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RESEARCH PAPERS

Compressor Blade Forced Response Due to Downstream Vane-Strut Potential Interaction

[+] Author and Article Information
H.-W. D. Chiang, M. G. Turner

GE Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 118(1), 134-142 (Jan 01, 1996) (9 pages) doi:10.1115/1.2836594 History: Received March 10, 1993; Online January 29, 2008

Abstract

A blade forced response prediction system has been developed using an implicit two-dimensional CFD solver to model the rotor blade forced response due to the static pressure distortion (potential disturbance) from the downstream stator vanes and struts. The CFD solver predicts the static pressure distortion upstream of the stator vanes and struts, which is used to calculate the induced velocity perturbation at the rotor inlet. Using the velocity perturbation and the blade’s natural frequencies and mode shapes from a finite element model, the unsteady aerodynamic modal forces and the aerodynamic damping are calculated. A modal response solution is then performed. The results show that the stator vanes cause a significant amplification of the potential disturbances due to the struts. Effects of strut and vane modifications are examined using the analysis. A vane modification with an “optimized” flow angle distribution shows that the disturbance can be greatly reduced. Recent testing of the strut modification shows exceptional correlation with the prediction.

Copyright © 1996 by The American Society of Mechanical Engineers
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