Hybrid aircraft propulsion system

An apparatus for an aircraft, comprising:

• a turbine engine including a compressor section, a combustor section, a turbine section, a support structure, a first rotor system, a second rotor system and an electrical system;
• the support structure extending axially along an axis through the first rotor system and the second rotor system;
• the first rotor system including an electric motor and a first bladed rotor, the electric motor attached to the support structure and configured to drive rotation of the first bladed rotor about the axis, and the first bladed rotor circumscribing the electric motor;
• the second rotor system including an electric generator and a second bladed rotor, the electric generator attached to the support structure and configured to be mechanically powered by rotation of the second bladed rotor about the axis, and the second bladed rotor circumscribing the electric generator;
• and
• the electrical system electrically coupled to the electric motor and the electric generator.

An apparatus for an aircraft, comprising:

• an aircraft propulsion system including a compressor section, a combustor section, a turbine section, flowpath, a first rotor system, a second rotor system, a first controller and a second controller;
• the flowpath extending through the compressor section, the combustor section and the turbine section;
• the first rotor system including a first electric machine and a first bladed rotor disposed in a section of the aircraft propulsion system, the first electric machine configurable as at least one of an electric motor or an electric generator, the first electric machine operatively coupled to the first bladed rotor, and the first bladed rotor circumscribing the first electric machine and configured to rotate about an axis;
• the second rotor system including a second electric machine and a second bladed rotor disposed in the section of the aircraft propulsion system, the second electric machine configurable as at least one of an electric motor or an electric generator, the second electric machine operatively coupled to the second bladed rotor, the second bladed rotor circumscribing the second electric machine and axially next to the first bladed rotor, and the second bladed rotor configured to rotate about the axis mechanically independent of the first bladed rotor;
• the first controller configured to control operation of the first electric machine;
• and
• the second controller configured to control operation of the second electric machine.