Abstract: A device for controlling an airflow guiding system comprising: at least one vane movable in rotation about an axis of rotation between a first angle and a second angle, an actuator comprising a body inside which a piston is mounted in translation secured to an actuation rod, and a control rod comprising a downstream end connected to the axis of the vane, the actuator being configured to drive the control rod in movement between a first end position and a second end position of a nominal operating range and, in the event of breakdown of said device, to perform an over-stroke of the actuation rod into a safety position. The device comprises a drive mechanism linking an upstream end of the actuation rod to an upstream end of the control rod, opposite to the downstream end.

Abstract: A method including the preparation of a spar preform arranged in a first mould, the spar preform including a core and a root; a first injection step of a first thermosetting resin in the spar preform; partial polymerization of the first resin in the spar preform until partial vitrification of the first thermosetting resin; positioning a body preform around the core of the spar preform; injection of a second resin into the blade body preform; and complete polymerization of the first and second resin.

Abstract: A sun gear for a mechanical gearbox of an aircraft turbomachine, the sun gear having an annular shape around an axis and including an internal annular part having at its internal periphery coupling grooves, an external annular part having at its external periphery at least one meshing tooth, the external part extending around the internal part, and an annular veil connecting the internal and external parts. At least one of the internal and external parts can include two independent rings, each having grooves or teeth, and the veil can have two annular branches connected respectively to the two rings.

Abstract: The present invention relates to a method of manufacture (S) of an optical surface (4) of an optical part (1), comprising the following steps: obtaining (S1) an optical part (1) comprising a substrate (3) made of a first aluminium alloy and a coating (2) made of a second aluminium alloy having a porosity less than that of the first aluminium alloy; determining (S3) a reference shape defect and a reference surface roughness of the optical surface (4); determining (S4) polishing parameters for obtaining the reference surface roughness; depending on the polishing parameters, machining (S5) the coating (2) so as to give it a modified shape defect; and polishing (S6) the coating (2) according to the polishing parameters until the reference surface roughness and the reference shape defect are obtained.

Abstract: The invention relates to an optronic sight (2) for a motorised vehicle such as an aerial, marine or land vehicle, comprising a sighting module (4) able to be moved about a first axis (8a) and a second axis (10) not parallel to the first axis (8a), means (17a, 17b) for moving the sighting module about the first (8a) and second (10) axes, means (14) for continuously measuring an angular datum of said module (4) about the first and second axes characterised in that it comprises a feedback control loop comprising: means for acquiring the fundamental frequency of vibratory disturbances generated by the operation of at least one device of the sight, and an adaptive corrector (26) configured to receive as input: said fundamental frequency, a discrepancy between an angular setpoint value (yck) and said angular datum outputting a movement setpoint value to the movement means (17a, 17b).

Abstract: The invention relates to a device for measuring the oxidation of an element comprising a carbon-carbon composite, including a means for measuring the diamagnetism of the element and a means for converting the diamagnetism measurement into an oxidation measurement.

Abstract: A blade for a ducted fan of a turbomachine includes an airfoil formed of plural airfoil sections stacked along an airfoil axis. A difference in sweep corresponding to a difference between a leading edge sweep and a trailing edge sweep of an airfoil section is substantially identical for any airfoil section having a height of between 10% and 20% of an airfoil height of the airfoil, and/or substantially identical for any airfoil section having a height of between 75% and 90% of the airfoil height.

Abstract: An assembly for a turbomachine of longitudinal axis includes a nozzle carried by an annular part which is fixed to an outer casing. The nozzle has an outer annular platform from which extends, radially outwards, a radial annular wall which carries an annular attachment tab extending longitudinally upstream from the radial annular wall. The assembly has a cooling circuit with an inner annular chamber delimited radially by the outer annular platform and the annular part and delimited downstream by the radial annular wall. An intermediate annular chamber is formed radially externally to the annular attachment tab and in fluid communication with the outer casing. Means of fluid communication between the inner annular chamber and the intermediate annular chamber is formed in the annular attachment tab of the nozzle.

Abstract: A nickel-based superalloy part includes a nickel-based superalloy substrate, and a metal sublayer covering the substrate, wherein the metal sublayer includes a first and a second layer, the first layer being located between the substrate and the second layer, the first layer including a first ??-Ni3Al phase and a second ?-Ni phase, the second layer including a first ??-Ni3Al phase, a second ?-Ni phase and a third ?-NiAl phase, the average atomic fraction of aluminum in the second layer being strictly greater than the average atomic fraction of aluminum in the first layer.

Abstract: The invention relates primarily to an assembly for an aircraft cabin (10), comprising: at least one seat unit (11) comprising a seat (12) and a privacy shell (13) extending at least partially around the seat (12), at least one separation curtain (21), and a storage compartment (18) delimiting an internal volume (22), a system (20) for deploying the separation curtain (21) being configured to selectively switch the separation curtain (21) between: a stored state in which said separation curtain (21) is disposed predominantly inside the internal volume (22) of the storage compartment (18), and a deployed state in which said separation curtain (21) is disposed predominantly outside the internal volume (22) of the storage compartment (18) so as to at least partially delimit an enclosed resting space (25) around the seat unit (11).

Abstract: The invention relates to a fan blade (3) of a turbomachine (15) comprising a structure (4) made of composite material having, within the root (5) and/or the stilt (6) of the blade, a first layer (11) comprising the lower face (16) and having a first thickness (E1) of between 10% and 25% of the total thickness (E), a second layer (12) comprising the suction face (17) and having a second thickness (E2) of between 10% and 25% of the total thickness (E), and a central layer (13) extending between the first layer (11) and the second layer (12), the shortening of the warp strands (9) in the first and second layers (11, 12) being greater than the shortening of the warp strands (9) in the central layer (13).

Abstract: An installation for compacting strands or a preform including strands, the strands or the preform including at least a first portion in which the strands are twisted at a first angle and a second portion in which the strands are twisted at a second angle different from the first angle, the installation including a mould which includes the strands or the preform, and wherein the mould has at least a first part in which the first portion of the strands or of the preform is disposed, having a first thickness and a second part in which the second portion of the strands or of the preform is disposed, having a second thickness different from the first thickness.

Abstract: Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

Abstract: A passenger seat assembly includes a passenger seat and a retractable divider assembly. The passenger seat includes a first side, a second side opposite from the first side, and a forward-facing surface extending between the first side and the second side. The retractable divider assembly is attached to the passenger seat proximate to the first side of the passenger seat and includes a divider. The divider is movable between a stowed position and a deployed position. In the deployed position, the divider extends in a forward direction relative to the forward-facing surface of the passenger seat.

Abstract: A process for manufacturing a blade made of composite material for a turbomachine. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: placing a preform, produced by three-dimensionally weaving fibers, in a mold, the sheath being positioned on an edge of the preform intended to form the leading edge of the airfoil; and injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying. At least one double-sided adhesive film may be inserted between the sheath and the edge of the preform prior to injection of the resin.

Abstract: A part of a turbomachine made of composite material includes a fiber reinforcement having a three-dimensional weaving including a first set of yarns made of a first material, wherein the fiber reinforcement includes a vibration-damping element formed by a second set of yarns including a second material which is viscoelastic and which is different to the first material, the second set of yarns being woven with the first set of yarns.

Abstract: The disclosure relates to a housing comprising at least one composite wall comprising woven or braided carbon fibers covered with a thermoplastic or thermosetting resin, an electronic card carrying electronic components, and a heat transfer device having at least one portion facing an electronic component to be cooled of the electronic card, said heat transfer device being inserted inside the composite wall, the heat transfer device comprising at least one cooling conduit containing a cooling fluid.

Abstract: An accessory gearbox houses at least one gear train with a series of pinions. The casing has two substantially flat and opposite parallel side walls between which are mounted support shafts for each of the pinions, each of which receives accessories, and which define in the enclosure an internal volume surrounding a shaft supporting at least one hybridization pinion. The gearbox receives at least one electric machine having a rotor and a stator, wherein the rotor of the electric machine is supported by the shaft supporting the hybridization pinion of the gear train, and the stator extends around the rotor in the internal volume.

Abstract: A method for manufacturing a shell mold intended for manufacturing at least one metal part by lost-wax casting, the shell mold including at least one molding cavity intended for molding the metal part, and at least one feed channel intended to convey a liquid metal to the molding cavity, the method including manufacturing a wax pattern including a part pattern intended to form the molding cavity and a feed channel pattern intended to form the feed channel, arranging at least one ceramic insert around at least a portion of the feed channel pattern, and manufacturing the shell mold around the wax pattern.

Abstract: Method for manufacturing composite blade cleats for an aircraft turbine engine, including providing a woven panel, including a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least a portion of the margin in common; injecting a matrix onto the panel; after injection, dividing the panel in order to separate the cleats from one another; machining the cleats to remove the margins.