Hybrid-electric aircraft propulsion system

An aircraft propulsion system comprising:

• a gas turbine engine including a high-pressure (HP) spool and a low-pressure (LP) spool;
• and
• an electrical system including a consolidated electric machine and a drive train,
• the consolidated electric machine including a first electric machine rotor and a second electric machine rotor, the first electric machine rotor and the second electric machine rotor concentric and rotatable about an electric machine rotational axis of the consolidated electric machine, and
• the drive train coupling the HP spool with the first electric machine rotor and coupling the LP spool with the second electric machine rotor, the drive train including a first tower shaft, a first drive shaft, an accessory gear box, and a first angled gear box, the first tower shaft coupled with the HP spool, the first tower shaft rotatable about a first tower shaft rotational axis transverse to the electric machine rotational axis, the first drive shaft operably coupled with the first electric machine rotor, the first drive shaft rotatable about a first drive shaft axis, the first drive shaft disposed within the accessory gear box, the accessory gear box including a gear box housing having the consolidated electric machine mounted thereon, the first angled gear box including a first angled gear assembly coupling the first tower shaft with the first drive shaft.

An aircraft propulsion system comprising:

• a gas turbine engine including a high-pressure (HP) spool and a low-pressure (LP) spool;
• and
• an electrical system including a consolidated electric machine and a drive train,
• the consolidated electric machine including an inner electric machine rotor and an outer electric machine rotor, the inner electric machine rotor and the outer electric machine rotor concentric and rotatable about an electric machine rotational axis of the consolidated electric machine, the outer electric machine rotor disposed radially outward of the inner electric machine rotor relative to the electric machine rotational axis, and
• the drive train coupling the HP spool with the inner electric machine rotor, the drive train configured to couple the LP spool with the outer electric machine rotor, the drive train including a first tower shaft, a first drive shaft, a first angled gear box, a second tower shaft, and a second drive shaft, the first tower shaft coupled with the HP spool, the first tower shaft rotatable about a first tower shaft rotational axis, the first drive shaft operably coupled with the inner electric machine rotor, the first drive shaft rotatable about a first drive shaft axis transverse to the first tower shaft rotational axis, the first angled gear box including a first angled gear assembly coupling the first tower shaft with the first drive shaft, the second tower shaft coupled with the LP spool, the second tower shaft rotatable about a second tower shaft rotational axis, the second drive shaft operably coupled with the second tower shaft and the outer electric machine rotor, the second drive shaft rotatable about a second drive shaft rotational axis transverse to the second tower shaft rotational axis.