A method for manufacturing a propeller blade or vane includes the production of a fibrous blank of an airfoil-shaped structure including an inner housing, the insertion of at least one insert into the inner housing with the interposition of an adhesive film between the insert and the inner housing of the fibrous blank so as to obtain a fibrous preform, the holding of the fibrous preform in a molding cavity of an injection tooling, the injection of a resin into the molding cavity containing the fibrous preform and the transformation of the resin into a matrix by heat treatment. The method further includes, after holding of the fibrous preform in the molding cavity and before injection of the resin into the fibrous preform, a procedure of pre-consolidating the adhesive film including at least the application of a consolidation pressure in the molding cavity.
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
A method for weaving a texture between warp yarns and weft yarns by a weaving loom including at least one rapier able to pass through the loom along a reference path and to draw a weft yarn, the method including at least displacing at least part of the warp yarns intended to be exited from the texture, so that the yarns are disposed on one side of the reference path and so that the rest of the non-exited warp yarns is disposed on another side of the reference path, then the rapier passing through the weaving loom along the reference path without drawing any weft yarn.
The invention relates to a mold for drying a fibrous preform, comprising at least one part having inner faces defining a cavity of the mold, against which the fibrous preform, wetted by a wetting liquid, is intended to be brought into contact, said part having an openwork structure allowing the wetting liquid to pass through this part of the mold, the openwork part consisting of a plurality of intersecting filaments defining through-openings allowing the passage of the wetting liquid.
A casing of a turbine engine compressor including an inner annular wall and an outer annular wall delimiting therebetween an annular cavity. The inner annular wall includes a plurality of slots hollowed out in the thickness of the wall, the slots being arranged next to one another in a circumferential direction and each extending in an axial direction. The casing further includes a sliding ring present in the annular cavity of the casing. The sliding ring is movable in the axial direction between an open position in which the slots in the inner annular wall of the casing open into the annular cavity and a closed position in which the sliding ring covers at least some slots.
A method for three-dimensionally weaving a texture between a plurality of warp yarns extending along a longitudinal direction and a plurality of columns of weft yarns, the weft yarns extending along a transverse direction, the texture including a central part extending along the transverse direction between a first selvedge and a second selvedge, wherein at least one of the selvedge includes at least one primary weaving plane perpendicular to the transverse direction in which the weft yarns derived from the same column of weft yarns of the central part of the texture are group-interlinked, the weft yarns of the same group being aligned along the longitudinal direction.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
A method for manufacturing an acoustic panel includes the assembly of at least one acoustic component with an acoustic skin, the acoustic component including a plurality of hollow acoustic elements having a shape progressively tapering between a base and an apex, the bases of the hollow acoustic elements being connected to one another by connecting edges, wherein the connecting edges of the acoustic component are made of a transparent thermoplastic material and wherein the acoustic skin is made of an opaque thermoplastic material, and the connecting edges are attached to the acoustic skin by laser welding.
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B29K 79/00 - Utilisation comme matière de moulage d'autres polymères contenant dans la chaîne principale uniquement de l'azote avec ou sans oxygène ou carbone
B29K 81/00 - Utilisation de polymères contenant dans la chaîne principale uniquement du soufre avec ou sans azote, oxygène ou carbone comme matière de moulage
7.
METHOD FOR ASSEMBLING AN ACOUSTIC PANEL USING A SHAPING TOOL
A method for manufacturing an acoustic panel includes at least one multicellular body and an acoustic component, the method including positioning a blank made of thermoplastic material between a male portion and a female portion of a tool; shaping the blank into an acoustic component in a first bringing together of the male and female portions, so as to close the tool, disposing the multicellular body between the female portion of the tool and the acoustic component; and then a second bringing together of the male and female portions of the tool, so as to press the acoustic component against the multicellular body.
B29C 51/00 - Façonnage par thermoformage, p. ex. façonnage de feuilles dans des moules en deux parties ou par emboutissage profondAppareils à cet effet
The invention relates to a system comprising: a harness for a weaving loom and a device for monitoring the manufacture of a preform woven by the loom, the monitoring device comprising: a plurality of sensors, each sensor of the plurality of sensors being connected to one of the plurality of strings and being configured to measure a deformation of the string, the deformation being induced by a force exerted by the loom on the string to which the sensor is connected; and a processing unit connected to the plurality of sensors and configured to analyse the deformation so as to identify a manufacturing abnormality on at least one string.
G01B 7/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer les déformations dans un solide, p. ex. au moyen d'une jauge de contrainte à résistance
D03J 1/00 - Appareils auxiliaires combinés ou associés aux métiers à tisser
9.
GUIDE VANE FOR ATTACHMENT TO A STATOR SHROUD OF A GAS TURBINE ENGINE, GAS TURBINE ENGINE STATOR ASSEMBLY AND GAS TURBINE ENGINE
The invention relates to a guide vane for attachment to a stator shroud of a gas turbine engine, comprising:—a profiled part intended to extend in a gas flow in order to guide the gas flow, the profiled part having a pressure-side surface and a suction-side surface, and—a platform having a guide surface from which the profiled part extends, a first lateral surface and a second lateral surface, the second lateral surface being able to be arranged facing a first lateral surface of an identical adjacent guide vane, fanning a raised portion which prevents a parasitic transverse flow of the gas flow, while creating a depression which at least partially compensates for the obstruction of the gas flow by the raised portion.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventeur(s)
Cavarroc, Marjorie Christine
Peigney, Erwan
Aymonier, Cyril
Aubert, Guillaume
Poulon, Angélique Nadine Jeanne
Abrégé
A method for depositing on a metal substrate a continuous coating of aluminum oxide by induction heating-assisted pressurized, temperature-controlled chemical deposition, the method including a solvothermal synthesis procedure based on an aluminum oxide precursor dissolved in a water-co-solvent mixture heated by induction to a temperature of between 400° C. and 700° C. and a pressure of between 1 MPa and 25 MPa.
C23C 18/12 - Revêtement chimique par décomposition soit de composés liquides, soit de solutions des composés constituant le revêtement, ne laissant pas de produits de réaction du matériau de la surface dans le revêtementDépôt par contact par décomposition thermique caractérisée par le dépôt sur des matériaux inorganiques, autres que des matériaux métalliques
11.
METHOD FOR SIMULATING THE FLOW OF A FLUID IN CONTACT WITH A MOVING SOLID
The invention relates to a method for simulating a fluid in contact with a moving solid modelled by a series of fixed positions (XA), the method comprising the steps of: —generating (E1) a fixed lattice (M1); —generating (E2) an auxiliary lattice (M2) of the solid (S) in a first position (XA) wherein each auxiliary lattice (N2) comprises a particle (P) comprising information on the volume (V2) of the auxiliary lattice (N2); —determining (E3) the position (XPA) of the particles (P) in the fixed lattice (M1); —calculating (E4, E5) the volume of the solid (V1s) and the volume fraction of the fluid (εF) in each fixed lattice (N1) based on the particles (P); —solving (E6) discretised Navier-Stokes equations using the finite volume approach applied to the volume fraction of the fluid (εF); —and, for each subsequent position (XB, XC) of the solid (S), a step (E7) of moving the particles (P) followed by the determining (E3), calculating (E4, E5) and solving (E6) steps.
G06F 30/28 - Optimisation, vérification ou simulation de l’objet conçu utilisant la dynamique des fluides, p. ex. les équations de Navier-Stokes ou la dynamique des fluides numérique [DFN]
A stator element an electrical conductor that is elongate and hollow in order to define a flow channel that allows a coolant to flow from one end of the conductor to the other. The stator element further includes a conductor designed to pass an electric current and a connection element located at one of the ends of the conductor. The connection element includes a fluid connection terminal designed to allow coolant to enter the channel or to exit from the channel, and an electrical connection terminal designed to electrically connect the conductor. The conductor and the connection element are formed of a single unitary part.
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p. ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
A turbomachine assembly includes a high-pressure compressor driven by a high-pressure shaft, a low-pressure compressor driven by a low-pressure shaft, the low-pressure shaft being driven at a lower speed than the high-pressure shaft, a first power converter driven by the high-pressure shaft, an air circulation system including a first air bleed port positioned in the high-pressure compressor and a second air bleed port placed upstream of the first air bleed port, a device that determines an operating condition of the turbomachine assembly, and a controller that sends transfer instructions to the first power converter for transferring a power from the high-pressure shaft to the low-pressure shaft or a power from the low-pressure shaft to the high-pressure shaft depending on the operating condition.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
14.
METHOD FOR MANAGING POWER TRANSITIONS BETWEEN A GENERATION MODE AND AN ASSISTANCE MODE
A method for a turbomachine having a high-pressure shaft driving a high-pressure electric machine and from which a high-pressure power taken off and a low-pressure shaft driving a low-pressure electric machine and from which a low-pressure power is taken off, the generation mode corresponding to a predetermined sharing of power between the high-pressure power and the low-pressure power and the assistance mode corresponding to a request for injection of an additional power into the high-pressure shaft or the low-pressure shaft, a method in which, to reach the requested additional power, when the high- or low-pressure power takeoff is interrupted and the high- or low-pressure electric machine respectively driving the high- or low-pressure shaft whose takeoff is interrupted enters motor mode.
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
There is provided an assembly of annular sectors of an annular multi-element acoustic component, each sector including a plurality of rows of hollow complex acoustic elements each having a shape that steadily narrows between a base and a vertex, each sector including a plurality of first rows including the same number of hollow complex elements and one or more second rows including one less hollow complex element than the first rows, each second row further including a male attachment element on one of the assembly edges and a female attachment element on the other assembly edge, the female attachment element having the same dimension as a hollow complex element along the direction of assembly.
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
G10K 11/16 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général
16.
METHOD FOR FORMING A SOUND ATTENUATION STRUCTURE PROVIDED WITH S-SHAPED CELLS
A method for forming an acoustic resonator panel for an aircraft propulsion assembly nacelle, the acoustic panel including cells with transverse internal obstacles in order to lengthen the path traveled by the sound waves. The method includes forming a perforated metal sheet, stacking a plurality of thermoplastic cellular cores and at least one perforated sheet, two successive cellular cores being separated by a perforated sheet, compacting the stack, and thermoplastic welding.
B29C 65/36 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p. ex. un "élément de soudage perdu" chauffés par induction
B21D 53/92 - Fabrication d'autres objets particuliers d'autres parties d'avions
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 3/26 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche continue dont le périmètre de la section droite a une allure particulièreProduits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche comportant des cavités ou des vides internes
B32B 15/08 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique de résine synthétique
B32B 15/18 - Produits stratifiés composés essentiellement de métal comportant du fer ou de l'acier
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
17.
VARIABLE LENGTH FIN HEAT EXCHANGER AND CORRESPONDING TURBOMACHINE
A heat exchanger for a turbomachine of an aircraft, the heat exchanger having a plurality of fins intended to be swept by a first fluid in a first direction, the fins extending in a second direction between a first panel and a second panel, being arranged in several rows in a third direction, and being arranged in a staggered manner, each row of fins being parallel and connected to one another. The heat exchanger can be annular, centered on the third direction and can have an inner cylindrical surface defining an inlet and an outer cylindrical surface defining an outlet, and the fins can have a length which decreases radially in the heat exchanger, in the first direction, between the inner cylindrical surface and the outer cylindrical surface.
F28F 3/04 - Éléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des évidements, avec des ondulations les moyens faisant partie intégrante de l'élément
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
Casing of a gas turbine engine compressor comprising openings cut in the thickness of the casing from an inner surface of the casing and arranged side by side over a circumference of the casing, characterised in that it also comprises a movable ring, formed by at least two annular portions, positioned on an outer surface of the casing opposite the openings and able to move along the circumference of the casing such as to open and close the openings of the casing to activate or deactivate a casing treatment, the movable ring comprising the same number of slots as there are openings in the casing.
F04D 29/56 - Moyens de guidage du fluide, p. ex. diffuseurs réglables
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F04D 25/06 - Ensembles comprenant des pompes et leurs moyens d'entraînement la pompe étant entraînée par l'électricité
F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
F04D 29/54 - Moyens de guidage du fluide, p. ex. diffuseurs
19.
Blade or vane with a root made by crossing weft yarns
A method for manufacturing a propeller blade or vane made of composite material, includes making a single-piece fibrous blank by three-dimensional weaving between warp yarns and weft yarns, including an airfoil part and a root part including a non-interlinking, the root part including at least one changing sub-area in which the number of weft yarns crossing on either side of the non-interlinking increases gradually from the airfoil part to the free end of the root part, shaping the fibrous blank to obtain a fibrous preform, densifying the preform by a matrix to obtain a propeller blade or vane made of composite material.
A method and a device for classifying and localizing an object in an image sequence. The proposed method includes obtaining a sequence of one or more images captured by a camera; and determining, by a classifier-localizer module based on the obtained image sequence a class assigned to the object, the assigned class being selected from among a list of classes; and an estimated position of the object; the classifier-localizer module being configured based on reference image sequences to minimize a multi-objective loss function representative both of an objective of classification and an objective of object localization in the reference sequences.
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
G06T 7/70 - Détermination de la position ou de l'orientation des objets ou des caméras
G06V 10/776 - ValidationÉvaluation des performances
21.
ASSEMBLY FOR AN ELECTRICALLY HYBRIDISED TURBINE ENGINE
This disclosure relates to an assembly for a gas turbine engine comprising:
a first rotary spool (222, 262, 282);
a second rotary spool (20, 220, 260, 280); and
an electrical system (4) comprising:
a bus (40);
a first generator (411);
a second generator (421);
a first converter (410);
a second converter (420); and
a control device (412, 422, 432, 4000).
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
A casting core includes a main portion made of molybdenum or a molybdenum alloy, and, at the surface of the main portion, at least two protuberances made of a refractory material, the whole of the main portion and the protuberances being covered with an anti-oxidation coating.
B22C 9/10 - NoyauxFabrication ou mise en place des noyaux
B22C 9/12 - Traitement des moules ou noyaux, p. ex. séchage, étuvage
B22D 29/00 - Extraction des pièces hors du moule, non limitée à un procédé de coulée couvert par un seul groupe principalExtraction des noyauxManipulation des lingots
23.
FIBROUS REINFORCEMENT FOR THE MANUFACTURE OF A COMPOSITE PART INTENDED TO BE ARTICULATED WITH OTHER PARTS
A fibrous preform of a core portion of a fibrous reinforcement for a composite material part, the preform having an elongate shape along a longitudinal direction and being formed by three-dimensional weaving of first yarns extending along the longitudinal direction with second yarns transverse to the first yarns, the preform including two longitudinal ends for articulation with other parts and a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area having a first volume ratio of first yarns to second yarns that is greater than one, and each longitudinal end having a second volume ratio of first yarns to second yarns that is less than the first ratio and closer to one than this first ratio.
B29C 70/22 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
A system for monitoring an aircraft assembly, the system comprising: a plurality of lubrication fittings, each lubrication fitting comprising a passive radio frequency identification component; and a grease gun comprising an radio frequency identification reader and a processor, wherein the processor is configured to: transmit a first signal to cause the radio frequency identification reader to transmit a radio frequency, RF, signal to the passive radio frequency identification components in the lubrication fittings; receive a unique identifier from the passive radio frequency identification component in the lubrication fittings; and transmit a second signal comprising the unique identifier to a digital system.
A method for automatically monitoring a plurality of rotating parts of rotating machines on the basis of a target database including a plurality of time signals from a distribution generated from each rotating part and on the basis of a source database including a plurality of time signals from a distribution S different from the distribution T generated from a source rotating part of a source rotating machine and being associated with an operating class, the monitoring being carried out by an adaptive deep learning model making it possible to adapt the source distribution to the target distribution, the deep learning module being trained by minimization of a cost function relating to Gaussian kernel functions having a parameter σ; σ being calculated in each period on the basis of the difference in distributions weighted by a constant static value estimated on the basis of a Pascal's triangle.
G06F 30/27 - Optimisation, vérification ou simulation de l’objet conçu utilisant l’apprentissage automatique, p. ex. l’intelligence artificielle, les réseaux neuronaux, les machines à support de vecteur [MSV] ou l’apprentissage d’un modèle
26.
IMPROVED HEAT EXCHANGER DEVICE FOR AN AIRCRAFT TURBOMACHINE
A device including a heat exchanger body, an upstream hot-fluid header attached to the heat exchanger body and configured to collect a first fluid at a first temperature and to feed it to the heat exchanger body, an upstream cold-fluid header attached to the heat exchanger body and configured to collect a second fluid at a second temperature lower than the first temperature and to feed it to the heat exchanger body, at least the upstream hot-fluid header including a double wall forming a peripheral cavity surrounding a main cavity configured to receive a main flow of the first fluid, the peripheral cavity being configured to receive a secondary flow of the first fluid or of the second fluid.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
INSTITUT NATIONAL POLYTECHNIQUE DE TOULOUSE (France)
UNIVERSITE PAUL SABATIER - TOULOUSE II (France)
Inventeur(s)
Azzopardi, Stéphane Joseph
Le, Thanh Long
Richardeau, Frédéric
Jouha, Wadia
Barazi, Yazan
Rouger, Nicolas
Blaquiere, Jean-Marc
Vinnac, Sébastien
Picot, Mathis
Abrégé
A device for controlling and protecting a power transistor, comprising: a nominal switching circuit for the transistor, a short-circuit detection circuit which keeps the transistor in the conducting state and detects an increase or decrease in the voltage VGS of the transistor relative to reference voltages representative of a short-circuit of the transistor; a protection circuit which discharges the gate of the transistor after the detection of a short-circuit; and a circuit for measuring and controlling the nominal switching circuit, the short-circuit detection circuit and the protection circuit.
H03K 17/0812 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension sans réaction du circuit de sortie vers le circuit de commande par des dispositions prises dans le circuit de commande
G01R 31/26 - Test de dispositifs individuels à semi-conducteurs
H03K 17/18 - Modifications pour indiquer l'état d'un commutateur
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventeur(s)
Riera, William Henri Joseph
Mondin, Gabriel Jacques Victor
Ottavy, Xavier Jean-Pierre
Abrégé
The invention relates to a stator part (20) of a turbine engine, comprising a platform (22), a blade (24, 26) extending radially relative to a central axis (A), and a fin (28) extending radially from a fin root (44) to a fin tip (46), the fin comprising a lower side (48) and an upper side (50), each point (100) of the lower side or of the upper side defining a radial axis (Ar) passing through the point, each plane (Pr) that includes the radial axis defining a section (S) of the lower side or of the upper side, an angle defined in the plane between the root profile and a tangent to the section at an intersection (104) of the section and of the root profile being less than or equal to 45 degrees, the section being located between the root profile and the tangent.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventeur(s)
Riera, William Henri Joseph
Mondin, Gabriel Jacques Victor
Ottavy, Xavier Jean-Pierre
Abrégé
The invention relates to a stator part (20) comprising a platform (22), a first blade (24), a second blade (26), and a fin (28) having a leading edge (30) and a trailing edge (32), the fin extending opposite an upper surface (124) of the first blade and a lower surface (126) of the second blade, the leading edge comprising a leading point (34) located on the platform, a tangent to the leading edge at the leading point extending between the first blade and a radial leading plane (Pa) and the leading point, and the trailing edge comprising a trailing point (36) located on the platform, a tangent to the trailing edge at the trailing point extending between the second blade and a radial trailing plane (Pf) and the trailing point.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
SAFRAN (France)
ECOLE NORMALE SUPERIEURE PARIS-SACLAY (France)
Inventeur(s)
Fragnaud, Cédric
Remacha, Clément
Roux, Stéphane
Betancur, Julian
Abrégé
The invention relates to a non-destructive inspection method based on 3D modelling of a part, comprising: using an x-ray device to acquire images of the part at various projection angles; computing projections based on the images acquired at the various projection angles; in each of multiple iterations: generating simulated projections corresponding to the computed projections, based on a reference model of an external surface of the part and on a vector μ of transformation parameters of the reference model; modifying the vector μ with a view to reducing a discrepancy between the simulated projections and the computed projections; determining a corrected model of the external surface through transformation of the reference model by way of the vector μ resulting from the iterations; determining an effective model of the part by way of the corrected model.
G01N 23/04 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et formant des images des matériaux
G01N 23/083 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p. ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et mesurant l'absorption le rayonnement consistant en rayons X
A navigation assistance device intended to be embedded in a mobile system includes a monocular camera capable to simultaneously acquire a first image of a scene with a first depth of field and one or more second images of the scene with a second depth of field smaller than the first depth of field, a depth estimator that determines a depth map of the scene from the first image of the scene and the one or more second images of the scene, and a computer that calculates a navigation trajectory from the first image of the scene and the depth map of the scene.
A matrix for a heat exchanger to exchange heat between a first fluid and a second fluid, the first fluid being for instance air and the second fluid being for instance oil. The matrix comprises: a channel for the first fluid. an array of passages for the second fluid, the passages extending in the channel. The array supports at least two cooling fins. The matrix is made by a process of additive manufacturing. The fins are inclined with respect to each other along the direction of the flow of the first fluid. The array defines rectangular corridors for the first fluid.
F28F 1/12 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire
F28D 7/16 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant espacées parallèlement
F28F 1/34 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire et s'étendant obliquement
F28F 1/38 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire et étant alternés en quinconce pour former des passages tortueux pour les fluides
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.
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
34.
System for controlling the temperature of a heat transfer fluid in a circulation loop, and temperature control method
The invention relates to a system (1) for controlling the temperature of a heat transfer fluid (F) configured to transfer heat to a fluid to be heated (Q) originating from a cryogenic tank (R), the control system (1) comprising: a loop (2) for circulating the heat transfer fluid (F), comprising an engine branch (21) and a tank branch (22); a first engine heat exchanger (41), configured to heat the heat transfer fluid (F) to a second temperature (T2) above a maximum operating temperature (Tmax); a mechanical pump (3) configured to circulate the heat transfer fluid (F) in the circulation loop (2), such that, in a second engine heat exchanger (42), a first part of the heat is transferred from the heat transfer fluid (F) to the fluid to be heated (Q) and the heat transfer fluid (F) is cooled to a third temperature (T3) below the maximum operating temperature (Tmax), before it leaves the engine enclosure (EN-M).
B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
35.
Fan blade or vane with cross-shaped or star-shaped composite root
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 span 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 preform parts being connected to one another by three-dimensional weaving. The root includes a plurality of branches. The root preform part of the fiber preform includes a plurality of branches each extending in a branch of the root.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
F01D 5/30 - Fixation des aubes au rotorPieds de pales
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
36.
METHOD FOR INJECTING A HYDROGEN-AIR MIXTURE FOR A TURBINE ENGINE BURNER
An injection method, for an injection device in a combustion chamber of an aircraft turbine engine, said injection device comprising an internal channel surrounded by an external annular channel, said channels leading into said combustion chamber of the gas turbine, the method including injecting a gaseous hydrogen/air mixture having a greater hydrogen richness level than the stoichiometric amount into said internal channel and injecting air into the external annular channel so as to produce, at the outlet of the internal channel, a first flame front resulting from rich combustion surrounded by a second flame front resulting from lean combustion.
F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
F23R 3/02 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la configuration du flux d'air ou du flux de gaz
F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
37.
METHOD FOR DETECTING AN ANOMALY IN A SYSTEM OF AN AIRCRAFT
A method for detecting an anomaly in a system of an aircraft, including obtaining a current series of measurements of one or more physical quantities of the system, during a time period when the system is in operation; —on the basis of the current series of measurements, providing, by an encoder-decoder, a current reconstructed series; and —comparing the reconstructed current series with the current series of measurements in order to obtain a current series of anomalies. The method further includes computing a current distribution function of the current series of anomalies; —computing an area separating the current distribution function from a reference distribution function; and —comparing the area with a predefined threshold.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
G06N 3/0442 - Réseaux récurrents, p. ex. réseaux de Hopfield caractérisés par la présence de mémoire ou de portes, p. ex. mémoire longue à court terme [LSTM] ou unités récurrentes à porte [GRU]
A method for manufacturing a fiber preform for a part, includes weaving a first core texture of elongate shape extending in a longitudinal direction and comprising, in cross section, a central portion having, on its opposite sides, two edges each including two non-interlinked fibrous portions, shaping the first texture which involves at least opening out the non-interlinked portions to form a positioning surface defined by the portions thus opened out and by an interleaved portion, situated between these opened-out portions, which can be formed by a prolongation of the central portion, and positioning a second belt texture over the opened-out lateral portions and the interleaved fibrous portion, the second texture forming a loop around the shaped first texture to define empty spaces for articulation to other parts.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/22 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins deux directions formant une structure bidimensionnelle
The invention relates to a conditioning system (SC) for fuel (Q), which is configured to supply an aircraft turbine engine (M) with fuel (Q) from a cryogenic tank (R), the conditioning system (SC) comprising at least one first heat exchanger (31) configured to heat the flow of fuel (Q) to a circulation temperature (Te), at least one second heat exchanger (32) configured to heat the flow of fuel (Q) to an injection temperature (Ti), a distribution valve (4) configured to divide a direct fuel flow (Q1) and a recirculated fuel flow (Q2), configured to circulate in a recirculation branch (12) so as to reheat the main fuel flow (Qp) in the first heat exchanger (31) by means of the recirculated fuel flow (Q2).
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
An aircraft landing gear assembly comprising: a ground contacting assembly (10); a main strut (8); a mounting bearing arranged for coupling the landing gear assembly to an aircraft such that the main strut supports the aircraft on the ground when the ground contacting assembly is in contact with the ground; a noise-inducing component; and a perforated sheet fairing (6a, 6b) comprising a body having a first surface and a second surface and plurality of holes (64) extending from the first surface to the second surface, each hole having an axis, wherein the perforated sheet fairing further comprises a plurality of airflow disruption elements (66) each extending towards the axis of a hole at an angle between 5° and 185° relative to the axis of the hole.
A method for monitoring a rotating machine in order to detect a fault in a bearing, the method including acquiring, from the rotating machine, a vibration signal measured by a vibration sensor; determining a first-order spectrogram by first-order cyclostationary analysis of the vibration signal using a delta transform and spectral standardisation; determining a second-order spectrogram by second-order cyclostationary analysis of the vibration signal using averaged cyclic coherence, a delta transform and spectral standardisation; and detecting a vibration signature of the fault in the bearing on the basis of the first-order spectrogram and the second-order spectrogram.
G06G 7/70 - Calculateurs analogiques pour des procédés, des systèmes ou des dispositifs spécifiques, p. ex. simulateurs de véhicules, p. ex. pour la détermination du chargement admissible de navires
G01M 13/045 - Analyse acoustique ou des vibrations
G01M 15/12 - Test des moteurs à combustion interne par contrôle des vibrations
42.
Fibrous reinforcement for the manufacture of a composite part intended to be articulated with other parts
A fibrous preform of a core portion of a fibrous reinforcement for a composite material part, the preform having an elongated shape along a longitudinal direction and being formed by first yarns extending along the longitudinal direction with second yarns transverse to the first yarns, the preform including two longitudinal ends intended for articulation with other parts and a median area located between the longitudinal ends, each longitudinal end having a thickness greater than a thickness of the median area, the median area including a stiffening segment including first non-woven yarns and each longitudinal end including a three-dimensional weave of the first yarns of this stiffening segment with second yarns.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
A Jacquard type loom intended to produce a fibrous structure by three-dimensional weaving between a plurality of warp yarns and a plurality of weft yarns extending in a horizontal direction, the loom including a reed movable between a rest position upstream of the rapier and a beat-up position of a fell of the fibrous structure in a beat-up direction parallel to the horizontal direction. The reed includes at least two stationary portions forming an angle therebetween. The reed is mounted on the loom by a positioning mechanism able to orient the reed about an axis of rotation so as to adjust an angular position of the stationary portions of the reed relative to a horizontal reference plane. The loom include vertical translation elements able to move the reed or the fell of the fibrous structure in the vertical direction.
D03D 13/00 - Tissus caractérisés par la disposition particulière des fils de chaîne ou de trame, p. ex. avec fils de trame incurvés, avec fils de chaîne discontinus, avec fils de chaîne ou de trame en diagonale
A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
A method for manufacturing a part made of composite material, includes the arrangement of a fibrous preform in a mould including an impregnation chamber, the impregnation chamber being closed by a membrane separating the impregnation chamber from a compaction chamber, the injection of an impregnation fluid into the impregnation chamber, and the injection of a compression fluid into the compaction chamber so as to apply a pressure on the membrane, the aspiration of the compression fluid present in the compaction chamber, the surface of the membrane present on the side of the compaction chamber including a plurality of grooves.
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
An aircraft landing gear assembly comprising: a ground contacting assembly; a main strut; a mounting bearing arranged for coupling the landing gear assembly to an aircraft such that the main strut supports the aircraft on the ground when the ground contacting assembly is in contact with the ground; a noise-inducing component which, in use, with the landing gear assembly deployed, has a front region and a back region separated by a pair of side regions, such that flight motion of the aircraft causes airflow to encounter the front region followed by the side regions, followed by the back region; and a first flow deflector mounted adjacent to and spaced from a first side region, the first flow deflector having a leading edge and a trailing edge separated by first and second sides and being shaped with a curved profile between the leading edge and trailing edge that is curved towards the back region of the noise-inducing component so as to redirect airflow adjacent the first side region at an angle between 30 to 90 degrees relative to a free stream flow.
An aircraft landing gear system comprising: a plurality of sensors (26A-D) arranged to detect a known acoustic input signal (28) within one or more components of an aircraft landing gear structure (14); and a processor (52) configured to: receive data from the plurality of sensors (26A-D), the data corresponding to the detected known acoustic input signal (28); compare the data to a mapping function (74), wherein the mapping function (74) defines a relationship between a detected acoustic signal (28) and a known load on the one or more components of the aircraft landing gear structure (14); and estimate the load experienced by the one or more components of the aircraft landing gear structure (14) based on the data and the mapping function (74).
The invention relates to a method for producing a part made of a nickel-based alloy with a Y/Y′ microstructure in which at least one hot-forging step is performed, which method is characterised in that the temperature at which the part is heated in the forging step is maintained within a temperature range lower than the abnormal grain growth temperature range of the alloy, the hot-forging temperature being maintained at a temperature lower than the temperature of the part, the hot-forging temperature being such that the difference compared with the temperature at which the part is heated is less than 250° C. and preferably less than 150° C.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
B21K 1/32 - Fabrication d'éléments de machines de rouesFabrication d'éléments de machines de disques de disques, p. ex. de roues pleines
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
49.
ROTATIONALLY SYMMETRICAL PART MADE OF COMPOSITE MATERIAL HAVING AN IMPROVED HOLDING CAPACITY
A method for manufacturing a composite material revolution part for a propulsion assembly includes making a fibrous preform on a mandrel having a profile corresponding to that of the part to be manufactured, and densifying the fibrous preform by a matrix. Making the fibrous preform includes forming a strip-shaped fibrous blank including at least one layer of continuous fibers and at least one layer of discontinuous fibers, the fibrous blank being shaped on the mandrel, the layer of continuous fibers of the fibrous blank extending at least over a complete turn around the mandrel.
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
50.
METHOD AND SYSTEM FOR DETERMINING THE PRESSURE OF AN AIRCRAFT TIRE
COMPAGNIE GENERALE DES ETABLISSEMENTS MICHELIN (France)
SAFRAN (France)
SAFRAN ELECTRONICS & DEFENSE (France)
SAFRAN LANDING SYSTEMS (France)
Inventeur(s)
Neba, Eric Carin
Abrégé
A method and a system for determining the temperature in a mounted aircraft tyre is characterized in that it has two temperature sensors installed inside the tire.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
39 - Services de transport, emballage et entreposage; organisation de voyages
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Appareils, instruments et équipements électriques et électroniques pour la navigation, le guidage, le téléguidage, le balisage, la localisation, le pilotage automatique, la stabilisation de véhicules aériens; systèmes de commande de vol pour aéronefs; calculateurs avioniques multifonctions; instruments et équipements de collecte de données pour l'aide à la maintenance (systèmes de gestion des données de vol); appareils, instruments et équipements d'analyse de données techniques et scientifiques (station d'analyses au sol); dispositifs de calculs pour les drones et les aéronefs; calculateurs de mission; simulateurs pour la direction et le contrôle des drones; appareils, instruments et équipements électroniques d'acquisition et de traitements de données et périphériques; supports d'enregistrement et de stockage électroniques pour le positionnement, le guidage et la transmission de données et de services par satellite; programmes d'ordinateurs enregistrés; logiciels pour l'exploitation et la commande de drones; logiciels de simulation et planification de vol; transmetteurs de signaux électroniques; émetteurs (télécommunication); composants électroniques, supports électroniques de banques de données de navigation et de positionnement, appareils d'analyse et de commande à distance mis à disposition sur des plateformes au sol pour l'exploitation de drones et d'aéronefs avec ou sans équipage; équipement d'essai en vol; appareils et instruments pour la télécommande et le guidage à distance de drones et autres aéronefs, à savoir les interfaces utilisateur de télécommande, les dispositifs de télémétrie de données, les émetteurs et récepteurs radio, les ordinateurs, les récepteurs du système de positionnement global et les instruments électroniques de navigation; batteries rechargeables pour drones; caméras et composants de caméras pour drones.
(2) Drones; drones de transport; véhicules aériens de transport de charge; transporteurs aériens par drones pour la manutention de charges; parties structurelles de drones. (1) Transport aérien de chargement; location de drones de livraison et de transport aérien de chargement; services de planification de vol; organisation et supervision de vols; services d'informations sur les vols et sur la navigation des drones et aéronefs avec ou sans équipage; fourniture de plans de vol; services de navigation par système de localisation mondial pour drones et aéronefs avec ou sans équipage; planification d'itinéraires pour drones et autres véhicules aériens [services de navigation]; navigation pour drones (positionnement et définition d'itinéraires et de trajectoires); services de remorquage de drones; consultation en matière de transport aérien de chargement; services de pilotage de drones; services d'assistance au pilote et au télépilote pour la compréhension et l'analyse du contexte et de la situation lors d'un vol de drone.
(2) Services d'assistance technique, à savoir fourniture de conseils techniques en matière de véhicules aériens sans pilote (UAV) ou drones; assistance technique pour véhicules aériens sans pilote (UAV) ou drones; personnalisation de matériel informatique et logiciels pour véhicules aériens sans pilote (UAV) ou drones, conception et développement de drones et systèmes de navigation pour drones; services scientifiques et technologiques ainsi que services de recherches mécaniques, aéronautiques et services d'analyses relatifs aux drones; services d'analyses de systèmes et de données informatiques et techniques provenant des drones; conception, élaboration, mise à jour (pour des tiers), installation, gestion et développement d'ordinateurs et de logiciels (programmes enregistrés) embarqués ou non et pour plateforme de contrôle de drones; tests, analyses et contrôles de signaux de navigation, de données et d'informations provenant des drones; services de simulations de vols; réalisation d'essais techniques et tests de vols, à savoir contrôle de qualité de drones; services d'ingénierie dronique et avionique; services de cartographie (géographie); logiciels en tant que service [SaaS] destinés aux drones et aéronefs avec ou sans équipage; mise à jour et maintenance de logiciels destinés aux drones et aéronefs avec ou sans équipage; plateforme informatique en tant que service [PaaS] destinée à la navigation des drones et des aéronefs avec ou sans équipage; analyse et gestion en matière de performance et de conformité (audit de qualité).
An aircraft landing gear assembly comprising: an elongate bogie beam including a bearing via which the bogie beam is arranged to be movably mounted to an aircraft landing gear main strut, first and second end regions, a first longitudinal axis (L) extending between the bearing and the first end region and a second longitudinal axis (L) extending between the bearing and the second end region; a first axle mounted at a first end region of the bogie beam, the first axle defining a first wheel mounting portion on a first side of the bogie beam for supporting a first wheel assembly and a second wheel mounting portion on a second side of the bogie beam for supporting a second wheel assembly; a second axle mounted at a second end region of the bogie beam, with the bearing between the first and second end regions, the second axle defining a third wheel mounting portion on the first side of the bogie beam for supporting a third wheel assembly and a fourth wheel mounting portion on the second side of the bogie beam for supporting a fourth wheel assembly, wherein the bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about the respective longitudinal axis of the bogie beam by an amount which is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.
B64C 25/10 - Atterrisseurs non fixes, p. ex. largables escamotables, repliables ou ayant un mouvement apparenté
B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p. ex. bogies à roues multiples
53.
REINFORCEMENT FOR A COMPOSITE BLADE OF A TURBOMACHINE, COMPRISING A MIXTURE OF FIBER CUTS AND A TACKIFIER
The present invention concerns a reinforcement for a blade of a turbomachine, the blade comprising a first outer skin and a second outer skin which are made of composite material each comprising an inner end portion spaced apart from each other in such a way as to delimit therebetween an inner cavity of the blade that opens into an opening at an inner end of the blade, the inner end being radially opposite the outer end, wherein the reinforcement is adapted to be arranged in the inner cavity in such a way as to close the opening, and wherein the reinforcement comprises a mixture of cuts of at least one fiber and a tackifier, the cuts having lengths comprised between 1 mm and 15 mm, the tackifier comprising an epoxy resin solubilized in a solvent.
Method for the manufacture of at least one skin, in particular of an acoustic panel for an aeronautical engine, including the laying of a thermoplastic material on a surface of a lay-up tooling, via a depositing tool configured to exert a pressure on the thermoplastic material and to heat the latter while it is being laid, wherein the lay-up tooling includes a thermal regulation device configured to locally heat the surface of the lay-up tooling.
B29C 35/02 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation
B29C 35/04 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation avec des liquides, des gaz ou de la vapeur d'eau
B29C 35/08 - Chauffage ou durcissement, p. ex. réticulation ou vulcanisation utilisant l'énergie ondulatoire ou un rayonnement corpusculaire
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29K 71/00 - Utilisation de polyéthers comme matière de moulage
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
A method for monitoring the state of health of an aircraft turbomachine for a flight of interest VI, based on a setpoint vector XSC of input parameters relative to the turbomachine of interest in steady-state regime, the method using a database of values of input and output parameters in transient regime for a plurality of flights including the flight of interest, and values of input and output parameters in steady-state regime for a plurality of flights with the exception of the flight of interest. The transient data are used to estimate a transient prediction model f, at least one portion of the transient prediction model f then being used, associated with the steady-state data, in order to estimate a steady-state prediction model H of the turbomachine of interest for the flight of interest and to determine the behaviour, in steady-state regime, of the turbomachine for the flight of interest.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
56.
REINFORCEMENT FOR A COMPOSITE BLADE OF A TURBOMACHINE, COMPRISING A STACK OF PLIES
The present application relates to a reinforcement (6) for a blade (1) of a turbomachine (100), the blade (1) comprising a first outer skin (2) and a second outer skin (3) which are made of composite material and each comprise an inner end portion (21, 31) spaced apart from each other in such a way as to delimit therebetween an inner cavity (4) of the blade (1) that opens into an opening (5), wherein the reinforcement (6) is adapted to be arranged in the inner cavity (4) in such a way as to close the opening (5), and wherein the reinforcement (6) comprises a stack of plies (61) that are superposed along a stacking direction (De) corresponding to a thickness direction (Pe) of the plies (61), at least two plies (61) having different lengths (Pl) and/or widths (PL) such that the reinforcement (6) has a profile of variable dimensions.
ONERA - OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventeur(s)
Rouffie, Anne-Laure
Franchet, Jean-Michel Patrick Maurice
Menou, Edern
Locq, Didier
Abrégé
A nickel-based superalloy, includes, in percent by weight of the total composition Al 2.5-3.8, Co 7.9-16.9, Cr 9.7-13.1, Mo 2.6-4.1, Nb 0-0.41, Ta 0-1.9, Ti 4.4-6.4, W 1.9-4.2, B 0.010-0.030, C 0.010-0.040, Hf 0.20-0.40, Zr 0.040-0.070, the remainder being Ni together with inevitable impurities.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22F 1/00 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
58.
Electrical system for an aircraft equipped with a motor
An electrical system for an aircraft includes first and second buses, first and second electric generators, and first and second AC-to-DC converters. The first bus is connected to an AC network. The second bus is connected to a DC network of the aircraft. The first electric generator is connected to the first bus and a first rotary spool of an engine of the aircraft to exchange mechanical and/or electrical power. The first AC-to-DC converter is connected to the first and second buses. The second electric generator is connected to a second rotary spool of the engine of the aircraft. The second AC-to-DC converter connected to the second electric generator and to the second bus. One or more of the converters operates in a forced mode providing regulation of the electrical power of one or more buses, and/or a free mode providing regulation of a voltage of the second bus.
H02P 9/30 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie par variation du champ utilisant des tubes à décharge ou des dispositifs à semi-conducteurs utilisant des dispositifs à semi-conducteurs
H02P 101/25 - Adaptation particulière des dispositions pour la commande de génératrices pour moteurs à combustion
H02P 101/30 - Adaptation particulière des dispositions pour la commande de génératrices pour aéronefs
H02P 103/20 - Dispositions pour la commande caractérisées par le type de génératrice du type synchrone
59.
DETECTING AN ELECTRIC ARC BY MEANS OF A BRAGG GRATING
An electrical distribution route for an aircraft includes electrical cables and electrical connection interface members, and a diagnostic and detection device for diagnosing and detecting an arc fault in the electrical distribution route. The diagnostic and detection device includes an optical fiber laid along the entire distribution route and having at least one Bragg grating at each connection interface member, an optical reflectometer coupled to an upstream end of the optical fiber, and an acquisition central processing unit configured to detect and locate one or more arc faults over a connection interface member by comparing the current spectral signature with the reference spectral signature of the optical fiber.
G01R 31/08 - Localisation de défauts dans les câbles, les lignes de transmission ou les réseaux
G01D 5/353 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens optiques, c.-à-d. utilisant de la lumière infrarouge, visible ou ultraviolette avec atténuation ou obturation complète ou partielle des rayons lumineux les rayons lumineux étant détectés par des cellules photo-électriques en modifiant les caractéristiques de transmission d'une fibre optique
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
G01R 31/52 - Test pour déceler la présence de courts-circuits, de fuites de courant ou de défauts à la terre
An aircraft landing gear assembly comprising a first structural member coupled to a second structural member via a joint, the joint comprising a bearing, the bearing comprising a tubular body formed from: a metal matrix composite (MMC) comprising a metal, a carbide compound and tungsten disulphide.
F16C 17/02 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges radiales uniquement
F16C 17/10 - Paliers à contact lisse pour mouvement de rotation exclusivement à la fois pour charges radiales et axiales
C22C 32/00 - Alliages non ferreux contenant entre 5 et 50% en poids d'oxydes, de carbures, de borures, de nitrures, de siliciures ou d'autres composés métalliques, p. ex. oxynitrures, sulfures, qu'ils soient soient ajoutés comme tels ou formés in situ
61.
METHOD FOR MANUFACTURING A PART MADE OF COMPOSITE MATERIAL
A method for manufacturing a part made of composite material includes three-dimensionally weaving a structure having a longitudinal axis (A). The method further includes the step of braiding of at least one layer of braiding threads at at least one predetermined angle relative to the longitudinal axis around the woven structure.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
An electrically interconnecting member configured to electrically join a printed circuit board belonging to a mechanical part to a piece of electrical equipment. The printed circuit board comprising output tracks. The electrically interconnecting member comprising: a contact surface configured to be fastened to the mechanical part, a free surface opposite the contact surface, input terminals placed on the contact surface and configured to be superposed on the output tracks of the printed circuit board, and output interfaces placed on the free surface at distance from the input terminals and configured to be connected to the piece of electrical equipment, at least one input terminal comprising a cavity configured to receive a conductive adhesive so as to connect together the input terminal and the output terminal when they are superposed.
The invention relates to a nickel-based alloy powder, that comprises in weight percentages, 14.00 to 15.25% of chromium, 14.25 to 15.75% of cobalt, 4.00 to 4.60% of aluminium, 0 to 0.50% of iron, 0 to 0.15% of manganese, 3.00 to 3.70% of titanium, 3.90 to 4.50% of molybdenum, 0 to 0.015% of sulphur, 0 to 0.06% of zirconium, 0.012 to 0.020% of boron, 0 to 0.20% of silicon, 0 to 0.10% of copper, 0 to 150 ppm of carbon, 0 to 0.5 ppm of bismuth, 0 to 5 ppm of lead, 0 to 1000 ppm of platinum, 0 to 1000 ppm of palladium, 0 to 50 ppm of hydrogen, 0 to 5 ppm of silver, 0 to 120 ppm of nitrogen, 0 to 1000 ppm of rhenium, 0 to 410 ppm of oxygen and 0 to 500 ppm of inevitable impurities, the rest being made up of nickel, and has a particle size D10 between 3 and 10 μm, a particle size D90 between 20 and 40 μm and a particle size D50 between 10 and 20 μm, the values of the particle sizes D10, D50 and D90 having been measured by laser diffraction according to standard ISO 13322-2. The invention also relates to a method for manufacturing a part using said powder and a resulting part.
B22F 1/10 - Poudres métalliques contenant des agents lubrifiants ou liantsPoudres métalliques contenant des matières organiques
B22F 3/22 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet pour la fabrication de pièces par coulée en moule poreux ou absorbant, c.-à-d. par coulée d'une suspension de poudre métallique dans un moule poreux, d'une façon analogue au coulage de la barbotine
B22F 3/24 - Traitement ultérieur des pièces ou objets
64.
NAVIGATION ASSISTANCE METHOD AND DEVICE BASED ON A KALMAN FILTER
Association Pour la Recherche et le Developpement des Methods et Processus Industriels-Armines (France)
Inventeur(s)
Barrau, Axel
Parellier, Colin
Bonnabel, Silvère
Abrégé
Method for monitoring the navigation of a vehicle for the implementation of a navigation maneuver: the method including the steps of: estimating a magnitude by a Kalman filter from parameters, a digital model of the vehicle in its environment, and at least one measurement made by at least one sensor and associated with an uncertainty on this measurement, the magnitude serving to implement the navigation maneuver; determining at least one partial derivative value of the magnitude with respect to the at least one measurement; obtaining at least one criticality value of the at least one measurement for the estimation, from the at least one partial derivative.
G01C 21/16 - NavigationInstruments de navigation non prévus dans les groupes en utilisant des mesures de la vitesse ou de l'accélération exécutées à bord de l'objet navigantNavigation à l'estime en intégrant l'accélération ou la vitesse, c.-à-d. navigation par inertie
G06F 7/544 - Méthodes ou dispositions pour effectuer des calculs en utilisant exclusivement une représentation numérique codée, p. ex. en utilisant une représentation binaire, ternaire, décimale utilisant des dispositifs n'établissant pas de contact, p. ex. tube, dispositif à l'état solideMéthodes ou dispositions pour effectuer des calculs en utilisant exclusivement une représentation numérique codée, p. ex. en utilisant une représentation binaire, ternaire, décimale utilisant des dispositifs non spécifiés pour l'évaluation de fonctions par calcul
65.
METHOD FOR MONITORING THE ENGINE SPEED OF AN AIRCRAFT
INSTITUT NATIONAL DES SCIENCES APPLIQUÉES LYON : (France)
SAFRAN (France)
Inventeur(s)
Hawwari, Yasmine
Abboud, Dany
Marnissi, Yosra
El Badaoui, Mohammed
Antoni, Jérôme
Andre, Hugo
Abrégé
A method for monitoring the engine speed of a rotating machine, includes constructing a raw spectrogram from a vibratory signal; denoising the spectrogram to obtain an equalised spectrogram, the denoising including a first sub-procedure of determining a foot of the spectrogram, the foot of the spectrum being a set of random harmonic components contained in the raw spectrogram, the first sub-procedure including a first sub-sub-procedure of constructing a regression function robust to the peaks of the spectrogram, the regression function being applied to a logarithm of the spectrogram or to the spectrogram; a second sub-sub-procedure of determining the foot of the spectrum from the regression function; a second sub-procedure of determining the equalised spectrogram from the foot of the spectrogram; separating sources in the equalised spectrogram by determining an estimator of the frequencies of interest; determining an instantaneous speed of rotation of the engine speed from the estimator.
09 - Appareils et instruments scientifiques et électriques
12 - Véhicules; appareils de locomotion par terre, par air ou par eau; parties de véhicules
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Appareils, équipements et instruments électriques, électroniques et numériques pour la navigation, le guidage, le pilotage, la stabilisation, la localisation de véhicules aériens, terrestres, maritimes et spatiaux; gyromètres; équipements et appareils gyroscopiques et accélérométriques; systèmes de navigation inertielle et hybride; casques de pilotage et équipements de visualisation pour applications civiles et militaires; équipements et bases de données pour la préparation, le suivi et la restitution des missions de véhicules terrestres, aériens et maritimes; appareils de cartographie numérique; calculateurs de mission; appareils, instruments et dispositifs électriques et électroniques pour l'aéronautique; systèmes d'aide à la maintenance (ACMS); systèmes de commandes du cockpit; actionneurs de commandes de frein et d'inverseur de poussée; systèmes de contrôle de vol automatique d'aéronefs; calculateurs de commandes de vol; centrales inertielles d'attitude et de cap; appareils, instruments et équipements d'analyse de données techniques et scientifiques (station d'analyses au sol); appareils, équipements et instruments optiques pour applications scientifiques, la navigation, le guidage, le pilotage, la stabilisation de véhicules aériens, terrestres, maritimes et spatiaux; caméras infrarouges; caméras vidéo; équipements et appareils de détection optique ou infrarouge; équipements et appareils de conduite de tir; imageurs thermiques; systèmes d'observation; systèmes de veille et de poursuite infrarouge; lunettes de visées, télescope, longue vues; viseurs optiques; appareils, équipements et instruments de navigation, d'observation et de contrôle pour véhicules sans pilote à usage civil et militaire; systèmes d'observation et de reconnaissance; systèmes de transmissions et de communication sécurisées; terminaux de télécommunication et de chiffrement; réseaux sécurisés; appareils, équipements et instruments électroniques pour fantassins et personnels de sécurité; systèmes de surveillance jour/nuit; jumelles pour vision jour/nuit; batteries, accumulateurs électriques; systèmes de surveillance aéroporté; plateforme optronique gyrostabilisée et orientable; appareils et équipements pour l'acquisition, la compression, la transmission, l'analyse et la restitution d'images satellites et de photographies aériennes; systèmes de transmission d'images par liaison radio numérique; optique spatiale; optique de reconnaissance aérienne; métrologie optique; parachutes et systèmes de parachutes.
(2) Avions sans pilote, drones, véhicules aériens; planches de bord; manches de pilotage avec manette intégrée. (1) Services d'installation, de réparation et de maintenance d'équipements électroniques de véhicules terrestres, maritimes et aériens; maintenance et réparation d'équipements aéronautiques; installation, entretien et réparation d'appareils et instruments d'astronomie terrestre, d'appareils et instruments optoélectroniques pour l'industrie des lasers, des semi-conducteurs et de la défense et notamment de télescopes, miroirs, objectifs.
(2) Conception (élaboration) de logiciels et de matériel informatique; développement et conception (élaboration) de logiciels pour systèmes de navigation (GPS et ou par satellite); développement et conception de logiciels pour systèmes d'information en matière de défense; conversion de données et de programmes informatiques; conception, organisation, mise à disposition, maintenance de logiciels et de composants logiciels et fourniture en ligne de logiciels; recherche technique, scientifique et industrielle; ingénierie; recherche et développement (travaux d'ingénieurs) dans le domaine aéronautique, nautique et de la défense; analyse de données techniques; conseils techniques dans le domaine aéronautique et de la défense (travaux d'ingénieurs); service d'ingénierie opérationnelle pour compagnies aériennes; rassemblement, systématisation et stockage de données.
67.
Heating turbomachine for a fuel-conditioning system configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank
A heating turbomachine for a fuel-conditioning system, which is configured to supply an aircraft turboshaft engine with fuel from a cryogenic tank. The heating turbomachine comprising: compressor; a turbine; a combustion chamber which is configured to discharge a flow of exhaust air loaded with heat energy and to rotate the turbine; at least one fluid circuit in which a heat-transfer fluid circulates in the downstream direction; and at least one post-combustion heat exchanger which is mounted in the fluid circuit and is configured to extract heat energy from the exhaust air chamber flow between the combustion and the turbine.
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
68.
Method for attaching a part to a carrier by transfer of an adhesive film
A method for transferring an adhesive onto a part intended to be glued on a carrier, the adhesive being in the form of a double-sided film including a separator on each face, the part including an internal concave portion that does not enable uniform application of the adhesive film once the separators have been removed. The method includes attaching the adhesive film to a punch that matches the shape of the part within a range that approximately corresponds to the thickness of the adhesive film; removing the separator from the side of the adhesive film that is to be attached to the part; setting the part on the punch covered with the adhesive film that has had its separator removed; and transferring the adhesive film onto the part by creating a vacuum between the part and the punch by means of a vacuum device.
B29C 63/16 - Garnissage ou gainage, c.-à-d. application de couches ou de gainages préformés en matière plastiqueAppareils à cet effet avec des matières sous forme de feuilles ou de nappes appliquées au moyen d'un sac ou d'une membrane en caoutchouc
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B29C 65/50 - Assemblage d'éléments préformésAppareils à cet effet en utilisant des adhésifs utilisant des rubans adhésifs
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
69.
Method for three-dimensional weaving of a fibrous structure with orientation of weft columns in a deployment portion and resulting fibrous structure
In a method for three-dimensional weaving of a fibrous structure between layers of warp yarns and layers of weft yarns, the weft yarns are woven in a plurality of columns spaced apart from one another in a longitudinal direction. The method includes weaving deployment portions in the fibrous structure that is interwoven with an adjacent portion, the weft yarns of the weft yarn columns of the adjacent portion being juxtaposed in a first stacking direction perpendicular to the longitudinal direction. During the process of weaving the deployment portions, the weft yarns of each weft yarn column are positioned against the fell of the fibrous structure in stacking directions that are different from the first stacking direction.
B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
D03D 1/00 - Tissus conçus pour faire des articles particuliers
D03D 13/00 - Tissus caractérisés par la disposition particulière des fils de chaîne ou de trame, p. ex. avec fils de trame incurvés, avec fils de chaîne discontinus, avec fils de chaîne ou de trame en diagonale
D03D 49/60 - Structure ou fonctionnement du battant
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE LORRAINE (France)
OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventeur(s)
Menou, Edern
Delfosse, Jérome
Millet, Yvon
Abrégé
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.
A gantry crane and associated method of erection, the gantry including a frame having at least three first members; a longitudinal rail supported by the frame; and at least three second members extending between a first end portion and an opposite second end portion. Each second member can be connected to the frame by means for rigid connection and continuous rotational movement of the second member relative to the frame between a first position in which the second member forms an angle of less than 90° with the first plane and a second position in which the second member is substantially perpendicular to the first plane.
B66C 17/00 - Ponts roulants à chariot transbordeur comportant une ou plusieurs poutres principales sensiblement horizontales dont les extrémités reposent directement sur des roues ou des rouleaux se déplaçant sur une voie soutenue par des supports espacés
B66C 23/78 - Appuis, p. ex. des longerons, pour grues mobiles
72.
ALLOY POWDER, METHOD FOR MANUFACTURING A PART BASED ON THIS ALLOY, AND PART THUS OBTAINED
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.
B22F 3/22 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittageAppareils spécialement adaptés à cet effet pour la fabrication de pièces par coulée en moule poreux ou absorbant, c.-à-d. par coulée d'une suspension de poudre métallique dans un moule poreux, d'une façon analogue au coulage de la barbotine
B22F 1/107 - Poudres métalliques contenant des agents lubrifiants ou liantsPoudres métalliques contenant des matières organiques contenant des matériaux organiques comportant des solvants, p. ex. pour la coulée en moule poreux ou absorbant
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.
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.
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.
G06V 10/75 - Organisation de procédés de l’appariement, p. ex. comparaisons simultanées ou séquentielles des caractéristiques d’images ou de vidéosApproches-approximative-fine, p. ex. approches multi-échellesAppariement de motifs d’image ou de vidéoMesures de proximité dans les espaces de caractéristiques utilisant l’analyse de contexteSélection des dictionnaires
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
76.
METHOD FOR MAKING A THIN-WALLED ACOUSTIC COMPONENT
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.
B29C 51/00 - Façonnage par thermoformage, p. ex. façonnage de feuilles dans des moules en deux parties ou par emboutissage profondAppareils à cet effet
B29C 51/26 - Éléments constitutifs, détails ou accessoiresOpérations auxiliaires
An aircraft landing gear assembly including a first structural member; a second structural member pivotally coupled to the first structural member to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly including an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point.
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.
B29C 70/24 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/86 - Incorporation dans des couches de renforcement imprégnées cohérentes
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
79.
Propeller blade or airfoil with wound composite root
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.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventeur(s)
Cavarroc, Marjorie Christine
Poulon, Angéline Nadine Jeanne
Mauvy, Fabrice Claude Michel
Achille, Aurélie Corinne
Michau, Dominique Paul Abel
Fourcade, Sébastien
Abrégé
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.
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
H01M 8/1246 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé caractérisés par le procédé de fabrication ou par le matériau de l’électrolyte l'électrolyte étant constitué d’oxydes
An aircraft landing gear shock absorber strut (50) comprising: an outer cylinder (26) having an inner surface defining a cylinder bore extending into the outer cylinder from a first axial face of the outer cylinder, the cylinder bore defining an oleo-pneumatic chamber containing a damping liquid and a gas which can mix within the cylinder bore; a sliding tube (28) including a first end portion movably mounted within the cylinder bore so as to be movable along the cylinder bore between a compressed position, in which a second end portion of the sliding tube disposed outside of the bore is relatively close to the first axial face of the outer cylinder, and an extended position, in which the second end portion of the sliding tube is relatively far from the first axial face of the outer cylinder, the sliding tube including a tube bore extending into the sliding tube from the first end portion, the tube bore being arranged in fluid communication with the cylinder bore to exchange the damping liquid with the cylinder bore; an elongate metering pin (34) having a longitudinal axis and including an axial channel for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position; and a flow restricting plate (52) including: a first portion (52a) provided with a first damping orifice (DO) in which the metering pin is located and through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions to vary the free space cross sectional area of the first damping orifice to control an axial flow of the damping liquid (J) moving from the tube bore to the cylinder bore as the sliding tube moves from the extended position towards the compressed position; and a second portion (52b) provided with a second damping orifice (DO2) for passage of damping liquid as the sliding tube moves from the extended position towards the compressed position to define a second flow of the damping liquid (J2), wherein the second damping orifice is orientated to direct the second flow of damping liquid towards the axial channel of the metering pin to disrupt the axial flow of damping liquid.
F16F 9/06 - Ressorts, amortisseurs de vibrations, amortisseurs de chocs ou amortisseurs de mouvement de structure similaire, utilisant un fluide ou moyen équivalent comme agent d'amortissement utilisant à la fois un gaz et un liquide
F16F 9/342 - Passages d'étranglement fonctionnant avec pointeau de jauge
F16F 9/48 - Dispositions permettant différents effets d'amortissement à différents points de la course
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
INSTITUT POLYTECHNIQUE DE BORDEAUX (France)
Inventeur(s)
Cavarroc, Marjorie Christine
Mauvy, Fabrice Claude Michel
Poulon, Angéline Nadine Jeanne
Achille, Aurélie Corinne
Michau, Dominique Paul Abel
Fourcade, Sébastien
Abrégé
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.
An attachment assembly for an aircraft strut mounting joint. The attachment assembly includes a tubular structure having a central axis and at least one open end. The attachment assembly further includes at least one mounting pin arranged at least partially within the at least one open end of the tubular structure and moveable along the central axis between a retracted position and an extended position. In the extended position, a portion of the at least one mounting pin protrudes for engagement with a lug and in the retracted position the at least one mounting pin is withdrawn for disengagement with the lug. The attachment assembly further includes a retraction mechanism arranged to convert a rotary input motion into linear motion of the at least one mounting pin along the central axis to drive the at least one mounting pin between the extended position and the retracted position.
A drive circuit for a plurality of piezo-actuated hydraulic pumps for an aircraft, and a hydraulic pump system implementing the same. The drive circuit includes a voltage boost stage that receives a DC input supply voltage and delivers an increased DC output voltage to a high voltage, HV, link point; a plurality of inverter stages coupled in parallel at the HV link point that receive DC voltage from the HV link point and generate an oscillating output voltage for driving a respective piezo-actuated pump; and a control system that controls the output voltage and phase of the inverter stages to drive the plurality of piezo-actuated pumps out of phase. The control system measures the power consumption of each piezo-actuated pump and regulates the output voltage of at least one of the inverter stages to balance the power consumption of each piezo-actuated pump.
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.
B32B 37/14 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse
B32B 37/06 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par le procédé de chauffage
B32B 37/10 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la technique de pressage, p. ex. faisant usage de l'action directe du vide ou d'un fluide sous pression
B32B 41/00 - Dispositions pour le contrôle ou la commande des procédés de stratificationDispositions de sécurité
86.
PROCÉDÉ DE FABRICATION D'UNE PRÉFORME FIBREUSE POUR PIÈCE COMPOSITE DESTINÉE À ÊTRE ARTICULÉE AVEC D'AUTRES PIÈCES
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.
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.
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.
B22D 17/24 - Accessoires pour la mise en place et le maintien des noyaux ou parties rapportées
B22D 25/02 - Coulée particulière caractérisée par la nature du produit par sa formeCoulée particulière caractérisée par la nature du produit d'œuvres d'art
90.
SYSTEM AND METHOD FOR CONDITIONING FUEL FOR AN AIR-BREATHING HYDROGEN ENGINE
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.
An aircraft landing gear assembly (36) comprising a wheel and brake assembly and a shock absorbing strut (37), the strut including a mounting bearing for movably coupling the aircraft landing gear assembly to an aircraft for movement between a stowed condition for flight and a deployed condition for take-off and landing, the aircraft landing gear assembly further comprising: a noise-inducing region (37); a first perforated sheet fairing (1n); and a second perforated sheet fairing (3n) arranged downstream of the first perforated sheet fairing when the landing gear is in the deployed condition.
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.
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29C 70/86 - Incorporation dans des couches de renforcement imprégnées cohérentes
B29D 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B29K 71/00 - Utilisation de polyéthers comme matière de moulage
B29K 77/00 - Utilisation de polyamides, p. ex. polyesteramides, comme matière de moulage
B29K 79/00 - Utilisation comme matière de moulage d'autres polymères contenant dans la chaîne principale uniquement de l'azote avec ou sans oxygène ou carbone
94.
SYSTEM FOR COOLING A LIQUID FOR LUBRICATING AN AIRCRAFT TURBOMACHINE
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.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
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.
H02P 9/10 - Commande s'exerçant sur le circuit d'excitation de la génératrice afin de réduire les effets nuisibles de surcharges ou de phénomènes transitoires, p. ex. application, suppression ou changement brutal de la charge
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
H02P 101/25 - Adaptation particulière des dispositions pour la commande de génératrices pour moteurs à combustion
H02P 101/30 - Adaptation particulière des dispositions pour la commande de génératrices pour aéronefs
96.
Method for producing a bladed component for an aircraft turbine engine
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.
09 - Appareils et instruments scientifiques et électriques
35 - Publicité; Affaires commerciales
38 - Services de télécommunications
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et 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.
09 - Appareils et instruments scientifiques et électriques
35 - Publicité; Affaires commerciales
38 - Services de télécommunications
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus for sound, image or data recording, transmission, reproduction or processing; equipment for data processing and computers; downloadable software for monitoring and tracking the location of goods and people, mapping geographic areas, operating system, communication, electronic position, location, and computer peripheral devices; scientific and research apparatus and instruments based on automatic analysis of geospatial information, namely, downloadable software and algorithms; data processing equipment; data processing equipment based on the automatic analysis of geospatial information; downloadable artificial intelligence software for analyzing high-resolution imagery, full motion video and acoustic signals; downloadable artificial intelligence software for automatic processing of satellite images; data and image storage media in the nature of downloadable database management software and devices in the nature of data processing equipment ; downloadable databases in the field of artificial intelligence, defense, security, space and aerospace; downloadable database management software; All of the foregoing goods are exclusively used in the fields of artificial intelligence, defense, security, space and aerospace. 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. Research and development of new products for others; technical project study, namely, conducting scientific feasibility studies, engineers' services; development, installation, maintenance, updating or rental of software for use in database management, mapping, location, change detection and monitoring, tracking, site surveillance, digital database analysis, and the automatic analysis of geospatial information; programming for computers; consultancy relating to computer software; conversion of computer programs and data, other than physical conversion; technological advice in the field of artificial intelligence technology; platforms for artificial intelligence, namely Software as a service (SAAS) services featuring software for the automatic analysis and compilation of geospatial information in the field of artificial intelligence, defense, security, space and aerospace ; research in the field of artificial intelligence technology; providing downloadable computer programs for artificial Intelligence for artificial Intelligence analytics solutions for high-resolution imagery, full motion video and acoustic signals ; development and testing of computing methods, algorithms and software; All of the foregoing services are exclusively used in the fields of artificial intelligence, defense, security, space and aerospace.
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.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
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.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
