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Research Papers

Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing-Jets—Part I: Flow Field Analysis

[+] Author and Article Information
Alessandro Armellini1

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

Filippo Coletti2

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

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

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

2

Corresponding author.

J. Turbomach 132(1), 011009 (Sep 16, 2009) (9 pages) doi:10.1115/1.3103929 History: Received August 06, 2008; Revised February 09, 2009; Published September 16, 2009

The present contribution addresses the aerothermal, experimental, and computational studies of a trapezoidal cross-sectional model simulating a trailing edge cooling cavity with one rib-roughened wall. The flow is fed through tilted slots on one side wall and exits through straight slots on the opposite side wall. The flow field aerodynamics is investigated in Part I of the paper. The reference Reynolds number is defined at the entrance of the test section and set at 67,500 for all the experiments. A qualitative flow model is deduced from surface-streamline flow visualizations. Two-dimensional particle image velocimetry measurements are performed in several planes around midspan of the channel and recombined to visualize and quantify three-dimensional flow features. The crossing-jets issued from the tilted slots are characterized and the jet-rib interaction is analyzed. Attention is drawn to the motion of the flow deflected by the rib-roughened wall and impinging on the opposite smooth wall. The experimental results are compared with the numerical predictions obtained from the finite volume Reynolds-averaged Navier–Stokes solver, CEDRE .

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Sketch of the setup

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Figure 3

Overall view of the PIV planes

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Figure 4

Configuration without ribs—Mean flow model obtained by means of surface streamlines flow visualizations: (a) crossing-jets interaction, and (b) impingements at the exit wall

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Figure 5

Modulus of time-averaged in-plane velocity and streamlines path in plane x′y

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Figure 6

Modulus of time-averaged in-plane velocity and streamlines path in planes x′y and xz_core_i

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Figure 7

Time-averaged streamwise velocity and rms of the velocity fluctuations in the crossing-jet

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Figure 8

Plane xy1: (a) modulus of time-averaged in-plane velocity, streamlines and ideal jet path (dashed lines); (b) cross-plane acceleration near the bottom wall

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Figure 9

Modulus of time-averaged in-plane velocity and streamlines path in planes xy2 and x′y (periodically duplicated)

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Figure 10

Modulus of time-averaged in-plane velocity and streamline paths in planes xz_mid_i_i+1 and xy1

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Figure 11

Modulus of time-averaged in-plane velocity and streamlines path in x″y

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Figure 12

Modulus of time-averaged in-plane velocity and streamlines in all PIV measurement planes

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Figure 13

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

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Figure 14

CFD: computational mesh

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Figure 15

CFD: modulus of mean in-plane velocity and streamlines path in plane xz_core_i

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Figure 16

CFD: modulus of mean in-plane velocity and streamlines path in plane xz_mid_i_i+1

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Figure 17

CFD: modulus of mean in-plane velocity and streamlines path in plane x″y

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