RESEARCH PAPERS: Gas Turbines: Structures and Dynamics

Prediction of Resonant Response of Shrouded Blades With Three-Dimensional Shroud Constraint

[+] Author and Article Information
B. D. Yang, J. J. Chen, C. H. Menq

Department of Mechanical Engineering, 206 W. 18th Avenue, The Ohio State University, Columbus, OH 43210

J. Eng. Gas Turbines Power 121(3), 523-529 (Jul 01, 1999) (7 pages) doi:10.1115/1.2818504 History: Received March 25, 1998; Revised March 23, 1999; Online December 03, 2007


In this paper, the three-dimensional shroud contact kinematics of a shrouded blade system is studied. The assumed blade motion has three components, namely axial, tangential, and radial components, which result in a three dimensional relative motion across the shroud interface. The resulting relative motion can be decomposed into two components. The first one is on the contact plane and can induce stick-slip friction. The other component is perpendicular to the contact plane and can cause variation of the contact normal load and, in extreme circumstances, separation of the two contacting surfaces. In order to estimate the equivalent stiffness and damping of the shroud contact an approach is proposed. In this approach, the in-plane slip motion is assumed to be elliptical and is decomposed into two linear motions along the principal major and minor axes of the ellipse. A variable normal load friction force model (Yang and Menq, 1996) is then applied separately to each individual linear motion, and the equivalent stiffness and damping of the shroud contact can be approximately estimated. With the estimated stiffness and damping, the developed shroud contact model is applied to the prediction of the resonant response of a shrouded blade system. The effects of two different shroud constraint conditions, namely two-dimensional constraint and three-dimensional constraint, on the resonant response of a shrouded blade system are compared and the results are discussed.

Copyright © 1999 by The American Society of Mechanical Engineers
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