|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/226R ; 60/244 ; 415/153A ; 137/862|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 9 인용 특허 : 1|
A variable ratio bypass turbojet engine comprising a front fan core engine and a forward fan connected thereto by an inverter valve arrangement which comprises a fixed forward duct system and a fixed after duct system selectively shaped and joined by flapper valve mechanism. The flapper valve mechanism may be actuated so that the bypass ratio of the engine can be varied to produce a low bypass ratio engine during cruise operation mode wherein the front fan air is conducted to the core engine fan and the auxiliary inlet air is discharged overboard, or to ...
A variable bypass ratio turbojet engine including: A. a front fan mounted for rotation about the engine axis, B. an annularly shaped auxiliary inlet concentrically enveloping said front fan, C. an engine fan concentrically enveloping said engine axis in spaced axial relation downstream of said front fan, D. an annular thrust nozzle enveloping said engine fan and concentric therewith, E. an annular inverter valve system concentric about the engine axis and positioned between said forward fan and auxiliary inlet and said engine fan and thrust nozzle so as ...