TY - GEN
T1 - Manifold-based Modeling for Supersonic Turbulent Combustion
AU - Cisneros–garibay, Esteban
AU - Mueller, Michael E.
N1 - Publisher Copyright:
© 2023, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2023
Y1 - 2023
N2 - An iterative algorithm to incorporate compressibility effects of high-speed flows into manifold-based turbulent-combustion models is developed. The algorithm allows for the equation of state—unclosed in compressible flow solvers—to be evaluated consistently with the manifold-based model, without further approximations. The manifold inputs (fuel and oxidizer temperatures and pressure) are determined iteratively to reflect the non-negligible variations in thermodynamic state (expressed in terms of transported density and energy in the flow solver) that are characteristic of supersonic combustion. The algorithm is demonstrated on data from simulations of high-speed reacting mixing layers and is significantly more accurate than established approaches that only partially couple the manifold to the compressible flow solver by only approximately evaluating the equation of state. Partial-coupling approximations can yield errors in temperature and water source term in excess of 10% and 20%, which are eliminated with the proposed iterative approach. Extensions and practical implementation are discussed.
AB - An iterative algorithm to incorporate compressibility effects of high-speed flows into manifold-based turbulent-combustion models is developed. The algorithm allows for the equation of state—unclosed in compressible flow solvers—to be evaluated consistently with the manifold-based model, without further approximations. The manifold inputs (fuel and oxidizer temperatures and pressure) are determined iteratively to reflect the non-negligible variations in thermodynamic state (expressed in terms of transported density and energy in the flow solver) that are characteristic of supersonic combustion. The algorithm is demonstrated on data from simulations of high-speed reacting mixing layers and is significantly more accurate than established approaches that only partially couple the manifold to the compressible flow solver by only approximately evaluating the equation of state. Partial-coupling approximations can yield errors in temperature and water source term in excess of 10% and 20%, which are eliminated with the proposed iterative approach. Extensions and practical implementation are discussed.
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U2 - 10.2514/6.2023-2529
DO - 10.2514/6.2023-2529
M3 - Conference contribution
AN - SCOPUS:85199571367
SN - 9781624106996
T3 - AIAA SciTech Forum and Exposition, 2023
BT - AIAA SciTech Forum and Exposition, 2023
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA SciTech Forum and Exposition, 2023
Y2 - 23 January 2023 through 27 January 2023
ER -