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TECHNICAL PAPERS

Turbine Blade Trailing Edge Flow Characteristics at High Subsonic Outlet Mach Number

[+] Author and Article Information
Claus H. Sieverding

Turbomachinery & Propulsion Department, von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Genèse, Belgiume-mail: sieverding@vki.ac.be

Hugues Richard

DLR, Institut für Strömungsmechanik, D-37073 Göttingen, Germanye-mail: Hugues.Richard@dlr.de

Jean-Michel Desse

ONERA, Institut de Mécanique des Fluides de Lille, F-59045 Lille Cedex, Francee-mail: desse@onera.fr

J. Turbomach 125(2), 298-309 (Apr 23, 2003) (12 pages) doi:10.1115/1.1539057 History: Received November 16, 2001; Revised September 25, 2002; Online April 23, 2003
Copyright © 2003 by ASME
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References

Ubaldi, M., and Zunino, P., 1999, “An Experimental Study of the Unsteady Characteristics of the Turbulent Wake of a Turbine Blade,” 4th Int. Symp. Engineering Turbulence Modeling and Measurements, Ajaccio.
Cicatelli,  G., and Sieverding,  C. H., 1997, “The Effect of Vortex Shedding on the Unsteady Pressure Distribution around the Trailing Edge of a Turbine Blade,” ASME J. Turbomach., 119(4), pp. 810–819.
Traupel, W., 1997, Thermische Turbomaschinen, Erster Band, Springer.
Denton,  J. D., 1993, “Loss Mechanisms in Turbomachines,” ASME J. Turbomach., 115(4), pp. 621–656.
Sieverding,  C. H., Stanislas,  M., and Snoeck,  J., 1980, “The Base Pressure Problem in Transonic Turbine Blades,” ASME J. Eng. Power, 102(3), pp. 711–718.
Xu,  L., and Denton,  J. D., 1988, “The Base Pressure Loss of a Family of Four Turbine Blades,” ASME J. Turbomach., 110(1), pp. 9–17.
Jouini, D. B. M., Sjolander, S. A., and Moustapha, S. H., 2000, “Aerodynamic Performance of a Transonic Turbine Cascade at Off-Design Conditions,” ASME Paper No. 2000-GT-0482
Han,  L. S., and Cox,  W. R., 1983, “A Visual Study of Turbine Blade Pressure Side Boundary Layer,” ASME J. Eng. Power, 105(1), pp. 47–52.
Lawaczeck, O., and Heineman, J., 1975, “von Karman Vortex Street in the Wake of Subsonic and Transonic Blades,” AGARD-CP-177, Unsteady Phenomena in Turbomachinery, Paper 28.
Heinemann, J., and Bütefisch, K. A., 1997, “Determination of the Vortex Shedding Frequency of Cascades with Different Trailing Edge Thicknesses,” AGARD-CP-227, Unsteady Aerodynamics, Paper 11.
Carscallen, W. E., Feige, H. U., and Gostelow, J. P., 1996, “Transonic Turbine Vane Wake Flows,” ASME Paper No. 96-GT-419
Cicatelli, G., and Sieverding, C. H., 1996, “A Review of the Research on Unsteady Turbine Blade Wake Characteristics,” AGARD-CP-571, Loss Mechanisms and Unsteady Flows in Turbomchines, Paper 6.
Desse,  J. M., 1998, “Effect of Time Varying Wake Characteristics Behind Flat Plates,” AIAA J., 36(11), pp. 2036–2043.
Carscallen,  W. E., Currie,  T. C., Hogg,  S. I., and Gostelow,  J. P., 1998, “Measurement and Computation of Energy Separation in Vortical Wake Flow of a Turbine Blade,” ASME J. Turbomach., 121(4), pp. 703–708.
Arnone, A., and Pacciani, R., 1997, “Numerical Prediction of Trailing Edge Wake Shedding,” ASME Paper No. 97-GT-89.
Manna,  M., Mulas,  M., and Cicatelli,  G., 1997, “Vortex Shedding Behind a Blunt Trailing Edge Turbine Blade,” Int. J. Turbo Jet Engines, 14, pp. 145–157.
Sondak,  D. L., Dorney,  D. J., 1998, “Simulation of Vortex Shedding in a Turbine Stage,” ASME J. Turbomach., 121(3), pp. 428–435.
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Magagnato, F., 1999, “Unsteady Flow Past a Turbine Blade using Non-Linear Two-Equation Turbulence Models,” Proc., 3th European Turbomachinery Conference, London, United Kingdom.
Sieverding, C. H., Cicatelli, G., Desse, J. M., Meinke, M., and Zunino, P., 1999, Experimental and Numerical Investigation of Time Varying Wakes behind Turbine Blades, Notes on Numerical Fluid Mechanics Volume 67, Vieweg.
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Figures

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Photograph of test section
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Blade instrumented with pressure taps and equipped with rotatable trailing edge and boundary layer fences
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Oil flow visualization demonstrating effectiveness of boundary layer fences—top: without fences; bottom: with fences
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Blade Mach number distribution at M2,is=0.79
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Boundary layer profiles at trailing edge
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Typical FFT of fast response pressure transducer near pressure side boundary layer separation point
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Strouhal number in function of outlet Mach number
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Schlieren photographs for one vortex shedding cycle at M2,is=0.79
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Interferograms taken at four different phase angles of the vortex shedding cycle, M2,is=0.79
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Steady-state trailing edge pressure distribution
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Unsteady trailing edge pressure distribution recorded at 300 kHz
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Phase-lock-averaged pressure amplitudes around trailing edge
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Unsteady pressure variations along rear blade suction side
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Phase-locked average pressure variation at −60 and +40 deg trailing edge angle

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