High-fidelity numerical simulations of the reacting flow field of an annular combustor model of an aircraft engine

Ahmed Taha, University of Illinois at Urbana-Champaign

Usage Details

The project is dedicated to perform high-fidelity numerical simulations of the full annular aeronautical combustor model from a turbofan engine using wall-resolved large-eddy simulation (LES). The challenges associated to the modelling of this system correspond to the full characterization of the reacting layers, the interactions between the injectors, the flame/wall interactions and the ability to fully resolve the momentum boundary layer on a practical configuration. The model includes 15 swirling stabilized fuel injection systems with a pilot and main injection sections, cooling air and passages. This project is defined to show the aerospace and aeronautical community that HPC codes can be used to perform real engine simulations and pretends to go one step beyond the state of the art on modelling large-scale combustion systems for propulsion and power.