|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/2261 ; 416/245R|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 54 인용 특허 : 0|
A gas turbine engine has a forward rotor, a row of fan blades radially extending from the rotor, and a core turbine engine located rearwardly of the fan blades and rotor and coupled to the rotor for rotatably driving the rotor. An outer annular nacelle surrounds the rotor, fan blades and core engine. An inner annular splitter fairing is disposed rearwardly of the fan blades, surrounds the core engine, and is spaced radially inwardly from the nacelle so as to define therebetween a bypass air flow duct located outwardly from the core engine and rearwardly ...
In a gas turbine engine having a forward rotor, a row of circumferentially spaced fan blades attached to and extending radially outward from said rotor, a core turbine engine located rearwardly of said fan blades and rotor and being coupled to said rotor for rotatably driving said rotor, an outer annular nacelle surrounding said rotor, fan blades, and core engine, and an inner annular splitter fairing disposed rearwardly from said fan blades, surrounding said core engine and spaced radially inwardly from said nacelle so as to define therebetween a bypass...