[특허]Aircraft, propulsion system, and system for taxiing an aircraft

Rolls-Royce Corporation

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

MyON담기

내보내기

Aircraft, propulsion system, and system for taxiing an aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-041/00
미국특허분류(USC)	244/058; 244/057
출원번호	US-0947424 (2010-11-16)
등록번호	US-8684304 (2014-04-01)
발명자 / 주소	Burns, Donald Rajashekara, Kaushik
출원인 / 주소	Rolls-Royce Corporation
대리인 / 주소	Krieg DeVault LLP
인용정보	피인용 횟수 : 13 인용 특허 : 17

초록
▼

One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith...

대표
청구항
▼

1. A propulsion system for an aircraft, comprising: a gas turbine engine having a high pressure (HP) spool and a low pressure (LP) spool, wherein the LP spool is operative to drive a propulsor;an auxiliary power unit (APU) mechanically coupled to the LP spool and operative to drive the LP spool, wherein the APU is a thermodynamic machine configured to generate mechanical power from fuel;an auxiliary electrical machine mechanically coupled to the LP spool and operative to drive the LP spool; andan electrical power source electrically coupled to the auxiliary electrical machine,wherein the APU and the auxiliary electrical machine jointly supply rotational power to the LP spool at the same time to generate thrust via the propulsor for taxiing the aircraft. 2. The propulsion system of claim 1, wherein the electrical power source is a battery. 3. The propulsion system of claim 1, wherein the electrical power source is a fuel cell. 4. The propulsion system of claim 1, wherein the electrical power source is a combination of a fuel cell and a battery. 5. The propulsion system of claim 1, wherein the APU is a hybrid APU having an APU compressor; an APU turbine; and a fuel cell fluidly disposed between the APU compressor and the APU turbine, wherein the fuel cell is operative to receive as an oxidant air pressurized by the APU compressor; to generate electrical power using a fuel and the oxidant; to heat the air pressurized by the APU compressor; and to discharge the heated pressurized air into the APU turbine. 6. The propulsion system of claim 1, further comprising an auxiliary combining gearbox mechanically coupled to the APU, the auxiliary electrical machine and the gas turbine engine. 7. The propulsion system of claim 6, wherein the auxiliary combining gearbox is configured to transmit mechanical power from the auxiliary electrical machine to the APU for starting the APU. 8. The propulsion system of claim 6, wherein the auxiliary combining gearbox is configured to transmit mechanical power from the APU to the auxiliary electrical machine for generating electrical power. 9. The propulsion system of claim 6, wherein the auxiliary combining gearbox is configured to transmit mechanical power from the APU to the gas turbine engine. 10. The propulsion system of claim 6, wherein the auxiliary combining gearbox is configured to transmit mechanical power from the auxiliary electrical machine to the gas turbine engine. 11. The propulsion system of claim 6, wherein the auxiliary combining gearbox is configured to transmit mechanical power from both the auxiliary electrical machine and the APU to the gas turbine engine. 12. The propulsion system of claim 1, wherein the gas turbine engine includes a gearbox; wherein the APU is mounted on the gearbox; and wherein the gearbox is configured to transfer power from the APU to the HP spool for starting the gas turbine engine. 13. The propulsion system of claim 12, wherein the gearbox is configured to transfer power from the APU and the auxiliary electrical machine to the HP spool for starting the gas turbine engine. 14. The propulsion system of claim 1, wherein the gas turbine engine includes a gearbox; wherein the APU is mounted on the gearbox; and wherein the gearbox is configured to transfer power from the APU and the auxiliary electrical machine to the LP spool to generate thrust via the propulsor for taxiing the aircraft. 15. An aircraft, comprising: a fuselage;an empennage coupled to the fuselage;a plurality of wings coupled to the fuselage; anda propulsion system, including:a gas turbine engine having a high pressure (HP) spool and a low pressure (LP) spool and an engine gearbox, wherein the LP spool is operative to drive a propulsor; and wherein the gas turbine engine is coupled to at least one of the fuselage, the empennage and at least one of the plurality of wings;an auxiliary power unit (APU) mechanically coupled to the LP spool via the gearbox and operative to drive the LP spool, wherein the APU is a thermodynamic machine configured to generate mechanical power from fuel;an auxiliary electrical machine mechanically coupled to LP spool via the gearbox and operative to drive the LP spool;an electrical power source electrically coupled to the auxiliary electrical machine,wherein the APU and the auxiliary electrical machine jointly supply rotational power via the engine gearbox to the LP spool at the same time to generate thrust via the propulsor for taxiing the aircraft. 16. The aircraft of claim 15, wherein the engine gearbox is also configured to mechanically couple the APU to the HP spool for starting the gas turbine engine. 17. The aircraft of claim 16, wherein the engine gearbox is configured to mechanically couple the auxiliary electrical machine to the HP spool to starting the gas turbine engine. 18. The aircraft of claim 15, further comprising an engine electrical machine mounted on the HP spool and electrically coupled to at least one of the electrical power source and the auxiliary electrical machine, wherein the engine electrical machine, and the at least one of the electrical power source and the auxiliary electrical machine are configured to start the gas turbine engine by supplying electrical power to the engine electrical machine, whereby the engine electrical machine imparts rotation to the HP spool sufficient to start the gas turbine engine. 19. The aircraft of claim 15, wherein the electrical power source is at least one of a fuel cell and a battery. 20. The aircraft of claim 15, wherein the electrical power source is a combination of a fuel cell and a battery. 21. The aircraft of claim 15, wherein the APU is a hybrid APU having an APU compressor; an APU turbine; and a fuel cell fluidly disposed between the APU compressor and the APU turbine, wherein the fuel cell is operative to receive as an oxidant air pressurized by the APU compressor; to generate electrical power using a fuel and the oxidant; to heat the air pressurized by the APU compressor; and to discharge the heated pressurized air into the APU turbine. 22. A system, comprising: a gas turbine engine having a high pressure (HP) spool and a low pressure (LP) spool, wherein the LP spool is operative to drive a propulsor;a gearbox coupled to the LP spool; andmeans for supplying mechanical power from at least two sources to the low pressure spool for taxiing the system, wherein the means for supplying mechanical power includes means for supplying mechanical power by generating mechanical power from fuel; and wherein the means for supplying mechanical power supplies the mechanical power from two machines at the same time via the gearbox to the LP spool and provides power to the propulsor for propelling the system. 23. The system of claim 22, wherein the two sources include an auxiliary power unit (APU) and an auxiliary electrical machine, wherein the auxiliary electrical machine is powered by at least one of a fuel cell and a battery. 24. The system of claim 23, wherein the APU is a hybrid APU employing the fuel cell in the APU thermodynamic cycle. 25. The system of claim 23, wherein the means for supplying mechanical power is means for supplying power via the gearbox to the LP spool for providing power to the propulsor for propelling the system without starting the gas turbine engine. 26. A method for providing propulsion for aircraft for taxiing the aircraft, comprising: providing a gas turbine engine having a high pressure (HP) spool and a low pressure (LP) spool, wherein the LP spool is operative to drive a propulsor;mechanically coupling an auxiliary power unit (APU) to the LP spool, wherein the APU is a thermodynamic machine configured to generate mechanical power from fuel;mechanically coupling an auxiliary electrical machine to the LP spool;coupling an electrical power source electrically to the auxiliary electrical machine;supplying rotational power from the APU and the auxiliary electrical machine at the same time to the LP spool to generate thrust via the propulsor; andtaxiing the aircraft using the rotational power supplied to the propulsor from the APU and the auxiliary electrical machine, wherein the taxiing is performed without starting the gas turbine engine.

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

Aircraft, propulsion system, and system for taxiing an aircraft

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Aircraft, propulsion system, and system for taxiing an aircraft

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (17)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼