A generator system (18) comprises an inner generator rotor (34), an outer generator rotor (36), and a stator (38). The inner rotor is mounted on a first shaft (20) rotating at a first speed, while the outer rotor is mounted on a second shaft (28) coaxial w...

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 fan (11) for especially an aviation gas turbine engine has a supplementary rotor (18) positioned upstream of the fan rotor (13) with blades (19) which extend radially outwards from a hub and finish at a distance from the outer wall (16) of the fan flow...