In order to reduce congestion of attachments between an aircraft engine and its attachments, an engine assembly is provided, the primary structure of the device of which includes a structural cover surrounding the engine and connected on a central box, the cover including an outer skin interiorly delimiting a secondary flow. A group of main mounts is provided as a group of secondary mounts laid out at the rear of the group of main mounts, the group of main mounts including a plurality of bolts distributed around the longitudinal axis of the engine and ensuring the attachment of a front end of the cover to the hub of the intermediate case, and a group of secondary mounts including a plurality of secondary mounts distributed around the axis and ensuring attachment of a rear portion of the engine to a rear end of the cover.

A strut and method for assembling a strut. The strut comprises two strut members attachable by a threading mechanism or the like. A first strut member is screwed into the second strut member. A pin hole is formed at the seam between the strut members and a pin is inserted into the pin hole. A locking ring is formed around the pin hole that includes an angular lip adjacent to the hole. The locking of the pin is accomplished, by swaging the angular lip into the hole and over the pin to lock the pin in the pin hole. The purpose of the pin is to ensure the joint does not untwist during operation.

An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.

A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.

Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

A propulsion assembly for an aircraft, having a turbomachine, a pylon, and a device for reacting thrust forces having a main fitting, a spreader pivoting on the main fitting and having an opening, two rods articulated to the turbomachine and to the spreader, a secondary fitting fastened beneath the pylon and having a secondary female clevis constituted of two secondary arms passed through by holes of oblong shape and aligned along a secondary axis (R2), wherein the spreader is housed in the secondary female clevis of the secondary fitting, wherein the opening is coaxial with the secondary axis (R2), and a backup connection pin inserted with a tight fit into the opening and with clearance into the holes. Also an aircraft with such a propulsion assembly.

Engine-mounting linkage systems may include a plurality of engine mounting links configured to couple an engine frame to an engine support structure of an aircraft. The plurality of engine-mounting links may include a forward link that is connectable to a forward frame portion of the engine frame and the engine support structure, and an aft link that is connectable to an aft frame portion of the engine frame and the engine support structure. The engine mounting linkage system may include an actuator that is connectable to the engine support structure and one of the plurality of engine-mounting links, or to the engine support structure and the engine frame. The actuator, when actuated, changes an inclination angle ? of at least one of the plurality of engine-mounting links.

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.

A system for mounting an engine on an aircraft. The system includes a lower forward element, lateral linkages, an upper forward element, and an aft element. The lower forward element couples a forward portion of an engine core with a lower forward portion of a pylon. The linkages extend laterally between the lower forward element and the forward portion of the engine core. The upper forward element couples an outer portion of the fan case with an upper portion of the pylon. The aft element is spaced aftwardly apart from the lower and upper forward elements, and couples an aft portion of the engine core to an aft portion of the pylon. The system reacts all major moments acting on the engine, and the system does not extend beyond an outer periphery of the fan case, which eliminates the need for or minimizes the height of an aerodynamic fairing.

A support structure for attaching an engine to an aircraft pylon at front, mid and rear attachment positions thereof, including a front mount joined to the engine and configured to attach to the pylon at the front attachment position and a rear mount joined to a core casing to attach to the pylon at the rear attachment position, each of the front and rear mounts configured to transfer lateral and vertical loads from the engine to the pylon, and the rear mount being spaced from the front mount such that yaw and pitch torques are transferred from the engine to the pylon through the front and rear mounts. The support structure also includes an axial load transfer formation to transfer axial loads from the engine to the pylon and a roll-torque transfer formation to transfer roll torque from the core casing to the pylon.