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Research Papers

Experimental and Numerical Investigation of the Flow in a Trailing Edge Ribbed Internal Cooling Passage

[+] Author and Article Information
Seungchan Baek

Department of Mechanical and
Aerospace Engineering,
Seoul National University,
Seoul 08826, South Korea
e-mail: dkjdjdj195@snu.ac.kr

Sangjoon Lee

Department of Mechanical and
Aerospace Engineering,
Seoul National University,
Seoul 08826, South Korea
e-mail: jun9303@snu.ac.kr

Wontae Hwang

Department of Mechanical and
Aerospace Engineering,
Institute of Advanced Machines and Design,
Seoul National University,
Seoul 08826, South Korea
e-mail: wthwang@snu.ac.kr

Jung Shin Park

Thermal and Fluid Research Team,
Doosan Heavy Industries & Co., LTD,
Yongin 16858, South Korea
e-mail: jungshin.park@doosan.com

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 22, 2018; final manuscript received October 24, 2018; published online December 5, 2018. Editor: Kenneth Hall.

J. Turbomach 141(1), 011012 (Dec 05, 2018) (9 pages) Paper No: TURBO-18-1264; doi: 10.1115/1.4041868 History: Received September 22, 2018; Revised October 24, 2018

The flow field in a ribbed triangular channel representing the trailing edge internal cooling passage of a gas turbine high-pressure turbine blade is investigated via magnetic resonance velocimetry (MRV) and large eddy simulation (LES). The results are compared to a baseline channel with no ribs. LES predictions of the mean velocity fields are validated by the MRV results. In the case of the baseline triangular channel with no ribs, the mean flow and turbulence level at the sharp corner are small, which would correspond to poor heat transfer in an actual trailing edge. For the staggered ribbed channel, turbulent mixing is enhanced, and flow velocity and turbulence intensity at the sharp edge increase. This is due to secondary flow induced by the ribs moving toward the sharp edge in the center of the channel. This effect is expected to enhance internal convective heat transfer for the turbine blade trailing edge.

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References

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Figures

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Fig. 2

Test setup in the MRI scanner

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Fig. 3

Water channel installed in the MRI room

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Fig. 4

Right triangular channels: (top) baseline and (bottom) ribbed

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Fig. 5

Cross section of triangular channels: (top) baseline and (bottom) ribbed

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Fig. 6

Rib geometry in the channel

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Fig. 7

Computational domain of numerical analysis with mesh details: (left) baseline channel and (right) ribbed channel

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Fig. 8

Friction factor in comparison with the Carlson–Irvine correlation and Blasius solution. Subplot shows the convergence of the friction factor with number of cells.

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Fig. 9

Contours of mean streamwise velocity normalized by bulk velocity: (top) MRV and (bottom) LES

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Fig. 10

Normalized mean streamwise velocity profile comparison along the centerline of the baseline channel

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Fig. 11

Root-mean-square velocity profiles along the centerline of the channel. (Top) current baseline channel at Re = 20,000, (bottom) isosceles triangular channel at Re = 4,500 [13].

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Fig. 12

Mean streamwise velocity contours for the ribbed channel: (top) MRV and (bottom) LES

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Fig. 13

Mean streamwise velocity comparisons between the ribbed channel and baseline channel for MRV and LES

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Fig. 14

Root-mean-square velocity profiles along the centerline of the ribbed channel obtained by LES

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Fig. 15

Secondary flow in the cross section: (top) MRV and (bottom) LES

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Fig. 16

Streamwise velocity contours with streamlines on a plane near the ribbed wall: (top) MRV and (bottom) LES

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Fig. 17

Streamwise velocity contours in the center plane of the ribbed channel: (top) MRV and (bottom) LES

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