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

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

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

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

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

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

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

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. 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

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

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

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 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

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

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

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

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

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

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

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 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

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

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 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 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

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 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

Abstract

An acoustic treatment device for an aircraft propulsion assembly includes two skins that enclose an acoustic structure. The acoustic structure has a cellular structure with hollow cells and a structure of shapes with protruding shapes, each of which is engaged in a different hollow cell of the cellular structure. The structure of shapes additionally has stubs designed to fit into the hollow cells of the cellular structure and to allow the acoustic treatment device to be fixed to a component of the aircraft propulsion assembly.

IPC Classes  ?

• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank. The fuel circuit comprising a buffer tank for supplying the turbine engine and a plurality of compression modules configured to supply the buffer tank, each compression module comprising an elementary tank of fixed volume, an elementary heat source configured to increase the temperature of the fuel in the elementary tank in an isochoric manner, an inlet valve connecting the elementary tank to an upstream part of the fuel circuit, an outlet valve connecting the elementary tank to the buffer tank, and a venting valve connecting the elementary tank to the cryogenic tank via a return circuit in which a gaseous stream circulates.

IPC Classes  ?

• B64D 37/34 - Conditioning fuel, e.g. heating
• F02C 7/232 - Fuel valvesDraining valves or systems
• F02C 9/40 - Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels

Abstract

The invention relates to a method, navigation device and computer program product for assisting with the navigation of a vehicle provided with a navigation device. The method comprises the following steps: acquiring a priori values of variables of a navigation device of the vehicle; determining current values of the variables and a current uncertainty matrix from previous values of the variables and a previous uncertainty matrix; and determining a correction from the current values of the variables, the current uncertainty matrix and a measurement.

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

Abstract

A propulsion system includes a gas turbine designed so that a combustion chamber can be ignited in a first ignition range of rotational speeds of a compressor shaft. The system further includes a control device designed to control an electric starter to accelerate the compressor shaft and, when the compressor shaft is accelerated, to control an attempt to ignite the combustion chamber. The gas turbine is designed so that the combustion chamber can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.

IPC Classes  ?

• F02C 7/268 - Starting drives for the rotor
• B64D 33/00 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
• F02C 7/264 - Ignition

Abstract

A tooling for winding a fibrous fabric on a support, allowing gradual modification of the shape of the support as winding progresses, and includes compaction devices to reduce wrinkling of the fabric obtained after compaction.

IPC Classes  ?

• 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 70/24 - 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
• 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

Abstract

A method for manufacturing an acoustic panel by welding of at least two acoustic components made of thermoplastic material, a thermal gradient being applied on the acoustic components during the welding operation so as to apply a temperature higher than the glass transition or melting temperature of the material on the area to be welded and so as to apply a temperature lower than or equal to the geometric stabilization temperature of the material on the parts furthest from the area to be welded.

IPC Classes  ?

• B29C 65/18 - Joining of preformed partsApparatus therefor by heating, with or without pressure using heated tool
• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 65/10 - Joining of preformed partsApparatus therefor by heating, with or without pressure using hot gases
• B29K 79/00 - Use of other polymers having nitrogen, with or without oxygen or carbon only, in the main chain, as moulding material
• B29L 31/38 - Loudspeaker conesAcoustic diaphragms

Abstract

A method includes coating of one or more zones of the refractory alloy part, using a treatment composition including one or more types of preceramic polymer, a solvent and one or more active fillers, and heat treating the coated refractory alloy part, the heat treatment allowing to partially convert the preceramic polymer to form a ceramic layer, the active filler forming on a surface of the refractory alloy part, one or more ternary alloys and forming a continuous layer between the surface of the refractory alloy part and the ceramic layer obtained by conversion. The heat treatment forms a continuous layer of the ternary alloy. The treatment composition includes, relative to the total weight of the treatment composition, a weight proportion of between 40% and 66% of the one or more active fillers, and an active filler/preceramic polymer weight ratio is greater than or equal to 2.

IPC Classes  ?

• B22C 9/12 - Treating moulds or cores, e.g. drying, hardening
• B22C 3/00 - Selection of compositions for coating the surfaces of moulds, cores, or patterns
• B22C 9/10 - CoresManufacture or installation of cores
• C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
• 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

Abstract

A spectral interrogation device, including: an optical source for emitting a light signal, a measurement optical fibre comprising a series of successive Bragg gratings for reflecting the light signal in different wavelength bands, a reflective optical fibre comprising a total reflection element, a wavelength detector, and an optical switch for switching between a sequence of three operating modes. In a first mode, the light signal emitted by a given optical source is guided from the optical source to a corresponding measurement optical fibre. In a second mode, the light signal is guided to make a predetermined number of return trips in a line formed by a coupling between the measurement optical fibre and a corresponding reflective optical fibre, generating a predetermined delay between the successive gratings. In a third mode, the light signal is guided to a corresponding detector to successively measure the wavelength bands associated with the gratings.

IPC Classes  ?

• 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

Abstract

A method for manufacturing a vane made of composite material for a turbomachine, including the steps of three-dimensional fibre weaving and producing a fibrous preform, reinforcing an edge of the preform intended to form a leading edge of a blade of the vane, by integrating a metallic reinforcement on this edge, mounting the preform and the reinforcement in a mould, densifying the preform by a matrix to form the vane, wherein, prior to the integration of the reinforcement, the method includes a step of introducing at least one reinforcement support configured to be interposed between the reinforcement and the edge, and wherein at the densification step, the support is enveloped with the matrix to bond the edge and the reinforcement with a predefined and homogeneous minimum thickness.

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 70/70 - Completely encapsulating inserts
• 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 fibrous structure intended to form the fibrous reinforcement of a part made of composite material includes a fibrous reinforcement densified by a matrix, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The fibrous structure includes at least a first portion having a first type of weave and a second portion, continuing on from the first portion, having a second type of weave, the warp yarns and the weft yarns having a degree of interweaving in the first type of weave that is greater than the degree of interweaving of the warp yarns and the weft yarns in the second type of weave.

IPC Classes  ?

• B29B 11/00 - Making preforms
• 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 25/00 - Woven fabrics not otherwise provided for
• B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
• D03D 11/00 - Double or multi-ply fabrics not otherwise provided for

Abstract

Method for controlling a turbomachine equipped with a gas generator, the turbomachine including at least one electric machine forming a device for the injection/take-off of power onto/from one of the low-pressure/high-pressure rotating shafts of the gas generator. Said method has steps included in a loop which include determining, for at least one shaft and according to a speed setpoint, of a variation dU in a power command; determining, for all of the electric machines as a whole and according to an injection/take-off setpoint, of a variation dPelec in a power injection/take-off command; and determining a command including components pertaining to fuel flow rate and to power injection/take-off for each electric machine, according to the variations dU dPelec, and according to the operational limits of the turbomachine.

IPC Classes  ?

• F02C 9/56 - Control of fuel supply conjointly with another control of the plant with power transmission control
• F02C 3/113 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors

Abstract

A propulsion unit including: a gas generator including a compressor, a combustion chamber, a turbine, at least two compressed-air propulsion modules, each propulsion module including: a fan, a compressed-air turbine configured to drive the rotation of the fan, a manifold allowing the respective turbines of the compressed-air propulsion modules to be supplied with compressed air, wherein the manifold is configured to collect and mix: at least a portion of the flow that has passed through the combustion chamber of the gas generator, typically as it leaves the turbine, and at least one bypass flow, the bypass flow being a flow of air which is not passed through the combustion chamber of the gas generator.

IPC Classes  ?

• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• B64D 27/10 - Aircraft characterised by the type or position of power plants of gas-turbine type
• F04D 17/02 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumpsHelico-centrifugal pumps specially adapted for elastic fluids having non-centrifugal stages, e.g. centripetal

Abstract

A fibrous texture for a blade has a three-dimensional weave between a first plurality of yarn layers and a second plurality of yarn layers, includes a blade aerofoil part extending between a first edge and a second edge. The texture includes a first part with at least three yarn layers of the first plurality of yarns and at least three yarn layers of the second plurality of yarns. Yarns of the two yarn layers of the first plurality of yarns bind yarns of the second plurality of yarns to the two yarn layers of the second plurality of yarns with a determined binding frequency.

IPC Classes  ?

• D03D 25/00 - Woven fabrics not otherwise provided for
• 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

Abstract

A stator part of a turbomachine includes a platform, a blade, and a fin. The blade and the fin extend from the platform. The platform, an extrados of the blade and the fin define therebetween a gas flow channel. The channel has a section in a plane normal to an axis of the turbomachine, the section having a surface area, the surface area continuously decreasing from upstream to downstream with reference to a general gas flow direction through the turbomachine.

IPC Classes  ?

• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F01D 5/14 - Form or construction

Abstract

An assembly including a turbine engine casing, in particular for an aircraft, the turbine engine casing including an annular or cylindrical radially outer shell, provided with a radially inner surface, and an aerody-namic treatment member including a plurality of grooves distributed in a circumferential direction. The radially outer shell includes a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and having a shape that matches that of the circumferential recess, the treatment member including a circumferential opening into which the plurality of grooves open.

IPC Classes  ?

• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids
• F04D 29/52 - CasingsConnections for working fluid for axial pumps
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers

Abstract

A nickel-based superalloy including, in weight percentages, 5.5 to 7.5% of aluminum, 1.0 to 4.0% of tantalum, 0.50 to 3.0% of titanium, 3.0 to 7.0% of cobalt, 8.0 to 12.0% of chromium, 0 to 2.5% of molybdenum, 0 to 3.0% of tungsten, 0.50 to 2.8% of rhenium, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities.

IPC Classes  ?

• F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C30B 29/52 - Alloys

Abstract

A power supply system comprising: a first converter module comprising an AC/DC converter and being arranged to produce an intermediate voltage from an input voltage; a second converter module comprising a DC/DC converter and being controllable to use the intermediate voltage to produce selectively at least two distinct output voltage levels; and a control unit arranged to acquire a flight parameter representative of the flight phase and/or of the altitude, and to control the power supply system in such a manner that the second converter module delivers to each electrical system a power supply voltage that depends on the flight parameter and on said electrical system, and that is equal to one of the output voltage levels.

IPC Classes  ?

• H02J 3/46 - Controlling the sharing of output between the generators, converters, or transformers
• B64C 25/32 - Alighting gear characterised by elements which contact the ground or similar surface
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
• H02J 1/10 - Parallel operation of dc sources
• H02J 3/38 - Arrangements for parallelly feeding a single network by two or more generators, converters or transformers

Abstract

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

IPC Classes  ?

• G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
• G01H 1/10 - Measuring vibrations in solids by using direct conduction to the detector of torsional vibrations
• G01N 29/46 - Processing the detected response signal by spectral analysis, e.g. Fourier analysis
• G01P 3/50 - Devices characterised by the use of electric or magnetic means for measuring linear speed

Goods & Services

(1) Appareils et instruments optiques; appareils et instruments scientifiques; appareils et instruments pour la navigation; logiciels (programmes enregistrés); appareils de transmission d'images; lunettes 3D; lunettes (optique); appareils d'enregistrement d'images; masques de plongée; équipements de traitement de données; ordinateurs; logiciels de jeux; ordiphones [smartphones]; casques de réalité virtuelle; dispositifs d'affichage électroniques transparents pour la fourniture d'informations de fonctionnement et de navigation à des pilotes et membres d'équipage d'aéronefs; dispositifs d'affichage tête haute (HUD) sous forme d'écrans d'affichage électroniques transparents pour la fourniture d'informations de fonctionnement et de navigation à des pilotes et membres d'équipage d'aéronefs. (1) Services d'affichage électronique (télécommunications). (2) Mise à jour de logiciels; conception de logiciels; élaboration (conception) de logiciels; recherches scientifiques; conception de systèmes informatiques; conseils en technologie de l'information; développement de logiciels; recherches technologiques; programmation pour ordinateurs.

Goods & Services

Electronic bulletin board services being telecommunication services. Optical apparatus and instruments, namely, eyeglass lenses; scientific apparatus and instruments, namely, thermal sensors, temperature sensors, pressure sensors, position sensors, proximity sensors, sensors chips, tracking sensors; navigation apparatus and instruments, namely, transmitters, calculators, compasses for measuring, GPS (global positioning systems) automatic steering for apparatus, safety and security lights; recorded computer software for use on augmented reality systems for pilot on land, air and sea vehicles; image transmission apparatus; 3d spectacles; spectacles; image recording equipment namely apparatus for recording of images; diving masks; data processing equipment; computers; downloadable computer game software; smartphones; virtual reality headsets; heads-up displays (HUDs) in the nature of transparent electronic display devices for providing aircraft crew members and pilots with navigational and operational information; head-up display (HUD) devices in the form of transparent electronic display screens for providing aircraft crew members and pilots with navigational and operational information. Updating of computer software; software design; software development and design; scientific research; computer system design; advice regarding information technology namely, IT consulting services relating to installation, maintenance and repair of computer software; software development; technological research in the field of augmented reality computer hardware systems; programming for computers.

Abstract

The present disclosure relates to the technical field of TiAl intermetallic foundry alloys. More particularly, it relates to such an alloy comprising: 44≤Al≤47 at. %; 0

IPC Classes  ?

• C22F 1/18 - High-melting or refractory metals or alloys based thereon
• C22C 14/00 - Alloys based on titanium
• C22F 1/00 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working

Abstract

A method for manufacturing a turbomachine component made of composite material includes the step of creating a shaped fibrous preform by three-dimensional weaving of filaments to create a fibrous texture which is wound in several superposed layers onto a mandrel of a profile corresponding to that of the component that is to be manufactured, so as to obtain the fibrous preform of a shape corresponding to that of the component that is to be manufactured, the filaments being divided into warp filaments and weft filaments, the warp filaments being interwoven with the weft filaments in a three-dimensional weave. The method further includes the step of creating a stiffening zone in the fibrous preform, the stiffening zone being formed of at least one layer of warp filaments not interwoven with weft filaments that is interposed between the interwoven warp filaments and weft filaments.

IPC Classes  ?

• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• 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
• 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
• 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 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
• B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
• D03D 25/00 - Woven fabrics not otherwise provided for

Abstract

Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring (201) a priori values of kinematic variables of the navigation device, determining (202) respective current values of kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, determining (203) a correction, updating (204) the respective current values of the kinematic variables based on the correction and on the current uncertainty matrix.

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

Abstract

Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring a priori values of kinematic variables of the navigation device, determining (202) respective current values of the kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, a previous uncertainty matrix representative of an uncertainty of the respective previous values of the kinematic variables and a model of Earth's gravity experienced by the navigation device, the modeled gravity increasing with an altitude of the navigation device.

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

Abstract

A method for focusing acoustic waves on an interface between two layers of a multilayer structure includes providing laser means able to emit a laser beam toward an exterior surface of the multilayer structure to produce a longitudinal wave from the centre of a laser-beam spot projected onto the exterior surface and a transverse wave from the periphery of said spot, determining the distance between said interface and the exterior surface, determining one or more propagation velocities of each of the longitudinal wave and the transverse wave in the one or more layers passed through by said waves to reach said interface, and determining a radius of the laser-beam spot depending on the one or more propagation velocities and on said distance so that the time taken by the longitudinal wave to reach said interface is equal to three times the time taken by the transverse wave to reach said interface.

IPC Classes  ?

• G01N 21/17 - Systems in which incident light is modified in accordance with the properties of the material investigated

Abstract

A surface heat exchanger for an aircraft turbomachine includes a support wall, a panel parallel to the support wall, partitions connecting the wall to the panel to define channels in which an air flow flows, and fins situated in the channels. The panel has a central part parallel to the wall and a downstream part that is inclined with respect to the wall. An upstream end is connected to the central part and a downstream end is situated at a distance from the wall and delimits with the latter a main outlet of the channels. The downstream part has fixed flaps disposed one after another so as to delimit between one another additional outlets of the channels.

IPC Classes  ?

• F28D 1/053 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with tubular conduits the conduits being straight
• F28F 1/32 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending transversely the means having portions engaging further tubular elements

Abstract

A turbojet includes in succession, from upstream to downstream in the flow direction of a primary air stream: a low-pressure casing, an intermediate casing, and a high-pressure casing that are longitudinally aligned and which jointly delimit an internal annular passage for the circulation of the air stream. The intermediate casing delimits a portion of the annular passage called a gooseneck and includes: an air discharge system able to extract air from the air stream circulating in a first zone of the gooseneck and to discharge it outside the passage, and an air extraction system able to extract air circulating in a second zone of the gooseneck for an air conditioning system, the second air extraction zone being located downstream of the first air extraction zone.

IPC Classes  ?

• F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages

Abstract

The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to provide a separation; c) the cut preform is deformed so as to provide an orifice then comprising a first and a second open end (27a, 27b); d) the deformed preform is placed into an injection mould; e) a resin is injected in order to impregnate the whole of the deformed preform; f) the resin is polymerised; and g) a composite part is extracted from the mould; characterised in that: h) a flexible mandrel (31) with a predetermined shape is positioned in the orifice before the injection step e); i) the flexible mandrel (31) is removed after step f) or the demoulding step g), the composite part then having a hollow core (25).

IPC Classes  ?

• F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
• B29C 37/00 - Component parts, details, accessories or auxiliary operations, not covered by group or
• 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]

Abstract

This invention relates to a superconducting electric machine (1), for example with axial flux or with radial flux, comprising an inductor (3) comprising superconducting pellets (7) circumferentially distributed around an axis (X) of the electric machine (1) and a flux barrier (12) comprising a superconducting material, said flux barrier (12) being centered on the axis (X) of rotation and extending radially inward of the superconducting pellets (7).

IPC Classes  ?

• H02K 55/00 - Dynamo-electric machines having windings operating at cryogenic temperatures
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
• H01F 6/00 - Superconducting magnetsSuperconducting coils

Abstract

The present invention relates to a superconducting electric machine (1) comprising an inductor (3) having: —superconducting pellets (7) circumferentially distributed about an axis (X) of the electric machine (1), —an armature (2) comprising coils (5), each coil (5) having a circumferential radially inner edge (10) and a circumferential radially outer edge (9), and—at least one flow barrier (12, 12′) extending circumferentially with respect to the axis (X), each flow barrier (12) extending between the superconducting pellets (7) and the armature (2) so as to at least partially cover at least one of the radially outer edge (9) and the radially inner edge (10) of all or part of the coils (5) of the armature (2).

IPC Classes  ?

• H02K 55/02 - Dynamo-electric machines having windings operating at cryogenic temperatures of the synchronous type
• B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force

Abstract

The present invention relates to a method for manufacturing a part, comprising the steps of chemically etching, in a wet acid medium, at least a portion of a surface of a substrate made of a monocrystalline superalloy, comprising at least one element chosen from rhenium and ruthenium, the substrate having a γ-γ′ phase, the substrate having an average mass fraction of rhenium and/or ruthenium greater than or equal to 3%, the chemical etching being done in such a way that the average mass fraction of rhenium and/or ruthenium over the portion of the surface of the substance is less than 2%, and a step of depositing on the portion of the substrate a protective coating having a γ-γ′ phase and an average mass fraction of rhenium and/or ruthenium of less than 1%.

IPC Classes  ?

• C23C 14/02 - Pretreatment of the material to be coated
• B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C23C 14/16 - Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon

Abstract

−4 m/s in the drawing direction. The present disclosure also relates to a plant having one or more devices for implementing the method.

IPC Classes  ?

• B22D 11/112 - Treating the molten metal by accelerated cooling
• B22D 11/00 - Continuous casting of metals, i.e. casting in indefinite lengths
• B22D 11/041 - Continuous casting of metals, i.e. casting in indefinite lengths into open-ended moulds for vertical casting
• B22D 11/14 - Plants for continuous casting, e.g. for upwardly drawing the strand
• B22D 21/00 - Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedureSelection of compositions therefor
• B22D 27/04 - Influencing the temperature of the metal, e.g. by heating or cooling the mould
• B22D 41/015 - Heating means with external heating, i.e. the heat source not being a part of the ladle
• C22C 1/02 - Making non-ferrous alloys by melting
• C22C 14/00 - Alloys based on titanium

Abstract

The invention relates to a method for monitoring the state of mechanical components such as bearings and gears on a shaft line equipping a rotating machine. Said method includes a step of obtaining at least one measurement yc[k] of the absolute acceleration of the shaft, as well as a set of steps of: obtaining a value fr[k] of the rotational frequency of the shaft, determining a matrix H[k] making it possible to define a state model described by: [k+1]=x[k]+w[k]etY[k]=[(y_c [k])¦SE[k]]=H[k]×x[k]+v[k], determining an estimator of the vector x[k] based on data from the state model, said set of steps further including, for at least one mechanical component, steps of: determining, from said estimator, a quantity characteristic of a contribution of said component to the vector Y[k], comparing said quantity with a threshold, detecting a possible defect of said at least one mechanical component.

IPC Classes  ?

• G01M 13/045 - Acoustic or vibration analysis
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Goods & Services

Electric and electronic apparatus, instruments and equipment for navigation, guidance, remote control, automatic piloting and stabilization of air, land, sea and space vehicles; hybrid and inertial navigation apparatus, instruments and equipment for land, sea, aeronautical and space vehicles; gyroscopes, gyrometers; miniature, micro-machined, simple or networked sensors and actuators; gyroscopic sensors; gyrometric sensors; vibrating sensors; accelerometer sensors; inertial sensors; gyrocompass; directional compasses; electric sensors; photoelectric sensors; optical sensors; opto-mechanical sensors; sensors for determination of position, rotation, speed, acceleration and temperature; sensors for determination of temperatures, positions, rotations and distances; micro-electromechanical systems (MEMS), namely, micro-machined fine structured elements and microsystems incorporating such sensors, actuators and/or elements; data processing systems; semi-conductors for micro-electronic systems; inertial power unit; recorded software.