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TECHNICAL PAPERS

Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade

[+] Author and Article Information
Gm. S. Azad, Je-Chin Han

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

Robert J. Boyle

NASA Glenn Research Center, Cleveland, OH 44135

J. Turbomach 122(4), 725-732 (Feb 01, 2000) (8 pages) doi:10.1115/1.1311284 History: Received February 01, 2000
Copyright © 2000 by ASME
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References

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., 1992, “The Effect of Blade Tip Geometry on the Tip Leakage Flow in Axial Turbine Cascades,” ASME J. Turbomach., 114, pp. 643–651.
Yang, T. T., and Diller, T. E., 1995, “Heat Transfer and Flow for a Grooved Turbine Blade Tip in a Transonic Cascade,” ASME Paper No. 95-WA/HT-29.
Ameri,  A., Rigby,  D. L., and Steinthorsson,  E., 1998, “Effects of Squealer Tip on Rotor Heat Transfer and Efficiency,” ASME J. Turbomach., 120, pp. 753–759.
Bindon, J. P., and Morphus, G., 1988, “The Effect of Relative Motion, Blade Edge Radius and Gap Size on the Blade Tip Pressure Distribution in an Annular Turbine Cascade With Clearance,” ASME Paper No. 88-GT-256.
Bindon,  J. P., 1989, “The Measurement and Formation of Tip Clearance Loss,” ASME J. Turbomach., 111, pp. 258–263.
Moore,  J., Moore,  J. G., Henry,  G. S., and Chaudhury,  U., 1989, “Flow and Heat Transfer in Turbine Tip Gaps,” ASME J. Turbomach., 111, pp. 301–309.
Yaras,  M. I., and Sjolander,  S. A., 1992, “Effects of Simulated Rotation on Tip Leakage in a Planar Cascade of Turbine Blades: Part I—Tip Gap Flow,” ASME J. Turbomach., 114, pp. 652–659.
Sjolander,  S. A., and Cao,  D., 1995, “Measurements of the Flow in an Idealized Turbine Tip Gap,” ASME J. Turbomach., 117, pp. 578–584.
Kaiser, I., and Bindon, J. P., 1997, “The Effect of Tip Clearance on the Development of Loss Behind a Rotor and a Subsequent Nozzle,” ASME Paper No. 97-GT-53.
Mayle, R. E., and Metzger, D. E., 1982, “Heat Transfer at the Tip of an Unshrouded Turbine Blade,” Proc. Seventh Int. Heat Transfer Conf., Hemisphere Pub., pp. 87–92.
Metzger,  D. E., Dunn,  M. G., and Hah,  C., 1991, “Turbine Tip and Shroud Heat Transfer,” ASME J. Turbomach., 113, pp. 502–507.
Ameri, A. A., and Steinthorsson, E., 1995, “Prediction of Unshrouded Rotor Blade Tip Heat Transfer,” ASME Paper No. 95-GT-142.
Ameri, A. A., and Steinthorsson, E., 1996, “Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer,” ASME Paper No. 96-GT-189.
Ameri,  A. A., Steinthorsson,  E., and Rigby,  D. L., 1999, “Effects of Tip Clearance and Casing Recess on Heat Transfer and Stage Efficiency in Axial Turbines,” ASME J. Turbomach., 121, pp. 683–693.
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Bunker,  Ronald S., Bailey,  J. C., and Ameri,  A. A., 2000, “Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part I—Experimental Results,” ASME J. Turbomach., 122, pp. 263–271.
Azad,  Gm S., Han,  Je-Chin, Teng,  Shuye, and Boyle,  Robert J., 2000, “Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip,” ASME J. Turbomach., 122, this issue, pp. 717–724.
Kline,  S. J., and McClintock,  F. A., 1953, “Describing Uncertainties in Single Sample Experiments,” Mech. Eng. (Am. Soc. Mech. Eng.), 75, Jan., pp. 3–8.

Figures

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Test section with five-bladed cascade
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Blade tip and shroud definition
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Pressure tap locations on blade and shroud
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(a) Coefficient of pressure at inlet and exit plane; (b) pressure distribution at midspan on the test blade and two nearby blades
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Pressure distributions from midspan to near-tip locations for C=1.5 percent and Tu=6.1 percent
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Pressure ratio distribution on the shroud surface
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Heat transfer coefficient at Tu=6.1 percent
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Heat transfer coefficient at Tu=9.7 percent
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Averaged heat transfer coefficient at: (a) Tu=6.1 percent; (b) Tu=9.7 percent

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