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TECHNICAL PAPERS

Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part I: Adiabatic Effectiveness Measurements

[+] Author and Article Information
J. R. Christophel, K. A. Thole

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

F. J. Cunha

Pratt & Whitney, United Technologies Corporation, East Hartford, Connecticut 06108

J. Turbomach 127(2), 270-277 (May 05, 2005) (8 pages) doi:10.1115/1.1812320 History: Received October 01, 2003; Revised March 01, 2004; Online May 05, 2005
Copyright © 2005 by ASME
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References

Christophel,  J., Thole,  K. A., and Cunha,  F., 2005, “Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part II: Heat Transfer Measurements,” ASME J. Turbomach. 127, pp. 278–286.
Bunker, R. S., 2000, “A Review of Turbine Blade Tip Heat Transfer,” Turbine 2000 Symposium on Heat Transfer in Gas Turbine Systems, Cesme, Turkey.
Kim,  Y. W., and Metzger,  D. E., 1995, “Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models,” ASME J. Turbomach., 117, pp. 12–21.
Kim,  Y. W., Downs,  J. P., Soechting,  F. O., Abdel-Messeh,  W., Steuber,  G., and Tanrikut,  S., 1995, “A Summary of the Cooled Turbine Blade Tip Heat Transfer and Film Effectiveness Investigations Performed by Dr. D. E. Metzger,” ASME J. Turbomach., 117, pp. 1–11.
Kwak, J. S., and Han, J. C., 2002, “Heat Transfer Coefficient and Film-Cooling Effectiveness on a Gas Turbine Blade Tip,” GT2002-30194.
Kwak, J. S., and Han, J. C., 2002, “Heat Transfer Coefficient and Film-Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade,” GT2002-30555.
Acharya, S., Yang, H., Ekkad, S. V., Prakash, C., and Bunker, R., 2002, “Numerical Simulation of Film Cooling Holes on the Tip of a Gas Turbine Blade,” GT-2002-30553.
Hohlfeld, E. M., Christophel, J. R., Couch, E. L., and Thole, K. A., 2003, “Predictions of Cooling From Dirt Purge Holes Along the Tip of a Turbine Blade,” GT2003-38251.
Srinivasan,  V., and Goldstein,  R. J., 2003, “Effect of Endwall Motion on Blade Tip Heat Transfer,” ASME J. Turbomach., 125, pp. 267–273.
Ameri, A. A., 2001, “Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip,” 2001-GT-0156.
Moffat,  R. J., 1988, “Describing the Uncertainties in Experimental Results,” Exp. Therm. Fluid Sci., 1, pp. 3–17.
Fluent Inc., Fluent User’s Guide, Version 6.0, 2002 (Fluent Inc., New Hampshire).

Figures

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Schematic showing the approximate hole placement for the tip model
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Photo of SLA/foam model for the dirt purge and cooling holes
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Schematic of (a) wind tunnel facility and (b) test section for the blade tips
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Predicted and measured static pressure distributions for the large and small tip gap cases
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Discharge coefficients that were measured for the cooling holes, dirt purge holes, and TEF
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Local mass flux ratios for each of cooling holes placed on the pressure side of the blade
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Percent difference between computational and experimental flow rates at 0.68% coolant flow
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Location and description of line data taken along blade tip
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Measured adiabatic effectiveness levels on the tip for the small tip gap
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Predicted path lines for the 0.58% coolant flow at the small tip gap
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Data taken along the camber line for the small tip gap at two blowing ratios
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Measured adiabatic effectiveness levels for the large tip gap
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Data taken along the camber line for the large tip gap
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(a)–(c) Line data for the different cases
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Area-averages for (a) the entire blade tip and (b) the downstream 70% of blade
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Effectiveness contours with no dirt purge blowing with 0.07% coolant flow for the large tip gap

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