Patent ID: 9004399
Filing Date: 2015-04-14
Classification: B64D,Y10T

Abstract:
1. A nacelle assembly for a turbine engine, comprising: a cowl for the turbine engine, said cowl extending along an axis wherein at least a portion of said cowl is axially forward of a fan of the turbine engine, said cowl having a first surface spaced from a second surface, said second surface configured to define a bypass flow passage radially inward of said second surface; a flow volume spaced between said first surface and said second surface; a plurality of holes disposed on said first surface and said second surface of the cowl and arranged to communicate air outside the nacelle assembly into said flow volume, each of said plurality of holes configured to alter local air pressure about one of said first surface and said second surface of said cowl, said plurality of holes in communication with said flow volume, and said plurality of holes extending between said flow volume and an exterior of the nacelle assembly; and a device in communication with said flow volume for altering local pressure at one of said first surface and said second surface, wherein said device is configured to increase local pressure.