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
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
4.
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.
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.
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 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
11.
NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL GUIDE VANE AND TURBINE ENGINE
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.
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 assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction.
An assembly for producing a molding, made of removable material, of a turbomachine blade, includes an injection mold for the removable material in which a first core element and a second core element are mounted in a predetermined molding position, wherein the first and second core elements extend in a first direction. The mold includes a first face for molding a pressure-side face of the blade and a second face for molding a suction-side face of the blade and arranged facing the first face in a second direction perpendicular to the first direction.
Retaining members hold the cores in position in the injection mold.
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
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
17.
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
19.
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
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Services related to data management or processing, including database management and more specifically data analysis services to assist customers in their decision-making processes; providing business information in the strategic and military field; strategic business analysis in the fields of defense and security. Providing access to databases, data transmission, electronic distribution of satellite images via a computer network. Apparatus for sound, image or data recording, transmission, reproduction or processing; equipment for data processing and computers; software, computer peripheral devices; scientific and research apparatus and instruments based on automatic analysis of geospatial information; data processing equipment; data processing equipment based on the automatic analysis of geospatial information; artificial intelligence software; artificial intelligence software for automatic processing of satellite images; data and image storage media and devices; databases; database management software. Research and development of new products (for others); technical project study; development (design), installation, maintenance, updating or rental of software; programming for computers; consultancy relating to computer software; conversion of computer programs or data (other than physical conversion); technological advice in the field of artificial intelligence; platforms for artificial intelligence as SaaS [Software as a Service]; research in the field of artificial intelligence technology; providing computer programs for artificial Intelligence; development and testing of computing methods, algorithms and software.
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
A process for additive manufacturing of a part by successive deposition of layers of powder layers is provided. The process steps are performed within a manufacturing machine having a preparation zone for at least one layer and a consolidation zone for the powder, offset from each other. The process includes: (a) preparing at least one layer comprising at least two zones filled with at least two different powders, e.g., of different materials and/or particle sizes, in the preparation zone; (b) moving the at least one layer into the consolidation zone; (c) placing the at least one layer on either a manufacturing support or on an already consolidated portion of the part; and (d) consolidating at least one portion of the at least one layer by sintering, by melting, or by adding a binder.
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p. ex. par frittage ou fusion laser sélectif
A heat exchanger for a turbomachine, in particular an aircraft turbomachine, having a longitudinal axis, including a supporting wall extending in a first direction; a plurality of fins, each of which rises in a second direction from the supporting wall and being intended to be swept by an air stream, and a profiled panel covering the fins and extending in the first direction between a first diverging-profile wall upstream of the fins and a second converging-profile wall downstream of the fins. The heat exchanger includes an air intake device configured to slow the air stream in a third direction, the device having multiple separate air intake openings which are arranged upstream of the fins in the first direction and which are distributed in the third direction.
A vane for an aircraft turbomachine includes a blade and a cooling circuit inside the blade. The cooling circuit has at least one longitudinal flow cavity of a cooling air stream (RF). The cooling circuit further includes elements that protrude into the cavity and are configured to disrupt the air stream. Each of the protruding elements is generally arc-shaped and internally defines, with a first wall, a first cross-sectional flow area, and externally, with a second wall opposite the first wall, a second cross-sectional flow area. Each of the elements is configured such that the first or second cross-sectional flow area is reduced from upstream to downstream relative to the direction of the air stream.
An apparatus for providing energy in an aircraft, including a DC bus; at least one low-pressure electrical source and at least one high-pressure electrical source. The apparatus further includes a system for calculating a droop gain for each electrical source, based on at least one operating characteristic of the turbine engine; and for each electrical source, a model for controlling the electrical source in question, which module is designed to implement a droop setting based on the droop gain calculated for the electrical source in question.
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur 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
A heat exchanger of the air/oil type, for an annular air stream of a turbomachine, comprising a heat exchange zone with oil passages and heat exchange surfaces with the air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and included in a plane perpendicular to said air flow, said profile of the exchange zone thermal being in an arc of a circle so as to be able to be arranged in the annular air stream, remarkable in that said heat exchanger comprises on a radially internal or external face of the exchange zone thermal, an oil inlet and an oil outlet, the oil passages comprising several paths between said oil inlet and said oil outlet, distributed along the profile in circular arc of the heat exchange zone.
A process carrying out non-planar three-dimensional forming of at least one segment of a flexible printed circuit board including an electrically insulating polymer film, and, on at least one side of the polymer film, a metallization then carrying out electrodeposition in which a conductive layer is deposited on at least the metallization of at least the formed segment.
H05K 3/18 - Appareils ou procédés pour la fabrication de circuits imprimés dans lesquels le matériau conducteur est appliqué au support isolant de manière à former le parcours conducteur recherché utilisant la technique de la précipitation pour appliquer le matériau conducteur
30.
METHOD FOR MANUFACTURING A COMPOSITE VANE FOR AN AIRCRAFT ENGINE
Method for manufacturing a blade made of a composite material for a turbomachine, in particular of an aircraft, including steps of: a) arranging a preform produced by three-dimensional weaving of fibres within a mould, a polymerisable adhesive being inserted between a shield and an edge of the preform, b) closing and heating the mould, then injecting the polymerisable resin into the mould, wherein the mould is heated according to a cycle including increases in temperature from T1 to T2, then from T2 to T3, and in that the resin is injected in step b) during or just before the increase in temperature from T2 to T3, the temperature T2 being selected so that the viscosity of the adhesive is greater than the viscosity of the resin.
B29C 70/02 - 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 des combinaisons de renforcements et de matières de remplissage dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées ou non remplies
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
The method for dimensioning a multi-pole oriented-flux magnetic ring for a rotor of a rotating electric machine, where the magnetic ring includes a predetermined number of pairs of poles, and the magnetic ring is formed by at least one oriented-flux magnet. The method includes determining a characteristic dimension of the magnet equal to the minimum value out of the outer perimeter of the ring and the axial length of the ring, determining a reference value equal to the minimum value out of a predetermined reference length and twice the value Pi, comparing the characteristic dimension of the magnet with the reference value, and if the characteristic dimension of the magnet is greater than the reference value, the method comprises circumferentially dividing the magnet into at least two sub-magnets.
An axial turbomachine, comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called a secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the tertiary flow being in a tertiary flow vein radially external to said primary flow, delimited by an internal wall and an external wall; and an air/oil type heat exchanger, disposed in the tertiary flow vein. The heat exchanger comprises several angular sectors, each angular sector comprising an oil inlet on the internal wall at an angular end of said sector, and an oil outlet on said internal wall at an opposite angular end of said sector.
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
F28D 7/08 - 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 ayant une autre courbure, p. ex. en serpentins ou en zigzag
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
F28F 7/02 - Blocs traversés par des passages pour sources de potentiel calorifique
F28F 13/08 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en faisant varier la section transversale des canaux d'écoulement
33.
TRIPLE-FLOW AXIAL TURBOMACHINE COMPRISING A DIVERGING HEAT EXCHANGER IN THE THIRD FLOW
An axial turbomachine comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a flow of radially external air, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow flow in a tertiary flow vein radially external to said primary flow; and a heat exchanger disposed in the tertiary flow vein. The heat exchanger extends radially and axially in an upstream section section of the tertiary flow vein, having a divergent longitudinal section, said tertiary flow vein comprises a downstream section presenting a converging longitudinal section, following the tertiary flow.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
F02K 3/077 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux l'ensemble fonctionnel étant du type multi-flux, c.-à-d. ayant au moins trois flux
34.
METHOD FOR PRODUCING COMPOSITE BLADE CLEATS FOR AN AIRCRAFT TURBINE ENGINE
Method for manufacturing composite blade cleats for an aircraft turbine engine, including providing a woven panel, including a plurality of cleat preforms each having a usable portion and at least one margin, the preforms being distributed in the panel so that two adjacent preforms have at least a portion of the margin in common; injecting a matrix onto the panel; after injection, dividing the panel in order to separate the cleats from one another; machining the cleats to remove the margins.
The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including:
at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device,
a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and
said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine,
a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and
a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.
An axial turbomachine including a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary f flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said flow primary; and an air/oil type heat exchanger disposed in the tertiary flow stream and including heat exchange surfaces with air and oil passages extending in said tertiary flow stream; and structural arms extending radially through the tertiary flow vein. Each structural arm has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE BORDEAUX (France)
Inventeur(s)
Cavarroc, Marjorie Christine
Aymonier, Cyril
Giroire, Baptiste Simon
Guillaume, Bertrand
Poulon, Angélique Nadine Jeanne
Aubert, Guillaume
Abrégé
A device for depositing a thick metal nitride on a sample by supercritical fluids includes a first enclosure forming a first closed volume; a second enclosure placed in the first enclosure and delimited by internal walls transparent to electromagnetic radiation forming a second closed volume intended to comprise a fluid under supercritical conditions; a heat transfer dielectric fluid circulating in the first volume around the second enclosure; a sample holder present in the second volume; an induction heating device surrounding the second enclosure; inlets for introducing a fluid and at least one precursor material into the second enclosure; and an outlet to purge the second volume.
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
38.
FUEL CONDITIONING SYSTEM FOR SUPPLYING AN AIRCRAFT TURBOMACHINE, AND METHOD OF SUPPLYING A TURBOMACHINE
A fuel conditioning system configured to supply an aircraft turbomachine with fuel from a cryogenic tank. The conditioning system comprising a primary heat exchanger designed to heat the fuel flow to at least one primary temperature, and at least one secondary heat exchanger, mounted downstream of the primary heat exchanger, designed to heat the fuel flow to at least one secondary temperature higher than the primary-temperature, the primary heat exchanger being configured to extract calories in the fuel flow that is at least at the secondary temperature.
B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
B64D 37/30 - Circuits de carburant pour carburants particuliers
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 7/224 - Chauffage du combustible avant son arrivée au brûleur
39.
SYSTEM FOR CONDITIONING FUEL FOR SUPPLYING AN AIRCRAFT TURBOMACHINE, AIRCRAFT AND METHOD OF USE
A fuel conditioning system configured to supply a turbomachine with fuel from a cryogenic tank, the conditioning system comprising a fuel circuit connected at the inlet to the cryogenic tank and at the outlet to the turbomachine, a pump, a fuel cell configured to provide electricity to an electrical network of the aircraft, at least a first heat exchanger belonging to the fuel circuit and configured to transmit calories from the fuel cell to the fuel flow in order to heat it, and at least one second heat mounted downstream of the first heat exchanger in the fuel circuit and configured to transmit calories from the turbomachine to the fuel flow in order to heat it.
B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
B64D 37/30 - Circuits de carburant pour carburants particuliers
F02C 6/10 - 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 fournissant un fluide de travail à un utilisateur, p. ex. un processus chimique, retournant le fluide de travail à une turbine de l'ensemble fonctionnel
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
40.
APPLICATION HEAD FOR AUTOMATICALLY APPLYING FIBRES
Application head for automated fiber placement, which application head includes at least: an application roller that is designed to apply fibers to a shaping tool which application roller is rotatably movable on its axis for applying fibers to the shaping tool, and a feed device includes a winding of a strip of fibers having a predefined orientation, the strip of fibers being configured to be transferred by unwinding from the feed device onto the application roller with at least one portion of the fibers of the strip being oriented such that they are not perpendicular to the axis of the roller.
B29C 70/38 - Empilage automatisé, p. ex. utilisant des robots, par application de filaments selon des modèles prédéterminés
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
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
41.
METHOD FOR MOUNTING AN AXLE IN A BOGIE, AND ASSOCIATED INSTALLATION
A method and system for mounting an axle in a bore of a bogie mounted on a landing gear of an aircraft, the landing gear being in a gear-down position, the bore extending in a substantially horizontal direction referred to as the axle installation direction, between a first open end and a second open end are disclosed. The method includes a) supplying a mobile bearing structure (30) comprising means for moving the axle (12) which are able to move along a direction substantially parallel to the axle installation direction, b) installing the axle (12) on the means for moving the axle, c) aligning the axis (C) of the axle (12) with the axis (B) of the bore (14), and d) inserting the axle (12) into said bore (14) of the bogie (16) by moving the means for moving the axle (12) along the direction substantially parallel to the axle installation direction.
The invention relates to a contactor comprising a motor (2) and a commutator-brush system (3), the motor comprising a stator (200) and a rotor (201), the commutator-brush system comprising: - a commutator (300) joined to the rotor, the commutator comprising at least one conductive portion (302) and at least one non-conductive portion (303); and - a pair of brushes formed by two brushes (304), the brushes each having a contact face configured to rub against the commutator. A side surface of the commutator (300) includes the conductive portion (302) and the non-conductive portion (303) of the commutator, the commutator being rotatable about an axis of rotation (X). The commutator-brush system (3) is configured to move between a conducting position in which the commutator electrically connects the pair of brushes, and an interrupting position in which the commutator electrically isolates the pair of brushes (304), the commutator-brush system passing from the conducting position to the interrupting position, and vice versa, by rotation of the commutator (300) by the motor.
H01H 1/36 - Contacts caractérisés par la manière dont les contacts coopérants s'engagent par glissement
H01H 19/56 - Organe d'actionnement à mouvement angulaire et portant des contacts, p. ex. interrupteurs à tambour
H01H 19/58 - Organe d'actionnement à mouvement angulaire et portant des contacts, p. ex. interrupteurs à tambour n'ayant qu'une pression de contact axiale, p. ex. interrupteur à disque
H01H 3/26 - Dispositions comportant une énergie à l'intérieur de l'interrupteur pour actionner le mécanisme d'entraînement utilisant un moteur dynamo-électrique
H01H 3/60 - Dispositions mécaniques pour empêcher ou amortir les vibrations ou les chocs
43.
CURING MOLD FOR MANUFACTURING A TURBOMACHINE COMPONENT MADE OF COMPOSITE MATERIAL FROM A PREFORM AND METHOD FOR PRODUCING A COMPONENT BY MEANS OF SUCH A MOLD
The invention relates to a curing mold (10) for manufacturing a turbomachine component made of composite material from a preform (200), comprising: —a first and a second body (11, 12) defining an air gap receiving the preform; —at least one primary channel (21) arranged in the first and/or the second body; —an injection member (22) of a pressurized fluid in the primary channels; —at least one secondary channel (23), in which a piston (24) slides, which delimits, on the one hand, a first chamber (26) in communication with the or a primary channel and, on the other hand, a second chamber (27) in communication with the air gap, and which is designed to compress thermosetting resin which has entered the second chamber from the preform in the air gap, so as to put the preform under hydrostatic pressure.
B29C 43/34 - Alimentation en matière à mouler des moules ou des moyens de pressage
B29C 43/02 - Moulage par pressage, c.-à-d. en appliquant une pression externe pour faire couler la matière à moulerAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 43/32 - Éléments constitutifs, détails ou accessoiresOpérations auxiliaires
B29C 43/36 - Moules pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
A part includes a substrate made of ceramic matrix composite material, the substrate being coated with a multilayer stack including at least, and in this order, starting from the substrate a tie layer including silicon; an insulation layer including a rare earth disilicate or silica; a barrier layer including a rare earth disilicate; the part further including at least one thermocouple inserted between the insulation layer and the barrier layer.
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
45.
FACILITY AND METHOD FOR PAIRING A SHIELD TO A PREFORM FOR THE PRODUCTION OF AN AIRCRAFT TURBINE ENGINE VANE
A facility for pairing a metal shield to a leading edge of a preform made of composite material for the production of an aircraft turbine engine blade, the facility including a support configured to receive and hold the metal shield, —a movement hexapod which carries the support and is able to move the support along and about the three axes of an XYZ coordinate system, —an automaton which includes jaws and is configured to receive and hold the preform, and—a computing unit for controlling the hexapod and the automaton with a view to producing the pairing. The invention also relates to a method for pairing the metal shield to the leading edge of the preform made of composite material for the production of the aircraft turbine engine blade.
An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.
The invention relates to a brushless starter-generator (1) comprising: - a main electrical machine (10) having a stator (11) comprising stator windings (12a, 12b, 12c) and a rotor (13) comprising a rotor winding (14) and intended to be mechanically coupled to the combustion engine (200); - an exciter (20) comprising a stator winding (24) and rotor windings (23a, 23b, 23c) connected to the rotor winding (14) of the main electrical machine (10), the rotors of the main electrical machine (10) and of the exciter (20) forming the rotor (75) of the starter-generator; and - a regulator (50) configured to supply the stator winding of the exciter with AC voltage with duty cycle modulation of alternation width when the starter-generator operates in starter mode, the regulator being configured to vary the duty cycle so as to vary an excitation delivered by the rotor (22) of the exciter to the rotor winding of the main electrical machine.
The invention relates to a battery comprising: - at least one electrochemical accumulator (3) including an active portion and a shell enclosing the active portion; - a casing (2) housing the at least one accumulator (3); and - a heat-transfer fluid (5) contained in the casing (2), the shell (300) including a weakened zone configured to open under the effect of an overpressure in the accumulator (3) and to discharge gases produced by the active portion of the accumulator (3) that caused the overpressure. During the overpressure in the at least one accumulator (3), the heat-transfer fluid (5) comes into contact with the gases produced by the accumulator (3) so as to contain the gases and cool the accumulator.
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
H01M 10/613 - Refroidissement ou maintien du froid
A method for manufacturing a shell mold intended for manufacturing at least one metal part by lost-wax casting, the shell mold including at least one molding cavity intended for molding the metal part, and at least one feed channel intended to convey a liquid metal to the molding cavity, the method including manufacturing a wax pattern including a part pattern intended to form the molding cavity and a feed channel pattern intended to form the feed channel, arranging at least one ceramic insert around at least a portion of the feed channel pattern, and manufacturing the shell mold around the wax pattern.
The invention relates to a thermocouple comprising: —a substrate comprising an upper surface; —a first arm comprising a first horizontal part and a first connection terminal; —a second arm comprising a second horizontal part and a second connection terminal; the first arm being arranged on the upper surface of the substrate, the second arm being arranged on the first arm such that the second horizontal part at least partially covers the first horizontal part and such that the second connection terminal is in contact with the upper part of the substrate, a hot junction of the thermocouple being defined by the zone of contact between the first arm and the second arm.
G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p. ex. des thermocouples
G01K 1/14 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers
H10N 10/13 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c.-à-d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck caractérisés par les moyens d'échange de chaleur à la jonction
H10N 10/17 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c.-à-d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck caractérisés par la structure ou la configuration de la cellule ou du thermocouple constituant le dispositif
51.
POWER MODULE HAVING SEMICONDUCTOR COMPONENTS AND INCORPORATING A TEMPERATURE SENSOR, AND ASSOCIATED MANUFACTURING METHOD
A power module includes a plurality of semiconductor-based power components and a substrate having an upper metallization receiving the components and a lower metallization opposite to the upper metallization. Optionally, a baseplate may be fixed to the lower metallization of the substrate. A metal structure is in direct contact with a lower surface defined by the either optional baseplate or the substrate, on the side opposite the components. The power module includes at least one elongated temperature sensor, at least partially immersed in the metal structure and spreading parallel to the lower surface.
H01L 23/36 - Emploi de matériaux spécifiés ou mise en forme, en vue de faciliter le refroidissement ou le chauffage, p. ex. dissipateurs de chaleur
G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p. ex. des thermocouples
G01K 11/3206 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant des changements dans la transmittance, la diffusion ou la luminescence dans les fibres optiques en des endroits distincts de la fibre, p. ex. utilisant la diffusion de Bragg
H01L 21/48 - Fabrication ou traitement de parties, p. ex. de conteneurs, avant l'assemblage des dispositifs, en utilisant des procédés non couverts par l'un uniquement des groupes ou
H01L 23/00 - Détails de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 23/057 - ConteneursScellements caractérisés par la forme le conteneur étant une structure creuse ayant une base isolante qui sert de support pour le corps semi-conducteur les connexions étant parallèles à la base
H01L 23/498 - Connexions électriques sur des substrats isolants
H01L 23/538 - Dispositions pour conduire le courant électrique à l'intérieur du dispositif pendant son fonctionnement, d'un composant à un autre la structure d'interconnexion entre une pluralité de puces semi-conductrices se trouvant au-dessus ou à l'intérieur de substrats isolants
H01L 25/00 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 25/065 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans une seule des sous-classes , , , , ou , p. ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans le groupe
52.
PROPULSION SYSTEM FOR A NON-ROTARY-WING AIRCRAFT, AND ASSOCIATED AIRCRAFT
The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current.
The invention relates to a propulsion system (20) for a non-rotary-wing aircraft (3), the system comprising an alternating-current generator (24), at least one wingtip propulsion unit (22) comprising an alternating-current motor, and at least one lift-increase propulsion unit (23a-23d) comprising an alternating-current motor. The generator is connected to the lift-increase propulsion unit via a AC/DC converter (261), an intermediate DC distribution stage (260) provided with electric batteries (262) and a DC/AC converter (263a-263d). On the other hand, the generator is connected to the wingtip propulsion unit in such a way as to supply this propulsion unit with alternating current, without intermediate conversion of this alternating current into direct current.
The invention also relates to an aircraft provided with such a propulsion system.
A method of control of a power generation and control system of an aircraft including: a hybrid propulsion system including an electrical network and a propulsive energy source, at least one non-propulsive energy source, a control unit of the hybrid propulsion system, and an overall aircraft power control unit, characterized in that the method includes: the determination of an operability limit of the propulsive energy source, the monitoring of the operability of the propulsive energy source by the control unit of the hybrid propulsion system, and the control of a power generated by the propulsive energy source by the overall aircraft power control unit when the operability of the propulsive energy source is less than said determined operability limit or the control of a power generated by the propulsive energy source by the control unit of the hybrid propulsion system.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
ECOLE NORMALE SUPERIEURE PARIS-SACLAY (France)
Inventeur(s)
Fragnaud, Cédric
Roux, Stéphane
Betancur, Julian
Abrégé
The invention relates to a method for non-destructively testing a part by means of transmission radiography, which method comprises the following steps of acquiring N projections (P(n)) of the part, generating calculated N images (P(n)) of the part, estimating, by successive iterations, the vector p from an initial vector p=pini and the vector c from an initial vector c=cini and/or the parameter vector a from an initial vector α=αini, by minimising the sum of the squared differences between the projections (P(n)) and the images (P(n)), processing the projections (P(n)) and/or the images (P(n)), identifying defects in the part by comparing the processed projections (P(n)) and the processed images (P(n)).
G01N 23/18 - Recherche de la présence de défauts ou de matériaux étrangers
G01N 23/20066 - 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 utilisant la diffraction de la radiation par les matériaux, p. ex. pour rechercher la structure cristallineRecherche 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 utilisant la diffusion de la radiation par les matériaux, p. ex. pour rechercher les matériaux non cristallinsRecherche 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 utilisant la réflexion de la radiation par les matériaux en mesurant la diffusion inélastique des rayons gamma, p. ex. effet Compton
55.
EXTRUSION HEAD FOR ADDITIVE MANUFACTURING, ADDITIVE MANUFACTURING SYSTEM AND METHOD
An extrusion head for additive manufacturing includes an enclosure defining a supply chamber. The enclosure includes at least one inlet port opening into the supply chamber and configured to receive a material to be extruded under pressure and a plurality of extrusion nozzles. Each nozzle is in communication with the supply chamber and opens onto the exterior of the enclosure via an outlet orifice. The nozzles of the plurality of nozzles are arranged adjacent to one another with a determined spacing between each nozzle outlet orifice.
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
A system for conditioning fuel configured to supply a main turbomachine, based on fuel from a cryogenic tank, comprising a pump configured to operate at a predetermined constant speed, at least one heat exchanger, a supply member for supplying the main turbomachine with a fuel flow, the supply member being configured to deliver a nominal flow rate when the pump is operating at a predetermined constant speed, at least one buffer tank, a first valve for controlling the supply of fuel to the buffer tank, a second valve for controlling the distribution of the fuel flew flow and a regulating device that is configured to open the second valve when the setpoint flow rate is higher than the nominal flow rate.
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 9/32 - Commande de l'alimentation en combustible caractérisée par l'étranglement de l'admission du combustible
57.
METHOD FOR DETECTING A BEARING DEFECT IN A ROTATING SYSTEM AND MONITORING SYSTEM IMPLEMENTING THIS METHOD
A method for detecting a defect in a bearing of a rotating system, includes acquiring a bearing position signal, a vibratory signal from the bearing and a theoretical characteristic vector of the bearing; determining a deterministic part of the vibratory signal and removing the deterministic part to obtain a residual signal function of the position signal; calculating, from the theoretical characteristic vector, lower and upper bounds of defect frequencies; calculating, from the vibratory signal, a spectral coherence and the square of the amplitude of the spectral coherence; calculating, from the square of the amplitude of the spectral coherence and the lower and upper bounds of the defect frequencies, a current characteristic vector of the bearing; determining a spectral cyclic contrast of the defect; finely identifying signatures of interest by calculating a weighted integrated cyclic coherence associated with the defect, and determining diagnostic indicators easily interpretable by an operator.
This method for determining a frictional coefficient of an aircraft on a runway includes the steps of:
producing a database of frictional coefficients simulated for various types of aircraft and various runway conditions by applying simulation data to models representing the braking of aircraft when landing, for various braking scenarios; and
predicting a frictional coefficient from real data of the aircraft for which the frictional coefficient is determined from data stored in the database.
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
A nickel-based superalloy comprises in weight percentages: 5.4 to 6.0% of aluminium, 7.5 to 9.0% of tantalum, 0.10 to 0.25% of titanium, 5.5 to 7.5% of cobalt, 4.0 to 5.5% of chromium, 0.10 to 0.70% of molybdenum, 4.0 to 5.0% of tungsten, 4.8 to 6.2% of rhenium, 0.04 to 0.15% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and to a turbomachine comprising such a blade.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
C23C 28/00 - Revêtement pour obtenir au moins deux couches superposées, soit par des procédés non prévus dans un seul des groupes principaux , soit par des combinaisons de procédés prévus dans les sous-classes et
Molding core for manufacturing an OMC hollow aeronautical part, in particular a fan module part, including a composite material including on the one hand a first phase of formula Mn+1AlCn, where n=1 to 3, and M being a transition metal selected from the group consisting of titanium, niobium, chromium or zirconium, the composite material including on the other hand a second phase of formula Al4C3
B29C 33/54 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille en matière poudreuse ou granulaire
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29C 70/46 - 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"
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
61.
Foundry core for manufacturing a hollow metal aeronautical part
B22C 9/10 - NoyauxFabrication ou mise en place des noyaux
B22C 1/00 - Compositions des matériaux réfractaires pour moules ou noyauxLeur structure granulaireCaractéristiques chimiques ou physiques de la mise en forme ou de la fabrication des moules
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
62.
IMPROVED COUNTER-FORM FOR THE MANUFACTURE OF A METAL AERONAUTICAL PART
A counter-form for producing metal aeronautical parts, in particular a turbine part by solid-phase densification, including a composite material containing, on the one hand, a first phase having formula Mn+1AlCn, where n=1 to 3 and M is a transition metal selected from the group consisting of titanium and/or molybdenum and/or niobium and/or chromium, and, on the other hand, a second phase having formula Al4C3.
B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
63.
METHOD FOR MANUFACTURING A DIAPHRAGM HOLDER FOR AN OLEO-PNEUMATIC SHOCK ABSORBER
A method for manufacturing a diaphragm holder for a shock absorber of the oleo-pneumatic type, in particular for an aircraft landing gear. The diaphragm holder includes a first end with a dome, and a tubular portion extending from the dome to a second end. The method includes a step of overmolding a first material onto an insert. The insert can be a second material with a value of compression breaking stress divided by density that is higher than the first material or alternatively, of a material identical to the first material. A diaphragm carrier which can be manufactured by this method.
F16F 15/023 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif utilisant des moyens fluides
64.
Method for producing a preform for part of a blade or propeller by winding a weave obtained by weaving to shape
A method for manufacturing a fibrous preform for a blade or propeller part of a turbomachine, includes at least one fixing base extended by a mounting portion of an aerodynamic profile, the method including the winding of a fibrous texture, obtained by contour weaving, on a substrate of changing section having at least a first region of extra thickness in the shape of the fixing base and a second region in the shape of the mounting portion of the aerodynamic profile.
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
B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
B29C 53/56 - Enroulement et assemblage, p. ex. enroulement en spirale
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 70/32 - 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
B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
An aircraft landing gear shock absorber strut including an outer cylinder having a bore defining an opening; an inner cylinder having a first end region movably coupled within the bore and a second end region which projects out of the opening. The inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition and a second condition and is biased by a spring force to assume the second condition. A mechanical outstop is arranged to engage an abutment surface of the inner cylinder to limit extension of the shock absorber strut; and a rotatable member drives the out stop axially to move the inner cylinder from the second condition towards the first condition. The rotatable member is arranged such that the spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.
INSTITUT NATIONAL DES SCIENCES APPLIQUEES DE LYON (France)
Inventeur(s)
Abboud, Dany
El Badaoui, Mohammed
Antoni, Jérôme
Girardin, François
Mbailassem, Fulbert
Abrégé
A method for monitoring a turbine engine, said method including, for at least one blade of a rotor with which the turbine engine is equipped, the steps of: obtaining a plurality of samples of at least one analogue time signal acquired by means of at least one fixed proximity sensor and representing a passage of said at least one blade in front of said at least one proximity sensor; calculating a deflection of said at least one blade for each of said samples: determining, in the form of a linear combination of sinusoidal signals, a so-called “approximation signal”, minimizing a cost function evaluating a deviation between said calculated deflections and said approximation signal; and monitoring the vibratory behavior of said at least one blade on the basis of frequencies and/or amplitudes and/or phases of the sinusoidal signals that make up said approximation signal.
A method for manufacturing a turbomachine vane made of composite material and having a cavity, the method includes producing a core having the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only a portion of the volume of the core, the core further including a sealed envelope defining the outer surface of said core; and forming a composite material skin around the core.
B29C 70/68 - 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 en incorporant ou en surmoulant des parties préformées, p. ex. des inserts ou des couches
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
68.
METHOD FOR PRODUCING A VANE COMPRISING A REINFORCED CAVITY
A method for manufacturing a composite material vane with a cavity, includes making a core with the shape of the cavity of the vane to be manufactured, the core including a reinforcing structure occupying only part of the volume of the core, the remaining volume of the core being occupied by a material of a fleeting nature, forming a composite material skin around the core, and eliminating the fleeting material to obtain a composite material vane with a cavity reinforced by the reinforcing structure.
B29C 70/68 - 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 en incorporant ou en surmoulant des parties préformées, p. ex. des inserts ou des couches
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
A turbomachine may include a high-pressure turbine connected to a high-pressure shaft and a low-pressure turbine connected to a low-pressure shaft, the hot gases leaving the high-pressure turbine driving the low-pressure turbine. A method for regulating the turbomachine includes electrically assisting the high-pressure shaft in order to provide said high-pressure shaft with electrical energy in addition to thermal energy obtained from a combustion chamber of the turbomachine, for an assistance period, and correcting the speed of the low-pressure shaft to achieve a reference speed of the low-pressure shaft that was previously determined in the absence of electrical assistance.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F01D 21/14 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à d'autres conditions spécifiques
70.
METHOD FOR MANUFACTURING AN ACOUSTIC ATTENUATION STRUCTURE WITH CONTROL OF THE POSITIONING OF AN ACOUSTIC SKIN
A method for manufacturing an acoustic attenuation structure including the following steps: making a complex acoustic multi-element panel including a plurality of hollow complex acoustic elements and a plurality of partitions forming acoustic cavities, each complex acoustic element being housed in an acoustic cavity so as to form an acoustic cell, making a first skin, piercing a plurality of perforations on the first skin at determined locations to form a multi-perforated acoustic skin, assembling the complex acoustic multi-element panel with the multi-perforated acoustic skin. The multi-perforated acoustic skin including on its assembly face a plurality of positioning studs configured to cooperate with a hollow complex acoustic element or an acoustic cavity during the assembly of the complex acoustic multi-element panel with the multi-perforated acoustic skin.
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 27/08 - Produits stratifiés composés essentiellement de résine synthétique comme seul composant ou composant principal d'une couche adjacente à une autre couche d'une substance spécifique d'une résine synthétique d'une sorte différente
B32B 27/28 - Produits stratifiés composés essentiellement de résine synthétique comprenant des copolymères de résines synthétiques non complètement couverts par les sous-groupes suivants
B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
71.
METHOD FOR INSPECTING FOR SURFACE DEFECTS ON A CAST PART MADE OF SINGLE-CRYSTAL METAL AND SYSTEM FOR IMPLEMENTING SAME
A method for inspecting the surface finish of a cast part made of single-crystal metal, the surface of the part potentially containing defects resulting from an inhomogeneity of orientation of at least a crystal lattice of the single-crystal metal, the method including acquiring, using an image-acquiring device, a series of images of the cast part illuminated by a polarized and collimated illuminating device, then analysing the series of images by an image-processing device, each image of the series of images being taken at a different polarization angle.
An aircraft landing gear shock absorber strut including a damping pin and a flow restricting plate having an orifice through which the metering pin axially moves as the sliding tube moves between the extended and compressed positions, wherein the damping pin or the flow restricting plate is coupled to a separator piston so as to move with the separator piston.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
ECOLE NORMALE SUPERIEURE PARIS- SACLAY (France)
SAFRAN (France)
SAFRAN AIRCRAFT ENGINES (France)
Inventeur(s)
Schneider-Die-Gross, Julien Paul
Mendoza Quispe, Arturo
Roux, Stéphane
Abrégé
A method for characterizing a mechanical part making it possible to evaluate the residual stresses in the part, as well as a method for constructing a predictive model and a non-destructive testing method making it possible to easily test such a part, the characterizing method including the following steps: measuring geometrical information of the part in a first state, physically transforming the part between the first state and a second state, measuring geometrical information of the part in its second state, determining the displacement field between the first state and the second state of the part by a digital image correlation method and obtaining the deformation field between the first state and the second state of the part, determining the stress field in the second state of the part by a finite element simulation method.
G01N 3/02 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique Parties constitutives
G06N 5/022 - Ingénierie de la connaissanceAcquisition de la connaissance
74.
METHOD FOR DETERMINING THE PRESENCE OF AT LEAST ONE DEFECT ON A TOMOGRAPHIC IMAGE OF A THREE-DIMENSIONAL PART BY BREAKING THE IMAGE DOWN INTO PRINCIPAL COMPONENTS
Associaton pour la Recherche et le Développement des Méthodws et Processus Industriels (A.R.M.I.N.E. (France)
Inventeur(s)
Remacha, Clément
Redoules, Guillaume
Aublet, Axel
Abrégé
A method for determining the presence of at least one defect in a three-dimensional part on the basis of a reference base, wherein:
an image of the part is acquired by tomography;
the image is segmented and the segmented image is registered with respect to the images of the reference base;
the subdomains associated with the registered segmented image are determined; and
for each subdomain of the registered segmented image, the following steps are carried out:
registering the subdomain;
breaking down the subdomain with respect to the principal modes of the reference base;
generating a synthetic image of the subdomain from the breakdown, which is subtracted from the registered segmented image of the subdomain; and
determining that a defect is present on the basis of the comparison of the value of each pixel of the residual image with a predetermined threshold.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE POITIERS (France)
ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS (France)
Inventeur(s)
Rame, Jérémy
Cormier, Jonathan
Mataveli Suave, Lorena
Menou, Edern
Abrégé
The invention relates to a nickel-based superalloy comprising in weight percentages: 5.0 to 6.0% of aluminium, 6.0 to 9.0% of tantalum, 1.0 to 5.0% of cobalt, 5.0 to 7.5% of chromium, 0 to 1.0% of molybdenum, 4.0 to 6.0% of tungsten, 0.50 to 3.5% of rhenium, 1.0 to 4.0% of platinum, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and to a turbomachine comprising such a blade.
A piezo-electric fluid pump is provided including a main housing; a fluid reservoir located within the main housing; a piston head moveably mounted within the main housing; a piezo-electric stack; a bias mechanism arranged to couple the piston head and piezo-electric stack and maintain the piezo-electric stack in compression; an outlet plate statically mounted within the main housing adjacent to the piston head, wherein the adjacent surfaces of the outlet plate and piston head define a pumping chamber; an inlet disc valve arranged to permit a one-way flow of fluid from the reservoir into the pumping chamber; and an outlet disc valve arranged to permit a one-way flow of fluid out of the pumping chamber. The combination of pre-loading of the piezo-electric stack in compression and use of inlet disc valve enables the piezo-electric pump to exhibit substantial improvement to the pressure and flow capability compared to other piezo-electric pumps.
F04B 17/00 - Pompes caractérisées par leur combinaison avec des machines motrices ou moteurs particuliers qui les entraînent ou par leur adaptation à ceux-ci
A method for manufacturing turbomachine disks is provided. The method includes: providing a nickel alloy powder; and shaping the powder to obtain a disk. Providing a powder can include: manufacturing a nickel alloy electrode by PAM-CHR; atomizing a nickel alloy by EIGA from the nickel alloy electrode, leading to a raw powder; and sifting the raw powder under inert atmosphere or under vacuum with a granulometric cut-off between 150 μm and 50 μm, leading to the nickel-based alloy powder. In some examples, the granulometric cut-off can be between 125 μm or 75 μm.
B22F 9/08 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques à partir d'un matériau liquide par coulée, p. ex. à travers de petits orifices ou dans l'eau, par atomisation ou pulvérisation
B22F 3/17 - 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 par forgeage
B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
78.
ACOUSTIC TREATMENT DEVICE FOR AN AIRCRAFT PROPULSION ASSEMBLY, AND ITS METHOD OF MANUFACTURE
An acoustic treatment device for an aircraft propulsion assembly includes two skins that enclose an acoustic structure. The acoustic structure has a cellular structure with hollow cells and a structure of shapes with protruding shapes, each of which is engaged in a different hollow cell of the cellular structure. The structure of shapes additionally has stubs designed to fit into the hollow cells of the cellular structure and to allow the acoustic treatment device to be fixed to a component of the aircraft propulsion assembly.
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
79.
Fuel conditioning system and method configured to supply an aircraft turbine engine with fuel from a cryogenic tank
A fuel conditioning system configured to supply an aircraft turbine engine with fuel from a cryogenic tank. The fuel circuit comprising a buffer tank for supplying the turbine engine and a plurality of compression modules configured to supply the buffer tank, each compression module comprising an elementary tank of fixed volume, an elementary heat source configured to increase the temperature of the fuel in the elementary tank in an isochoric manner, an inlet valve connecting the elementary tank to an upstream part of the fuel circuit, an outlet valve connecting the elementary tank to the buffer tank, and a venting valve connecting the elementary tank to the cryogenic tank via a return circuit in which a gaseous stream circulates.
An aircraft landing gear assembly including a first landing gear element movably coupled relative to a second landing gear element to pivot about a pivot axis; a cam surface defined by the second landing gear element; and a leaf spring having a first end region and a second end region, the first end region of the leaf spring being coupled to the first landing gear element including a cam follower arranged in moving contact with the cam surface such that the cam follower moves from a first region to a third region via a second region, wherein the cam surface is shaped such that a distance between the pivot axis and the cam surface increases between the first region and the second region and the distance between the pivot axis and the cam surface varies between the second region and the third region of the cam.
The invention relates to a method, navigation device and computer program product for assisting with the navigation of a vehicle provided with a navigation device. The method comprises the following steps: acquiring a priori values of variables of a navigation device of the vehicle; determining current values of the variables and a current uncertainty matrix from previous values of the variables and a previous uncertainty matrix; and determining a correction from the current values of the variables, the current uncertainty matrix and a measurement.
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
82.
AIRCRAFT PROPULSION SYSTEM WITH START-UP CONTROL DEVICE
A propulsion system includes a gas turbine designed so that a combustion chamber can be ignited in a first ignition range of rotational speeds of a compressor shaft. The system further includes a control device designed to control an electric starter to accelerate the compressor shaft and, when the compressor shaft is accelerated, to control an attempt to ignite the combustion chamber. The gas turbine is designed so that the combustion chamber can be ignited in a second ignition range which is higher than the first ignition range, but not between these two ignition ranges, and the ignition attempt is carried out in the second ignition range.
A tooling for winding a fibrous fabric on a support, allowing gradual modification of the shape of the support as winding progresses, and includes compaction devices to reduce wrinkling of the fabric obtained after compaction.
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 70/24 - 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 70/32 - 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
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
84.
Method for manufacturing an acoustic panel by welding
A method for manufacturing an acoustic panel by welding of at least two acoustic components made of thermoplastic material, a thermal gradient being applied on the acoustic components during the welding operation so as to apply a temperature higher than the glass transition or melting temperature of the material on the area to be welded and so as to apply a temperature lower than or equal to the geometric stabilization temperature of the material on the parts furthest from the area to be welded.
B29C 65/18 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec un outil chauffé
B29C 65/00 - Assemblage d'éléments préformésAppareils à cet effet
B29C 65/10 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des gaz chauds
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
B29L 31/38 - Cônes de haut-parleurMembranes acoustiques
A control system (100) for a battery-powered aircraft (1), the control system comprising: a landing gear assembly (10, 20) moveable between a retracted position in which the landing gear assembly is housed within the aircraft and an extended position in which the landing gear assembly is deployed from the aircraft, the landing gear assembly comprising: a main landing gear (10); and a nose landing gear (20); at least one local hydraulic pressure source (110) configured to receive power from at least one battery (101); a landing gear controller (321) configured to receive and deliver control inputs to the at least one local hydraulic pressure source; and at least one actuator (130) in fluid communication with the at least one local hydraulic pressure source and configured to move the landing gear assembly between the retracted position and the extended position in response to inputs received by the landing gear controller; wherein at least one of the main landing gear and nose landing gear is biased in the retracted position by hydraulic pressure.
COMMISSARIAT A L'ENERGIE ATOMIQUE ET AUX ENERGIES ALTERNATIVES (France)
Inventeur(s)
Soulier, Mathieu
Laucournet, Richard
Bancillon, Jacky
Montani, Alexander
Bechelany, Mirna
Jaquet, Virginie
Saboundji, Amar
Abrégé
A method includes coating of one or more zones of the refractory alloy part, using a treatment composition including one or more types of preceramic polymer, a solvent and one or more active fillers, and heat treating the coated refractory alloy part, the heat treatment allowing to partially convert the preceramic polymer to form a ceramic layer, the active filler forming on a surface of the refractory alloy part, one or more ternary alloys and forming a continuous layer between the surface of the refractory alloy part and the ceramic layer obtained by conversion. The heat treatment forms a continuous layer of the ternary alloy. The treatment composition includes, relative to the total weight of the treatment composition, a weight proportion of between 40% and 66% of the one or more active fillers, and an active filler/preceramic polymer weight ratio is greater than or equal to 2.
B22C 9/12 - Traitement des moules ou noyaux, p. ex. séchage, étuvage
B22C 3/00 - Emploi de compositions spécifiées pour revêtir les surfaces des moules, noyaux ou modèles
B22C 9/10 - NoyauxFabrication ou mise en place des noyaux
C23C 24/08 - Revêtement à partir de poudres inorganiques en utilisant la chaleur ou une pression et la chaleur
C23C 28/00 - Revêtement pour obtenir au moins deux couches superposées, soit par des procédés non prévus dans un seul des groupes principaux , soit par des combinaisons de procédés prévus dans les sous-classes et
87.
METHOD AND SYSTEM FOR CALCULATING ACCUMULATED DAMAGE ON A STRUCTURAL COMPONENT
A method and system for calculating the accumulated damage on a component of an aircraft, the method comprising determining the weight of the aircraft at a predetermined point of a flight cycle, calculating, based at least partially on the determined weight of the aircraft, a calculated damage inflicted on the component during the flight cycle, obtaining historic data indicating the damage inflicted on the component before the flight cycle and calculating the accumulated damage of the component, based on the calculated damage inflicted on the component during the flight cycle and the historic data.
A spectral interrogation device, including: an optical source for emitting a light signal, a measurement optical fibre comprising a series of successive Bragg gratings for reflecting the light signal in different wavelength bands, a reflective optical fibre comprising a total reflection element, a wavelength detector, and an optical switch for switching between a sequence of three operating modes. In a first mode, the light signal emitted by a given optical source is guided from the optical source to a corresponding measurement optical fibre. In a second mode, the light signal is guided to make a predetermined number of return trips in a line formed by a coupling between the measurement optical fibre and a corresponding reflective optical fibre, generating a predetermined delay between the successive gratings. In a third mode, the light signal is guided to a corresponding detector to successively measure the wavelength bands associated with the gratings.
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
89.
VANE MADE OF COMPOSITE MATERIAL COMPRISING A METALLIC REINFORCEMENT AND METHOD FOR MANUFACTURING SUCH A VANE
A method for manufacturing a vane made of composite material for a turbomachine, including the steps of three-dimensional fibre weaving and producing a fibrous preform, reinforcing an edge of the preform intended to form a leading edge of a blade of the vane, by integrating a metallic reinforcement on this edge, mounting the preform and the reinforcement in a mould, densifying the preform by a matrix to form the vane, wherein, prior to the integration of the reinforcement, the method includes a step of introducing at least one reinforcement support configured to be interposed between the reinforcement and the edge, and wherein at the densification step, the support is enveloped with the matrix to bond the edge and the reinforcement with a predefined and homogeneous minimum thickness.
B29C 70/68 - 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 en incorporant ou en surmoulant des parties préformées, p. ex. des inserts ou des couches
A lockable telescopic actuator arranged to be in a locked state or in an unlocked state, the lockable telescopic actuator including: a body defining a cylindrical cavity; a piston mounted to slide in the cylindrical cavity; and a locking mechanism including a first locking segment, arranged to move from a locked position to an unlocked position. In the locked position the first locking segment is engaged with the piston to prevent the piston from moving. In the unlocked position the first locking segment is disengaged from the piston to allow the piston to move. A first shape memory alloy, SMA, biasing element configured to be extended or compressed such that when the first SMA biasing element is compressed the first locking element is biased into the locked position and when the first SMA bias element is extended the first locking element is biased into the unlocked position.
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
F15B 15/16 - Dispositifs actionnés par fluides pour déplacer un organe d'une position à une autreTransmission associée à ces dispositifs caractérisés par la structure de l'ensemble moteur le moteur étant du type à cylindre droit du type télescopique
91.
Method for three-dimensional or multilayer weaving of a fibrous structure and fibrous structure having a three-dimensional or multilayer weave
A fibrous structure intended to form the fibrous reinforcement of a part made of composite material includes a fibrous reinforcement densified by a matrix, the fibrous structure having a three-dimensional or multilayer weave between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The fibrous structure includes at least a first portion having a first type of weave and a second portion, continuing on from the first portion, having a second type of weave, the warp yarns and the weft yarns having a degree of interweaving in the first type of weave that is greater than the degree of interweaving of the warp yarns and the weft yarns in the second type of weave.
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
Method for controlling a turbomachine equipped with a gas generator, the turbomachine including at least one electric machine forming a device for the injection/take-off of power onto/from one of the low-pressure/high-pressure rotating shafts of the gas generator. Said method has steps included in a loop which include determining, for at least one shaft and according to a speed setpoint, of a variation dU in a power command; determining, for all of the electric machines as a whole and according to an injection/take-off setpoint, of a variation dPelec in a power injection/take-off command; and determining a command including components pertaining to fuel flow rate and to power injection/take-off for each electric machine, according to the variations dU dPelec, and according to the operational limits of the turbomachine.
F02C 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance
F02C 3/113 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance aves des transmissions de puissance variables entre les rotors
93.
DISTRIBUTED PROPULSION WITH OFFSET PROPULSION MODULES
INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPAC (France)
SAFRAN (France)
SAFRAN AIRCRAFT ENGINES (France)
Inventeur(s)
Gonidec, Patrick
Aguirre, Miguel Angel
Duplaa, Sébastien
Robic, Bernard
Rodriguez, Benoit
Tantot, Nicolas Jérôme Jean
Abrégé
A propulsion unit including: a gas generator including a compressor, a combustion chamber, a turbine, at least two compressed-air propulsion modules, each propulsion module including: a fan, a compressed-air turbine configured to drive the rotation of the fan, a manifold allowing the respective turbines of the compressed-air propulsion modules to be supplied with compressed air, wherein the manifold is configured to collect and mix: at least a portion of the flow that has passed through the combustion chamber of the gas generator, typically as it leaves the turbine, and at least one bypass flow, the bypass flow being a flow of air which is not passed through the combustion chamber of the gas generator.
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
F04D 17/02 - Pompes à flux radial spécialement adaptées aux fluides compressibles, p. ex. pompes centrifugesPompes hélicocentrifuges spécialement adaptées aux fluides compressibles ayant des étages non centrifuges, p. ex. centripètes
An aircraft braking system including a braking actuator; a primary hydraulic fluid supply circuit configured to supply pressurised hydraulic fluid to the braking actuator; and a secondary hydraulic fluid supply circuit including a piezoelectric pump configured to supply pressurised hydraulic fluid to the braking actuator.
An anti-lock braking system for an aircraft, including a braking actuator configured to apply a braking pressure to a brake stator, and a piezoelectric actuator connected in series with the braking actuator. The piezoelectric actuator is operable to modify the braking pressure applied to the brake stator to provide anti-skid protection.
B64C 25/46 - Régulateurs de freinage pour empêcher le dérapage ou le capotage des aéronefs
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/36 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p. ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p. ex. accélération ou décélération comportant un régulateur de pression fluidique répondant à une condition de vitesse comportant un clapet-pilote sensible à une force électromagnétique
A fibrous texture for a blade has a three-dimensional weave between a first plurality of yarn layers and a second plurality of yarn layers, includes a blade aerofoil part extending between a first edge and a second edge. The texture includes a first part with at least three yarn layers of the first plurality of yarns and at least three yarn layers of the second plurality of yarns. Yarns of the two yarn layers of the first plurality of yarns bind yarns of the second plurality of yarns to the two yarn layers of the second plurality of yarns with a determined binding frequency.
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
97.
Stator part of a turbomachine comprising a blade and a fin defining between them a decreasing surface from upstream to downstream in the gas flow direction
A stator part of a turbomachine includes a platform, a blade, and a fin. The blade and the fin extend from the platform. The platform, an extrados of the blade and the fin define therebetween a gas flow channel. The channel has a section in a plane normal to an axis of the turbomachine, the section having a surface area, the surface area continuously decreasing from upstream to downstream with reference to a general gas flow direction through the turbomachine.
The invention relates to a fast overvoltage and slow overvoltage protection device (1) arranged in parallel with an alternating current generation channel (L1-L2), the protection device (1) comprising: - a first current source (S1) comprising an input (S11) and an output (S12), the input (S11) of the first current source (S1) being connected to a first terminal (L1) of the generation channel; - a second current source (S2) comprising an input (S21) and an output (S22), the input (S21) of the second current source (S2) being connected to a second terminal (L2) of the generation channel, the output (S22) of the second current source (S2) being connected to the output (S12) of the first current source (S1).
H02H 9/04 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion sensibles à un excès de tension
H03K 17/082 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension par réaction du circuit de sortie vers le circuit de commande
99.
POSITION DETECTOR FOR A SPATIAL GEARED STEPPING MOTOR
The invention relates to a rotating device (1) comprising a fixed part (2) and a rotary part (4) rotatable about an axis of rotation with respect to the fixed part (2), the rotating device (1) comprising an angular position detector (6) detecting the angular position of the rotary part (4) with respect to the fixed part (2), the angular position detector (6) comprising: - a magnet (62) integral with the rotary part (4), capable of generating a magnetic flux along a radial axis (A2) of the rotary part (4), - a magnetic field binary detector integral with the fixed part (2), configured to switch from a so-called open state to a so-called closed state when the magnetic flux of the magnet (62) is passing through the magnetic field binary detector.
G01D 5/252 - 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 électriques ou magnétiques sélectionnant un ou plusieurs conducteurs ou circuits parmi un certain nombre de conducteurs ou circuits, p. ex. en fermant des contacts une combinaison de conducteurs ou circuits
G01P 3/487 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions délivrés par des aimants rotatifs
G01P 3/484 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions délivrés par des interrupteurs à contacts mobiles
H01H 36/00 - Interrupteurs actionnés par la variation du champ magnétique ou champ électrique, p. ex. par le changement de la position relative d'un aimant et d'un interrupteur, par écran
H01H 19/00 - Interrupteurs actionnés par un organe moteur qui est rotatif autour de son axe longitudinal et qui est entraîné directement par un corps solide extérieur à l'interrupteur, p. ex. une main
H03K 17/00 - Commutation ou ouverture de porte électronique, c.-à-d. par d'autres moyens que la fermeture et l'ouverture de contacts
100.
Turbine engine assembly comprising a casing and an aerodynamic treatment member at the blade tips, and corresponding turbine engine
An assembly including a turbine engine casing, in particular for an aircraft, the turbine engine casing including an annular or cylindrical radially outer shell, provided with a radially inner surface, and an aerody-namic treatment member including a plurality of grooves distributed in a circumferential direction. The radially outer shell includes a circumferential recess in which the aerodynamic treatment member is removably mounted, the treatment member extending along at least one angular sector and having a shape that matches that of the circumferential recess, the treatment member including a circumferential opening into which the plurality of grooves open.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F04D 19/00 - Pompes à flux axial spécialement adaptées aux fluides compressibles
F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites