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Journal of Heat Transfer | Volume 134 | Issue 1 | Research Paper
Research Papers: Heat Transfer Enhancement

Local Heat/Mass Transfer and Friction Loss Measurement in a Rotating Matrix Cooling Channel

[+] Author and Article Information
In Taek Oh, Kyung Min Kim, Dong Hyun Lee, Jun Su Park

Department of Mechanical Engineering,  Yonsei University, Seoul 120-749, Koreahhcho@yonsei.ac.kr

Hyung Hee Cho1

Department of Mechanical Engineering,  Yonsei University, Seoul 120-749, Koreahhcho@yonsei.ac.kr

1

Corresponding author.

J. Heat Transfer 134(1), 011901 (Oct 27, 2011) (9 pages) doi:10.1115/1.4004853 History: Received August 30, 2010; Accepted August 12, 2011; Published October 27, 2011; Online October 27, 2011
Article
References
Figures
Tables
Citing Articles

The present investigation provides detailed local heat/mass transfer and pressure drop characteristics in a matrix cooling channel, under rotating conditions. The matrix channel had cooling subpassages with crossing angles of 45 deg. The detailed heat/mass transfer coefficients were measured via the naphthalene sublimation method, and pressure drops were also obtained. The experiments were conducted for various Reynolds numbers (10,500 to 44,000) and rotation numbers (0.0 to 0.8). In the stationary case, the heat transfer characteristics were dominated by turning, impinging, and swirling flow, induced by the matrix channel geometry. Average heat/mass transfer coefficients on the leading and trailing surfaces in the stationary channel were approximately 2.1 times greater than those in a smooth channel. In the rotating cases, the effect of rotation on heat/mass transfer characteristics differed from that of typical rotating channels with radially outward flow. As the rotation number increased, the Sherwood number ratios increased on the leading surfaces but changed only slightly on the trailing surfaces. The thermal performance factors increased with rotation number due to the increased Sherwood number ratios and decreased friction factor ratios.
Copyright © 2012 by American Society of Mechanical Engineers
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References

1
Park, J. S., Kim, K. M., Lee, D. H., Cho, H. H., and Chyu, M. K., 2011, “Heat Transfer in Rotating Channel With Inclined Pin-Fins,” ASME J. Turbomach., 133 , p. 021003.  [CrossRef]
2
Huh, M., Lei, J., Liu, Y. H., and Han, J. C., 2011, “High Rotation Number Effects on Heat Transfer in a Rectangular (AR = 2:1) Two-Pass Channel,” ASME J. Turbomach., 133 , p. 021001.  [CrossRef]
3
Cho, H. H., Rhee, D. H., and Goldstein, R. J., 2008, “Effects of Hole Arrangements on Local Heat/Mass Transfer for Impingement/Effusion Cooling With Small Hole Spacing,” ASME J. Turbomach., 130 , p. 041003.  [CrossRef]
4
Hong, S. K., Rhee, D. H., and Cho, H. H., 2007, “Effects of Fin Shapes and Arrangements on Heat Transfer for Impingement/Effusion Cooling With Crossflow,” ASME J. Heat Transfer, 129 , pp. 1697–1707.  [CrossRef]
5
Sundberg, J., 2006, "The Heat Transfer Correlations for Gas Turbine Cooling", Linköping University, Linköping, Sweden, pp. 38–63.
6
Goreloff, V., Goychengerg, M., and Malkoff, V., 1990, “The Investigation of Heat Transfer in Cooled Blades of Gas Turbines,” AIAA Paper No. 90-2144.
7
Gillespie, D. R. H., Ireland, P. T., and Dailey, G. M., 2000, “Detailed Flow and Heat Transfer Coefficient Measurements in a Model of an Internal Cooling Geometry Employing Orthogonal Intersecting Channels,” ASME Turbo Expo 2000, Paper No. 2000-GT-653.
8
Bunker, R. S., 2004, “Latticework (vortex) Cooling Effectiveness Part 1: Stationary Channel Experiments,” ASME Turbo Expo 2004, Paper No. GT 2004-54157.
9
Saha, K., Acharya, S., Guo, S., and Nakamata, C., 2008, “Heat Transfer and Pressure Measurement in a Lattice-Cooled Trailing Edge of a Turbine Airfoil,” ASME Turbo Expo 2008, Paper No. GT 2008-51324.
10
Su, S., Liu, J. J., Fu, J. L., Hu, J., and An, B. T., 2008, “Numerical Investigation of Fluid Flow and Heat Transfer in a Turbine Blade With Serpentine Passage and Latticework Cooling,” ASME Turbo Expo 2008, Paper No. GT 2008-50392.
11
Acharya, S., Zhou, F., Lagrone, J., Mahmood, G., and Bunker, R. S., 2005, “Latticework (vortex) Cooling Effectiveness Part 2: Rotating Channel Experiments,” ASME J. Turbomach., 127 , pp. 471–478.  [CrossRef]
12
Oh, I. T., Kim, K. M., Lee, D. H., and Cho, H. H., 2008, “Measurement of Local Heat/Mass Transfer in a Matrix Cooling Channel,” TFEC 2008, Paper No. TFEC2008-FULL-0299.
13
Oh, I. T., Kim, K. M., Lee, D. H., Park, J. S., and Cho, H. H., 2009, “Local Heat/Mass Transfer and Friction Loss Measurements in a Rotating Matrix Cooling Channels,” ASME Turbo Expo 2009, Paper No. GT 2009-59873.
14
Hong, S. K., Lee, D. H., and Cho, H. H., 2008, “Heat/Mass Transfer Measurement on Concave Surface in Rotating Jet Impingement,” J. Mech. Sci. Technol., 22 (10), pp. 1952–1958.  [CrossRef]
15
Ambrose, D., Lawrenson, I. J., and Sparke, C. H. S., 1975, “The Vapor Pressure of Naphthalene,” J. Chem. Thermodyn., 7 , pp. 1173–1176.  [CrossRef]
16
Goldstein, R. J., and Cho, H.H., 1995, “A Review of Mass Transfer Measurements Using Naphthalene Sublimation,” Exp. Therm. Fluid Sci., 10 , pp. 416–434.  [CrossRef]
17
Abernethy, R. B., Benedict, R. P., and Dowdel, R. B., 1985, “Measurement Uncertainty,” ASME J. Fluid Eng., 107 , pp. 161–164.  [CrossRef]
18
McAdams, W. H., 1942, "Heat Transmission", 2nd ed., McGraw-Hill, New York.
19
Petukhov, B. S., 1970, "Advances in Heat Transfer", Vol. 6 , Academic, New York, pp. 503–504.
20
Gee, D. L. and Webb, R. L., 1980, “Forced Convection Heat Transfer in Helically Rib-Roughened Tubes,” Int. J. Heat and Mass Transfer, 23 , pp. 1127–1136.  [CrossRef]
21
Jun, Y. H., Park, S. H., Kim, K. M., Rhee, D. H., and Cho, H. H., 2007, “Effects of Bleed Flow on Heat/Mass Transfer in a Rotating Rib-Roughened Channel,” ASME J. Turbomach., 129 , pp. 636–642.  [CrossRef]
22
Kim, K. M., Park, S. H., Jun, Y. H., Rhee, D. H., and Cho, H. H., 2008, “Heat/Mass Transfer Characteristics in Angled Ribbed Channels With Various Bleed Ratios and Rotation Numbers,” ASME J. Turbomach., 130 , p. 031021.  [CrossRef]

Figures

Grahic Jump Location
+Line-averaged ShL /Sh0 ratio distributions in the middle region (channel 8) at Ro = 0.4 with various Reynolds numbers; (a) trailing surface (pressure side), (b) leading surface (suction side)
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Line-averaged ShL /Sh0 ratio distributions in the middle region (channel 8) at Ro = 0.4 with various Reynolds numbers; (a) trailing surface (pressure side), (b) leading surface (suction side)
Figure 11

Line-averaged ShL /Sh0 ratio distributions in the middle region (channel 8) at Ro = 0.4 with various Reynolds numbers; (a) trailing surface (pressure side), (b) leading surface (suction side)

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+Thermal performance factors for various rotation numbers
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Thermal performance factors for various rotation numbers
Figure 13

Thermal performance factors for various rotation numbers

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+Sh/Sh0 in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)
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Sh/Sh0 in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)
Figure 14

Sh/Sh0 in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)

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+Friction factor ratios in the various cooling method cases
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Friction factor ratios in the various cooling method cases
Figure 15

Friction factor ratios in the various cooling method cases

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+Thermal performance in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)
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Thermal performance in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)
Figure 16

Thermal performance in the various cooling method cases; (a) trailing surface (pressure side), (b) leading surface (suction side)

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+Friction factor ratios for various rotation and Reynolds numbers
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Friction factor ratios for various rotation and Reynolds numbers
Figure 12

Friction factor ratios for various rotation and Reynolds numbers

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+Schematic view of experimental apparatus [14]
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Schematic view of experimental apparatus [14]
Figure 1

Schematic view of experimental apparatus [14]

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+Geometry of the test channel
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Geometry of the test channel
Figure 2

Geometry of the test channel

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+Geometry parameters of matrix channel
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Geometry parameters of matrix channel
Figure 3

Geometry parameters of matrix channel

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+Subchannel numbers of the test section; (a) trailing surface (pressure side), (b) leading surface (suction side)
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Subchannel numbers of the test section; (a) trailing surface (pressure side), (b) leading surface (suction side)
Figure 4

Subchannel numbers of the test section; (a) trailing surface (pressure side), (b) leading surface (suction side)

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+Contour plots of Sh/Sh0 at Re = 44,000 in the stationary case (Ro = 0.0); (a) trailing surface (pressure side), (b) leading surface (suction side)
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Contour plots of Sh/Sh0 at Re = 44,000 in the stationary case (Ro = 0.0); (a) trailing surface (pressure side), (b) leading surface (suction side)
Figure 5

Contour plots of Sh/Sh0 at Re = 44,000 in the stationary case (Ro = 0.0); (a) trailing surface (pressure side), (b) leading surface (suction side)

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+Line-averaged ShL /Sh0 in the middle region (channel 5) at Ro = 0.0 for various Reynolds numbers; (a) trailing surface (pressure side) (b) leading surface (suction side)
View Large  |  Save Figure  |  Download Slide (.ppt)
Line-averaged ShL /Sh0 in the middle region (channel 5) at Ro = 0.0 for various Reynolds numbers; (a) trailing surface (pressure side) (b) leading surface (suction side)
Figure 6

Line-averaged ShL /Sh0 in the middle region (channel 5) at Ro = 0.0 for various Reynolds numbers; (a) trailing surface (pressure side) (b) leading surface (suction side)

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+Predicted vector plot along the center plane of a subchannel
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Predicted vector plot along the center plane of a subchannel
Figure 7

Predicted vector plot along the center plane of a subchannel

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+Contour plots of Sh/Sh0 at Re = 44,000 for various rotation numbers; (a) Ro = 0.2 (trailing surface), (b) Ro = 0.2 (leading surface); (c) Ro = 0.4 (trailing surface), (d) Ro = 0.4 (leading surface)
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Contour plots of Sh/Sh0 at Re = 44,000 for various rotation numbers; (a) Ro = 0.2 (trailing surface), (b) Ro = 0.2 (leading surface); (c) Ro = 0.4 (trailing surface), (d) Ro = 0.4 (leading surface)
Figure 8

Contour plots of Sh/Sh0 at Re = 44,000 for various rotation numbers; (a) Ro = 0.2 (trailing surface), (b) Ro = 0.2 (leading surface); (c) Ro = 0.4 (trailing surface), (d) Ro = 0.4 (leading surface)

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+Line-averaged ShL /Sh0 distributions in the middle region on leading surface (channel 8) for various rotation numbers; (a) Re = 10,500, (b) Re = 44,000
View Large  |  Save Figure  |  Download Slide (.ppt)
Line-averaged ShL /Sh0 distributions in the middle region on leading surface (channel 8) for various rotation numbers; (a) Re = 10,500, (b) Re = 44,000
Figure 9

Line-averaged ShL /Sh0 distributions in the middle region on leading surface (channel 8) for various rotation numbers; (a) Re = 10,500, (b) Re = 44,000

Grahic Jump Location
+Line-averaged ShL /Sh0 distributions in the middle region on trailing surface (channel 8) for various rotation numbers; (a) Re = 10,500 (b) Re = 44,000
View Large  |  Save Figure  |  Download Slide (.ppt)
Line-averaged ShL /Sh0 distributions in the middle region on trailing surface (channel 8) for various rotation numbers; (a) Re = 10,500 (b) Re = 44,000
Figure 10

Line-averaged ShL /Sh0 distributions in the middle region on trailing surface (channel 8) for various rotation numbers; (a) Re = 10,500 (b) Re = 44,000

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