The aircraft gas turbine engine has an engine core (10) that is surrounded by a secondary flow channel. An annular cooling element (30) is arranged in the region of a radial inner wall (21) of the secondary flow channel, corresponding to the downstream dir...

The drive shaft has a metallic, hollow output shaft (1) with a load introducing element (2) formed at the ends. The output shaft has a metal rod (3) designed as semi-finished goods for the transmission of torsion loads. A fiber composite layer is made from...

The adjustable bloom mixer (6) has an air guiding element (13) for branching a cold air flow (3) or hot air flow (9) from the bypass channel and the core flow channel of the engine. The air guiding element is arranged upstream the thin-walled, corrugated p...

The cone part has a partition wall (3) positioned between an outside cone part (1) and an inside cone part (2) for connecting the inside cone part to the outside cone part in a spaced apart manner to form an interspace between the outside cone part and the...