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

Claim 6:
7. An aircraft, comprising:
a gas turbine engine that includes a high pressure (HP) spool, a low pressure (LP) spool, a first generator driven by the HP spool, and a second generator driven by the LP spool;
an electric propulsion fan having a fan and one or more motors for driving the fan;
one or more aircraft loads;
a secondary aircraft systems bus electrically coupled with the one or more aircraft loads;
a power distribution bus, the one or more motors, the first generator, the second generator, and the secondary aircraft systems bus being electrically coupled with the power distribution bus, wherein power generated by the first generator and power generated from the second generator is provided via the power distribution bus to the one or more motors for driving the fan and the secondary aircraft systems bus; and
a control system having one or more processors configured to:
manage a power split of electric power between the one or more motors of the electric propulsion fan and the secondary aircraft systems bus, 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 generators;

a propulsion system controller (PSC);
a bus power control unit (BPCU) controller communicatively coupled with the PSC;
an auxiliary power unit;
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;
a third power converter electrically coupled with the one or more motors and the power distribution bus;
a fourth power converter electrically coupled with the secondary aircraft systems bus and the power distribution bus;
a fifth power converter electrically coupled with the auxiliary power unit and the power distribution bus;
wherein the PSC controls the first power converter, the second power converter, and the third power converter 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;
wherein the BPCU controller controls the fourth power converter 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 the fifth power converter to allocate auxiliary electric power generated by the 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.