Investigation of multi-scale flow structures and combustion characteristics in a cavity-enhanced circular scramjet

This study delves into the investigation of multi-scale flow structures and combustion characteristics in a cavityenhanced circular scramjet operating under a Mach-4.5 freestream flow condition with a total temperature of 2200 K and a total pressure of 164 kPa. To achieve this, a hybrid large-eddy/Reynolds-averaged Navier-Stokes method, coupled with a pressure-corrected Flamelet/Progress Variable model, is employed and validated. The combustion flow field shows abundant small- and medium-scale flow structures induced by compressibility and combustion heat release. Vorticity alteration is found to be mainly caused by these factors, with the volumetric expansion term and baroclinic term serving as the primary driving terms. The whole combustion process is characterized by zoning and multi-scale features in spatial, temporal, heat release and species distribution, arising from differences in fuel-air mixing state and chemical reaction rates in the flow field. The injectionformed bow shock and the cavity ramp-formed compression wave interact intensively with the fuel plume, enriching the turbulent structures and strongly coupling with the chemical reaction process. The cavity not only promotes fuel-air mixing and combustion, but also facilitate the rapid transition from the laminar-like flame to thickened turbulent combustion. Statistical analysis reveals that the combustion heat release is predominantly governed by the scramjet mode and the diffusion flames, and further demonstrates the multi-scale flow and chemical reaction characteristics. Most of the combustion flow field is observed to be governed by fast chemistry, primarily in the corrugated flamelet regime, while some slow chemistry zones are also identified, lying in the distributed reaction zone regime.