Aerodynamic Detuning Analysis of an Unstalled Supersonic Turbofan Cascade

[+] Author and Article Information
D. Hoyniak

NASA-Lewis Research Center, Cleveland, OH

S. Fleeter

School of Mechanical Engineering, Thermal Sciences and Propulsion Center, School of Mechanical Engineering, Purdue University, West Lafayette, IN

J. Eng. Gas Turbines Power 108(1), 60-67 (Jan 01, 1986) (8 pages) doi:10.1115/1.3239886 History: Received January 16, 1985; Online October 15, 2009


A new, and as yet unexplored, approach to passive flutter control is aerodynamic detuning, defined as designed passage-to-passage differences in the unsteady aerodynamic flow field of a rotor blade row. Thus, aerodynamic detuning directly affects the fundamental driving mechanism for flutter, i.e., the unsteady aerodynamic forces and moments acting on individual rotor blades. In this paper, a model to demonstrate the enhanced supersonic unstalled aeroelastic stability associated with aerodynamic detuning is developed. The stability of an aerodynamically detuned cascade operating in a supersonic inlet flow field with a subsonic leading edge locus is analyzed, with the aerodynamic detuning accomplished by means of nonuniform circumferential spacing of adjacent rotor blades. The unsteady aerodynamic forces and moments on the blading are defined in terms of influence coefficients in a manner that permits the stability of both a conventional uniformly spaced rotor configuration as well as the detuned nonuniform circumferentially spaced rotor to be determined. With Verdon’s uniformly spaced Cascade B as a baseline, this analysis is then utilized to demonstrate the potential enhanced aeroelastic stability associated with this particular type of aerodynamic detuning.

Copyright © 1986 by ASME
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