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

3D RANS Simulation of Turbulent Flow and Combustion in a 5 MW Reverse-Flow Type Gas Turbine Combustor

[+] Author and Article Information
Daero Joung, Kang Y. Huh

Department of Mechanical Engineering, Pohang University of Science and Technology, Pohang 790-784, Korea

J. Eng. Gas Turbines Power 132(11), 111504 (Aug 11, 2010) (9 pages) doi:10.1115/1.4000894 History: Received August 07, 2009; Revised September 02, 2009; Published August 11, 2010; Online August 11, 2010

This study is concerned with 3D RANS simulation of turbulent flow and combustion in a 5 MW commercial gas turbine combustor. The combustor under consideration is a reverse flow, dry low NOx type, in which methane and air are partially mixed inside swirl vanes. We evaluated different turbulent combustion models to provide insights into mixing, temperature distribution, and emission in the combustor. Validation is performed for the models in STAR-CCM+ against the measurement data for a simple swirl flame (http://public.ca.sandia.gov/TNF/swirlflames.html). The standard k-ε model with enhanced wall treatment is employed to model turbulent swirl flow, whereas eddy break-up (EBU), presumed probability density function laminar flamelet model, and partially premixed coherent flame model (PCFM) are tried for reacting flow in the combustor. Independent simulations are carried out for the main and pilot nozzles to avoid flashback and to provide realistic inflow boundary conditions for the combustor. Geometrical details such as air swirlers, vane passages, and liner holes are all taken into account. Tested combustion models show similar downstream distributions of the mean flow and temperature, while EBU and PCFM show a lifted flame with stronger effects of swirl due to limited increase in axial momentum by expansion.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Configuration of the Sydney swirl flame (SM1)

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Figure 2

Radial profiles of the mean axial velocity and temperature at different axial locations

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Figure 3

Radial profiles of CO and CO2 mass fractions at different axial locations

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Figure 4

Grid for the whole combustor in coupled simulation

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Figure 5

Grid for the pilot nozzle

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Figure 6

Grid for the main nozzle

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Figure 7

Grid for the combustor chamber in decoupled simulation

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Figure 8

Grid sensitivity at Y=35 mm

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Figure 9

Grid sensitivity at the centerline

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Figure 10

Distribution of the mean equivalence ratio at the exits of the main (outside) and pilot (inside) nozzles

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Figure 11

Distribution of the mean equivalence ratio at the exits of the main (left) and pilot (right) nozzles

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Figure 12

Mean axial velocity component in the nonreacting flow (m/s)

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Figure 13

TKE in the nonreacting flow (m2/s2)

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Figure 14

Mean equivalence ratio in the nonreacting flow

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Figure 15

Distribution of the mean temperature in the whole combustor (K)

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Figure 16

Mean temperatures at the main (left) and pilot (right) nozzle exits

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Figure 17

Distribution of the axial velocity component for different combustion models in the reacting flow (m/s)

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Figure 18

Distribution of the mean temperature for different combustion models in the reacting flow (K)

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Figure 19

Axial profiles of velocity, temperature, TKE, CO, and CO2 mass fractions along the centerline

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Figure 20

Flame structures of equilibrium PPDF and LFM for different scalar dissipation rates at 1.41 MPa

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Figure 21

Mean temperature distributions of PCFM with varying model parameter α (K)

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