Abstract: A low-emission combustion chamber for gas turbine engines comprises an outer casing with an upstream end wall with a pilot fuel injector, a first flow swirler, an igniting members for initiating a stable diffusion frame in a pilot zone, at least one second coaxial swirler, main fuel injectors, secondary air inlets, and a main combustion zone. For obtaining a still further reduced emissions of primarily nitrogen oxides, the pilot zone is confined radially outwardly by a surrounding wall which constitutes the radially inner confinement of an axial outlet portion of a radial vaporization channel within the second swirler and a third radial flow swirler is adapted to supply the secondary air in a rotary motion opposite to that of the main flow of fuel and air.