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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e-mail: yj.chan@gmail.com
e-mail: d.ewins@imperial.ac.uk
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October 2011
Research Papers
The Amplification of Vibration Response Levels of Mistuned Bladed Disks: Its Consequences and Its Distribution in Specific Situations
Y.-J. Chan,
Y.-J. Chan
Department of Mechanical Engineering,
e-mail: yj.chan@gmail.com
Imperial College London
, South Kensington, London SW7 2AZ, UK
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D. J. Ewins
D. J. Ewins
Department of Mechanical Engineering,
e-mail: d.ewins@imperial.ac.uk
Imperial College London
, South Kensington, London SW7 2AZ, UK
Search for other works by this author on:
Y.-J. Chan
Department of Mechanical Engineering,
Imperial College London
, South Kensington, London SW7 2AZ, UKe-mail: yj.chan@gmail.com
D. J. Ewins
Department of Mechanical Engineering,
Imperial College London
, South Kensington, London SW7 2AZ, UKe-mail: d.ewins@imperial.ac.uk
J. Eng. Gas Turbines Power. Oct 2011, 133(10): 102502 (8 pages)
Published Online: April 28, 2011
Article history
Received:
May 23, 2010
Revised:
November 10, 2010
Online:
April 28, 2011
Published:
April 28, 2011
Citation
Chan, Y., and Ewins, D. J. (April 28, 2011). "The Amplification of Vibration Response Levels of Mistuned Bladed Disks: Its Consequences and Its Distribution in Specific Situations." ASME. J. Eng. Gas Turbines Power. October 2011; 133(10): 102502. https://doi.org/10.1115/1.4003021
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