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특허 상세정보

Torque link fan jet engine support for reducing engine bending

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-003/02   
미국특허분류(USC) 60/2261 ; 60/3931
출원번호 US-0719255 (1991-06-21)
발명자 / 주소
출원인 / 주소
인용정보 피인용 횟수 : 15  인용 특허 : 0
초록

A support system for the aft end of fan jet gas turbine engines which reduces engine bending in operation while accommodating radial and longitudinal thermal expansion forces. A plurality of inwardly extending small flanges are provided on a first ring, which may form part of the engine core cowl, that is secured to the pylon supporting the overall engine. A plurality of outwardly extending small flanges are provided on a second ring, which is secured to, or otherwise forms a part of, the engine. These flanges are spaced in adjacent pairs, one on each ri...

대표
청구항

In a fan jet type gas turbine engine having an engine nacelle secured to an aircraft pylon, an engine core within said nacelle housed in a structural core cowl and secured at its forward end to said pylon, the improvement comprising: a substantially fully annular core cowl ring forming part of the core cowl and surrounding the aft end of the engine core and positioned transverse to the engine\s longitudinal centerline; mount means securing said cowl ring to the engine pylon near the aft end of the core cowl; a plurality of circumferentially arranged inwa...

이 특허를 인용한 특허 피인용횟수: 15

  1. Journade, Frédéric; Jalbert, Delphine. Aircraft engine assembly comprising a turbojet engine with reinforcing structures connecting the fan casing to the central casing. USP2014118881536.
  2. Journade, Frédéric; Jalbert, Delphine. Aircraft engine assembly comprising an annular load-transfer structure surrounding the central casing of a turbojet engine. USP2014058733693.
  3. Journade, Frédéric; Lafont, Laurent; Jalbert, Delphine. Engine assembly for an aircraft comprising attachments for engines offset below on the fan frame. USP2015059032740.
  4. Lafont, Laurent. Engine assembly for an aircraft the engine attachment strut of which includes a structural case forming an internal radial delimitation of the secondary flow. USP2014028646725.
  5. Cass, Michael F.; Elder, James S.; Merry, Brian D.; Suciu, Gabriel L.; Dye, Christopher M.. Gas turbine engine with stacked accessory components. USP2017119816441.
  6. Todorovic, Predrag. Joint between components. USP20180810054007.
  7. Philippart, Olivier. Motor stand of a primary motor-driven pump unit of a pressurized water nuclear reactor. USP2016039281084.
  8. Heyerman, Jeffrey Bernard; Olver, Bryan W.. Support links with lockable adjustment feature. USP2016029267435.
  9. Heyerman, Jeffrey Bernard; Olver, Bryan W.. Support links with lockable adjustment feature. USP2013108567202.
  10. Barnes, Emily; Chouard, Pierre-Alain Jean-Marie Philippe Hugues. Suspension for an engine on an aircraft strut including a suspension arch. USP2015119193467.
  11. Alexander, Eric J.. System and method for aft mount of gas turbine engine. USP2018069988155.
  12. Heyerman, Jeffrey Bernard; Olver, Bryan; Caulfeild, Stephen. Turbofan mounting arrangement. USP2015038979491.
  13. Heyerman, Jeffrey Bernard; Olver, Bryan W.; Fielding, Bruce; Smythe, Carl. Turbofan mounting system. USP2012118313293.
  14. Riviere, Thomas Gérard Daniel; Bellabal, François Robert; Renon, Olivier; Seize, Guilhem. Turbojet engine cold stream flow path suspended from the exhaust case by radial crevice mounts and link rods. USP2017119828877.
  15. Watson, Bill Russell; Warden, Max. Turbomachine core coupling assembly. USP2014018621874.