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Research Papers

Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing Jets—Part II: Heat Transfer Analysis

[+] Author and Article Information
Filippo Coletti1

Department of Turbomachinery and Propulsion, Von Karman Institute, Rhode Saint Genese 1640, Belgiumcoletti@vki.ac.be

Alessandro Armellini2

Department of Turbomachinery and Propulsion, Von Karman Institute, Rhode Saint Genese 1640, Belgiumalessandro.armellini@uniud.it

Tony Arts

Department of Turbomachinery and Propulsion, Von Karman Institute, Rhode Saint Genese 1640, Belgiumarts@vki.ac.be

Christophe Scholtes

Department of Methods, Aerothermal Unit, Snecma, Groupe Safran, Reau 77550, Francechristophe.scholtes@snecma.fr

1

Corresponding author.

2

Present address: Dipartimento di Energetica e Macchine, University of Udine, Udine 33100, Italy.

J. Turbomach 133(3), 031024 (Dec 07, 2010) (8 pages) doi:10.1115/1.4002425 History: Received March 05, 2010; Revised March 10, 2010; Published December 07, 2010; Online December 07, 2010

The present contribution addresses the aerothermal experimental and computational study of a trapezoidal cross-section model simulating a trailing edge cooling cavity with one rib-roughened wall and slots along two opposite walls. Highly resolved heat transfer distributions for the geometry with and without ribs are achieved using a steady state liquid crystals method in part II of this paper. The reference Reynolds number defined at the entrance of the test section is set at 67,500 for all the experiments. Comparisons are made with the flow field visualizations presented in part I of this paper. The results show the dramatic impact of the flow structures on the local and global heat transfer coefficients along the cavity walls. Of particular importance is the jet deflected by the rib-roughened wall and impinging on the opposite smooth wall. The experimental results are compared with the numerical predictions obtained using the finite volume, Reynolds-Averaged Navier–Stokes solver Calcul d'Écoulements Diphasiques Réactifs pour l'Énergétique (CEDRE ).

Copyright © 2011 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Energy balance in the heated cavity

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Figure 3

TLC stach: (a) bottom wall and (b) upper wall

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Figure 14

CFD: Nusselt number profile along the rib. Distance from the rib is 0.3e.

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Figure 15

CFD: heat transfer and streamlines on the bottom wall: rib-roughened configuration

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Figure 16

CFD/TLC comparison on the bottom wall: rib-roughened configuration

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Figure 17

CFD: heat transfer on the upper wall: rib-roughened configuration

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Figure 18

CFD: heat transfer and streamlines on the upper wall: rib-roughened configuration

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Figure 19

CFD/TLC comparison on the upper wall: rib-roughened configuration

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Figure 4

Heat transfer characterization on the bottom wall: smooth configuration

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Figure 5

Heat transfer characterization on the upper wall: smooth configuration

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Figure 6

Summary of the mean flow path model: (a) inter-rib region and vertical structures and (b) near to the upper wall

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Figure 7

Heat transfer characterization on the bottom wall: rib-roughened configuration

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Figure 8

EF profile along the rib. Distance from the rib is 0.3e.

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Figure 9

Cross-plane acceleration near and iso-EF lines on the bottom wall

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Figure 10

Heat transfer characterization on the upper wall: rib-roughened configuration

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Figure 11

Local-to-local EF: rib-roughened configuration

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Figure 12

Cross-plane acceleration near and iso-EF lines on the upper wall

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Figure 13

CFD: heat transfer on the bottom wall: rib-roughened configuration

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