Abstract: metal blade including a first part and a second part each made of different materials, and the method including: a first heat treatment at a first temperature, the first heat treatment being undergone by only the first part of the metal blade, and a second heat treatment at a second temperature lower than the first temperature, the second heat treatment being undergone by the second part of the metal blade.

Abstract: The invention relates to a nickel-based superalloy comprising in weight percentages: 5.0 to 6.0% of aluminium, 6.0 to 9.0% of tantalum, 1.0 to 5.0% of cobalt, 5.0 to 7.5% of chromium, 0 to 1.0% of molybdenum, 4.0 to 6.0% of tungsten, 0.50 to 3.5% of rhenium, 1.0 to 4.0% of platinum, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and to a turbomachine comprising such a blade.

Abstract: An electrical system for a gas turbine engine includes a power supply bus, first and second converters, and a monitoring device connected to the first and second converters. The monitoring device receives a monitoring signal representative of a correction associated with a difference between a measurement of a voltage of the bus and a reference, performs a frequency filtering of the monitoring signal to determine low and high frequency components, pilots the first converter to compensate for a change in a voltage of the bus and being implemented from a first part of the low-frequency component and a first part of the high-frequency component, and pilots the second converter to compensate for the change in the voltage of the bus and being implemented from a second part of the low-frequency component and a second part of the high-frequency component.

Abstract: An electrically interconnecting member configured to electrically join a printed circuit board belonging to a mechanical part to a piece of electrical equipment. The printed circuit board comprising output tracks. The electrically interconnecting member comprising: a contact surface configured to be fastened to the mechanical part, a free surface opposite the contact surface, input terminals placed on the contact surface and configured to be superposed on the output tracks of the printed circuit board, and output interfaces placed on the free surface at distance from the input terminals and configured to be connected to the piece of electrical equipment, at least one input terminal comprising a cavity configured to receive a conductive adhesive so as to connect together the input terminal and the output terminal when they are superposed.

Abstract: A system for cooling a liquid for lubricating an aircraft turbomachine, includes an exchanger including a cooling volume and a circuit for cooling a heat-transfer fluid by a loop for circulating the two-phase fluid, with thermocapillary pumping. The cooling circuit includes a condenser including channels connected in parallel to one another in order to make it possible to cool the fluid circulating in the condenser from a vapour state to a liquid state, a first capillary evaporator of the exchanger in order to absorb the heat of the lubricating liquid in the first volume, the first evaporator including a capillary porous wick for separating the heat-transfer fluid in the two-phase state between a liquid state and a gaseous state by a capillary pressure jump.

Abstract: The invention relates to a metal powder for a metal injection moulding method, the metal powder being formed of a cobalt-based alloy comprising: —between 23.00 wt % and 24.25 wt% chromium; —between 9.00 wt % and 11.00 wt % nickel; —between 6.50 wt % and 7.50 wt % tungsten; —between 3.00 wt % and 4.00 wt % tantalum; —between 0.45 wt% and 0.60 wt % carbon; —between 0.30 wt % and 0.50 wt % zirconium; —between 0.15 wt % and 0.25 wt % titanium; —at most 2.00 wt % iron; —at most 0.30 wt % silicon; —at most 0.10 wt % manganese; —at most 0.10 wt % copper; —at most 0.015 wt % sulphur; —at most 0.015 wt % phosphorus; —at most 0.010 wt % boron; —at most 200 ppm oxygen; —at most 200 ppm nitrogen; —at most 100 ppm hydrogen.

Abstract: Method for the automated weaving of a woven structure (30) by means of a weaving machine (1), comprising the insertion of a weft thread during the opening of a shed of warp threads, and prior steps of optimization, by an optimization tool (20), of an objective function having a first member evaluating the balance of said warp threads during the shed opening, said balance of the warp threads being evaluated by differences in elongation between the warp threads of an upper opening (10a) of said shed, and of a lower opening (10b) of said shed, and a second member evaluating constraints specific to the weaving machine (1). This optimization comprises the determination of a set of opening parameters that, at least locally, minimize said objective function, and this set of opening parameters is used to set the parameters of the weaving machine (1).

Abstract: The present invention relates to a method for estimating a speed (v) of movement of a wheeled vehicle, wherein a frequency trajectory (?t) representative of the speed (v) of a wheel (RO) of the vehicle (VE) in a filtered spectrogram (S(ft, t)) is estimated (E5) as follows: a probability (pZt|?t) of observation of the trajectory (ft) is estimated (E51) on the basis of a computed amplitude of the filtered spectrogram (S(ft, t)), an a posteriori observation law (pZt|?t) proportional to the product of the probability (p?) and of the probability (p?|Z)? is estimated (E52), the trajectory (ft) is estimated (E53) on the basis of the law (p?|Z), and the speed (v) of movement of the wheel of the vehicle is estimated (E6) on the basis of the trajectory (?t).

Abstract: A method for manufacturing an acoustic attenuation structure including the following steps: making a complex acoustic multi-element panel including a plurality of hollow complex acoustic elements and a plurality of partitions forming acoustic cavities, each complex acoustic element being housed in an acoustic cavity so as to form an acoustic cell, making a first skin, piercing a plurality of perforations on the first skin at determined locations to form a multi-perforated acoustic skin, assembling the complex acoustic multi-element panel with the multi-perforated acoustic skin. The multi-perforated acoustic skin including on its assembly face a plurality of positioning studs configured to cooperate with a hollow complex acoustic element or an acoustic cavity during the assembly of the complex acoustic multi-element panel with the multi-perforated acoustic skin.

Abstract: A turbomachine stator extending about a central axis and including an inner wall and an outer wall delimiting an annular flow passage, a plurality of variable-pitch vanes, each vane extending radially in the annular flow passage between a base movably fixed to the outer wall, and a free end, the inner wall including a main profile and at least one circular platform arranged opposite the free end of one of the vanes, the platform including a main surface and at least one longitudinal groove, the platform being movable in rotation relative to the main profile between a first position in which a main axis of the groove is substantially parallel to the central axis, and at least a second position in which the main axis is transverse to the central axis.

Abstract: An electrical distribution route for an aircraft includes electrical cables and electrical connection interface members, and a diagnostic and detection device for diagnosing and detecting an arc fault in the electrical distribution route. The diagnostic and detection device includes an optical fiber laid along the entire distribution route and having at least one Bragg grating at each connection interface member, an optical reflectometer coupled to an upstream end of the optical fiber, and an acquisition central processing unit configured to detect and locate one or more arc faults over a connection interface member by comparing the current spectral signature with the reference spectral signature of the optical fiber.

Abstract: A method for detecting an anomaly in a plurality of predefined zones of a single aeronautical component includes supplying an image to be inspected to a detection system that includes a backbone neural network configured to supply an intermediate representation of the image to be inspected, and localisation neural networks that are respectively associated with the zones and each designed, on the basis of the intermediate representation, to search for one or more anomalies and to locate each anomaly found in the image to be inspected. The detection system has been previously trained, for each zone, by a step of supplying, to the backbone network, training images, and, on the basis of the training images of the relevant zone, an adaptive adjustment step during which parameters of the backbone network and of the localisation network that is associated with the relevant zone are adjusted.

Abstract: A method for manufacturing a diaphragm holder for a shock absorber of the oleo-pneumatic type, in particular for an aircraft landing gear. The diaphragm holder includes a first end with a dome, and a tubular portion extending from the dome to a second end. The method includes a step of overmolding a first material onto an insert. The insert can be a second material with a value of compression breaking stress divided by density that is higher than the first material or alternatively, of a material identical to the first material. A diaphragm carrier which can be manufactured by this method.

Abstract: The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.

Abstract: Electrical power supply circuit for a power module comprising an electrical transformer, a first substrate having a first side including a heat sink and a second side, a second substrate having a first side including a heat sink and a second side, first metal tracks disposed on the second side of the first substrate, second metal tracks disposed on the second side of the second substrate, electrical connectors disposed between the first and second substrates to electrically connect a first metal track to a second metal track, the primary circuit of the electrical transformer comprising a first part of the first metal tracks and a first part of the second metal tracks, and the secondary circuit of the electrical transformer comprising a second part of the first metal tracks and a second part of the second metal tracks.

Abstract: A method for controlling the speed of an engine assembly of an aircraft, including updating the speed setpoint of the engine assembly as a function of the current state-of-charge of an onboard energy storage device, and controlling the engine assembly according to the speed setpoint of the engine assembly, as well as a control device suitable for implementing this method and an engine assembly and an aircraft incorporating such a control device.

Abstract: A method for producing a component including a plurality of hollow complex elements, includes: filling a plurality of molding cavities with a thermoplastic material, the mold being maintained at a first temperature, applying a hold pressure to the thermoplastic material while the mold is cooled to a second temperature, and interrupting the hold pressure on the thermoplastic material while the mold is cooled to a third temperature.

Abstract: A method for forming an acoustic resonator panel for an aircraft propulsion assembly nacelle, the acoustic panel including cells with transverse internal obstacles in order to lengthen the path traveled by the sound waves. The method includes forming a perforated metal sheet, stacking a plurality of thermoplastic cellular cores and at least one perforated sheet, two successive cellular cores being separated by a perforated sheet, compacting the stack, and thermoplastic welding.

Abstract: A system for monitoring an aircraft engine, including an acquisition module for acquiring current measurements of physical quantities, referred to as input and output physical sizes, relative to the aircraft engine, a module for simulating the physical behavior of the aircraft engine, in order to simulate output physical quantities as a function of the current measurements of input physical sizes, a processor for calculating physical margins, referred to as actual physical margins, between the simulated values of output physical quantities and the corresponding current measurements of output physical quantities, a learning module for predicting margins, the margins being predicted using current measurements of input physical quantities and wherein the processor is configured to calculate surveillance residuals giving an indication of the state of the aircraft engine.

Abstract: This method (200) for producing a composite spacer ring for a turbine engine fan comprises preparing (210) an upstream skin preform, preparing (220) a downstream skin preform, preparing (230) an insert preform, inserting (251) the insert preform between the upstream skin preform and the downstream skin preform so as to form a rotating spacer ring preform, and baking (260) the rotating spacer ring preform. The preparation (210) of the upstream skin preform and/or the preparation (220) of the downstream skin preform comprises drape forming (212, 222) prepreg tows on a skin mold by means of automated fiber placement.