The aerodynamics of combustion chambers for aeronautical engines is studied by means of a compressible Navier-Stokes solver without chemical reactions. The three-dimensional (3-D) code is designed for the simulation of complex geometries by introducing non orthogonal curvilinear coordinates. The implicit solver, which is based on the scalar approximate factorization method, accounts for turbulence effects by using a zero-equation turbulence model and solves in terms of primitive variables. Particular care is devoted to boundary conditions to account properly for swirl velocities and cooling air lateral holes. The code showed good flexibility and design capability for 3-D complex flow fields. The tests show that the presence of circumferential and toroidal recirculation zones can be controlled by either the inlet swirl velocity or the lateral jet holes.