The high pressure turbine stage within gas turbine engines is exposed to combustor exit flows that are nonuniform in both stagnation pressure and temperature. These highly turbulent flows typically enter the first stage vanes with significant spatial gradients near the inner and outer diameter endwalls. These gradients can result in secondary flow development within the vane passage that is different than what classical secondary flow models predict. The heat transfer between the working fluid and the turbine vane surface and endwalls is directly related to the secondary flows. The goal of the current study was to examine the migration of different inlet radial temperature and pressure profiles through the high turbine vane of a modern turbine engine. The tests were performed using an inlet profile generator located in the Turbine Research Facility at the Air Force Research Laboratory. Comparisons of area-averaged radial exit profiles are reported as well as profiles at three vane pitch locations to document the circumferential variation in the profiles. The results show that the shape of the total pressure profile near the endwalls at the inlet of the vane can alter the redistribution of stagnation enthalpy through the airfoil passage significantly. Total pressure loss and exit flow angle variations are also examined for the different inlet profiles.
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April 2009
Research Papers
Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes
M. D. Barringer,
M. D. Barringer
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
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K. A. Thole,
K. A. Thole
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
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M. D. Polanka,
M. D. Polanka
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
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J. P. Clark,
J. P. Clark
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
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P. J. Koch
P. J. Koch
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
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M. D. Barringer
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
K. A. Thole
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
M. D. Polanka
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
J. P. Clark
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
P. J. Koch
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433J. Turbomach. Apr 2009, 131(2): 021010 (10 pages)
Published Online: January 23, 2009
Article history
Received:
July 26, 2007
Revised:
January 3, 2008
Published:
January 23, 2009
Citation
Barringer, M. D., Thole, K. A., Polanka, M. D., Clark, J. P., and Koch, P. J. (January 23, 2009). "Migration of Combustor Exit Profiles Through High Pressure Turbine Vanes." ASME. J. Turbomach. April 2009; 131(2): 021010. https://doi.org/10.1115/1.2950076
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