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TECHNICAL PAPERS

Heat Transfer Coefficients and Film Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade

[+] Author and Article Information
Jae Su Kwak, Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

J. Turbomach 125(4), 648-657 (Dec 01, 2003) (10 pages) doi:10.1115/1.1622712 History: Received December 01, 2001; Revised March 01, 2002; Online December 01, 2003
Copyright © 2003 by ASME
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References

Han, J. C., Dutta, S., and Ekkad, S. V., 2000, Gas Turbine Heat Transfer and Cooling Technology, Taylor & Francis, New York.
Metzger,  D. E., Bunker,  R. S., and Chyu,  M. K., 1989, “Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel,” ASME J. Heat Transfer, 111, pp. 73–79.
Chyu,  M. K., Moon,  H. K., and Metzger,  D. E., 1989, “Heat Transfer in the Tip Region of Grooved Turbine Blades,” ASME J. Turbomach., 111, pp. 131–138.
Heyes, F. J. G., Hodson, H. P., and Dailey, G. M., 1991, “The Effect of Blade Tip Geometry on the Tip Leakage Flow in Axial Turbine Cascades,” ASME Paper 91-GT-135.
Yang, T. T., and Diller, T. E., 1995, “Heat Transfer and Flow for a Grooved Turbine Blade Tip in a Transonic Cascade,” ASME Paper 95-WA/HT-29.
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Dunn,  M. G., and Haldeman,  C. W., 2000, “Time-Averaged Heat Flux for a Recessed Tip, Lip, and Platform of a Transonic Turbine Blade,” ASME J. Turbomach., 122, pp. 692–697.
Azad,  GM S., Han,  J. C., Teng,  S., and Boyle,  R., 2000, “Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip,” ASME J. Turbomach., 122, pp. 717–724.
Azad,  GM S., Han,  J. C., and Boyle,  R., 2000, “Heat Transfer and Pressure Distributions on the Squealer Tip of a Gas Turbine Blade,” ASME J. Turbomach., 122, pp. 725–732.
Azad,  GM S., Han,  J. C., Lee,  C. P., and Bunker,  R. S., 2001, “Effect of Squealer Geometry Arrangement on Gas Turbine Blade Heat Transfer,” ASME J. Heat Transfer, 124, pp. 452–459.
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Metzger,  D. E., Dunn,  M. G., and Hah,  C., 1991, “Turbine Tip and Shroud Heat Transfer,” ASME J. Turbomach., 113, pp. 502–507.
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Figures

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Schematic of a modern gas turbine blade with common cooling techniques
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Schematic of blow down facility
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Definition of blade tip and shroud
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Film-cooling measurement blade
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Geometry of film-cooling holes
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Pressure distribution on the shroud surface for C=1.5% and injection from tip hole only case
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(a) Relation between hue and temperature for both liquid crystals (b) Initial temperature distribution for C=1.5%
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Heat transfer coefficient for C=1.5% and coolant injection from tip holes only
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Conceptual view of flow in the cavity, (a) cavity closer to the trailing edge, (b) cavity closer to the leading edge
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Heat transfer coefficient for C=1.5% and coolant injection from both tip and pressure side holes
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Averaged heat transfer coefficient for C=1.5% and (a) coolant injection from tip holes only (b) coolant injection from both tip and pressure side holes
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Averaged heat transfer coefficient for coolant injection from both tip and pressure side holes and (a) C=1.0%, (b) C=2.5%
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Film cooling effectiveness for C=1.5% and coolant injection from tip holes only
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Film cooling effectiveness for C=1.5% and coolant injection from both tip and pressure side holes
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Averaged film cooling effectiveness for (a) and (b): C=1.5%, injection from tip holes only (c) and (d): C=1.5%, injection from both tip and pressure side holes
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Averaged film cooling effectiveness for injection from both tip and pressure side holes, (a) and (b): C=1.0%; (c) and (d): C=2.5%

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