|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/2261 ; 60/2263|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 76 인용 특허 : 0|
An aircraft turbofan engine and method of operation effect variable specific thrust. The engine includes a fan disposed in a fan casing and a booster compressor disposed in a first flow splitter and powered by a core engine. A second flow splitter is disposed inside the fan casing and defines fan outer and inner ducts. The booster compressor includes at least one stage of rotor blades each having a shroud and an integral rotor flade extending radially outwardly therefrom into the fan inner duct. The fan outer duct includes a variable area first exhaust n...
A turbofan gas turbine engine comprising: a fan disposed in a fan casing defining an annular fan duct for receiving fan air compressed by said fan; a booster compressor disposed in an annular first flow splitter and in serial flow communication with said fan; a second compressor disposed in an inner casing and in flow communication with said booster compressor, said inner casing extending aft of said first splitter and coextensively therewith; a combustor disposed in said inner casing and in flow communication with said second compressor; a high pressure...