TECHNICAL PAPERS: Gas Turbines: Combustion and Fuel

Implementation and Validation of a New Soot Model and Application to Aeroengine Combustors

[+] Author and Article Information
M. Balthasar, F. Mauss

  Division of Combustion Physics, Lund Institute of Technology, 22100 Lund, Sweden

M. Pfitzner, A. Mack

BMW Rolls-Royce AeroEngines, Eschenweg 11, D-15827 Dahlewitz, Germany

J. Eng. Gas Turbines Power 124(1), 66-74 (Oct 01, 2000) (9 pages) doi:10.1115/1.1377596 History: Received October 01, 1999; Revised October 01, 2000
Copyright © 2002 by ASME
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Schematic representation of the soot model
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Interface between the CFD code and the subroutine containing the rates of soot formation
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Comparison between measured (symbols) and calculated (lines) soot volume fraction on the center line of a turbulent jet diffusion flame. Calculations have been done with surface reactions proportional to soot surface (line) and proportional to soot volume fraction (broken line).
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Particle inception rate in the mixture fraction scalar dissipation rate space as calculated from the flamelet model
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(a) The beta function fitted to the source term of particle inception (p=1 bar,Tox=850 K, χ=700 s−1 ); (b) parameters of oxidation soot source term—symbols: flamelet calculations, lines: fits
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BRR staged combustor configuration
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BRR staged combustor computational grid
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BRR staged combustor temperature contours (main zone plane)
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BRR staged combustor (main zone plane: contours of soot volume fraction (log10)
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BRR staged combustor (main zone plane): contours of mean mixture fraction (log10)
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BRR staged combustor (main zone plane): contours of particle inception source term
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BRR staged combustor (main zone plane): contours of surface growth source term
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BRR staged combustor (main zone plane): contours of oxidation source term
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BRR staged combustor: isosurface of soot mass fraction Ys=5*10−4 colored by temperature contours




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