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Research Papers

Momentum and Thermal Boundary Layer Development on an Internally Cooled Turbine Vane

[+] Author and Article Information
Jason E. Dees, David G. Bogard, Gustavo A. Ledezma, Gregory M. Laskowski, Anil K. Tolpadi

 The University of Texas at Austin, Austin, TX 78712GE Global Research Center, Niskayuna, NY 12309GE Energy, Schenectady, NY 12345

J. Turbomach 134(6), 061004 (Aug 27, 2012) (11 pages) doi:10.1115/1.4006281 History: Received September 28, 2010; Revised May 23, 2011; Published August 27, 2012; Online August 27, 2012

Recent advances in computing power have made conjugate heat transfer simulations of turbine components increasingly popular; however, limited experimental data exist with which to evaluate these simulations. The primary parameter used to evaluate simulations is often the external surface temperature distribution, or overall effectiveness. In this paper, the overlying momentum and thermal boundary layers at various streamwise positions around a conducting, internally cooled simulated turbine vane were measured under low (Tu = 0.5%) and high (Tu = 20%) freestream turbulence conditions. Furthermore, experimental results were compared to computational predictions. In regions where a favorable pressure gradient existed, the thermal boundary layer was found to be significantly thicker than the accompanying momentum boundary layer. Elevated freestream turbulence had the effect of thickening the thermal boundary layer much more effectively than the momentum boundary layer over the entire vane. These data are valuable in understanding the conjugate heat transfer effects on the vane as well as serving as a tool for computational code evaluation.

Copyright © 2012 by by ASME
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References

Figures

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Figure 1

Schematic of the simulated turbine vane test section

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Figure 2

Test airfoil pressure distribution

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Figure 3

Test airfoil schematic

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Figure 4

Schematic of secondary flow loop

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Figure 5

Schematic of boundary layer measurement locations

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Figure 6

Computational domains

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Figure 7

Effect of grid refinement near wall treatment and cavity inlet velocity boundary condition. Overall effectiveness distribution, suction side, smooth internal wall.

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Figure 8

Measured mean velocity profiles for vane pressure surface

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Figure 9

Measured fluctuating velocity profiles for vane pressure surface

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Figure 10

Measured and predicted mean velocity profiles, pressure surface, Tu = 0.5%

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Figure 11

Measured and predicted mean velocity profiles, pressure surface, Tu = 20%

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Figure 12

Measured mean velocity profiles on the suction surface

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Figure 13

Measured fluctuating velocity profiles on the suction surface

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Figure 14

Measured and predicted mean velocity profiles, suction surface, Tu = 0.5%

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Figure 15

Measured and predicted mean velocity profiles, suction surface, Tu = 20%

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Figure 16

Predicted turbulence kinetic energy (left) and eddy viscosity ratio (right); Tu = 0.5%

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Figure 17

Measured mean velocity and temperature profiles, pressure side, Tu = 0.5%

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Figure 18

Mean velocity and temperature profiles, pressure side, Tu = 20%

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Figure 19

Mean temperature profiles, pressure side, high and low Tu

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Figure 20

Measured and predicted temperature profiles, pressure surface, Tu = 0.5%

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Figure 21

Measured and predicted temperature profiles, pressure surface, Tu = 20%

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Figure 22

Mean velocity and temperature profiles, suction side, Tu = 0.5%

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Figure 23

Mean velocity and temperature profiles, suction side, Tu = 20%

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Figure 24

Measured and predicted temperature profiles, suction surface, Tu = 0.5%

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Figure 25

Measured and predicted temperature profiles, suction surface, Tu = 20%

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Figure 26

Measured velocity and thermal boundary layer thicknesses

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