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
2.
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
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 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
6.
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.
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
9.
SYSTEM AND METHOD FOR CONDITIONING FUEL FOR AN AIR-BREATHING HYDROGEN ENGINE
A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.
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
11.
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
13.
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.
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
20.
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
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
22.
METHOD FOR DIMENSIONING A MULTI-POLE ORIENTED-FLUX MAGNETIC RING, AND ASSOCIATED ROTOR, ROTATING ELECTRIC MACHINE AND AIRCRAFT
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.
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.
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
26.
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
27.
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
28.
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
29.
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.
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
32.
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 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
35.
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
36.
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
39.
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
41.
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
45.
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
46.
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
47.
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
48.
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
49.
METHOD, DEVICE AND SYSTEM FOR MONITORING A TURBINE ENGINE
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
51.
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
53.
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
54.
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.
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
56.
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 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
59.
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
60.
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.
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
62.
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
64.
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
65.
METHOD FOR COATING A REFRACTORY ALLOY PART, AND THE PART THUS COATED
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
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
67.
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
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
69.
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
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
72.
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.
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
74.
NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE
A nickel-based superalloy including, in weight percentages, 5.5 to 7.5% of aluminum, 1.0 to 4.0% of tantalum, 0.50 to 3.0% of titanium, 3.0 to 7.0% of cobalt, 8.0 to 12.0% of chromium, 0 to 2.5% of molybdenum, 0 to 3.0% of tungsten, 0.50 to 2.8% of rhenium, 0.05 to 0.25% of hafnium, 0 to 0.15% of silicon, the remainder consisting of nickel and unavoidable impurities.
A power supply system comprising: a first converter module comprising an AC/DC converter and being arranged to produce an intermediate voltage from an input voltage; a second converter module comprising a DC/DC converter and being controllable to use the intermediate voltage to produce selectively at least two distinct output voltage levels; and a control unit arranged to acquire a flight parameter representative of the flight phase and/or of the altitude, and to control the power supply system in such a manner that the second converter module delivers to each electrical system a power supply voltage that depends on the flight parameter and on said electrical system, and that is equal to one of the output voltage levels.
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
76.
METHOD, DEVICE AND COMPUTER PROGRAM FOR ESTIMATING A SPEED OF A WHEELED VEHICLE
INSTITUT NATIONAL DE RECHERCHE EN INFORMATIQUE ET EN AUTOMATIQUE (France)
Inventeur(s)
Abboud, Dany
Barrau, Axel
Leiber, Maxime
Marnissi, Yosra
Abrégé
The present invention relates to a method for estimating a speed (v) of movement of a wheeled vehicle, wherein a frequency trajectory (ξt) representative of the speed (v) of a wheel (RO) of the vehicle (VE) in a filtered spectrogram (S(ft, t)) is estimated (E5) as follows: a probability (pZt|ξt) of observation of the trajectory (ft) is estimated (E51) on the basis of a computed amplitude of the filtered spectrogram (S(ft, t)), an a posteriori observation law (pZt|ξt) proportional to the product of the probability (pξ) and of the probability (pξ|Z)′ is estimated (E52), the trajectory (ft) is estimated (E53) on the basis of the law (pξ|Z), and the speed (v) of movement of the wheel of the vehicle is estimated (E6) on the basis of the trajectory (ξt).
G01P 3/48 - 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
G01H 1/10 - Mesure des vibrations dans des solides en utilisant la conduction directe au détecteur les vibrations étant torsionnelles
G01N 29/46 - Traitement du signal de réponse détecté par analyse spectrale, p. ex. par analyse de Fourier
G01P 3/50 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer une vitesse linéaire
09 - Appareils et instruments scientifiques et électriques
38 - Services de télécommunications
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Appareils et instruments optiques; appareils et instruments scientifiques; appareils et instruments pour la navigation; logiciels (programmes enregistrés); appareils de transmission d'images; lunettes 3D; lunettes (optique); appareils d'enregistrement d'images; masques de plongée; équipements de traitement de données; ordinateurs; logiciels de jeux; ordiphones [smartphones]; casques de réalité virtuelle; dispositifs d'affichage électroniques transparents pour la fourniture d'informations de fonctionnement et de navigation à des pilotes et membres d'équipage d'aéronefs; dispositifs d'affichage tête haute (HUD) sous forme d'écrans d'affichage électroniques transparents pour la fourniture d'informations de fonctionnement et de navigation à des pilotes et membres d'équipage d'aéronefs. (1) Services d'affichage électronique (télécommunications).
(2) Mise à jour de logiciels; conception de logiciels; élaboration (conception) de logiciels; recherches scientifiques; conception de systèmes informatiques; conseils en technologie de l'information; développement de logiciels; recherches technologiques; programmation pour ordinateurs.
09 - Appareils et instruments scientifiques et électriques
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Electronic bulletin board services being telecommunication services. Optical apparatus and instruments, namely, eyeglass lenses; scientific apparatus and instruments, namely, thermal sensors, temperature sensors, pressure sensors, position sensors, proximity sensors, sensors chips, tracking sensors; navigation apparatus and instruments, namely, transmitters, calculators, compasses for measuring, GPS (global positioning systems) automatic steering for apparatus, safety and security lights; recorded computer software for use on augmented reality systems for pilot on land, air and sea vehicles; image transmission apparatus; 3d spectacles; spectacles; image recording equipment namely apparatus for recording of images; diving masks; data processing equipment; computers; downloadable computer game software; smartphones; virtual reality headsets; heads-up displays (HUDs) in the nature of transparent electronic display devices for providing aircraft crew members and pilots with navigational and operational information; head-up display (HUD) devices in the form of transparent electronic display screens for providing aircraft crew members and pilots with navigational and operational information. Updating of computer software; software design; software development and design; scientific research; computer system design; advice regarding information technology namely, IT consulting services relating to installation, maintenance and repair of computer software; software development; technological research in the field of augmented reality computer hardware systems; programming for computers.
OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES (France)
Inventeur(s)
Sallot, Pierre Jean
Huvelin, Zhao
Perrut, Mikael
Bachelier-Locq, Agnès
Abrégé
The present disclosure relates to the technical field of TiAl intermetallic foundry alloys. More particularly, it relates to such an alloy comprising:
44≤Al≤47 at. %;
0
A method for manufacturing a turbomachine component made of composite material includes the step of creating a shaped fibrous preform by three-dimensional weaving of filaments to create a fibrous texture which is wound in several superposed layers onto a mandrel of a profile corresponding to that of the component that is to be manufactured, so as to obtain the fibrous preform of a shape corresponding to that of the component that is to be manufactured, the filaments being divided into warp filaments and weft filaments, the warp filaments being interwoven with the weft filaments in a three-dimensional weave. The method further includes the step of creating a stiffening zone in the fibrous preform, the stiffening zone being formed of at least one layer of warp filaments not interwoven with weft filaments that is interposed between the interwoven warp filaments and weft filaments.
F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
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
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
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/12 - 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 caractérisés par la disposition relative des fibres ou filaments des couches adjacentes
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring (201) a priori values of kinematic variables of the navigation device, determining (202) respective current values of kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, determining (203) a correction, updating (204) the respective current values of the kinematic variables based on the correction and on the current uncertainty matrix.
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.
METHOD FOR ASSISTING WITH THE NAVIGATION OF A VEHICLE
Method, navigation device and computer program product for assisting with the navigation of a vehicle equipped with a navigation device, comprising the following steps: acquiring a priori values of kinematic variables of the navigation device, determining (202) respective current values of the kinematic variables of the navigation device and a current uncertainty matrix representative of an uncertainty of the respective current values of the kinematic variables, based on respective previous values of the kinematic variables, a previous uncertainty matrix representative of an uncertainty of the respective previous values of the kinematic variables and a model of Earth's gravity experienced by the navigation device, the modeled gravity increasing with an altitude of the navigation device.
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
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
SORBONNE UNIVERSITE (France)
ECOLE NATIONALE SUPERIEURE D'ARTS ET METIERS (ENSAM) (France)
CONSERVATOIRE NATIONAL DES ARTS ET METIERS (France)
Inventeur(s)
Ducousso, Mathieu Loïc
Cuenca, Edouardo
Coulouvrat, François
Berthe, Laurent
Abrégé
A method for focusing acoustic waves on an interface between two layers of a multilayer structure includes providing laser means able to emit a laser beam toward an exterior surface of the multilayer structure to produce a longitudinal wave from the centre of a laser-beam spot projected onto the exterior surface and a transverse wave from the periphery of said spot, determining the distance between said interface and the exterior surface, determining one or more propagation velocities of each of the longitudinal wave and the transverse wave in the one or more layers passed through by said waves to reach said interface, and determining a radius of the laser-beam spot depending on the one or more propagation velocities and on said distance so that the time taken by the longitudinal wave to reach said interface is equal to three times the time taken by the transverse wave to reach said interface.
A surface heat exchanger for an aircraft turbomachine includes a support wall, a panel parallel to the support wall, partitions connecting the wall to the panel to define channels in which an air flow flows, and fins situated in the channels. The panel has a central part parallel to the wall and a downstream part that is inclined with respect to the wall. An upstream end is connected to the central part and a downstream end is situated at a distance from the wall and delimits with the latter a main outlet of the channels. The downstream part has fixed flaps disposed one after another so as to delimit between one another additional outlets of the channels.
F28D 1/053 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture avec des canalisations d'échange de chaleur immergées dans la masse du fluide avec canalisations tubulaires les canalisations étant rectilignes
F28F 1/32 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire et s'étendant transversalement les moyens ayant des parties engageant d'autres éléments tubulaires
A turbojet includes in succession, from upstream to downstream in the flow direction of a primary air stream: a low-pressure casing, an intermediate casing, and a high-pressure casing that are longitudinally aligned and which jointly delimit an internal annular passage for the circulation of the air stream. The intermediate casing delimits a portion of the annular passage called a gooseneck and includes: an air discharge system able to extract air from the air stream circulating in a first zone of the gooseneck and to discharge it outside the passage, and an air extraction system able to extract air circulating in a second zone of the gooseneck for an air conditioning system, the second air extraction zone being located downstream of the first air extraction zone.
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to provide a separation; c) the cut preform is deformed so as to provide an orifice then comprising a first and a second open end (27a, 27b); d) the deformed preform is placed into an injection mould; e) a resin is injected in order to impregnate the whole of the deformed preform; f) the resin is polymerised; and g) a composite part is extracted from the mould; characterised in that: h) a flexible mandrel (31) with a predetermined shape is positioned in the orifice before the injection step e); i) the flexible mandrel (31) is removed after step f) or the demoulding step g), the composite part then having a hollow core (25).
F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
B29C 37/00 - Éléments constitutifs, détails, accessoires ou opérations auxiliaires non couverts par le groupe ou
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]
This invention relates to a superconducting electric machine (1), for example with axial flux or with radial flux, comprising an inductor (3) comprising superconducting pellets (7) circumferentially distributed around an axis (X) of the electric machine (1) and a flux barrier (12) comprising a superconducting material, said flux barrier (12) being centered on the axis (X) of rotation and extending radially inward of the superconducting pellets (7).
The present invention relates to a superconducting electric machine (1) comprising an inductor (3) having: —superconducting pellets (7) circumferentially distributed about an axis (X) of the electric machine (1), —an armature (2) comprising coils (5), each coil (5) having a circumferential radially inner edge (10) and a circumferential radially outer edge (9), and—at least one flow barrier (12, 12′) extending circumferentially with respect to the axis (X), each flow barrier (12) extending between the superconducting pellets (7) and the armature (2) so as to at least partially cover at least one of the radially outer edge (9) and the radially inner edge (10) of all or part of the coils (5) of the armature (2).
B22D 11/112 - Traitement du métal liquide par refroidissement accéléré
B22D 11/00 - Coulée continue des métaux, c.-à-d. en longueur indéfinie
B22D 11/041 - Coulée continue des métaux, c.-à-d. en longueur indéfinie dans des moules sans fond pour la coulée verticale
B22D 11/14 - Installations pour la coulée continue, p. ex. pour tirer la barre vers le haut
B22D 21/00 - Coulée de métaux non ferreux ou de composés métalliques, dans la mesure où leurs propriétés métallurgiques affectent le procédé de couléeUtilisation de compositions appropriées
B22D 27/04 - Action sur la température du métal, p. ex. par chauffage ou refroidissement du moule
B22D 41/015 - Moyens de chauffage avec chauffage extérieur, c.-à-d. la source de chaleur ne faisant pas partie de la poche
C22C 1/02 - Fabrication des alliages non ferreux par fusion
The invention relates to a method for monitoring the state of mechanical components such as bearings and gears on a shaft line equipping a rotating machine. Said method includes a step of obtaining at least one measurement yc[k] of the absolute acceleration of the shaft, as well as a set of steps of: obtaining a value fr[k] of the rotational frequency of the shaft, determining a matrix H[k] making it possible to define a state model described by: [k+1]=x[k]+w[k]etY[k]=[(y_c [k])¦SE[k]]=H[k]×x[k]+v[k], determining an estimator of the vector x[k] based on data from the state model, said set of steps further including, for at least one mechanical component, steps of: determining, from said estimator, a quantity characteristic of a contribution of said component to the vector Y[k], comparing said quantity with a threshold, detecting a possible defect of said at least one mechanical component.
The present invention relates to a method for manufacturing a part, comprising the steps of chemically etching, in a wet acid medium, at least a portion of a surface of a substrate made of a monocrystalline superalloy, comprising at least one element chosen from rhenium and ruthenium, the substrate having a γ-γ′ phase, the substrate having an average mass fraction of rhenium and/or ruthenium greater than or equal to 3%, the chemical etching being done in such a way that the average mass fraction of rhenium and/or ruthenium over the portion of the surface of the substance is less than 2%, and a step of depositing on the portion of the substrate a protective coating having a γ-γ′ phase and an average mass fraction of rhenium and/or ruthenium of less than 1%.
09 - Appareils et instruments scientifiques et électriques
Produits et services
Electric and electronic apparatus, instruments and equipment for navigation, guidance, remote control, automatic piloting and stabilization of air, land, sea and space vehicles; hybrid and inertial navigation apparatus, instruments and equipment for land, sea, aeronautical and space vehicles; gyroscopes, gyrometers; miniature, micro-machined, simple or networked sensors and actuators; gyroscopic sensors; gyrometric sensors; vibrating sensors; accelerometer sensors; inertial sensors; gyrocompass; directional compasses; electric sensors; photoelectric sensors; optical sensors; opto-mechanical sensors; sensors for determination of position, rotation, speed, acceleration and temperature; sensors for determination of temperatures, positions, rotations and distances; micro-electromechanical systems (MEMS), namely, micro-machined fine structured elements and microsystems incorporating such sensors, actuators and/or elements; data processing systems; semi-conductors for micro-electronic systems; inertial power unit; recorded software.
93.
Propulsion system with downstream section having deformable shape-memory material and actuators extending in different consecutive angular sectors
b), both of which are made of a deformable shape memory material, and in that the downstream end (21) includes pneumatic or hydraulic actuators (23, 23′) extending in different consecutive angular sectors about said axis (X), each actuator being independently actuatable and being configured to deform, in a direction that extends radially in relation to said axis (X) and is centered angularly in relation to its angular sector, under the effect of a predetermined control pressure.
F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
B64C 15/02 - Commande de l'assiette, de la direction du vol ou de l'altitude par jets réactifs les jets étant des jets propulsifs
94.
System for controlling discharge doors of a turbomachine
A system for controlling discharge doors of a turbomachine includes: a ring and a device connecting the ring to each discharge door. The ring is made up of bars connected end-to-end by rotary links ensuring that a bar pivoting on itself causes the other bars to pivot on themselves, with each discharge door being connected to a corresponding bar in order to open or close when this bar pivots.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
F04D 27/00 - Commande, p. ex. régulation, des pompes, des installations ou des systèmes de pompage spécialement adaptés aux fluides compressibles
Method for checking the compliance of a workpiece, comprising the following steps: estimating a risk of non-compliance of characteristic on the basis of a law of probability associated with the characteristic; and verifying whether the estimated risk of non-compliance satisfies a decision criterion and, if so, declaring that the workpiece is compliant for characteristic; if not, measuring a value of the characteristic, determining whether or not the workpiece is compliant based on the measured value, and updating the law of probability associated with characteristic based on the measured value.
A control circuit for a first switch includes at least one transistor, the first switch being arranged in series with a second switch in an inverter arm of an electrical power supply device supplying a load connected to the mid-point of the series arrangement of the first and second switch. The control circuit is configured to adjust the gate-source voltage of the at least one transistor of the first switch according to a control scheme including, during a deactivation period of the first switch, the increase of the gate-source voltage in a time window including the deactivation of the second switch and the reduction of the gate-source voltage in a time window including the activation of the second switch.
H02M 7/539 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur avec commande automatique de la forme d'onde ou de la fréquence de sortie
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H02M 1/088 - Circuits spécialement adaptés à la production d'une tension de commande pour les dispositifs à semi-conducteurs incorporés dans des convertisseurs statiques pour la commande simultanée de dispositifs à semi-conducteurs connectés en série ou en parallèle
H03K 17/0812 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension sans réaction du circuit de sortie vers le circuit de commande par des dispositions prises dans le circuit de commande
97.
Hybrid turbofan engine for an aircraft, comprising a motor/generator cooled by heat pipes
A hybrid turbofan engine for an aircraft, comprising a fan, an electric motor/generator and a gas generator, the engine comprising, between the fan and a splitter that separates the flows, an internal wall for delimiting an air duct, situated upstream of inlet guide vanes of a primary duct, and, upstream of outlet guide vanes, an internal upstream wall for delimiting a secondary duct, the motor/generator having a stator carried by a stator support fixed to a stator part of the engine. According to the invention, a plurality of heat pipe for cooling the motor/generator are provided, each heat pipe having an evaporation section fixed to the stator support, and a condensation section fixed to the internal wall or the internal upstream wall.
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
F02C 7/12 - Refroidissement des ensembles fonctionnels
F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
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
98.
IMPROVED METHOD FOR MANUFACTURING A PART BY ADDITIVE MANUFACTURING
Method for manufacturing an aeronautical part by additive manufacturing, the part to be manufactured extending around a central axis and comprising at least two walls angled with respect to one another and connected to one another by means of at least one connection section comprised in a connection plane perpendicular to the central axis, the method comprising: providing a digital model of the part to be manufactured, orienting the digital model with respect to a vertical construction direction of the part so that the central axis of the part has an angle β of between 0.1° and 1°; and manufacturing the part by additive manufacturing from the digital model obtained in the orientation step.
B22F 10/80 - Acquisition ou traitement des données
B22F 10/47 - Structures destinées à soutenir des pièces ou des articles pendant la fabrication et retirées par la suite caractérisées par des caractéristiques structurelles
B22F 10/66 - Traitement de pièces ou d'articles après leur formation par des moyens mécaniques
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Schneider-Die-Gross, Julien Paul
Jailin, Clément
Mendoza Quispe, Arturo
Roux, Stéphane
Abrégé
Method for processing a plurality of X-ray tomography volume images each associated with a part, the plurality of volume images comprising a reference volume image, including:
a step of correlating volume images to obtain a displacement field between each image and the reference image, to obtain a plurality of displacement fields minimizing the difference between the volume images,
a processing by a dimensionality reduction method of the plurality of the image displacement fields to express them according to eigenmodes, and
a statistical analysis of the fields expressed according to the eigenmodes.
A stator assembly including plural stator vanes distributed around an axis of revolution of the stator assembly, a chord of the stator vane, taken at a root of the stator vane, not overlapping, in the direction of the axis of revolution, a chord of an adjacent stator vane, taken at a root of the adjacent stator vane, and a chord of the stator vane, taken at a tip of the stator vane, overlapping, in the direction of the axis of revolution, a chord of the adjacent stator vane, taken at a tip of the adjacent stator vane.
