L'invention concerne un ensemble (100) pour un aéronef comportant une nacelle (18) d'un turboréacteur qui comporte un capot portant des deuxièmes ferrures d'articulation, un mât (16) fixé entre le turboréacteur et une aile, un échangeur thermique (1...

A gas turbine engine assembly is connected to a pylon (14) for mounting the gas turbine engine (10) to an aircraft. The assembly has a frame (26) supporting at least one accessory (35, 50) independently of the gas turbine engine (10). The frame (26) is att...

A gas turbine engine assembly is connected to a pylon (14) for mounting the gas turbine engine (10) to an aircraft. The assembly has a frame (26) supporting at least one accessory (35, 50) independently of the gas turbine engine (10). The frame (26) is att...

Accessories (35) are mounted to a gas turbine engine from a frame (14)attached to a pylon which is used to mount the engine to an airframe. The frame independently mounts the accessories so that engine vibrations are not transmitted to the accessories.

The assembly (1) has an attachment device (4) including a front aerodynamic structure (24) having a cradle (40) equipped with an aerodynamic fairing (46), where the cradle is pivotally mounted on an air inlet (32) of a turbojet engine (6), and fan cowls ar...

A fan containment case (26) includes a mount ring (32) that supports a portion of the engine core. The mount ring (32) includes openings and features that define a mounting location for the gas turbine engine. The example fan containment case (30) includes...

A method of manufacturing an inlet assembly (17) for an aircraft engine nacelle comprises the steps of: providing an inner barrel (39) and an outer barrel (41) which is radially spaced from said inner barrel; forming at least one zone of deformation (71) i...

An aircraft engine mounting assembly (14) comprising a bracket arrangement (16) with two plates (20, 22) located either side of an opening (18) in the structural bypass duct (12). The bracket arrangement (16) mounts two inclined links (30) which connect to...

A connector assembly (100) comprises a thrust link (102) and a clevis (120). The thrust link comprises a first end (124), a second end, and a body extending therebetween. The clevis is telescopically coupled to at least one of the thrust link first end and...