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TECHNICAL PAPERS

Evaluation of Pressure Side Film Cooling With Flow and Thermal Field Measurements—Part I: Showerhead 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), 670-677 (Nov 07, 2002) (8 pages) doi:10.1115/1.1504441 History: Received November 02, 2001; Online November 07, 2002
Copyright © 2002 by ASME
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References

Ericksen,  V. L., and Goldstein,  R. J., 1974, “Heat Transfer and Film Cooling Following Injection Through Inclined Circular Tubes,” ASME J. Heat Transfer, 96, pp. 239–245.
Muska,  J. F., Fish,  R. W., and Suo,  M., 1976, “The Additive Nature of Film Cooling from Rows of Holes,” ASME J. Eng. Power, 98, pp. 457–474.
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.
Ethridge,  M. I., Cutbirth,  J. M., and Bogard,  D. G., 2001, “Scaling of Performance for Varying Density Ratio Coolants on an Airfoil with Strong Curvature and Pressure Gradient Effects,” ASME J. Turbomach., 123, pp. 1–7.
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.
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.
Cutbirth,  J. M., and Bogard,  D. G., 2002, “Evaluation of Pressure Side Film Cooling With Flow and Thermal Field Measurements—Part II: Turbulence Effects,” ASME J. Turbomach., 124, pp. 678–685.
Polanka, M. D., 1999, “Detailed Film Cooling Effectiveness and Three Component Velocity Field Measurements on a First Stage Turbine Vane Subject to High Freestream Turbulence,” Ph.D. Dissertation, The University of Texas at Austin.
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.
Witteveld, V. C., Polanka, M. D., and Bogard, D. G., 1999, “Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part I: Stagnation Region and Near-Suction Side,” ASME Paper No. 99-GT-49.
Sellers,  J. P., 1963, “Gaseous Film Cooling with Multiple Injection Stations,” AIAA J., 1, No. 9, pp. 2154–2156.
Polanka, M. D., Witteveld, V. C., and Bogard, D. G., 1999, “Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part I: Stagnation Region and Near-Pressure Side,” ASME Paper No. 99-GT-48.
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.
Polanka, M. D., Cutbirth, J. M., and Bogard, D. G., 2001, “Three Component Velocity Field Measurements in the Stagnation Region of a Film Cooled Vane,” ASME Paper No. 2000-GT-240.

Figures

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Turbine vane test section
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Film-cooling hole configuration and location of measurement plane
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Flow visualization of the showerhead film cooling with z/p=7.5 and Msh*=1.5
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Flow visualization of the upstream flow field for the pressure side film cooling with Ips=0.0 and Msh*=1.5
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Thermal profile of the showerhead coolant flow immediately upstream of the pressure side coolant row with Msh*=1.5 and x/d=−22
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Showerhead (a) mean and (b) rms profiles at x/d=−9 and −28 with Msh*=1.5
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Comparison of upstream coolant conditions for (a) Ips=0.0 and Msh*=1.5, (b) Ips=0.2 and Msh*=0.0, and (c) Ips=0.2 and Msh*=1.5
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Laterally averaged effectiveness for the pressure side film cooling for (a) Msh*=0.0, and (b) Msh*=1.5
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Lateral distribution of effectiveness for the combined coolant flow and predicted superposition at x/d=−28, and (a) Ips=0.2, and (b) Ips=1.2
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Flow visualization of the pressure side film cooling with and without showerhead flow
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Thermal profile of the pressure side coolant jet with Tu=0.5%, and x/d=−28 with Msh*=0.0 for (a) Ips=0.2, (b) Ips=1.2, and Msh*=1.5 for (c) Ips=0.2, and (d) Ips=1.2
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V-W velocity vectors representing the velocity field for the pressure side film cooling (PS3) at x/d=−28 for (a) Msh*=0.0,Ips=1.2, and Msh*=1.5,Ips=1.2 for (b) actual flow, and (c) embedded structure
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Turbulence levels of the pressure side film cooling with Ips=1.2 and x/d=−28 for (a) Msh*=0.0, and (b) Msh*=1.5

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