Study on the Effect of the Aero-Engine Mounting Stiffness on the Whole Engine Coupling Vibration

[+] Author and Article Information
Qu Meijiao

College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

Chen Guo

College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

1Corresponding author.

ASME doi:10.1115/1.4038542 History: Received September 07, 2016; Revised October 03, 2017


A finite element model of an aero engine rotor tester, which thin-wall casing structure and actual engine mounting, is established to simulate the intrinsic vibration characteristics under actual engine mounting condition. Firstly, the modal experiment of the whole aero-engine rotor tester is conducted, and the finite element simulation model is modified and validated based on the modal experimental results. Secondly, the first 3 orders natural frequencies and modal shapes are calculated by the modified finite element model under three kinds of the different mounting stiffness that are respectively the fixed mounting border, the free mounting border, and the flexible mounting border, and the influence of the mounting stiffness on the rotor and stator coupling vibration is studied by means of a new rotor-stator coupling factor which is proposed in this paper. The results show that, the higher is the rotor-stator coupling degree of the modal shape, the greater influence of the mounting condition on this modal shape is, in additional, the influence of mounting stiffness on the rotor-stator coupling degree is nonlinear. Rotor and stator coupling phenomena exsits in many modal shapes of the actual large turbofan engines, the effect of mounting stiffness on rotor-stator coupling can not be ignored, therefore, the mounting stiffness should be considered carefully in the finite element modeling and simulation for the paractic aero-engine vibration.

Copyright (c) 2017 by ASME
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