Manifold-based Modeling for Supersonic Turbulent Combustion

Esteban Cisneros–garibay, Michael E. Mueller

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish (US)
Title of host publicationAIAA SciTech Forum and Exposition, 2023
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624106996
DOIs
StatePublished - 2023
EventAIAA SciTech Forum and Exposition, 2023 - Orlando, United States
Duration: Jan 23 2023Jan 27 2023

Publication series

NameAIAA SciTech Forum and Exposition, 2023

Conference

ConferenceAIAA SciTech Forum and Exposition, 2023
Country/TerritoryUnited States
CityOrlando
Period1/23/231/27/23

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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