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TECHNICAL PAPERS

Spatially Resolved Heat Transfer and Friction Factors in a Rectangular Channel With 45-Deg Angled Crossed-Rib Turbulators

[+] Author and Article Information
P. M. Ligrani, G. I. Mahmood

Convective Heat Transfer Laboratory, Department of Mechanical Engineering, University of Utah, Salt Lake City, UT 84112

J. Turbomach 125(3), 575-584 (Aug 27, 2003) (10 pages) doi:10.1115/1.1565353 History: Received October 24, 2001; Online August 27, 2003
Copyright © 2003 by ASME
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References

Han,  J. C., Glicksman,  L. R., and Rohsenow,  W. M., 1978, “An Investigation of Heat Transfer and Friction For Rib-Roughened Surfaces,” Int. J. Heat Mass Transf., 21(7), pp. 1143–1156.
Han,  J. C., and Park,  J. S., 1988, “Developing Heat Transfer in Rectangular Channels With Rib Turbulators,” Int. J. Heat Mass Transf., 31(1), pp. 183–195.
Han,  J. C., Zhang,  Y. M., and Lee,  C. P., 1991, “Augmented Heat Transfer in Square Channels With Parallel, Crossed, and V-Shaped Angled Ribs,” ASME J. Heat Transfer, 113, pp. 590–596.
Han J. C., Huang J. J., and Lee C. P., 1993, “Augmented Heat Transfer in Square Channels With Wedge-Shaped and Delta-Shaped Turbulence Promoters,” Enhanced Heat Transfer, Vol. 1, No. 1, pp. 37–52.
Taslim,  M. E., Li,  T., and Kercher,  D. M., 1996, “Experimental Heat Transfer and Friction in Channels Roughened With Angled, V-Shaped, and Discrete Ribs on Two Opposite Walls,” ASME J. Turbomach., 118, pp. 20–28.
Taslim,  M. E., Li,  T., and Spring,  S. D., 1998, “Measurements of Heat Transfer Coefficients and Friction Factors in Passages Rib-Roughened On All Walls,” ASME J. Turbomach., 120, pp. 564–570.
Wang,  Z., Ireland,  P. T., Kohler,  S. T., and Chew,  J. W., 1998, “Heat Transfer Measurements to a Gas Turbine Cooling Passage With Inclined Ribs,” ASME J. Turbomach., 120, pp. 63–69.
Thurman D., and Poinsatte P., 2000, “Experimental Heat Transfer and Bulk Air Temperature Measurements for a Multipass Internal Cooling Model With Ribs and Bleed,” ASME Paper No. 2000-GT-233.
Cho H. H., Lee S. Y., and Wu S. J., 2001, “The Combined Effects of Rib Arrangements and Discrete Ribs on Local Heat/Mass Transfer in a Square Duct,” ASME Paper No. 2001-GT-175.
Ligrani,  P. M., Oliveira,  M. M., and Blaskovich,  T., 2003, “Comparison of Heat Transfer Augmentation Techniques,” AIAA J., 41(3), pp. 337–362.
Mahmood,  G. I., Hill,  M. L., Nelson,  D. L., Ligrani,  P. M., Moon,  H.-K., and Glezer,  B., 2001, “Local Heat Transfer and Flow Structure On and Above a Dimpled Surface in a Channel,” ASME J. Turbomach., 123, pp. 115–123.
Sargent,  S. R., Hedlund,  C. R., and Ligrani,  P. M., 1998, “An Infrared Thermography Imaging System For Convective Heat Transfer Measurements in Complex Flows,” Meas. Sci. Technol., 9(12), pp. 1974–1981.
Kline,  S. J., and McClintock,  F. A., 1953, “Describing Uncertainties in Single Sample Experiments,” Mech. Eng. (Am. Soc. Mech. Eng.) 75, pp. 3–8.
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Metzger D. E., Chyu M.-K., and Bunker R. S., 1988, “The Contribution of On-Rib Heat Transfer Coefficients to Total Heat Transfer From Rib-Roughened Surfaces,” Transport Phenomena in Rotating Machinery, J. H. Kim ed., Hemisphere Publishing Co., Washington, DC.
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Figures

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Schematic diagrams of (a) the experimental apparatus used for heat transfer measurements, and (b) the experimental apparatus used for flow visualizations and measurements of flow structure
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Schematic diagram of the rib turbulator test surfaces, including coordinate system
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Baseline Nusselt numbers, measured with smooth channel surfaces and constant heat flux boundary condition, as dependent upon Reynolds number based on hydraulic diameter
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Local Nusselt number ratio Nu/Nuo distribution along the rib turbulator test surface for ReH=48,000 and Toi/Tw=0.94, with constant surface heat flux and no surface conduction analysis applied
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Local Nusselt number ratio Nu/Nuo distribution along the rib turbulator test surface for ReH=48,000 and Toi/Tw=0.94, for variable surface heat flux and surface conduction analysis applied
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Constant heat flux local Nusselt number ratios Nu/Nuo along the rib turbulator test surface at Z/Dh=0.0 for different Reynolds numbers ReH and Toi/Tw of 0.93–0.95. No conduction analysis applied.
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Constant heat flux local Nusselt number ratios Nu/Nuo along the rib turbulator test surface at X/Dh=6.90 for different Reynolds numbers ReH and Toi/Tw of 0.93–0.95. No conduction analysis applied. Symbols are defined in Fig. 6.
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Local Nusselt number ratios Nu/Nuo along the rib turbulator test surface at Z/Dh=0.11 for a Reynolds number ReH=48,000 and Toi/Tw of 0.94. Data are given for constant surface heat flux (no surface conduction analysis) and for variable surface heat flux (with surface conduction analysis).
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Local Nusselt number ratios Nu/Nuo along the rib turbulator test surface at X/Dh=6.90 for a Reynolds number ReH=48,000 and Toi/Tw of 0.94. Data are given for constant surface heat flux (no surface conduction analysis) and for variable surface heat flux (with surface conduction analysis).
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Schematic diagram of a portion of the bottom rib turbulator test surface showing the orientations and layout of several rib turbulators, and the coordinates W/Dh and L/Dh, which are oriented perpendicular to and parallel to the rib turbulators, respectively
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Nusselt number ratios N̄u/Nuo, for fully developed conditions measured at the downstream end of the test section and averaged in the W/Dh direction, as dependent upon the L/Dh coordinate for different Reynolds numbers and Toi/Tw=0.93–0.95. Symbols are defined in Fig. 12. Surface heat flux is constant and no surface conduction analysis is applied.
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Nusselt number ratios N̄u/Nuo, for fully developed conditions measured at the downstream end of the test section and averaged in the L/Dh direction, as dependent upon the W/Dh coordinate for different Reynolds numbers and Toi/Tw=0.93–0.95. Surface heat flux is constant and no surface conduction analysis is applied.
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Nusselt number ratios N̄u/Nuo, for fully developed conditions measured at the downstream end of the test section and averaged in the L/Dh direction, as dependent upon the W/Dh coordinate for a Reynolds number ReH=48,000 and Toi/Tw of 0.94. Data are shown with and without conduction analysis applied (variable and constant surface heat flux respectively).
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Nusselt number ratios N̄u/Nuo, for thermally developing flow measured at the upstream end of the test section and averaged in the W/Dh direction, as dependent upon the L/Dh coordinate for ReH=53,500 and Toi/Tw=0.93–0.95.
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Nusselt number ratios N̄u/Nuo, for thermally developing flow measured at the upstream end of the test section and averaged in the L/Dh direction, as dependent upon the W/Dh coordinate for ReH=53,500 and Toi/Tw=0.93–0.95. Surface heat flux is constant and no surface conduction analysis is applied.
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Rib turbulator channel globally averaged Nusselt number ratios for fully developed flow, averaged over the surface area corresponding to one period of rib turbulator surface geometry. Comparisons with results from other investigations 345 are included.
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Rib turbulator channel friction factor ratios f/fo for fully developed flow conditions as dependent upon Reynolds number for Toi/Tw=0.93–0.95. Symbols are defined in Fig. 16. Comparisons with results from other investigations 345 are included.
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Rib turbulator channel globally averaged Nusselt numbers for fully developed flow and Toi/Tw=0.93–0.95 as dependent upon friction factor ratios, including comparisons with results from other investigations 345. Symbols are defined in Fig. 16.
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Rib turbulator channel globally averaged performance parameters for fully developed flow and Toi/Tw=0.93–0.95 as dependent upon Reynolds number, including comparisons with results from other investigations 345. Symbols defined in Fig. 16.

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