Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade

[+] Author and Article Information
Gm. S. Azad, Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

Robert J. Boyle

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 122(4), 725-732 (Feb 01, 2000) (8 pages) doi:10.1115/1.1311284 History: Received February 01, 2000
Copyright © 2000 by ASME
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Test section with five-bladed cascade
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Blade tip and shroud definition
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Pressure tap locations on blade and shroud
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(a) Coefficient of pressure at inlet and exit plane; (b) pressure distribution at midspan on the test blade and two nearby blades
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Pressure distributions from midspan to near-tip locations for C=1.5 percent and Tu=6.1 percent
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Pressure ratio distribution on the shroud surface
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Heat transfer coefficient at Tu=6.1 percent
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Heat transfer coefficient at Tu=9.7 percent
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Averaged heat transfer coefficient at: (a) Tu=6.1 percent; (b) Tu=9.7 percent




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