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 - Publisher Copyright:
Copyright © 2022 by ASME and The United States Government.
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
UR - http://www.scopus.com/inward/record.url?scp=85141409482&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85141409482&partnerID=8YFLogxK
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 -