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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

Panovsky, J., Nowinski, M., and Bölcs, A., 1997, “Flutter of Aircraft Engine Low Pressure Turbine Blades,” presented at the 8th International Symposium of Unsteady Aerodynamics and Aeroelasticity of Turbomachines, Stockholm, Sweden, Sept. 14–18, 1997.
Nowinski, M. C., Panovsky, J., and Bölcs, A., 1998, “Flutter Mechanisms in Low Pressure Turbine Blades,” to be presented at ASME Gas Turbine Conference and Exhibition, Stockholm, Sweden, June, 1998.
Bendiksen,  O., and Friedmann,  P., 1980, “Coupled Bending-Torsion Flutter in Cascades,” AIAA J., 18, pp. 194–201.
Försching, H., 1989, “A Parametric Study of the Flutter Stability of Two-Dimensional Turbine and Compressor Cascades in Incompressible Flow,” Zeitschrift für Flugwissenschaften und Weltraumforschung, Vol. 13, pp. 351–364.
Hall,  K. C., and Crawley,  E. F., 1989, “Calculation of Unsteady Flows in Turbomachinery Using the Linearized Euler Equations,” AIAA J., 27, No. 6, pp. 777–787.
Kirschner, A., Pelet, C., and Gyarmathy, G., 1976, “Investigation of Blade Flutter in a Subsonic Turbine Cascade,” Proceedings, International Union of Theoretical and Applied Mechanics and Association Technique pour la Turbine a Gaz, Symposium sur l’Aeroelasticite dans les Turbomachines, Paris, France, Oct. 18–23, 1976: Revue Francais de Macanique. Special Issue, pp. 97–104.
Whitehead, D. S., 1987, “Flutter of Turbine Blades,” Unsteady Aerodynamics and Aeroelasticity of Turbomachines and Propellors, Proceedings, Fourth International Symposium, Aachen, Germany, pp. 437–452, Sept. 6–10, 1987.
Holmes, D. G., and Chuang, H. A., 1993, “2D Linearized Harmonic Euler Flow Analysis for Flutter and Forced Response,” in Unsteady Aerodynamics, Aeroacoustics, and Aeroelasticity of Turbomachines and Propellers, H. M. Atassi, ed., Springer-Verlag, New York.
Crawley, E. F., 1988, “Aeroelastic Formulation for Tuned and Mistuned Rotors,” chap. 19 in AGARD Manual on Aeroelasticity in Axial-Flow Turbomachines, Vol. 2, Structural Dynamics and Aeroelasticity, M. F. Platzer and F. O. Carta, eds., AGARD-AG-298.
Buffum, D. H., and Fleeter, S., 1990, “Aerodynamics of a Linear Oscillating Cascade,” NASA Technical Memorandum 103250.
Szechenyi, E., 1985, “Fan Blade Flutter—Single Blade Instability or Blade to Blade Coupling?” ASME Paper 85-GT-216.
Panovsky, J., 1997, “Flutter of Aircraft Engine Turbine Blades,” Ph.D. thesis, University of Cincinnati, Cincinnati, OH.
Holmes, D. G., and Cedar, R. D., 1995, personal communication.
Bölcs, A., and Fransson, T. H., 1986, “Aeroelasticity in Turbomachines Comparison of Theoretical and Experimental Cascade Results. Appendix A5: All Experimental and Theoretical Results for the 9 Standard Configurations,” Communication du Laboratoire de Thermique Appliquee et de Turbomachines, EPF-Lausanne, No. 13.

Figures

Grahic Jump Location
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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