# US 12,006,051 B2 · Electrical power system for a vehicle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,051 B2 - Document ID: US12006051B2 - Status: Granted - Kind: B2 - Application number: 17/730,683 - Filed: 2022-04-27 - Published: 2023-11-02 - Granted: 2024-06-11 - Earliest claimed: 2022-04-27 - Assignees: General Electric Company; General Electric Deutschland Holding GmbH - Applicants: General Electric Company; General Electric Deutschland Holding GmbH - Inventors: Satish Prabhakaran; Mohamed Osama - Web page: https://patentgrep.com/patent/US12006051B2 ## CPC - F02C 3/113: with variable power transmission between rotors - B64D 27/12: within, or attached to, wings - B64D 29/02: associated with wings - B64D 31/18: for hybrid-electric power plants - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F02K 5/00: Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan - B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)} - B64D 2221/00: Electric power distribution systems onboard aircraft - F02K 3/06: with front fan - F05D 2220/76: an electrical generator - F05D 2260/40: Transmission of power - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A vehicle includes a gas turbine engine having at least two spools and an associated power system. The power system includes two independent power subsystems, including a first power subsystem for managing power transfer between spools and a second power subsystem for supplying a base power load to the vehicle. The first power subsystem has a first electric machine mechanically coupled with a first spool of the gas turbine engine and a second electric machine mechanically coupled with a second spool. The second electric machine is electrically coupled with the first electric machine such that electrical power is transmittable therebetween. The second power subsystem has a third electric machine mechanically coupled with one of the spools. The third electric machine is electrically coupled with a load positioned offboard the gas turbine engine. The first power subsystem and the second power subsystem are electrically decoupled from one another. ## Claims ### Claim 1 An aircraft, comprising: a fuselage; a wing extending from the fuselage; a gas turbine engine mounted to the wing or to the fuselage, the gas turbine engine having a high pressure spool and a low pressure spool; one or more electrical loads positioned offboard the gas turbine engine; and a power system associated with the gas turbine engine, the power system comprising: a first power subsystem having a first electric machine mechanically coupled with the high pressure spool and a second electric machine mechanically coupled with the low pressure spool, the second electric machine being electrically coupled with the first electric machine such that electrical power is transmittable therebetween; and a second power subsystem having a third electric machine mechanically coupled with the high pressure spool, the third electric machine being electrically coupled with the one or more electrical loads such that electrical power is transmittable therebetween, wherein the first power subsystem and the second power subsystem are electrically decoupled from one another. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein the gas turbine engine defines an axial direction, and wherein the second electric machine is positioned aft of both the first electric machine and the third electric machine along the axial direction. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the gas turbine engine has a combustion section and defines an axial direction, and wherein the first electric machine is positioned forward of the combustion section along the axial direction, and the second electric machine and the third electric machine are positioned aft of the of the combustion section along the axial direction. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein the first power subsystem has a first power converter electrically connected to the first electric machine and a second power converter electrically connected to the second electric machine. ### Claim 5 (depends on 4) The aircraft of claim 4, wherein the first power converter and the second power converter are co-located. ### Claim 6 (depends on 4) The aircraft of claim 4, wherein the first power converter and the second power converter are spaced from one another and are electrically coupled with one another by a DC bus. ### Claim 7 (depends on 1) The aircraft of claim 1, wherein the first power subsystem has a first power converter electrically connected to the first electric machine and a second power converter electrically connected to the second electric machine, the first power converter being electrically coupled with the second power converter via a bus, and wherein a nacelle of the gas turbine engine is mounted to the wing via a pylon, and wherein the one or more electrical loads are positioned offboard the nacelle and the pylon. ### Claim 8 (depends on 7) The aircraft of claim 7, wherein the first power converter and the second power converter are positioned onboard the fuselage. ### Claim 9 (depends on 8) The aircraft of claim 8, wherein a first line electrically connects the first electric machine with the first power converter and a second line electrically connects the second electric machine with the second power converter, a first contactor being disposed along the first line and being positioned onboard the fuselage and a second contactor being disposed along the second line and being positioned onboard the fuselage. ### Claim 10 (depends on 1) The aircraft of claim 1, further comprising: a second wing extending from the fuselage; a second gas turbine engine mounted to the second wing or to the fuselage, the second gas turbine engine having at least two spools; and a second power system associated with the second gas turbine engine, the second power system comprising: a first power subsystem having a first electric machine mechanically coupled with a first spool of the at least two spools of the second power system and a second electric machine mechanically coupled with a second spool of the at least two spools of the second power system, the second electric machine of the second power system being electrically coupled with the first electric machine of the second power system such that electrical power is transmittable therebetween; and a second power subsystem having a third electric machine mechanically coupled with one of the at least two spools of the second power system, the third electric machine of the second power system being electrically coupled with the one or more electrical loads such that electrical power is transmittable therebetween, wherein the first power subsystem and the second power subsystem of the second power system are electrically decoupled from one another. ### Claim 11 (depends on 1) The aircraft of claim 1, wherein the first electric machine and the third electric machine are co-axially mounted to and rotatable with the high pressure spool. ### Claim 12 A power system associated with a gas turbine engine mounted to an aircraft, the power system comprising: a first power subsystem having a first electric machine mechanically coupled with a high pressure spool of the gas turbine engine and a second electric machine mechanically coupled with a low pressure spool of the gas turbine engine, the second electric machine being electrically coupled with the first electric machine such that electrical power is transmittable therebetween; and a second power subsystem having a third electric machine mechanically coupled with the high pressure spool, the third electric machine being electrically coupled with one or more electrical loads positioned offboard the gas turbine engine, and wherein the first power subsystem and the second power subsystem are electrically decoupled from one another. ### Claim 13 A method of power transmission for an aircraft, comprising: transferring, by a first power subsystem, power between a high pressure spool and a low pressure spool of a gas turbine engine by transmitting electrical power generated by a first electric machine mechanically coupled with the high pressure spool to a second electric machine mechanically coupled with the low pressure spool; and transmitting, by a second power subsystem, electrical power generated by a third electric machine mechanically coupled with the high pressure spool to one or more loads positioned offboard the gas turbine engine, and wherein the first power subsystem and the second power subsystem are electrically decoupled from one another.