zhenyang XIANG , Dayi ZHANG . Simulation method and dynamic characteristics analysis of complex blade rubbing in aero-engines[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(24) : 232058 -232058 . DOI: 10.7527/S1000-6893.2025.32058

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