Computational study of an aerodynamic flow through a micro-turbine engine combustor

The study presents 3-D numerical simulations of aerodynamic flow inside a micro-turbine engine combustion chamber. The process of generating a numerical grid and its properties are described, and boundary conditions were determined on the basis of gas-dynamic calculation of the theoretical engine cycle. For the assumed boundary conditions, numerical simulations were performed of the aerodynamics of "cold" air flow through the combustion chamber (without fuel supply to the interior). A numerical experiment was also conducted which allowed the influence of the thermal energy supply into the combustion chamber on the aerodynamic flow through the chamber to be investigated. The work ends with a discussion of the results, in particular concerning the loss of pressure in the combustion chamber and possible design changes to minimize them.