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TECHNICAL PAPERS

Large-Eddy Simulation of Reacting Turbulent Flows in Complex Geometries

[+] Author and Article Information
K. Mahesh

Aerospace Engineering and Mechanics, University of Minnesota, 107 Akerman Hall, Minneapolis, MN 55455

G. Constantinescu

Civil and Environmental Engineering, University of Iowa, Iowa City, IA 52242

S. Apte, G. Iaccarino, F. Ham, P. Moin

Center for Integrated Turbulence Simulations, Stanford University, Building 500, Stanford, CA 94305

J. Appl. Mech 73(3), 374-381 (Nov 09, 2005) (8 pages) doi:10.1115/1.2179098 History: Received December 15, 2003; Revised November 09, 2005

Large-eddy simulation (LES) has traditionally been restricted to fairly simple geometries. This paper discusses LES of reacting flows in geometries as complex as commercial gas turbine engine combustors. The incompressible algorithm developed by Mahesh (J. Comput. Phys., 2004, 197, 215–240) is extended to the zero Mach number equations with heat release. Chemical reactions are modeled using the flamelet/progress variable approach of Pierce and Moin (J. Fluid Mech., 2004, 504, 73–97). The simulations are validated against experiment for methane-air combustion in a coaxial geometry, and jet-A surrogate/air combustion in a gas-turbine combustor geometry.

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Copyright © 2006 by American Society of Mechanical Engineers
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Figures

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Figure 10

(a) Gas turbine combustor sector geometry. (b) Instantaneous position of fuel spray superposed on contours of temperature from LES of reacting flow in gas turbine combustor geometry.

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Figure 1

Contrast between an idealized coaxial dump combustor (a), and the combustor from a Pratt and Whitney gas-turbine engine (b)

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Figure 2

Profiles of mean velocity and turbulent kinetic energy in LES of incompressible swirling flow in a coaxial combustor geometry. The solid lines are LES results, and the symbols are data from experiments by Sommerfeld and Qiu (27). H denotes the outer radius of the annular section, u¯x, u¯r, and u¯θ denote the mean axial, radial, and azimuthal velocity, respectively, and q2∕2 denotes the turbulent kinetic energy.

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Figure 3

Instantaneous contours of the (a) streamwise velocity, (b) temperature, (c) CO mass fraction, and (d) progress variable (YCO2+YH2O) in an azimuthal plane from LES of reacting flow in a coaxial combustor geometry

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Figure 4

Comparison of the mean and rms values of the streamwise velocity in unstructured grid LES (UNSTR) to Spadaccini (30) experiments (EXPT) and Pierce and Moin’s (2) LES on structured grids (STR)

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Figure 5

Comparison of the mean temperature in unstructured grid LES (UNSTR) to Spadaccini (30) experiments (EXPT) and Pierce and Moin’s (2) LES on structured grids (STR)

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Figure 6

Comparison of the mixture fraction in unstructured grid LES (UNSTR) to Spadaccini (30) experiments (EXPT) and Pierce and Moin’s (2) LES on structured grids (STR)

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Figure 7

Comparison of progress variable (YCO2+YH2O) between unstructured grid LES (UNSTR) to Spadaccini (30) experiments (EXPT) and Pierce and Moin’s (2) structured grid LES (STR)

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Figure 8

Comparison of CO mass fraction between unstructured grid LES (UNSTR) to Spadaccini (30) experiments (EXPT) and Pierce and Moin’s (2) structured grid LES (STR)

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Figure 9

Instantaneous contours of the (a) velocity magnitude, (b) streamwise velocity, (c) mixture fraction, and (d) progress variable from LES of reacting flow in gas turbine combustor geometry

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