The paper presents an experimental investigationof the effect of the trailing edge vortex shedding on the steady and unsteady trailing blade pressure distribution of a turbine blade at high subsonic Mach number and high Reynolds number The vortex formation and shedding process is visualized using a high-speed schlieren camera and a holographic interferometric density measuring technique. The blade is equipped with a rotatable trailing edge cylinder instrumented side-by-side with a pneumatic pressure tap and a fast response pressure sensor for detailed measurements of the trailing edge pressure distribution. The experiments demonstrate that contrary to the isobaric dead air region demonstrated at low subsonic Mach numbers the data reveal the existence of a highly nonuniform trailing edge pressure distribution with a strong pressure minimum at the center of the trailing edge. This finding is significant for the determination of the base pressure coefficient that is in general measured with a single pressure-sensing hole at the trailing edge center. The paper investigates further the effect of the vortex shedding on the blade rear suction side and discusses the superposition of unsteady effects emanating from the trailing edge and from the neighboring blade. The experimental data are a unique source for the validation of unsteady Navier-Stokes codes.
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April 2003
Technical Papers
Turbine Blade Trailing Edge Flow Characteristics at High Subsonic Outlet Mach Number
Claus H. Sieverding,
Claus H. Sieverding
Turbomachinery & Propulsion Department, von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Gene`se, Belgium
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Hugues Richard,
Hugues Richard
DLR, Institut fu¨r Stro¨mungsmechanik, D-37073 Go¨ttingen, Germany
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Jean-Michel Desse
Jean-Michel Desse
ONERA, Institut de Me´canique des Fluides de Lille, F-59045 Lille Cedex, France
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Claus H. Sieverding
Turbomachinery & Propulsion Department, von Karman Institute for Fluid Dynamics, B-1640 Rhode Saint Gene`se, Belgium
Hugues Richard
DLR, Institut fu¨r Stro¨mungsmechanik, D-37073 Go¨ttingen, Germany
Jean-Michel Desse
ONERA, Institut de Me´canique des Fluides de Lille, F-59045 Lille Cedex, France
Contributed by the International Gas Turbine Institute for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received by the IGTI November 16, 2001; revised manuscript received September 25, 2002. Associate Editor: S. Sjolander.
J. Turbomach. Apr 2003, 125(2): 298-309 (12 pages)
Published Online: April 23, 2003
Article history
Received:
November 16, 2001
Revised:
September 25, 2002
Online:
April 23, 2003
Citation
Sieverding, C. H., Richard, H., and Desse, J. (April 23, 2003). "Turbine Blade Trailing Edge Flow Characteristics at High Subsonic Outlet Mach Number ." ASME. J. Turbomach. April 2003; 125(2): 298–309. https://doi.org/10.1115/1.1539057
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