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

Claim 0:
1. An electrical system for an aircraft having a gas turbine engine that includes a high pressure (HP) spool and a low pressure (LP) spool, the electrical system comprising:
a power distribution bus;
a first generator driven by the HP spool, the first generator being electrically coupled with the power distribution bus;
a second generator driven by the LP spool, the second generator being electrically coupled with the power distribution bus;
an electric propulsion fan having a fan and one or more motors for driving the fan, the one or more motors being electrically coupled with the power distribution bus;
a secondary aircraft systems bus electrically coupled with one or more aircraft loads, the secondary aircraft systems bus also being electrically coupled with the power distribution bus; and
a control system 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 generator;
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 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 systems 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.