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RESEARCH PAPERS

Flutter of a Fan Blade in Supersonic Axial Flow

[+] Author and Article Information
R. E. Kielb, J. K. Ramsey

NASA Lewis Research Center, Cleveland, OH 44135

J. Turbomach 111(4), 462-467 (Oct 01, 1989) (6 pages) doi:10.1115/1.3262294 History: Received October 01, 1987; Online November 09, 2009

Abstract

An application of a simple aeroelastic model to an advanced supersonic axial flow fan is presented. Lane’s cascade theory is used to determine the unsteady aerodynamic loads. Parametric studies are performed to determine the effects of mode coupling, Mach number, damping, pitching axis location, solidity, stagger angle, and mistuning. The results show that supersonic axial flow fan and compressor blades are susceptible to a strong torsional mode flutter having critical reduced velocities that can be less than one.

Copyright © 1989 by ASME
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