$\require{mediawiki-texvc}$
  • 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"

특허 상세정보

Turbofan gas turbine engine and mountings therefore

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/062   
미국특허분류(USC) 60/3931 ; 60/2261
출원번호 US-0035865 (1987-04-08)
우선권정보 GB-0008659 (1986-04-09)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 14  인용 특허 : 0
초록

The present invention relates to turbofan gas turbine engines in which the fan assembly is positioned downstream of the core engine of the turbofan gas turbine engine i.e. an aft fan turbofan. Conventional turbofan engines have the fan assembly positioned upstream of the core engine, and the core engine is mounted onto an aircraft pylon. The fan casing is then carried by the core engine. This arrangement in an aft fan would result in losses and intake distortions under side winds and aircraft yaw. The aft fan turbofan has a core engine and a fan assembly...

대표
청구항

A turbofan gas turbine engine comprising: a core engine which includes compressor means, combustor means, turbine means, and a core casing, a fan assembly positioned downstream of the core engine and including at least one fan, the at least one fan operating within a fan duct defined in part by a fan casing, the fan casing having an integral deep section support ring, upstream support means extending from the fan casing to the core engine casing to support the core engine from the fan casing, downstream support means extending from the fan casing to the ...

이 특허를 인용한 특허 피인용횟수: 14

  1. Gall, Pierre-Emmanuel; Cros, Christophe. Aircraft having reduced environmental impact. USP2012068196860.
  2. Eleftheriou, Andreas; Denis, David; Leclair, Denis; Roussel, Yves. Gas turbine engine case and method of making. USP2010097797922.
  3. Heyerman, Jeffrey Bernard; Olver, Bryan W.. Support links with lockable adjustment feature. USP2016029267435.
  4. Heyerman, Jeffrey Bernard; Olver, Bryan W.. Support links with lockable adjustment feature. USP2013108567202.
  5. Eleftheriou, Andreas; Lobo, Kevin Walter; Weinberg, Maurice; Liu, Quantai. Turbofan case and method of making. USP2010087770378.
  6. Eleftheriou, Andreas; Lobo, Kevin Walter; Weinberg, Maurice; Liu, Quantai. Turbofan case and method of making. USP2010097793488.
  7. Eleftheriou, Andreas; Lobo, Kevin Walter; Weinberg, Maurice; Liu, Quantai. Turbofan case and method of making. USP2010087765787.
  8. Eleftheriou, Andreas; Lobo, Kevin Walter; Weinberg, Maurice; Liu, Quantai. Turbofan case and method of making. USP2010067739866.
  9. Eleftheriou, Andreas; Lobo, Kevin Walter; Weinberg, Maurice; Liu, Quantai. Turbofan case and method of making. USP2009077565796.
  10. Eleftheriou,Andreas; Lobo,Kevin Walter; Weinberg,Maurice; Liu,Quantai. Turbofan case and method of making. USP2007097266941.
  11. Heyerman, Jeffrey Bernard; Olver, Bryan; Caulfeild, Stephen. Turbofan mounting arrangement. USP2015038979491.
  12. Heyerman, Jeffrey Bernard; Olver, Bryan W.; Fielding, Bruce; Smythe, Carl. Turbofan mounting system. USP2012118313293.
  13. Watson, Bill Russell; Warden, Max. Turbomachine core coupling assembly. USP2014018621874.
  14. Baughman, John Lewis; Eheart, Raymond. Variable-cycle gas turbine engine with front and aft FLADE stages. USP2015049016041.