An aircraft electrical network including a first starter generator mechanically coupled to a first shaft of an aircraft main engine. The first starter generator is configured to turn the first shaft of the main engine in a starting mode, and to generate electricity from the first shaft of the gas tu
An aircraft electrical network including a first starter generator mechanically coupled to a first shaft of an aircraft main engine. The first starter generator is configured to turn the first shaft of the main engine in a starting mode, and to generate electricity from the first shaft of the gas turbine engine in a generating mode. The network further includes a DC electrical bus electrical coupled to one or more electrical loads and an AC electrical bus electrically coupled to the first starter generator. The DC electrical bus is electrically coupled to the AC electrical bus via a bi-directional AC/DC converter, which is configured to provide AC electrical power from the DC electrical bus to power the first starter generator when the first starter generator is in a starting mode, and DC electrical power to the DC electrical bus when the first starter generator is in a generating mode.
대표청구항▼
1. An aircraft comprising a main engine, a network controller, and an electrical network, the electrical network comprising: a first starter generator mechanically coupled to a first shaft of the main engine, the first starter generator being configured to turn the first shaft of the main engine whe
1. An aircraft comprising a main engine, a network controller, and an electrical network, the electrical network comprising: a first starter generator mechanically coupled to a first shaft of the main engine, the first starter generator being configured to turn the first shaft of the main engine when operated in a starting mode, and to generate electricity from the first shaft of the main engine when operated in a generating mode, the generating mode including a normal generating mode and a fuel saving generating mode;a further electrical generator mechanically coupled to a further shaft of the main engine;a DC electrical bus electrically coupled to one or more electrical loads; andan engine AC electrical bus comprising one or more engine electrical loads and an aircraft AC electrical bus comprising one or more aircraft electrical loads, each of the engine AC electrical bus and the aircraft AC electrical bus being electrically coupled to the first starter generator and the further electrical generator;wherein: the DC electrical bus is electrically coupled to one of the AC electrical buses via a bi-directional AC/DC converter;the bi-directional AC/DC converter is configured to provide AC electrical power from the DC electrical bus to power the first starter generator when the first starter generator is in the starting mode, and DC electrical power to the DC electrical bus when the first starter generator is in the generating mode; andthe network controller is configured to control electrical power provided to the engine electrical loads and the aircraft electrical loads from each of the first starter generator and the further electrical generator, and to control the power provided to at least the first starter generator from the DC electrical bus, the network controller being further configured to operate the electrical network in the normal generating mode in which the further electrical generator provides all AC electrical power for the engine electrical loads and the first starter generator provides all AC electrical power for the aircraft electrical loads, and the fuel-saving generating mode in which the further electrical generator provides at least part of the electrical power for each of the aircraft electrical loads and engine electrical loads and the first starter generator provides the balance of electrical power for the aircraft electrical loads. 2. The aircraft according to claim 1, wherein the electrical network comprises a plurality of main engines, each being electrically coupled to a respective DC electrical bus, engine AC electrical bus, aircraft AC electrical bus, and bi-directional AC/DC converter. 3. The aircraft according to claim 1, wherein the electrical network comprised an AC interconnector connecting the aircraft AC electrical bus to the engine AC electrical bus. 4. The aircraft according to claim 1, wherein the electrical network comprises an energy storage device electrically coupled to the DC electrical bus. 5. The aircraft according to claim 1, wherein the main engine comprises a gas turbine engine having a high pressure shaft and one or more further shafts. 6. The aircraft according to claim 5, wherein the first starter generator is mechanically coupled to the high pressure shaft. 7. The aircraft according to claim 1, wherein the further electrical generator is electrically coupled to a further AC to DC converter to provide DC electrical power to the DC electrical bus. 8. The aircraft according to claim 3, wherein the further electrical generator is electrically coupled to the bi-directional AC/DC converter via the AC interconnector to provide AC electrical power to the bi-directional AC/DC converter. 9. The aircraft according to claim 1, wherein the DC electrical bus provides DC electrical power to one or more AC motor controllers, which motor controllers are configured to provide AC electrical power to a respective AC motor. 10. The aircraft according to claim 9, wherein the bi-directional AC/DC converter is electrically coupled to one or more AC motors to provide AC electrical power to the one or more coupled AC motors. 11. The aircraft according to claim 1, wherein the controller is configured to switch between the normal and fuel-saving generating modes on the basis of a determination that operation in a respective mode will result in a reduced fuel flow compared to operation in the other mode. 12. The aircraft according to claim 11, wherein the determination that operation in the respective mode will result in the reduced fuel flow is made on the basis of one or more of a predetermined engine shaft rotation speed, spare electrical generating capacity in the further electrical generator and an engine shutdown condition. 13. The aircraft according to claim 1, wherein the controller is configured to operate the electrical network in the starting mode, wherein the aircraft and engine electrical loads are provided by the further generator and/or an auxiliary power source. 14. The aircraft according to claim 1, wherein the further generator comprises a starter generator configured to turn the further shaft of the main engine when operated in the starting mode, and to generate electricity from the further shaft of the main engine when operated in the generating mode. 15. The aircraft according to claim 14, wherein the controller is configured such that, when the electrical network is in the starting mode, the further starter generator is first operated in the starting mode to turn the further shaft, and the first starter generator is then operated in the starting mode to turn the first shaft.
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이 특허에 인용된 특허 (2)
Bansal Madan L. (Rockford IL) Vaidya Jayant G. (Rockford IL), Dual output synchronous-induction starting/generating system.
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