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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Modeling Strategies for Large Eddy Simulation of Lean Burn Spray Flames

[+] Author and Article Information
S. Puggelli

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: stefano.puggelli@htc.de.unifi.it

D. Bertini

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: davide.bertini@htc.de.unifi.it

L. Mazzei

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: lorenzo.mazzei@htc.de.unifi.it

A. Andreini

Department of Industrial Engineering,
University of Florence,
via S. Marta 3,
Florence 50139, Italy
e-mail: antonio.andreini@htc.de.unifi.it

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 26, 2017; final manuscript received August 9, 2017; published online November 21, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(5), 051501 (Nov 21, 2017) (11 pages) Paper No: GTP-17-1396; doi: 10.1115/1.4038127 History: Received July 26, 2017; Revised August 09, 2017

Over the last years, aero-engines are progressively evolving toward design concepts that permit improvements in terms of engine safety, fuel economy, and pollutant emissions. With the aim of satisfying the strict NOx reduction targets imposed by ICAO-CAEP, lean burn technology is one of the most promising solutions even if it must face safety concerns and technical issues. Hence, a depth insight on lean burn combustion is required, and computational fluid dynamics can be a useful tool for this purpose. In this work, a comparison in large eddy simulation (LES) framework of two widely employed combustion approaches like the artificially thickened flame (ATF) and the flamelet generated manifold (FGM) is performed using ANSYS fluent v16.2. Two literature test cases with increasing complexity in terms of geometry, flow field, and operating conditions are considered. First, capabilities of FGM are evaluated on a single swirler burner operating at ambient pressure with a standard pressure atomizer for spray injection. Then, a second test case, operated at 4 bar, is simulated. Here, kerosene fuel is burned after an injection through a prefilming airblast atomizer within a corotating double swirler. Obtained comparisons with experimental results show different capabilities of ATF and FGM in modeling the partially premixed behavior of the flame and provide an overview of the main strengths and limitations of the modeling strategies under investigation.

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Figures

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Fig. 1

Sketch of the geometry experimentally studied and of the spray flame under investigation (adapted from Ref. [4])

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Fig. 2

DLR generic single sector combustor with details of the swirler geometry and of the studied flame (adapted from Refs. [5] and [6])

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Fig. 3

Computational domain and boundary conditions used for Sheen burner

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Fig. 4

Instantaneous (τft = 3.5 for M1; τft = 2.5 for M2) and mean temperature and velocity distributions for Sheen burner for M1 and M2

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Fig. 5

Axial velocity (top) and temperature (bottom) profiles at several axial positions

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Fig. 6

Dry (percent) mole fractions of CO2 (top) and O2 (bottom) profiles at several axial positions

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Fig. 7

Dry (percent) mole fractions of H2 (top) and CO (bottom) profiles at several axial positions

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Fig. 8

Computational domain used for DLR-SSGC burner

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Fig. 9

Instantaneous (for τft = 2) and mean axial velocity and temperature distributions obtained with FGM and ATF

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Fig. 10

Isocontours of heat release rates obtained with FGM and ATF against the experimental map (modified from Ref. [6]). Super-imposed isolines represent different levels of fuel distribution. The horizontal white line indicates the burner exit plane. The red points A, B, C, and D on the experimental map highlight the radial positions where spray PDF is evaluated (see Fig. 14).

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Fig. 11

Temperature distributions obtained with FGM and ATF against the experimental map (modified from Ref. [6]). The white line indicates the burner exit plane.

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Fig. 12

Isocontours of heat release rates obtained with FGM using finite rate (left) and Zimont (right) closures. The white line indicates the burner exit plane.

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Fig. 13

Temperature profiles obtained with FGM and ATF at several axial distances

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Fig. 14

PDF spray distributions obtained with FGM and ATF at z = 7 mm at four radial positions (see Fig. 10 for details about the four locations)

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Fig. 15

Comparison of SMD (top) and axial velocity (bottom) obtained with FGM and ATF against experimental data

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Fig. 16

Comparison of liquid volume flux for the 16 μm class obtained with ATF against experimental data (adapted from Ref.[6])

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Fig. 17

Profiles of axial velocities at axial position 7 mm for different size classes obtained with FGM and ATF

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