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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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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