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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

A Design Method to Prevent Low Pressure Turbine Blade Flutter

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

GE Aircraft Engines, 1 Neumann Way, MD A413 Cincinnati, OH 45215

J. Eng. Gas Turbines Power 122(1), 89-98 (Oct 20, 1999) (10 pages) doi:10.1115/1.483180 History: Received December 09, 1997; Revised October 20, 1999
Copyright © 2000 by ASME
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References

Figures

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Definition of the stability parameter
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Definition of fundamental mode shapes
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Damping as a function of IBPA for the three fundamental modes
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Magnitudes of the influence coefficients for the fundamental modes
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Stability parameter versus reduced frequency, including contributions due to reference blade and adjacent blade pair
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Damping as a function of torsion axis location for k=0.2 and IBPA=90 deg. The reference blade is in the center.
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Unstable regions (shaded) for various levels of reduced frequency
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Critical (flutter) reduced frequency as a function of torsion axis location near the reference blade
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Critical (flutter) reduced frequency as a function of torsion axis location for the expanded range

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