Flow Field Simulations of a Gas Turbine Combustor

[+] Author and Article Information
M. D. Barringer, O. T. Richard, J. P. Walter, S. M. Stitzel, K. A. Thole

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

J. Turbomach 124(3), 508-516 (Jul 10, 2002) (9 pages) doi:10.1115/1.1475742 History: Received November 01, 2000; Revised March 01, 2001; Online July 10, 2002
Copyright © 2002 by ASME
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Illustration of the low speed wind tunnel facility with the combustor simulator section
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Illustration of the supply channels for each of the combustor liner and dilution flows (a), and geometric details of the primary flow path (b).
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Film-cooling hole pattern for each liner panel
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Schematic illustrating the combustor liner exit slot
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Measured discharge coefficients of the film-cooling hole arrays
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Measured velocity profiles downstream of the first panel at three different spanwise positions
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Mean velocity profiles measured at the exit of the simulator in the span (a) and pitch (b) with, and without the dilution jets
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Turbulence profiles measured at the exit of the combustor simulator in the span (a) and pitch (b), and streamwise velocity energy spectra (c)
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Contours of normalized streamwise velocity (a) and turbulence levels upstream of the slot exit (b) for the dilution flow case
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The nonuniform total pressure profile across the pin-finned exit slot. Below the plot is an indication of where the pin fins and slot feeder holes are located.
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Nondimensional total pressure profiles of the exit slot for the no dilution (a) and dilution cases (b)
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Spatially averaged nondimensional total pressure profiles downstream of the combustor liner slot for the no dilution and dilution cases compared to a turbulent boundary layer 21
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Nondimensional thermal field contours after the exit slot for no dilution (a) and dilution (b)
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Adiabatic effectiveness contours (a) and downstream levels (b) on the endwall for the case with dilution jets



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