A starter-generator module for a gas turbine engine includes an inner stator portion with an armature defining a rotation axis and an outer rotor portion disposed about the rotation axis. The outer rotor portion includes a permanent magnet and a gear teeth member. The permanent magnet is disposed about the rotation axis and the gear teeth member is defined on the outer rotor portion such that the gear teeth member transmits rotational energy to an accessory gearbox in a start mode and receives rotational energy from the accessory gearbox in a generate mode.

An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

An aircraft engine apparatus (1) includes: a rotating shaft (6); a fan (10) driven by the rotating shaft; a fan case surrounding the fan; aircraft equipment (28) disposed upstream of the fan and, in a radial direction of the rotating shaft, disposed inward of a peripheral edge of the fan case; a casing (2) that accommodates at least part of the rotating shaft and supports the fan case; a first motive force transmitter (9) coupled to the rotating shaft and the fan; a second motive force transmitter (32) disposed inward of the first motive force transmitter in the radial direction of the rotating shaft and coupled to the rotating shaft and the aircraft equipment; and a support member (12) disposed between the first motive force transmitter and the second motive force transmitter, the support member coupling the casing and the aircraft equipment and supporting the aircraft equipment.

A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density. The power system also includes one or more electric motors operably coupled to the hybrid energy storage system and to an aircraft engine. The power system further includes a means for controlling one or more electric power flows of the hybrid energy storage system to/from the one or more electric motors based on a modeled electric power demand associated with an engine load of one or more spools of the aircraft engine.

A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.

Provided is a gas turbine system that is used for a moving body including a thrust generator configured to generate thrust from electric power and includes: a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; a first generator that is coupled to the turbine to generate electric power by driving of the turbine and supplies electric power to the thrust generator; and a second generator that is arranged downstream of the turbine in a flow direction of a combustion gas and converts kinetic energy and/or thermal energy of a combustion gas that passed through the turbine into electric power.

Provided is a gas turbine system that is used for a moving body including a thrust generator configured to generate thrust from electric power and includes: a compressor that compresses external air to generate compressed air; a combustor that burns the compressed air generated by the compressor together with fuel to generate a combustion gas; a turbine driven by the combustion gas generated by the combustor; a first generator that is coupled to the turbine to generate electric power by driving of the turbine and supplies electric power to the thrust generator; and a second generator that is arranged downstream of the turbine in a flow direction of a combustion gas and converts kinetic energy and/or thermal energy of a combustion gas that passed through the turbine into electric power.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

A turbomachine dual spool transmission system can include a transmission assembly configured to connect to a combination output of a dual spool differential at a transmission input to be driven by the combination output to turn a transmission output. The transmission assembly can be configured to provide a first output gear ratio in a first state and a second output gear ratio in a second state. The system can include the dual spool differential. The dual spool differential can include a gear assembly configured to combine a low pressure spool input and a high pressure spool input into a combination output to provide an output speed range smaller than a low pressure speed range alone.