For this study, a simulated film cooled turbine blade leading edge, constructed of a special high conductivity material, was used to determine the normalized “metal temperature” representative of actual engine conditions. The Biot number for the model was matched to that for operational engine conditions, ensuring that the normalized wall temperature, i.e., the overall effectiveness, was matched to that for the engine. Measurements of overall effectiveness were made for models with and without thermal barrier coating (TBC) at various operating conditions. This was the first study to experimentally simulate TBC and the effects on overall effectiveness. Two models were used: one with a single row of holes along the stagnation line, and the second with three rows of holes straddling the stagnation line. Film cooling was operated using a density ratio of 1.5 and for range of blowing ratios from to . Both models were tested using a range of angles of attack from 0.0 deg to ±5.0 deg. As expected, the TBC coated models had significantly higher external surface temperatures, but lower metal temperatures. These experimental results provide a unique database for evaluating numerical simulations of the effects of TBC on leading edge film cooling performance.
Skip Nav Destination
Article navigation
January 2011
Research Papers
Experimental Simulation of a Film Cooled Turbine Blade Leading Edge Including Thermal Barrier Coating Effects
Jonathan Maikell,
Jonathan Maikell
Department of Mechanical Engineering,
University of Texas at Austin
, Austin, TX 79712
Search for other works by this author on:
David Bogard,
David Bogard
Department of Mechanical Engineering,
University of Texas at Austin
, Austin, TX 79712
Search for other works by this author on:
Justin Piggush,
Justin Piggush
Pratt & Whitney
, United Technologies, CT 06108
Search for other works by this author on:
Atul Kohli
Atul Kohli
Pratt & Whitney
, United Technologies, CT 06108
Search for other works by this author on:
Jonathan Maikell
Department of Mechanical Engineering,
University of Texas at Austin
, Austin, TX 79712
David Bogard
Department of Mechanical Engineering,
University of Texas at Austin
, Austin, TX 79712
Justin Piggush
Pratt & Whitney
, United Technologies, CT 06108
Atul Kohli
Pratt & Whitney
, United Technologies, CT 06108J. Turbomach. Jan 2011, 133(1): 011014 (7 pages)
Published Online: September 21, 2010
Article history
Received:
March 23, 2009
Revised:
August 25, 2009
Online:
September 21, 2010
Published:
September 21, 2010
Citation
Maikell, J., Bogard, D., Piggush, J., and Kohli, A. (September 21, 2010). "Experimental Simulation of a Film Cooled Turbine Blade Leading Edge Including Thermal Barrier Coating Effects." ASME. J. Turbomach. January 2011; 133(1): 011014. https://doi.org/10.1115/1.4000537
Download citation file:
Get Email Alerts
Related Articles
Effects of Surface Deposition, Hole Blockage, and Thermal Barrier Coating Spallation on Vane Endwall Film Cooling
J. Turbomach (July,2007)
Effect of Hole Spacing on Deposition of Fine Coal Flyash Near Film Cooling Holes
J. Turbomach (July,2012)
Film Cooling Measurements for Cratered Cylindrical Inclined Holes
J. Turbomach (January,2009)
Deposition Near Film Cooling Holes on a High Pressure Turbine Vane
J. Turbomach (July,2012)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential