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RESEARCH PAPERS: Turbomachinery

A Parametric Study of Dynamic Response of a Discrete Model of Turbomachinery Bladed Disk

[+] Author and Article Information
A. Muszyńska

University of Dayton Research Institute, Dayton, Ohio

D. I. G. Jones

Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio

J. Vib., Acoust., Stress, and Reliab 105(4), 434-443 (Oct 01, 1983) (10 pages) doi:10.1115/1.3269125 History: Received June 23, 1981; Online November 23, 2009

Abstract

A model consisting of n five-degree-of-freedom subsystems has been developed to characterize some of the mechanical response features of a bladed disk system, including four modes of each blade, n bending modes of the disk, blade-to-blade and blade-to-ground Coulomb friction, structural damping, blade-to-blade mistuning, and various types of excitation. The equations of motion and method of solution are described, and numerical results illustrate some of the interesting effects of various levels of frictional damping on tuned and mistuned systems, which may shed light on some aspects of damped system design and performance.

Copyright © 1983 by ASME
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