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TECHNICAL PAPERS

Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner

[+] Author and Article Information
J. J. Scrittore

Mechanical Engineering Department, Virginia Polytechnic Institute and State University, Blacksburg, VA 24061

K. A. Thole

Department of Mechanical and Nuclear Engineering , Pennsylvania State University, University Park, PA 16802-1412

S. W. Burd

Pratt & Whitney, United Technologies, East Hartford, CT 06108

J. Turbomach 129(3), 518-526 (Aug 02, 2006) (9 pages) doi:10.1115/1.2720492 History: Received July 13, 2006; Revised August 02, 2006

Effusion cooling of combustor liners for gas turbine engines is quite challenging and necessary to prevent thermal distress of the combustor liner walls. The flow and thermal patterns in the cooling layer are affected by the closely spaced film-cooling holes. It is important to fully document how the film layer behaves with a full-coverage cooling scheme to gain an understanding into surface cooling phenomena. This paper discusses experimental results from a combustor simulator tested in a low-speed wind tunnel. Engine representative, nondimensional coolant flows were tested for a full-coverage effusion plate. Laser Doppler velocimetry was used to measure the flow characteristics of the cooling layer. These experiments indicate that the full-coverage film cooling flow has unique and scaleable velocity profiles that result from the closely spaced effusion holes. A parametric study of the cooling flow behavior illustrates the complex nature of the film flow and how it affects cooling performance.

Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 1

Illustration of the wind tunnel facility used for film-cooling experiments

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Figure 2

Illustration of the test plate schematic showing surface temperature measurement region and locations for measurements of velocity profiles

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Figure 3

Inlet flow conditions measured at mid-pitch and quarter-pitch

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Figure 4

Streamwise dependence on the local momentum-flux ratios of film cooling jets

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Figure 5

Streamwise velocity profiles measured for I=10.6

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Figure 6

Streamwise velocity profiles measured for I=25.5

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Figure 7

Turbulence level profiles for I=10.6

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Figure 8

Turbulence level profiles for I=25.5

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Figure 9

Streamwise velocity profiles measured one row downstream of rows 1, 5, and 10 for I=10.6 and 25.5 using the blowing ratio, M, to normalize the profiles

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Figure 10

Turbulence level profiles measured one row downstream of rows 1, 5, and 10 for I=10.6 and 25.5. Profiles normalized to the blowing ratio, M.

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Figure 11

Streamwise velocity profiles measured one row downstream of row 20

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Figure 12

Turbulence level profiles measured one row downstream of row 20

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Figure 13

Streamwise velocities profiles measured one row downstream of row 20. Profiles normalized to the blowing ratio, M.

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Figure 14

Turbulence level profiles measured one row downstream of row 20. Profiles normalized to the blowing ratio, M.

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Figure 15

Streamwise velocity contours downstream of row fifteen for I=25.5. Vectors show streamwise and wall-normal velocity components. Arrow indicates row 15 cooling hole.

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Figure 16

Turbulence levels with vectors for I=25.5 showing streamwise and wall-normal velocity components. Arrow indicates row 15 cooling hole.

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Figure 17

Cross-sectional, plane x∕d=3 downstream of row 15 showing (a) streamwise velocity, u∕U∞; (b) wall-normal velocity, v∕U∞; and (c) turbulence levels. Solid arrows indicate row 15 hole location and dashed arrows indicate row 14 hole location.

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Figure 18

Adiabatic effectiveness contours of the effusion panel from rows 1 to 20 for (a) I=10.6 and (b) I=25.5

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Figure 19

Lateral average of adiabatic effectiveness of the effusion panel from rows 1 to 20 for I=10.6 and I=25.5. Note that x∕s=0 is the leading edge of the first hole row.

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