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Research Papers: Gas Turbines: Structures and Dynamics

Forced Response of Mistuned Bladed Disks in Gas Flow: A Comparative Study of Predictions and Full-Scale Experimental Results

[+] Author and Article Information
Evgeny Petrov

Department of Mechanical Engineering, Imperial College London, Exhibition Road, SW7 2AZ, UKy.petrov@imperial.ac.uk

Luca Di Mare

Department of Mechanical Engineering, Imperial College London, Exhibition Road, SW7 2AZ, UKl.di.mare@imperial.ac.uk

Holger Hennings

German Aerospace Center, Institute of Aeroelasticity, Bunsenstrasse 10, Göttingen, Germanyholger.hennings@dlr.de

Robert Elliott

 Rolls-Royce plc, P.O. Box 31 Derby, DE24 8BJ, UKrobert.elliott@rolls-royce.com

J. Eng. Gas Turbines Power 132(5), 052504 (Mar 05, 2010) (10 pages) doi:10.1115/1.3205031 History: Received April 08, 2009; Revised April 15, 2009; Published March 05, 2010; Online March 05, 2010

An integrated experimental-numerical study of forced response for a mistuned bladed disk has been performed. A full chain for the predictive forced response analysis has been developed including data exchange between the computational fluid dynamics code and a code for the prediction of the nonlinear forced response for a bladed disk. The experimental measurements are performed at a full-scale single stage test rig with excitation by aerodynamic forces from gas flow. The numerical modeling approaches and the test rig setup are discussed. Comparison of experimentally measured and predicted values of blade resonance frequencies and response levels for a mistuned bladed disk without dampers is performed. A good correspondence between frequencies at which individual blades have maximum response levels is achieved. The effects of structural damping and underplatform damper parameters on amplitudes and resonance frequencies of the bladed disk are explored. It is shown that the underplatform damper significantly reduces scatters in values of the individual blade frequencies and maximum forced response levels.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

RGG wind tunnel at DLR: (a) a general view and (b) a configuration of a stage analyzed

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Figure 2

Rotor outside of the rig (a) and strain gauge location (b)

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Figure 3

The electronic board of the data acquisition system

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Figure 4

Experimentally determined Campbell diagram

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Figure 5

Repeatability of the measurements for blade resonance frequencies

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Figure 6

Repeatability of the measurements for blade maximum amplitudes

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Figure 7

NGV suction side boundary layer profiles from grid convergence study

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Figure 8

Comparison of computed and measured NGV wakes at 50% span

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Figure 9

Comparison of computed and measured NGV wakes at 90% span: computed values showing an effect of 0.1 mm gap for L2F optical window

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Figure 10

General view of the whole mistuned assembly (a) and nodes where mistuning elements are applied (b)

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Figure 11

FE models of a bladed disk sector (a) and an underplatform damper (b)

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Figure 12

Natural frequencies of the bladed disk

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Figure 13

Aerodynamic modal damping factors

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Figure 14

Excitation aerodynamic modal forces

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Figure 15

Envelope of the bladed disk forced response: a case 7EO excitation without dampers

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Figure 16

Frequencies providing maximum response levels for individual blades: a case of 7EO without dampers

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Figure 17

Frequencies providing maximum response levels for individual blades: a case of 5EO without dampers

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Figure 18

Comparison of predicted and measured maximum response levels for individual blades for a case of 7EO without dampers

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Figure 19

Effect of number of excitation harmonic applied simultaneously on the forced response

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Figure 20

Effect of excitation level on the forced response

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Figure 21

Effect of contact interface parameters of forced response: (a) friction coefficient and (b) contact stiffness

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Figure 22

Envelope of the mistuned forced response (7EO)

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Figure 23

Envelope of the mistuned forced response excited by 7EO with different levels of excitation

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Figure 24

Frequencies providing maximum response levels for individual blades: a case of 7EO with dampers

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Figure 25

Maximum response levels for individual blades for a case of 7EO with dampers

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