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

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