Heat Transfer Enhancement Within a Turbine Blade Cooling Passage Using Ribs and Combinations of Ribs With Film Cooling Holes-Reference-Cited by-同舟云学术

Heat Transfer Enhancement Within a Turbine Blade Cooling Passage Using Ribs and Combinations of Ribs With Film Cooling Holes

Published:1996-07-01 Issue:3 Volume:118 Page:428-434
ISSN:0889-504X
Container-title:Journal of Turbomachinery
language:en
Short-container-title:

Author:

Shen J. R.¹,Wang Z.²,Ireland P. T.²,Jones T. V.²,Byerley A. R.³

Affiliation:

1. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing, China

2. Dept. of Engineering Science, University of Oxford, Oxford, United Kingdom

3. Department of Mechanical Engineering, Mercer University, Macon, GA 31207

Abstract

A transient heat transfer method using liquid crystals has been applied to a scale model of a turbine rotor blade passage. Detailed contours of local heat transfer coefficient are presented for the passage in which the heat transfer to one wall was enhanced first by ribs and then with ribs combined with holes. The hole geometry and experimental dimensionless flow rates were representative of those occurring at the entrance to engine film cooling holes. The results for the ribbed passage are compared to established correlations for developed flow. Qualitative surface shear stress distributions were determined with liquid crystals. The complex distributions of heat transfer coefficient are discussed in light of the interpreted flow field.

Publisher

ASME International

Subject

Mechanical Engineering

Link

http://asmedigitalcollection.asme.org/turbomachinery/article-pdf/118/3/428/5840484/428_1.pdf

Reference16 articles.

1. Atli V. , 1988, “Subsonic Flow Over a Two-Dimensional Obstacle Immersed in a Turbulent Boundary Layer on a Flat Surface,” Journal of Wind Engineering and Industrial Aerodynamics, Vol. 31, pp. 225–239.

2. Baughn J. W. , IrelandP. T., JonesT. V., and SaneiM., 1989, “A Comparison of the Transient and Heated-Coating Methods for the Measurement of Local Heat Transfer Coefficients on a Pin Fin,” ASME Journal of Heat Transfer, Vol. 111, pp. 887–881.

3. Bonnett P. , JonesT. V., and McDonnellD. G., 1989, “Shear Stress Measurements in Aerodynamic Testing Using Cholesteric Liquid Crystals,” Liquid Crystals, Vol. 6, No. 33, pp. 271–280.

4. Byerley, A. R., Ireland, P. T., Jones, T. V., and Ashton, S. A., 1988, “Detailed Heat Transfer Coefficient Measurements Near and Within the Entrance of a Film Cooling Hole,” ASME Paper No. 88-GT-155.

5. Byerley, A. R., Jones, T. V., and Ireland, P. T., 1992, “Internal Cooling Passage Heat Transfer Near the Entrance to a Film Cooling Hole: Experimental and Computational Results,” ASME Paper No. 92-GT-241.

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