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: Support (10) for holding a portable electronic device. The support includes a body (12) having an upper pivot location (18) relative to a passenger seat back, a support structure (22) coupled to the body and extendible below a lower edge of the body. The support structure is shaped to receive a lower edge of the portable electronic device and secure the portable electronic device to the body when the portable electronic device is received by the support structure.

Abstract: A method for manufacturing an aeronautical part utilizes injection molding. After injecting the prepared mixtures to obtain two green blanks, an assembly area of at least one of these two blanks is heated. The blanks are assembled and then debinding is carried out. A sintering treatment is then carried out.

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: A method for monitoring a starting sequence of a turbomachine including a compressor provided with a rotor, a starter capable of rotating the rotor and a combustion chamber, the method including determining a bracketing of a time zone during which the ignition instant takes place, the bracketing being defined by, on the one hand, a lower limit corresponding to an event necessarily taking place before the ignition instant and an upper limit corresponding to an event necessarily taking place after the ignition instant; and determining between the lower limit and the upper limit, a break point in the variation with time of the measurement signal, this break point corresponding to an ignition instant of the air-fuel mixture in the combustion chamber.

Abstract: A blade made of a composite material, the blade including a fibrous reinforcement densified by an organic matrix and being provided, in an attachment zone, with a metal element, wherein the reinforcement includes, in at least one region of the attachment zone, a surface textile orientation adapted to the direction of mechanical stresses by having first skin threads that extend in a main mechanical stress direction and that are bonded to second skin threads transverse to the first threads, the first skin threads making up most of the surface area of the region of the attachment zone.

Abstract: A method for monitoring an aircraft component, including the following steps: receiving, from a video acquisition device, a video stream that represents at least one portion of the component; in the event that the realization of a predetermined condition is detected, extracting a portion of the video stream to form a sequence of interest; identifying, within the extracted sequence of interest, at least one image of interest; including a signature, obtained using each image of interest, with at least one predetermined signature from a library of signatures; and generating an anomaly detection signal if the result of the comparison meets a predetermined criterion.

Abstract: A method for controlling a turbojet engine thrust reverser during an aborted aircraft takeoff, the thrust reverser including doors movable between a stowed position, an overstowed position and a deployed position; door actuators to move the doors between the stowed, overstowed and deployed positions; a device for locking the doors in the stowed position, moveable between a locking position and an unlocking position; and a lock actuator to move the locking device between the locking and unlocking positions. The method includes decreasing the engine speed of the turbojet engine by following a setpoint value below a first engine speed threshold value at which the aerodynamic forces being exerted on the doors are equal to the forces developed by the door actuators; controlling the door actuators to bring the doors into the overstowed position; controlling the lock actuator to bring the locking device into the unlocking position.

Abstract: A method for coating fibres includes coating short fibres having an average length less than or equal to 5 mm by chemical vapour deposition in a fluidised bed, the short fibres treated being made of ceramic material or carbon and being mixed with spacer particles distinct from the short fibres, the spacer particles having an average diameter greater than or equal to 20 ?m.

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 component for a solid-oxide electrolyte fuel cell or electrolyser provided with an anticorrosion coating, as well as such a solid-oxide electrolyte fuel cell or electrolyser, the component including an electrically conductive substrate, and an anticorrosion coating deposited on at least one surface of the substrate, the anticorrosion coating including at least one main tantalum-nitride-based layer doped with one or more dopant elements chosen from the family of the transition metals or lanthanides.

Abstract: The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23?) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.

Abstract: A sub-assembly for a low-pressure compressor of an aircraft turbine engine includes a straightener provided with cantilevered vanes and a rotor hub having a cavity covered by an inner shroud opposite the vanes. Orifices are made in the inner shroud to allow an air flow to circulate in the downstream to upstream direction of the low-pressure compressor.

Abstract: An aircraft passenger suite is provided. The suite comprises an aircraft seat for use by a passenger. The suite also comprises a controller for controlling a number of output states of the suite, the controller comprising a logic condition receiver operable to receive a logic condition input. The suite also comprises sensor equipment operable to provide a sensor input to the controller, the sensor input providing an indication of at least one attribute of a passenger of the suite. The sensor equipment comprises one or more of: an image sensor a pressure sensor and a physiological sensor. The controller is configured to control at least one of the output states of the suite based on both the logic condition input and the sensor input.

Abstract: An aircraft thruster includes at least a first propeller provided with a plurality of radial blades extending about an axis of rotation of the said first propeller, which is driven in rotation by a first electric motor. An electrical supply of the first electric motor includes power circuits carried by a fairing of the thruster characterized in that the power circuits are arranged in an annular manner in an annular part integral with the fairing of the thruster, this annular part being arranged around the said first propeller.

Abstract: The invention relates to an electronic circuit (1) comprising a plurality of printed circuits (2) connected by at least one bus bar (4), each printed circuit (2) comprising at least two superposed layers enclosing at least a portion of said at least one bus bar (4), so as to cover said at least one bus bar (4).

Abstract: An electrical contactor that includes separable contacts that include a first pair of mating contacts and a second pair of mating contacts. The electrical contactor also includes a first portion that includes the first pair of mating contacts and a solenoid plunger that is configured to receive a plunger rod; The electrical contactor additionally includes a second portion that includes the second pair of mating contacts. The plunger rod is configured to be inserted within the solenoid plunger and rotated towards the second portion to be threaded into the second portion to enable the second portion to be pulled up towards the first portion. The second pair of mating contacts are configured to move closer to the first pair of mating contacts until the second pair of mating contacts mate with the first pair of mating contacts to increase a wear allowance to a predetermined desired level.

Abstract: An acoustic attenuation panel includes a cellular structure including a plurality of acoustic cells separated from one another by peripheral partitions, a perforated acoustic structure, the perforated acoustic structure and the cellular structure being formed in one piece in a first material, and a porous acoustic layer formed of a second material and fastened to a surface of the perforated acoustic structure by entangling the first material and the second material.

Abstract: A method for densifying porous annular substrates having a central passage by chemical vapor infiltration, the method including providing stacks of porous annular substrates, providing a plurality of individual modules including stacks disposed on a support plate having a perforated injection tube each mounted on a gas inlet opening, forming a stack of individual modules, aligning the individual modules of the stack in a sealed manner by means of an annular seal disposed between the injection tube of a second individual module and the gas inlet opening of a first individual module with which it cooperates, and injecting into the internal volume of each stack of porous annular substrates a gas phase including a gaseous precursor of a matrix material to be deposited within the porosities of the substrates.

Abstract: A three-phase autotransformer including three output groups and three inputs each connected to each of the outputs of a respective output group by windings, the windings being configured so that, when each input has a respective input voltage applied thereto, the three input voltages having the same input amplitude, being 120° out of phase with each other and defining a neutral point: for each output group, a main output voltage, taken between a main output of said output group and the neutral point, has an amplitude greater than the input amplitude; and output voltages of the autotransformer belong to a same Reuleaux polygon, each output voltage being associated with a respective output and being equal to a voltage between said output and the neutral point.