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Research Papers

Simulation Analysis of Casing Vibration Response and Its Verification Under Blade–Casing Rubbing Fault

[+] Author and Article Information
H. F. Wang

College of Civil Aviation,
Nanjing University of Aeronautics
and Astronautics,
No. 29 Jiangjun Dadao,
Jiangning District,
Nanjing 211106, China
e-mail: wanghaifei1986318@163.com

G. Chen

College of Civil Aviation,
Nanjing University of Aeronautics
and Astronautics,
No. 29 Jiangjun Dadao,
Jiangning District,
Nanjing 211106, China
e-mail: cgzyx@263.net

P. P. Song

College of Civil Aviation,
Nanjing University of Aeronautics
and Astronautics,
No. 29 Jiangjun Dadao,
Jiangning District,
Nanjing 211106, China
e-mail: spp0104@sina.com

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received March 9, 2015; final manuscript received December 19, 2015; published online March 21, 2016. Assoc. Editor: John Yu.

J. Vib. Acoust 138(3), 031004 (Mar 21, 2016) (14 pages) Paper No: VIB-15-1081; doi: 10.1115/1.4032512 History: Received March 09, 2015; Revised December 19, 2015

A new rotor–stator rubbing model considering the blade–casing rubbing fault is put forward in this paper. The model couples the rotor together with its suspension (ball or roller bearings), the disk, the (multiple) blades, and the casing. In addition, the influence of the rotor–stator clearance on rubbing forces was considered. It can simulate rubbing faults for single-point rubbing on the casing and complete-cycle rubbing on the rotor. The new rubbing model was applied to the rotor–support–casing coupling model, and the casing acceleration response under rubbing faults was obtained by the time-integration approach. The casing acceleration response, blade tip response, and rubbing force were analyzed. An aero-engine rotor tester, including casing, was used to carry out the rubbing experiment for single-point rubbing on the casing and for whole-cycle rubbing on the rotor. The simulation results were found in highly consistent with the experimental results, which fully verified the effectiveness of the new blade–casing rubbing model.

Copyright © 2016 by ASME
Topics: Rotors , Blades , Stators
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References

Figures

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Fig. 1

Elastic rubbing model

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Fig. 2

Diagram of blade–disk coupled dynamic model

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Fig. 3

Blade–casing rubbing model: (a) clearance curve, (b) rubbing clearance, and (c) rubbing force

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Fig. 4

Coupling model between two blades

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Fig. 5

Relationship between rotor–stator clearance and casing cycle angle change: (a) β = 5 deg and (b) β = 20 deg

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Fig. 6

Aero-engine rotor tester

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Fig. 7

Acceleration test points on turbine casing

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Fig. 8

Rotor–support–casing coupling dynamic model

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Fig. 9

Rotor–casing support

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Fig. 10

Solving flow for rotor–support–casing coupling dynamics with rubbing fault

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Fig. 11

Natural frequencies of blade in three directions for the simulation model: (a) the x′ tensile direction, (b) the y′ bending direction, and (c) the z′ bending direction

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Fig. 12

Four modes of the blade for the ansys model: (a) along the x tensile direction, (b) along the y bending direction, (c) along the z bending direction, and (d) around the x torsional direction

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Fig. 13

Time waveform: (a) experimental results and (b) simulation results

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Fig. 14

Time waveform (the enlargement of circled portion of Fig. 13): (a) experimental results and (b) simulation results

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Fig. 15

Spectrum: (a) experimental results and (b) simulation results

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Fig. 16

Spectrum (the enlargement of the circled portion 2 of Fig. 15): (a) experimental results and (b) simulation results

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Fig. 17

Spectrum (the enlargement of the circled portion 1 of Fig. 15): (a) experimental results and (b) simulation results

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Fig. 18

Cepstrum: (a) experimental results and (b) simulation results

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Fig. 19

Rubbing positions on (a) casing and (b) rotor blades for simulation model

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Fig. 20

Evolution of rubbing force between blade and casing for simulation model: (a) rubbing force changing with time and blade order and (b) rubbing force changing with time

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Fig. 21

Blade vibration mode under the rubbing fault for simulation model

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Fig. 22

Time waveform of the acceleration of 32 blade tips along the x′-axis for simulation model

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Fig. 23

Acceleration of the 32nd blade tip along the x′ axis, and its spectrum for simulation model: (a) time waveform, (b) time waveform (the enlargement of circled portion of (a)), (c) spectrum, and (d) spectrum

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Fig. 24

Time waveform of the acceleration of 32 blade tips around the z′-axis for simulation model

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Fig. 25

Acceleration of the 32nd blade tip along the y′-axis, and its spectrum for simulation model: (a) time waveform, (b) time waveform (the enlargement of circled portion of (a)), (c) spectrum, and (d) spectrum

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Fig. 26

Time waveform of 32 blade tips acceleration around z′-axis for simulation model

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Fig. 27

The acceleration of the 32nd blade tip along the z′-axis, and its spectrum for simulation model: (a) time waveform and (b) spectrum

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Fig. 28

Time waveform of the torsion angle of 32 blade tips around the x′ axis for simulation model

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Fig. 29

Torsion angle of the 32nd blade tip around the x′-axis, and its spectrum for simulation model: (a) time waveform and (b) spectrum

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