|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/110B ; 244/130 ; 244/204|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 4|
An aircraft propulsive power unit having an engine (20), a nacelle structure (12) which houses the engine (20) and which has an exterior low drag boundary surface (16) which is subjected to exterior air flow in a boundary layer adjacent the boundary surface (16) and an air flow disruption device (19) activatable to cause at a control location in the boundary surface disruption of exterior air flow in the boundary layer at the control location without reversal or deflection of engine thrust gaseous flow. Where the power unit is a turbofan and the nacelle ...
[ What is claimed is:] [1.] An aircraft propulsive power unit comprising a core engine and a fan driven by the core engine, a nacelle structure which (i) houses the core engine and fan, (ii) has an exterior low drag boundary surface which extends from an upstream region to a downstream trailing edge region and which is subjected to exterior air flow in a boundary layer adjacent the boundary surface and (iii) includes an annular fan duct (a) within which the fan is mounted, (b) through which air from the fan is conveyed, and (c) which has inner and outer ...