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TECHNICAL PAPERS

Convective Heat Transfer and Aerodynamics in Axial Flow Turbines

[+] Author and Article Information
Michael G. Dunn

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

J. Turbomach 123(4), 637-686 (Feb 01, 2001) (50 pages) doi:10.1115/1.1397776 History: Received February 01, 2001
Copyright © 2001 by ASME
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References

Figures

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Predicted versus measured unsteady surface pressure history at 50 percent span and 21 percent wetted distance on suction surface 34
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Predicted versus measured unsteady surface pressure on LPT blade at 50 percent span and 21 percent wetted distance on suction surface 34
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Predicted versus measured surface pressure for blade at 50 percent span, TFE-731 64
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(a) Influence of combustion on exit plane turbulence intensity for low-swirl geometry 89; (b) Influence of combustion on exit plane turbulence intensity for high-swirl geometry 89; (c) Exit plane radial turbulence intensity for high-swirl geometry 89
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Predicted versus measured Nusselt number distribution for Allison VBI blade, 187
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Predicted versus measured heat flux distribution for GE vane 189
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Predicted versus measured heat flux distribution for GE blade 189
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Predicted versus measured heat flux distribution for GE blade, three-dimensional 189
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Comparison of measured surface pressure with measured surface heat flux near blade stagnation point 187
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Comparison of measured surface pressure with measured surface heat flux on blade pressure surface near stagnation point 187
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Predicted versus measured unsteady Nusselt number for blade surface 187
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Predicted versus measured Nusselt number distribution for an uncooled Rolls Royce ACE turbine blade 238
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Predicted versus measured Nusselt number distribution for a cooled Rolls Royce ACE turbine blade; case #71 238
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Two-dimensional and three-dimensional predictions versus measured Nusselt number distribution for cooled blade of Rolls Royce ACE turbine, case #71 238
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Predicted versus measured heat transfer coefficient for cooled blade of Rolls Royce ACE turbine 324
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Vane and blade time-mean pressure at 20 percent spacing 31
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Vane and blade time-mean pressure at 60 percent spacing 31
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Vane and blade time-mean pressure at 20 percent spacing, three-dimensional calculation 31
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Predicted versus measured unsteady pressure envelope at 20 percent vane/blade spacing 31
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Predicted versus measured unsteady pressure envelope at 60 percent vane/blade spacing 31
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Predicted versus measured time-averaged surface pressure for vane and blade at 20 percent vane/blade spacing 32
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Magnitude and phase of unsteady surface pressure on blade at vane passing frequency 32
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Magnitude and phase of unsteady surface pressure on blade at 2× vane passing frequency 32
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Predicted versus measured time-averaged surface pressure for HPT vane and blade at midspan 34
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Predicted versus measured unsteady surface pressure envelope at 75 percent span for LPT blade 34
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Predicted versus measured Stanton number distribution for blade 66
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Predicted versus measured Nusselt number distribution for blade, various Reynolds numbers 161
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Influence of stagnation point initial profiles on blade heat transfer distribution, TFE-731 179
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Predicted versus measured Stanton number distribution for TFE 731-2 vane and blade, 179
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Predicted versus measured Nusselt number distribution for Rolls-Royce ACE blade 134
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Predicted versus measured Nusselt number distribution for Allison VBI 187

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