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TECHNICAL PAPERS

Evaluation of Pressure Side Film Cooling With Flow and Thermal Field Measurements—Part II: Turbulence Effects

[+] Author and Article Information
J. Michael Cutbirth

William B. Morgan Large Cavitation Channel, Naval Surface Warfare Center, Carderock Division, Memphis, TN 38113

David G. Bogard

Mechanical Engineering Department, University of Texas at Austin, Austin, TX 78712

J. Turbomach 124(4), 678-685 (Nov 07, 2002) (8 pages) doi:10.1115/1.1504442 History: Received November 02, 2001; Online November 07, 2002
Copyright © 2002 by ASME
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References

Moss, R. W., and Oldfield, L. G., 1991, “Measurements of Hot Combustor Turbulence Spectra,” ASME Paper No. 91-GT-351.
Goldstein,  R. J., Lau,  K. Y., and Leung,  C. C., 1983, “Velocity and Turbulence Measurements in Combustion Systems,” Exp. Fluids, 1, pp. 93–99.
Koutmos,  P., and McGuirk,  J. J., 1989, “Isothermal Flow in a Gas Turbine Combustor—A Benchmark Experimental Study,” Exp. Fluids, 7, pp. 344–354.
Radomsky, R. W., and Thole, K. A., 1998, “Effects of High Freestream Turbulence Levels and Length Scales on Stator Vane Heat Transfer,” ASME Paper No. 98-GT-236.
Moss, R. W., 1992, “The Effects of Turbulence Length Scale on Heat Transfer,” University of Oxford, Department of Engineering Science, Report No. OUEL 1924, Ph.D. Disseration.
Ames,  F. E., 1997, “The Influence of Large Scale High Intensity Turbulence on Vane Heat Transfer,” ASME J. Turbomach., 119, pp. 23–30.
Polanka, M. D., Witteveld, V. C., and Bogard, D. G., 1999, “Film Cooling Effecitveness in the Showerhead Region of a Gas Turbine Vane—Part I: Stagnation Region and Near-Pressure Side,” ASME Paper No. 99-GT-48.
Polanka, M. D., Ethridge, M. I., Cutbirth, J. M., and Bogard, D. G., 2000, “Effects of Showerhead Injection on Film Cooling Effectiveness of Downstream Rows of Holes,” ASME Paper No. 2000-GT-240.
Ames,  F. E., 1998, “Aspects of Vane Film Cooling with High Turbulence: Part II—Adiabatic Effectiveness,” ASME J. Turbomach., 120, pp. 777–784.
Drost, U., and Bölcs, A., 1999, “Performance of a Turbine Airfoil with Multiple Film Cooling Stations Part I: Heat Transfer and Film Cooling Effectiveness,” ASME Paper No. 99-GT-171.
Cutbirth,  J. M., and Bogard,  D. G., 2002, “Evaluation of Pressure Side Film Cooling With Thermal Field Measurements—Part I: Showerhead Effects,” ASME J. Turbomach., 124, pp. 670–677.
Cutbirth, J. M., 2000, “Turbulence and Three-Dimensional Effects on the Film Cooling of a Turbine Vane,” Ph.D. dissertation, The University of Texas at Austin.
Cutbirth, J. M., and Bogard, D. G., 2001, “Thermal Field and Flow Visualization within the Stagnation Region of a Film Cooled Turbine Vane,” ASME Paper No. 2001-GT-401.
Radomsky,  R., and Thole,  K. A., 2000, “Flowfield Measurements for a Highly Turbulent Flow in a Stator Vane Passage,” ASME J. Turbomach., 122(2), pp. 255–262.

Figures

Grahic Jump Location
Effect of turbulence on the pressure side film cooling as a function of blowing ratio for Tu=20% with integral length scale, Λx/d=7
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Effect of turbulence on the pressure side film cooling with Tu=0.5%,Msh=0.0, and (a) Ips=0.09, and (b) Ips=1.2
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Effect of turbulence on the pressure side film cooling with Msh=0.0,Tu=20%, and (a) Ips=0.11, and (b) Ips=1.2
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Thermal profiles for the pressure side film cooling with Msh=0.0 at x/d=−28 for (a) Tu=0.5% and (b) Tu=20%
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Instantaneous flow visualization at x/d=−28 with Msh=0.0 and (a) Ips=1.2,Tu=0.5%, (b) Ips=1.2,Tu=20%, and (c) Ips=0.2,Tu=20%
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RMS values at a location of x/d=−28 for Ips=1.2 and Msh=0.0
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Effect of turbulence on the mid-span pressure side film cooling with Msh*=1.5,Ips=0.2, and (a) Tu=0.5%, and (b) Tu=20%
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Superposition of the showerhead, Msh*=1.5, and pressure side film cooling with Tu=20% shown by the lateral distribution of effectiveness
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Thermal fields due to showerhead injection measured immediately upstream of the pressure side holes (x/d=−22) for (a) Tu=0.5%, and (b) Tu=20%
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Thermal profiles for the pressure side film cooling with Tu=20%,x/d=−28,Msh=1.5, and (a) Ips=1.2, (b) Ips=0.5, and (c) Ips=0.2
Grahic Jump Location
Instantaneous flow visualization with Ips=1.2,Msh*=1.5, for (a) Tu=0.5%, and (b) Tu=20% at x/d=−28
Grahic Jump Location
RMS values at a location of x/d=−28 for Ips=1.2 and Msh*=1.5

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