Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.

Abstract: An annular or semi-annular acoustic attenuation structure includes an inner skin and an outer skin, defining between them an annular or semi-annular volume, and a plurality of partitions extending in the space in a radial direction perpendicular to the inner and outer skins and in a circumferential direction. The inner and outer skins and the partitions are made of composite material including a fibrous reinforcement densified by a matrix. The fibrous reinforcement of each partition includes yarns or fibers extending into the fibrous reinforcement of at least one of the inner or outer skins.

Abstract: The invention relates to a seat, in particular for an aircraft, including: a seat support, a seat base, a backrest hinged relative to the seat base by means of a pivot link, a leg rest hinged relative to the seat base by means of a pivot link, the seat being able to move between a sitting position and a bed position in which the backrest and the leg rest are situated in a continuation of the seat base, the seat base being mounted so as to be able to slide relative to the seat support, the seat comprising at least one connecting rod, referred to as the backrest pivot connecting rod, comprising a first end connected in rotation relative to the backrest and a second end connected in rotation relative to the seat support, the leg rest being mechanically connected to the backrest by means of a connecting rod deployment device, the seat further comprising a single actuator capable alone of moving a set of components of the seat formed at least by the seat base, the backrest, and the leg rest in order to move the

Abstract: A rotor of a turbine extending around a longitudinal axis includes a rotor disc bearing at its periphery one or more rotor blades, each blade including an airfoil provided at its radially outer end with a platform equipped with an upstream lip and a downstream lip, the platform having a front lateral edge and a back lateral edge with respect to the normal direction of rotation of the rotor about the longitudinal axis, and a suction face portion which extends from the front lateral edge to the suction face of the airfoil. The upstream lip and the downstream lip each includes sawtooth-shaped cut-outs such as to form a front tooth and a back tooth which are contiguous, in that the back tooth has a cutting edge and in that the front tooth of each lip is disposed on the suction face portion of the platform.

Abstract: A stator vane assembly for a compressor of an aircraft turbine engine includes an inner shroud, an outer shroud and stator vanes. The stator vanes are attached only to the inner shroud and are in non-immobilizing mechanical contact with the outer shroud.

Abstract: A turbine for a turbomachine includes an annular row (20) of moving blades (20a) surrounded by a support ring (26) of abradable material (24) carried by a housing (10). The turbine also includes a distributor (30) mounted downstream of the moving blades (20a) and having an attachment mechanism with a radially outer spoiler (38) coming to bear radially inwards on a cylindrical wall (12) connected to housing (10). An annular wall (14) extends radially inwards from the cylindrical wall (12) and engages at its radially inner end in an annular groove (28) of the support ring (26), and in which a free annular space (40) is formed between a radially outer face (26b) of the ring (26) and the cylindrical wall (12).

Abstract: A thrust reverser for a turbojet aircraft nacelle includes a fixed structure, a movable structure and an actuator. The actuator extends along a main axis and is connected by a first connection to the fixed structure and by a second connection to the movable structure for the deployment of the movable structure between a direct jet position and a reverse jet position. The actuator is also connected to the fixed structure by a third connection arranged longitudinally between the first connection and the second connection. An axis of the third connection is radially eccentric from the main axis and the third connection allows a predetermined displacement of the actuator with respect to the fixed structure.

Abstract: An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.

Abstract: A centrifugal degasser of an air-oil mixture of a turbine engine includes a hollow shaft extending along an X axis and a pinion for rotating the hollow shaft, and an annular chamber for centrifugal separation of the mixture. The chamber is arranged around the hollow shaft and forms a fluid passage area, an inlet of which is oriented axially for feeding the chamber with the mixture, and a first outlet of which is oriented radially inwards for the outlet of the de-oiled air separated from said mixture. The chamber also includes at least one second oil outlet oriented radially outwards and configured for discharging the oil separated from said mixture to the outside of the degasser. The chamber and the pinion form a single piece.

Abstract: An installation for pre-assembling the turbine stators of a turbine each formed of several juxtaposed sectors, includes: an input carriage for conveying sectors intended to form the turbine stators. Each sector includes side faces provided with slots and being associated with a given turbine stator; an output carriage having various trays, each associated with a turbine stator; an automated device for inserting sealing pads configured to interact with a sector conveyed by an automated convey pallet, comprising a robot arm for inserting sealing pads into the slots in a side face of the sector; and another robot arm for gripping a sector equipped with pads from a pallet and depositing it on the tray associated with the turbine stator to pre-assemble the turbine stator.

Abstract: A movable close-out shroud suitably configured to substantially cover, partially block, or otherwise close out an articulating opening to a cavity, void, etc., of a first part, such as a passenger seat section. The close-out shroud is configured to move between a stored position and a close-out position.

Abstract: Described are passenger seats having a seat frame and a seat bottom slidingly and pivotally attached to the seat frame that, when the passenger seats are reclined, are configured to articulate forward from an upright configuration of the passenger seat to a second seat position corresponding to a reclined configuration of the passenger seat. The seat bottom can include an aft articulating mechanism that defines a declining first path in an aft-to-forward direction to cause the aft end of the seat bottom to drop when the seat bottom articulates forward; and a forward articulating mechanism connected with the seat bottom near a forward end of the seat bottom that defines a second path shaped to cause the forward end of the seat bottom to move upward when the seat bottom articulates forward, such that the seat bottom tilts aft in response to articulating forward when the passenger seat is reclined.

Abstract: A turbomachine sealing ring has an axis of revolution and includes an annular support, an annular coating made of abradable material which is carried by the support, and an annular thermal protection plate which is carried by the support. The ring is divided into sectors and has a plurality of ring sectors disposed circumferentially next to one another about the axis. Each ring sector has a support sector, a coating sector, and a plate sector. Each plate sector ling includes a flat tab that is pressed against a face of the corresponding support sector and is fixed to this face by brazing. The tab is inserted into a through-slot in the support sector in order to improve its integrity in operation.

Abstract: A fibrous texture has the shape of a strip extending in a longitudinal direction over a determined length between a proximal portion and a distal portion and in a lateral direction over a determined width between a first lateral edge and a second lateral edge. The fibrous texture has a three-dimensional or multi-layer weaving between a plurality of layers of warp strands extending in the longitudinal direction and a plurality of layers of weft strands extending in the lateral direction, the fibrous texture including first and second longitudinal sections extending over a width from the first or second lateral edge smaller than the determined width of the fibrous texture along the lateral direction. The first and second longitudinal sections each include warp strands and weft strands constituted by carbon fibers. The fibrous texture further includes a third section present between the first and second sections.

Abstract: A fan module for an aircraft turbomachine includes a fan with a disc carrying fan blades and a rotor of an electric machine. The rotor has an annular shape and is mounted coaxially downstream of the fan. The module further includes an annular support for the rotor with a downstream end fixed to the rotor and with an upstream end fixed to the fan disc. The support is fixed to the disc by shear bolts configured to break when a torque transmitted by the disc to the support exceeds a predetermined threshold.

Abstract: Methods for determining an operating state of a battery with respect to one or more use profiles include: a step of prior learning during which operational limits of the battery are defined depending on parameters of the battery; the operational limits defining an operational zone in which the battery carries out the one or more use profiles, and a non-operational zone in which the battery does not carry out the one or more use profiles; a step of determining the operating state of the battery for a given use profile in the course of which the parameters of the battery in operation are determined; and a comparison step in which the operational limits and the parameters of the battery are compared and the battery is positioned in the operational or non-operational zone.

Abstract: A sealing joint for an aircraft turbojet engine nacelle includes a bead designed to be mounted in a joint support. The sealing joint is characterized in that the bead includes a retaining projection which extends in a direction substantially transverse to a longitudinal axis of the sealing joint, the retaining projection being designed to extend through the joint support when the sealing joint is mounted in the support thereof and/or a sealing lip which extends under the bead in a direction substantially parallel to the longitudinal axis of the sealing joint and which is designed to be compressed on the joint support when the sealing joint is mounted in the support thereof.

Abstract: A method for repairing an end plate of a turbomachine rotor, the end plate including a crown having at least two collar fastening holes and at least one balancing-weight fastening hole located between the two collar fastening holes, each collar fastening hole being equipped with a crimped nut, the crown having a damaged portion between two collar fastening holes, the method including the steps of removing the two crimped nuts located on either side of the damage; removing the damaged crown portion, for example by machining; putting in place a strip in the form of a crown portion closing off the removed crown portion, the strip having at least one balancing-weight fastening hole and two mounting holes; fastening the strip to the crown with two crimped nuts, which penetrate the mounting holes, by crimping each nut in a collar fastening hole.

Abstract: A turbojet includes in succession, from upstream to downstream in the flow direction of a primary air stream: a low-pressure casing, an intermediate casing, and a high-pressure casing that are longitudinally aligned and which jointly delimit an internal annular passage for the circulation of the air stream. The intermediate casing delimits a portion of the annular passage called a gooseneck and includes: an air discharge system able to extract air from the air stream circulating in a first zone of the gooseneck and to discharge it outside the passage, and an air extraction system able to extract air circulating in a second zone of the gooseneck for an air conditioning system, the second air extraction zone being located downstream of the first air extraction zone.

Abstract: A one-piece fitting (56) for a stiffened panel (51) comprising a panel body (52) with a plurality of stiffeners (53, 54, 55) arranged thereon, the fitting comprising a fitting body (56) configured to be fastened, in use, to two or more of the stiffeners (53, 54, 55) so as to provide a junction to transfer load between the two or more stiffeners, wherein the fitting body further comprises an integral functional fitting (57) arranged for engagement with a component other than the stiffened panel.