Abstract: A removable closure member is configured to close a female portion received in an external opening formed in the external surface of a nacelle for an aircraft engine. The female portion includes at least one air inlet opening. The closure member includes a base that forms the external contour of the member and that extends beyond the external opening of the nacelle so as to move into abutment against the external surface of the nacelle. The closure member further includes at least one resiliently deformable position retention member that projects from the base and is configured to be inserted into the air inlet opening.

Abstract: An aircraft propulsion assembly has a hinge for articulating a first and a second of its panels. The hinge includes a yoke rigidly connected to the first panel and a counter-yoke rigidly connected to the second panel, which is received between two lugs of the yoke.The yoke and the counter-yoke are passed through by a hinge pin that is movable between an extended position between the lugs of the yoke and a retracted position outside the yoke. The hinge further includes bayonet mounting means interposed between the pin and the yoke.

Abstract: A vane of a turbine engine blade includes a first portion of structural resistance formed by two end portions including the leading and trailing edges and end strips of the lower surface and the upper surface, and of a core joining them. Two other portions of the blade are constructed of light material, composite for example, between the end portions to reconstitute the complete vane. The core has an oblique or diagonal extension between the end portions.

Abstract: The invention relates to a method for verifying the positioning of a fibrous preform in a blade, the blade having been obtained by injecting a resin into a mould having the shape of a blade and in which a preform has been placed, the blade extending in an orthonormal blade frame of reference X, Y, Z, the blade comprising a blade root extending longitudinally along an axis X, a vane extending from the blade root along an axis Z, the blade having a thickness defined along an axis Y, the preform comprising glass tracers positioned at the surface of the preform, the centre of the tracers defining a neutral axis located at a height along the axis Z in the direction defined by the axis X, the method comprising the following steps: the acquisition (E31) of tomographic 2D projections of the blade using an imaging system comprising an X-ray source, each projection being acquired at a given orientation of the X-ray source with respect to the blade; the combining (E32, E32a, E32b) of the 2D projections in the direction

Abstract: A bistable electromagnetic actuator includes a housing extending along an exertion axis of the actuator, two excitation coils arranged inside the housing and having at least one winding around the exertion axis for generating a magnetic control flux, a core that can be moved along the exertion axis and immobilized in two end positions depending on the magnetic flux generated by the coils, an actuating member coupled to the core to form a movable assembly, and a manual control device comprising a drive shaft mounted such that it can rotate about a first axis orthogonal to the exertion axis. The drive shaft has at least one tooth engaging with at least one first raised part translationally connected to the actuating member such that rotation of the drive shaft generates translational movement of the movable assembly.

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 having has a support sector, a coating sector, and a plate sector. Each plate sector having 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: The invention relates to a braking device (1) of an aircraft wheel, comprising a ring (15) which has a plurality of cavities (17) in which actuators (18) are fitted in order to apply a braking force to a stack of discs (11) which extend opposite the ring. The ring is provided with a heat shield (25) which extends opposite a face of the ring directed towards the stack of discs in order to protect the ring from thermal radiation which is generated by the stack of discs. According to the disclosure, the heat shield is provided with holes (26) through which the actuators extend and which have a sectional profile which is formed to reflect the thermal radiation away from the device.

Abstract: A modular tray, for the additive manufacturing of a part with an axis of revolution on a powder bed, includes: a shaft-mounted circular module including a shaft provided with a circular tray at one of the ends thereof, the shaft and the circular tray being concentric; and a main support module including, in one face, a cavity configured for receiving the shaft-mounted circular module, the shaft being completely inserted in the cavity. The assembly of the shaft-mounted circular module and of the main support module define a planar top surface that is at least partly formed by the circular tray of the shaft-mounted circular module.

Abstract: An aircraft wheel (1) comprising a hub connected to a rim (3) provided with a tire (100), the hub having an outer surface that extends facing an inner surface (4) of the rim (3) and that co-operates therewith to define an annular space for receiving a stack of brake disks including rotor disks having axial peripheral notches, each notch receiving a segment of an axial bar (10) extending projecting from the inner surface (4) of the rim (3), and respective heat shields (20), each in the form of an annular segment, being mounted between the two bars (10) of respective pairs of adjacent bars. Each heat shield (20) includes at least one holder portion bearing against at least one first abutment (19, 119) secured to the rim (3) in order to hold the heat shield (20) in position on the rim (3) elastically.

Abstract: A manufacturing method of an acoustic coating in an ordered array of interconnected micro-channels intended to receive, on a reception surface, an incident acoustic wave with direction Ac normal to this surface, the method including depositing a sacrificial material on a substrate surface to form a three-dimensional scaffold of filaments, infiltrating at least one part of the three-dimensional scaffold with a thermosetting material, solidifying the thermosetting material to form a solidified material, and removing the sacrificial material from the solidified material to form the ordered array of interconnected micro-channels, the filaments forming by superimposed layers the three-dimensional scaffold being, for a given layer of filaments, oriented in a direction forming, in a plane formed by the layer, a first angle ? relative to the direction Ac of the incident acoustic wave, to confer acoustic properties to the ordered array of interconnected micro-channels and thus form the acoustic coating.

Abstract: The invention relates to the production of a composite material of a lobed structure (10) of a flow mixer which comprises a portion having a plurality of lobes (17, 19). For this purpose, a fibrous preform containing a resin will be produced in a simple geometric configuration of developable revolution. This is an intermediate state. By exploiting the thermoformable or thermosetting nature of the resin, the geometry of this intermediate preform is modified to deform it with limited offsets towards the final geometry.

Abstract: A profiled structure for an aircraft or turbomachine is elongated in a direction in which the structure has a length exposed to an airflow and includes serrations defined by successive teeth and depressions. The serrations may be transverse to a leading edge and/or a trailing edge of the profiled structure and in the direction of elongation. Along the profiled leading edge and/or profiled trailing edge, the successive teeth and depressions may extend only over a part of the length exposed to the flow. The amplitude and/or spacing of the teeth may vary monotonically except for the few teeth nearest each end of the part, with a remaining part of the length being smooth.

Abstract: A method for controlling a clearance control valve of a turbomachine wherein, during a maneuver to increase engine speed in cruise phase, a command to reduce the opening of the clearance control valve is actuated by a Full Authority Digital Engine Control based on a change in the state of a step-climb signal provided by a flight management system in order to increase clearances at the tips of the turbomachine blades and an increase in the opening of the clearance control valve follows its reduction, at the expiry of either of the following two time limits: a first time limit starting at the change in the state of the step-climb signal and determined not to penalize the performance of the engine for too long and a second time limit starting at the end of the maneuver and determined as a function of a thermal time constant of the casing.

Abstract: Locking device comprising: a support, a first locking member and a second locking member, the first locking member being mounted on the support and configured to move between a locked position and an unlocked position, an intermediate member movable between a retaining position and a release position, the intermediate member in the retaining position retaining the first locking member in the locked position, and a shape-memory member, the shape-memory member being connected to the intermediate member and configured to move the intermediate member to the release position when the shape-memory member is activated.

Abstract: A manufacturing method for a component made from composite material, in particular of a turbomachine, includes the steps of producing a preform with a fibrous reinforcement comprising a first fibrous portion and a second fibrous portion, and injecting a pressurized matrix into an injection chamber of an injection mold, in which the preform is arranged. The method further includes the steps of polymerizing the preform and positioning a flexible pocket that encloses a fluid and that is arranged between the first fibrous portion and the second fibrous portion before the injection step. The fluid is configured to apply an additional pressure to the preform of the fluid during the polymerization step.

Abstract: A pressure regulating device includes an on-board storage tank, a mixing chamber, first and second lines, a recirculation line, a pressure sensor and a controller. The storage tank stores and supplies cryogenic fuel to a combustion chamber and includes a booster pump. The first line supplies cryogenic fuel in the liquid state and includes a pressurizing pump and a first regulation valve. The second line supplies cryogenic fuel in the gaseous state and includes a compressor and a first control valve. The recirculation line includes a second regulation valve and with a first heat exchanger. The pressure sensor detects the pressure inside the storage tank. The controller receives the pressure and controls the first and second regulation valves, the first control valve, the pressurizing pump, the booster pump and the compressor, as a function of a value of a setpoint pressure inside the storage tank.

Abstract: A shaft assembly (22, 32) for an aircraft turbine engine (1), comprising a first outer shaft (32) and a second inner shaft (22), the first outer shaft being intended to be engaged axially on the second shaft and comprising inner longitudinal splines (34) for coupling with outer longitudinal splines (24) of the second shaft, characterised in that, when the first and second shafts are in the coupling position, the inner and outer splines are engaged in one another and cooperate with each other in an axial coupling area (Z), the inner and outer teeth being situated outside this coupling area.

Abstract: The invention relates to a communication network for an aircraft comprising at least one processing member and a first switch which is connected to the first processing member in order to provide data exchange within the first processing member and/or between the first processing member and at least one user terminal remote from the first processing member and connected to the first switch. According to the invention, the first switch comprises local means for observing logical communication channels of the first switch, and the first processing member includes means for controlling said observation means.

Abstract: A turbomachine compressor module comprising an annular array of struts provided with pivotable flaps. The struts can define inter-strut spaces between two circumferentially adjacent struts, and variably oriented stator vanes are disposed at least partially in the inter-strut spaces. Also, a turbomachine having such a module and a row of rotor blades directly downstream of the module.

Abstract: A jet for lubricating a piece of a turbomachine for an aircraft such as an airplane, including a circulation duct for flowing a pressurised fluid, includes a first duct chamber, a second duct chamber, a first nozzle for passing between the first duct chamber and the second duct chamber, the first nozzle having a fixed minimum passage cross-section, and a second nozzle for passing from the second chamber to the outlet port formed by the second nozzle, the second nozzle including a fixed minimum passage cross-section. The ratio of the cross-section of the first nozzle to the cross-section of the second nozzle is between 0.16 and 3.61.