TY - GEN
T1 - COMPUTATIONAL FLUID DYNAMICS MODELING OF FUEL PROPERTIES IMPACT ON LEAN BLOWOUT IN THE ARC-M1 COMBUSTOR
AU - Dasgupta, Debolina
AU - Som, Sibendu
AU - Wood, Eric
AU - Lee, Tonghun
AU - Mayhew, Eric
AU - Temme, Jacob
AU - Kweon, Chol Bum
N1 - Fellowship). The experimental research was also funded by the U.S. Federal Aviation Administration Office of Environment and Energy through ASCENT, the FAA Center of Excellence for Alternative Jet Fuels and the Environment, project 65b Rapid Jet Fuel Prescreening through FAA Award Number DOT FAA 13-C-AJFE-UI 030 under the supervision of Anna Oldani. Any opinions, findings, conclusions, or recommendations expressed in this material are those of the authors and do not necessarily reflect the views of the FAA. This research used resources of the Advanced Photon Source, a U.S. Department of Energy (DOE) Office of Science User Facility operated for the DOE Office of Science by Argonne National Laboratory under Contract No. DE-AC02-06CH11357. The authors would like to thank Dr. Prithwish Kundu for his modeling efforts in initial phases of this research. 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 Army Research Laboratory or the U.S. Government. The CFD simulations were performed using computing resources provided on Bebop, a high-performance computing cluster operated by the Laboratory Computing Resource Center (LCRC) at Argonne. Lastly, the authors wish to thank Convergent Science, Inc. for providing the CONVERGE software licenses.
The simulation research was sponsored by the Army Research Laboratory. The experimental research was sponsored by the Army Research Laboratory and was accomplished under Cooperative Agreement Numbers W911NF-20-2-0220,
PY - 2022
Y1 - 2022
N2 - The flow and flame dynamics within liquid fueled gas turbine combustors are complex due to the interactions between the highly turbulent flow, spray dynamics and combustion. Computational tools help understand these governing processes. A computational fluid dynamics model for Army Research Combustor Midsize (ARC-M1) is developed to characterize the complex turbulent flow, multi-phase spray physics and hydrocarbon chemistry. Using high-quality X-ray data for the combustor, the spray is initialized in the near nozzle region. To understand the overall impact of liquid properties, the liquid properties corresponding to Jet-A and F-24 are tested. It is observed that F-24 has a higher LBO liquid flow rate compared to Jet A. To understand the impact of individual properties, liquid properties such as density, viscosity, specific heat, heat of vaporization, are changed one at a time. It was observed that an increase in density, viscosity, heat of vaporization and specific heat w.r.t Jet-A tends to increase the LBO liquid flow rate i.e. makes the flame blow-off at higher equivalence ratios. This is attributed to the altered flame shapes and the impact of these properties on fuel heating and its subsequent vaporization.
AB - The flow and flame dynamics within liquid fueled gas turbine combustors are complex due to the interactions between the highly turbulent flow, spray dynamics and combustion. Computational tools help understand these governing processes. A computational fluid dynamics model for Army Research Combustor Midsize (ARC-M1) is developed to characterize the complex turbulent flow, multi-phase spray physics and hydrocarbon chemistry. Using high-quality X-ray data for the combustor, the spray is initialized in the near nozzle region. To understand the overall impact of liquid properties, the liquid properties corresponding to Jet-A and F-24 are tested. It is observed that F-24 has a higher LBO liquid flow rate compared to Jet A. To understand the impact of individual properties, liquid properties such as density, viscosity, specific heat, heat of vaporization, are changed one at a time. It was observed that an increase in density, viscosity, heat of vaporization and specific heat w.r.t Jet-A tends to increase the LBO liquid flow rate i.e. makes the flame blow-off at higher equivalence ratios. This is attributed to the altered flame shapes and the impact of these properties on fuel heating and its subsequent vaporization.
KW - Computational Fluid Dynamics modeling
KW - Liquid fueled gas turbines
KW - Multiphase turbulent reacting flow
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U2 - 10.1115/GT2022-79347
DO - 10.1115/GT2022-79347
M3 - Conference contribution
AN - SCOPUS:85141409482
T3 - Proceedings of the ASME Turbo Expo
BT - Combustion, Fuels, and Emissions
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition, GT 2022
Y2 - 13 June 2022 through 17 June 2022
ER -