[특허]Modulated flow turbine nozzle

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

Modulated flow turbine nozzle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/12
미국특허분류(USC)	060/782; 060/806
출원번호	US-0885147 (2004-07-06)
발명자 / 주소	Orlando,Robert Joseph Moniz,Thomas Ory Brauer,John Christopher Prentice,Ian Francis Krammer,Erich Alois Dolan,James Patrick Frederick,Robert Alan
출원인 / 주소	General Electric Company
인용정보	피인용 횟수 : 16 인용 특허 : 12

초록
▼

A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooli...

대표
청구항
▼

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A gas turbine engine comprising: a compressor joined to a turbine for being powered thereby; said turbine including a nozzle having a row of hollow vanes extending radially between outer and inner bands, and said outer band is supported in an annular outer casing; each of said vanes having an internal cooling plenum, and a bypass tube extending through said outer and inner bands; a two-ply septum disposed radially between said outer casing and said outer band, and defining independent first and second manifolds; said first manifold surrounding said outer band and disposed in flow communication with said plenums of said vanes; said second manifold surrounding said first manifold and disposed in flow communication with said bypass tubes of said vanes; a bleed circuit disposed in flow communication between said compressor and said first and second manifolds for channeling pressurized air therebetween; and a control valve disposed between said bleed circuit and said first manifold for modulating flow of said pressurized cooling air into said vane plenums. 2. An engine according to claim 1 wherein said first and second manifolds are disposed in parallel flow from said bleed circuit, and said second manifold is directly joined to said bleed circuit without a flow modulation valve. 3. An engine according to claim 2 wherein said septum comprises outer and inner plies spaced apart radially to define said first manifold therebetween, with said second manifold being defined radially between said outer ply and said outer casing. 4. An engine according to claim 3 wherein each of said bypass tubes has an outer end disposed in flow communication with said second manifold through said septum, and an inner end extending through said inner band. 5. An engine according to claim 4 wherein said septum outer ply includes a plurality of apertures disposed in flow communication with said second supply tubes. 6. An engine according to claim 5 further comprising: an inner spoolie joining each of said bypass tubes to said septum in flow communication with said second manifold; and an outer spoolie joining each of said second supply tubes to said septum in flow communication with said first manifold. 7. An engine according to claim 6 wherein said septum is single ply over forward ends of said vanes, and supports said inner spoolies therein, and is two-ply circumferentially between said forward ends of said vanes and supports said outer spoolies in said outer ply thereof. 8. An engine according to claim 7 wherein said septum is two-ply circumferentially between and over aft ends of said vanes for providing a circumferentially continuous first manifold over a plurality of adjacent vanes. 9. An engine according to claim 8 wherein: said septum inner ply includes a multitude of impingement holes along said first manifold for discharging said pressurized air therefrom to impingement cool said outer band; and each of said vanes includes an impingement baffle inside said plenum 48 thereof having an inlet through said outer band surrounding a corresponding bypass tube for receiving spent impingement air discharged through said impingement holes. 10. An engine according to claim 8 wherein: each of said vanes includes a partition dividing said plenum into forward and aft channels; said bypass tube comprises a forward impingement baffle disposed inside said forward channel; said aft channel includes an aft impingement baffle having an inlet through said outer band; and an aft spoolie joins said first manifold in flow communication with said inlet of said aft impingement baffle. 11. A gas turbine engine comprising: a compressor joined to a turbine for being powered thereby; said turbine including a nozzle having a row of hollow vanes extending radially between outer and inner bands; each of said vanes having an internal cooling plenum, and a bypass tube extending through said outer and inner bands; a first manifold surrounding said outer band and disposed in flow communication with said plenums of said vanes; a second manifold surrounding said first manifold and disposed in flow communication with said bypass tubes of said vanes; a bleed circuit disposed in flow communication between said compressor and first and second manifolds for channeling pressurized air therebetween; and a control valve disposed between said bleed circuit and first manifold for modulating flow of said pressurized air into said vane plenums. 12. An engine according to claim 11 wherein said first and second manifolds are disposed in parallel flow from said bleed circuit, and said second manifold is directly joined to said bleed circuit without a flow modulation valve. 13. An engine according to claim 12 further comprising an annular outer casing supporting said nozzle, and a septum disposed radially therebetween to separate radially said first and second manifolds. 14. An engine according to claim 13 wherein said bleed circuit comprises: a plurality of first supply tubes extending through said casing to said first manifold for channeling said pressurized air thereto; and a plurality of second supply tubes extending through said casing to said second manifold for channeling said pressurized air thereto. 15. An engine according to claim 14 wherein said each of said first tubes includes a corresponding one of said control valves for modulating airflow therethrough. 16. An engine according to claim 15 wherein said bleed circuit further comprises a common supply manifold joined in flow communication with said compressor, and said first and second tubes extend therefrom to said first and second manifolds, respectively. 17. An engine according to claim 15 wherein said septum comprises outer and inner plies spaced apart radially to define said first manifold therebetween, with said second manifold being defined radially between said outer ply and said outer casing. 18. An engine according to claim 17 wherein each of said bypass tubes has an outer end disposed in flow communication with said second manifold through said septum, and an inner end extending through said inner band. 19. An engine according to claim 18 wherein said septum outer ply includes a plurality of apertures disposed in flow communication with said second supply tubes. 20. An engine according to claim 19 further comprising: an inner spoolie joining each of said bypass tubes to said septum in flow communication with said second manifold; and an outer spoolie joining each of said second supply tubes to said septum in flow communication with said first manifold. 21. An engine according to claim 20 wherein said septum is single ply over forward ends of said vanes, and supports said inner spoolies therein, and is two-ply circumferentially between said forward ends of said vanes and supports said outer spoolies in said outer ply thereof. 22. An engine according to claim 21 wherein said septum is two-ply circumferentially between and over aft ends of said vanes for providing a circumferentially continuous first manifold over a plurality of adjacent vanes. 23. An engine according to claim 22 wherein said septum inner ply includes a multitude of impingement holes along said first manifold for discharging said pressurized air therefrom to impingement cool said outer band. 24. An engine according to claim 23 wherein each of said vane plenums includes an inlet through said outer band surrounding a corresponding bypass tube for receiving spent impingement air discharged through said impingement holes. 25. An engine according to claim 23 wherein each of said vanes includes an impingement baffle inside said plenum thereof having an inlet through said outer band surrounding a corresponding bypass tube for receiving spent impingement air discharged through said impingement holes. 26. An engine according to claim 22 wherein: each of said vanes includes a partition dividing said plenum into forward and aft channels; said bypass tube comprises a forward impingement baffle disposed inside said forward channel; and said aft channel includes an aft impingement baffle having an inlet through said outer band. 27. An engine according to claim 26 further comprising an aft spoolie joining said first manifold in flow communication with said inlet of said aft impingement baffle. 28. An engine according to claim 15 further comprising: a first stage nozzle and first stage rotor disk disposed forward of said turbine nozzle to define a forward cavity therebetween; a second stage rotor disk disposed aft of said turbine nozzle to define an aft cavity therebetween; and said bypass tubes extend through said inner band in flow communication with said forward cavity for discharging said pressurized air channeled therethrough. 29. An engine according to claim 28 wherein said inner band includes an inner manifold disposed in flow communication with said bypass tubes, and said inner manifold includes a row of discharge holes facing said forward cavity. 30. A method of cooling a turbine nozzle in a gas turbine engine having a row of hollow nozzle vanes extending radially between outer and inner bands and disposed axially between first and second turbine rotor disks comprising: channeling pressurized purge air from a compressor in said engine radially through said vanes to purge forward and aft cavities located between said nozzle inner band and said first and second disks, respectively; channeling pressurized cooling air from said compressor and inside said vanes to cool said vanes independently from said purge air; and modulating flowrate of said cooling air inside said vanes without modulating flowrate of said purge air through said vanes. 31. A method according to claim 30 further comprising channeling said purge air and cooling air from said compressor in parallel flowpaths through said vanes isolated from each other through said outer band. 32. A method according to claim 31 wherein: said purge air is channeled directly through said outer band to purge said forward and aft cavities; and said cooling air is first channeled in impingement against said outer band for impingement cooling thereof followed in turn by routing into said vanes for internal impingement cooling thereof.

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 16

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

Modulated flow turbine nozzle

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 16

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

Modulated flow turbine nozzle

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 16

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼