[특허]Air diffuser for a head end of a combustor

General Electric Company

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, Kafe, Webinar 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

Air diffuser for a head end of a combustor

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F23R-003/28 F23R-003/04 F23R-003/10
출원번호	US-0797912 (2013-03-12)
등록번호	US-9671112 (2017-06-06)
발명자 / 주소	Chila, Ronald James Boardman, Gregory Allen Westmoreland, James Harold
출원인 / 주소	General Electric Company
대리인 / 주소	Fletcher Yoder, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 89

초록
▼

A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle includes a support structure defining an interior volume configured to receive an air flow; a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector; and an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward...

대표
청구항
▼

1. A system, comprising: a multi-tube fuel nozzle of a turbine combustor, comprising: a support structure defining an interior volume configured to receive an air flow;a plurality of mixing tubes disposed within the interior volume, wherein each mixing tube of the plurality of mixing tubes comprises a respective fuel injector positioned within an inlet end of the respective mixing tube and configured to inject a fuel into the respective mixing tube, and each mixing tube of the plurality of mixing tubes comprises at least one hole formed in a side wall of the respective mixing tube;an outer annular wall having a first curved profile and extending radially outward from the support structure, wherein the outer annular wall is configured to direct the air flow from an annulus between a liner and a flow sleeve of the turbine combustor, at least partially radially inward into the interior volume through an air inlet disposed downstream of the respective fuel injector of each mixing tube of the plurality of mixing tubes relative to a flow direction of the fuel through each mixing tube of the plurality of mixing tubes, and at least partially axially upstream toward the respective fuel injector of each mixing tube of the plurality of mixing tubes and toward the at least one hole of each mixing tube of the plurality of mixing tubes, and the outer annular wall at least partially defines an air flow passage directing the air flow and extending from the annulus to the interior volume; andan inner annular wall at least partially defining the air flow passage, wherein the inner annular wall has a second curved profile and extends radially outward from the support structure. 2. The system of claim 1, wherein the first curved profile extends from the flow sleeve to the support structure, and the inner annular wall is substantially parallel to the liner. 3. The system of claim 1, wherein the first curved profile has a first radius of curvature, and the second curved profile has a second radius of curvature. 4. The system of claim 3, wherein the first radius of curvature and the second radius of curvature are substantially equal. 5. The system of claim 3, wherein the first radius of curvature is greater than the second radius of curvature. 6. The system of claim 1, wherein the outer annular wall and the inner annular wall each approach the interior volume at a substantially constant angle. 7. The system of claim 1, wherein the at least one hole of each mixing tube of the plurality of mixing tubes comprises a plurality of holes configured to receive the air flow from the interior volume. 8. The system of claim 7, wherein the plurality of holes of each mixing tube of the plurality of mixing tubes is upstream of the air inlet relative to the flow direction of fuel through the plurality of mixing tubes. 9. The system of claim 1, wherein the inner annular wall curves radially outward from the support structure such that a portion of the inner annular wall is radially spaced apart from the support structure. 10. A system, comprising: a multi-tube fuel nozzle assembly of a combustor, comprising: a support structure defining an interior volume, wherein the interior volume is configured to receive an air flow through an air inlet;an air diffuser comprising an outer annular wall and an inner annular wall, wherein the outer annular wall and the inner annular wall each has a curved profile and extends radially outward from the support structure, and the outer annular wall and the inner annular wall define an air passage extending to the air inlet of the interior volume;a plurality of mixing tubes disposed within the interior volume, wherein each mixing tube of the plurality of mixing tubes comprises at least one hole formed in a side wall of the respective mixing tube and configured to receive the air flow from the interior volume; anda plurality of fuel injectors, wherein each fuel injector of the plurality of fuel injectors is at least partially disposed within an inlet end of a respective one of the plurality of mixing tubes and is configured to inject a fuel flow into the respective one of the plurality of mixing tubes, and the plurality of fuel injectors are disposed upstream of the air inlet relative to a direction of the fuel flow through the plurality of mixing tubes. 11. The system of claim 10, wherein the air diffuser is configured to direct the air flow radially inward through the air inlet and axially upstream toward the plurality of fuel injectors and toward the at least one hole of each mixing tube of the plurality of mixing tubes. 12. The system of claim 10, wherein the air passage extends from an annulus between a liner and a flow sleeve of the combustor to the interior volume. 13. The system of claim 12, wherein a cross-section of the air passage increases in size from the annulus to the interior volume. 14. The system of claim 10, wherein the at least one hole of each mixing tube of the plurality of mixing tubes comprises a plurality of holes disposed upstream of the air diffuser relative to the direction of the fuel flow through the plurality of mixing tubes. 15. The system of claim 10, comprising the combustor or a gas turbine engine having the multi-tube fuel nozzle assembly. 16. The system of claim 10, wherein the inner annular wall curves radially outward from the support structure such that a portion of the inner annular wall is radially spaced apart from the support structure. 17. A method, comprising: directing an air flow with an air diffuser of a turbine combustor from an axial flow direction to a radial flow direction and into an interior volume through an air inlet, wherein the interior volume comprises a plurality of mixing tubes, each mixing tube of the plurality of mixing tubes comprises a mixing chamber and at least one hole formed in a side wall of the respective mixing tube and configured to receive the air flow, and wherein the air diffuser comprises an outer annular wall and an inner annular wall, the outer annular wall and the inner annular wall each has a curved profile and extends radially outward from a support structure defining the interior volume;injecting fuel from a plurality of fuel injectors into the plurality of mixing tubes, wherein each fuel injector of the plurality of fuel injectors is positioned within an inlet end of one of the plurality of mixing tubes and is positioned upstream of the air inlet relative to a flow direction of the fuel through the plurality of mixing tubes;mixing the air flow and the fuel within the mixing chamber of each mixing tube of the plurality of mixing tubes to create a fuel-air mixture; andoutputting the fuel-air mixture from each mixing chamber into a combustion chamber of the turbine combustor. 18. The method of claim 17, wherein the at least one hole of each mixing tube of the plurality of mixing tubes comprises a plurality of holes formed in the side wall of the respective mixing tube and located upstream of the air diffuser relative to the flow direction of the fuel through the plurality of mixing tubes. 19. The method of claim 17, wherein the support structure surrounds the plurality of mixing tubes and the plurality of fuel injectors. 20. The method of claim 17, wherein the outer annular wall and the inner annular wall define an air passage extending from an annulus between a liner and a flow sleeve of the turbine combustor to the interior volume.

이 특허에 인용된 특허 (89)

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

Air diffuser for a head end of a combustor

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (89)

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

Air diffuser for a head end of a combustor

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (89)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼