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TECHNICAL PAPERS

Heat Transfer and Flow on the First-Stage Blade Tip of a Power Generation Gas Turbine: Part 2—Simulation Results

[+] Author and Article Information
A. A. Ameri

AYT Corporation, Brook Park, OH 44135

R. S. Bunker

General Electric Corp. R & D Center, Schenectady, NY 12309

J. Turbomach 122(2), 272-277 (Feb 01, 1999) (6 pages) doi:10.1115/1.555444 History: Received February 01, 1999
Copyright © 2000 by ASME
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References

Figures

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Airfoil and shroud definition
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Overall grid using periodic flow assumption
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Model of complete passage: (a) overall geometry and grid; (b) close-up near leading edge
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Radiused edge tip and surface grid
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Blade pressure distribution data and computed pressure distribution using periodic conditions
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Near-tip pressure distribution data and computed pressure distribution using the complete passage and periodic cascade
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Blade tip surface pressure distribution with sharp edged tip and baseline clearance of 2.03 mm
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Blade tip surface pressure distribution with round edged tip and baseline clearance of 2.03 mm
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Heat transfer blade tip: (a) computational domain; (b) measuring area
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Sharp edged blade tip heat transfer coefficient (W/m2 /K) for clearance of 2.03 mm and Tu=5 percent: (a) measured; (b) calculated
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Radiused edge blade tip heat transfer coefficient (W/m2 /K) for clearance of 2.03 mm and Tu=5 percent: (a) measured; (b) calculated
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Flow streamlines over the blade tip for: (a) sharp edged blade; (b) radiused edge blade
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Magnitude of the velocity, V, at the midgap height of the blade tip for: (a) sharp edged blade; (b) radiused edge blade

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