ASSEMBLY CONSISTING OF A TURBINE ENGINE, AND SYSTEM FOR ATTACHING SAME TO AN AIRCRAFT STRUCTURE

摘要

In an assembly comprising a dual-flow turbine engine and a system for attaching the turbine engine to an aircraft structure, the attachment system includes a pylon, at least two rear fasteners connecting the pylon to two rear attachment points of the turbine engine, and a rear cowl of the pylon covering the rear fasteners and forming an aerodynamic fairing. The rear cowl includes two sidewalls (42), each of which have a first portion (42a) extending along and near the pylon, and extending rearward, and a second portion (42b) that projects laterally relative to the first wall portion of the exterior side thereof, so as to cover the rear fasteners. Each second sidewall portion (42b) of the rear cowl is substantially hump-shaped and is connected to the first wall portion along a curved connecting line (42c) extending between front and rear points located substantially at the inner longitudinal edge of the first sidewall portion, such that the impact on the circulation of the secondary flow outside of the secondary stream (13) is minimized.