Abstract: A combustion chamber arrangement for a gas turbine engine which can be annular or can-annular, though the annular arrangement is preferred, comprises in the annular form, an annular combustion chamber having in its upstream end a plurality of primary air inlets with associated swirling means, such as a ring of swirl vanes and a plurality of fuel injectors located in fuel injector apertures, the fuel injectors and primary air inlets being arranged so that at least two primary air inlets are located between any two fuel injectors, the primary air all being swirled in one direction so that the fuel from one injector is sheared in opposing directions by the swirling primary air from adjacent primary air inlets. Little or no air enters the combustion chamber in the region of the fuel injectors and any air that does enter in that region is not swirled.