.A model of an idealized CAN type gas turbine combustion chamber is chosen to familiarize users with STAR-CCM+'s combustion modeling capabilities and introduce various recommended practices for simulating combusting flows.
The problem geometry (shown below) consists of three sets of air inlets placed circumferentially at the combustor head to promote maximum mixing and flame stabilization. Swirling air enters the primary combustion zone through the two sets of inlets nearest to the axis of symmetry. Non-swirling air enters the upper inlet and thence the primary, secondary and dilution zones via five injection holes in the baffle.
Air is assumed to be composed of 23.3% oxygen and 76.7% nitrogen, by mass, and its initial pressure and temperature are 1 bar and 293 K, respectively.
The use of periodic interfaces allows the cylindrical combustor to be represented by a single sixty-degree sector, reducing the computational effort required by a factor of roughly .
The combustion models illustrated using the above geometry are: