Aircraft propulsion system engine with multiple independent rotating structures

A turbine engine, comprising:

• a first rotating assembly including a propulsor rotor and a power turbine rotor configured to drive rotation of the propulsor rotor;
• an engine core, the engine core comprising a first core rotating structure including a first compressor rotor, a second core rotating structure including a second compressor rotor and a turbine rotor, a combustor, and a flowpath extending sequentially across the first compressor rotor, the second compressor rotor, the combustor and the turbine rotor;
• an electric machine configured to drive rotation of the first core rotating structure, the electric machine disposed axially between the first compressor rotor and the second core rotating structure,
• an accessory gearbox coupling a second electric machine to the first rotating assembly;
• and
• a geartrain coupling the propulsor rotor to the power turbine rotor;
• wherein the first rotating assembly does not extend axially through the first core rotating structure or the second core rotating structure;
• wherein the first core rotating structure does not extend axially through the second core rotating structure, and the first core rotating structure is mechanically independent of the second core rotating structure;
• wherein the geartrain is disposed axially between and spaced from the accessory gearbox and the propulsor rotor;
• wherein the accessory gearbox is axially forward of the power turbine rotor;
• and
• wherein the propulsor rotor is axially between a forward upstream end of the turbine engine and the engine core.