The invention relates to a gas turbine (1) having a combustion chamber arrangement and a turbine chamber (2) connected downstream of said combustion chamber arrangement, wherein the combustion chamber arrangement includes a plurality of individual combustion chambers (3) formed by input areas (4) and transition areas (5) converging in an annular gap leading to the turbine chamber and wherein the longitudinal axes (B) of the individual combustion chambers are placed at an angle relative to an engine axis (M) that is defined by the axial extension of the turbine chamber (2). In order to improve said gas turbine by visibly reducing the thermal and mechanical loads of the individual combustion chambers in the transition area so that cooling requirements can be lowered in said area, the transition area (5) of at least one individual combustion chamber (3) and a corresponding input area (9) of the turbine chamber (2) are embodied in such a way that the gas flow running from the at least one individual combustion chamber (3) into the turbine chamber (2) is deflected in the direction of the engine axis (M) and substantially in the input area (9) of the turbine chamber (2).