|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 : 10 인용 특허 : 84|
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: sensing an operable condition of an aircraft; andpassing air between a selected one of a plurality of interior nacelle volumes and a nacelle exterior region via holes connecting the selected interior nacelle volume and the nacelle exterior region in response to the sensed operable condition to alter an air pressure at the nacelle exterior region, wherein the holes are arranged to selectively pass air out of the selected one of the plurality of int...