[특허]Combustor module

Allison Advanced Development 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

Combustor module

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/22
미국특허분류(USC)	060/737; 060/743
출원번호	US-0951848 (2001-09-12)
발명자 / 주소	Oechsle, Victor L. Roesler, Timothy C.
출원인 / 주소	Allison Advanced Development Company
대리인 / 주소	Woodard Emhardt Moriarty McNett & Henry LLP
인용정보	피인용 횟수 : 3 인용 특허 : 27

초록
▼

A combustor module includes a pre-vaporizing chamber defined by an inner wall, and an outer wall, and a heat shield. The heat shield separates the pre-mixing zone from the reaction zone of the combustor. At least one fueling nozzle is disposed in the pre-vaporizing chamber for injecting fuel into the pre-vaporizing chamber. Fuel from the fueling nozzle is sprayed onto the surface of the heat shield, thereby simultaneously vaporizing the fuel and cooling the heat shield. The heat shield also includes a pilot fueling spray opening to allow fuel to pass dir...

대표
청구항
▼

1. A combustor dome module for a gas turbine engine combustor comprising:an annular pre-vaporizing chamber defined by an outer wall, an inner wall, and a heat shield, said heat shield including an opening adapted to allow a fuel to pass into a piloting flame stability region of the gas turbine engine combustor;an outer swirler coupled to said outer wall of said pre-vaporizing chamber; andan inner swirler coupled to said inner wall of said pre-vaporizing chamber. 2. The combustor dome module of claim 1, wherein said inner swirler is formed integral with said inner wall member of said pre-vaporizing chamber, and said outer swirler is formed integral with said outer wall member of said pre-vaporizing chamber. 3. The combustor dome module of claim 1, wherein said heat shield is made of a ceramic material and is coupled to float relative to at least one of said inner and outer wall members of said pre-vaporizing chamber. 4. The combustor dome module of claim 1, wherein said inner swirler is adapted to impart a swirl to a flow discharged therefrom in a direction that is the same as, or opposite, that imparted to a flow discharged from said outer swirler. 5. The combustor dome module of claim 1, wherein each of said swirlers discharges a flow that recirculates toward said heat shield, thereby creating a double vortex. 6. A combustor for a gas turbine engine comprising:a combustion chamber having an annular configuration defined by an inner wall and an outer wall;a combustor dome module coupled to said inner and outer walls of said combustion chamber, said combustor dome module including an annular pre-vaporizing chamber defined by an inner wall member, an outer wall member, and a heat shield, said heat shield is made from ceramic material and coupled to float relative to said inner and outer wall members of said pre-vaporizing chamber;a working fluid flow passageway extending along said pre-vaporizing chamber for flowing a working fluid that has not passed through said pre-vaporizing chamber;a first swirler in fluid flow communication with said working fluid flow passageway to impart a swirl to the working fluid from said passageway and discharge into said combustion chamber; andmeans disposed in said pre-vaporizing chamber for delivering a fuel into said pre-vaporizing chamber. 7. The combustor of claim 6, wherein said heat shield includes an opening to allow fuel to pass into a piloting flame stability region of said combustion chamber. 8. The combustor of claim 6, further comprising a second swirler in fluid flow communication with said working fluid flow passageway to impart a swirl to the working fluid from said passageway and discharge into said combustion chamber. 9. The combustor of claim 8, wherein said first swirler is an inner swirler formed integral with said inner wall member of said pre-vaporizing chamber, and said second swirler is an outer swirler formed integral with said outer wall member of said pre-vaporizing chamber. 10. The combustor of claim 8, wherein said inner swirler is adapted to impart a swirl to a flow discharged therefrom in a direction that is the same as, or opposite, that imparted to a flow discharged from said outer swirler. 11. The combustor of claim 8, wherein each of said swirlers discharges a flow that recirculates forward toward said heat shield, thereby creating a double vortex. 12. The combustor of claim 8, wherein a vaporized fuel and air mixture exiting said pre-vaporizing chamber enters said combustion chamber between said heat shield and said swirlers. 13. The combustor of claim 6, wherein said means for delivering fuel into said pre-vaporizing chamber includes at least one fuel nozzle with at least one opening oriented to spray fuel onto said heat shield, whereby the fuel is normally vaporized upon reaching the heat shield. 14. The combustor of claim 13, wherein said at least one opening numbers nine. 15. The combustor of claim 6, wherein said means for delivering fuel into said pre-vap orizing chamber includes a plurality of fueling nozzles spaced around said annular pre-vaporizing chamber. 16. The combustor of claim 15, wherein said plurality of fueling nozzles numbers eight. 17. A gas turbine engine combustor comprising:a pre-mixing chamber;a reaction zone;a heat shield separating said pre-mixing chamber from said reaction zone, said heat shield having an outer surface in said pre-mixing chamber and has a substantially concave shape exposed to said reaction zone, said heat shield is coupled to a float relative to at least a portion of said pre-mixing chamber;an inner and outer cowling disposed around said pre-mixing chamber and defining a fluid flow passageway extending along said pre-mixing chamber for passage of a working fluid to said reaction zone without passing through said pre-mixing chamber;at least one swirler in fluid flow communication with said fluid flow passageway to impart a swirl to the working fluid from said passageway; anda fueling nozzle disposed in said pre-mixing chamber for spraying fuel onto said outer surface of said heat shield, thereby cooling said heat shield. 18. A combustor dome module for a gas turbine engine combustor comprising:an annular pre-vaporizing chamber defined by an outer wall, an inner wall, and a heat shield, said heat shield including an opening adapted to allow a fuel to pass into a piloting flame stability region of the gas turbine engine combustor, wherein said heat shield is coupled to float relative to at least one of said inner and outer wall members of said pre-vaporizing chamber;an outer swirler coupled to said outer wall of said pre-vaporizing chamber; andan inner swirler coupled to said inner wall of said pre-vaporizing chamber. 19. The combustor of claim 18, which further comprises an inner and an outer cowling disposed around said pre-vaporizing chamber and defining a fluid flow passageway for passage of a pressurized working fluid to said swirlers. 20. The combustor of claim 19, wherein said fluid flow passageway delivers pressurized working fluid that has not passed through said pre-vaporizing chamber. 21. The combustor of claim 20, wherein said inner swirler is formed integral with said pre-vaporizing chamber, and said outer swirler is formed integral with said pre-vaporizing chamber. 22. A combustor for a gas turbine engine comprising:a combustion chamber having an annular configuration defined by an inner wall and an outer wall;a combustion chamber having an annular configuration defined by an inner wall and an outer wall;a combustor dome module coupled to said inner and outer walls of said combustion chamber, said combustor dome module including an annular pre-vaporizing chamber defined by an inner wall member, an outer wall member, and a heat shield, said heat shield includes an opening to allow fuel to pass into a piloting flame stability region of said combustion chamber;a working fluid flow passageway extending along said pre-vaporizing chamber for flowing a working fluid that has act passed through said pre-vaporizing chamber;a first swirler in fluid flow communication with said working fluid flow passageway to impart a swirl to the working fluid from said passageway and discharge into said combustion chamber; andmeans disposed in said pre-vaporizing chamber for delivering a fuel into said pre-vaporizing chamber.

이 특허에 인용된 특허 (27)

이 특허를 인용한 특허 피인용횟수: 3

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

Combustor module

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (27)

이 특허를 인용한 특허 피인용횟수: 3

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

Combustor module

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (27)

이 특허를 인용한 특허 피인용횟수: 3

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼