TY - GEN
T1 - Numerical Simulation of Scram-mode Operation of an Axisymmetric Combustor in an Arc Tunnel
AU - Richardson, Samuel
AU - Hash, Caleb A.
AU - Drummond, Paige M.
AU - Edwards, Jack R.
AU - Lee, Tonghun
AU - Kato, Nozomo
N1 - Publisher Copyright:
© 2024 by Samuel Richardson, Caleb Hash, Paige Drummond, Jack Edwards, Tonghun Lee, Nozomo Kato.
PY - 2024
Y1 - 2024
N2 - Large-eddy simulations of scram-mode operation of an axisymmetric inlet-isolator-combustor configuration experimentally tested in the University of Illinois’s ACT-II arc-heated combustion tunnel are presented in this work. A 32-species ethylene oxidation mechanism including nitrous oxide formation reactions is used for most calculations; sensitivities due to the use of a 43-species model are also assessed. Numerical flame stabilization under conditions of the experiment (Mach 4.5 inflow, equivalence ratio of 0.82) is sensitive function of the rate of energy release within the combustor. This can be altered by changes in the inflow O atom composition (using values obtained from simulations of the arc heater itself), the choice of reaction mechanism, and the wall-heating level, but even with these controls, it was found necessary to threshold the pressure level supplied to the reaction rates to achieve stable supersonic combustion within the unit. The results presented show a strong sensitivity to these controlling factors in that good agreement with experimental trends can be obtained for specific combinations but the prescription is not unique. The predictions show that scram mode operation occurs under lean premixed conditions, characterized by a predominance of CO, very little formation of CO2, an appreciable temperature rise, and an OH signal that rises substantially prior to increases in the formation rates of the major combustion products.
AB - Large-eddy simulations of scram-mode operation of an axisymmetric inlet-isolator-combustor configuration experimentally tested in the University of Illinois’s ACT-II arc-heated combustion tunnel are presented in this work. A 32-species ethylene oxidation mechanism including nitrous oxide formation reactions is used for most calculations; sensitivities due to the use of a 43-species model are also assessed. Numerical flame stabilization under conditions of the experiment (Mach 4.5 inflow, equivalence ratio of 0.82) is sensitive function of the rate of energy release within the combustor. This can be altered by changes in the inflow O atom composition (using values obtained from simulations of the arc heater itself), the choice of reaction mechanism, and the wall-heating level, but even with these controls, it was found necessary to threshold the pressure level supplied to the reaction rates to achieve stable supersonic combustion within the unit. The results presented show a strong sensitivity to these controlling factors in that good agreement with experimental trends can be obtained for specific combinations but the prescription is not unique. The predictions show that scram mode operation occurs under lean premixed conditions, characterized by a predominance of CO, very little formation of CO2, an appreciable temperature rise, and an OH signal that rises substantially prior to increases in the formation rates of the major combustion products.
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U2 - 10.2514/6.2024-0976
DO - 10.2514/6.2024-0976
M3 - Conference contribution
AN - SCOPUS:85193857709
SN - 9781624107115
T3 - AIAA SciTech Forum and Exposition, 2024
BT - AIAA SciTech Forum and Exposition, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2024
Y2 - 8 January 2024 through 12 January 2024
ER -