Integrated electrical power extraction for aircraft engines
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H02P-009/00
F02C-001/06
F02C-001/00
출원번호
UP-0256691
(2008-10-23)
등록번호
US-7605483
(2009-11-10)
발명자
/ 주소
Kern, John Michael
Wiegman, Herman Lucas Norbert
출원인 / 주소
General Electric Company
대리인 / 주소
Clarke, Penny A.
인용정보
피인용 횟수 :
16인용 특허 :
13
초록▼
An aircraft power system includes an aircraft engine having a plurality of engine spools, a plurality of AC generators driven by at least one spool, wherein each AC generator is independently operational to supply AC power to a respective AC power bus or a respective power electronics module, and at
An aircraft power system includes an aircraft engine having a plurality of engine spools, a plurality of AC generators driven by at least one spool, wherein each AC generator is independently operational to supply AC power to a respective AC power bus or a respective power electronics module, and at least one generator driven by a different engine spool, wherein the at least one generator is operational to supply additional AC power to each AC power bus in synchronization with each respective AC generator, or to supply additional AC power to each power electronics module in parallel with the AC power delivered to each power electronics module by the plurality of AC generators. The power electronics module(s) are operational to selectively provide either AC or DC power to desired distribution buses. Each AC generator and the at least one generator may be responsive to commands from an electrical power extraction (EPX) controller. At least one generator may be directly driven to provide variable frequency power.
대표청구항▼
We claim: 1. A method of providing aircraft power, the method comprising the steps of: driving a plurality of generators via an aircraft engine spool such that each generator provides AC power to a respective AC bus; driving at least one generator via a different engine spool to selectively provide
We claim: 1. A method of providing aircraft power, the method comprising the steps of: driving a plurality of generators via an aircraft engine spool such that each generator provides AC power to a respective AC bus; driving at least one generator via a different engine spool to selectively provide additional AC power to each respective AC bus; and controlling the at least one generator to selectively synchronize the additional AC power generated via the at least one generator with the AC power generated via the plurality of generators. 2. The method of claim 1, further comprising the step of controlling the at least one generator to pick-up or shed loads supplied via at least one AC generator to selectively load the engine spools. 3. The method of claim 1, wherein the step of controlling the at least one generator comprises transmitting commands via an electrical power extraction (EPX) controller to a plurality of generator power electronics (PE) modules, wherein each PE module is associated with a respective AC bus. 4. The method of claim 3, further comprising the step of transmitting commands via an engine control unit to the EPX controller in response to desired engine parameters selected from fuel efficiency parameters, transient performance parameters, and stall margin parameters. 5. The method of claim 3, wherein the step of transmitting commands via an engine control unit comprises transmitting commands via a full authority digital engine controller (FADEC). 6. The method of claim 1, wherein the step of driving a plurality of generators comprises driving the plurality of generators to selectively generate wild AC power or constant AC power. 7. The method of claim 1, wherein the step of driving at least one generator comprises driving the at least one generator to selectively generate wild AC power or constant AC power. 8. An aircraft power system comprising: an aircraft engine; a plurality of AC generators driven by the aircraft engine, wherein each AC generator is independently operational to supply AC power to a respective AC power bus in response to commands from an electrical power extraction (EPX) controller ; and at least one generator driven by the aircraft engine, wherein the at least one generator is operational to selectively supply additional AC power to each AC power bus in synchronization with each respective AC generator in response to commands from the EPX controller. 9. The aircraft power system according to claim 8, further comprising an engine controller selected from an electronics engine controller (EEC) and a full authority digital engine controller (FADEC), wherein the engine controller transmits commands to the EPX controller in response to desired engine parameters. 10. The aircraft power system according to claim 9, wherein the desired engine parameters are selected from fuel efficiency parameters, transient performance parameters, and stall margin parameters, to selectively load aircraft engine spools. 11. The aircraft power system according to claim 8, wherein at least one generator is a directly driven generator. 12. A method of providing aircraft power, the method comprising the steps of: driving a plurality of generators via an aircraft engine spool such that each generator provides AC power to a respective power electronic system; driving at least one generator via a different engine spool to selectively provide additional AC power to each power electronics system; and controlling the at least one generator to selectively supply additional AC power to each power electronics system in parallel with each respective AC generator. 13. The method of claim 12, further comprising the step of controlling the at least one generator to pick-up or shed loads supplied via the plurality of generators to selectively load the engine spools. 14. The method of claim 13 wherein the step of controlling the at least one generator comprises transmitting commands via an electrical power extraction (EPX) controller to the power electronics modules, wherein each power electronics module is associated with a respective power bus. 15. The method of claim 14, further comprising the step of transmitting commands via an engine control unit to the EPX controller in response to desired engine parameters selected from fuel efficiency parameters, transient performance parameters, and stall margin parameters. 16. The method of claim 15, wherein the step of transmitting commands via an engine control unit comprises transmitting commands via a full authority digital engine controller (FADEC). 17. The method of claim 12, wherein the step of driving a plurality of generators comprises directly driving the plurality of generators to selectively generate wild AC power or constant AC power. 18. The method of claim 12, wherein the step of driving at least one generator comprises driving the at least one generator to selectively generate wild AC power or constant AC power.
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