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TECHNICAL PAPERS

Adiabatic Effectiveness Measurements of Endwall Film-Cooling for a First-Stage Vane

[+] Author and Article Information
D. G. Knost, K. A. Thole

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

J. Turbomach 127(2), 297-305 (May 05, 2005) (9 pages) doi:10.1115/1.1811099 History: Received October 01, 2003; Revised March 01, 2004; Online May 05, 2005
Copyright © 2005 by ASME
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References

Friedrichs,  S., Hodson,  H. P., and Dawes,  W. N., 1996, “Distribution of Film-Cooling Effectiveness on a Turbine Endwall Measured Using the Ammonia and Diazo Technique,” ASME J. Turbomach., 118, pp. 613–621.
Friedrichs,  S., Hodson,  H. P., and Dawes,  W. N., 1997, “Aerodynamic Aspects of Endwall Film-Cooling,” ASME J. Turbomach., 119, pp. 786–793.
Friedrichs,  S., Hodson,  H. P., and Dawes,  W. N., 1999, “The Design of an Improved Endwall Film-Cooling Configuration,” ASME J. Turbomach., 121, pp. 772–780.
Blair,  M. F., 1974, “An Experimental Study of Heat Transfer and Film Cooling on Large-Scale Turbine Endwalls,” ASME J. Heat Transfer, 97, pp. 524–529.
Granser, D., and Schulenberg, T., 1990, “Prediction and Measurement of Film Cooling Effectiveness for a First-Stage Turbine Vane Shroud,” ASME Paper No. 90-GT-95.
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,” ASME Paper No. 2000-GT-198.
Burd, S. W., and Simon, T. W., 2000, “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 Ijection over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part II Thermal Measurements,” ASME Paper No. 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,” ASME Paper No. 2000-GT-214.
Oke, R., Simon, T., Shih, T. Zhu, B., Lin, Y. L., and Chyu, M. “Measurements Over a Film-Cooled, Contoured Endwall with Various Coolant Injection Rates,” ASME Paper No. 2001-GT-140.
Colban,  W. F., Thole,  K. A., and Zess,  G., 2002, “Combustor-Turbine Interface Studies: Part 1: Endwall Measurements,” ASME J. Turbomach., 125, pp. 193–202.
Colban,  W. F., Lethander,  A. T., Thole,  K. A., and Zess,  G., 2002, “Combustor-Turbine Interface Studies: Part 2: Flow and Thermal Field Measurements,” ASME J. Turbomach., 125, pp. 203–209.
Zhang, L., and Moon, H. K., 2003, “Turbine Nozzle Endwall Inlet Film Cooling–The Effect of a Back-Facing Step,” ASME Paper No. GT-2003-38319.
Kost, F., and Nicklas, M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part I–Aerodynamic Measurements,” ASME Paper No. 2001-GT-0145.
Nicklas, M., 2001, “Film-Cooled Turbine Endwall in a Transonic Flow Field: Part II–Heat Transfer and Film-Cooling Effectiveness Measurements,” ASME Paper No. 2001-GT-0146.
Knost, D. K., and Thole, K. A., 2003, “Computational Predictions of Endwall Film-Cooling for a First Stage Vane,” ASME Paper No. GT-2003-38252.
Radomsky,  R. W., and Thole,  K. A., 2000, “Flowfield Measurements for a Highly Turbine Flow in a Stator Vane Passage,” ASME J. Turbomach., 122, pp. 255–262.
Harasgama,  S. P., and Burton,  C. D., 1992, “Film Cooling Research on the Endwall of a Turbine Nozzle Guide Vane in a Short Duration Annular Cascade: Part 1—Experimental Technique and Results,” ASME J. Turbomach., 114, pp. 734–540.
Barringer,  M. D., Richard,  O. T., Walter,  J. P., Stitzel,  S. M., and Thole,  K. A., 2002, “Flow Field Simulations of a Gas Turbine Combustor,” ASME J. Turbomach., 124, pp. 508–516.
Moffat,  R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1, pp. 3–17.

Figures

Grahic Jump Location
The two film-cooling patterns that were simulated in this study with iso–velocity contours (U/Uinlet) and injection direction for the cooling holes
Grahic Jump Location
(a) Illustration of wind tunnel facility, (b) cooling supply for slot and film cooling holes
Grahic Jump Location
Film-cooling holes for (a) Passage 1 and (b) the leading edge region
Grahic Jump Location
Contours of adiabatic effectiveness for the baseline film-cooling only cases: (a) pattern 1, 0.5% coolant (b) pattern #1, 0.75% coolant, (c) pattern #2, 0.5% coolant, and (d) pattern 2, 0.75% coolant
Grahic Jump Location
Contours of the difference between the predicted flow angles at 2% span and midspan are shown for the high 0.75% slot flow case. The hole locations of pattern 1 are shown for reference.
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Predicted streamlines at 2% span for both the 0.5% and 1.0% slot flow rates. The hole locations of pattern 1 are shown for reference.
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Predicted streamlines at 2% span for 0.5% slot flow without film cooling are superimposed on measured effectiveness levels for (a) pattern 1 with 0.5% slot flow and 0.5% film cooling and (b) pattern 2 with 0.5% slot flow and 0.5% film cooling
Grahic Jump Location
Predicted streamlines at 2% span for 1% slot without film cooling superimposed for (a) pattern 1 with 0.75% slot flow and 0.5% film cooling, and (b) pattern 2 with 0.75% slot flow and 0.5% film cooling
Grahic Jump Location
Area-averaged effectiveness levels for a range of coolant flow rates (percentage is based on total passage flow)
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Momentum flux ratios for holes indicated by the dashed lines are shown in (a) leading edge, (b) pressure side upstream, and (c) pressure side downstream regions. Hole locations are shown to the right

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