A combined experimental and computational study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (>100 MW). This paper is concerned with the design and execution of the experimental portion of the study, which represents the first reported investigation to obtain nearly full surface information on heat transfer coefficients within an environment that develops an appropriate pressure distribution about an airfoil blade tip and shroud model. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high-pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of and total turning of about 110 deg. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5 or 9 percent. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp edge and rounded edge tip geometries at each of the inlet turbulence intensity levels. [S0889-504X(00)01902-4]
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April 2000
Technical Papers
Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results
Ronald S. Bunker,
Ronald S. Bunker
General Electric Corp. R&D Center, Schenectady, NY 12309
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Jeremy C. Bailey,
Jeremy C. Bailey
General Electric Corp. R&D Center, Schenectady, NY 12309
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Ali A. Ameri
Ali A. Ameri
AYT Corporation, Brook Park, OH 44135
Search for other works by this author on:
Ronald S. Bunker
General Electric Corp. R&D Center, Schenectady, NY 12309
Jeremy C. Bailey
General Electric Corp. R&D Center, Schenectady, NY 12309
Ali A. Ameri
AYT Corporation, Brook Park, OH 44135
Contributed by the International Gas Turbine Institute and presented at the 44th International Gas Turbine and Aeroengine Congress and Exhibition, Indianapolis, Indiana, June 7–10, 1999. Manuscript received by the International Gas Turbine Institute February 1999. Paper No. 99-GT-169. Review Chair: D. C. Wisler.
J. Turbomach. Apr 2000, 122(2): 263-271 (9 pages)
Published Online: February 1, 1999
Article history
Received:
February 1, 1999
Citation
Bunker , R. S., Bailey, J. C., and Ameri, A. A. (February 1, 1999). "Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 1—Experimental Results ." ASME. J. Turbomach. April 2000; 122(2): 263–271. https://doi.org/10.1115/1.555443
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