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TECHNICAL PAPERS

Heat Transfer Coefficients and Film Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade

[+] Author and Article Information
Jae Su Kwak, Je-Chin Han

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

J. Turbomach 125(4), 648-657 (Dec 01, 2003) (10 pages) doi:10.1115/1.1622712 History: Received December 01, 2001; Revised March 01, 2002; Online December 01, 2003
Copyright © 2003 by ASME
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References

Figures

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Schematic of a modern gas turbine blade with common cooling techniques
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Schematic of blow down facility
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Definition of blade tip and shroud
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Film-cooling measurement blade
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Geometry of film-cooling holes
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Pressure distribution on the shroud surface for C=1.5% and injection from tip hole only case
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(a) Relation between hue and temperature for both liquid crystals (b) Initial temperature distribution for C=1.5%
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Heat transfer coefficient for C=1.5% and coolant injection from tip holes only
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Conceptual view of flow in the cavity, (a) cavity closer to the trailing edge, (b) cavity closer to the leading edge
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Heat transfer coefficient for C=1.5% and coolant injection from both tip and pressure side holes
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Averaged heat transfer coefficient for C=1.5% and (a) coolant injection from tip holes only (b) coolant injection from both tip and pressure side holes
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Averaged heat transfer coefficient for coolant injection from both tip and pressure side holes and (a) C=1.0%, (b) C=2.5%
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Film cooling effectiveness for C=1.5% and coolant injection from tip holes only
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Film cooling effectiveness for C=1.5% and coolant injection from both tip and pressure side holes
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Averaged film cooling effectiveness for (a) and (b): C=1.5%, injection from tip holes only (c) and (d): C=1.5%, injection from both tip and pressure side holes
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Averaged film cooling effectiveness for injection from both tip and pressure side holes, (a) and (b): C=1.0%; (c) and (d): C=2.5%

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