Aircraft propulsion system with auxiliary drive unit

An assembly for an aircraft propulsion system, comprising:

• an engine core including a compressor section, a combustor section, a turbine section, a flowpath and a first rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section, and the first rotating structure comprising a first turbine rotor disposed in the turbine section;
• a drive unit comprising at least one of an electric machine or an air turbine;
• a first propulsor rotor;
• a second propulsor rotor;
• and
• a first clutch, the first rotating structure operatively coupled to the first propulsor rotor through the first clutch, the first rotating structure operatively coupled to the second propulsor rotor independent of the first clutch, and the drive unit operatively coupled to the first propulsor rotor independent of the first clutch.

An assembly for an aircraft propulsion system, comprising:

• an engine core including a compressor section, a combustor section, a turbine section, a flowpath and a first rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section, and the first rotating structure comprising a first turbine rotor disposed in the turbine section;
• a drive unit comprising at least one of an electric machine or an air turbine;
• a first propulsor rotor;
• a second propulsor rotor;
• and
• a first clutch, the drive unit operatively coupled to the first propulsor rotor through the first clutch, and the first rotating structure operatively coupled to the first propulsor rotor and the second propulsor rotor independent of the first clutch, wherein the first rotating structure and the first propulsor rotor are configured to rotate at a common rotational speed.

An assembly for an aircraft propulsion system, comprising:

• an open propulsor rotor comprising a rotor base and a plurality of propulsor blades, the open propulsor rotor configured to rotate about an axis;
• the rotor base including a hub, a nose cone and a plurality of air compression passages, the nose cone projecting axially along the axis out from the hub to a forward tip end of the rotor base, the plurality of air compression passages arranged circumferentially about the axis in an array and located radially inboard of an outer periphery of the hub, and the plurality of air compression passages projecting axially through the nose cone and the hub;
• and
• the plurality of propulsor blades arranged circumferentially about the rotor base in an array, the plurality of propulsor blades mounted to the hub, and the plurality of propulsor blades projecting radially out from the outer periphery of the hub into an environment external to the aircraft propulsion system.