|국가/구분||United States(US) Patent 등록|
|국제특허분류(IPC7판)||B64D-033/02 B64C-021/04 B64C-021/06|
|미국특허분류(USC)||244/053B; 244/207; 244/208|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 5 인용 특허 : 88|
A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A flow volume is spaced between the first surface and the second surface. A plurality of holes are disposed on the cowl. Each of the plurality of holes are configured to alter local air pressure about one of the first surface and the second surface of the cowl. The plurality of holes are in communication with the flow volume.
1. A method of altering air pressure on a surface of a nacelle assembly, the method comprising the steps of: (a) sensing an operable condition of an aircraft;(b) selecting between increasing local air pressure and decreasing local air pressure at the nacelle surface of the nacelle assembly through a plurality of holes on said nacelle surface based on the sensed operable condition; and(c) decreasing air flow at a first area of the nacelle surface and increasing airflow at a second area of the nacelle surface, the first area different from the second area,...