Pylon for attaching a gas turbine engine

摘要

A pylon (5a) is provided for attachment of a gas turbine engine (1) to a wing of an aircraft. The gas turbine engine (1) comprises a core fairing (3) surrounding a core generator and defining a nozzle for discharging a core gas flow, and a fan nacelle (2) surrounding the core fairing (3) to define an annular bypass duct (4) therebetween for discharging fan air. The pylon (5a) has a trailing edge (7) which is rearward of the trailing edge of the core fairing (3) and the trailing edge of the fan nacelle (2). The pylon (5a) further has having two laterally-spaced side faces which span the bypass duct between the fan nacelle (2) and the core fairing (3) and extend in the rearward direction of the engine to end at the trailing edge (7) of the pylon (5a). Each side face has a bottom edge which extends in a rearward direction of the engine (1) from the core fairing (3) to the bottom end of the trailing edge of the pylon. The bottom edges merge at a merging position between the trailing edge of the fan nacelle (2) and the trailing edge (7) of the pylon (5a) such that the bottom edges form a single bottom edge from the merging position to the bottom end of the trailing edge (7) of the pylon (5a). The pylon (5a) is intended to exert control on the bypass flow of a gas turbine engine. Other pylons are also provided which can also exert such control.