Résumé:
This thesis presents a numerical investigation of supersonic combustion within a scramjet combustor
featuring a double parallel cavity geometry, analyzed across varying inlet Mach numbers.
Using ANSYS Fluent, the study solves the Reynolds-averaged Navier-Stokes (RANS)
equations with the standard k–epsilon turbulence model to capture turbulent flow behavior. A
finite-rate/eddy dissipation model is employed to simulate the chemical kinetics of combustion.
The research focuses on how the double parallel cavity configuration affects flame stabilization,
fuel-air mixing, and combustion efficiency at different supersonic flow conditions.
Comparative analysis of results at various Mach numbers provides insights into optimizing
combustor design and operating parameters for enhanced scramjet performance.
Model validation is achieved by comparing simulation outcomes with experimental data
to ensure accuracy and reliability. This work contributes to the advancement of supersonic
combustion understanding and supports the development of more efficient propulsion systems
for high-speed aerospace applications.
