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TECHNICAL PAPERS

Measurement and Prediction of Heat Transfer Distributions on an Aft-Loaded Vane Subjected to the Influence of Catalytic and Dry Low NOx Combustor Turbulence

[+] Author and Article Information
F. E. Ames, M. Argenziano, C. Wang

Mechanical Engineering, University of North Dakota, UPII, Room 266, Grand Forks, ND 58202-8359

J. Turbomach 126(1), 139-149 (Mar 26, 2004) (11 pages) doi:10.1115/1.1645867 History: Received December 01, 2002; Revised March 01, 2003; Online March 26, 2004
Copyright © 2004 by ASME
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References

Figures

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Schematic of contoured endwall cascade test section with aft-loaded vane
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Cross-sectional view of large-scale aft-loaded vane used in the present study compared with conventionally loaded vane used in the previous study
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Schematic of mock combustor turbulence generator in aero-derivative configuration showing interface with cascade
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Digital photo of dry low NOx swirlers installed in mock combustor liner
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Digital photo of catalytic combustor surface installed in mock combustor liner
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Comparison between measured and predicted vane midspan pressure distributions for aft and fully loaded vanes
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Low turbulence vane Stanton number distributions with STAN7 predictions
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One-dimensional energy spectra of u for aero-derivative combustor
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Effects of mock combustor turbulence on vane Stanton number distributions, ReC=500,000
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Effects of mock combustor turbulence on vane Stanton number distributions, ReC=1,000,000
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Effects of mock combustor turbulence on vane Stanton number distributions, ReC=2,000,000
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Comparison between conventional and aft loaded vane heat transfer distributions, ReC=2,000,000, Catalytic and DLN combustor
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Effects of mock combustor turbulence on Stanton number augmentation and location of transition, ReC=500,000
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Effects of mock combustor turbulence on Stanton number augmentation and location of transition, ReC=1,000,000
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Effects of mock combustor turbulence on Stanton number augmentation and location of transition, ReC=2,000,000
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Correlation of pressure surface Stanton number augmentation with turbulence intensity, energy scale, and chord Reynolds number.
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Correlation of stagnation region Nusselt number augmentation with TRL parameter
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Prediction of turbulence effects on vane Stanton number distributions using STAN7 with ATM and Mayle 13, ReC=500,000
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Prediction of turbulence effects on vane Stanton number distributions using STAN7 with ATM and Mayle 13, ReC=1,000,000
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Prediction of turbulence effects on vane Stanton number distributions using STAN7 with ATM and Mayle 13, ReC=2,000,000

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