Abstract: The turbine (12) for a turbine engine (100) extends around a major axis (X-X) and comprises: —a casing (4) comprising an annular hook (38), —a movably mounted impeller (16), —a ring (30) extending opposite the impeller in a direction radial to the major axis (XX), —a distributor (14) comprising a blade provided with a platform (11), the platform being extended radially outwards by a spoiler (22, 24), the spoiler (22, 24) being radially mounted on the hook (38), and —foils (40) each having a profiled trough shape in a direction circumferential to the axis, the foils extending in succession in the circumferential direction, each foil (40) extending between the spoiler (22, 24) and the hook (38). The turbine comprises stops (162) to prevent the foils (40) from moving in the circumferential direction. Each foil (40) comprises a protrusion (162) arranged so as to extend circumferentially opposite another protrusion (162) of another adjacent foil (40).

Abstract: A control system includes an actuator, a locking/unlock device, a central control valve, first and second control valves, and a spool control valve. The actuator is arranged so as to move a door of a thrust reverser between direct jet and reverse jet positions. The locking/unlocking device unlockable under load allowing locking and/or unlocking of the door. The locking/unlocking device is movable between a closure position in which it holds the door in the direct jet position and an opening position in which the door is released. The first and second control valves each fed by the central control valve. The spool control valve fed at least by the first and second control valves. The spool control valve is configured so that a pressure difference between two inlets of the first and second control valves provides a displacement of the spool control valve between first and second stable positions.

Abstract: A passenger seat assembly can include a seat frame; a seat back supported by the seat frame, comprising a rearward surface, and moveable between a stowed position and a deployed position; and a monitor shroud positioned proximate to the rearward surface of the seat back and fixedly coupled to a stationary surface, wherein the monitor shroud remains stationary as the seat back moves between the stowed position and the deployed position, and the monitor shroud defines an opening that provides access to the rearward surface of the seat back.

Abstract: A part for a centrifugal breather for an air/oil mixture of a turbomachine is configured to rotate about a longitudinal axis of symmetry. The breather forms an annular chamber for centrifugal separation of said mixture. The chamber includes mesh structure that takes up at least one space in a duct which closes communication between an axial inlet and an internal radial outlet. The mesh structure is formed by the spatial repetition of the material or of the space of a single pattern produced by the interconnection of simple shapes. The pattern is designed such that the spaces between the materials paths passing through the materials in at least three dimensions of space forming a trihedron.

Abstract: A remote towing interface is used to couple a towbar to an aircraft having a fuselage and a steerable landing gear. The remote towing interface includes a towbar coupler mounted to the aircraft and configured to releasably couple a towbar to the aircraft. The remote towing interface further includes a sensor and a controller. The sensor is configured to sense a position of the towbar relative to the aircraft when the towbar is coupled to the towbar coupler, and the controller controls the steerable landing gear according to the sensed position of the towbar relative to the aircraft.

Abstract: A turbomachine turbine nozzle extending around a central axis, including at least one radially outer shroud, at least one radially inner shroud, and at least one blade made of ceramic matrix composite material, distinct from the radially inner shroud and from the radially outer shroud, and extending radially between the radially inner shroud and the radially outer shroud, the blade being hollow and including a cavity opening at a radially inner end and at a radially outer end of the blade, the nozzle including at least one tubular mast arranged in the cavity of the blade and allowing routing the ventilation air passing through the cavity of the blade, the mast including a radially outer end attached to the radially outer shroud, and a radially inner end cooperating with a radial flange for positioning the radially inner shroud.

Abstract: A method for manufacturing an integrally formed bladed disk of a turbomachine, includes manufacturing a plurality of blades, the blades including a root and a profiled portion; and spark plasma sintering the blades with a metal powder, the blades being angularly distributed over a contour of an annular spark plasma sintering mold, the root of the blades being embedded into the metal powder, the profiled portion of the blades protruding from the metal powder radially outwardly.

Abstract: In order to fill a reservoir while avoiding laborious manual filling operations, there is added to the existing device, including a supply duct, a pump and a measuring probe, a stop valve designed to interrupt the filling as soon as the desired level has been reached, which is detected for example by an air intake which controls the closure of the valve. Two level indicators are added and make it possible to ascertain either that optimum filling has been achieved or that a malfunction is present in the system. Application to the systems for oil filling of aircraft engine reservoirs from another reservoir arranged within the aircraft, generally common to all the engines.

Abstract: The present invention relates to a bidirectional data communication method for a bidirectional data communication system (100), in particular an embedded bidirectional data communication system (100), comprising: at least one first communicating device (200a) configured to implement a single-pair Ethernet protocol and one second communicating device (200b) configured to implement a single-pair Ethernet protocol and comprising a second packet management module (220b) connected to a first physical link management module (231b) and to a second physical link managment module.

Abstract: An uplock for the selective retention of a capture pin of a movable element includes a hook, a locking member, and a detector. The hook is movable between a release position and a retaining position for retaining the capture pin. The locking member moves between a locked position, and an unlocked position. The detector detects whether the hook is in the retaining position and the capture pin is in the hook. The detector includes a sensor movable relative to a target. The target or the sensor is carried by the locking member and the other by an indicator lever which is movable between a first position indicating absence of the capture pin in the hook and a second position indicating presence. The target and the sensor are only in the proximate position if the locking member is in the locked position and the indicator lever is in the second position.

Abstract: A ventilation ring for a bearing support member of an aircraft turbine engine includes two or more tubular walls and one or more spacer walls. The two or more tubular walls extend opposite each other, and one or more of the tubular walls includes a main portion and a base, the base having a thickness greater than a thickness of the main portion. The one or more spacer walls connect the two or more tubular walls. The one or more spacer walls have one or more apertures extending into the base and a rim around the aperture. An entirety of the rim has a thickness greater than a thickness of the spacer wall at a distance from the rim.

Abstract: An assembly including a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer skin and the inner skin, and the nacelle panel having a free inner enclosure contiguous with the outer skin, and a member forming a link including one or more degrees of freedom, the member being attached to the nacelle panel solely by one or both of the outer skin and the inner skin, and the member extending facing the free inner enclosure.

Abstract: An assembly includes a nacelle panel of an aircraft engine, the nacelle panel including an outer skin, an inner skin and a central layer interposed between the outer and inner skins. The central layer has a housing, the outer skin has an opening which opens into the housing, and a linking member extends in the opening and in the housing, the linking member to be connected to an actuator.

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 system and method for replacing or retrofitting aircraft galley monuments that include standard inserts therein with monuments that include at least some spaces for larger non-standard inserts.

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: A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

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: A thrust reverser includes a diverter configured to divert at least a portion of an air flow from a nacelle and a cowl movable relative to an outer fixed structure of the thrust reverser. The thrust reverser further includes at least one rotatably hinged flap. The cowl configured to move from a closure position in which it provides aerodynamic continuity of the nacelle with the flap and covers the diverter. The flap is movable from a retracted position to an opening position in which it opens a passage in the nacelle and uncovers the diverter. The flap obstructs a portion of an annular channel of the nacelle when in the opening position. The thrust reverser also includes a cable-pulley system for driving the flap. The cable-pulley system includes at least one cable associated with at least one pulley to connect the flap to the thrust reverser.

Abstract: The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15).