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RESEARCH PAPER

Effects of Catalytic and Dry Low NOx Combustor Turbulence on Endwall Heat Transfer Distributions

[+] Author and Article Information
F. E. Ames, P. A. Barbot, C. Wang

Mechanical Engineering Department, University of North Dakota, Grand Forks, ND 58202

J. Heat Transfer 127(4), 414-424 (Mar 30, 2005) (11 pages) doi:10.1115/1.1861923 History: Received December 23, 2003; Revised October 12, 2004; Online March 30, 2005
Copyright © 2005 by ASME
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References

Kays, W. M., and Crawford, M. E., 1993, Convective Heat and Mass Transfer, 3rd ed., McGraw-Hill, New York.
Sieverding,  C. H., 1985, “Recent Progress in the Understanding of Basic Aspects of Secondary Flow in Turbine Blade Passages,” ASME J. Eng. Gas Turbines Power, 107, pp. 248–257.
Klein, A., 1966, “Investigation of the Entry Boundary Layer on the Secondary Flows in the Blading of Axial Turbines,” BHRA T 1004.
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Marchal, P., and Sieverding, C. H., 1977, “Secondary Flows Within Turbomachinery Bladings,” Secondary Flows in Turbomachines, AGARD CP 214.
Ames, F. E., Hylton, L. D., and York, R. E., 1986 (unpublished).
Zess, G. A., and Thole, K. A., 2001, “Computational Design and Experimental Evaluation of Using an Inlet Fillet on a Gas Turbine Vane,” ASME Paper No. 2001-GT-404.
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York,  R. E., Hylton,  L. D., and Milelc,  M. S., 1984, “An Experimental Investigation of Endwall Heat Transfer and Aerodynamics in a Linear Vane Cascade,” ASME J. Eng. Gas Turbines Power, 106, p. 159.
Harasgama,  S. P., and Wedlake,  E. T., 1989, “Heat Transfer and Aerodynamics of a High Rim Speed Turbine Nozzle Guide Vane Tested in the RAE Isentropic Light Piston Cascade,” ASME J. Turbomach., 113, pp. 384–391.
Spencer,  M. C., Jones,  T. V., and Lock,  G. D., 1996, “Endwall Heat Transfer Measurements in an Annular Cascade of Nozzle Guide Vanes at Engine Representative Reynolds and Mach Numbers,” Int. J. Heat Fluid Flow, 17, pp. 139–147.
Arts, T., and Heider, R., 1994, “Aerodynamic and Thermal Performance of a Three Dimensional Annular Transonic Nozzle Guide Vane, Part I—Experimental Investigation,” Paper No. 1994-31, 30th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.
Radomsky,  R., and Thole,  K. A., 2000, “High Freestream Turbulence Effects in the Endwall Leading Edge Region,” ASME J. Turbomach., 122, pp. 699–708.
Ames,  F. E., Barbot,  P. A., and Wang,  C., 2003, “Effects of Aeroderivative Combustor Turbulence on Endwall Heat Transfer Distributions Acquired in a Linear Vane Cascade,” ASME J. Turbomach., 125, pp. 210–220.
Goldstein,  R. J., and Spores,  R. A., 1988, “Turbulent Transport on the Endwall in the Region Between Adjacent Turbine Blades,” ASME J. Heat Transfer, 110, pp. 862–869.
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Figures

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Schematic of mock low NOx combustor turbulence generator
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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 distribution, ReC
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Comparison between CC and DLN inlet boundary layers, ReC=500,000 and 2,000,000
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Comparison of 95% span pressure distribution with midspan values, ReC=2,000,000
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Endwall flow visualization using lampblack and oil showing separation saddle point and pressure and suction surface separation lines (see Ref. 6)
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The large-scale low speed wind tunnel with cascade
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Schematic of the large-scale low speed cascade facility
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Endwall Stanton number contours, CC, Tu=0.01,Lu=3.8 cm,ReC=500,000
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Endwall Stanton number contours, DLN, Tu=0.134,Lu=8.8 cm,ReC=500,000
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Endwall Stanton number contours, CC, Tu=0.015,Lu=5.2 cm,ReC=1,000,000
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Endwall Stanton number contours, DLN, Tu=0.143,Lu=9.0 cm,ReC=1,000,000
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Endwall Stanton number contours, CC, Tu=0.01,Lu=1.8 cm,ReC=2,000,000
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Endwall Stanton number contours, DLN, Tu=0.142,Lu=10.8 cm,ReC=2,000,000

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