[특허]Gas turbine engine speed control system and method during maximum fuel flow

Honeywell International Inc.

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

Gas turbine engine speed control system and method during maximum fuel flow

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/057 F02C-009/54
미국특허분류(USC)	060/039.27; 060/039.23; 060/793
출원번호	US-0189252 (2011-07-22)
등록번호	US-8850790 (2014-10-07)
발명자 / 주소	McLeister, Larry Moeckly, Kevin Hancock, Ammon
출원인 / 주소	Honeywell International Inc.
대리인 / 주소	Ingrassia Fisher & Lorenz P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 11

초록
▼

Methods and apparatus are provided for selectively controlling the rotational speed of a gas turbine engine that drives a load compressor having movable inlet guide vanes and that is coupled to receive fuel at a fuel flow rate up to a maximum fuel flow rate. The rotational speed of the gas turbine engine, and the fuel flow rate to the gas turbine engine, are both sensed. If the sensed rotational speed of the gas turbine engine is less than a predetermined value and the sensed fuel flow rate to the gas turbine engine equals or exceeds the maximum fuel flo...

대표
청구항
▼

1. A method of selectively controlling rotational speed of a gas turbine engine that drives a load compressor having movable inlet guide vanes, the gas turbine engine coupled to receive fuel at a fuel flow rate up to a maximum fuel flow rate, the method comprising the steps of: sensing the rotational speed of the gas turbine engine;sensing the fuel flow rate to the gas turbine engine; andcontrolling a position of the inlet guide vanes to reduce load compressor mechanical load on the gas turbine engine when (i) the sensed rotational speed of the gas turbine engine is less than a predetermined value and (ii) the sensed fuel flow rate to the gas turbine engine equals or exceeds the maximum fuel flow rate. 2. The method of claim 1, further comprising: receiving a speed command representative of a commanded rotational speed of the gas turbine engine; andselectively modulating the position of the inlet guide vanes to control the rotational speed of the gas turbine engine to the commanded rotational speed. 3. The method of claim 1, further comprising: moving the inlet guide vanes to a position that causes the sensed fuel flow rate to be less than the maximum fuel flow rate. 4. The method of claim 3, further comprising: receiving a speed command representative of a commanded rotational speed of the gas turbine engine; andcontrolling the fuel flow rate to the gas turbine engine to control the rotational speed of the gas turbine engine to the commanded rotational speed. 5. The method of claim 1, further comprising: receiving historical engine operational data;processing at least the historical engine operational data to predict whether the sensed fuel flow rate to the gas turbine engine will equal the maximum fuel flow rate simultaneous with the sensed rotational speed of the gas turbine engine being less than the predetermined value; andestablishing a maximum position limit for the inlet guide vanes that will prevent the sensed fuel flow rate to the gas turbine engine from being equal to the maximum fuel flow rate simultaneous with the sensed rotational speed of the gas turbine engine being less than the predetermined value. 6. The method of claim 1, wherein the step of sensing the fuel flow rate to the gas turbine engine comprises directly sensing fuel flow rate using a flow rate sensor. 7. The method of claim 1, wherein the step of sensing the fuel flow rate to the gas turbine engine comprises indirectly sensing fuel flow rate based on a position of a flow control valve. 8. A compressor inlet guide vane control system, comprising: a gas turbine engine for receiving fuel at a fuel flow rate up to a maximum fuel flow rate;a load compressor coupled to, and mechanically loading, the gas turbine engine, the load compressor including a plurality of movable inlet guide vanes;a rotational speed sensor configured to sense gas turbine engine rotational speed and supply a rotational speed signal representative thereof;a fuel flow sensor configured to sense fuel flow rate to the gas turbine engine and supply a fuel flow rate signal representative thereof; anda control coupled to receive the rotational speed signal and the fuel flow rate signal, the control configured, upon receipt of the rotational speed signal and the fuel flow rate signal, to control inlet guide vane position to reduce load compressor load on the gas turbine engine when (i) the gas turbine engine rotational speed is less than a predetermined value and (ii) the fuel flow rate equals or exceeds the maximum fuel flow rate. 9. The system of claim 8, wherein: the control is further coupled to receive a speed command representative of a commanded rotational speed of the gas turbine engine; andthe control is further configured to selectively modulate the position of the inlet guide vanes to control the rotational speed of the gas turbine engine to the commanded rotational speed. 10. The system of claim 8, wherein the control is further configured to move the inlet guide vanes to a position that causes the sensed fuel flow rate to be less than the maximum fuel flow rate. 11. The system of claim 10, wherein: the control is further coupled to receive a speed command representative of a commanded rotational speed of the gas turbine engine; andthe control is further configured to control the fuel flow rate to the gas turbine engine to control the rotational speed of the gas turbine engine to the commanded rotational speed. 12. The system of claim 8, further comprising memory in operable communication with the control and having historical engine operational data stored therein, wherein the control is further configured to: selectively retrieve the historical engine operation data from the memory;process at least the historical engine operational data to predict whether the sensed fuel flow rate to the gas turbine engine will equal the maximum fuel flow rate simultaneous with the sensed rotational speed of the gas turbine engine being less than the predetermined value; andestablish a maximum position limit for the inlet guide vanes that will prevent the sensed fuel flow rate to the gas turbine engine from being equal to the maximum fuel flow rate simultaneous with the sensed rotational speed of the gas turbine engine being less than the predetermined value. 13. The system of claim 8, wherein: the control is further configured to supply position commands representative of a commanded inlet guide vane position; andthe system further comprises an inlet guide vane actuator coupled to the inlet guide vanes and coupled to receive the position commands, the inlet guide vane actuator configured, upon receipt of the position commands, to move the inlet guide vanes to the commanded inlet guide vane position. 14. The system of claim 8, wherein the fuel flow sensor is configured to directly sense the fuel flow rate to the gas turbine engine. 15. The system of claim 8, further comprising: a fuel metering valve coupled to receive valve position commands from the control and configured, upon receipt of the valve position commands, to control the fuel flow rate to the gas turbine engine; anda valve position sensor coupled to the fuel metering valve, the valve position sensor configured to sense a position of the fuel metering valve and supply valve position signals representative thereof. 16. The system of claim 15, wherein: the fuel flow sensor is configured to indirectly sense the fuel flow rate to the gas turbine engine; andthe fuel flow sensor comprises the valve position sensor.

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 1

Unnikrishnan, Sunil; Minto, Karl Dean; Pobbati, Omprakash. System and method for model based turbine shaft power predictor. USP20180710033316.

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

Gas turbine engine speed control system and method during maximum fuel flow

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 1

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

Gas turbine engine speed control system and method during maximum fuel flow

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (11)

이 특허를 인용한 특허 피인용횟수: 1

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼