Patent ID: 8870530
Filing Date: 2014-10-28
Classification: B64D,F01D,F02C,F02K,F05D

Abstract:
1. A gas turbine engine comprising: a fan nacelle surrounding a core fairing to define an annular bypass duct there-between for discharging fan air; and one or more bifurcator members positioned inside the bypass duct which cause the air flow through the duct to bifurcate around the bifurcator members prior to exiting the bypass duct; wherein the, or each, bifurcator member spans locations in the duct in a non-radial direction of the engine, and at least one of the one or more bifurcator members: (a) extend between the fan nacelle and an attachment pylon for the engine; (b) extend from one position on the fan nacelle to a second position on the fan nacelle; or (c) extend between the core fairing and the attachment pylon for the engine.