[특허]Aircraft gas turbine engine backbone deflection control

General Electric Company

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

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

특허 상세정보

MyON담기

내보내기

Aircraft gas turbine engine backbone deflection control

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/20
미국특허분류(USC)	060/039.31; 060/039.32; 244/054
출원번호	US-0985776 (1992-12-04)
발명자 / 주소	Brantley, James W.
출원인 / 주소	General Electric Company
대리인 / 주소	Squillaro, Jerome C.Rafter, John R.
인용정보	피인용 횟수 : 13 인용 특허 : 5

초록
▼

A gas turbine engine backbone deflection control apparatus to counter the effects of backbone bending due to gust, thrust. and maneuver loads by introducing a controlled backbone counter-bending moment by applying controlled tensioning forces only between axially spaced apart frames connected by the backbone. One embodiment of the invention, for a high bypass ratio turbofan engine, provides a hydraulically powered actuator to produce tensioning forces in cables connected between a fan frame and a turbine frame and the actuator is controlled by the engine...

대표
청구항
▼

1. A backbone counter-bending control apparatus for an aircraft gas turbine engine, said apparatus comprising: a backbone counter-bending moment means for applying tensioning forces only throughout the operating range of the aircraft gas turbine engine between axially spaced apart forward and aft frames that are connected by a backbone structure and a control means for controlling the amount of tensioning forces produced by aid backbone counter-bending moment means. 2. An apparatus as claimed in claim 1 wherein said backbone counter-bending moment means further comprises a passive actuating means. 3. An apparatus as claimed in claim 2 wherein said passive actuating means further comprises: a radially inner cable pivotably connected at one of its ends at a radially inner point on one of said frames and at its other end to a first lever end point on a first end of a pivotable lever, said pivotable lever intermediately pivotable at a lever pivot point at which said lever is pivotably connected to said other of said frames, a radially outer cable pivotably connected at one of its ends at a radially outer point on said one of said frames at a point radially outward of said radially inner point, said radially outer cable pivotably connected at its other end to a second lever end point on a second end of said lever. 4. An apparatus as claimed in claim 3 wherein said passive actuating means further comprises: a first lever arm distance L1 between said first lever end point and said lever pivot point, a second lever arm distance L2 between said second lever end point and said lever pivot point, and control of the backbone counter-bending moment to counter the case deflection is effectuated by providing a ratio L1/L2 corresponding to a predetermined case deflection flight mission. 5. An apparatus as claimed in claim 1 wherein said backbone counter-bending moment means further comprises a powered actuator. 6. An apparatus as claimed in claim 5 wherein said actuator is powered by one of the following group: hydraulic power, electric power, and pneumatic power. 7. An apparatus as claimed in claim 5 wherein said control means is an engine control operably connected to a sensor that is operable to generate at least one control input signal for said engine control wherein said input signal is indicative of backbone bending. 8. An apparatus as claimed in claim 7 wherein said input signal is at least one of a plurality of backbone bending indicative signals, said plurality of backbone bending signals including one that measures inlet moment load and others that measure blade tip clearances. 9. An apparatus as claimed in claim 8 further comprising: said powered actuator pivotably mounted at one of its ends to one of said frames and at its other end to a first end of a pivotable lever, said pivotable lever intermediately pivotable at a lever pivot point at which said lever is pivotably connected to one end of a first cable, said first cable pivotably connected at its other end to other of said frames, a second end of said lever is pivotably attached to one end of a second cable, and said second cable is pivotably connected at its other end to said one of said frames. 10. An apparatus as claimed in claim 9 wherein said axially spaced apart forward and aft frames comprise a fan frame and turbine frame respectively. 11. An apparatus as claimed in claim 10 wherein said control means is an aircraft gas turbine engine electronic control. 12. An apparatus as claimed in claim 11 wherein said powered actuator is hydraulically powered. 13. A backbone counter-bending control apparatus for an aircraft gas turbine engine, said apparatus comprising: a backbone counter-bending moment means for applying tensioning forces only between axially spaced apart forward and art frames that are connected by a backbone structure and a control means for controlling the amount of tensioning forces produced by said backbone counter-bending moment means, wherein said backbone counter-bending moment means further comprises a powered actuator. 14. A backbone counter-bending control apparatus for an aircraft gas turbine engine, said apparatus comprising: a backbone counter-bending moment means for applying tensioning forces only between axially spaced apart forward and aft frames that are connected by a backbone structure and a control means for controlling the amount of tensioning forces produced by said backbone counter-bending moment means, wherein said backbone counter-bending moment means further comprises a passive actuating means, wherein said passive actuating means further comprises: a radially inner cable pivotably connected at one of its ends at a radially inner point on one of said frames and at its other end to a first lever end point on a first end of a pivotable lever, said pivotable lever intermediately pivotable at a lever pivot point at which said lever is pivotably connected to said other of said frames, a radially outer cable pivotably connected at one of its ends at a radially outer point on said one of said frames at a point radially outward of said radially inner point, said radially outer cable pivotably connected at its other end to a second lever end point on a second end of said lever.

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 13

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

특허 상세정보

Aircraft gas turbine engine backbone deflection control

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

Aircraft gas turbine engine backbone deflection control

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼