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RESEARCH PAPER

Film-Cooling Effectiveness on a Gas Turbine Blade Tip Using Pressure-Sensitive Paint

[+] Author and Article Information
Jaeyong Ahn, Shantanu Mhetras, Je-Chin Han

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

J. Heat Transfer 127(5), 521-530 (May 25, 2005) (10 pages) doi:10.1115/1.1909208 History: Received July 28, 2004; Revised October 20, 2004; Online May 25, 2005
Copyright © 2005 by ASME
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References

Figures

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Schematic of test section and 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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Local blowing ratio for plane and squealer tip
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Calibration setup for PSP
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Calibration curve for PSP
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Distributions of pressure ratio (Pt/P) for plane blade tip (top row) and squealer blade tip (bottom row) for coolant injection through tip holes only (T case) and C=2.5%
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Film-cooling effectiveness distribution on plane blade tip
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Film-cooling effectiveness distribution on squealer blade tip
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Averaged film-cooling effectiveness for plane and squealer blade tip

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