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Research Papers

Heat Transfer in a Rotating Two-Pass Rectangular Channel Featuring a Converging Tip Turn With Various 45 deg Rib Coverage Designs

[+] Author and Article Information
Andrew F Chen

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: mrandrewchen@outlook.com

Chao-Cheng Shiau

Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: joeshiau@tamu.edu

Je-Chin Han

Fellow ASME
Turbine Heat Transfer Laboratory,
Department of Mechanical Engineering,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

Robert Krewinkel

MAN Energy Solutions,
Oberhausen, Germany
e-mail: robert.krewinkel@man-es.com

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the Journal of Thermal Science and Engineering Applications. Manuscript received December 9, 2018; final manuscript received March 31, 2019; published online May 22, 2019. Assoc. Editor: Steve Q. Cai.

J. Thermal Sci. Eng. Appl 11(6), 061015 (May 22, 2019) (12 pages) Paper No: TSEA-18-1656; doi: 10.1115/1.4043471 History: Received December 09, 2018; Accepted April 01, 2019

Varying aspect ratio (AR) channels are found in modern gas turbine airfoils for internal cooling purposes. Corresponding experimental data are needed in understanding and assisting the design of advanced cooling systems. The present study features a two-pass rectangular channel with an AR = 4:1 in the first pass with the radial outward flow and an AR = 2:1 in the second pass with the radial inward flow after a 180 deg tip turn. Effects of rib coverage near the tip region are investigated using profiled 45 deg ribs (P/e = 10, e/Dh ≈ 0.11, parallel and in-line) with three different configurations: less coverage, medium coverage, and full coverage. The Reynolds number (Re) ranges from 10,000 to 70,000 in the first passage. The highest rotation number achieved was Ro = 0.39 in the first passage and 0.16 in the second passage. Heat transfer coefficients on the internal surfaces were obtained by the regionally averaged copper plate method. The results showed that the rotation effects on both heat transfer and pressure loss coefficient are reduced with an increased rib coverage in the tip turn region. Different rib coverage upstream of the tip turn significantly changes the heat transfer in the turn portion. Heat transfer reduction (up to −27%) on the tip wall was seen at lower Ro. Dependence on the Reynolds number can be seen for this particular design. The combined geometric, rib coverage, and rotation effects should be taken into consideration in the internal cooling design.

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Figures

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Fig. 1

Schematic of the rotating test facility

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Fig. 2

Schematic figure of the test section: (a) as viewed from the leading side to the trailing surface (Config. 1) and (b) as viewed from the hub to the tip (without ribs)

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Fig. 3

Rib cross-sectional profile

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Fig. 4

Rib configurations with different coverages: (a) Config. 1 with less coverage, (b) Config. 2 with medium coverage, and (c) Config. 3 with full coverage

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Fig. 5

Temperature distribution for Config. 2 at Re = 35k, 0 and 400 rpm

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Fig. 6

Nusselt number ratio comparison with existing data

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Fig. 7

Stationary Nus/Nu0 distribution at Re = 10k, 0 rpm

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Fig. 8

Nu/Nu0 distribution at Re = 10k, 400 rpm

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Fig. 9

Effect of rotation number (Ro) on LS and TS heat transfer (Nu/Nus) in region 4

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Fig. 10

Effect of rotation number (Ro) on LS and TS heat transfer (Nu/Nus) in region 6

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Fig. 11

Effect of rotation number (Ro) on LS and TS heat transfer (Nu/Nus) in region 7

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Fig. 12

Effect of rotation number (Ro) on LS and TS heat transfer (Nu/Nus) in region 11

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Fig. 13

Effect of rotation number (Ro) on tip surface heat transfer (Nu/Nus) in regions 6 and 7 (Tip-6 and Tip-7)

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Fig. 14

Comparison of the maximum and minimum Nu/Nus for all surfaces considered within the Re and Ro range

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Fig. 15

Stationary pressure loss coefficient

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Fig. 16

Effect of rotation on pressure loss coefficient

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