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Research Papers

Multipass Serpentine Cooling Designs for Negating Coriolis Force Effect on Heat Transfer: 45-deg Angled Rib Turbulated Channels

[+] Author and Article Information
Prashant Singh

Department of Mechanical and Aerospace Engineering,
North Carolina State University,
Raleigh, NC 27695;
Advanced Propulsion and Power Laboratory,
Department of Mechanical Engineering,
Virginia Tech,
Blacksburg, VA 24061
e-mail: psingh23@ncsu.edu

Yongbin Ji

Institute of Turbomachinery,
School of Mechanical Engineering,
Shanghai Jiao Tong University,
Shanghai, China
e-mail: yongbinji@sjtu.edu.cn

Srinath V. Ekkad

Mechanical and Aerospace Engineering,
North Carolina State University,
Raleigh, NC 27695
e-mail: sekkad@ncsu.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received September 24, 2018; final manuscript received December 28, 2018; published online February 15, 2019. Assoc. Editor: Kenneth Hall.

J. Turbomach 141(7), 071003 (Feb 15, 2019) (10 pages) Paper No: TURBO-18-1269; doi: 10.1115/1.4042648 History: Received September 24, 2018; Revised December 28, 2018; Accepted December 31, 2018

Rotation-induced Coriolis and centrifugal buoyancy forces result in significant modification of cooling characteristics of blade pressure and suction side internal walls. The nonuniformity in cooling, coupled with high-speed rotation, results in increased levels of thermal stresses. To address this problem, this study presents two multipassage configurations featuring 45-deg angled turbulators, in four- and six-passage designs. Experiments were carried out under stationary and rotating conditions using transient liquid crystal thermography to measure detailed heat transfer coefficient. It has been shown through experimental data that heat transfer characteristics of the new configurations’ pressure and suction side internal walls were very similar under rotating conditions, at both local and global scales. The heat transfer levels under rotating conditions were also similar to those of the stationary conditions. The contribution of multiple passages connected with 180-deg bends toward overall frictional losses has been evaluated in terms of pumping power and normalized friction factor. The configurations are ranked based on their thermal hydraulic performances over a wide range of Reynolds numbers. The four-passage ribbed configuration had slightly higher heat transfer levels compared with those of the corresponding six-passage ribbed configuration.

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References

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. [CrossRef]
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Han, J. C., and Zhang, Y. M., 1992, “High Performance Heat Transfer Ducts With Parallel Broken and V-Shaped Broken Ribs,” Int. J. Heat Mass. Transf., 35(2), pp. 513–523. [CrossRef]
Han, J. C., Dutta, S., and Ekkad, S., 2012, Gas Turbine Heat Transfer and Cooling Technology, CRC Press, Boca Raton, FL.
Wagner, J. H., Johnson, B. V., and Kopper, F. C., 1991, “Heat Transfer in Rotating Serpentine Passages With Smooth Walls,” ASME J. Turbomach., 113(3), pp. 321–330. [CrossRef]
Wagner, J. H., Johnson, B. V., Graziani, R. A., and Yeh, F. C. 1991, Heat Transfer in Rotating Serpentine Passages With Trips Normal to the Flow. ASME. Turbo Expo: Power for Land, Sea, and Air, Vol. 4: Heat Transfer; Electric Power; Industrial and Cogeneration, V004T09A015.
Johnson, B. V., Wagner, J. H., Steuber, G. D., and Yeh, F. C., 1994, “Heat Transfer in Rotating Serpentine Passages With Trips Skewed to the Flow,” Trans. Am. Soc. Mech. Eng. J. Turbomach., 116, pp. 113–113.
Dutta, S., and Han, J. C., 1996, “Local Heat Transfer in Rotating Smooth and Ribbed Two-Pass Square Channels With Three Channel Orientations,” J. Heat Transf., 118(3), pp. 578–584. [CrossRef]
Singh, P., Li, W., Ekkad, S. V., and Ren, J., 2017, “A New Cooling Design for Rib Roughened Two-Pass Channel Having Positive Effects of Rotation on Heat Transfer Enhancement on Both Pressure and Suction Side Internal Walls of a Gas Turbine Blade,” Int. J. Heat Mass. Transf., 115, pp. 6–20. [CrossRef]
Incropera, F. P., Lavine, A. S., Bergman, T. L., and DeWitt, D. P., 2007, Fundamentals of Heat and Mass Transfer, Wiley, New York.
Singh, P., and Ekkad, S., 2017, “Experimental Study of Heat Transfer Augmentation in a Two-Pass Channel Featuring V-Shaped Ribs and Cylindrical Dimples,” Appl. Therm. Eng., 116, pp. 205–216. [CrossRef]
Camci, C., Kim, K., and Hippensteele, S. A., 1992, “A New Hue Capturing Technique for the Quantitative Interpretation of Liquid Crystal Images Used in Convective Heat Transfer Studies,” Trans. Am. Soc. Mech. Eng. J. Turbomach., 114, pp. 765–765.
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Figures

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Fig. 1

Schematic of experimental setup

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Fig. 2

Cooling configuration geometrical details

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Fig. 3

Mainstream temperature evolution with time, measurement locations shown in Fig. 3

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Fig. 4

Calibration of wall temperature with Hue

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Fig. 5

Heat transfer enhancement contours: the four-passage ribbed

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Fig. 6

Detailed Nusselt number ratio for the six-passage configuration under the stationary condition

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Fig. 7

Detailed Nusselt number ratio contour for the four-passage ribbed configuration under rotating conditions

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Fig. 8

Detailed Nusselt number ratio contour for the ribbed six-passage configuration under rotating conditions

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Fig. 9

Passagewise-averaged Nusselt number ratio under stationary conditions for (a) the four-passage configuration (dashed lines indicate smooth channel results) and (b) the six-passage configuration (dashed lines indicate smooth channel results)

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Fig. 10

Passagewise-averaged Nusselt number ratio for (a) the four-passage ribbed configuration and (b) the six-passage ribbed configuration

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Fig. 11

Static pressure variation with increasing streamwise distance from inlet, (a) four passage and (b) six passage

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Fig. 12

Normalized friction factor and pumping power variation with Reynolds number

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Fig. 13

Globally averaged Nusselt number ratio (Nu/Nu0) and thermal hydraulic performance variation with Reynolds number

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