[특허]Controlled pilot oxidizer for a gas turbine combustor

[미국특허] Controlled pilot oxidizer for a gas turbine combustor 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-009/00
출원번호	UP-0173655 (2005-07-01)
등록번호	US-7752850 (2010-08-02)
발명자 / 주소	Laster, Walter R. Bandaru, Ramarao V.
출원인 / 주소	Siemens Energy, Inc.
인용정보	피인용 횟수 : 91 인용 특허 : 29

초록 ▼

A combustor (22) for a gas turbine (10) includes a main burner oxidizer flow path (34) delivering a first portion (32) of an oxidizer flow (e.g., 16) to a main burner (28) of the combustor and a pilot oxidizer flow path (38) delivering a second portion (36) of the oxidizer flow to a pilot (30) of the combustor. The combustor also includes a flow controller (42) disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot.

대표청구항 ▼

We claim: 1. A combustor for a gas turbine comprising: a main burner oxidizer flow path delivering a first portion of an oxidizer flow to a main burner of a gas turbine combustor; a pilot oxidizer flow path delivering a second portion of the oxidizer flow to a pilot of the combustor; a flow controller disposed in the pilot oxidizer flow path for controlling an amount of the second portion delivered to the pilot; a pilot fuel flow for delivering fuel to the pilot; and a flow controller actuator controlling a position of the flow controller responsive to an operating condition of the gas turbine; wherein the flow controller comprises a plurality of maintainable open positions between a fully opened state and a fully closed state; and wherein the position of the flow controller is correlated with the amount of fuel to the pilot; and wherein the flow controller actuator is configured to selectively reduce the amount of the second portion delivered to the pilot via maintenance of a position of the flow controller at one of the plurality of maintainable open positions between the fully opened state and the fully closed state as an amount of fuel delivered to the pilot is reduced. 2. The combustor of claim 1, wherein the main burner oxidizer flow path comprises a catalytic module. 3. The combustor of claim 1, wherein the flow controller actuator is configured to control the position of the flow controller in response to an operating condition of the gas turbine. 4. The combustor of claim 3, wherein the operating condition comprises a load on the gas turbine. 5. The combustor of claim 3, further comprising a processor receiving a signal indicative of the operating condition and generating a command to control the flow controller actuator responsive to the signal. 6. The combustor of claim 1, wherein the flow controller actuator comprises a hydraulically operated mechanism. 7. The combustor of claim 1, wherein the flow controller actuator comprises a pneumatically operated mechanism. 8. The combustor of claim 1, wherein the flow controller further comprises a biasing mechanism to return the flow controller to the fully opened state in the absence of a flow controller actuating force acting to position the flow controller away from the fully opened state. 9. The combustor of claim 1, wherein the oxidizer flow comprises a combustible fuel. 10. The combustor of claim 1, wherein the flow controller comprises a valve selected from the group consisting of a gate valve, a butterfly valve, a ball valve, and a spool valve. 11. A gas turbine engine comprising the combustor of claim 1. 12. The combustor of claim 1 used to implement a method of controlling combustion comprising: delivering the first portion to the main burner; delivering the second portion of the oxidizer flow to the pilot; and controlling an amount of the second portion delivered to the pilot. 13. A method of controlling combustion in a gas turbine comprising: delivering a first portion of an oxidizer flow to a main burner of a gas turbine combustor; delivering a second portion of the oxidizer flow to a pilot of the combustor; controlling an amount of the second portion delivered to the pilot; delivering an amount of fuel to the pilot; and controlling an amount of oxidizer delivered to the pilot via a flow controller comprising a plurality of maintainable open positions between a fully opened state and a fully closed state; wherein the position of the flow controller is correlated with the amount of fuel to the pilot; and wherein the controlling an amount of the second portion delivered to the pilot comprises selectively reducing the amount of the oxidizer flow delivered to the pilot via maintaining a position of the flow controller at one of the plurality of maintainable open positions between the fully opened state and the fully closed state as the amount of fuel delivered to the pilot is reduced. 14. The method of claim 13, further comprising controlling the amount of the second portion delivered to the pilot responsive to an operating condition of the gas turbine. 15. The method of claim 14, wherein the operating condition comprises a load on the gas turbine. 16. The method of claim 13, wherein the flow controller is disposed in a pilot oxidizer flow path conducting the second portion of the oxidizer flow, and wherein controlling the amount of the second portion delivered to the pilot comprises controlling the position of the flow controller disposed in the pilot oxidizer flow path. 17. The method of claim 16, further comprising positioning the flow controller in the fully opened state to provide an amount of the second portion delivered to the pilot comprising about 10% to 2% of the oxidizer flow. 18. The method of claim 16, further comprising positioning the flow controller in the fully opened state to provide an amount of the second portion delivered to the pilot comprising about 7% to 5% of the oxidizer flow. 19. The method of claim 16, further comprising positioning the flow controller in the fully closed state to provide an amount of the second portion delivered to the pilot comprising about 0.75% to 0.25% of the oxidizer flow. 20. The method of claim 16, further comprising positioning the flow controller in the fully closed state to provide an amount of the second portion delivered to the pilot comprising about 0.6% to 0.4% of the oxidizer flow to the pilot. 21. The method of claim 13, wherein the main burner comprises a catalytic combustion module. 22. The method of claim 13, further comprising simultaneously allowing flow of the oxidizer flow to each of the main burner and the pilot. 23. The combustor of claim 1, wherein the flow controller is configured to simultaneously enable flow of the first portion to the main burner oxidizer flow path and flow of the second portion to the pilot oxidizer flow path.

이 특허에 인용된 특허 (29) 인용/피인용 타임라인 분석

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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

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