[특허]Gas turbine engine including a third flowpath exhaust nozzle

United Technologies Corporation

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

검색도움말
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

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Gas turbine engine including a third flowpath exhaust nozzle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-003/077 F02K-001/12 F02K-003/02 F02K-001/38 F02K-003/075 F02K-001/00
출원번호	US-0768714 (2014-02-14)
등록번호	US-10197008 (2019-02-05)
국제출원번호	PCT/US2014/016509 (2014-02-14)
국제공개번호	WO2014/130361 (2014-08-28)
발명자 / 주소	Roberge, Gary D.
출원인 / 주소	United Technologies Corporation
대리인 / 주소	O'Shea Getz P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 5

초록
▼

A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.

대표
청구항
▼

1. A turbofan engine, comprising: a first flowpath that is radially inboard of a second flowpath at a location upstream of a core section of the turbofan engine;a third flowpath that is radially outboard of the second flowpath at the location upstream of the core section of the turbofan engine;a third flowpath exhaust nozzle that defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged; anda primary exhaust nozzle that defines a primary exhaust exit port through which a first gas flow travelling along the first flowpath and a second gas flow traveling along the second flowpath may be discharged;wherein the third flowpath exhaust nozzle is configured so that an area of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable;wherein the third flowpath exhaust nozzle is positioned on the turbofan engine so that the gas discharged through the plurality of third flowpath exhaust exit ports subsequently discharges through the primary exhaust exit port; andwherein, at a location downstream of the core section of the turbofan engine, the third flowpath is radially inboard of the second flowpath. 2. The turbofan engine of claim 1, wherein by independently and selectively adjusting an area of one of the plurality of third flowpath exhaust exit ports, a characteristic of the gas passing there through may be independently and selectively adjusted. 3. The turbofan engine of claim 1, wherein the first flowpath, the second flowpath, and the third flowpath extend generally axially in a direction between an inlet section of the turbofan engine and an exhaust section of the turbofan engine. 4. The turbofan engine of claim 1, further comprising an engine case that at least partially defines the first flowpath, the second flowpath, or the third flowpath. 5. The turbofan engine of claim 1, further comprising an engine duct that at least partially defines the first flowpath, the second flowpath, or the third flowpath. 6. The turbofan engine of claim 1, wherein the gas traveling along the third flowpath has a temperature that is lower than a temperature of the first gas flow traveling along the first flowpath. 7. An exhaust section of a turbofan engine, comprising: a first flowpath;a second flowpath radially outboard of the first flowpath; anda third flowpath exhaust nozzle that defines a plurality of third flowpath exhaust exit ports through which gas traveling along a third flowpath of the turbofan engine may be discharged, the third flowpath exhaust nozzle radially outboard of the second flowpath; anda primary exhaust nozzle that defines a primary exhaust exit port through which a first gas flow traveling along the first flowpath and a second gas flow traveling along the second flowpath may be discharged;wherein the third flowpath exhaust nozzle is configured so that an area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable;wherein the third flowpath exhaust nozzle is positioned on the turbofan engine so that the gas discharged through the plurality of third flowpath exhaust exit ports subsequently discharges through the primary exhaust exit port; andwherein, at a location downstream of a core section of the turbofan engine, the third flowpath is radially inboard of the second flowpath. 8. The exhaust section of claim 7, wherein the third flowpath is radially outboard of the second flowpath at a location upstream of the core section of the turbofan engine, and wherein the second flowpath is radially outboard of the first flowpath at the location upstream of the core section of the turbofan engine. 9. The exhaust section of claim 8, wherein the first flowpath, the second flowpath, and the third flowpath extend generally axially in a direction between an inlet section of the turbofan engine and the exhaust section of the turbofan engine. 10. The exhaust section of claim 8, further comprising an engine case that at least partially defines the first flowpath, the second flowpath, or the third flowpath. 11. The exhaust section of claim 8, further comprising an engine duct that at least partially defines the first flowpath, the second flowpath, or the third flowpath. 12. The exhaust section of claim 7, wherein by independently and selectively adjusting the area or the geometry of one of the plurality of third flowpath exhaust exit ports, a characteristic of the gas passing there through may be independently and selectively adjusted. 13. A method for operating a turbofan engine having a third flowpath exhaust nozzle that defines a plurality of third flowpath exhaust exit ports through which gas traveling along a third flowpath of the turbofan engine may be discharged, the third flowpath exhaust nozzle being configured so that an area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable, the method comprising: independently and selectively adjusting an area of at least one of the plurality of third flowpath exhaust exit ports to achieve an engine operation;wherein a first flowpath is radially inboard of a second flowpath at a location;wherein the third flowpath is radially outboard of the second flowpath at the location;wherein a primary exhaust nozzle defines a primary exhaust exit port through which a first gas flow traveling along the first flowpath and a second gas flow traveling along the second flowpath is discharged;wherein the third flowpath exhaust nozzle is positioned on the turbofan engine so that the gas discharged through the plurality of third flowpath exhaust exit ports subsequently discharges through the primary exhaust exit port; andwherein, at a location downstream of a core section of the turbofan engine, the third flowpath is radially inboard of the second flowpath. 14. The method of claim 13, wherein the engine operation is selected from the group that includes: thrust vectoring, noise reduction, enhanced plume mixing, aircraft drag reduction, and thermal protection of aircraft structure.

이 특허에 인용된 특허 (5)

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

연합인증

특허 상세정보

Gas turbine engine including a third flowpath exhaust nozzle

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (5)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Gas turbine engine including a third flowpath exhaust nozzle

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (5)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼