An aircraft engine pylon includes two side panels and an upper stringer and a lower stringer assembled to form a strut assembly extending in a longitudinal direction (AX) corresponding to the direction in which the aircraft is moving and an internal reinforcement structure including a plurality of reinforcements. The pylon also includes a reinforcement zone on each side panel and a front housing to receive a main front center reinforcement and a rear housing to receive a main rear center reinforcement.

A connection assembly for mounting an engine to a mounting structure. The engine is rotatable about an axis of rotation and defines an axial direction extending along the axis of rotation from a forward end to an aft end. The engine has a center of gravity. The connection assembly includes: an engine coupling piece coupled to the engine; and a connection piece connecting the engine coupling piece and the mounting structure, the connection piece being inclined toward the axial direction. A mounting system including the connection assembly is also described.

In the so called internal combustion (reaction type) airbreathing jet engines (including turbojets and turbofans) fast moving discharging combustion exhaust gases from core exhaust stream and air will generate jet propulsion. In other words, the produced thrust thru an exit nozzle in such engines moves the jet aircraft forward in flight.

During flight of a jet aircraft the essential steering movements (roll, pitch and yaw type maneuvers) are normally performed via control surfaces on its wings and its tail sections. These controls are activated by pilot from inside the cabin.

This invention allows for swiveling of a pivotable jet engine mounted under the wings of a commercial jet aircraft, to direct exhaust gases (combustion gases and bypass airflow in case of turbofan engines and in general the engine core exhaust gases for turbojets) upward or downward or sideways (outboard of the cabin and the fuselage) to some limited extent to achieve more agile air maneuvers compared to the traditional fixed under the wing-mounted jet engines. The restricted hinged swivel angular motion of the engine(s) pivotally mounted under the wings of such a jet aircraft will make it possible for comfortably (and not abruptly) shortening the required air distance needed to perform aircraft's attitude adjustment maneuvers needed such as during descent, takeoff, landing approach or during cruise to control flightpath and/or quickly avoid air traffic potential problems.

Therefore, the idea of performing agile maneuvers which at times can become critical in the flight safety of especially larger passenger jetliners is realized by swiveling jet engines under the wings of a 2 or 4 engine commercial jet aircraft about a pivot point mounted along the engine nacelle to enable highly efficient pitch and roll motions in flight (with enhanced agility), as well as making efficient and agile yaw type motion in flight by turning the entire/plurality of engine assembly (away from the fuselage/cabin) around a central point underneath the wing assembly.

A gas turbine engine assembly is connected to a pylon for mounting the gas turbine engine to an aircraft. The assembly has a frame supporting at least one accessory independently of the gas turbine engine. Frame is attached to the pylon at forward and rearward engine mounting locations. The frame includes at least one hollow tube and at least one hollow tube is fluid tight. The one hollow tube is evacuated or contains pressurized fluid and a pressure sensor is provided to detect a change in pressure in the at least one hollow tube to determine if there is a leak in the at least one hollow tube and hence if the frame is damaged. This ensures that the frame may be repaired or replaced before there is a loss of operation of one or more of the accessories which may result in a failure of the gas turbine engine.

A swivel axis for an aircraft engine attachment, comprising a tubular main axis which has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a first nut. A fail-safe axis is configured to be mounted to swivel inside the main axis. The fail-safe axis has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a second nut. The fail-safe axis is linked by an axial link to the first nut. Since the fail-safe axis is linked to the first nut, it is necessarily inserted into the main axis when the first nut is screwed onto the main axis.

A gas turbine engine includes a support structure for attaching the engine to an aircraft pylon. The support structure includes: an engine-side interface member, a pylon-side interface member interfacing to the engine-side interface member, and a top V-shaped connection formation above the engine core and pair of side V-shaped connection formations on opposite lateral sides of the engine core, each V-shaped connection formation being formed by a pair of connection members meeting at a vertex, the vertex of the top V-shaped connection formation joining to the top of the engine-side interface member, the vertices of the side V-shaped connection formations respectively joining to the bottom ends of the engine-side interface member, and the connection members extending forwardly from their respective vertices to join to front fixation points at the core casing.

A pylon system for coupling an engine to a vehicle is provided. The pylon system includes a vehicle pylon to be coupled to the vehicle. The vehicle pylon includes a seal along a portion of the vehicle pylon. The pylon system includes an engine pylon including an inboard longeron and an outboard longeron. The inboard longeron is coupled to the outboard longeron at a first end of the engine pylon and is spaced apart from the outboard longeron at a second end of the engine pylon. The engine pylon is to be coupled to the engine, and the engine pylon is slidably coupled to the seal such that the engine pylon is movable relative to the vehicle pylon between at least a first position and a second position.

A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising a first fitting configured to be fixed against the bottom face and having a wall, a second fitting configured to be secured to a structural casing of the engine, two front links and two rear links, which are fixed by one and the same main link point to the wall and by two link points on either side of the second fitting. Such a motorization assembly allows for a reduction of the bulk, in particular at the rear engine attachment, which helps in improving the overall performance of the motorization assembly.

To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

The invention relates to a system for suspending two modules of a propulsion unit, such as two fan modules, said system comprising a pylon (28) and a rudder bar (30). One part (30) of the rudder bar is hinged to the pylon, while the opposing ends thereof are hinged to connecting rods (34, 36). The system also comprises a torque bar (40) which has an elongate shape and is mounted on the pylon such that it can pivot about an axis substantially parallel to an axis (B) of elongation of the torque bar, the opposing ends (42) of said bar being secured on each side of the above-mentioned part of the rudder bar.