TY - GEN
T1 - Computational Fluid Dynamics Modeling of Combustor Performance in the ARC-S1 Gas Turbine Combustor
AU - Dasgupta, Debolina
AU - Christopher, Joshua
AU - Shim, Hanseul
AU - O’Brien, Casey
AU - Lee, Tonghun
AU - Kim, Jeongwon
AU - Mayhew, Eric
AU - Temme, Jacob E.
AU - Kweon, Chol Bum M.
N1 - The simulation research was funded by DEVCOM Army Research Laboratory (ARL). The experimental research was funded by ARL under Cooperative Agreement Numbers W911NF-24-2-0031 and W911NF-20-2-0220. This research used resources of the Advanced Photon Source, a U.S. Department of Energy (DOE) Office of Science User Facility 12 operated for the DOE Office of Science by Argonne National Laboratory under Contract No. DE-AC02-06CH11357. The submitted manuscript has been created by UChicago Argonne, LLC, Operator of Argonne National Laboratory (Argonne). The U.S. Government retains for itself, and others acting on its behalf, a paid-up nonexclusive, irrevocable world-wide license in said article to reproduce, prepare derivative works, distribute copies to the public, and perform publicly and display publicly, by or on behalf of the Government. The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the ARL, or the U.S. Government. The CFD simulations were performed using computing resources provided on Bebop and Improv, high-performance computing clusters operated by the Laboratory Computing Resource Center at Argonne. Lastly, the authors wish to thank Convergent Science, Inc. for providing the CONVERGE software licenses.
PY - 2025
Y1 - 2025
N2 - The internal dynamics of liquid-fueled gas turbine combustors are complex due to the interaction between the spray physics, turbulence, and combustion. Computational tools help understand these processes. A Computational Fluid Dynamics (CFD) model is developed for the Army Research Combustor-small size, ARC-S1 to characterize the steady-state combustion behavior of F-24 jet fuel for different operating conditions and geometry. High quality droplet data, measured with high-speed X-ray phase contrast imaging, is used for spray model initialization. The initial design of ARC-S1 is based on a trapped vortex cavity combustor. To compare changes in the geometry, metrics such as the mass exchange between cavities, fuel consumption, and combustion efficiency are developed. In particular, the impact of swirl and cavity shapes are investigated for a range of operating conditions. In general, it is observed that the presence of swirl can improve mixing but also increases fuel lost as film on the walls of the cavities and combustor. Modification in the cavity geometry can lead to changes in temperature distribution that can be leveraged for improved fuel consumption.
AB - The internal dynamics of liquid-fueled gas turbine combustors are complex due to the interaction between the spray physics, turbulence, and combustion. Computational tools help understand these processes. A Computational Fluid Dynamics (CFD) model is developed for the Army Research Combustor-small size, ARC-S1 to characterize the steady-state combustion behavior of F-24 jet fuel for different operating conditions and geometry. High quality droplet data, measured with high-speed X-ray phase contrast imaging, is used for spray model initialization. The initial design of ARC-S1 is based on a trapped vortex cavity combustor. To compare changes in the geometry, metrics such as the mass exchange between cavities, fuel consumption, and combustion efficiency are developed. In particular, the impact of swirl and cavity shapes are investigated for a range of operating conditions. In general, it is observed that the presence of swirl can improve mixing but also increases fuel lost as film on the walls of the cavities and combustor. Modification in the cavity geometry can lead to changes in temperature distribution that can be leveraged for improved fuel consumption.
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U2 - 10.2514/6.2025-1517
DO - 10.2514/6.2025-1517
M3 - Conference contribution
AN - SCOPUS:105001248547
SN - 9781624107238
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
BT - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2025
Y2 - 6 January 2025 through 10 January 2025
ER -