Computational study of the impact of chosen geometry parameters on stability of recirculation zone in GTD-350 gas turbine combustor

The aim of this paper is to evaluate the impact of modifications of selected geometric parameters on the formation of the main recirculation zone in the combustion chamber of GTD-350 turbine engine. Changes were evaluated based mainly on the swirl number as a non-dimensional criterion to characterize the amount of rotation imparted to the axial flow. Geometric modifications include the changes in the angle of swirler vanes, as well as the changes in the position of holes along an axis of the chamber and its diameter. Moreover, a special modification which would cause an additional angular momentum of air flowing through the hole inlets on the outer side of the combustor liner has been proposed. This modification will improve the mixing process in the primary zone and may reduce the temperature pulsation of exhaust gas. The study presents 3-D numerical simulations of aerodynamic flow inside a GTD-350 turbine engine combustion chamber. The process of generating a numerical grid, determining boundary conditions and their properties are also described.