The present research includes a comprehensive computational fluid dynamics (CFD) investigation to enhance the scramjet combustor performance. Although scramjet propulsion systems have a lot of potential for use in hypersonic flight, they face substantial technological difficulties when operating effectively at supersonic speeds. The present study’s main objective is to analyse a dual-strut and cavity-based model of a scramjet combustor in order to boost its effectiveness. To analyse the intricate flow and combustion processes that occur inside the scramjet combustor, the study employs a high-fidelity CFD technique. To precisely depict the complicated features of supersonic combustion, a two-dimensional, compressible Reynolds averaged Navier-Stokes solver with turbulence modelling is used. By including the struts and cavities in the design, various modifications are made to the standard DLR model, and the flow is then analysed. In the current simulations, the air velocity at the strut and species fraction at the outlet of the combustor are primarily observed, which aids in understanding of the mixing time and combustion efficiency of the combustor. The dual strut with cavity creates the recirculation region that could enhance the fuel air mixing of the combustor. The distribution of hydrogen in the lateral direction of the flow is improved by the shock wave interaction from the cavity compared to the baseline strut design. The findings of the present study advance our understanding of scramjet combustor performance and offer insightful information for upcoming design advancements.