Gas turbine engine

A gas turbine engine, comprising a compressor with a compressed air cooler between stages and a turbine with a heat recuperator for exhaust gases, characterized by the fact that the air cooler is formed by a set of parallel tubes joined at both ends to a first flange and uniformly distributed so as to form a hollow body in the inner part of which the heat recuperator is housed, said heat recuperator being formed by a set of parallel tubes joined at both ends to a second flange, both flanges being joined to each other and to the body of the engine, the compressor and the turbine comprising a shell assembly having plural shells arranged one within the other and fixed to the body of the engine, said shells forming the diffusers of the compression stages with their free ends supported on the flanges of the heat exchangers and hermetically closing the different compressed air chambers therein, each annular space so described coinciding with the corresponding inlet and outlet areas of compressed air in the cooler and in the heat recuperator, and housed within said shell assembly are:

• a distribution chamber for combustion gases connected to a flame tube, turbine nozzles, and a rotor assembly formed by the rotors of the compressor and of the turbine assembled on a single shaft and coupled to an output shaft by means of a reduction gear box joined to the body of the engine.