The design and development of current and future gas turbine engines for aircraft propulsion have focused on operating the high pressure turbine at increasingly elevated temperatures and pressures. The drive toward thermal operating conditions near theoretical stoichiometric limits as well as increasingly stringent requirements on reducing harmful emissions both equate to the temperature profiles exiting combustors and entering turbines becoming less peaked than in the past. This drive has placed emphasis on determining how different types of inlet temperature and pressure profiles affect the first stage airfoil endwalls. The goal of the current study was to investigate how different radial profiles of temperature and pressure affect the heat transfer along the vane endwall in a high pressure turbine. Testing was performed in the Turbine Research Facility located at the Air Force Research Laboratory using an inlet profile generator. Results indicate that the convection heat transfer coefficients are influenced by both the inlet pressure profile shape and the location along the endwall. The heat transfer driving temperature for inlet profiles that are nonuniform in temperature is also discussed.
Skip Nav Destination
Article navigation
April 2009
Research Papers
An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes
M. D. Barringer,
M. D. Barringer
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
Search for other works by this author on:
K. A. Thole,
K. A. Thole
Department of Mechanical and Nuclear Engineering,
Pennsylvania State University
, University Park, PA 16802
Search for other works by this author on:
M. D. Polanka
M. D. Polanka
Turbines Branch, Turbine Engine Division,
Air Force Research Laboratory
, WPAFB, OH 45433
Search for other works by this author on:
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 45433J. Turbomach. Apr 2009, 131(2): 021009 (10 pages)
Published Online: January 23, 2009
Article history
Received:
July 26, 2007
Revised:
December 5, 2007
Published:
January 23, 2009
Citation
Barringer, M. D., Thole, K. A., and Polanka, M. D. (January 23, 2009). "An Experimental Study of Combustor Exit Profile Shapes on Endwall Heat Transfer in High Pressure Turbine Vanes." ASME. J. Turbomach. April 2009; 131(2): 021009. https://doi.org/10.1115/1.2950072
Download citation file:
Get Email Alerts
Related Articles
Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration
J. Turbomach (January,2012)
Discussion: “Effect of Tip Clearance on the Thermal and Hydrodynamic Performance of a Shrouded Pin Fin Array” ( Moores, K. A., and Joshi, Y. K., 2003, ASME J. Heat Transfer, 125, pp. 999–1006)
J. Heat Transfer (August,2006)
Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine
J. Turbomach (April,2009)
Discrete Green’s Function Measurements in a Single Passage Turbine Model
J. Heat Transfer (April,2005)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
The Special Characteristics of Closed-Cycle Gas Turbines
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Combined Cycle Power Plant
Energy and Power Generation Handbook: Established and Emerging Technologies