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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuel

Flow and Thermal Field Measurements in a Combustor Simulator Relevant to a Gas Turbine Aeroengine

[+] Author and Article Information
S. S. Vakil, K. A. Thole

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

J. Eng. Gas Turbines Power 127(2), 257-267 (Apr 15, 2005) (11 pages) doi:10.1115/1.1806455 History: Received October 01, 2002; Revised March 01, 2003; Online April 15, 2005
Copyright © 2005 by ASME
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References

Figures

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(a) Layout and measurements planes for the combustor simulator (dimensions in cm). (b) Illustration and description of cooling hole arrangement for liners.
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Comparisons of two and three-component LDV profiles measured independently in an overlap location just downstream of the first row of dilution
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Film-cooling thermal field measurements in plane 0p with an average liner flow of I=3,DR=1.1
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Film-cooling thermal field measurements in plane 0p with an average liner flow of I=9,DR=1.1
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Thermal field contours in a streamwise plane through a first row dilution hole (plane 1s) with Lefebvre’s 15 jet penetration correlation
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Thermal field contours in plane 1p
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Measured (a) secondary velocity vectors with contours of u/uin and (b) turbulence levels for plane 1p
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Thermal field contours for plane 2s showing Lefebvre’s 15 jet penetration correlation
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(a), (b) Flow field vectors (left) and contours of turbulence levels (right) for plane 2s, downstream of the second row of dilution jets
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Thermal field contours in plane 2p downstream of the second row of dilution
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Secondary velocity vectors with contours of the streamwise velocities in plane 2p
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(a)–(c) Contours of the rms fluctuations for the flow in plane 2p
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Contours of turbulence levels in plane 2p
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Illustration of the wind tunnel facility used for the combustor simulator experiments

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