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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2022, Vol. 43 ›› Issue (12): 425072.doi: 10.7527/S1000-6893.2021.25072

• Material Engineering and Mechanical Manufacturing • Previous Articles     Next Articles

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

JIN Yulin1,2, LIU Zhiwen1, CHEN Yushu3   

  1. 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)

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

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