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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Forced Response of Turbine Engine Bladed Disks and Sensitivity to Harmonic Mistuning

[+] Author and Article Information
J. A. Kenyon

Air Force Research Laboratory, Propulsion Directorate, Wright-Patterson AFB, OH 45433

J. H. Griffin

Department of Mechanical Engineering, Carnegie Mellon University, 5000 Forbes Avenue, Pittsburgh, PA 15213

J. Eng. Gas Turbines Power 125(1), 113-120 (Dec 27, 2002) (8 pages) doi:10.1115/1.1498269 History: Received December 01, 2000; Revised March 01, 2001; Online December 27, 2002
Copyright © 2003 by ASME
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References

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Bladh, R., Castanier, M. P., and Pierre, C., 2000, “Component-Mode-Based Reduced Order Modeling Techniques for Mistuned Bladed Disks, Part II: Application,” ASME Paper No. 2000-GT-0360.
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Figures

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Reduction in sensitivity near worst-case mistuning
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Maximum amplitude magnification as a function of number of harmonics
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Forced response approximation for nonsplitting modes
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The effects of various terms on the solution for splitting modes
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Mistuned response sensitivity curves
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Discrete mass-spring model of bladed disks
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Circular ring with a continuous ring-to-ground shear spring

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