[특허]Gas turbine combustor and operating method thereof

[미국특허] Gas turbine combustor and operating method thereof 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/22
출원번호	US-0136554 (2005-05-25)
등록번호	US-7343745 (2008-03-18)
우선권정보	JP-2001-259119(2001-08-29)
발명자 / 주소	Inoue,Hiroshi Koganezawa,Tomomi Kobayashi,Nariyoshi Takehara,Isao
출원인 / 주소	Hitachi, Ltd.
대리인 / 주소	Mattingly, Stanger, Malur & Brundidge, P.C.
인용정보	피인용 횟수 : 15 인용 특허 : 16

초록

A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.

대표청구항 ▼

What is claimed is: 1. A gas turbine combustor having a combustion chamber supplied with fuel and air, comprising: a plurality of fuel nozzles for jelling gaseous fuel into said combustion chamber; a plurality of air holes for jetting air into said combustion chamber, said plurality of fuel nozzles and said plurality of air holes being arranged so that coaxial flows, each of which is formed with a fuel jet flow and an air flow flowing on an outer peripheral side of said fuel jet flow, are formed; a disc member having said plurality of air holes formed therein and arranged on a wall surface of said combustor so that gaseous fuel and air of said coaxial jet flows are jetted into said combustion chamber; wherein a flow passage area of each of said air holes is larger than a flow passage area of each fuel hole of said plurality of fuel nozzles; ends of said plurality of fuel nozzles are arranged around inlets of said air holes and at an upstream side of said wall surface of said combustion chamber so that the air from the upstream side of said disc member and gaseous fuel from said plurality of fuel nozzles are rapidly mixed in said combustion chamber after the air and the gaseous fuel are premixed in premixing flow passages of said air holes, and the gaseous fuel is jetted from said fuel nozzles to said air holes, said plurality of fuel nozzles and said plurality of air holes are formed as a single module, and axes of only a part of said plurality of air holes provided in said module are inclined against fuel jet flow axes of said fuel nozzles. 2. A gas turbine combustor according to claim 1, wherein said plurality of fuel nozzles are partitioned into a plurality of fuel supply systems, and a control system is provided to individually control a flow rate of fuel of each of said fuel supply systems according to a load of said gas turbine. 3. A gas turbine combustor according to claim 1, wherein a mechanism for imparting a swirling component around an axis of each of said air holes or said fuel nozzles is provided on each of said air holes or each of said fuel nozzles. 4. A gas turbine combustor according to claim 1, wherein at least one of said fuel nozzles is formed in a double-structure so that spraying of liquid fuel and gaseous fuel are switched or combined. 5. A method of operating a gas turbine combustor having a plurality of fuel nozzles for jetting gaseous fuel into a combustion chamber and a plurality of air hole for jetting air into said combustion chamber, comprising: providing a disc member having said plurality of air holes formed therein and arranged on a wall surface of said combustion chamber; forming a flow passage area of each of said air holes larger than a flow passage area of each fuel jet hole of said plurality of fuel nozzles; jetting said gaseous fuel to said air holes from ends of said fuel nozzles arranged around inlets of said air holes at an upstream side of said wall surface of said combustor to form coaxial jet flows of said fuel jet flows and air flows flowing on outer peripheral sides of said fuel jet flows, premixing air on the upstream side of said disc member and gaseous fuel from said fuel nozzles in premixing passages of said air holes, jetting the gaseous fuel and air of said coaxial jet flows from said disc member into said combustion chamber to rapidly mix the gaseous fuel and air in said combustion chamber after said premixing, and forming said plurality of fuel nozzles and said plurality of air holes as a single module, wherein axes of coaxial jet flows of only part of said plurality of air holes provided in said module are inclined against the fuel jet flows from said fuel nozzles. 6. A method of operating a gas turbine combustor according to claim 5, wherein said plurality of fuel nozzles are partitioned into a plurality of fuel supply systems, and a control system is provided to individually control a flow rate of fuel of each of said fuel supply systems according to a load of said gas turbine.

이 특허에 인용된 특허 (16) 인용/피인용 타임라인 분석

Shekleton Jack R. (San Diego CA) Sledd Michael W. (Vista CA) Sachrison Steven A. (LaJolla CA), Air assist fuel injection system.
상세보기
Shekleton Jack R. (San Diego CA) Rodgers Colin (San Diego CA) Archibald John P. (LaJolla CA) Smith Robert W. (Lakeside CA), Annular combustor with tangential cooling air injection.
상세보기
Cohen Mitchell ; Kuwata Masayoshi ; Steber Charles E. ; Mick Warren J., Center burner in a multi-burner combustor.
상세보기
Brhwiler Eduard (Turgi CHX) Koch Hans (Zrich NY CHX) Roffe Gerald (East Northport NY), Combustion chamber of a gas turbine and method of operating it.
상세보기
Ansart Denis Roger Henri (Bois le Roi FRX) Commaret Patrice Andre (Maincy FRX) Sandelis Denis Jean Maurice (Nangis FRX), Fuel injection assembly for a gas turbine engine.
상세보기
Shekleton Jack R. (San Diego CA) Smith Robert W. (Lakeside CA), Fuel injector for a gas turbine engine.
상세보기
Harjit Singh Hura ; Paul Edward Sabla ; James Neil Cooper ; Beverly Stephenson Duncan ; Hukam Chand Mongia ; Steven Joseph Lohmueller, Fuel nozzle assembly for reduced exhaust emissions.
상세보기
LeMer Joseph (Saint Thegonnec FRX), Gas burners.
상세보기
Komatsu Yasutaka,JPX ; Urushidani Haruo,JPX ; Azuhata Shigeru,JPX ; Iizuka Nobuyuki,JPX ; Watanabe Yasuyuki,JPX ; Arai Hiroyuki,JPX ; Kobayashi Nariyoshi,JPX ; Ohtsuka Masaya,JPX ; Ito Kazuyuki,JPX, Gas turbine combustor and operation method thereof for a diffussion burner and surrounding premixing burners separated b.
상세보기
Iwai Yasuo (Katsuta JPX) Azuhata Shigeru (Hitachi JPX) Sohma Kenichi (Hitachi JPX) Narato Kiyoshi (Taga JPX) Kobayashi Hironobu (Katsuta JPX) Inada Tooru (Hitachi JPX) Murakami Tadayoshi (Hitachi JPX, Gas turbine combustor of the completely premixed combustion type.
상세보기
Sion Martin (Mantes La Jolie FRX) Desclos Pierre (Vernon FRX) Raymond Dominique (Houlbec Cocherel FRX), Injection system and an associated tricoaxial element.
상세보기
Sugahara Tatsuya (Tokyo JPX) Takagi Takao (Fuji JPX) Mochizuki Kimio (Fujinomiya JPX) Akiyama Shigetoshi (Fuji JPX), Low-NOx gas burner.
상세보기
Suttrop Friedemann,DEX, Method and combustor for combusting hydrogen.
상세보기
Arthur Wesley Johnson ; Robert Andrew Wade ; Hukam Chand Mongia ; David Louis Burrus, Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer.
상세보기
Ishiguro Tatsuo,JPX ; Mandai Shigemi,JPX ; Inada Mitsuru,JPX ; Tanimura Satoshi,JPX ; Nishida Kouichi,JPX, Multi-nozzle combustor.
상세보기
Chamberlain John (Lake Park FL), Staged combustor having aerodynamically separated combustion zones.
상세보기

이 특허를 인용한 특허 (15) 인용/피인용 타임라인 분석

Zuo, Baifang; Washam, Roy Marshall; Wu, Chunyang, Apparatus and method for cooling a combustor cap.
상세보기
Patel, Bhawan B.; Morenko, Oleg, Combustion system for a gas turbine engine and method of operating same.
상세보기
Manoharan, Madanmohan; Kulkarni, Rahul R.; Bathina, Mahesh, Combustor.
상세보기
Stoia, Lucas John; Melton, Patrick Benedict; Westmoreland, III, James Harold, Combustor.
상세보기
Miura, Keisuke; Inoue, Hiroshi; Koyama, Kazuhito; Saito, Takeo, Combustor and a fuel supply method for the combustor.
상세보기
Boardman, Gregory Allen; Myers, Geoffrey David; Karim, Hasan; Hughes, Michael John; Hajiloo, Azardokht, Combustor and method for distributing fuel in the combustor.
상세보기
Miura, Keisuke; Inoue, Hiroshi; Koyama, Kazuhito; Saito, Takeo, Combustor having a first plurality of fuel nozzles having a first cross-sectional shape and a second plurality of fuel nozzles having a second cross-sectional shape different than the first cross-sectional shape.
상세보기
Berry, Jonathan Dwight; Ostebee, Heath Michael, Combustor leaf seal arrangement.
상세보기
Oskam, Gareth W., Gas turbine and fuel injector for the same.
상세보기
Uhm, Jong Ho; Johnson, Thomas Edward; Kim, Kwanwoo, Injection nozzle for a turbomachine.
상세보기
Oskam, Gareth W., Lean direct fuel injector.
상세보기
Oskam, Gareth W., Method of operating a gas turbine engine.
상세보기
Chen,Alexander G.; Kendrick,Donald W., Multi-point staging strategy for low emission and stable combustion.
상세보기
Uhm, Jong Ho; Ziminsky, Willy Steve; Johnson, Thomas Edward; Hughes, Michael John; York, William David, System for reducing combustion dynamics and NOx in a combustor.
상세보기
Rohrssen, Robert Joseph; Melton, Patrick Benedict, System for supplying pressurized fluid to a cap assembly of a gas turbine combustor.
상세보기

활용도 분석정보

상세보기

다운로드

내보내기

활용도 Top5 특허

해당 특허가 속한 카테고리에서 활용도가 높은 상위 5개 콘텐츠를 보여줍니다.
더보기 버튼을 클릭하시면 더 많은 관련자료를 살펴볼 수 있습니다.

IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
구성항목	기본정보 상세정보 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

연합인증

[미국특허] Gas turbine combustor and operating method thereof 원문보기

초록

대표청구항 ▼

연구과제 타임라인

이 특허에 인용된 특허 (16) 인용/피인용 타임라인 분석

이 특허를 인용한 특허 (15) 인용/피인용 타임라인 분석

활용도 분석정보

활용도 Top5 특허

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

연합인증

[미국특허] Gas turbine combustor and operating method thereof 원문보기

초록

대표청구항 ▼

연구과제 타임라인

전체(0) 논문(0) 특허(0) 보고서(0)

전체(0) 논문(0) 특허(0) 보고서(0)

이 특허에 인용된 특허 (16) 인용/피인용 타임라인 분석

이 특허를 인용한 특허 (15) 인용/피인용 타임라인 분석

활용도 분석정보

활용도 Top5 특허 더보기

관련 콘텐츠

특허 원문 보기

IPC 상위 출원인

AI-Helper ※ AI-Helper는 오픈소스 모델을 사용합니다.

선택된 텍스트

활용도 Top5 특허