Abstract: A frangible strut for a gas turbine engine includes a first end to couple to a first structure of the gas turbine engine, and a second end opposite the first end. The second end is to couple to a second structure of the gas turbine engine. The second end includes an outer portion coaxial with and spaced radially apart from an inner portion. The inner portion is to receive a fastening device to couple the second end to the second structure. The outer portion is coupled to a body of the frangible strut. The inner portion is interconnected to the outer portion by a plurality of frangible members that are spaced apart about a perimeter of the inner portion, and each of the frangible members are configured to release the inner portion from the outer portion. The frangible strut includes the body interconnecting the first end and the second end.

Abstract: For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.

Abstract: Methods and systems for nacelle door electromechanical actuation may include a power distribution unit comprising a motor and differential gears; and a plurality of electromechanical actuators, each coupled to an output of a corresponding one of the differential gears. Each of the electromechanical actuators may include a configurable brake and a mechanical output, where the power distribution unit may provide mechanical torque to one of the electromechanical actuators via the motor and the differential gears based on configuration of the configurable brakes in each of the electromechanical actuators. At least one of the configurable brakes may be an electrically configurable brake. At least one of the configurable brakes may be a mechanically configurable brake. The differential gears may include two or more differential gears for receiving an input torque and supplying an output torque to one of a plurality of outputs of the differential gears.

Abstract: A nacelle mounted above a wing of an aircraft. A support structure on the nacelle above the pylon resists forces in different directions, and includes door supports allowing the door to be opened upwardly. A retaining structure on the pylon below the nacelle resists forces in different directions, and includes a fixed support track and multiple keepers. Each keeper includes a first end which slides within the channel, and a second end which engages a latch on the closed door. A pylon below the nacelle supports the nacelle and an engine in the nacelle above the wing, increases aerodynamic efficiency, and may include a side spar for supporting the engine from the side. A fire seal assembly includes a depressor surface and a fire seal, and the latter does not contact the former until the door is almost closed, so that compression is substantially direct and scrubbing is reduced.

Abstract: A primary structure of an aircraft power plant support pylon is disclosed having a bottom stringer and two lateral walls formed in a single piece or welded so as to form a U-shaped bottom part, and a top cover which closes the U-shaped bottom part. The U-shaped part closed by a cover makes it possible to construct a box or box structure that exhibits a rigidity suitable for taking up the forces deriving from the power plant and makes it possible to limit the number of ribs (C1 . . . C10) in the structure.

Abstract: An engine assembly having an improved mounting system or assembly is disclosed. Features of this mounting system include having crankcase arms that are integrally formed with a crankcase of the engine assembly, having multiple mounting legs that each have a dedicated vibration damping subassembly and where the stiffness of at least two of the mounting legs is different (by varying the configurations of the corresponding vibration damping subassemblies), and using a mounting ring or base with having differently oriented mounting pads for securement of the corresponding mounting leg relative thereto.

Abstract: A method for assembling a primary structure of an aircraft pylon, includes a step of fixing an angle bracket to each of the first and second lateral panels such as to obtain an L form for each of the first and second lateral panels prior to a placement of said L forms each placed against two sides of each transverse frame. This assembly technique makes it possible to reduce the mounting clearances such that it is unnecessary to fit shims, resulting in a reduction of mounting time and manufacturing costs.

Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a tubular inner housing, a tubular outer housing and a bifurcation. The bifurcation includes a leading edge structure structurally connected to the inner housing and the outer housing.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical bearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: The invention relates to an aircraft comprising a fuselage, flight control surfaces and a turbojet engine (20) integrated into the rear of said fuselage in the extension thereof, the turbojet engine (12) comprising two gas generators (22) that supply, via a common central duct (30), a power turbine (32) comprising two counter-rotating rotors (34, 36) respectively driving two upstream (38) and downstream (40) coaxial and counter-rotating fans each comprising a ring of vanes (42, 44), the set of fans (38, 40) being integrated into a fairing (46) of the turbojet engine (20) formed at the rear of the fuselage (12), characterised in that at least said fairing (46) is axially arranged behind the flight control surfaces and comprises an upstream section (50), surrounding the upstream fan (38), configured to be radially traversed by at least one fragment (43) of a vane (42) of the upstream fan (38) in the event of the breakage of a vane (42) of said upstream fan (38) and the ejection of said at least one fragment (43

Abstract: An exhaust casing of a turbine engine for an aircraft which extends along an axis and includes: a central hub, an annular outer shroud and arms which connect the central hub to the outer shroud, at least one yoke for attaching the exhaust casing to the turbine engine being located on the outer shroud and forming at least one lug extending in a plane perpendicular to the axis and protruding toward the exterior of the outer shroud. The outer shroud includes ribs which form a constant excess of the outer shroud, which are located on either side of the at least one lug of the at least one yoke, and which are aligned with the at least one lug.

Abstract: A system for mounting an engine to an aircraft includes an engine forward mount angled toward the forward end of the engine at a first angle. At least two thrust links extend between an engine aft mount to a link support connection at a second angle. The engine aft mount is angled toward the forward end of the engine at a third angle. A projection of a load vector of the engine forward mount onto a vertical plane extending through the axis of rotation of the engine and a projection of a load vector of each of the at least two thrust links onto the vertical plane intersect the axis of rotation of the engine within a first vertical plane segment extending between a forward end of a nose of a fan assembly and forward of a forward mount interface.

Abstract: The present disclosure relates to a nacelle for an aircraft turbojet engine that includes an air inlet having a leading edge of the nacelle extending forward by an inner wall and an outer wall of the air inlet and a fan cowling defining, in a closed position, aerodynamic continuity with the outer wall of the nacelle, intended for surrounding a turbojet engine fan cowling. The air inlet is designed to define at least one portion of the fan cowling. The present disclosure also relates to a propulsion assembly that includes a nacelle surrounding a turbojet engine.

Abstract: To allow the attachment of an engine of the “Open Rotor Puller” type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.

Abstract: 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.

Abstract: An inlet for a gas turbine engine having an inlet lip and an inlet barrel, the inlet lip having a highlight defining a boundary between inner and outer surfaces of the inlet lip. The inlet barrel has a forwardly extending flange that is joined to the inlet lip by overlapping surfaces. The flange interface surface has a conus angle that is divergent from the highlight axis.

Abstract: A turbine engine includes an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11), with said member (17) being intended to be attached onto a mounting (18) used for the attachment thereof onto an aircraft structural part. A thermal protection member (23) surrounds said member (17), with said thermal protection member (23) including a base flexibly supported on the wall (11) of the element (3), with said base matching the shape of said wall and at least one covering part which surrounds said load-bearing member.

Abstract: A jet engine support structure includes an inboard support fitting that is configured to be operatively attached to the jet engine, an outboard support fitting that is configured to be operatively attached to the jet engine, an inboard longeron that is configured to be attached to the inboard support fitting and an exterior underside surface of an aircraft wing, an outboard longeron that is configured to be attached to the outboard support fitting and the exterior underside surface of the wing, and a drag brace fitting that is configured to be attached to the inboard longeron and the outboard longeron and operatively attached to the jet engine. These component parts are employed in operatively attaching the jet engine to the aircraft wing. The same set of component parts is employed in operatively attaching the jet engine to either a left side or port side wing or to operatively attach a jet engine to a right side or starboard side wing.

Abstract: An inlet lip structure includes: an annular inner barrel with forward and aft ends; an annular outer barrel with forward and aft ends; an annular aft bulkhead interconnecting the aft ends of the inner and outer barrels; an annular forward bulkhead interconnecting the forward ends of the inner and outer barrels; an annular lip skin interconnecting the forward ends of the inner and outer barrels, the lip skin having a C-shaped cross-section comprising a nose with inner and outer legs extending therefrom, the lip skin having opposed inner and outer surfaces; and wherein the outer leg of the lip skin incorporates a fuse element having an ultimate strength which is lower than an ultimate strength of the remainder of the lip skin.

Abstract: An aircraft engine attachment assembly having a wing section, an engine pylon, upper secondary attachment links, lateral load attachment links, and a number of fuse pins. The engine pylon is mounted to the front end of the wing section so that the engine pylon is not restricted by a minimum structural depth. The wing section, engine pylon, upper secondary attachment links, and lateral load links form primary and secondary attachment joints configured to form alternate load paths if one of the joints fails. The wing section and engine pylon include knuckle-off geometries for promoting mechanical fusing of the fuse pins during high energy dynamic events.

Abstract: An assembly is provided that includes a first component, a second component, a plurality of retainers and a fastener. The first component is configured with a plurality of first apertures. The second component is configured with a plurality of second apertures. Each of the retainers includes a pin and an arm projecting out from an end of the pin. The pin of each of the retainers is mated with a respective one of the first apertures and a respective one of the second apertures. The fastener is configured to fixedly connect the arm of each of the retainers to the first component.

Abstract: A bearing joint assembly includes a bearing sleeve, a first mount, a pair of second mounts and a fastener. The bearing sleeve extends axially along a centerline and includes a spherical bearing, a first collar and a second collar. The spherical bearing is axially between the first collar and the second collar. An annular channel is formed by and extends axially between the spherical bearing and the first collar. The first mount is mounted on and slidably engages the spherical bearing. The bearing sleeve is axially between the second mounts. The fastener projects through the bearing sleeve and secures the bearing sleeve to the second mounts.

Abstract: 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.

Abstract: A suspension device for suspending, for example, a turbine engine to a pylon, the device comprising a first unit interposed between a first lug and a second lug of a second unit, the first unit having a bore for passing an axle running through first and second bushings mounted respectively in said first and second lugs; and a clamping unit interacting with the axle. The device further comprising a third bushing mounted in the second lug and having radial centering means which interact with the complementary centering means of a head section of the axle; and a fourth axially slidably mounted bushing, biased axially by the clamping unit, and comprising radial centering means which interact with complementary centering means of the first bushing.

Abstract: Systems and methods for integrating Boundary Layer Ingestion (BLI) apparatus into an aircraft (1). The longerons (34) in the aft fuselage (18) may be extended to support an aft propulsor (20). The aft propulsor may be a turbofan or turboelectric propulsion system (46). An upper longeron (34a) may support a tail section (14) of an aircraft. The aft fuselage skin (22) is contoured to permit boundary layer airflow to enter an intake fan (24) of the aft propulsor.

Abstract: An engine mount assembly for mounting an engine which produces a torque to a body having a persistent troublesome frequency vibration is disclosed. The engine mount assembly includes two fluid elastomeric chambers groundable to the body, an intermediate cradle link disposed between the two fluid chambers, a lateral link grounded to the body and the intermediate cradle, and a fluid conduit connecting the two fluid chambers. When subjected to torque a positive fluid pressure is generated within the fluid chambers and fluid conduit with the two fluid chambers share a plurality of loads while a transfer of the persistent troublesome frequency vibration from the body to the engine is inhibited.

Abstract: A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.

Abstract: A rear engine mount for a turbomachine of an aircraft comprising a pylon. The rear engine mount comprises a beam attached to the pylon, a first and a second lateral connecting rod having an abutment and attached between the beam and the turbomachine, a three-point, V-shaped central connecting rod, of which the vertex is attached to the turbomachine, and of which the ends of the arms are attached to the beam. The rear engine mount has a plane of symmetry passing through the center of the ball joint of the vertex. The beam has, for each abutment, a buffer, wherein each abutment comes to bear against the buffer in the event of failure of the central connecting rod.

Abstract: To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.

Abstract: An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled between the engine and the airframe. The torsion bar has upper and lower tapered bosses. Upper and lower arm assemblies couple the engine to the torsion bar. Each arm assembly has an end bell crank with a tapered socket that is adapted to receive a respective tapered boss therein to secure the end bell cranks to the torsion bar such that the end bell cranks rotate with the torsion bar responsive to movements of the engine.

Abstract: An engine mount system having failsafe securement points. The engine mount system includes a forward mount carrying a coat hanger shackle having a spherical bearing and a cylindrical hearing. Securement of the engine mount to a support utilizes pins and bolts with a retaining double wrench washer incorporated into the final mounting structure. The engine mount system additionally includes an aft mount.

Abstract: Pylon mounting assemblies are provided for mounting an engine (e.g., a turbojet engine) to a wing of an aircraft. The pylon mounting assemblies include an upper pylon connection member, and a lower pylon connection box, wherein the upper pylon connection member and the lower pylon connection box respectively include multiple opposed pairs of connection lobes. At least one pair of the connection lobes includes a pin connection to restrict degrees of freedom thereat along an x-axis and a mutually perpendicular z-axis, while at least one other pair of connection lobes includes a connection rod to restrict degrees of freedom thereat along the z-axis.

Abstract: A variable pitch fan for gas turbine engine is provided. The variable pitch fan includes a plurality of fan blades rotatably coupled to a disk and an actuation assembly for changing a pitch of each of the plurality of fan blades. The actuation assembly generally includes an actuation member operably connected to at least one of the plurality of fan blades and a pin. The pin is movable between a first position in which the pin is positioned at least partially in a channel defined in the actuation member, and a second position. The pin blocks movement of the actuation member relative to the pin past a range defined by the channel when in the first position. The actuation assembly further includes a retraction system for selectively engaging the pin in moving the pin from the first position to the second position.

Abstract: A propulsive assembly including a turbine engine configured to be fastened to an aircraft by means of a suspension, having certain casing portions suitable for being decoupled so as to attenuate certain bending modes of the turbine engine in the event of an incident, the propulsive assembly comprising at least first and second casing portions (33a, 22) extending axially one after another, one of said casing portions being cantilevered out relative to said suspension, wherein a first casing portion (33a) possesses a first fastener portion (41) connected rigidly to the body (43) of the first casing portion (33a) and a second fastener portion (42) connected more flexibly to the body (43) of the first casing portion (33a), and wherein the second casing portion (22) is fastened to the second fastener portion (42) of the first casing portion (33a) in a manner that is permanent, and to the first fastener portion (41) of the first casing portion (33a) in a manner that is releasable.

Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.

Abstract: An adaptive aerial vehicle includes a vehicle support, at least one frame assembly mounted relative to the support, at least one propulsion unit mounted to the frame assembly and operable to move the adaptive aerial vehicle, and an actuator configured to move the support relative to the frame assembly to redistribute the weight of the adaptive aerial vehicle.

Abstract: A propulsor and mount arrangement comprises a propulsor rotor and a fan casing surrounding the propulsor rotor. The fan casing receives two side mounts and a thrust link pivotally attached to the fan casing at a location that will be within 10° of a vertically lowermost location when the propulsor is mounted on an aircraft, and the side mounts being at circumferentially opposed positions, and within a lower 270° when the propulsor is mounted on an aircraft. At least a portion of both the side mounts, and a pivot point connect the thrust link to the fan casing in a common plane defined perpendicular to a rotational axis of the propulsor rotor. An aircraft is also disclosed.

Abstract: An engine mount assembly for coupling an engine to an airframe includes a torsion bar, a lateral movement control assembly and a vertical movement control assembly. The torsion bar has a torsional stiffness and is coupled between the engine and the airframe such that torsional movement of the engine causes torsion in the torsion bar. The lateral movement control assembly has a lateral stiffness and is coupled between the torsion bar and the airframe such that lateral movement of the engine causes rotation of the torsion bar which reacts on lateral movement control assembly. The vertical movement control assembly has a vertical stiffness and is coupled between the engine and the airframe such that vertical movement of the engine reacts on the vertical movement control assembly. The engine mount assembly, thereby enables torsional, lateral and vertical movement of the engine to be independently controlled.

Abstract: A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid communication with a combustor and a turbine is in fluid communication with the compressor section. A speed reduction device driven by the turbine section for rotating the fan about the axis is mounted forward of the bearing assembly supporting rotation of the hub.

Abstract: An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled to the engine and a lateral movement control assembly coupled between the torsion bar and the airframe. The lateral movement control assembly includes a spring having a lateral stiffness. The torsion bar rotates in response to lateral movement of the engine such that the lateral movement of the engine is controllable based on the lateral stiffness of the spring.

Abstract: The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and comprising a central part (18) and side arms (19) projecting from the central part (18).

Abstract: The gas turbine engine includes a core engine, a low pressure turbine, a fan assembly, a gearbox, and a lubrication scavenge pump. The core engine includes a high pressure compressor, a combustor, and a high pressure turbine configured in a serial flow arrangement. The low pressure turbine is positioned axially aft of the core engine. The fan assembly is positioned axially forward of the core engine. The gearbox is positioned axially forward of the fan assembly. The lubrication scavenge pump is positioned forward of the gearbox.

Abstract: In order to bring a turbofan engine closer to the lower surface of a wing box, the disclosure herein foresees an assembly for an aircraft including a mount for mounting a rigid structure of an engine strut to the wing box, the mount including an upper wing mount including a fitting secured to the upper surface of the wing box.

Abstract: 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.

Abstract: An engine mount assembly for coupling an engine to an airframe. The engine mount assembly includes a torsion bar coupled between the engine and the airframe. The torsion bar includes an external spline. The engine mount assembly also includes a bell crank having a clamp forming an internal spline with the internal spline of the bell crank adapted to mate with the external spline of the torsion bar to secure the bell crank to the torsion bar such that the bell crank rotates with the torsion bar responsive to movements of the engine.

Abstract: In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.

Abstract: The invention relates to an assembly comprising a structure (2) and a tubular element (6), which is mounted isostatically in the structure (2), said tubular element (6) comprising a first end (7) connected to said structure by at least four connecting rods 10a-10b-10c-10d, thus setting four first degrees of freedom, and a second end (8) connected to said structure (2) by an attachment means (20) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

Abstract: 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.

Abstract: Turbine engine, comprising two structural annular casings (16, 22) which are interconnected by connecting rods (54), characterized in that the turbine engine further has at least one accessory gearbox (40) which is fixed to a first of the casings (16) and which is connected by the connecting rods to the other of the casings (22).