TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Experimental and Numerical Investigation of a Planar Combustor Sector at Realistic Operating Conditions

[+] Author and Article Information
M. Carl, T. Behrendt, C. Fleing, M. Frodermann, J. Heinze, C. Hassa

Institute of Propulsion Technology, German Aerospace Center, Linder Höhe, DLR D-51147 Cologne, Germany

U. Meier, D. Wolff-Gassmann

Institute of Combustion Technology, German Aerospace Center, Pfaffenwaldring 38–40 D-70569 Stuttgart, Germany

S. Hohmann, N. Zarzalis

Daimler Chrysler Aerospace, Dachauerstrasse 665, D-80995 Munich, Germany

J. Eng. Gas Turbines Power 123(4), 810-816 (Oct 01, 2000) (7 pages) doi:10.1115/1.1378298 History: Received October 01, 1999; Revised October 01, 2000
Copyright © 2001 by ASME
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RMS of vertical gas velocity in the mixing zone (P30=6 bar,T30=700 K,AFR=40)
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OH LIF in the mixing zone (P30=6 bar,T30=700 K,AFR=40), (a) upper figure: single shot, (b) lower figure: RMS
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Gas velocity in the mixing zone (P30=6 bar,T30=700 K,AFR=40)
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SMD and volume concentration at an axial distance of 6 mm to the nozzle, cf. Fig. 9(a), (P30=6 bar,T30=700 K,AFR=90)
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OH distribution (P30=6 bar,T30=700 K,AFR=40)
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OH* chemiluminescence, Mie scattering on kerosene and gas velocity in the primary zone (P30=6 bar,T30=700 K); (a) upper figure: AFR=90, (b) lower figure: AFR=40
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Gas velocity in the primary zone (P30=6 bar,T30=700 K); (a) upper figure: AFR=90, (b) lower figure: AFR=40
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Optical set up of PDA (top view onto combustor)
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Experimental mixing field in the plane through the center of the nozzle
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Predicted mixing field in the plane through the center of the nozzle
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Control volume and surface grid
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Schematic view of test plant
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Radial circumferential cross section of combustor and pressure vessel



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