Abstract

The present invention concerns a reinforcement for a blade of a turbomachine, the blade comprising a first outer skin and a second outer skin which are made of composite material each comprising an inner end portion spaced apart from each other in such a way as to delimit therebetween an inner cavity of the blade that opens into an opening at an inner end of the blade, the inner end being radially opposite the outer end, wherein the reinforcement is adapted to be arranged in the inner cavity in such a way as to close the opening, and wherein the reinforcement comprises a mixture of cuts of at least one fiber and a tackifier, the cuts having lengths comprised between 1 mm and 15 mm, the tackifier comprising an epoxy resin solubilized in a solvent.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 5/14 - Form or construction
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

Abstract

The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner end portion (21, 31) spaced apart from each other in such a way as to delimit therebetween an inner cavity (4) of the blade (1) that opens into an opening (5), wherein the reinforcement (6) is adapted to be arranged in the inner cavity (4) in such a way as to close the opening (5), and wherein the reinforcement (6) comprises a stack of plies (61) that are superposed along a stacking direction (De) corresponding to a thickness direction (Pe) of the plies (61), at least two plies (61) having different lengths (Pl) and/or widths (PL) such that the reinforcement (6) has a profile of variable dimensions.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 9/02 - NozzlesNozzle boxesStator bladesGuide conduits
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

Method for the manufacture of at least one skin, in particular of an acoustic panel for an aeronautical engine, including the laying of a thermoplastic material on a surface of a lay-up tooling, via a depositing tool configured to exert a pressure on the thermoplastic material and to heat the latter while it is being laid, wherein the lay-up tooling includes a thermal regulation device configured to locally heat the surface of the lay-up tooling.

IPC Classes  ?

• B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
• B29C 35/04 - Heating or curing, e.g. crosslinking or vulcanising using liquids, gas or steam
• B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation
• B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29K 71/00 - Use of polyethers as moulding material
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29L 31/00 - Other particular articles

Abstract

A method for monitoring the state of health of an aircraft turbomachine for a flight of interest VI, based on a setpoint vector XSC of input parameters relative to the turbomachine of interest in steady-state regime, the method using a database of values of input and output parameters in transient regime for a plurality of flights including the flight of interest, and values of input and output parameters in steady-state regime for a plurality of flights with the exception of the flight of interest. The transient data are used to estimate a transient prediction model f, at least one portion of the transient prediction model f then being used, associated with the steady-state data, in order to estimate a steady-state prediction model H of the turbomachine of interest for the flight of interest and to determine the behaviour, in steady-state regime, of the turbomachine for the flight of interest.

IPC Classes  ?

• B64F 5/60 - Testing or inspecting aircraft components or systems
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for

Abstract

A nickel-based superalloy, includes, in percent by weight of the total composition Al 2.5-3.8, Co 7.9-16.9, Cr 9.7-13.1, Mo 2.6-4.1, Nb 0-0.41, Ta 0-1.9, Ti 4.4-6.4, W 1.9-4.2, B 0.010-0.030, C 0.010-0.040, Hf 0.20-0.40, Zr 0.040-0.070, the remainder being Ni together with inevitable impurities.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Abstract

An electrical system for an aircraft includes first and second buses, first and second electric generators, and first and second AC-to-DC converters. The first bus is connected to an AC network. The second bus is connected to a DC network of the aircraft. The first electric generator is connected to the first bus and a first rotary spool of an engine of the aircraft to exchange mechanical and/or electrical power. The first AC-to-DC converter is connected to the first and second buses. The second electric generator is connected to a second rotary spool of the engine of the aircraft. The second AC-to-DC converter connected to the second electric generator and to the second bus. One or more of the converters operates in a forced mode providing regulation of the electrical power of one or more buses, and/or a free mode providing regulation of a voltage of the second bus.

IPC Classes  ?

• H02P 9/30 - Arrangements for controlling electric generators for the purpose of obtaining a desired output by variation of field using discharge tubes or semiconductor devices using semiconductor devices
• B64D 47/00 - Equipment not otherwise provided for
• H02P 101/25 - Special adaptation of control arrangements for generators for combustion engines
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft
• H02P 103/20 - Controlling arrangements characterised by the type of generator of the synchronous type

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.

IPC Classes  ?

• G01R 31/08 - Locating faults in cables, transmission lines, or networks
• G01D 5/353 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using optical means, i.e. using infrared, visible or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
• G01R 31/00 - Arrangements for testing electric propertiesArrangements for locating electric faultsArrangements for electrical testing characterised by what is being tested not provided for elsewhere
• G01R 31/52 - Testing for short-circuits, leakage current or ground faults

Abstract

An aircraft landing gear assembly comprising a first structural member coupled to a second structural member via a joint, the joint comprising a bearing, the bearing comprising a tubular body formed from: a metal matrix composite (MMC) comprising a metal, a carbide compound and tungsten disulphide.

IPC Classes  ?

• B64C 25/02 - Undercarriages
• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B64C 25/00 - Alighting gear
• F16C 11/04 - Pivotal connections
• F16C 17/02 - Sliding-contact bearings for exclusively rotary movement for radial load only
• F16C 17/10 - Sliding-contact bearings for exclusively rotary movement for both radial and axial load
• C22C 32/00 - Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ

Abstract

A method for manufacturing a part made of composite material includes three-dimensionally weaving a structure having a longitudinal axis (A). The method further includes the step of braiding of at least one layer of braiding threads at at least one predetermined angle relative to the longitudinal axis around the woven structure.

IPC Classes  ?

• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29K 307/04 - Carbon
• B29K 309/08 - Glass
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

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.

IPC Classes  ?

• H05K 1/11 - Printed elements for providing electric connections to or between printed circuits
• B64D 47/00 - Equipment not otherwise provided for

Abstract

The invention relates to a nickel-based alloy powder, that comprises in weight percentages, 14.00 to 15.25% of chromium, 14.25 to 15.75% of cobalt, 4.00 to 4.60% of aluminium, 0 to 0.50% of iron, 0 to 0.15% of manganese, 3.00 to 3.70% of titanium, 3.90 to 4.50% of molybdenum, 0 to 0.015% of sulphur, 0 to 0.06% of zirconium, 0.012 to 0.020% of boron, 0 to 0.20% of silicon, 0 to 0.10% of copper, 0 to 150 ppm of carbon, 0 to 0.5 ppm of bismuth, 0 to 5 ppm of lead, 0 to 1000 ppm of platinum, 0 to 1000 ppm of palladium, 0 to 50 ppm of hydrogen, 0 to 5 ppm of silver, 0 to 120 ppm of nitrogen, 0 to 1000 ppm of rhenium, 0 to 410 ppm of oxygen and 0 to 500 ppm of inevitable impurities, the rest being made up of nickel, and has a particle size D10 between 3 and 10 μm, a particle size D90 between 20 and 40 μm and a particle size D50 between 10 and 20 μm, the values of the particle sizes D10, D50 and D90 having been measured by laser diffraction according to standard ISO 13322-2. The invention also relates to a method for manufacturing a part using said powder and a resulting part.

IPC Classes  ?

• B22F 1/10 - Metallic powder containing lubricating or binding agentsMetallic powder containing organic material
• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor for producing castings from a slip
• B22F 3/24 - After-treatment of workpieces or articles

Abstract

Method for monitoring the navigation of a vehicle for the implementation of a navigation maneuver: the method including the steps of: estimating a magnitude by a Kalman filter from parameters, a digital model of the vehicle in its environment, and at least one measurement made by at least one sensor and associated with an uncertainty on this measurement, the magnitude serving to implement the navigation maneuver; determining at least one partial derivative value of the magnitude with respect to the at least one measurement; obtaining at least one criticality value of the at least one measurement for the estimation, from the at least one partial derivative.

IPC Classes  ?

• G01C 21/16 - NavigationNavigational instruments not provided for in groups by using measurement of speed or acceleration executed aboard the object being navigatedDead reckoning by integrating acceleration or speed, i.e. inertial navigation
• G06F 7/544 - Methods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using non-contact-making devices, e.g. tube, solid state deviceMethods or arrangements for performing computations using exclusively denominational number representation, e.g. using binary, ternary, decimal representation using unspecified devices for evaluating functions by calculation

Abstract

A method for monitoring the engine speed of a rotating machine, includes constructing a raw spectrogram from a vibratory signal; denoising the spectrogram to obtain an equalised spectrogram, the denoising including a first sub-procedure of determining a foot of the spectrogram, the foot of the spectrum being a set of random harmonic components contained in the raw spectrogram, the first sub-procedure including a first sub-sub-procedure of constructing a regression function robust to the peaks of the spectrogram, the regression function being applied to a logarithm of the spectrogram or to the spectrogram; a second sub-sub-procedure of determining the foot of the spectrum from the regression function; a second sub-procedure of determining the equalised spectrogram from the foot of the spectrogram; separating sources in the equalised spectrogram by determining an estimator of the frequencies of interest; determining an instantaneous speed of rotation of the engine speed from the estimator.

IPC Classes  ?

• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• G01H 1/00 - Measuring vibrations in solids by using direct conduction to the detector

Goods & Services

(1) Appareils, équipements et instruments électriques, électroniques et numériques pour la navigation, le guidage, le pilotage, la stabilisation, la localisation de véhicules aériens, terrestres, maritimes et spatiaux; gyromètres; équipements et appareils gyroscopiques et accélérométriques; systèmes de navigation inertielle et hybride; casques de pilotage et équipements de visualisation pour applications civiles et militaires; équipements et bases de données pour la préparation, le suivi et la restitution des missions de véhicules terrestres, aériens et maritimes; appareils de cartographie numérique; calculateurs de mission; appareils, instruments et dispositifs électriques et électroniques pour l'aéronautique; systèmes d'aide à la maintenance (ACMS); systèmes de commandes du cockpit; actionneurs de commandes de frein et d'inverseur de poussée; systèmes de contrôle de vol automatique d'aéronefs; calculateurs de commandes de vol; centrales inertielles d'attitude et de cap; appareils, instruments et équipements d'analyse de données techniques et scientifiques (station d'analyses au sol); appareils, équipements et instruments optiques pour applications scientifiques, la navigation, le guidage, le pilotage, la stabilisation de véhicules aériens, terrestres, maritimes et spatiaux; caméras infrarouges; caméras vidéo; équipements et appareils de détection optique ou infrarouge; équipements et appareils de conduite de tir; imageurs thermiques; systèmes d'observation; systèmes de veille et de poursuite infrarouge; lunettes de visées, télescope, longue vues; viseurs optiques; appareils, équipements et instruments de navigation, d'observation et de contrôle pour véhicules sans pilote à usage civil et militaire; systèmes d'observation et de reconnaissance; systèmes de transmissions et de communication sécurisées; terminaux de télécommunication et de chiffrement; réseaux sécurisés; appareils, équipements et instruments électroniques pour fantassins et personnels de sécurité; systèmes de surveillance jour/nuit; jumelles pour vision jour/nuit; batteries, accumulateurs électriques; systèmes de surveillance aéroporté; plateforme optronique gyrostabilisée et orientable; appareils et équipements pour l'acquisition, la compression, la transmission, l'analyse et la restitution d'images satellites et de photographies aériennes; systèmes de transmission d'images par liaison radio numérique; optique spatiale; optique de reconnaissance aérienne; métrologie optique; parachutes et systèmes de parachutes. (2) Avions sans pilote, drones, véhicules aériens; planches de bord; manches de pilotage avec manette intégrée. (1) Services d'installation, de réparation et de maintenance d'équipements électroniques de véhicules terrestres, maritimes et aériens; maintenance et réparation d'équipements aéronautiques; installation, entretien et réparation d'appareils et instruments d'astronomie terrestre, d'appareils et instruments optoélectroniques pour l'industrie des lasers, des semi-conducteurs et de la défense et notamment de télescopes, miroirs, objectifs. (2) Conception (élaboration) de logiciels et de matériel informatique; développement et conception (élaboration) de logiciels pour systèmes de navigation (GPS et ou par satellite); développement et conception de logiciels pour systèmes d'information en matière de défense; conversion de données et de programmes informatiques; conception, organisation, mise à disposition, maintenance de logiciels et de composants logiciels et fourniture en ligne de logiciels; recherche technique, scientifique et industrielle; ingénierie; recherche et développement (travaux d'ingénieurs) dans le domaine aéronautique, nautique et de la défense; analyse de données techniques; conseils techniques dans le domaine aéronautique et de la défense (travaux d'ingénieurs); service d'ingénierie opérationnelle pour compagnies aériennes; rassemblement, systématisation et stockage de données.

Abstract

A method for transferring an adhesive onto a part intended to be glued on a carrier, the adhesive being in the form of a double-sided film including a separator on each face, the part including an internal concave portion that does not enable uniform application of the adhesive film once the separators have been removed. The method includes attaching the adhesive film to a punch that matches the shape of the part within a range that approximately corresponds to the thickness of the adhesive film; removing the separator from the side of the adhesive film that is to be attached to the part; setting the part on the punch covered with the adhesive film that has had its separator removed; and transferring the adhesive film onto the part by creating a vacuum between the part and the punch by means of a vacuum device.

IPC Classes  ?

• B29C 63/16 - Lining or sheathing, i.e. applying preformed layers or sheathings of plasticsApparatus therefor using sheet or web-like material applied by "rubber" bag or diaphragm
• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 65/50 - Joining of preformed partsApparatus therefor using adhesives using adhesive tape
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A heating turbomachine for a fuel-conditioning system, which is configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank. The heating turbomachine comprising: compressor; a turbine; a combustion chamber which is configured to discharge a flow of exhaust air loaded with heat energy and to rotate the turbine; at least one fluid circuit in which a heat-transfer fluid circulates in the downstream direction; and at least one post-combustion heat exchanger which is mounted in the fluid circuit and is configured to extract heat energy from the exhaust air chamber flow between the combustion and the turbine.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner
• F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure

Abstract

In a method for three-dimensional weaving of a fibrous structure between layers of warp yarns and layers of weft yarns, the weft yarns are woven in a plurality of columns spaced apart from one another in a longitudinal direction. The method includes weaving deployment portions in the fibrous structure that is interwoven with an adjacent portion, the weft yarns of the weft yarn columns of the adjacent portion being juxtaposed in a first stacking direction perpendicular to the longitudinal direction. During the process of weaving the deployment portions, the weft yarns of each weft yarn column are positioned against the fell of the fibrous structure in stacking directions that are different from the first stacking direction.

IPC Classes  ?

• D03D 25/00 - Woven fabrics not otherwise provided for
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• D03D 1/00 - Woven fabrics designed to make specified articles
• D03D 13/00 - Woven fabrics characterised by the special disposition of the warp or weft threads, e.g. with curved weft threads, with discontinuous warp threads, with diagonal warp or weft
• D03D 49/60 - Construction or operation of slay

Abstract

A titanium alloy includes, in content by weight 4.0% to 5.0% aluminium; 3.50% to 4.50% tin; 1.0% to 4.0% zirconium; 2.0% to 5.25% molybdenum; 1.0% to 2.50% niobium; 0.10% to 0.25% silicon; 0.10% to 0.18% oxygen; the remainder being titanium and unavoidable impurities, the alloy further being such that the Aleq criterion, referred to as equivalent aluminium content by weight, is less than or equal to 8.5%, the Aleq criterion being defined as Aleq=[Al]+[Sn]/3+[Zr]/6+10*[O] where, [Sn], [Zr] and [O] are the contents by weight of aluminium, tin, zirconium and oxygen respectively.

IPC Classes  ?

• C22C 14/00 - Alloys based on titanium
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups

Abstract

A gantry crane and associated method of erection, the gantry including a frame having at least three first members; a longitudinal rail supported by the frame; and at least three second members extending between a first end portion and an opposite second end portion. Each second member can be connected to the frame by means for rigid connection and continuous rotational movement of the second member relative to the frame between a first position in which the second member forms an angle of less than 90° with the first plane and a second position in which the second member is substantially perpendicular to the first plane.

IPC Classes  ?

• B66C 17/00 - Overhead travelling cranes comprising one or more substantially-horizontal girders the ends of which are directly supported by wheels or rollers running on tracks carried by spaced supports
• B66C 23/78 - Supports, e.g. outriggers, for mobile cranes

Abstract

The invention relates to a titanium-based alloy powder which comprises, in percentages by weight, 32.0 to 33.5% aluminium, 4.50 to 5.10% niobium, 2.40 to 2.70% chromium, 0 to 0.1% iron, 0 to 0.025% silicon, 0 to 100 ppm carbon, 0 to 100 ppm nitrogen, 0 to 1000 ppm dioxygen, 0 to 50 ppm dihydrogen and 0 to 500 ppm unavoidable impurities, the balance being titanium, and which has a D10 particle size of between 3 and 10 μm, a D90 particle size of between 20 and 40 μm and a D50 particle size of between 10 and 25 μm, the D10, D50 and D90 particle size values having been measured by laser diffraction in accordance with standard ISO 13322-2. The invention also relates to a method for manufacturing a part using this powder and to a part thus obtained.

IPC Classes  ?

• B22F 3/22 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor for producing castings from a slip
• B22F 1/107 - Metallic powder containing lubricating or binding agentsMetallic powder containing organic material containing organic material comprising solvents, e.g. for slip casting
• B22F 3/15 - Hot isostatic pressing
• B22F 3/24 - After-treatment of workpieces or articles

Abstract

The invention relates to a system for measuring the fatigue of a mechanical structure, comprising: a first force sensor capable of generating a first signal representative of a force applied to a first mechanical part of the mechanical structure; a second force sensor capable of generating a second signal representative of a force applied to a second mechanical part of the mechanical structure; and an electronic processing module configured to calculate a correlation coefficient between the first signal and the second signal, and to indicate a state of fatigue of the mechanical structure as a function of a temporal change in the previously calculated correlation coefficient.

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• B64D 11/06 - Arrangements or adaptations of seats
• G01M 99/00 - Subject matter not provided for in other groups of this subclass

Abstract

A method for producing a magnet for a rotor of an electric machine has a first phase of producing a magnet blank which includes a step of pressing powders into a magnet mold in the presence of a magnetic field while subjecting the powders to a magnetic field generated by a first magnetization tool. The method further includes a step of densifying the obtained magnet blank and a second phase. The second phase includes finishing the magnet blank by at least one final magnetization step in order to obtain a magnet. The mold is arranged in a densifying chamber, and the densifying step is carried out by flash SPS sintering in the densifying chamber.

IPC Classes  ?

• H02K 15/038 - Polarising or magnetising the permanent magnets
• B22F 3/105 - Sintering only by using electric current, laser radiation or plasma

Abstract

A method for detecting defects for an aeronautical part, includes training, during a plurality of epochs, an artificial neural network to supply a defect probability for each pixel of an image, for each epoch and for each image of a validation set, creating a defect probability matrix based on defect probabilities for each pixel of the image, for each epoch, determining, for each image of the validation set, based on the defect probability matrices, a curve of defect detection as a function of false alarms, determining a set of the N best epochs on the basis of the defect detection curves and of a business criterion, for each epoch of the N best epochs, inspecting the image to be inspected by applying the artificial neural network with parameters associated with the epoch, so as to obtain an inspected sub-image associated with the training epoch.

IPC Classes  ?

• G06T 7/00 - Image analysis
• G06V 10/75 - Organisation of the matching processes, e.g. simultaneous or sequential comparisons of image or video featuresCoarse-fine approaches, e.g. multi-scale approachesImage or video pattern matchingProximity measures in feature spaces using context analysisSelection of dictionaries
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks

Abstract

A method for making an acoustic component includes a plurality of hollow complex acoustic elements, the method including heating a film of thermoplastic material to a first temperature above the glass transition temperature of the film; shaping the heated film of thermoplastic material in a tool including a mould which has a plurality of mould cavities having a shape corresponding to the shape of the complex acoustic elements of the acoustic component to be made, the heated film of thermoplastic material being shaped locally in each of the mould cavities, at least the mould being kept at a second temperature above the glass transition temperature of the thermoplastic material; cooling the mould; and removing a complex acoustic multi-element panel including a plurality of hollow complex acoustic elements from the mould.

IPC Classes  ?

• B29C 51/00 - Shaping by thermoforming, e.g. shaping sheets in matched moulds or by deep-drawingApparatus therefor
• B29C 51/26 - Component parts, details or accessoriesAuxiliary operations
• B29C 51/42 - Heating or cooling
• B29L 22/00 - Hollow articles

Abstract

An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.

IPC Classes  ?

• B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways

Abstract

A propeller blade or airfoil of a turboprop of composite material includes a fibrous reinforcement densified by a matrix, the propeller blade or airfoil including, in a span direction, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic preform portion present in the aerodynamic profile, the root and aerodynamic preform portions being linked to one another by the three-dimensional weave. The root preform portion of the fibrous preform includes an unlinked area delimiting an internal root recess forming a cavity opening at a free end of the root.

IPC Classes  ?

• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including along a longitudinal direction a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile parts being connected to one another by three-dimensional weaving. The root preform part includes two woven skins wound around an insertion element.

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements

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.

IPC Classes  ?

• H01M 8/0228 - Composites in the form of layered or coated products
• H01M 8/0243 - Composites in the form of mixtures
• H01M 8/12 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte
• H01M 8/1246 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides

Abstract

An aircraft landing gear shock absorber strut (50) comprising: an outer cylinder (26) having an inner surface defining a cylinder bore extending into the outer cylinder from a first axial face of the outer cylinder, the cylinder bore defining an oleo-pneumatic chamber containing a damping liquid and a gas which can mix within the cylinder bore; a sliding tube (28) including a first end portion movably mounted within the cylinder bore so as to be movable along the cylinder bore between a compressed position, in which a second end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder, and an extended position, in which the second end portion of the sliding tube is relatively far from the first axial face of the outer cylinder, the sliding tube including a tube bore extending into the sliding tube from the first end portion, the tube bore being arranged in fluid communication with the cylinder bore to exchange the damping liquid with the cylinder bore; an elongate metering pin (34) having a longitudinal axis and including an axial channel for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position; and a flow restricting plate (52) including: a first portion (52a) provided with a first damping orifice (DO) in which the metering pin is located and through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions to vary the free space cross sectional area of the first damping orifice to control an axial flow of the damping liquid (J) moving from the tube bore to the cylinder bore as the sliding tube moves from the extended position towards the compressed position; and a second portion (52b) provided with a second damping orifice (DO2) for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position to define a second flow of the damping liquid (J2), wherein the second damping orifice is orientated to direct the second flow of damping liquid towards the axial channel of the metering pin to disrupt the axial flow of damping liquid.

IPC Classes  ?

• F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
• F16F 9/342 - Throttling passages operating with metering pins
• F16F 9/48 - Arrangements for providing different damping effects at different parts of the stroke

Abstract

A component for an acid electrolyte fuel cell or electrolyser provided with an anticorrosion coating, as well as such an acid 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.

IPC Classes  ?

• H01M 8/0228 - Composites in the form of layered or coated products
• C25B 9/60 - Constructional parts of cells
• H01M 8/0243 - Composites in the form of mixtures
• H01M 8/086 - Phosphoric acid fuel cells [PAFC]
• H01M 8/10 - Fuel cells with solid electrolytes
• H01M 8/1018 - Polymeric electrolyte materials

Abstract

An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.

IPC Classes  ?

• B64C 25/08 - Undercarriages non-fixed, e.g. jettisonable

Abstract

A drive circuit for a plurality of piezo-actuated hydraulic pumps for an aircraft, and a hydraulic pump system implementing the same. The drive circuit includes a voltage boost stage that receives a DC input supply voltage and delivers an increased DC output voltage to a high voltage, HV, link point; a plurality of inverter stages coupled in parallel at the HV link point that receive DC voltage from the HV link point and generate an oscillating output voltage for driving a respective piezo-actuated pump; and a control system that controls the output voltage and phase of the inverter stages to drive the plurality of piezo-actuated pumps out of phase. The control system measures the power consumption of each piezo-actuated pump and regulates the output voltage of at least one of the inverter stages to balance the power consumption of each piezo-actuated pump.

IPC Classes  ?

• F04B 49/06 - Control using electricity
• F04B 43/04 - Pumps having electric drive

Abstract

A method for manufacturing a panel including a plurality of partitions defining cells covered by at least one skin, the skin being formed by draping fibrous structures impregnated with a thermoplastic material on the upper edges of the partitions by automatic placement of fibers, the upper edges of the partitions and the fibrous structures being joined together with the aid of a localized heating device at the moment they are placed in contact, the method wherein the fibrous structures are draped with a draping tension on the interface between each edge of a partition and the deposited fibrous structure applying a shear stress of between 50% and 80% of the maximum shear stress before rupture of the interface.

IPC Classes  ?

• B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
• B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
• B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
• B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
• B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
• B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
• B32B 41/00 - Arrangements for controlling or monitoring lamination processesSafety arrangements

Abstract

A nickel-based superalloy including in weight percentages: 5.0 to 6.5% aluminium, 0.50 to 2.5% tantalum, 1.50 to 4.0% titanium, 0 to 7.0% cobalt, 12.0 to 16.0% chromium, 0.50 to 2.5% molybdenum, 0 to 2.0% tungsten, 0.05 to 0.15% hafnium, 0 to 0.15% silicon, the remainder consisting of nickel and unavoidable impurities. A single-crystal blade including such an alloy and to a turbomachine including such a blade.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

This control device for a propulsion system, comprising means for calculating a blade-pitch setpoint of at least one propeller of the propulsion system, the calculation means using a performance predictive model of the propeller taking account of at least one flight speed for adapting a blade-pitch angle setpoint, is characterised in that the performance predictive model of the propeller is configured to use polar charts implemented in the form of a mathematical law.

IPC Classes  ?

• B64C 11/30 - Blade pitch-changing mechanisms
• B64C 11/44 - Blade pitch-changing mechanisms electric

Abstract

A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

An assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction. Retaining members hold the cores in position in the injection mold.

IPC Classes  ?

• B22D 17/24 - Accessories for locating and holding cores or inserts
• B22D 25/02 - Special casting characterised by the nature of the product by its peculiarity of shapeSpecial casting characterised by the nature of the product of works of art

Abstract

An aircraft landing gear assembly (36) comprising a wheel and brake assembly and a shock absorbing strut (37), the strut including a mounting bearing for movably coupling the aircraft landing gear assembly to an aircraft for movement between a stowed condition for flight and a deployed condition for take-off and landing, the aircraft landing gear assembly further comprising: a noise-inducing region (37); a first perforated sheet fairing (1n); and a second perforated sheet fairing (3n) arranged downstream of the first perforated sheet fairing when the landing gear is in the deployed condition.

IPC Classes  ?

• B64C 25/00 - Alighting gear

Abstract

A method for producing a part, in particular a part made of composite material, in particular for a turbomachine, including at least: a step of producing a preform, during which a fibrous preform intended to form an outer skin of the part is produced; a step of producing a core, during which a rigid core, in particular a hollow rigid core, intended to form a framework of the part is produced; an insertion step, during which the rigid core is inserted into the fibrous preform, an injection step, during which a matrix is injected into the fibrous preform; and a heat-treatment step, during which polymerisation of the matrix is carried out.

IPC Classes  ?

• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29K 71/00 - Use of polyethers as moulding material
• B29K 77/00 - Use of polyamides, e.g. polyesteramides, as moulding material
• B29K 79/00 - Use of other polymers having nitrogen, with or without oxygen or carbon only, in the main chain, as moulding material

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.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• F02C 7/06 - Arrangement of bearingsLubricating

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.

IPC Classes  ?

• H02P 9/10 - Control effected upon generator excitation circuit to reduce harmful effects of overloads or transients, e.g. sudden application of load, sudden removal of load, sudden change of load
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• H02P 101/25 - Special adaptation of control arrangements for generators for combustion engines
• H02P 101/30 - Special adaptation of control arrangements for generators for aircraft

Abstract

A method for producing a bladed component for an aircraft turbine engine, this bladed component comprising including a blade which has a stacking axis and at least one longitudinal end of which is connected to a transverse platform, the method including the steps of: a) producing a fibrous preform, this preform including a first part that is intended to form a blade and at least one second part that is intended to form a platform, this second part of the preform including a disconnect that defines two stacked portions that are separated by a disconnect surface that is substantially parallel to the axis, b) folding the portions, respectively, on two opposing sides of the first part, and c) stiffening the preform.

IPC Classes  ?

• B29B 11/14 - Making preforms characterised by structure or composition
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• D03D 25/00 - Woven fabrics not otherwise provided for

Goods & Services

(1) Appareils pour l'enregistrement, la transmission, la reproduction ou le traitement de sons, images ou données; équipement pour le traitement de l'information et les ordinateurs; logiciels, périphériques d'ordinateurs; appareils et instruments scientifiques et de recherche basés sur l'analyse automatique d'informations géospatiales; équipements de traitement de données; équipements de traitement de données basés sur l'analyse automatique d'informations géospatiales; logiciels d'intelligence artificielle; logiciels d'intelligence artificielle pour le traitement automatique d'images satellites; dispositifs et supports de stockage des données et images; bases de données; logiciels de gestion de bases de données. (1) Services annexes liés à la gestion ou au traitement des données, y compris la gestion de bases de données et plus spécifiquement services d'analyse de données pour assister les clients dans leurs processus de prise de décision; fourniture d'informations d'affaires dans le domaine stratégique et militaire; analyses commerciales stratégiques dans les domaines de la défense et de la sécurité. (2) Fourniture d'accès à des bases de données, transmission de données, distribution électronique d'images satellite via un réseau informatique. (3) Recherche et développement de nouveaux produits (pour des tiers); étude de projets techniques; élaboration (conception), installation, maintenance, mise à jour ou location de logiciels; programmation pour ordinateurs; consultation en matière de logiciels informatiques; conversion de données ou de programmes informatiques (autres conversions physiques); conseil technologique dans le domaine de l'intelligence artificielle; plates-formes pour intelligence artificielle en tant que logiciel-service [SaaS]; recherche dans le domaine de la technologie de l'intelligence artificielle; fourniture de programmes informatiques d'intelligence artificielle; développement et test de méthodes, d'algorithmes et de logiciels informatiques.

Goods & Services

Services related to data management or processing, including database management and more specifically data analysis services to assist customers in their decision-making processes; providing business information in the strategic and military field; strategic business analysis in the fields of defense and security. Providing access to databases, data transmission, electronic distribution of satellite images via a computer network. Apparatus for sound, image or data recording, transmission, reproduction or processing; equipment for data processing and computers; software, computer peripheral devices; scientific and research apparatus and instruments based on automatic analysis of geospatial information; data processing equipment; data processing equipment based on the automatic analysis of geospatial information; artificial intelligence software; artificial intelligence software for automatic processing of satellite images; data and image storage media and devices; databases; database management software. Research and development of new products (for others); technical project study; development (design), installation, maintenance, updating or rental of software; programming for computers; consultancy relating to computer software; conversion of computer programs or data (other than physical conversion); technological advice in the field of artificial intelligence; platforms for artificial intelligence as SaaS [Software as a Service]; research in the field of artificial intelligence technology; providing computer programs for artificial Intelligence; development and testing of computing methods, algorithms and software.

Abstract

The invention relates to a nickel-based alloy comprising, in weight percent: 4.0 to 20.0% cobalt, 14.0 to 18.5% chromium, 1.8 to 2.6% aluminum, 1.3 to 1.9% titanium, 5.5 to 6.5% tantalum, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Abstract

A nickel-based alloy includes, in weight percent: 4.0 to 15.7% cobalt, 15.3 to 19.5% chromium, 1.6 to 5.45% molybdenum, 1.65 to 2.5% aluminum, 2.8 to 4.3% titanium, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings

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.

IPC Classes  ?

• B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
• B29C 64/336 - Feeding of two or more materials
• B29C 64/371 - Conditioning of environment using an environment other than air, e.g. inert gas
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
• B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
• B33Y 70/10 - Composites of different types of material, e.g. mixtures of ceramics and polymers or mixtures of metals and biomaterials

Abstract

A heat exchanger for a turbomachine, in particular an aircraft turbomachine, having a longitudinal axis, including a supporting wall extending in a first direction; a plurality of fins, each of which rises in a second direction from the supporting wall and being intended to be swept by an air stream, and a profiled panel covering the fins and extending in the first direction between a first diverging-profile wall upstream of the fins and a second converging-profile wall downstream of the fins. The heat exchanger includes an air intake device configured to slow the air stream in a third direction, the device having multiple separate air intake openings which are arranged upstream of the fins in the first direction and which are distributed in the third direction.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

A vane for an aircraft turbomachine includes a blade and a cooling circuit inside the blade. The cooling circuit has at least one longitudinal flow cavity of a cooling air stream (RF). The cooling circuit further includes elements that protrude into the cavity and are configured to disrupt the air stream. Each of the protruding elements is generally arc-shaped and internally defines, with a first wall, a first cross-sectional flow area, and externally, with a second wall opposite the first wall, a second cross-sectional flow area. Each of the elements is configured such that the first or second cross-sectional flow area is reduced from upstream to downstream relative to the direction of the air stream.

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades

Abstract

An apparatus for providing energy in an aircraft, including a DC bus; at least one low-pressure electrical source and at least one high-pressure electrical source. The apparatus further includes a system for calculating a droop gain for each electrical source, based on at least one operating characteristic of the turbine engine; and for each electrical source, a model for controlling the electrical source in question, which module is designed to implement a droop setting based on the droop gain calculated for the electrical source in question.

IPC Classes  ?

• B64D 31/00 - Power plant control systemsArrangement of power plant control systems in aircraft
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for

Abstract

A heat exchanger of the air/oil type, for an annular air stream of a turbomachine, comprising a heat exchange zone with oil passages and heat exchange surfaces with the air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and included in a plane perpendicular to said air flow, said profile of the exchange zone thermal being in an arc of a circle so as to be able to be arranged in the annular air stream, remarkable in that said heat exchanger comprises on a radially internal or external face of the exchange zone thermal, an oil inlet and an oil outlet, the oil passages comprising several paths between said oil inlet and said oil outlet, distributed along the profile in circular arc of the heat exchange zone.

IPC Classes  ?

• F01D 25/12 - Cooling

Abstract

Method for manufacturing a blade made of a composite material for a turbomachine, in particular of an aircraft, including steps of: a) arranging a preform produced by three-dimensional weaving of fibres within a mould, a polymerisable adhesive being inserted between a shield and an edge of the preform, b) closing and heating the mould, then injecting the polymerisable resin into the mould, wherein the mould is heated according to a cycle including increases in temperature from T1 to T2, then from T2 to T3, and in that the resin is injected in step b) during or just before the increase in temperature from T2 to T3, the temperature T2 being selected so that the viscosity of the adhesive is greater than the viscosity of the resin.

IPC Classes  ?

• B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
• B29K 63/00 - Use of epoxy resins as moulding material
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29K 307/04 - Carbon
• B29K 705/00 - Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A process carrying out non-planar three-dimensional forming of at least one segment of a flexible printed circuit board including an electrically insulating polymer film, and, on at least one side of the polymer film, a metallization then carrying out electrodeposition in which a conductive layer is deposited on at least the metallization of at least the formed segment.

IPC Classes  ?

• H05K 1/18 - Printed circuits structurally associated with non-printed electric components
• H02K 11/33 - Drive circuits, e.g. power electronics
• H05K 1/02 - Printed circuits Details
• H05K 3/18 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using precipitation techniques to apply the conductive material

Abstract

The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, where the magnetic ring includes a predetermined number of pairs of poles, and the magnetic ring is formed by at least one oriented-flux magnet. The method includes determining a characteristic dimension of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, determining a reference value equal to the minimum value out of a predetermined reference length and twice the value Pi, comparing the characteristic dimension of the magnet with the reference value, and if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.

IPC Classes  ?

• H02K 1/2783 - Surface mounted magnetsInset magnets with magnets arranged in Halbach arrays
• B64D 27/32 - Aircraft characterised by electric power plants within, or attached to, fuselages

Abstract

An axial turbomachine, comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called a secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the tertiary flow being in a tertiary flow vein radially external to said primary flow, delimited by an internal wall and an external wall; and an air/oil type heat exchanger, disposed in the tertiary flow vein. The heat exchanger comprises several angular sectors, each angular sector comprising an oil inlet on the internal wall at an angular end of said sector, and an oil outlet on said internal wall at an opposite angular end of said sector.

IPC Classes  ?

• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
• F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
• F28F 7/02 - Blocks traversed by passages for heat-exchange media
• F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels

Abstract

An axial turbomachine comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a flow of radially external air, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow flow in a tertiary flow vein radially external to said primary flow; and a heat exchanger disposed in the tertiary flow vein. The heat exchanger extends radially and axially in an upstream section section of the tertiary flow vein, having a divergent longitudinal section, said tertiary flow vein comprises a downstream section presenting a converging longitudinal section, following the tertiary flow.

IPC Classes  ?

• F02C 7/14 - Cooling of plants of fluids in the plant
• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02K 3/077 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows

Abstract

Method for manufacturing composite blade cleats for an aircraft turbine engine, including providing a woven panel, including a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least a portion of the margin in common; injecting a matrix onto the panel; after injection, dividing the panel in order to separate the cleats from one another; machining the cleats to remove the margins.

IPC Classes  ?

• B29D 99/00 - Subject matter not provided for in other groups of this subclass

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.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators

Abstract

An axial turbomachine including a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary f flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said flow primary; and an air/oil type heat exchanger disposed in the tertiary flow stream and including heat exchange surfaces with air and oil passages extending in said tertiary flow stream; and structural arms extending radially through the tertiary flow vein. Each structural arm has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.

IPC Classes  ?

• F01D 25/12 - Cooling

Abstract

A device for depositing a thick metal nitride on a sample by supercritical fluids includes a first enclosure forming a first closed volume; a second enclosure placed in the first enclosure and delimited by internal walls transparent to electromagnetic radiation forming a second closed volume intended to comprise a fluid under supercritical conditions; a heat transfer dielectric fluid circulating in the first volume around the second enclosure; a sample holder present in the second volume; an induction heating device surrounding the second enclosure; inlets for introducing a fluid and at least one precursor material into the second enclosure; and an outlet to purge the second volume.

IPC Classes  ?

• C23C 18/12 - Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coatingContact plating by thermal decomposition characterised by the deposition of inorganic material other than metallic material

Abstract

A fuel conditioning system configured to supply an aircraft turbomachine with fuel from a cryogenic tank. The conditioning system comprising a primary heat exchanger designed to heat the fuel flow to at least one primary temperature, and at least one secondary heat exchanger, mounted downstream of the primary heat exchanger, designed to heat the fuel flow to at least one secondary temperature higher than the primary-temperature, the primary heat exchanger being configured to extract calories in the fuel flow that is at least at the secondary temperature.

IPC Classes  ?

• B64D 37/34 - Conditioning fuel, e.g. heating
• B64D 37/30 - Fuel systems for specific fuels
• F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
• F02C 7/224 - Heating fuel before feeding to the burner

Abstract

A fuel conditioning system configured to supply a turbomachine with fuel from a cryogenic tank, the conditioning system comprising a fuel circuit connected at the inlet to the cryogenic tank and at the outlet to the turbomachine, a pump, a fuel cell configured to provide electricity to an electrical network of the aircraft, at least a first heat exchanger belonging to the fuel circuit and configured to transmit calories from the fuel cell to the fuel flow in order to heat it, and at least one second heat mounted downstream of the first heat exchanger in the fuel circuit and configured to transmit calories from the turbomachine to the fuel flow in order to heat it.

IPC Classes  ?

• B64D 37/34 - Conditioning fuel, e.g. heating
• B64D 37/30 - Fuel systems for specific fuels
• F02C 6/10 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
• F02C 7/224 - Heating fuel before feeding to the burner

Abstract

Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A method and system for mounting an axle in a bore of a bogie mounted on a landing gear of an aircraft, the landing gear being in a gear-down position, the bore extending in a substantially horizontal direction referred to as the axle installation direction, between a first open end and a second open end are disclosed. The method includes a) supplying a mobile bearing structure (30) comprising means for moving the axle (12) which are able to move along a direction substantially parallel to the axle installation direction, b) installing the axle (12) on the means for moving the axle, c) aligning the axis (C) of the axle (12) with the axis (B) of the bore (14), and d) inserting the axle (12) into said bore (14) of the bogie (16) by moving the means for moving the axle (12) along the direction substantially parallel to the axle installation direction.

IPC Classes  ?

• B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

Abstract

The invention relates to a contactor comprising a motor (2) and a commutator-brush system (3), the motor comprising a stator (200) and a rotor (201), the commutator-brush system comprising: - a commutator (300) joined to the rotor, the commutator comprising at least one conductive portion (302) and at least one non-conductive portion (303); and - a pair of brushes formed by two brushes (304), the brushes each having a contact face configured to rub against the commutator. A side surface of the commutator (300) includes the conductive portion (302) and the non-conductive portion (303) of the commutator, the commutator being rotatable about an axis of rotation (X). The commutator-brush system (3) is configured to move between a conducting position in which the commutator electrically connects the pair of brushes, and an interrupting position in which the commutator electrically isolates the pair of brushes (304), the commutator-brush system passing from the conducting position to the interrupting position, and vice versa, by rotation of the commutator (300) by the motor.

IPC Classes  ?

• H01H 1/36 - Contacts characterised by the manner in which co-operating contacts engage by sliding
• H01H 19/56 - Angularly-movable actuating part carrying contacts, e.g. drum switch
• H01H 19/58 - Angularly-movable actuating part carrying contacts, e.g. drum switch having only axial contact pressure, e.g. disc switch, wafer switch
• H01H 3/26 - Power arrangements internal to the switch for operating the driving mechanism using dynamo-electric motor
• H01H 3/60 - Mechanical arrangements for preventing or damping vibration or shock

Abstract

A facility for pairing a metal shield to a leading edge of a preform made of composite material for the production of an aircraft turbine engine blade, the facility including a support configured to receive and hold the metal shield, —a movement hexapod which carries the support and is able to move the support along and about the three axes of an XYZ coordinate system, —an automaton which includes jaws and is configured to receive and hold the preform, and—a computing unit for controlling the hexapod and the automaton with a view to producing the pairing. The invention also relates to a method for pairing the metal shield to the leading edge of the preform made of composite material for the production of the aircraft turbine engine blade.

IPC Classes  ?

• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives
• B29D 99/00 - Subject matter not provided for in other groups of this subclass
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.

IPC Classes  ?

• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.

IPC Classes  ?

• C04B 41/52 - Multiple coating or impregnating
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramicsTreatment of natural stone
• C04B 41/45 - Coating or impregnating
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/51 - Metallising
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for

Abstract

The invention relates to a curing mold (10) for manufacturing a turbomachine component made of composite material from a preform (200), comprising: —a first and a second body (11, 12) defining an air gap receiving the preform; —at least one primary channel (21) arranged in the first and/or the second body; —an injection member (22) of a pressurized fluid in the primary channels; —at least one secondary channel (23), in which a piston (24) slides, which delimits, on the one hand, a first chamber (26) in communication with the or a primary channel and, on the other hand, a second chamber (27) in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.

IPC Classes  ?

• B29C 43/34 - Feeding the material to the mould or the compression means
• B29C 43/02 - Compression moulding, i.e. applying external pressure to flow the moulding materialApparatus therefor of articles of definite length, i.e. discrete articles
• B29C 43/32 - Component parts, details or accessoriesAuxiliary operations
• B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
• B29C 43/52 - Heating or cooling
• B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• B29C 70/54 - Component parts, details or accessoriesAuxiliary operations
• B29L 31/00 - Other particular articles

Abstract

The invention relates to a brushless starter-generator (1) comprising: - a main electrical machine (10) having a stator (11) comprising stator windings (12a, 12b, 12c) and a rotor (13) comprising a rotor winding (14) and intended to be mechanically coupled to the combustion engine (200); - an exciter (20) comprising a stator winding (24) and rotor windings (23a, 23b, 23c) connected to the rotor winding (14) of the main electrical machine (10), the rotors of the main electrical machine (10) and of the exciter (20) forming the rotor (75) of the starter-generator; and - a regulator (50) configured to supply the stator winding of the exciter with AC voltage with duty cycle modulation of alternation width when the starter-generator operates in starter mode, the regulator being configured to vary the duty cycle so as to vary an excitation delivered by the rotor (22) of the exciter to the rotor winding of the main electrical machine.

IPC Classes  ?

• H02P 9/08 - Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
• F02C 7/268 - Starting drives for the rotor
• F02N 11/04 - Starting of engines by means of electric motors the motors being associated with current generators
• H02K 19/38 - Structural association of synchronous generators with exciting machines
• F02N 11/08 - Circuits specially adapted for starting of engines
• F02C 7/275 - Mechanical drives

Abstract

The invention relates to a battery comprising: - at least one electrochemical accumulator (3) including an active portion and a shell enclosing the active portion; - a casing (2) housing the at least one accumulator (3); and - a heat-transfer fluid (5) contained in the casing (2), the shell (300) including a weakened zone configured to open under the effect of an overpressure in the accumulator (3) and to discharge gases produced by the active portion of the accumulator (3) that caused the overpressure. During the overpressure in the at least one accumulator (3), the heat-transfer fluid (5) comes into contact with the gases produced by the accumulator (3) so as to contain the gases and cool the accumulator.

IPC Classes  ?

• H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
• H01M 10/613 - Cooling or keeping cold
• H01M 10/6567 - Liquids
• H01M 10/6569 - Fluids undergoing a liquid-gas phase change or transition, e.g. evaporation or condensation
• H01M 50/325 - Re-sealable arrangements comprising deformable valve members, e.g. elastic or flexible valve members
• H01M 50/342 - Non-re-sealable arrangements
• H01M 50/358 - External gas exhaust passages located on the battery cover or case
• H01M 50/317 - Re-sealable arrangements

Abstract

A method for manufacturing a shell mold intended for manufacturing at least one metal part by lost-wax casting, the shell mold including at least one molding cavity intended for molding the metal part, and at least one feed channel intended to convey a liquid metal to the molding cavity, the method including manufacturing a wax pattern including a part pattern intended to form the molding cavity and a feed channel pattern intended to form the feed channel, arranging at least one ceramic insert around at least a portion of the feed channel pattern, and manufacturing the shell mold around the wax pattern.

IPC Classes  ?

• B22C 7/02 - Lost patterns
• B22C 9/04 - Use of lost patterns
• B22C 9/08 - Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
• B33Y 80/00 - Products made by additive manufacturing

Abstract

The invention relates to a thermocouple comprising: —a substrate comprising an upper surface; —a first arm comprising a first horizontal part and a first connection terminal; —a second arm comprising a second horizontal part and a second connection terminal; the first arm being arranged on the upper surface of the substrate, the second arm being arranged on the first arm such that the second horizontal part at least partially covers the first horizontal part and such that the second connection terminal is in contact with the upper part of the substrate, a hot junction of the thermocouple being defined by the zone of contact between the first arm and the second arm.

IPC Classes  ?

• G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
• G01K 1/14 - SupportsFastening devicesArrangements for mounting thermometers in particular locations
• H10N 10/01 - Manufacture or treatment
• H10N 10/13 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the heat-exchanging means at the junction
• H10N 10/17 - Thermoelectric devices comprising a junction of dissimilar materials, i.e. devices exhibiting Seebeck or Peltier effects operating with only the Peltier or Seebeck effects characterised by the structure or configuration of the cell or thermocouple forming the device

Abstract

A power module includes a plurality of semiconductor-based power components and a substrate having an upper metallization receiving the components and a lower metallization opposite to the upper metallization. Optionally, a baseplate may be fixed to the lower metallization of the substrate. A metal structure is in direct contact with a lower surface defined by the either optional baseplate or the substrate, on the side opposite the components. The power module includes at least one elongated temperature sensor, at least partially immersed in the metal structure and spreading parallel to the lower surface.

IPC Classes  ?

• H01L 23/36 - Selection of materials, or shaping, to facilitate cooling or heating, e.g. heat sinks
• G01K 7/02 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using thermoelectric elements, e.g. thermocouples
• G01K 11/3206 - Measuring temperature based on physical or chemical changes not covered by group , , , or using changes in transmittance, scattering or luminescence in optical fibres at discrete locations in the fibre, e.g. using Bragg scattering
• H01L 21/48 - Manufacture or treatment of parts, e.g. containers, prior to assembly of the devices, using processes not provided for in a single one of the groups or
• H01L 23/00 - Details of semiconductor or other solid state devices
• H01L 23/057 - ContainersSeals characterised by the shape the container being a hollow construction and having an insulating base as a mounting for the semiconductor body the leads being parallel to the base
• H01L 23/498 - Leads on insulating substrates
• H01L 23/538 - Arrangements for conducting electric current within the device in operation from one component to another the interconnection structure between a plurality of semiconductor chips being formed on, or in, insulating substrates
• H01L 25/00 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices
• H01L 25/065 - Assemblies consisting of a plurality of individual semiconductor or other solid-state devices all the devices being of a type provided for in a single subclass of subclasses , , , , or , e.g. assemblies of rectifier diodes the devices not having separate containers the devices being of a type provided for in group

Abstract

The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current. The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current. The invention also relates to an aircraft provided with such a propulsion system.

IPC Classes  ?

• B64D 27/33 - Hybrid electric aircraft
• B64D 27/18 - Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
• B64D 27/31 - Aircraft characterised by electric power plants within, or attached to, wings
• B64D 27/357 - Arrangements for on-board electric energy production, distribution, recovery or storage using batteries

Abstract

A method of control of a power generation and control system of an aircraft including: a hybrid propulsion system including an electrical network and a propulsive energy source, at least one non-propulsive energy source, a control unit of the hybrid propulsion system, and an overall aircraft power control unit, characterized in that the method includes: the determination of an operability limit of the propulsive energy source, the monitoring of the operability of the propulsive energy source by the control unit of the hybrid propulsion system, and the control of a power generated by the propulsive energy source by the overall aircraft power control unit when the operability of the propulsive energy source is less than said determined operability limit or the control of a power generated by the propulsive energy source by the control unit of the hybrid propulsion system.

IPC Classes  ?

• B64D 27/33 - Hybrid electric aircraft
• B64D 41/00 - Power installations for auxiliary purposes

Abstract

The invention relates to a method for non-destructively testing a part by means of transmission radiography, which method comprises the following steps of acquiring N projections (P(n)) of the part, generating calculated N images (P(n)) of the part, estimating, by successive iterations, the vector p from an initial vector p=pini and the vector c from an initial vector c=cini and/or the parameter vector a from an initial vector α=αini, by minimising the sum of the squared differences between the projections (P(n)) and the images (P(n)), processing the projections (P(n)) and/or the images (P(n)), identifying defects in the part by comparing the processed projections (P(n)) and the processed images (P(n)).

IPC Classes  ?

• G01N 23/18 - Investigating the presence of defects or foreign matter
• G01N 23/20066 - Measuring inelastic scattering of gamma rays, e.g. Compton effect

Abstract

An extrusion head for additive manufacturing includes an enclosure defining a supply chamber. The enclosure includes at least one inlet port opening into the supply chamber and configured to receive a material to be extruded under pressure and a plurality of extrusion nozzles. Each nozzle is in communication with the supply chamber and opens onto the exterior of the enclosure via an outlet orifice. The nozzles of the plurality of nozzles are arranged adjacent to one another with a determined spacing between each nozzle outlet orifice.

IPC Classes  ?

• B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
• B29C 64/209 - HeadsNozzles
• B29C 64/314 - Preparation
• B33Y 10/00 - Processes of additive manufacturing
• B33Y 30/00 - Apparatus for additive manufacturingDetails thereof or accessories therefor
• B33Y 40/10 - Pre-treatment

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.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner
• F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
• F02C 9/32 - Control of fuel supply characterised by throttling of fuel

Abstract

A method for detecting a defect in a bearing of a rotating system, includes acquiring a bearing position signal, a vibratory signal from the bearing and a theoretical characteristic vector of the bearing; determining a deterministic part of the vibratory signal and removing the deterministic part to obtain a residual signal function of the position signal; calculating, from the theoretical characteristic vector, lower and upper bounds of defect frequencies; calculating, from the vibratory signal, a spectral coherence and the square of the amplitude of the spectral coherence; calculating, from the square of the amplitude of the spectral coherence and the lower and upper bounds of the defect frequencies, a current characteristic vector of the bearing; determining a spectral cyclic contrast of the defect; finely identifying signatures of interest by calculating a weighted integrated cyclic coherence associated with the defect, and determining diagnostic indicators easily interpretable by an operator.

IPC Classes  ?

• G01M 13/045 - Acoustic or vibration analysis

Abstract

This method for determining a frictional coefficient of an aircraft on a runway includes the steps of: producing a database of frictional coefficients simulated for various types of aircraft and various runway conditions by applying simulation data to models representing the braking of aircraft when landing, for various braking scenarios; and predicting a frictional coefficient from real data of the aircraft for which the frictional coefficient is determined from data stored in the database.

IPC Classes  ?

• G06F 30/27 - Design optimisation, verification or simulation using machine learning, e.g. artificial intelligence, neural networks, support vector machines [SVM] or training a model
• G08G 5/00 - Traffic control systems for aircraft

Abstract

A nickel-based superalloy comprises in weight percentages: 5.4 to 6.0% of aluminium, 7.5 to 9.0% of tantalum, 0.10 to 0.25% of titanium, 5.5 to 7.5% of cobalt, 4.0 to 5.5% of chromium, 0.10 to 0.70% of molybdenum, 4.0 to 5.0% of tungsten, 4.8 to 6.2% of rhenium, 0.04 to 0.15% 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.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
• C30B 29/52 - Alloys

Abstract

Molding core for manufacturing an OMC hollow aeronautical part, in particular a fan module part, including a composite material including on the one hand a first phase of formula Mn+1AlCn, where n=1 to 3, and M being a transition metal selected from the group consisting of titanium, niobium, chromium or zirconium, the composite material including on the other hand a second phase of formula Al4C3

IPC Classes  ?

• B29C 33/54 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles made of powdered or granular material
• B29C 33/38 - Moulds or coresDetails thereof or accessories therefor characterised by the material or the manufacturing process
• B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

3.

IPC Classes  ?

• B22C 9/10 - CoresManufacture or installation of cores
• B22C 1/00 - Compositions of refractory mould or core materialsGrain structures thereofChemical or physical features in the formation or manufacture of moulds
• B22C 9/04 - Use of lost patterns
• B22D 29/00 - Removing castings from moulds, not restricted to casting processes covered by a single main groupRemoving coresHandling ingots

Abstract

A counter-form for producing metal aeronautical parts, in particular a turbine part by solid-phase densification, including a composite material containing, on the one hand, a first phase having formula Mn+1AlCn, where n=1 to 3 and M is a transition metal selected from the group consisting of titanium and/or molybdenum and/or niobium and/or chromium, and, on the other hand, a second phase having formula Al4C3.

IPC Classes  ?

• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades

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.

IPC Classes  ?

• B64C 25/60 - Oleo legs
• F16F 15/023 - Suppression of vibrations of non-rotating, e.g. reciprocating, systemsSuppression of vibrations of rotating systems by use of members not moving with the rotating system using fluid means

Abstract

A method for manufacturing a fibrous preform for a blade or propeller part of a turbomachine, includes at least one fixing base extended by a mounting portion of an aerodynamic profile, the method including the winding of a fibrous texture, obtained by contour weaving, on a substrate of changing section having at least a first region of extra thickness in the shape of the fixing base and a second region in the shape of the mounting portion of the aerodynamic profile.

IPC Classes  ?

• B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• B29C 53/56 - Winding and joining, e.g. winding spirally
• B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

An aircraft landing gear shock absorber strut including an outer cylinder having a bore defining an opening; an inner cylinder having a first end region movably coupled within the bore and a second end region which projects out of the opening. The inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition and a second condition and is biased by a spring force to assume the second condition. A mechanical outstop is arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member drives the out stop axially to move the inner cylinder from the second condition towards the first condition. The rotatable member is arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.

IPC Classes  ?

• B64C 25/60 - Oleo legs
• B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways

Abstract

A method for monitoring a turbine engine, said method including, for at least one blade of a rotor with which the turbine engine is equipped, the steps of: obtaining a plurality of samples of at least one analogue time signal acquired by means of at least one fixed proximity sensor and representing a passage of said at least one blade in front of said at least one proximity sensor; calculating a deflection of said at least one blade for each of said samples: determining, in the form of a linear combination of sinusoidal signals, a so-called “approximation signal”, minimizing a cost function evaluating a deviation between said calculated deflections and said approximation signal; and monitoring the vibratory behavior of said at least one blade on the basis of frequencies and/or amplitudes and/or phases of the sinusoidal signals that make up said approximation signal.

IPC Classes  ?

• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

A method for manufacturing a turbomachine vane made of composite material and having a cavity, the method includes producing a core having the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only a portion of the volume of the core, the core further including a sealed envelope defining the outer surface of said core; and forming a composite material skin around the core.

IPC Classes  ?

• B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A method for manufacturing a composite material vane with a cavity, includes making a core with the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only part of the volume of the core, the remaining volume of the core being occupied by a material of a fleeting nature, forming a composite material skin around the core, and eliminating the fleeting material to obtain a composite material vane with a cavity reinforced by the reinforcing structure.

IPC Classes  ?

• B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
• B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
• B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
• B29L 31/08 - Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers

Abstract

A turbomachine may include a high-pressure turbine connected to a high-pressure shaft and a low-pressure turbine connected to a low-pressure shaft, the hot gases leaving the high-pressure turbine driving the low-pressure turbine. A method for regulating the turbomachine includes electrically assisting the high-pressure shaft in order to provide said high-pressure shaft with electrical energy in addition to thermal energy obtained from a combustion chamber of the turbomachine, for an assistance period, and correcting the speed of the low-pressure shaft to achieve a reference speed of the low-pressure shaft that was previously determined in the absence of electrical assistance.

IPC Classes  ?

• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F01D 21/14 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to other specific conditions

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.

IPC Classes  ?

• B32B 3/12 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
• B32B 3/26 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layerLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a layer with cavities or internal voids
• B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
• B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
• B32B 27/38 - Layered products essentially comprising synthetic resin comprising epoxy resins
• F02K 1/82 - Jet pipe walls, e.g. liners

Abstract

A method for inspecting the surface finish of a cast part made of single-crystal metal, the surface of the part potentially containing defects resulting from an inhomogeneity of orientation of at least a crystal lattice of the single-crystal metal, the method including acquiring, using an image-acquiring device, a series of images of the cast part illuminated by a polarized and collimated illuminating device, then analysing the series of images by an image-processing device, each image of the series of images being taken at a different polarization angle.

IPC Classes  ?

• G01N 21/88 - Investigating the presence of flaws, defects or contamination
• G01N 21/95 - Investigating the presence of flaws, defects or contamination characterised by the material or shape of the object to be examined

Abstract

An aircraft landing gear shock absorber strut including a damping pin and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.

IPC Classes  ?

• B64C 25/60 - Oleo legs
• B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways

Abstract

A method for characterizing a mechanical part making it possible to evaluate the residual stresses in the part, as well as a method for constructing a predictive model and a non-destructive testing method making it possible to easily test such a part, the characterizing method including the following steps: measuring geometrical information of the part in a first state, physically transforming the part between the first state and a second state, measuring geometrical information of the part in its second state, determining the displacement field between the first state and the second state of the part by a digital image correlation method and obtaining the deformation field between the first state and the second state of the part, determining the stress field in the second state of the part by a finite element simulation method.

IPC Classes  ?

• G01N 3/02 - Investigating strength properties of solid materials by application of mechanical stress Details
• G06N 5/022 - Knowledge engineeringKnowledge acquisition

Abstract

A method for determining the presence of at least one defect in a three-dimensional part on the basis of a reference base, wherein: an image of the part is acquired by tomography; the image is segmented and the segmented image is registered with respect to the images of the reference base; the subdomains associated with the registered segmented image are determined; and for each subdomain of the registered segmented image, the following steps are carried out: registering the subdomain; breaking down the subdomain with respect to the principal modes of the reference base; generating a synthetic image of the subdomain from the breakdown, which is subtracted from the registered segmented image of the subdomain; and determining that a defect is present on the basis of the comparison of the value of each pixel of the residual image with a predetermined threshold.

IPC Classes  ?

• G06T 7/00 - Image analysis
• G06T 7/10 - SegmentationEdge detection

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.

IPC Classes  ?

• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22C 19/00 - Alloys based on nickel or cobalt
• C22C 30/00 - Alloys containing less than 50% by weight of each constituent
• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion

Abstract

A piezo-electric fluid pump is provided including a main housing; a fluid reservoir located within the main housing; a piston head moveably mounted within the main housing; a piezo-electric stack; a bias mechanism arranged to couple the piston head and piezo-electric stack and maintain the piezo-electric stack in compression; an outlet plate statically mounted within the main housing adjacent to the piston head, wherein the adjacent surfaces of the outlet plate and piston head define a pumping chamber; an inlet disc valve arranged to permit a one-way flow of fluid from the reservoir into the pumping chamber; and an outlet disc valve arranged to permit a one-way flow of fluid out of the pumping chamber. The combination of pre-loading of the piezo-electric stack in compression and use of inlet disc valve enables the piezo-electric pump to exhibit substantial improvement to the pressure and flow capability compared to other piezo-electric pumps.

IPC Classes  ?

• F04B 17/00 - Pumps characterised by combination with, or adaptation to, specific driving engines or motors

Abstract

A method for manufacturing turbomachine disks is provided. The method includes: providing a nickel alloy powder; and shaping the powder to obtain a disk. Providing a powder can include: manufacturing a nickel alloy electrode by PAM-CHR; atomizing a nickel alloy by EIGA from the nickel alloy electrode, leading to a raw powder; and sifting the raw powder under inert atmosphere or under vacuum with a granulometric cut-off between 150 μm and 50 μm, leading to the nickel-based alloy powder. In some examples, the granulometric cut-off can be between 125 μm or 75 μm.

IPC Classes  ?

• B22F 9/08 - Making metallic powder or suspensions thereofApparatus or devices specially adapted therefor using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
• B22F 3/17 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sinteringApparatus specially adapted therefor by forging
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product