Abstract: The invention relates to a method for producing a part made of a nickel-based alloy with a Y/Y? microstructure in which at least one hot-forging step is performed, which method is characterised in that the temperature at which the part is heated in the forging step is maintained within a temperature range lower than the abnormal grain growth temperature range of the alloy, the hot-forging temperature being maintained at a temperature lower than the temperature of the part, the hot-forging temperature being such that the difference compared with the temperature at which the part is heated is less than 250° C. and preferably less than 150° C.

Abstract: The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

Abstract: A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk further including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface, a shroud having a second platform which has a radially inner surface, and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge. The shroud is formed of a material and has a defined difficulty.

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: A thrust reverser for an aircraft propulsion assembly, including a fixed structure equipped with at least one cascade as well as a radially inner delimiting wall of a secondary vein, and a movable structure including at least one reverser cowling, the cascade being arranged, in the forward direct thrust position, in a housing of the reverser cowling, and, in the retracted thrust reversal position, the wall reveals a passage opening of the secondary vein towards the cascade, the thrust reverser also including at least one sealing membrane designed to deflect at least one portion of the secondary flow. A hook is provided for securing the membrane to a rear cascade support frame, and to the radially inner delimiting wall of the secondary vein.

Abstract: A thrust reverser for an aircraft propulsion assembly, including at least one sealing membrane designed to deflect at least one portion of the secondary flow towards a set of cascades when the movable structure of the reverser is in the retracted thrust reversal position, the reverser also including a first flexible hook connecting a first end of the membrane to the fixed structure of the reverser, a second hook connecting a second end of the membrane to the fixed structure or to the movable structure, the second hook being fixed to the radially inner delimiting wall of the secondary vein, or guided by an internal guide fixed to the same radially inner delimiting wall.

Abstract: A device and method for measuring angles of orientation of an x-ray imaging system including an x-ray source, an x-ray detector and a sample holder arranged to receive a sample to be analysed. The method includes: emitting a polychromatic x-ray beam through a reference sample installed on the sample holder in order to form a diffraction pattern on the sensing area of the x-ray detector, generating, with the x-ray detector, an observed image comprising the diffraction pattern, and determining the orientation of the x-ray source and the orientation of the x-ray detector by comparing the observed image with at least one target image comprising a diffraction pattern obtained for the reference sample with preset orientations of the x-ray source and of the x-ray detector.

Abstract: The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including: at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device, a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine, a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.

Abstract: A method for manufacturing a metal part includes forming by additive manufacturing a blank of a first portion of the part to be manufactured including a first binder and a first metal powder present in the first binder, forming by injection molding a blank of a second portion of the part to be manufactured including a second binder and a second metal powder in the second binder, debinding the blank of the first portion and the blank of the second portion, and joint sintering of the first debound blank and of the second debound blank to obtain the part, the first and the second blanks being in contact during sintering.

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 fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.

Abstract: A breathing apparatus for aircraft includes a breathing mask with an oronasal face cover and a support. The oronasal face cover has a cavity and the support supports a transparent lens and has an upper edge portion. An inflatable harness extends around the user's head opposite the shell and includes at least one rear portion. A guiding link includes an upper end linked to the upper edge portion and a lower end, the upper end being linked to the upper edge portion, the lower end being linked to the rear portion of the harness. A plate is linked to the lower end of the guiding link and has an abutment face that contacts the oronasal face cover, facing the cavity.

Abstract: A device for shaping at least one fibrous preform of a bladed part of a turbine engine, the device including a mould formed of multiple parts nested inside one another, the mould defining an internal cavity for enclosing the preform entirely, the cavity having two platform zones and a blade zone extending between the two platform zones, wherein the mould includes at least a lower shell, an upper shell, a side shell, and end shells, and in that each of the side and end shells includes three elements, respectively lower, intermediate and upper.

Abstract: A multi-flow turbine engine for an aircraft, the turbine engine having a gas generator with geometrical characteristics allowing it to have at its periphery a cold compartment larger than its hot compartment.

Abstract: A thrust reverser including a sealing membrane designed to deflect at least one portion of a secondary flow towards a deflection cascade when a movable structure of the reverser is in the retracted reverse-thrust position, the reverser including a rear frame for supporting the deflection cascade. The reverser further includes an interface device between the sealing membrane and a rear cascade structure including the rear cascade support frame, the vanes located furthest back on the deflection cascade, and a bearing member via which the cascade bears against the rear cascade support frame. Moreover, the device forms an elastic clip mounted around the rear structure, and a rear clip portion whereof is arranged behind the structure.

Abstract: A system for delivering breathing gas to passengers includes: a face mask including a face part having a breathing cavity, a tube configured to be supplied by pressurized breathing gas, and a reservoir bag disposed between the tube and the face part. A passage connects the reservoir bag to the breathing cavity so that the system is configured to supply the breathing cavity through the reservoir bag. The reservoir bag includes a front portion and a back portion. The front portion is connected to the face mask, and the system has a stowed configuration and a deployed configuration. In the stowed configuration, the reservoir bag is maintained folded between a backing and the face part.

Abstract: Described are mounting assemblies for an item of aircraft furniture in an aircraft. The mounting assemblies each include a base, a first connector, and a second connector. The base includes a first slot elongated in a first direction and a second slot elongated in a second direction. The first connector is retained within and is movable within the first slot, and the second connector is retained within and is movable within the second slot. The first connector and the second connector may be simultaneously movable in the first direction and the second direction.

Abstract: The invention relates to a bar (10) for a braked aircraft wheel (103), the bar being for fitting to a rim (104) of the wheel in order to drive rotor brake disks (106b) in rotation. The bar comprises a substantially rectilinear body (11) having at least one segment (14) including two wings (15) connected together by a core (16) and intended to co-operate with the rotor disks. At least one brace element (17) connects a free edge of each of the wings to a central portion of the core.

Abstract: A foil and a root of a blade of a turbomachine rotor and includes a base, two side limbs that are connected to each other by the base, at least the first limb includes at least one recess including at least two folds in two different directions, the recess being capable of engaging with a notch provided in the root of the blade to ensure the foil is longitudinally retained relative to the root of the blade at least in a longitudinal direction.

Abstract: A passenger seat assembly includes a leg, a crushable insert, and a connector assembly. The leg includes an end and a slot extending through the leg proximate to the end, and the slot has a first slot end a second slot end. The crushable insert is retained within the slot, and the connector assembly may connect the leg with a track fitting assembly. The connector assembly includes at least one connector that is at least partially positioned within the slot between the second slot end and the crushable insert such that the connector deforms the crushable insert during a dynamic event.