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TECHNICAL PAPERS

Heat-Transfer Measurements and Predictions for the Vane and Blade of a Rotating High-Pressure Turbine Stage

[+] Author and Article Information
Charles W. Haldeman, Michael G. Dunn

Gas Turbine Laboratory, The Ohio State University, Columbus, OH 43235

J. Turbomach 126(1), 101-109 (Mar 26, 2004) (9 pages) doi:10.1115/1.1626132 History: Received December 01, 2002; Revised March 01, 2003; Online March 26, 2004
Copyright © 2003 by ASME
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References

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Figures

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HPT vane outer wall Stanton number as a function of axial chord at Re=7.94×106 (average runs 6, 8, 9, and 11)
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HPT vane outer wall Stanton number as a function of % pitch at Re=7.94×106 (average runs 6, 8, 9, and 11)
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Vane thermal-barrier-coating (VBC) effects on Stanton number at vane 50% span Re=7.94×106 (average runs 6, 8, 9, and 11)
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HPV pressure distribution with predictions, 50% span
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HPB pressure distribution with predictions, 50% span
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Vane Stanton number at 50% span; Reynolds number =7.94×106 (runs 6, 8, 9, and 11)
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Rotor Stanton number at 50% span; Reynolds number =7.94×106
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Influence of Reynolds number on vane Stanton number at 50% span
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Influence of Reynolds number on blade Stanton number at 50% span
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Comparison of measured and predicted Stanton number for HPT vane at 20% span
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Comparison of measured and predicted Stanton number for HPT vane at 80% span
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Comparison of measured and predicted Stanton number for HPT blade at 20% span
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Comparison of measured and predicted Stanton number for HPT blade at 96% span
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HPT blade tip and HPT blade shroud measured heat flux as a function of Reynolds number
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HPT blade tip and HPT blade shroud measured Stanton number as a function of Reynolds number
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HPT blade platform Stanton number at Re=8.24×106 (average runs 6 and 8)
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HPV inner wall Stanton number as a function of axial chord at Re=7.94×106 (average runs 6, 8, 9, and 11)
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HPV inner wall Stanton number as a function of pitch at Re=7.94×106 (average runs 6, 8, 9, and 11)

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