Selective power distribution for an aircraft propulsion system

An assembly for an aircraft, comprising:

• a rotating structure comprising a turbine rotor;
• an epicyclic gear system including a sun gear, a ring gear and a plurality of intermediate gears, the sun gear rotatably driven by the rotating structure, and each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear;
• a carrier rotatably supporting each of the plurality of intermediate gears;
• a first propulsor rotor coupled to the ring gear;
• a second propulsor rotor coupled to the carrier;
• and
• an electric machine coupled to the first propulsor rotor and the second propulsor rotor through the epicyclic gear system, wherein the assembly is configured to at least one of
• stop rotation of the first propulsor rotor using the electric machine while the second propulsor rotor continues to rotate;
• or
• stop rotation of the second propulsor rotor using the electric machine while the first propulsor rotor continues to rotate.

An assembly for an aircraft, comprising:

• a rotating structure comprising a turbine rotor;
• an epicyclic gear system including a sun gear, a ring gear and a plurality of intermediate gears, the sun gear rotatably driven by the rotating structure, and each of the plurality of intermediate gears between and meshed with the sun gear and the ring gear;
• a carrier rotatably supporting each of the plurality of intermediate gears;
• a first propulsor rotor coupled to the ring gear;
• a second propulsor rotor coupled to the carrier;
• and
• a lock system configured to at least one of
• lock rotation of the ring gear about a centerline axis during a second propulsor mode of operation;
• or
• lock rotation of the carrier about the centerline axis during a first propulsor mode of operation.