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TECHNICAL PAPERS

Turbine Tip and Shroud Heat Transfer and Loading—Part A: Parameter Effects Including Reynolds Number, Pressure Ratio, and Gas-to-Metal Temperature Ratio

[+] Author and Article Information
Marc D. Polanka, Donald A. Hoying, Matthew Meininger, Charles D. MacArthur

Air Force Research Laboratory, AFRL/PRTT, Wright-Patterson AFB, OH 45433

J. Turbomach 125(1), 97-106 (Jan 23, 2003) (10 pages) doi:10.1115/1.1515338 History: Received October 30, 2001; Online January 23, 2003
Copyright © 2003 by ASME
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References

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Figures

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Schematic of turbine research facility
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Cross section of TRF test section
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Radial inlet temperature profiles
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Test window showing “steady” flow regime
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Effects of Reynolds number on blade loading at 96.5% span
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Effects of pressure ratio on blade loading at 96.5% span
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Local heat flux at 50 and 96.5% span for the baseline case
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Boundary layer state of blade at 96.5% span
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Effects of pressure ratio and Reynolds number on local Nusselt number at 96.5% span
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Pressure ratio effect at 96.5% span
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Effect of inlet temperature and inlet profile on local Nusselt number at 96.5% span
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Heat flux distribution on the tip and shroud for the baseline case
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Tip streamlines—gage locations indicated
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Comparing tip Nusselt numbers to (a) laminar correlation (b) turbulent correlation
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Tip Nusselt numbers comparing gas to metal Temperature and inlet profile effects
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Effects of Reynolds number and pressure ratio on shroud Nusselt number
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Effects of gas to metal temperature and inlet profile on shroud Nusselt number

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