Electric Generator with Combined Rotors

A method comprising:

• operating a turbine engine to provide thrust to a vehicle that includes the turbine engine, wherein the turbine engine comprises:
• a core section comprising at least one compressor and at least one turbine, the at least one compressor and the at least one turbine both rotate about a longitudinal axis of the turbine engine, wherein the at least one compressor comprises an intermediate pressure compressor and a high pressure compressor;
• a fan comprising a plurality of radially distributed blades, the fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the plurality of radially distributed blades providing the thrust to the vehicle that includes the turbine engine;
• and
• an electrical generator positioned in the core section aft of the fan, wherein at least a portion of the electrical generator is positioned fore of an entirety of the intermediate pressure compressor and an entirety of the high pressure compressor, and wherein the electrical generator comprises:
• a combined rotor mechanically rotated via a mechanical connection to the at least one turbine, the combined rotor configured to rotate about the longitudinal axis and formed from a single component that incorporates a blade retainer for retaining at least one of the plurality of radially distributed blades;
• and
• a stator configured to electromagnetically interact with the combined rotor;
• and
• operating the electrical generator via the mechanical connection to the turbine engine to output power.

An aircraft comprising:

• an airframe;
• and
• a turbine engine comprising:
• a core section comprising at least one compressor and at least one turbine, the at least one compressor and the at least one turbine both rotate about a longitudinal axis of the turbine engine, wherein the at least one compressor comprises an intermediate pressure compressor and a high pressure compressor;
• a fan comprising a plurality of radially distributed blades, the fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the plurality of radially distributed blades providing thrust to the airframe;
• and
• an electrical generator integrated into a core vane assembly, wherein at least a portion of the electrical generator is positioned in the core section aft of the fan and fore of an entirety of the intermediate pressure compressor and an entirety of the high pressure compressor, and wherein the electrical generator comprises:
• a combined rotor rotationally coupled to the fan, the combined rotor configured to rotate about the longitudinal axis and formed from a single component that incorporates a blade retainer for retaining at least one of the plurality of radially distributed blades;
• and
• a stator configured to electromagnetically interact with the combined rotor.