Patent ID: 8485783

Claim:
Gas turbine engine comprising in serial flow relationship: a first compressor provided with at least one row of compressor blades distributed circumferentially around the first compressor; a combustion chamber; and a first turbine provided with at least one row of turbine blades distributed circumferentially around the first turbine, wherein the first compressor and the first turbine are rotationally rigidly connected by a first shaft, wherein the first turbine is adapted to influence a normalized gas flow rate through the gas turbine engine depending on a rotational speed of the first turbine, wherein a turbine rotor of the first turbine is arranged directly downstream of the combustion chamber so that no stator vanes or similar gas deflecting components are arranged in a region downstream of the combustion chamber and upstream of the first turbine rotor, and the gas turbine engine further comprises means for controlling the rotational speed of the first turbine, and wherein there is no inlet stator associated with the first turbine.