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Journal of Turbomachinery | Volume 130 | Issue 4 | Research Paper
Research Papers

Large Eddy Simulation of Leading Edge Film Cooling—Part II: Heat Transfer and Effect of Blowing Ratio

[+] Author and Article Information
Ali Rozati, Danesh K. Tafti

High Performance Computational Fluid-Thermal Sciences and Engineering Laboratory, Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

J. Turbomach 130(4), 041015 (Aug 04, 2008) (7 pages) doi:10.1115/1.2812411 History: Received June 08, 2007; Revised June 20, 2007; Published August 04, 2008
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Detailed investigation of film cooling for a cylindrical leading edge is carried out using large eddy simulation (LES). The paper focuses on the effects of coolant to mainstream blowing ratio on flow features and, consequently, on the adiabatic effectiveness and heat transfer coefficient. With the advantage of obtaining unique, accurate, and dynamic results from LES, the influential coherent structures in the flow are identified. Describing the mechanism of jet-mainstream interaction, it is shown that as the blowing ratio increases, a more turbulent shear layer and stronger mainstream entrainment occur. The combined effects lead to a lower adiabatic effectiveness and higher heat transfer coefficient. Surface distribution and span-averaged profiles are shown for both adiabatic effectiveness and heat transfer (presented by Frossling number). Results are in good agreement with the experimental data of Ekkad [1998, “Detailed Film Cooling Measurement on a Cylindrical Leading Edge Model: Effect of Free-Steam Turbulence and Coolant Density  ,” ASME J. Turbomach., 120, pp. 799–807].
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+Computational domain
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Computational domain
Figure 1

Computational domain

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+Coherent structures, B.R.=0.4 (isosurface value=18)
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Coherent structures, B.R.=0.4 (isosurface value=18)
Figure 2

Coherent structures, B.R.=0.4 (isosurface value=18)

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+Pressure contour at x∕d=1.0 downstream of the coolant hole
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Pressure contour at x∕d=1.0 downstream of the coolant hole
Figure 3

Pressure contour at x∕d=1.0 downstream of the coolant hole

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+Coherent structures, B.R.=0.8 (isosurface value=18)
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Coherent structures, B.R.=0.8 (isosurface value=18)
Figure 4

Coherent structures, B.R.=0.8 (isosurface value=18)

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+Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.4)
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Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.4)
Figure 5

Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.4)

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+Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.8)
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Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.8)
Figure 6

Temperature contour and velocity vectors on cross-sectional planes normal to the surface and downstream the hole (B.R.=0.8)

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+Time averaged temperature profile normal to the wall at jet centerline
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Time averaged temperature profile normal to the wall at jet centerline
Figure 7

Time averaged temperature profile normal to the wall at jet centerline

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+T.K.E. profile normal to the wall at jet centerline
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T.K.E. profile normal to the wall at jet centerline
Figure 8

T.K.E. profile normal to the wall at jet centerline

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+Surface distribution of adiabatic effectiveness
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Surface distribution of adiabatic effectiveness
Figure 9

Surface distribution of adiabatic effectiveness

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+Spanwise averaged adiabatic effectiveness distribution
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Spanwise averaged adiabatic effectiveness distribution
Figure 10

Spanwise averaged adiabatic effectiveness distribution

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+Surface distribution of the Frossling number
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Surface distribution of the Frossling number
Figure 11

Surface distribution of the Frossling number

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+Spanwise averaged Frossling number distribution
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Spanwise averaged Frossling number distribution
Figure 12

Spanwise averaged Frossling number distribution

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