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Research Papers

Heat Transfer for High Aspect Ratio Rectangular Channels in a Stationary Serpentine Passage With Turbulated and Smooth Surfaces

[+] Author and Article Information
Matthew A. Smith

e-mail: MatthewAlan.Smith@ge.com

Randall M. Mathison

e-mail: mathison.4@osu.edu

Michael G. Dunn

e-mail: dunn.129@osu.edu
The Ohio State University,
Gas Turbine Laboratory,
2300 West Case Road,
Columbus, OH 43221

1Presently at GE Aviation, Cincinnati, OH 45215.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received April 19, 2013; final manuscript received May 31, 2013; published online September 27, 2013. Editor: Ronald Bunker.

J. Turbomach 136(5), 051002 (Sep 27, 2013) (11 pages) Paper No: TURBO-13-1057; doi: 10.1115/1.4025307 History: Received April 19, 2013; Revised May 31, 2013

Heat transfer distributions are presented for a stationary three passage serpentine internal cooling channel for a range of engine representative Reynolds numbers. The spacing between the sidewalls of the serpentine passage is fixed and the aspect ratio (AR) is adjusted to 1:1, 1:2, and 1:6 by changing the distance between the top and bottom walls. Data are presented for aspect ratios of 1:1 and 1:6 for smooth passage walls and for aspect ratios of 1:1, 1:2, and 1:6 for passages with two surfaces turbulated. For the turbulated cases, turbulators skewed 45 deg to the flow are installed on the top and bottom walls. The square turbulators are arranged in an offset parallel configuration with a fixed rib pitch-to-height ratio (P/e) of 10 and a rib height-to-hydraulic diameter ratio (e/Dh) range of 0.100–0.058 for AR 1:1–1:6, respectively. The experiments span a Reynolds number range of 4000–130,000 based on the passage hydraulic diameter. While this experiment utilizes a basic layout similar to previous research, it is the first to run an aspect ratio as large as 1:6, and it also pushes the Reynolds number to higher values than were previously available for the 1:2 aspect ratio. The results demonstrate that while the normalized Nusselt number for the AR 1:2 configuration changes linearly with Reynolds number up to 130,000, there is a significant change in flow behavior between Re = 25,000 and Re = 50,000 for the aspect ratio 1:6 case. This suggests that while it may be possible to interpolate between points for different flow conditions, each geometric configuration must be investigated independently. The results show the highest heat transfer and the greatest heat transfer enhancement are obtained with the AR 1:6 configuration due to greater secondary flow development for both the smooth and turbulated cases. This enhancement was particularly notable for the AR 1:6 case for Reynolds numbers at or above 50,000.

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Figures

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Fig. 1

Serpentine model detail

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Fig. 2

Passage end view for (a) AR 1:1 and (b) AR 1:6

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Fig. 3

Skewed turbulator configuration (a) offset turbulator configuration (b) bottom turbulator

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Fig. 4

Stationary test facility

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Fig. 5

Reynolds number and pressure history during a typical experiment

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Fig. 6

Measured (a) temperatures and (b) total power for a typical run

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Fig. 7

Smooth wall passage comparison, AR 1:1

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Fig. 8

Skewed turbulated passage comparison, AR 1:1

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Fig. 9

Smooth passage comparison, AR 1:6

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Fig. 10

Skewed turbulated passage comparison, AR 1:6

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Fig. 11

Schematic of turbulated passage flow structure

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Fig. 12

Smooth AR1:6 comparison for Re = 50,000

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Fig. 13

Turbulated AR1:6 comparison for Re = 50,000

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Fig. 14

Turbulated passage comparison, Re = 10,000

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Fig. 15

Nusselt number for AR 1:6 with two wall configurations and five Reynolds numbers

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Fig. 16

Normalized heat transfer, AR 1:6

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Fig. 17

Passage average normalized heat transfer comparison

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Fig. 18

Alternate relationship for passage average Nusselt number

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Fig. 19

Normalized friction factor

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Fig. 20

Thermal performance

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