Patent ID: 11970062
Assignee: GE AVIATION SYSTEMS LIMITED
Field: Transport (Mechanical engineering)
Classification: CPC B  F  H  Y | IPC B  F  H

Claim 12:
13. A method, comprising:
generating, by a first generator driven by a high pressure (HP) spool of a gas turbine engine mounted an aircraft, electric power;
generating, by a second generator driven by a low pressure (LP) spool of the gas turbine engine, electric power;
providing the electric power generated by the first generator and the second generator to a power distribution bus; and
managing a power split of electric power between one or more motors of an electric propulsion fan mounted to the aircraft and a secondary aircraft systems bus electrically coupled with one or more aircraft loads positioned offboard of the gas turbine engine, the electric power managed in the power split between the one or more motors of the electric propulsion fan and the secondary aircraft systems bus being generated by the first generator and the second generator and provided to the power distribution bus, wherein power generated by the first generator and power generated from the second generator is delivered from the power distribution bus to the one or more motors for driving the fan and to the secondary aircraft system bus;
wherein in managing the power split:
a propulsion system controller (PSC) controls a first power converter electrically coupled with the first generator and the power distribution bus, a second power converter electrically coupled with the second generator and the power distribution bus, and a third power converter electrically coupled with the one or more motors and the power distribution bus to allocate electric power generated by the first generator and the second generator to the one or more motors in accordance with the power split;
a bus power control unit (BPCU) controller communicatively coupled with the PSC controls a fourth power converter electrically coupled with the secondary aircraft systems bus and the power distribution bus to allocate electric power generated by the first generator and the second generator to the secondary aircraft systems bus in accordance with the power split; and
wherein the PSC and/or the BPCU controller are configured to control a fifth power converter to allocate auxiliary electric power generated by an auxiliary power unit to supplement the electric power supplied by the first generator and the second generator to the one or more motors of the electric propulsion fan and the secondary aircraft systems bus in accordance with the power split.