Patent ID: 7200999
Filing Date: 2007-04-10
Classification: B64C,B64D,F01D,F02K,F04D,F05D,Y02T

Abstract:
1. An aircraft engine comprising a nacelle and a stator structure having a surface, the nacelle defining an aerodynamic shape for a fluid, the nacelle having at least one aperture at a region of relatively low pressure, means to bleed fluid from a region of relatively high pressure on the surface of the stator structure, at least one duct to connect the means to bleed fluid from the region of relatively high pressure on the surface of the stator structure to the at least one aperture in the nacelle at the region of relatively low pressure, whereby the static pressure at the region of high pressure being greater than the static pressure at the region of relatively low pressure such that at least some of the boundary layer of the fluid on the surface of the stator structure flows through the at least one duct to the at least one aperture in the nacelle, the stator structure comprising at least one set of stator vanes, the at least one set of stator vanes comprising a plurality of stator vanes extending between a first wall and a second wall, the surface is a surface of at least one of the first wall, the second wall and the stator vanes wherein the nacelle includes a highlight and a chord length wherein the region of relatively low pressure extends between 50% and 70% of the chord length of the nacelle from the highlight of the nacelle.