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TECHNICAL PAPERS

Thermal Field and Flow Visualization Within the Stagnation Region of a Film-Cooled Turbine Vane

[+] Author and Article Information
J. Michael Cutbirth, David G. Bogard

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

J. Turbomach 124(2), 200-206 (Apr 09, 2002) (7 pages) doi:10.1115/1.1451086 History: Received October 03, 2000; Online April 09, 2002
Copyright © 2002 by ASME
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References

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, Austin, TX.
Drost, U., and Bölcs, A., 1999, “Performance of a Turbine Airfoil with Multiple Film Cooling Stations Part 1: Heat Transfer and Film Cooling Effectiveness,” ASME Paper No. 99-GT-171.
Du, H., Han, J.-C., and Ekkad, S. V., 1997, “Effect of Unsteady Wake on Detailed Heat Transfer Coefficient and Film Effectiveness Distributions for a Gas Turbine Blade,” ASME Paper No. 97-GT-166.
Takeishi,  K., Aoki,  S., Sato,  T., and Tsukagoshi,  K., 1992, “Film Cooling on a Gas Turbine Rotor Blade,” ASME J. Turbomach., 114, pp. 828–834.
Thole, K. A., Sinha, A. K., Bogard, D. G., and Crawford, M. E., 1992, “Mean Temperature Measurements if Jets With a Crossflow for Gas Turbine Film Cooling Application,” Rotating Machinery Transport Phenomena, J. H. Kim and W. J. Yang, eds., Hemisphere Pub. Corp., New York, NY, pp. 65–81.
Oke, R. A., and Simon, I. W., 2000, “Measurements in Film Cooling with Lateral Injection: Adiabatic Effectiveness Values and Temperature Fields,” ASME Paper No. 2000-GT-597.
Pietryzk,  J. R., Bogar,  D. G., and Crawford,  M. E., 1990, “Effect of Density Ratio on the Hydrodynamics of Film Cooling,” ASME J. Turbomach., 112, pp. 437–450.
Sinha,  A. K., Bogard,  D. G., and Crawford,  M. E., 1991, “Gas Turbine Film Cooling: Flowfield due to a Second Row of Holes,” ASME J. Turbomach., 113, pp. 450–456.
Wang,  H. P., Olson,  S. J., Goldstein,  R. J., and Eckert,  E. R. G., 1997, “Flow Visualization in a Linear Turbine Cascade of High Performance Turbine Blades,” ASME J. Turbomach., 119, pp. 1–8.
Roy, R. P., Squires, K. D., Gerendas, M., Song, S., Howe, W. J., and Ansari, A., 2000, “Flow and Heat Transfer at the Hub Endwall of Inlet Vane Passages—Experiments and Simulations,” ASME Paper No. 2000-GT-198.
Schwarz, S. G., Goldstein, R. J., and Eckert, E. R. G., 1990, “The Influence of Curvature on Film Cooling Performance,” ASME Paper No. 90-GT-10.
Polanka, M. D., Cutbirth, J. M., and Bogard, D. G., 2001, “Three Component Velocity Field Measurements in the Stagnation Region of a Film Cooled Turbine Vane,” ASME Paper No. 2001-GT-0402.
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.
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, Austin, TX.
Witteveld, V. C., Polanka, M. D., and Bogard, D. G., 1999, “Film Cooling Effectiveness in the Showerhead Region of a Gas Turbine Vane Part II: Stagnation Region and Near-Suction Side,” ASME Paper No. 99-GT-49
Ethridge, M. I., Cutbirth, J. M., and Bogard, D. G., 2000, “Effects of Showerhead Cooling on Turbine Vane Suction Side Film Cooling Effectiveness,” ASME IMECE Conference, Orlando, FL.

Figures

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Turbine vane test section
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Film cooling hole configuration and location of measurement planes (dashed lines)
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Thermal profiles above the surface and along the Stag row of holes (x/d=0.0) showing the build-up effect for Msh=1.5
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Thermal profiles above the surface and along the PS2 row of holes showing the build-up effect for Msh=1.5
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Flow visualization of showerhead film cooling holes at x/d=0.0 and with Tu=0.5 percent. (images averaged over 1 second at 8 frames/s)
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Effect of the blowing ratio on the film cooling jet for the Stag row of holes (x/d=0.0). Profiles at z/p=7.2 and with Tu=0.5 percent.
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Comparison of laterally averaged adiabatic effectiveness for the showerhead region with Tu=0.5 percent.
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Showerhead adiabatic effectiveness contours for Tu=0.5 percent, DR=1.8 and blowing ratios (a) Msh=1.0, and (b) Msh=1.5
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Relationship of the thermal and velocity fields at z/p=7.2 for blowing ratios (a) Msh=0.0, (b) Msh=1.0, and (c) Msh=1.5
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Comparison of laterally averaged adiabatic effectiveness for the showerhead region with Tu=20 percent
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Effect of mainstream turbulence level on adiabatic effectiveness contours for Msh=1.5 and DR=1.8. (a) Tu=0.5 percent, and (b) Tu=20 percent
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Flow visualization of the Stag row (x/d=0) for Msh=1.5 and Tu=20 percent—(a) time-averaged, and (b) instantaneous images

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