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Research Papers: Gas Turbines: Structures and Dynamics

Nonlinear Dynamic Analysis and Experiment Verification of Rotor-Ball Bearings-Support-Stator Coupling System for Aeroengine With Rubbing Coupling Faults

[+] Author and Article Information
G. Chen1

College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Jiangsu, Nanjing, 210016, P.R.C.cgzyx@263.net

C. G. Li

Strength and Vibration Technique Center, Shenyang Aeroengine Research Institute, Liaoning, Shenyang, 110015, P.R.C.lichenggang606@126.net

D. Y. Wang

Strength and Vibration Technique Center, Shenyang Aeroengine Research Institute, Liaoning, Shenyang, 110015, P.R.C.

1

Corresponding author.

J. Eng. Gas Turbines Power 132(2), 022501 (Oct 15, 2009) (9 pages) doi:10.1115/1.2940355 History: Received November 26, 2007; Revised May 05, 2008; Published October 15, 2009

In this paper, a new rotor-ball bearings-support-stator coupling system dynamic model with rubbing coupling faults is established for practical aeroengine. In the model, the rubbing fault is modeled, the stator motion is considered, the flexible support and squeeze film damper are established, and the nonlinear factors of ball bearing, such as the clearance of the bearing, the nonlinear Hertzian contact force between balls and races, and the varying compliance vibration because of the periodical variety of the contact position between balls and races, are modeled. The numerical integral method is used to obtain the system responses, the effect of support stiffness on rotor responses is studied using a vibration amplitude-rotating speed plot, and the characteristics of the rubbing fault is analyzed using a 3D cascade plot. An aeroengine tester with a stator is established to carry out the rubbing fault experiments, the simulation results from the rotor-ball bearings-support-stator coupling model are compared with the experimental results, and the consistency of the results show fully the effectiveness of the new rotor-ball bearings-support-stator coupling model with rubbing fault.

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Figures

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Figure 1

Rotor-ball bearings-support-stator coupling model with imbalance and rubbing coupling faults

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Figure 2

A sketch map of ball bearing model

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Figure 3

The rotor response in the X direction at rotor disk (300rpm)

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Figure 4

The rotor response in the Y direction at rotor disk (300rpm)

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Figure 5

Vibration amplitude-rotating speed plots of rotor responses under different support stiffnesses

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Figure 6

Cascade plot of rotor response

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Figure 7

Time wave form, frequency spectrum, and Poincaré map of the rotor response at a rotating speed of 1500rad∕s (kt=2.5×107N∕m, kr=1.25×108N∕m)

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Figure 8

The aeroengine rotor tester

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Figure 9

The vibration testing system of the aeroengine rotor tester

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Figure 10

The cascade plot of rotor rubbing fault response

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