In a gas turbine combustion chamber which surrounds the rotor as an annulus and therefore has the shape of an annular combustion chamber, the front wall (10) is equipped with a number of burners whose ends occupy a uniform plane. These burners form a double ring (10b, 10c) on the front wall (10). In each ring, the same direction of rotation is present in the burners and this is opposite to the adjacent ring. In addition, two burners at a time are alternately displaced outwards and inwards in each ring in order to achieve a favorable flow field for combustion. The number of burners on the front wall (10) is divided into a larger quantity of piloting burners (A1, A2 ) and a smaller quantity of piloted burners (B1, B2).