|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||F02C-007/20 B64D-027/18 B64D-027/26|
|미국특허분류(USC)||244/54 ; 60/3931 ; 248/554|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 160 인용 특허 : 0|
A nacelle and mounting arrangement for a high bypass ratio ducted fan aircraft engine mounted external to the aircraft main structure is disclosed. The nacelle and mounting arrangement isolate the engine from the adverse effects of certain aerodynamic forces acting on the nacelle by transferring substantially all of those forces directly from the nacelle to the aircraft and transferring substantially none of those forces to the engine. Various arrangements of the nacelle components which facilitate engine removal while avoiding the placement of nacelle c...
For an aircraft ducted fan engine with a core section bounded by a core case and enclosed within a core cowl, a fan section of larger diameter than said core section secured to and concentric with said core section and bounded by a fan case having a fan duct outer wall downstream thereof, said fan duct outer wall and said core cowl defining an axially extending fan duct terminating at a fan duct discharge plane for conducting a fan flow stream essentially axially, a nacelle and mounting arrangement for mounting said engine on an aircraft, with said aircr...