Patent ID: 7818958
Filing Date: 2010-10-26
Classification: F02K,Y02T

Abstract:
1. An aircraft engine nacelle having a high bypass ratio, wherein there is installed an engine with a longitudinal axis, the nacelle comprising: a wall that concentrically surrounds the engine at least partly and that defines therewith an annular internal fluid flow conduit, which at a downstream end of the nacelle wall includes a flow-outlet passage cross section; means for displacement, on command, of a part of the nacelle wall to vary a flow-outlet passage cross section via which a major part of the flow escapes, this displacement creating, in the nacelle wall, at least one aperture via which there naturally escapes a leakage flow part of the flow; and a fluid-control device that causes a fluid to force the leakage flow to pass along the external face of the part of the nacelle wall situated downstream from the at least one aperture.