Gas turbine engine electrical generator

A gas turbine engine for an aircraft, the gas turbine engine comprising:

• a main engine shaft comprising a radially inner portion joined to a radially outer portion separated by an annular space;
• a main engine shaft bearing arrangement configured to rotatably support the main engine shaft;
• and
• an electric machine comprising a rotor and a stator;
• wherein:
• the rotor is mounted to the radially outer portion of the main engine shaft and is rotatably supported by an electric machine bearing arrangement extending between the rotor and the stator,
• the stator is mounted to a static structure of the gas turbine engine by a stator mount member extending rearward or forward from the static structure to the stator,
• the radially outer portion comprises a flexible bellows arrangement configured to permit movement between the radially inner portion and the radially outer portion of the main engine shaft in use, and
• the flexible bellows arrangement comprises a lower stiffness relative to the stator mount member.