[특허]Segmented annular ring-manifold quaternary fuel distributor

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

Segmented annular ring-manifold quaternary fuel distributor

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00
미국특허분류(USC)	060/739;
출원번호	US-0754813 (2010-04-06)
등록번호	US-8418468 (2013-04-16)
발명자 / 주소	McMahan, Kevin Weston Valeev, Almaz Wu, Chunyang
출원인 / 주소	General Electric Company
대리인 / 주소	Cantor Colburn LLP
인용정보	피인용 횟수 : 1 인용 특허 : 21

초록

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

대표
청구항
▼

1. A combustor section, comprising: a segmented annular quaternary fuel manifold mounted at a location defined axially upstream from a fuel nozzle support relative to a combustor centerline axis, the segmented annular manifold being mounted in a section of a passage through which an oxidizer flows,the passage being defined such that the oxidizer flows through the passage in a reverse direction radially outwardly of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle support,the segmented annular manifold being located in a section of the passage in which the oxidizer flows in the reverse direction at a local velocity that exceeds oxidizer flow velocities in other sections of the passage,each segment of the manifold being substantially axially aligned with one another and including a body to accommodate fuel internally, the body being formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows, the fuel injection occurring axially upstream of the fuel nozzle support. 2. The combustor section according to claim 1, further comprising a casing and a cap assembly, the casing surrounding the segmented annular manifold and the cap assembly being located radially inwardly of the casing and including the fuel nozzle support, which is provided as one of a plurality of fuel nozzle supports, wherein the section of the passage through which an oxidizer flows is radially interposed between the casing and the cap assembly of a combustor. 3. The combustor section according to claim 2, further comprising an annular baffle extending axially from the cap assembly to surround the plurality of fuel nozzle supports, wherein the section of the passage in which the segmented annular manifold is located is radially interposed between the casing and the baffle. 4. The combustor section according to claim 1, wherein each segment defines an internal volume, and wherein a sum total volume of the segmented manifold accommodates up to about 30% by mass of available fuel of the combustor. 5. The combustor section according to claim 4, wherein an amount of the available fuel accommodated within each segment is one of fixed and actively controlled. 6. The combustor section according to claim 1, wherein the injection holes are perimetrically arrayed at each segment. 7. The combustor section according to claim 1, wherein each of the bodies comprises a segmented ring-shaped casing having first and second opposing sides, at least one of which is tapered. 8. The combustor section according to claim 1, wherein the segmented annular manifold comprises one or more segments that is plural in number such that, for each of the plural manifold segments, one segment is radially outward of another one of the plural manifold segments. 9. The combustor section according to claim 8, wherein the one or more of the segments are fueled independently with differing fuels, diluents, and/or steam. 10. The combustor section according to claim 1, further comprising: at least one fuel source; andat least one supply line coupled to the at least one fuel source by which fuel is supplied from the fuel source to at least one of the segments of the manifold. 11. The combustor section according to claim 1, wherein the axial location upstream from the fuel nozzle support is defined as an axial location that is axially interposed between an axial location of the fuel nozzle support and an axial location at which the air and/or the fuel/air mixture changes from flowing in the reverse direction to flowing in the forward direction. 12. A combustor section, comprising: a casing;a cap assembly, having a fuel nozzle support formed therein, the cap assembly being disposed within the casing to define an annular passage between the casing and the cap assembly through which oxidizer flows in a reverse direction, then in a radially inward direction and then in a forward direction opposite the reverse direction upstream from the fuel nozzle support; anda segmented annular quaternary fuel manifold mounted within a section of the passage at which the oxidizer flows in the reverse direction, the segmented annular manifold being mounted at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis, each of the segments being substantially axially aligned with one another and including a body in which fuel is accommodated and injection holes through which the fuel is injected into the passage section. 13. The combustor section according to claim 12, wherein the casing comprises: first and second flanges; anda quaternary fuel distribution manifold axially interposed between the first and second flanges and substantially axially aligned with the segmented annular manifold, the quaternary fuel distribution manifold being configured to supply fuel to the segmented annular manifold. 14. The combustor section according to claim 13, further comprising at least one or more fuel line flanges, wherein each fuel line flange supplies to one or more of the segments a same or different fuel as another fuel line flange. 15. An annular fuel manifold of a combustor, the combustor including a casing; and a cap assembly disposed within the casing to define an annular passage through which oxidizer flows in a reverse direction, then in a radially inward direction and then in a forward direction opposite the reverse direction upstream from a fuel nozzle support, the annular fuel manifold comprising: a segmented annular body, each body segment being substantially axially aligned with one another, formed to accommodate fuel therein, and formed to define fuel injection holes by which the fuel is injected into a section of the passage at which the oxidizer flows in the reverse direction at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis. 16. The annular fuel manifold according to claim 15, wherein the segmented annular body is segmented into two or more body segments having substantially uniform circumferential lengths and being separated from one another by substantially uniform spacing. 17. The annular fuel manifold according to claim 15, wherein each body segment is coupled to a same or different fuel source as another of the body segments. 18. The annular fuel manifold according to claim 15, wherein the segmented annular body is tapered. 19. The annular fuel manifold according to claim 15, wherein the fuel injection holes are disposed at a downstream portion of the segmented annular body. 20. The annular fuel manifold according to claim 15, wherein the fuel injection holes are arrayed with at least one of substantially uniform and non-uniform spacing along the segmented annular body, and wherein the fuel is injected in radially inward and radially outward directions relative to a combustor centerline axis. 21. The annular fuel manifold according to claim 15, wherein multiple segmented annular fuel manifolds are provided in a gas turbine engine. 22. A combustor section, comprising: a segmented manifold configured for quaternary fuel injection into a combustor, the segmented manifold being mounted at a location defined axially upstream from a fuel nozzle support relative to a combustor centerline axis in a section of a passage through which an oxidizer flows, the passage being defined such that the oxidizer flows through the passage in a reverse direction radially outwardly of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle supporteach segment of the manifold being substantially axially aligned with one another and including a body to accommodate fuel internally,the bodies together defining the segmented manifold having a shape similar to a shape of the passage section at an axial location of the body and wherein each body is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows, the fuel injection occurring axially upstream of the fuel nozzle support. 23. The combustor section according to claim 22, wherein the passage section is annular and the shape of the segmented manifold is annular. 24. The combustor section according to claim 22, wherein the passage section and the shape of each of the bodies in the segmented manifold are angular. 25. The combustor section according to claim 22, wherein the passage section and the shape of each of the bodies in the segmented manifold are rectangular. 26. A combustor section, comprising: a casing;a cap assembly, having a fuel nozzle support formed therein, the cap assembly being disposed within the casing to define a passage between the casing and the cap assembly through which oxidizer flows upstream from the fuel nozzle support, the oxidizer flows through the passage in a reverse direction radially outward of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle support; anda segmented manifold mounted within a section of the passage at which the oxidizer flows, the segmented manifold being mounted at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis, each of the segments being substantially axially aligned with one another and including a body in which fuel is accommodated,the bodies together defining a segmented manifold having a shape similar to a shape of the passage section at an axial location of the body and each body defining injection holes through which the fuel is injected into the passage section, the fuel injection occurring axially upstream of the fuel nozzle support. 27. The combustor section according to claim 26, wherein the passage section is annular and the shape of the segmented manifold is annular. 28. The combustor section according to claim 26, wherein the passage section and the shape of each of the bodies in the segmented manifold are angular. 29. The combustor section according to claim 26, wherein the passage section and the shape of each of the bodies in the segmented manifold are rectangular.

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 1

Chasse, Jr., James P.; Tu, Peter; Sheil, Robert F.. Fuel manifold for a gas turbine engine. USP20181110132244.

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

Segmented annular ring-manifold quaternary fuel distributor

초록

대표
청구항
▼

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 1

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

Segmented annular ring-manifold quaternary fuel distributor

초록

대표청구항 ▼

이 특허에 인용된 특허 (21)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

대표
청구항
▼