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TECHNICAL PAPERS: Combustion and Gas Turbine Heat Transfer

Heat Transfer Coefficients on the Squealer Tip and Near Squealer Tip Regions of a Gas Turbine Blade

[+] Author and Article Information
Jae Su Kwak

Aeropropulsion Department, Korea Aerospace Research Institutee-mail: jskwak@kari.re.kr

Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123e-mail: jchan@mengr.tamu.edu

J. Heat Transfer 125(4), 669-677 (Jul 17, 2003) (9 pages) doi:10.1115/1.1571849 History: Revised February 25, 2003; Online July 17, 2003; Received August 26, 2003
Copyright © 2003 by ASME
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References

Figures

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Schematic of blow-down facility
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Definition of blade tip and shroud
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Heat transfer measurement blade
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Detailed view of the blade tip
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(a) Definition of blade coordinate and location of pressure taps on the blade; and (b) Pressure distributions on the blade pressure and suction side with C=1.5 percent.
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Pressure distribution on the shroud surface
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(a) The relation between hue and temperature; and (b) initial temperature on the tip for C=1.5 percent.
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Heat transfer coefficient on the blade tip
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Conceptual view of flow near squealer tip: (a) the cavity closer to the trailing edge; and (b) the cavity closer to the leading edge
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Heat transfer coefficient on the shroud
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Heat transfer coefficient on the pressure side
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Heat transfer coefficient on the suction side
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Averaged heat transfer coefficient on the tip
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Averaged heat transfer coefficient on the shroud
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Averaged heat transfer coefficient on the pressure side
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Averaged heat transfer coefficient on the suction side

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