TY - GEN
T1 - Ethylene combustion in an axisymmetric mach 4.5 cavity
AU - Hyde, Evan W.
AU - Goodwin, Gabriel B.
AU - Johnson, Ryan F.
AU - Lee, Tonghun
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Axisymmetric cavity combustors are not subjected to the corner boundary-layer effects present in planar combustors, making them an attractive configuration for robust flameholding. Experiments at the University of Illinois have investigated ethylene combustion in an axisymmetric combustor using a cavity flameholder with inlet flow at Mach 4.5. Cavity flameholding was achieved for a range of fuel equivalence ratios. This paper presents preliminary results in using the Naval Research Laboratory’s discontinuous Galerkin finite element method code, JENRE®, to simulate the operation of the University of Illinois ACT-II cavity combustor facility. The overall goal of this ongoing effort is to gain further insight into combustion dynamics in an axisymmetric supersonic cavity combustor. Two and three dimensional simulations were performed using a reduced model for ethylene-air combustion. Robust, cavity-stabilized combustion was achieved and results are compared to experimental data.
AB - Axisymmetric cavity combustors are not subjected to the corner boundary-layer effects present in planar combustors, making them an attractive configuration for robust flameholding. Experiments at the University of Illinois have investigated ethylene combustion in an axisymmetric combustor using a cavity flameholder with inlet flow at Mach 4.5. Cavity flameholding was achieved for a range of fuel equivalence ratios. This paper presents preliminary results in using the Naval Research Laboratory’s discontinuous Galerkin finite element method code, JENRE®, to simulate the operation of the University of Illinois ACT-II cavity combustor facility. The overall goal of this ongoing effort is to gain further insight into combustion dynamics in an axisymmetric supersonic cavity combustor. Two and three dimensional simulations were performed using a reduced model for ethylene-air combustion. Robust, cavity-stabilized combustion was achieved and results are compared to experimental data.
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M3 - Conference contribution
AN - SCOPUS:85100269775
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 9
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -