[특허]Gas turbine engine controls for minimizing combustion dynamics and emissions

[미국특허] Gas turbine engine controls for minimizing combustion dynamics and emissions 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02M-063/02
출원번호	US-0039183 (2008-02-28)
등록번호	US-8504276 (2013-08-06)
발명자 / 주소	Martling, Vincent C. So, Peter Xiao, Zhenhua Ricklin, Plazi
출원인 / 주소	Power Systems Mfg., LLC
대리인 / 주소	Shook, Hardy & Bacon L.L.P.
인용정보	피인용 횟수 : 1 인용 특허 : 19

초록 ▼

Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.

대표청구항 ▼

1. A method of controlling a gas turbine engine having a compressor, at least one combustor, a turbine, and a control system comprising: measuring a compressor inlet temperature;calculating a turbine reference temperature as a function of at least compressor discharge pressure, exhaust pressure, and pressure across the combustor;selecting a baseline fuel schedule for a fuel circuit corresponding to the turbine reference temperature;determining whether a baseline fuel split corresponds to the turbine reference temperature;determining a bias parameter so as to increase or decrease the baseline fuel split wherein the bias parameter is a percentage change in fuel split that varies as a function of the measured compressor inlet temperature for a given turbine reference temperature; and,adjusting the fuel flow for the fuel circuit to a sum of the baseline fuel split and the bias parameter. 2. The method of claim 1, further comprising the step of interpolating the baseline fuel split from two known fuel splits associated with two known turbine reference temperatures listed in the baseline fuel schedule if the calculated turbine reference temperature is not listed in the baseline fuel schedule. 3. The method of claim 1, further comprising the step of interpolating the bias parameter from two known compressor inlet temperatures. 4. The method of claim 1, wherein the bias parameter varies for each turbine reference temperature. 5. The method of claim 1, wherein the combustor has fuel splits determined for four fuel circuits. 6. The method of claim 1, wherein the bias parameter results in an increase, a decrease, or no change to the fuel split. 7. A gas turbine engine comprising: an inlet;a compressor;at least one combustor having at least two fuel circuits;a turbine; and,a control system having a processor and a memory component containing a series of computer-readable instructions that measures a compressor inlet temperature in real-time and calculates a turbine reference temperature that is a function of at least compressor discharge pressure, exhaust pressure and pressure across the combustor, wherein the compressor inlet temperature and turbine reference temperature are utilized to identify a fuel split for each fuel circuit of the combustor with each fuel split biased higher or lower based on measured compressor inlet temperature. 8. The gas turbine engine of claim 7, wherein the fuel split is a percentage of an available fuel balance. 9. The gas turbine engine of claim 7, wherein the computer-readable instructions consult look-up tables and interpolate between listed values in order to identify an optimal fuel split for a given compressor inlet temperature and turbine reference temperature.

이 특허에 인용된 특허 (19) 인용/피인용 타임라인 분석

Williams, Darrell R., Compressor inlet guide vane flow based anti-ice formation control system and method.
상세보기
Rajamani Ravi (Schenectady NY) Norman Bruce G. (Charlton NY), Coordinated fuel-air controller for gas turbine without load feedback.
상세보기
Myers, Gerald A.; Little, David A., Engine brake for part load CO reduction.
상세보기
Solomons, Keith E.; Mahakul, Budhadeb; Islam, Rafiqul; Liu, Chih L.; Silvers, Bradley S.; Martin, Le Blanc, Engine emission control system and method.
상세보기
Tim Keller ; Mohamad Vhora ; Dan Burnes ; John Lipinski, Fuel control method for gas turbine.
상세보기
Donnelly Brian G. (Suffield CT) Dyer Gerald P. (Enfield CT) Wiesner Charles E. (Glastonbury CT), Fuel splitter valve assembly for gas turbine.
상세보기
Beebe Kenneth W. (Schenectady NY) Davis L. Berkly (Schenectady NY) Iasillo Robert J. (Schenectady NY), Fuel trim system for a multiple chamber gas turbine combustion system.
상세보기
Hironori Muramatsu JP, Gas turbine aeroengine control system.
상세보기
Sato Isao (Hitachi JPX) Hirose Fumiyuki (Hitachi JPX) Takaba Minoru (Hitachi JPX) Shimura Akira (Hitachi JPX) Takahashi Shoei (Hitachi JPX) Ikeda Hiraku (Hitachinaka JPX), Gas turbine control method and apparatus.
상세보기
Maeda Fukuo,JPX ; Iwai Yasunori,JPX ; Sato Yuzo,JPX, Gas turbine multi-stage combustion system.
상세보기
Gadde, Satish; Gordon, Thomas J., Gas turbine pilot burner water injection and method of operation.
상세보기
Gadde, Satish; Holm, Richard; Harrison, Chris, Humidity compensation for combustion control in a gas turbine engine.
상세보기
Kothnur,Vasanth Srinivasa; Ali,Mohamed Ahmed; Vandale,Daniel Doyle; Roberts,Matthew Eugene, Method and apparatus for actuating fuel trim valves in a gas turbine.
상세보기
Fletcher,Paul; Walsh,Philip P, Method and system for controlling fuel supply in a combustion turbine engine.
상세보기
Steber, Charles Evan; Parisay, Massoud; Annigeri, Ravindra; Ziminsky, Willy Steve; Henderson, John Stephen, Method for operating gas turbine engine systems.
상세보기
Andrew Philip Lynn ; Marks Paul Thomas ; Dwyer Daniel Robert ; Stampfli John David ; Cotroneo Joseph Anthony ; Miller Harold Edward ; Wesorick Ronald Richard, Method of operation of industrial gas turbine for optimal performance.
상세보기
Ziminsky, Willy Steve; Fossum, Arthur James, Methods and systems for operating a gas turbine.
상세보기
Tomlinson, Leroy O.; Garry, Robert S., System and method for determining gas turbine firing and combustion reference temperatures having correction for water content in fuel.
상세보기
Tomlinson, Leroy O.; Garry, Robert S., System for determining gas turbine firing and combustion reference temperature having correction for water content in combustion air.
상세보기

이 특허를 인용한 특허 (1) 인용/피인용 타임라인 분석

Prociw, Lev Alexander, Automatic control of turbine blade temperature during gas turbine engine operation.
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.

내보내기 메뉴

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

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

AI-Helper ※ AI-Helper는 을 사용합니다.

AI-Helper

안녕하세요, AI-Helper입니다. 좌측 "선택된 텍스트"에서 텍스트를 선택하여 요약, 번역, 용어설명을 실행하세요.
※ AI-Helper는 부적절한 답변을 할 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

연합인증

[미국특허] Gas turbine engine controls for minimizing combustion dynamics and emissions 원문보기