|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3931 ; 60/2261|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 14 인용 특허 : 0|
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...
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 ...