Gas turbine engine

摘要

A gas turbine engine has an annular bypass duct defined between a fan nacelle and a core fairing through which fan air is discharged. One or more bifurcator members are positioned inside the exit of the bypass duct to bifurcate the air flow in the bypass duct around the bifurcator members prior to exiting the bypass duct. The bifurcator members modify the flow field of the air in the bypass duct radially and/or tangentially with respect to the axis of the annular bypass duct.

主权项

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.