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Research Papers: Gas Turbines: Structures and Dynamics

The Amplification of Vibration Response Levels of Mistuned Bladed Disks: Its Consequences and Its Distribution in Specific Situations

[+] Author and Article Information
Y.-J. Chan1

Department of Mechanical Engineering, Imperial College London, South Kensington, London SW7 2AZ, UKyj.chan@gmail.com

D. J. Ewins

Department of Mechanical Engineering, Imperial College London, South Kensington, London SW7 2AZ, UKd.ewins@imperial.ac.uk

1

Corresponding author.

J. Eng. Gas Turbines Power 133(10), 102502 (Apr 28, 2011) (8 pages) doi:10.1115/1.4003021 History: Received May 23, 2010; Revised November 10, 2010; Published April 28, 2011; Online April 28, 2011

It is known that small differences between nominally identical turbomachine blades, known as mistuning, can lead to significant variation in their vibration response levels. A commonly used term in mistuning studies called the “amplification factor” is clearly defined in this paper, and the high sensitivity of high-cycle-fatigue-related fatigue life to the level of vibration response levels is presented. Computer simulations are run to study the distribution of the amplification factor in three situations, namely, (i) bladed disks with damping mistuning, (ii) EO excitation of bladed disk modes in the veering region, and (iii) apparently tuned bladed disks. In addition to running simulations, the upper bound of the adjusted amplification factor in damping-mistuned bladed disks is derived theoretically.

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Copyright © 2011 by American Society of Mechanical Engineers
Topics: Damping , Vibration , Disks , Blades
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Figures

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Figure 1

The responses of a blade on a tuned bladed disk and a cantilevered blade

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Figure 2

Typical pdfs of amplification factor and partial amplification factors

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Figure 4

Layout of a 64-sector lumped parameter model

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Figure 5

Adjusted amplification factor pdfs under various levels of damping mistuning

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Figure 6

Selected normalized natural frequencies of the 64-sector models

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Figure 7

Tuned vibration response levels of Models 64C and 64E under various EO excitations

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Figure 8

Maximum adjusted amplification factor under various levels of mistune, without damping mistuning

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Figure 9

Adjusted amplification factor pdfs of Models 64C and 64E without damping mistuning

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Figure 3

Fatigue life of a coated superalloy, after Wright (15)

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Figure 11

Adjusted amplification factor pdfs of all selected samples

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Figure 12

Adjusted amplification factor pdfs of (a) apparently tuned bladed disks and (b) mistuned bladed disks

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Figure 10

Correlation between the adjusted amplification factor and the resonance frequency. Groups V1 and V2 correspond to bladed disks with resonance frequencies of about 167 Hz and about 197 Hz, respectively.

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