Akademik Veri Yönetim Sistemi
Isi Bilimi Ve Teknigi Dergisi/ Journal of Thermal Science and Technology, cilt.45, sa.1, ss.10-21, 2025 (SCI-Expanded, Scopus, TRDizin)
The design of a dual-inlet dump ramjet combustor is critical to the development of a ramjet propulsion system. Parameters such as pressure drop, pressure fluctuations, and combustion efficiency must be evaluated across different flight regimes. In this study, Large Eddy Simulation (LES) and Delayed Detached Eddy Simulation (DDES) techniques, coupled with the Steady Laminar Flamelet combustion model, are used to model a generic ramjet combustor. Grid convergence was ensured through the Richardson extrapolation method, and the grid quality was evaluated using the M-index. Close agreement between both LES and DDES approaches and experimental data confirms their accuracy in simulating the complex flow behaviour of the combustor. The present research demonstrates that the Steady Laminar Flamelet model is capable of predicting flow structures in a ramjet combustor under reacting conditions. In LES simulations, turbulent kinetic energy prediction in the near-wall region was enhanced, leading to faster mixing and an overestimation of combustion efficiency. DDES predictions achieved even closer agreement with experimental data, highlighting the effectiveness of eddy simulation with near-wall modelling when wall resolution is not feasible. This approach demonstrates improved agreement between DDES predictions and experimental data and highlights its efficiency in reducing the need for excessively refined meshes in studying dump-type low subsonic combustors.