Electric machine and accessory gearbox arrangement for aircraft propulsion system

An assembly for an aircraft, comprising:

• a turbine engine core including a flowpath, a compressor section, a combustor section, a turbine section, a first rotating structure and a second rotating structure, the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath, the first rotating structure comprising a first bladed rotor configured to rotate about an axis, and the second rotating structure comprising a second bladed rotor configured to rotate about the axis;
• an engine case housing the turbine engine core;
• a first gearbox mounted with to the engine case;
• a second gearbox mounted with to the engine case;
• a first electric machine operatively coupled to the first rotating structure through the first gearbox, the first electric machine disposed axially adjacent the first gearbox along the axis;
• and
• a second electric machine operatively coupled to the second rotating structure through the second gearbox, the second electric machine disposed axially adjacent the second gearbox along the axis;
• wherein the second gearbox is axially aligned with the first gearbox along the axis.

An assembly for an aircraft, comprising:

• an open propulsor rotor;
• a turbine engine core configured to drive rotation of the open propulsor rotor about an axis, the turbine engine core including a first rotating structure and a second rotating structure, the first rotating structure comprising a first bladed rotor, and the second rotating structure comprising a second bladed rotor;
• an engine case housing the turbine engine core;
• a first gearbox mounted to the engine case;
• a second gearbox mounted to the engine case, the second gearbox structurally and operable independent of the first gearbox;
• a first electric machine operatively coupled to the first rotating structure through the first gearbox;
• and
• a second electric machine operatively coupled to the second rotating structure through the second gearbox;
• wherein the second gearbox is axially offset from the first gearbox along the axis.