|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/2261 ; 60/3931|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 15 인용 특허 : 0|
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...
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...