|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/053B ; 181/214|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 51 인용 특허 : 9|
Boundary layer separation at the boundary surface of an intake duct (18) of a turbofan aeroengine nacelle (12) at conditions of high incidence and high engine mass flow arises from shockwave induced pressure gradients in the boundary layer. To control separation, gaseous fluid is withdrawn from a high pressure region of the boundary layer at a downstream region of the boundary surface, conveyed within the intake duct structure (19) and discharged at an upstream region of the boundary surface into a low pressure region of the boundary layer. The intake du...
[ What is claimed is:] [1.] An aeroengine nacelle structure including an intake duct, comprisinga lipskin defining an intake throat leading into the intake duct and including a noise attenuation panel having a facing component part with a front face which forms a boundary surface of the intake duct and which is subjected to fluid flow over it in a boundary layer adjacent the boundary surface, the facing component part of the noise attenuation panel having a plurality of flow apertures which extend through the facing component part at a downstream region ...