Abstract: A fibrous preform for forming the fibrous reinforcement of a composite material part, the fibrous preform being made as a single piece and obtained by three-dimensional weaving, the preform including first and second skins and a longitudinal stiffening portion connecting the first to the second skin, the longitudinal stiffening portion forming a stiffening element of the part in the longitudinal direction. The preform has an intermediate portion extending in the longitudinal direction between two end portions. The longitudinal stiffening portion includes, in the intermediate portion, longitudinal non-woven threads or strands held together by first transverse threads or strands coming from the first skin and second transverse threads or strands coming from the second skin. In the end portions, the longitudinal threads or strands of the longitudinal stiffening portion are woven with the transverse threads or strands.

Abstract: A method of configuring an aircraft electrical system. The aircraft electrical system comprises a wiring harness and a plurality of electronic modules. The wiring harness comprises a plurality of connection points. The method comprises: connecting a first electronic module in the plurality to the wiring harness via a first connection point in the plurality; transmitting by the first electronic module, a connection point identification request; in response to the transmitting, receiving at the first electronic module from the wiring harness, an identifier of the first connection point; on the basis of the received identifier, determining configuration data for the first electronic module, the configuration data being associated with the first connection point; and configuring the first electronic module to operate in accordance with the determined configuration data.

Abstract: A system for conditioning fuel configured to supply a main turbomachine, based on fuel from a cryogenic tank, comprising a pump configured to operate at a predetermined constant speed, at least one heat exchanger, a supply member for supplying the main turbomachine with a fuel flow, the supply member being configured to deliver a nominal flow rate when the pump is operating at a predetermined constant speed, at least one buffer tank, a first valve for controlling the supply of fuel to the buffer tank, a second valve for controlling the distribution of the fuel flew flow and a regulating device that is configured to open the second valve when the setpoint flow rate is higher than the nominal flow rate.

Abstract: The invention relates to an aircraft turbomachine subassembly comprising an annular duct (36) extending concentrically about a longitudinal axis and in which an air stream flows from upstream to downstream, the annular duct comprising a duct portion (28) defining a swan neck having an upstream inlet section and a downstream outlet section. A plurality of radial arms (B1, B2) extend circumferentially in the duct portion (28). One or several intermediate walls (P1, P2) extend between two circumferentially adjacent arms (B1, B2) which form a pair of circumferentially adjacent arms among the plurality of circumferentially adjacent arms so as to locally separate, between the two arms of the pair of arms, the annular duct portion (28) into a radially inner portion (Ci) and a radially outer portion (Ce) further away from the longitudinal axis than the radially inner portion.

Abstract: An assembly for an aircraft propulsion system including a nacelle extending around a longitudinal axis and including an internal face that delimits, with an external face of the aircraft propulsion system, a fire zone, an extinguisher for extinguishing a fire in the fire zone, the extinguisher including a tank for containing an extinguishing agent, and a spraying nozzle for spraying the extinguishing agent out of the tank and into the fire zone, an activation device for activating the extinguisher, and a controller that transmits a control order to the activation device, the activation device receiving the control order and transmitting an activation order to the extinguisher, the activation order activating the extinguisher so as to cause the expulsion of the extinguishing agent via the nozzle. The extinguisher is mounted on the nacelle. The assembly includes one or more of a wireless communicator and a cable.

Abstract: An assembly for an aircraft gas turbine engine includes a nacelle extending substantially around a longitudinal axis and including a fixed structure disposed around the aircraft gas turbine engine, the fixed structure including an internal surface suitable for delimiting with an external surface of the gas turbine engine a fire zone of the nacelle, a thermal protection covering the internal surface of the fixed structure of the nacelle at the level of the fire zone of the nacelle, and an extinguisher designed to extinguish a fire in the fire zone of the nacelle, the extinguisher including a tank suitable for containing an extinguishing agent. The tank is located between the thermal protection and the internal surface of the fixed structure of the nacelle.

Abstract: A method includes receiving an operating setpoint for an electrical power source, receiving a measurement of a voltage of an electrical bus connecting the electrical power source to an electrical receiver, comparing the measurement of the voltage with a template having limits of change over time for the voltage, and controlling the electrical power source such that if the measurement of the voltage lies within the limits of the template, the electrical power source applies the operating setpoint, and if the measurement of the voltage lies outside the limits of the template, the electrical power source regulates the voltage so as to restore the voltage to within the limits of the template. The method is implemented by a controller of the electrical power source.

Abstract: An architecture for supplying air to a high-pressure compressor of an auxiliary gas generator from a pressurized cabin of an aircraft, comprising: a load compressor rotationally driven by a common rotation shaft providing a mechanical coupling between the high-pressure compressor and a high-pressure turbine of the auxiliary gas generator and supplied by an outside air intake; a first regulation valve assembled at the outlet of the load compressor to control all or part of the air flow delivered by the load compressor; a second regulation valve assembled at the outlet of the pressurized cabin to control the air flow drawn from inside the pressurized cabin; a mixer receiving the outputs of the first and second regulation valves to add the air drawn from inside the pressurized cabin to all or part of the air delivered by the load compressor.

Abstract: A fibrous structure intended to form the fibrous reinforcement of a part made of composite material includes a fibrous reinforcement densified by a matrix, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The fibrous structure includes at least a first portion having a first type of weave and a second portion, continuing on from the first portion, having a second type of weave, the warp yarns and the weft yarns having a degree of interweaving in the first type of weave that is greater than the degree of interweaving of the warp yarns and the weft yarns in the second type of weave.

Abstract: A thrust reverser for an aircraft propulsion unit, including a movable system with cascade vanes and an actuator allowing moving a movable system between an advanced direct thrust position and a backward thrust reversal position, the system also including an inter-cascade structure for limiting buckling of the actuator, forming a channel crossed by the actuator and delimited by a cylindrical internal surface extending along a first closed directrix curve, the fixed portion of the actuator including an end equipped with an external ring for limiting buckling of the actuator, the ring having a cylindrical external surface extending along a second closed directrix curve, the first and second closed directrix curves preferably having the same shapes and being concentric while being spaced apart from one another with the same spacing.

Abstract: An abradable coating includes a tubular cell structure, wherein the the tubular cell structure includes a fibrous reinforcement of discontinuous short fibers which is densified by a ceramic matrix.

Abstract: A method determines the angular setting (?_2) of an annular row of stator vanes arranged downstream of a pusher propeller of a propulsion system with a longitudinal axis. The annular row of stator vanes receives an air flow having a velocity (V2) including a longitudinal component (Viz) and a tangential component (V_i?) associated with the velocity of gyration generated by the pusher propeller. The method includes the steps of establishing a theoretical model of the pusher propeller using a power (P1) and a mechanical speed (N1) associated with said pusher propeller, and flight conditions that include a velocity of the airflow incident on the pusher propeller, the altitude of said propulsion system and ambient temperature. The method further includes the step of determining an angular setting (?_1) of the pusher propeller from the theoretical model.

Abstract: A method for parameterizing a digital filter for attenuation of a torsional mode of a power transmission line of an aircraft turbine engine is disclosed. The mode is associated with a frequency in a confidence interval, the digital filter is low-pass and described by a transfer function equal to the quotient N(z)/D(z), integrated into a pre-existing monitoring loop of the turbine engine, to filter signals sampled at a frequency. The method includes: calculating zeros of N(z), so that the filter attenuates the frequency; updating the zeros of N(z), so that the gain of the filter satisfies, in the interval, a first gain template; and determining the poles of D(z), so that, in the bandwidth of the loop: the phase of the filter satisfies a phase template, and the gain of the filter satisfies a second gain template.

Abstract: An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Abstract: An aircraft wheel and brake assembly includes a wheel, a brake configured to brake the wheel, and a measurement device configured to measure the speed of rotation of the wheel. The brake includes at least one friction member, an actuator support, and at least one brake actuator carried by the actuator support and configured to exert a braking force selectively on the friction member. The measurement device includes a target and a sensing component for producing a measurement signal representative of the speed of rotation of the target. The aircraft wheel and brake assembly is configured in such a manner that, when assembled, the target is constrained to rotate with the wheel and the sensing component is mounted on the actuator support. The target and the sensing component is configured in such a manner that the sensing component detects rotation of the target.

Abstract: The electrical insulating element for a stator comprising a stack of magnetic sheets having at least one first stator tooth and comprising at least one first stator coil wound around the first stator tooth, the first stator tooth having a first end face located at one end of the stack of magnetic sheets, the insulating element comprises an electrically insulating foil having a face coated with adhesive. The insulating element is configured to be inserted between the first face of the first stator tooth and the stator coil, the face coated with adhesive being adhered to the first face.

Abstract: A casing for a turbomachine includes an internal hub, an external flange coaxial with the internal hub, arms extending radially from the internal hub to the external flange, each arm having a wall, two or more wire harnesses that connect a first electrical apparatus, which is arranged radially outside the external flange, and a second electrical apparatus, which is arranged radially inside the internal hub, a sheath extending within an arm at a distance from the wall of the arm, the sheath including an internal face defining an internal cavity that receives the two or more wire harnesses, and one or more shims mounted in the sheath and holding the wire harnesses at a distance from an internal face of the sheath and holding the wire harnesses at a distance from one another within the sheath.

Abstract: A process for additive manufacturing of a part by successive deposition of layers of powder layers is provided. The process steps are performed within a manufacturing machine having a preparation zone for at least one layer and a consolidation zone for the powder, offset from each other. The process includes: (a) preparing at least one layer comprising at least two zones filled with at least two different powders, e.g., of different materials and/or particle sizes, in the preparation zone; (b) moving the at least one layer into the consolidation zone; (c) placing the at least one layer on either a manufacturing support or on an already consolidated portion of the part; and (d) consolidating at least one portion of the at least one layer by sintering, by melting, or by adding a binder.

Abstract: The present invention concerns a metal powder for an additive manufacturing method, the metal powder comprising a nickel-based alloy comprising between 0.02% and 0.04% of carbon, between 18% and 22% of chromium, between 11% and 13% of cobalt, between 5% and 5.5% of niobium, between 3% and 3.5% of tantalum, between 3% and 3.4% of molybdenum, between 0.9% and 1.1% of titanium, between 0.4% and 0.6% of aluminium, between 0.003% and 0.005% of boron, not more than 0.5% of iron, not more than 0.1% of copper, not more than 0.1% of silicon, not more 10 than 0.05% of manganese, not more than 0.01% of phosphorus, not more than 0.01% of zirconium, not more than 0.004% of magnesium, not more than 0.003% of sulfur, not more than 0.025% of oxygen, not more than 0.018% of nitrogen and not more than 0.003% of hydrogen.

Abstract: A hydraulic assembly for an aircraft engine includes a pump with a housing and a rotor arranged inside the housing. The housing has at least one hydraulic line configured for the passage of a fluid; and a hydraulic transfer unit comprising: a hydraulic transfer block attached to the housing and comprising an internal fluid passage channel which communicates with the hydraulic line, and a casing which covers the transfer block and which is guided in rotation about an axis of revolution (Y) and about the transfer block, the casing having a fluid outlet port that communicates with the internal channel.