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TECHNICAL PAPERS

Combustor Turbine Interface Studies—Part 1: Endwall Effectiveness Measurements

[+] Author and Article Information
W. F. Colban, K. A. Thole

Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

G. Zess

Pratt and Whitney, East Hartford, CT 06108

J. Turbomach 125(2), 193-202 (Apr 23, 2003) (10 pages) doi:10.1115/1.1561811 History: Received January 16, 2002; Online April 23, 2003
Copyright © 2003 by ASME
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References

Langston,  L. S., 1980, “Crossflows in a Turbine Cascade Passage,” ASME J. Eng. Power, 102, pp. 866–874.
Blair,  M. F., 1974, “An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls,” ASME J. Heat Transfer, Nov., pp. 524–529.
Granser, D., and Schulenberg, T., 1990, “Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud,” 90-GT-95.
Burd, S. W., and Simon, T. W., “Effects of Slot Bleed Injection over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I: Flow Field Measurements,” ASME Paper No. 2000-GT-199.
Burd, S. W., Satterness, C. J., and Simon, T. W., “Effects of Slot Bleed Injection over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II: Thermal Measurements,” 2000-GT-200.
Oke, R., Simon, T., Burd, S. W., Vahlberg, R., “Measurements in a Turbine Cascade Over a Contoured Endwall: Discrete Hole Injection of Bleed Flow,” 2000-GT-214.
Oke, R., Simon, T., Shih, T. Zhu, B., Lin, Y. L., Chyu, M. “Measurements Over a Film-Cooled, Contoured Endwall with Various Coolant Injection Rates,” 2001-GT-140.
Zhang,  L. J., and Jaiswal,  R. S., 2001, “Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint,” ASME J. Turbomach., 123, pp. 730–738.
Roy, R. P., Squires, K. D., Gerendas, M., Song, S., Howe, W. J., and Ansari, A., “Flow and Heat Transfer at the Hub Endwall of Inlet Vane Passages-Experiments and Simulations,” 2000-GT-198.
Kost,  F., and Nicklas,  M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I-Aerodynamic Measurements,” ASME J. Turbomach., 123, pp. 709–719.
Nicklas,  M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II-Heat Transfer and Film-Cooling Effectiveness Measurements,” ASME J. Turbomach., 123, pp. 720–729.
Radomsky,  R. W., and Thole,  K. A., 2000, “Flowfield Measurements for aHighly Turbine Flow in a Stator Vane Passage,” ASME J. Turbomach., 122, pp. 255–262.
M. D. Barringer, O. T. Richard, J. P. Walter, S. M. Stitzel, and K. A. Thole, 2001, “Flow Field Simulations of a Gas Turbine Combustor,” 2001-GT-0170; to appear in J. Turbomach.
Moffat,  R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1, pp. 3–17.
Stitzel, S. (2001), “Flow Field Computations of Combustor-Turbine Interactions in a Gas Turbine Engine,” MSME thesis, Mechanical Engineering Department, Virginia Tech.

Figures

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Comparison of pitchwise-averaged effectiveness
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Area-averaged adiabatic effectiveness levels
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Pitchwise-averaged adiabatic effectiveness levels  
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Flow field prediction for case 1 indicating injestion of flow above the step into the slot 13
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Adiabatic effectiveness contours for case 5
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Adiabatic effectiveness contours for case 5
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Adiabatic effectiveness contours for case 3
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Adiabatic effectiveness contours for case 2
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Adiabatic effectiveness contours for case 1
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Static pressure distribution along the vane midspan for the five cases investigated
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Flow uniformity of the mean and turbulent velocities measured at the midspan across both the inside and outside vane passages
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Total pressure profiles measured at the combustor exit for the five cases investigated in this study
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Total pressure contours across the vane passage (midpitch to midpitch) measured at combustor exit
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Total pressure profiles measured on top of the step at the exit of the combustor indicating the relative effect of the panel flows (a and b) and the dilution holes (c)
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Illustration of the film-cooling holes relative to the vane location (a); slot geometry (b), and film cooling-hole configuration (c)
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Schematic of the wind tunnel facility

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