Abrégé

A turboshaft engine for an air-craft including a gas generator including a compressor, a combustion chamber and an expansion turbine; a power turbine rotating a power take-off by a reduction gear; a heat exchanger including a first circuit and a second circuit. The compressor includes a first shaft rotated by a second shaft of the expansion turbine by a trans-mission mechanism, the transmission mechanism and the reduc-tion gear forming part of a gearbox which is arranged axially at a front end of the turboshaft engine, such that the compressor is arranged axially between the gearbox and the power turbine.

Classes IPC  ?

• F02C 3/107 - 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
• F02C 7/10 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement au moyen d'échangeurs de récupération de chaleur
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• 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

Abrégé

An aircraft turbomachine has a gas generator that includes, along a longitudinal axis (X), at least one compressor, a combustion chamber, and at least one turbine. The turbomachine further includes at least one duct for supplying liquid to at least one member chosen from an oil jet and a fuel injector. The duct (20) has rectilinear portions and bent portions and includes at least one region in which the liquid is liable to coke. The turbomachine also includes at least one turbulence element in the at least one region in the duct.

Classes IPC  ?

• F02C 7/30 - Prévention de la corrosion dans les espaces balayés par les gaz
• 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
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible

Abrégé

A method for regulating the speed of a propulsion device of an aircraft including: the propulsion device and a gearbox MGB; the heat engine and at least one electric motor, mounted in parallel on the MGB, the heat engine having a fuel circuit; main and backup regulation systems, and a regulation system, each capable of regulating the speed of the heat engine or the electric motor, respectively; a control system of the aircraft, capable of sending a speed or power setpoint to each of the regulation of the heat engine and the electric motor. The method includes: sending a speed setpoint NM2ref to the regulation system of the electric motor, the regulation system sending a power command PM2*, to obtain an instantaneous power PM2m; simultaneously, sending a speed or power command to the backup regulation system of the heat engine, the backup regulation system sending a selected fuel flow command QCarbAux* to the fuel circuit of the heat engine.

Classes IPC  ?

• B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
• B64D 31/14 - Transmissions entre les dispositifs d'amorçage de la commande et les groupes moteurs

Abrégé

A method for checking the maximum power available to members of a propulsion system of an aircraft includes first members that are sized to compensate for the failure of second members of the propulsion system by delivering a maximum power to keep the aircraft in a safe operating range. The method includes the following steps for each of the first members: placing the first member in a state that is substantially equal to a maximum power state; adjusting the power delivered by the second member working in synergy with the first member so that the first member and the second member contribute to delivering the power required for the aircraft in the flight phase; determining the power delivered by the first member placed in the maximum power state; from the determined power, deducing information relating to the maximum power available to the first member.

Classes IPC  ?

• B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques

Abrégé

The present invention relates to a metal powder for a powder bed additive manufacturing process, the metal powder comprising a nickel-based alloy comprising at least 0.05% carbon, at least 14.25% cobalt, at least 14% chromium, at least 4% aluminium, at least 3.9% molybdenum, at least 3% titanium, at most 0.5% iron, at least 0.012% boron, at most 0.060% zirconium, at most 0.150% manganese, at most 0.2% silicon, at most 0.1% copper, at most 0.5 ppm bismuth, at most 5 ppm silver, at most 5 ppm lead, at most 25 ppm sulphur, at most 200 ppm oxygen, and at most 60 ppm nitrogen.

Classes IPC  ?

• C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
• B22F 1/05 - Poudres métalliques caractérisées par la dimension ou la surface spécifique des particules
• B22F 10/28 - Fusion sur lit de poudre, p. ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques
• B22F 10/66 - Traitement de pièces ou d'articles après leur formation par des moyens mécaniques
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 40/20 - Posttraitement, p. ex. durcissement, revêtement ou polissage
• B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive

Abrégé

The invention relates to a method for anticorrosion treatment of a magnesium alloy part, in which the part is immersed for a given duration in an anticorrosion aqueous solution having a given temperature and containing permanganate ions MnO4- and dihydrogen phosphate ions H2PO4-. According to the invention, the anticorrosion aqueous solution contains, prior to immersion of the part, a molar ion concentrate of permanganate ions [MnO4-] of greater than or equal to 0.18 mol/L and less than or equal to 0.32 mol/L, the pH of the anticorrosion aqueous solution is maintained for the given duration at a value of greater than or equal to 3.2 and less than or equal to 4.2, preferably greater than or equal to 3.4 and less than or equal to 4.0, by addition of phosphoric acid, and, after the given duration, the part is removed from the solution and rinsed with water.

Classes IPC  ?

• C23C 22/18 - Orthophosphates contenant des cations du manganèse
• C23C 22/73 - Traitement chimique de surface de matériaux métalliques par réaction de la surface avec un milieu réactif laissant des produits de réaction du matériau de la surface dans le revêtement, p. ex. revêtement par conversion, passivation des métaux caractérisé par le procédé

Abrégé

A device for controlling an airflow guiding system comprising: at least one vane movable in rotation about an axis of rotation between a first angle and a second angle, an actuator comprising a body inside which a piston is mounted in translation secured to an actuation rod, and a control rod comprising a downstream end connected to the axis of the vane, the actuator being configured to drive the control rod in movement between a first end position and a second end position of a nominal operating range and, in the event of breakdown of said device, to perform an over-stroke of the actuation rod into a safety position. A device for controlling an airflow guiding system comprising: at least one vane movable in rotation about an axis of rotation between a first angle and a second angle, an actuator comprising a body inside which a piston is mounted in translation secured to an actuation rod, and a control rod comprising a downstream end connected to the axis of the vane, the actuator being configured to drive the control rod in movement between a first end position and a second end position of a nominal operating range and, in the event of breakdown of said device, to perform an over-stroke of the actuation rod into a safety position. The device comprises a drive mechanism linking an upstream end of the actuation rod to an upstream end of the control rod, opposite to the downstream end.

Classes IPC  ?

• F01D 17/16 - 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 en obturant les injecteurs
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

122), and at least one electric starter coupled to each turboshaft engine; the propulsion system being designed to have a nominal mode in which the two turboshaft engines drive the rotor and air is bled/electricity is tapped from the two turboshaft engines, and an eco mode in which only the first turboshaft engine drives the rotor, the second turboshaft engine being in standby mode, and the air being bled/electricity being tapped only from the first turboshaft engine, the rotor having a setpoint speed in the two modes, the method comprising: - with the propulsion system in nominal mode, verifying compatibility between aircraft operating parameters and the eco mode; - if compatible and if a command to switch to an eco mode is received, stopping the bleeding of air/tapping of electricity from the second turboshaft engine and verifying compatibility between operating parameters of the first turboshaft engine and the eco mode; - if compatible, idling the second turboshaft engine so that its output shaft has a speed lower than that of the rotor; - verifying correct operation of the starter of the second turboshaft engine; - if correct, placing the second turboshaft engine in standby mode by interrupting a supply of fuel to the second turboshaft engine in order to switch to the eco mode.

Classes IPC  ?

• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant

Abrégé

The present disclosure relates to a propulsion assembly (4) for an aircraft (1) and to a method for the thermal management of such a propulsion assembly (4). The propulsion assembly (4) comprises a first engine (5a) with a heat exchanger (16a) through which an air duct (15a) passes, a second engine (5b), which is a heat engine, and an air interconnection duct (21) connecting the air duct (15a), downstream of the heat exchanger (16a) of the first engine (5a), to the second engine (5b). The thermal management method comprises the steps of heating, in the heat exchanger (16a) of the first engine (5a), an air flow circulating in the air duct (15a) passing through the heat exchanger (16a) of the first engine (5a), and diverting the heated air flow downstream of the heat exchanger (16a) of the first engine (5a), through the air interconnection duct (21), to the second engine (5b).

Classes IPC  ?

• B64D 33/10 - Disposition du radiateur
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64C 27/12 - Entraînements des rotors
• F01D 25/18 - Systèmes de lubrification
• 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
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 17/10 - Organes de commande terminaux

Produits et services

Generators for aircraft, compressors; machine coupling and transmission and propulsion components (other than for land vehicles); systems using propulsive and non-propulsive power (machines) for aircraft and component parts thereof included in this class, including turbines, motors, engines, thrusters, nacelles, thrust reversers; auxiliary power units for air vehicles (machines); lubrication systems for motors, engines and turbines of air vehicles (machines); test benches for motors, engines, turbines and other thrusters (machines) for aircraft. Electric and electronic apparatus and instruments namely generators and/or starters for fixed or mobile installations for aircraft; electric, electronic and magnetic pressure, speed, displacement, temperature, position and vibration sensors; electronic on-board or ground systems, apparatus and equipment for data and parameter acquisition and processing; electric and electronic maintenance and control equipment and hardware for generators, starters and integrated sets for generating propulsive and non-propulsive power. Sales services for propulsion and non-propulsion power systems (machines) for aircraft; administrative and commercial management of parts, replacement equipment for users of engines, systems, equipment and parts of aircraft; commercial advice on propulsion systems for airplanes, turbines; processing services for acquisition of data recorded during the operation of aircraft engines, systems, equipment and parts [office work]. Repair, overhaul, servicing and maintenance services for propulsive and non-propulsive power systems (machines) for aircraft and their component parts, including turbines, engines, thrusters, nacelles, thrust reversers; advisory services for definition and selection of tools for repair, overhaul, servicing, standardization and maintenance of aircraft systems, equipment and parts. Technical, scientific and industrial research; engineering; research and development (engineering work) in the aeronautical field; analysis of technical data; services provided by engineers relating to evaluations, estimates and research in connection with the technologies used in systems, equipment and parts of aeronautical vehicles; testing of machines and materials; design and development of software and computer programming; analysis and expertise services for aircraft equipment and parts; analysis and expertise of data recorded during the operation of aircraft engines, systems, equipment and parts; technical project studies in connection with aeronautical vehicles and their components, including motors and engines, aircraft engine pods, reactors, thruster units or reversers, aeronautical vehicles.

Abrégé

Disclosed is a lubrication/cooling system (100) for an aircraft, comprising: a first circuit (20), a second circuit (30), a third circuit (40) for circulating a lubricating and/or cooling fluid (13), a first pump (50) and a second pump (60) for circulating the lubricating and/or cooling fluid (13), a first tank (70) and a second tank (80), and a first heat exchanger (90), wherein the first tank (70) and the second tank (80) are fluidically connected. Also disclosed are a hydraulic enclosure for such a system (100) as well as a turbine engine and an aircraft comprising such a system and/or such an enclosure.

Classes IPC  ?

• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F01D 25/18 - Systèmes de lubrification
• F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F01D 25/12 - Refroidissement

Abrégé

Disclosed is a hybrid turbomachine (10), in particular for a rotary-wing aircraft, comprising a gas generator (13) having a first shaft (16), at least one electric machine (11) having a second shaft (17), and a rotating equipment (15) coupled to a third mechanical shaft (18). The hybrid turbomachine (10) further comprises a switching coupling means (20) configured to couple the third mechanical shaft (18) to the first mechanical shaft (16) or the second mechanical shaft (17), depending on the operating phases of the gas generator (13) and the electric machine (11).

Classes IPC  ?

• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 3/107 - 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
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

A rotor of an aircraft electric motor includes a shaft made of a first material, and a conductive assembly made of a second material different from the first material. The shaft includes a shoulder portion, the shoulder portion includes longitudinal notches. The notches include two contiguous notches radially superimposed in the shoulder portion, a first opening on a radially outer face of the shoulder portion, and a second opening connecting the two contiguous notches. The conductive assembly is a one-piece structure including a conductive bar that is positioned in one notch of the notches, and a skin that is fixed on the shoulder portion.

Classes IPC  ?

• H02K 17/16 - Moteurs asynchrones à induction avec des rotors à enroulement court-circuité à l'intérieur de la machine, p. ex. des rotors à cage
• B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
• H02K 15/00 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques

Abrégé

A system (2) for the transmission of propulsion power of a propulsion assembly (1) for an aircraft comprises means (12) for coupling a first rotating element (4) with a second rotating element (8), and an actuator (10) for moving the second rotating element (8) axially between a coupling position in which the coupling means (12) are engaged with one another, and a disengaging position in which the coupling means (12) are disengaged from one another. The actuator (10) comprises an actuating member (40) extending in a bore (8A) of the second rotating element (8) and cooperating with a drive device (42). A rolling bearing (44) is interposed between the actuating member (40) and an inner surface (8B) of the second rotating element (8) so as to secure the actuating member (40) and the second rotating element (8) to one another axially while allowing the second rotating element (8) to rotate freely relative to the actuating member (40). The rotor is kinematically connected to the rotor of an electric machine configured to receive propulsion power from the first rotating element (4).

Classes IPC  ?

• F16D 11/10 - Embrayages dans lesquels les organes ont des parties qui se pénètrent mutuellement actionnés par le déplacement axial d'une pièce non tournante avec organes d'embrayage mobiles selon l'axe uniquement

Abrégé

The present invention relates to a turbomachine element (1), comprising at least one blade (2) obtained by additive manufacturing, the blade (2) having a skin (4) and an internal lattice (6) allowing air circulation in the blade (2) and having an additive manufacturing support function for the skin (4).

Classes IPC  ?

• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• B22F 10/28 - Fusion sur lit de poudre, p. ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 25/12 - Refroidissement

Abrégé

A method for training a pilot to cope with a fault affecting one powertrain of a hybrid propulsion system for an aircraft. The aircraft includes, connected in parallel to a transmission unit, n powertrains (where n≥2), including a first and a second powertrain that are heterogeneous in nature. It involves, during a flight of the aircraft, simulating a fault affecting the first powertrain while, at the same time as performing the simulation, checking the status of the n powertrains of the propulsion system. If a fault affecting one of the n powertrains is detected, the simulation is halted and the instantaneous power delivered by at least one of either the first or the second powertrain is increased so that the sum of the instantaneous powers delivered by the n powertrains is ≥ a minimum total instantaneous power required for the aircraft to continue its flight.

Classes IPC  ?

• G09B 9/44 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p. ex. bancs d'entraînement au pilotage sans visibilité assurant la simulation dans un aéronef réel qui vole à travers l'atmosphère sans limitation de sa trajectoire
• B64D 27/33 - Aéronefs électriques hybrides
• G09B 9/46 - Simulateurs pour l'enseignement ou l'entraînement pour l'enseignement de la conduite des véhicules ou autres moyens de transport pour l'enseignement du pilotage des aéronefs, p. ex. bancs d'entraînement au pilotage sans visibilité l'aéronef étant un hélicoptère

Abrégé

The invention relates to a propulsion assembly (100) comprising a first and second engine (1, 2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric machine (30, 40) coupled to the gas generator (12, 22) only, a second electric machine (32, 42) coupled to the gas generator (12, 22) via a first coupling means (34, 44) when said machine rotates in a first direction, and coupled to the free turbine (11, 21) via a second coupling means (36, 46) when said machine rotates in a second direction, the first electric machine (30, 40) operating selectively in a motor or generator mode, the second electric machine (32, 42) operating in the motor mode when it rotates in the first direction, and selectively in the motor mode or the generator mode when it rotates in the second direction.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• B64D 27/33 - Aéronefs électriques hybrides
• 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
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 7/26 - DémarrageAllumage
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

A rotor of an aircraft electric motor includes a shaft made of a first material, and a skin made of a second material different from the first material. The skin includes two half-shells welded together, each half-shell of the two half-shells including a chamfer, and the chamfers assembling the two half-shells together. The shaft includes a shoulder portion the skin being fixed on the shoulder portion. The rotor further includes an interpenetration layer of the first material and of the second material, the interpenetration layer including an alloy of the first material and an alloy of the second material, the interpenetration layer being between the shaft and the skin.

Classes IPC  ?

• H02K 17/16 - Moteurs asynchrones à induction avec des rotors à enroulement court-circuité à l'intérieur de la machine, p. ex. des rotors à cage
• B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
• H02K 15/00 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques

Abrégé

The invention relates to a sensor (1) for determining a liquid level (NE) for an aircraft tank (100), the determining sensor (1) comprising a closure device (2) for closing a port (101) of the tank (100) and a measuring device (3), removably mounted on the closure device (2), comprising a liquid line (20) configured to convey liquid from the port (100) of the tank (100), and a member (21) for automatically sealing the liquid line (20) if the measuring device (3) is not mounted on the closure device (2), the measuring device (3) comprising at least one pressure measuring member (30) configured to measure a pressure difference between the liquid pressure (P1) in the liquid line (20) and a reference pressure (P2) in order to deduce the liquid level (NE) thereof.

Classes IPC  ?

• G01F 23/16 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme par mesurage de la pression les dispositifs d'indication, d'enregistrement ou d'alarme étant actionnés par des moyens mécaniques ou hydrauliques, p. ex. en utilisant un gaz, du mercure ou un diaphragme comme élément de transmission, ou par une colonne de liquide
• B64D 1/16 - Largage en vol d'une matière poudreuse, liquide ou gazeuse, p. ex. pour la lutte contre l'incendie
• G01F 22/02 - Procédés ou appareils pour la mesure du volume des fluides ou des matériaux solides fluents, non prévus ailleurs comportant un mesurage de pression
• G01F 23/18 - Indication ou mesure du niveau des liquides ou des matériaux solides fluents, p. ex. indication en fonction du volume ou indication au moyen d'un signal d'alarme par mesurage de la pression les dispositifs d'indication, d'enregistrement ou d'alarme étant actionnés électriquement

Abrégé

A turboprop includes a propeller, a propeller shaft carrying the propeller, the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine having at least a first configuration in which it is mechanically coupled to the propeller shaft and at least one oil pump configured to supply a hydraulic circuit for adjusting the pitch of the propeller. The oil pump is configured to be electrically operated. An aircraft can include such a turboprop and methods can control such a turboprop and such an aircraft.

Classes IPC  ?

• B64D 35/021 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques
• B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
• B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement

Abrégé

A longitudinal-axis (X) dihydrogen injection device is configured to be mounted on an annular bottom of an annular combustion chamber of a turbomachine. The injection device includes an inner channel for dihydrogen circulation and an outer annular channel for circulation of a mixture of at least air. The inner channel and the outer annular channel are coaxial. An inner swirler is housed in the inner channel and an outer swirler is housed in the outer annular channel. A downstream end of the inner channel is arranged upstream, at a distance r, from a downstream end of the outer annular channel. With this dihydrogen combustion, polluting carbon emissions such as carbon monoxide, unburned hydrocarbons or even fine and smoke particles can be eliminated.

Classes IPC  ?

• F23D 14/24 - Brûleurs à gaz sans prémélangeur, c.-à-d. dans lesquels le combustible gazeux est mélangé à l'air de combustion à l'arrivée dans la zone de combustion avec des conduits d'alimentation en air et en gaz séparés, p. ex. avec des conduits disposés parallèlement ou se croisant au moins un des fluides étant soumis à un mouvement tourbillonnant
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible

Abrégé

The invention relates to a metal powder for an additive manufacturing process, the metal powder comprising an alloy comprising by weight between 20% and 24% chromium, between 20% and 24% nickel, between 13.00% and 16.00% tungsten, between 0.02% and 0.12% lanthanum, between 0.05% and 0.15% carbon, between 0.20% and 0.50% silicon, at most 1.25% manganese, at most 3.00% iron, at most 0.015% sulfur, at most 0.020% phosphorus, at most 0.0001% bismuth, at most 0.0010% silver, at most 0.0010% lead, at most 0.015% boron, at most 0.0250% oxygen, at most 0.0200% nitrogen and less than 0.050% other elements in total, the balance being cobalt.

Classes IPC  ?

• C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
• B22F 1/052 - Poudres métalliques caractérisées par la dimension ou la surface spécifique des particules caractérisées par un mélange de particules de dimensions différentes ou par la distribution granulométrique des particules
• 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 10/28 - Fusion sur lit de poudre, p. ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
• B22F 10/366 - Paramètres de balayage, p. ex. distance d’éclosion ou stratégie de balayage
• B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques

Abrégé

The invention relates to a metal powder for an additive manufacturing method, the metal powder comprising an alloy comprising, by weight, between 23% and 24.5% of chromium, between 9% and 11% of nickel, between 6.5% and 7.5% of tungsten, between 3% and 4% of tantalum, between 0.55% and 0.65% of carbon, between 0.3% and 0.5% of zirconium, between 0.15% and 0.25% of titanium, at most 2% of iron, at most 0.3% of silicon, at most 0.1% of manganese, at most 0.1% of copper, at most 0.015% of sulfur, at most 0.015% of phosphorus, at most 0.01% of boron, at most 0.025% of oxygen, at most 0.020% of nitrogen and at most 0.010% of hydrogen and less than 0.050% of other elements in total, the remainder being cobalt.

Classes IPC  ?

• C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
• B22F 1/05 - Poudres métalliques caractérisées par la dimension ou la surface spécifique des particules
• 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
• B33Y 40/20 - Posttraitement, p. ex. durcissement, revêtement ou polissage
• B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
• C22C 19/07 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de cobalt
• B22F 10/28 - Fusion sur lit de poudre, p. ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 10/36 - Commande ou régulation des opérations des paramètres du faisceau d’énergie
• B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques
• B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• 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
• B22F 10/366 - Paramètres de balayage, p. ex. distance d’éclosion ou stratégie de balayage
• B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser

Abrégé

An assembly for a turbomachine includes at least one turbine having a turbine disc with an internal bore and an annular cavity which is arranged upstream of the disc. The assembly further includes a fire safety system with a cooling device that supplies the cavity with cooling air via injection means. The fire safety system includes means that divide the annular cavity into first and second cavities. A cooling air speed is maintained at the outlet of the injection means and the cooling air in the first cavity is guided to the internal bore of the turbine disc. A diffuser co-operates with the injection means and an annular cover co-operates with the diffuser and covers first attachment members arranged in the cavity. A radially outer surface of the cover at least partially guides the cooling air at the outlet of the diffuser.

Classes IPC  ?

• F02C 7/25 - Prévention ou protection contre l'incendie
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• F01D 25/12 - Refroidissement

Abrégé

A fuel supply circuit of an aircraft engine includes a centrifugal pump mechanically coupled with an engine shaft delivering mechanical power. The circuit further includes at least one electromagnetic pump including at least one stator delimiting an annular internal volume in which is present a rotor able to drive a fluid, a plurality of magnets annularly distributed on the rotor and at least a plurality of coils annularly distributed inside the stator face-to-face with the magnets. The rotor is connected to the engine shaft by a one-way clutching element.

Classes IPC  ?

• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F02C 7/26 - DémarrageAllumage
• F02C 9/30 - Commande de l'alimentation en combustible caractérisée par un débit variable d'une pompe à combustible

Abrégé

The invention relates to a method for starting an aeronautical turbine engine having a free turbine and a single-spool gas generator, wherein, in order to ensure, under the control of a computer for controlling the turbine engine, the turbine engine is started only from a battery delivering a nominal DC voltage of 28 V, two electric machines coupled to the same accessory drive mechanically linked to the gas generator of the turbine engine and connected in parallel to the battery are actuated sequentially, the first electric machine being started with a starting torque enabling an increase in the speed of the gas generator with a given minimum acceleration and the second electric machine being started only after the ignition of the combustion chamber of the gas generator has been detected and only before a critical speed corresponding to the maximum resisting torque of the gas generator has been reached, the sum of the starting torques (40) produced by the two electric machines being sufficient to ensure, at all times, that the torque margin M at the maximum drag point B corresponding to the maximum resisting torque (42) of the generator is positive.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02N 11/00 - Démarrage des moteurs au moyen de moteurs électriques

Abrégé

The invention relates to a method for starting an aeronautical turbine engine of a twin-engine aircraft, the aeronautical turbine engine having a free turbine and a single-spool gas generator and comprising two independent electrical networks each being provided with a 28 V battery (BAT1, BAT2) selectively powering a starter-generator (S/G 1, S/G 2), wherein, in order to ensure, under the control of a computer for controlling the turbine engine (EECU), the turbine engine is started first with a voltage of 28 V by connecting the two batteries in parallel and then with a voltage of 56 V by connecting them in series, while the gas generator is prevented from accelerating at an excessive speed, the two batteries are connected in series only when the combustion chamber of the gas generator has been ignited and the speed of the gas generator is higher than a predetermined speed threshold NI, which makes it possible to provide, by the batteries being connected in series, a positive acceleration margin at the maximum drag point of the gas generator.

Classes IPC  ?

• F02C 7/268 - Entraînement du rotor pour le démarrage

Abrégé

The invention relates to a device (12) for centring and rotationally guiding a shaft line (14) of a turbomachine; said device (12) comprising: - a first inner ring (16) fixed to the shaft line, a first outer ring (18), a first ball bearing (20) arranged between the first inner ring (16) and the first outer ring (18), a first support (22) supporting the first outer ring, - a second inner ring (24) fixed to the shaft line, a second outer ring (26), a second bearing (28) arranged between the second inner ring (24) and the second outer ring (26), and a flexible cage (30) supporting the second outer ring. The first support (22) has a stiffness greater than the stiffness of the flexible cage (30), and the second bearing (28) is spaced apart from the first ball bearing (20) by a predefined axial spacing (E).

Classes IPC  ?

• F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
• F02C 7/06 - Aménagement des paliersLubrification
• F16C 19/54 - Systèmes formés d'une pluralité de paliers à frottement de roulement
• F16C 27/04 - Roulements à billes ou à rouleaux, p. ex. à organes de roulement élastiques
• F16C 35/04 - Supports rigides de paliersCorps de paliers, p. ex. calottes, couvercles dans le cas de roulements à billes ou à rouleaux

Abrégé

A rotor wheel for an aircraft turbine engine has a disc with a main axis and cells at its outer periphery. The cells extend along the axis, and each has a bottom and two side flanks. Vanes are mounted in the cells of the disc, each vane including a blade connected by a platform to a root mounted in one of the cells. Each root includes, at its radially inner end, a lobe with a first axial end having a circumferential notch and a second axial end having a radially inward facing stop configured to axially bear on a first face of the disc. An annular ring engages the notches of the vanes and is axially clamped against a second face of the disc. Each lobe has a radially inward facing projecting bulb configured to radially bear on the surface of the bottom of the corresponding cell.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F01D 5/32 - Verrouillage, p. ex. par des aubes terminales de verrouillage ou par des clavettes

Abrégé

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.

Classes IPC  ?

• F02C 7/268 - Entraînement du rotor pour le démarrage
• B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
• F02C 7/264 - Allumage

Abrégé

A disengageable coupling assembly (2) for an aircraft propulsion assembly (1) comprises a first shaft (4) and a second shaft (6); a coupling sleeve (8) movable between positions of coupling and of uncoupling the shafts; fluid chambers defined between the coupling sleeve and the shafts; a tube (10) extending into a bore of the coupling sleeve; and means (12) for selectively supplying a first selection of the chamber(s) (39, 52, 62) and a second selection of the chamber(s) (64) with a fluid (F), via the tube (10). When the coupling sleeve is in the coupling position, a pressure of the fluid in the first selection of chamber(s) applies to the coupling sleeve a first axial force (F1) that maintains the coupling. A pressure of the fluid (F) in the second selection of chamber(s) applies to the coupling sleeve a second axial force (F2) that brings the sleeve into the uncoupling position.

Classes IPC  ?

• F16D 25/08 - Embrayages actionnés par fluide avec organe actionné par fluide ne tournant pas avec l'organe d'embrayage
• F01D 3/02 - "Machines" ou machines motrices avec équilibrage des poussées axiales effectué par le fluide énergétique caractérisées par le fait d'avoir un écoulement de fluide dans une direction axiale et un autre dans la direction opposée
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• F01D 25/18 - Systèmes de lubrification
• F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant

Abrégé

Method for assisting the piloting of a rotary wing aircraft, the aircraft comprising at least two engines, a first engine capable of being placed on standby to ensure an operation of a second engine in the fuel-economy mode, called ECO mode, in which method, in order to reach a determined time between overhauls by limiting the wear of the second engine in the ECO mode, an engine control temperature (TC_PME) associated with the second engine is calculated in a flight computer as a function of a predefined maximum power (PME) of the second engine in ECO mode, the engine control temperature being representative of a current state of damage of the second engine and displayed on a flight screen for the attention of a pilot of the aircraft, so as to allow said pilot to keep below this engine control temperature.

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• B64D 43/00 - Aménagements ou adaptations des instruments
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• B64C 27/04 - Hélicoptères

Abrégé

The invention relates to a system for assisting with the piloting of a rotary wing aircraft (10), including two engines, a first engine of which is put on standby to ensure an operation in a fuel economy mode referred to as ECO, the second engine remaining active in the ECO mode, in which system, in order to enable the activation of the ECO mode by a pilot, a flight computer (20) is configured to check in real time the fulfilment of the following conditions to authorise the entry into ECO mode: the sum of the powers supplied by the engines is less than a continuous maximum power, the speed of rotation N2 of a free turbine of the second engine is greater than a predetermined speed threshold that is comprised between 80% and 90% of the maximum speed of the engine, the altitude of the aircraft is greater than a minimum value allowing a transient autorotation phase during the reactivation of the engine in standby in the event of failure of the active engine, and there is no critical failure.

Classes IPC  ?

• B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
• B64D 31/04 - Dispositifs amorçant la mise en œuvre actionnés par l'homme
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 27/14 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur des fuselages ou fixés à ceux-ci
• B64C 27/06 - Hélicoptères à rotor unique
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune

Abrégé

A device for guiding a main air flow (F1) for an aircraft turbine engine, the device including a first air flowing pipe of a main air flow, the first pipe having a main axis, a plurality of ejectors of a secondary air flow located within the first pipe and configured to eject a secondary air flow and force the flow of the main air flow into the first pipe, the ejectors being distributed around the main axis, and a second air flowing pipe located at the outlet of the ejectors and including one end which is connected to one end of the first pipe, wherein the second pipe includes a narrow end.

Classes IPC  ?

• F04F 5/16 - Pompes à jet, p. ex. dispositifs dans lesquels le flux est produit par la chute de pression causée par la vitesse d'un autre fluide le fluide inducteur étant un fluide compressible déplaçant des fluides compressibles
• F02C 7/057 - Commande ou régulation

Abrégé

A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

Classes IPC  ?

• B64D 35/022 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride
• B64C 27/12 - Entraînements des rotors
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

A propeller for an aircraft propulsion assembly extending longitudinally along an axis X. The propeller comprising a propeller cone, blades, a guide member extending longitudinally along the axis X and rotating as one with the propeller cone, the guide member being mounted outside the propeller cone in such a way as to form between them a guide path, the guide member having an upstream opening configured to convey a flow of air in the guide path and a downstream opening in such a way as to remove the flow of air downstream, the guide member having through-orifices through which extend the blades of the propeller and compressor vanes, which rotate as one with the propeller cone and which are positioned in the guide path in such a way as to generate an accelerated air flow.

Classes IPC  ?

• B64C 11/14 - Cônes de pénétration
• B64C 11/16 - Pales

Abrégé

The invention relates to a method for the automated control of the turbine engines of a rotary-wing aircraft during a failure on a turbine engine. Following detection of a failure on a first turbine engine of the aircraft, the automated control method comprises: - determining (102) the flight phase, and then, when the aircraft is in a phase other than a takeoff phase, - activating (110) operation of the turbine engines in a misaligned mode via a progressive decrease in the power of the first turbine engine and a progressive increase in the power of at least one second turbine engine, the progressive decrease in power of the first turbine engine and the progressive increase in power of the at least one second turbine engine being controlled in a complementary manner so as to maintain the rotational speed of the rotary wing at the speed of the rotational speed setpoint of the rotary wing, and - activating (120) an indicator of an engine anomaly, and - arming (130) a power limiter.

Classes IPC  ?

• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels
• F02C 9/46 - Commande de secours de l'alimentation en combustible

Abrégé

The invention relates to an electrical supply circuit of a turbine engine comprising a high-voltage DC circuit powered by a high-voltage DC source, connected to at least one DC/AC converter (3), the at least one DC/AC converter being respectively connected to at least one rotary electrical machine (2), the at least one rotary electrical machine being respectively coupled to at least one propeller of the turbine engine so as to rotate the at least one propeller or to generate electricity by the rotation of the at least one propeller, the circuit comprising at least one voltage step-up stage (3') connected between the high-voltage source and the at least one DC/AC converter (3), the at least one voltage step-up stage being capable of raising the voltage supplied to the at least one rotary electrical machine when the rotary electrical machine rotates the at least one propeller.

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
• H02M 1/00 - Détails d'appareils pour transformation
• H02M 3/00 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu
• H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
• H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
• H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif 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 avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs

Abrégé

The invention relates to a method for analysing the thermal history of a part (100) by means of an optical device, the part having a coating that includes a first marker, the optical device comprising a camera (20) and a light source (10), the method comprising: a calibration step, wherein a reference part having the same coating as the part undergoes a predetermined thermal cycle, a step of acquiring images of the part and a step of acquiring images of the reference part, a step of analysing the images of the part and a step of analysing the images of the reference part, a step of determining a transfer function, wherein a transfer function linking the temperature, the processed optical information and the spatial dimensions is determined, an interpretation step, wherein an image of the thermal history is calculated and the image of the thermal history represents the thermal history of the part according to the predetermined angle.

Classes IPC  ?

• G01K 11/12 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant le changement de couleur, de translucidité ou de réflectance
• G01K 11/14 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant le changement de couleur, de translucidité ou de réflectance de matériaux inorganiques
• G01K 11/20 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant des matériaux thermo-luminescents
• G01K 15/00 - Test ou étalonnage des thermomètres
• G01K 1/143 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers pour la mesure de la température de surfaces
• G06T 7/00 - Analyse d'image

Produits et services

Computer software and programs providing information relating to aircraft engines and to the operation, maintenance and repair of aircraft engines and/or parts and fittings therefor; Content management software; Databases on digital media; Databases on digital media featuring information relating to aircraft engines, the operation thereof, the repair, servicing, upkeep, maintenance and reconditioning of engines, modules and fittings for aircraft engines; All of the aforesaid goods being for use in and/or designed for aeronautics. Providing of information in relation to the following fields: Repair and maintenance of aircraft engines and components thereof. Providing of technical documentation relating to aircraft engines, the operation thereof, repair, servicing, upkeep, maintenance; Providing online information about industrial analysis and research services; Provision of technical information, in the field of aeronautics; Development (setting up) of databases; Design, installation, maintenance, updating of computer software relating to the aeronautical sector; Rental of computer software in the aeronautical sector; Scientific and technological services and research and design relating thereto, relating to the aeronautical sector: namely engineering; Analysis, surveying and processing of data recorded during the operation of aircraft engines and parts and fittings therefor; Providing of online technical documentation; Hosting of online databases featuring technical documentation; Storage of data; All the aforesaid services being used and/or for use in the aeronautical sector.

Abrégé

Disclosed is an aircraft electric or hybrid propulsion architecture comprising at least two propulsion trains, each propulsion train comprising at least one electric motor (Moteur1, Moteur2) powered by at least two power sources (Source1, Source2, Source3) of the propulsion architecture through at least two power-supply paths that each comprise at least one power converter, and one electrical protection delivering a DC voltage to an HVDC bus (HVDC bus1, HVDC bus2), each HVDC bus distributing this DC voltage to at least one electric motor through at least one power converter and one electrical protection, the propulsion architecture comprising power-supply paths that are at least partially dissimilar and preferably completely dissimilar.

Classes IPC  ?

• B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
• H02J 1/08 - Systèmes à trois filsSystèmes ayant plus de trois fils
• B64D 27/34 - Aéronefs tout électriques
• B64D 27/33 - Aéronefs électriques hybrides
• B64D 27/357 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles

Abrégé

The invention relates to an installation for transferring power (P) between a high-pressure body and a low-pressure body of an aircraft turbine engine, comprising: - an electrical network (PDS) designed to have a DC voltage; - a first electromechanical system (104) connected to the electrical network (PDS) and coupled to the high-pressure body; and - a second electromechanical system (106) connected to the electrical network (PDS) and coupled to the low-pressure body. The installation also comprises a control system (108) designed to control at least one of the first and second electromechanical systems (104, 106) so as to control the transferred power and to control at least the other of the first and second electromechanical systems (104, 106) so as to regulate the DC voltage.

Classes IPC  ?

• 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
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• 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

Abrégé

The invention relates to a turbine engine (10) for an aircraft, comprising: - a rotating element (14) which is rotatably mounted in a structural element (12) and is intended to generate thrust during the rotation thereof; and - controlled means for immobilising the rotating element (14) with respect to the structural element (12); characterised in that the controlled immobilisation means are formed by a magnetic coupling device (42) that comprises: - a rotor (44) which is coupled with the rotating element (14) and comprises first magnetic elements (46); - a stator (52) which is stationary with respect to the structural element (12) and comprises second magnetic elements (54); the magnetic coupling device (42) being controlled between an inoperative state, in which the rotor (44) is free to rotate with respect to the stator (52), and an operative state, in which the rotor (44) is rotatably immobilised by an immobilisation resisting torque.

Classes IPC  ?

• B64C 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• 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
• H02K 49/10 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à aimant permanent

Abrégé

The invention relates to a method for controlling the permeability of a lubrication circuit for an aircraft turbomachine, the turbomachine comprising at least one guide bearing, the lubrication circuit being configured to circulate an oil flow from upstream to downstream between an oil inlet and an oil outlet for lubricating the guide bearing, the method comprising the steps of: measuring a first temperature (T1) of the oil upstream of the guide bearing; measuring a second temperature (T2) of the oil downstream of the guide bearing; calculating a temperature difference between the second temperature (T2) and the first temperature (T1); comparing the temperature difference (ΔT) with a predetermined expected temperature difference (ΔT0); and, when the temperature difference (ΔT) is greater than the expected temperature difference (ΔT0), signalling a permeability fault in the lubrication circuit.

Classes IPC  ?

• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F01D 25/18 - Systèmes de lubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification
• F16N 29/04 - Dispositifs particuliers dans les installations ou les systèmes de lubrification indiquant ou détectant des conditions indésirablesUtilisation des dispositifs sensibles à ces conditions dans les installations ou les systèmes de lubrification permettant de donner une alarmeDispositifs particuliers dans les installations ou les systèmes de lubrification indiquant ou détectant des conditions indésirablesUtilisation des dispositifs sensibles à ces conditions dans les installations ou les systèmes de lubrification permettant d'arrêter des pièces en mouvement
• G01K 3/14 - Thermomètres donnant une indication autre que la valeur instantanée de la température fournissant des différences de valeursThermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs différenciées par rapport à l'espace
• G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction

Abrégé

The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.

Classes IPC  ?

• H02P 29/10 - Prévention de la survitesse ou la sous-vitesse
• B64C 11/30 - Mécanismes de changement de pas des pales
• B64D 27/34 - Aéronefs tout électriques

Abrégé

A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.

Classes IPC  ?

• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The invention relates to a hybrid turboprop engine (100) for an aircraft, comprising: a gas generator (12) which is supported by a generator shaft (14); a free turbine (11) which is supported by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), the turbine shaft (13) meshing with a main rotor (60) via a transmission system (50) comprising a first overrunning clutch (51) which is oriented such that the main rotor (60) cannot drive the free turbine (11); and a reversible electric machine (30) meshing with the main rotor via the transmission system (50) in order to drive the main rotor (60) during electric or hybrid operation, the turboprop engine comprising a single oil pump (40) meshing with the transmission system (50) in order to be driven selectively by the turbine shaft (13) or by the electric machine (30) according to the operating mode.

Classes IPC  ?

• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/06 - Aménagement des paliersLubrification
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• 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
• F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur

Abrégé

A turbomachine including a gas generator endowed with a first shaft, a gear box, at least one reversible electric machine coupled to the gear box, and a free turbine endowed with a second shaft and rotationally driven by a gas stream of the gas generator and at least one accessory coupled to the accessory gear box, wherein the turbomachine includes a first mechanical coupling means configured to mechanically couple said first mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said first mechanical shaft from the accessory gear box in a second configuration, and a second mechanical coupling means configured to mechanically couple said second mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said second mechanical shaft from the accessory gear box in a second configuration.

Classes IPC  ?

• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• F02C 7/26 - DémarrageAllumage
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The invention relates to a method capable of providing information to an operator, for example a pilot, or to an automated system, for example an autopilot, to assist in managing, flight after flight, at least one cumulative ageing process, for example creep, affecting at least part of a gas turbine of an aircraft of versatile use, for example a helicopter, in order to make the best use of such a turbine over the long term.

Classes IPC  ?

• B64C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
• G06F 11/30 - Surveillance du fonctionnement
• G08G 5/00 - Systèmes de contrôle du trafic aérien
• G05B 19/042 - Commande à programme autre que la commande numérique, c.-à-d. dans des automatismes à séquence ou dans des automates à logique utilisant des processeurs numériques
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

Abrégé

The invention relates to an electromagnetic signal-based data collection system, comprising, on the one hand, a collector (100) provided with a first antenna (105) having a first bandwidth and, on the other hand, at least one remote electronic device (200) comprising a second antenna (205) tuned so as to exchange signals with the first antenna, characterized in that the device comprises a thermally protective block (209) in which the second antenna (205) is embedded, and in that the second antenna (205) is tuned such that the second antenna (205) and the thermally protective block (209) form a radiating assembly having a second bandwidth that coincides with the first bandwidth. The invention also relates to a vehicle (A) comprising at least one propulsion engine (M) arranged in an engine compartment (G), and at least one remote device (200) of such a system.

Classes IPC  ?

• H01Q 1/02 - Dispositifs de dégivrageDispositifs de séchage
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons
• H01Q 21/28 - Combinaisons d'unités ou systèmes d'antennes sensiblement indépendants et n’interagissant pas entre eux
• H01Q 1/22 - SupportsMoyens de montage par association structurale avec d'autres équipements ou objets
• H01Q 1/32 - Adaptation pour l'utilisation dans ou sur les véhicules routiers ou ferroviaires
• G06K 19/00 - Supports d'enregistrement pour utilisation avec des machines et avec au moins une partie prévue pour supporter des marques numériques
• G06K 19/077 - Détails de structure, p. ex. montage de circuits dans le support

Abrégé

The invention relates to an electromagnetic signal-based data collection system, comprising, on the one hand, a collector (100) provided with a first antenna (105) having a predetermined bandwidth and, on the other hand, at least one remote electronic device (200) comprising a second antenna (205) having a second bandwidth that coincides with the first bandwidth for exchanging signals with the first antenna. The device comprises a thermally protective casing (207; 210) surrounding at least the second antenna (205) while defining a cavity around it, such that the second antenna radiates signals outside the protective casing substantially in the second bandwidth. The invention also relates to an aircraft equipped with such a system.

Classes IPC  ?

• H01Q 1/00 - Détails de dispositifs associés aux antennes
• H01Q 1/22 - SupportsMoyens de montage par association structurale avec d'autres équipements ou objets
• H01Q 1/28 - Adaptation pour l'utilisation dans ou sur les avions, les missiles, les satellites ou les ballons

Abrégé

A system for pumping and metering a fluid for a turbine engine, which system includes at least one pump for the fluid and an electronic computer configured to determine the flow rate of the fluid to be delivered to the turbine engine, the pumping and metering system being wherein it further includes a first electric motor and a second electric motor, which are each configured to drive the at least one pump, and in that the electronic computer includes a first control loop for controlling at least the first electric motor and a second control loop for controlling at least the second electric motor.

Classes IPC  ?

• F02C 9/30 - Commande de l'alimentation en combustible caractérisée par un débit variable d'une pompe à combustible

Abrégé

A fixed-wing combat aircraft comprising an electrical power source, a propulsion system, a low-power non-propulsion assembly comprising a flight control system, a high-power non-propulsion assembly comprising an electrical weapon system, and a management unit configured to selectively establish on command multiple operating modes comprising: a flight mode, in which the management unit distributes the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly, and an attack mode, in which the management unit limits the electrical power supplied by the electrical power source to the propulsion system and to the low-power non-propulsion assembly to the power required to allow the aircraft to glide, and reserves a majority of the available electrical power for the high-power non-propulsion assembly.

Classes IPC  ?

• B64U 10/25 - Aéronefs à voilure fixe
• B64U 20/83 - Composants électroniques structurellement intégrés à des éléments de l’aéronef, p. ex. circuits imprimés portant des charges
• B64U 50/34 - Chargement en vol
• B64U 101/15 - Véhicules aériens sans pilote spécialement adaptés à des utilisations ou à des applications spécifiques à la guerre conventionnelle ou électronique

Abrégé

A turbine for a turbomachine of longitudinal axis including an alternating arrangement of annular rows of movable blades and of fixed blades and a radially inner annular cavity formed radially inside the movable and fixed blades, and a supply circuit for supplying cooling air to the inner annular cavity, the downstream end of the supply circuit comprising an inner annular row of orifices and an outer annular row of orifices opening into the radially inner annular cavity. The turbine may also include means for controlling the flow rate of supply air to the orifices of the inner and outer annular rows of orifices.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A turbomachine including a rotary body including a motor shaft supplying mechanical power, and at least one magnetic drive pump including at least: one stator delimiting an annular inner space and including a first and a second flange, a rotor arranged in the inner space between the first and second flanges and capable of driving fluid, the rotor being able to rotate about an axis of rotation, a pair of magnets having opposite polarities coaxially arranged on the rotor with the axis of rotation, a magnet arranged on the first flange in order to co-operate with one of the magnets of the pair of magnets of the rotor, a magnetic rotator for rotating the rotor arranged on the second flange, the second flange being non-magnetic.

Classes IPC  ?

• F04D 29/048 - Paliers magnétiquesPaliers électromagnétiques
• F02C 7/22 - Systèmes d'alimentation en combustible

Abrégé

The invention relates to an assembly comprising a turbomachine engine structure (10) extending along a first axis (Z), at least one equipment item (30) and a suspension device (20) for suspending the equipment item (30) on the engine structure (10) while being offset in the direction of at least one second axis (X) perpendicular to the first axis, the suspension device (20) comprising: at least six support links (21; 22; 23; 24; 25; 26) connecting the equipment item (30) to the engine structure (10) in a statically-determinant manner; at least one safety link (27) connecting the equipment item (30) to the engine structure (10), the safety link (27) being configured to have a mechanical loading lower than a mechanical loading of each of the support links (21; 22; 23; 24; 25; 26).

Classes IPC  ?

• F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines

Abrégé

The present invention relates to an aircraft turbomachine (10) with a recuperation cycle, comprising: - a heat exchanger (6) comprising a first circuit (62) with an inlet (622) connected to an outlet (444) of a flow path (44) of a turbine (4), and a second circuit (64) with an inlet (642) connected to an air bleed system (20), and an air outlet (644), - at least one duct (7) for passing services (S) extending from a turbine casing (40) to a bearing housing (5), and - an air circulation device (8) comprising a first channel (82) with a first upstream end (822) connected to the system (20) and a first downstream end (824) connected to the inlet (642) and a second channel (84) having a second downstream end (844) connected to the outlet (644), and wherein the duct (7) extends radially outwards as far as the device (8).

Classes IPC  ?

• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement

Abrégé

Device (210) for measuring a rotational speed of an aircraft propeller (211), comprising: - an optical speed sensor (220); - an optical fiber (230) connected to the optical speed sensor and intended to be connected to a control unit of the aircraft; and - at least one target (251, 252) configured to follow the rotation of the propeller, the optical speed sensor being configured to detect the target.

Classes IPC  ?

• G01P 3/481 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• B64C 11/50 - Synchronisation des hélices multiples
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts

Abrégé

Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.

Classes IPC  ?

• B64D 35/023 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride du type en série-parallèle
• B64C 27/12 - Entraînements des rotors
• B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques

Abrégé

The present application relates to a method for calibrating a model for estimating a torque supplied by an electric machine (10), which comprises the following steps: (E1) measuring an electric current in the electric machine (10) for an operating point; (E2) estimating the torque supplied by the electric machine (10) for the operating point from the measured electric current and an estimation model which associates an output torque with an input electric current; (E3) measuring a reference torque provided by the electric machine (10) for the operating point; (E4) comparing the estimated torque with the reference torque; and (E5) adjusting the estimation model so as to reduce, or even cancel, a difference between the estimated torque and the reference torque.

Classes IPC  ?

• G01M 15/00 - Test des moteurs
• H02P 21/20 - Estimation du couple
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• G01R 31/34 - Tests de machines dynamoélectriques

Abrégé

The invention relates to a propulsion system (1, 1) for an aircraft, comprising a rotor (2) and a nacelle failing (3) that extends around said rotor in relation to an axis (X) and includes an upstream portion (10) forming an inlet section (BA) of the nacelle fairing (3) as well as a downstream portion (20), a downstream end (21) of which forms an outlet section (BF) of the nacelle fairing (3); and characterized in that the downstream portion (20) has a radially inner wall (20a) and a radially outer wall (20b), 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.

Classes IPC  ?

• 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
• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs

Abrégé

A rotor for a centrifugal breather for an air/oil mixture of a turbomachine, this rotor including a hollow shaft extending along an axis, a pinion for rotating the hollow shaft, this pinion extending around the axis and being formed of a single part and in a first material with at least one first portion of the hollow shaft, and an annular structure extending around the axis and constrained to rotate with the shaft, this structure being produced in a second material, different from the first material, wherein the structure is made integral with the shaft by additive manufacturing of this structure directly on at least one annular surface of the pinion which forms at least one annular support surface for this additive manufacturing.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01M 13/04 - Ventilation ou aération du carter par des moyens épurant l'air avant qu'il ne sorte du carter, p. ex. des séparateurs d'huile

Produits et services

Generators for aircraft, Compressors; Transmission and propulsion couplings and components (except for land vehicles); Propulsive and non-propulsive power systems machines, For use with the following goods: Aircraft and components thereof included in this class, including turbines, motors and engines, propellers, engine cars, thrust reversers; Auxiliary power units for air vehicles (machines); Lubrication systems for engines and turbines of air vehicles (machines); Test benches for engines, turbines and other propellers (machines) for aircraft. Electric and electronic apparatus and instruments, namely generators and/or starters for static or mobile installations for aircraft; Electric, electronic and magnetic pressure, speed, motion, temperature, position and vibration sensors; Electronic systems, apparatus and equipment, whether on-board or not, for the acquisition and processing of parameters and data; Electric and electronic hardware and equipment for maintaining and controlling generators, starters and integrated assemblies for the generation of propulsive and non-propulsive power. Services in connection with the sale of the following goods: Propulsive and non-propulsive power systems (machines) for aircraft; Administrative and commercial management of parts and spare parts for users of engines, systems, equipment and parts for aircraft; Business organisation consultancy, in relation to the following fields: Aircraft propulsion systems, turbines. Repair, overhaul, Maintenance and Maintenance, In connection with the following goods: Propulsive and non-propulsive power systems (machines) for aircraft and components therefor, including turbines, motors and engines, propellers, engine cars, thrust inverters; Consultancy relating to the identification and selection of tools for the repair, servicing, upkeep, standardisation and maintenance of systems, equipment and parts for aeronautical vehicles. Technical, scientific and industrial research; Engineering services; Research and development (engineering) in the field of aeronautics; Analysis of technical data; Engineering in relation to evaluation, assessment and research in connection with technologies used in aeronautical vehicle systems, equipment and parts; Testing of machines and materials; Computer software design and computer programming; Analysis and surveying of equipment and parts for aircraft; Analysis, surveying and processing of the acquisition of data recorded during the operation of engines, systems, equipment and parts for aircraft; Conducting technical project studies, In connection with the following goods: Air vehicles and components therefor, including motors and engines, engine cars, reactors, propellers or reverse thrusters, air vehicles.

Abrégé

A method for igniting a continuous combustion engine including an electronic engine control member, a high energy box, a spark plug ignition circuit and a fuel solenoid valve, cooperating with a starter motor, the method being implemented by the electronic engine control member and including precharging the high energy box before an engine starting procedure, activated on an engine starting command, the precharging being controlled by switching on the electronic engine control member, or by putting the engine in idle mode.

Classes IPC  ?

• F02C 7/266 - Allumage électrique

Abrégé

This method for managing the output of a specific-consumption mode of an aircraft comprises a step of identifying a need to reactivate a turbine engine in the nominal mode of said turbine engine, and a step of: - normal reactivation of the turbine engine in the nominal mode for the turbine engine for a first duration when a first condition (C1) is met (step 10); - accelerated reactivation of the turbine engine in the nominal mode for the turbine engine for a second duration when a second condition (C2) is met (step 12); - rapid reactivation of the turbine engine in the nominal mode of the turbine engine for a third duration when a third condition (C3) is met (step 14), the first duration being longer than the second duration, and the second duration being longer than the third duration.

Classes IPC  ?

• F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage

Abrégé

The invention relates to a method for assisting with propulsion by detecting a failure of a turboshaft engine of an aircraft operating in a nominal mode, the aircraft comprising a deactivated assistance motor, which method comprises a step (2) of comparing operating parameters of the turboshaft engine with the equivalent parameters of a model representative of a healthy turboshaft engine, a step (4) of detecting a failure of the turboshaft engine by detecting an anomaly in at least one operating parameter of the turboshaft engine, a step (6) of selecting an activation mode for the assistance motor on the basis of the operating parameters of the turboshaft engine and/or of flight parameters of the aircraft, and a step (8) of activating the assistance motor with the selected activation mode.

Classes IPC  ?

• F01D 13/00 - Combinaisons de plusieurs "machines" ou machines motrices
• B64C 27/12 - Entraînements des rotors
• F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage

Abrégé

An assembly for measuring a torque transmitted between a first member and a second member of a turbomachine includes a pinion having a first annular portion and a second annular portion joining together at a connecting portion carrying a gearing of the pinion, said first and second annular portions extending axially in opposite directions, from the connecting portion. The pinion also includes an axial power shaft with a first area coupled to the first annular portion, and a second area for coupling to the second member, and a device for measuring the torsion between the first and second areas. The device includes a first phonic wheel on the power shaft, a second phonic wheel equipping the second annular portion of the pinion and axially aligned with the first phonic wheel, and an acquisition means axially aligned with and opposite to the first phonic wheel and the second phonic wheel and outputting a signal representative of an angular variation.

Classes IPC  ?

• G01L 3/08 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple comporte un arbre élastique en torsion impliquant des moyens optiques d'indication

Abrégé

The invention relates to an aircraft turbine engine (10) having: - a compressor (14), - an annular combustion chamber (24), - a system (32) for diffusing and straightening an air stream exiting the compressor in order to supply the combustion chamber, and - a heat exchanger (38), this heat exchanger having: + a first circuit (38a) supplied with exhaust gas from the turbine engine, and + a second circuit (38b) comprising an inlet (38ba) connected by a first scroll (40a) to an outlet (34b) of the diffuser (34), and an outlet (38bb) connected by a second scroll (40b) to an inlet (36a) of the straightener (36), the scrolls (40a, 40b) comprising connecting arms (82, 84) that rigidly connect the annular portions (86, 88, 94) of the scrolls which are secured or connected to the diffuser (34) and to the straightener (36), respectively. Figure for the abstract: Figure 5

Classes IPC  ?

• F02C 3/09 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur comprenant au moins un étage radial du type centripète
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement
• F04D 29/44 - Moyens de guidage du fluide, p. ex. diffuseurs
• F04D 29/58 - RefroidissementChauffageRéduction du transfert de chaleur

Abrégé

A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams, outside the external wall, which cool the internal wall. The internal wall being free of perforations to prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Abrégé

The invention relates to a turboprop (10) comprising: - a turbine (12) mechanically connected to an input (21) of a reducer (20); - a tail shaft (30) bearing a variable-pitch propeller (31); - a rotary electric machine (46); and - an electric oil pump (40) configured to supply a hydraulic circuit (33) for adjusting the pitch of the propeller (31), wherein the electric oil pump (40) is configured to supply a lubrication circuit (53) for lubricating the bearings (25) of the reducer (20).

Classes IPC  ?

• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 17/26 - Dispositifs utilisant des éléments sensibles ou des organes de commande terminaux ou les organes de liaison entre les deux, p. ex. commande assistée l'énergie de fonctionnement ou de puissance assistée étant essentiellement non mécanique à fluide, p. ex. hydraulique
• 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
• F01D 25/18 - Systèmes de lubrification
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• F02C 9/58 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance avec la commande d'une hélice à pas variable

Abrégé

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), which comprises: - calculating, for each damage counter (FC, EF), a maximum incrementation rate (dC_FC_max, dC_EF_max) of the counter (FC, EF) so that the counter (FC, EF) remains below a predefined threshold (C_FC_max, C_EF_max) throughout a target service life (DDV_cible); - calculating, on the basis of one or more thresholds (NGmax FC, NGmax EF, T4xmax_EF) of at least one parameter (NG, T4x), at least one limit (PEinf, PEsup) of an operating variable of the turboshaft engine (TM) which must not be exceeded so that the incrementation rate (dC_FC, dC_EF) of the counter (FC, EF) remains below the maximum incrementation rate (dC_FC_max, dC_EF_max); and - transmitting a current value and the limit (PEinf, PEsup) of the operating variable to a display device (AF) of the aircraft (100).

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• G01M 15/05 - Test des moteurs à combustion interne par contrôle combiné d'au moins deux paramètres différents des moteurs
• G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
• G05B 23/02 - Test ou contrôle électrique

Abrégé

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric machine (30, 40) and a second electric machine (32, 42) that is less powerful than the first electric machine, one of the electric machines being coupled to the gas generator (12, 22) to rotate the gas generator during a starting phase, and being coupled to the free turbine (11, 21) after the starting phase to generate electric energy, the other of the electric machines being coupled to the gas generator (12, 22) only, at least one of the first and second electric machines of the first engine (1) and/or the second engine (2) being able to transmit electric energy to the other electric machine.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/26 - DémarrageAllumage
• 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

Abrégé

Disclosed is a propulsion assembly (100) for a hybrid aircraft, comprising a first engine (1) and a second engine (2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbines (11, 21) of the first and second engines (1, 2), the first engine (1) comprising a first electric machine (30) and a second electric machine (32) that is less powerful than the first electric machine (30), one of the first and second electric machines (30, 32) being able to be coupled to the gas generator (12) and to rotate the gas generator during a starting phase of the engine, and also being able to be coupled to the free turbine (11) in order to generated electric energy after the starting phase, the other of the first and second electric machines being coupled to the gas generator (12) only.

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/26 - DémarrageAllumage
• 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

Abrégé

The invention relates to a method for monitoring a propulsion system (102) of an aircraft (100), comprising: - computing a margin of a parameter (NG, T4x) of a thermal chain (TH), this margin being taken as margin (PMD1, PMT1) of the thermal chain (TH); - computing a margin of a parameter (IBAT) of an electrical chain (ELEC), at least part of this margin being taken as margin of the electrical chain (ELEC); - adding together the margin (PMD1, PMT1) of the thermal chain (TH) and the margin of the electrical chain (ELEC) so as to obtain a total margin (ePMD) of the propulsion system (102); and - transmitting the total margin (ePMD) to a display device (AF) in the aircraft (100) so that the display device (AF) displays the total margin (ePMD).

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

Abrégé

The invention relates to a hybrid propulsion system (2) comprising: a turbine engine (3) comprising a high-pressure spool (4) and a low-pressure spool (5), the low-pressure spool (5) comprising reduction gear (11), the reduction gear (11) forming part of a transmission gearbox (12) which is positioned axially at a front end (13) of the propulsion system (2); - first and second electric machines (14, 15) mechanically and respectively connected to the high-pressure and low-pressure spools (4, 5), the electric machines (14, 15) being configured to operate in modes referred to as motor and generator, the first and second electric machines (14, 15) being fixed to the transmission gearbox (12); - a control system (16) which is configured to allow the transfer of power between the high-pressure and low-pressure spools (4, 5) via the first and second electric machines (14, 15).

Classes IPC  ?

• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• B64C 27/12 - Entraînements des rotors
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 3/107 - 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
• 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 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

This method for stopping at least one aircraft turbogenerator (1) comprises: —controlling the stopping (E1) of the turbogenerator (1); —passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); —controlling the extinction of the combustion chamber (6) of the gas turbine (2); —maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, —controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs

Abrégé

A turbomachine includes a propeller, a propeller shaft carrying the propeller, a rotating electric machine, having at least a first configuration in which it is mechanically coupled to the propeller shaft, and a motor oil pump supplying a lubricating circuit of the turbomachine. The rotating electric machine in the first configuration is mechanically coupled to the motor oil pump in such a way that the rotating electric machine additionally drives the motor oil pump when it is supplied with current. Also disclosed is an aircraft including such a turbomachine.

Classes IPC  ?

• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 7/06 - Aménagement des paliersLubrification

Abrégé

a) at a safe pitch angle between the first angle and the second angle.

Classes IPC  ?

• F01D 17/16 - 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 en obturant les injecteurs
• F04D 29/56 - Moyens de guidage du fluide, p. ex. diffuseurs réglables

Abrégé

A method for determining an efficiency fault of at least one module of a turboshaft engine of an aircraft. The method comprising a step of determining an estimated real mapping, a step of determining real indicators from the estimated real mapping, a step of determining a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine for different efficiency configurations, a step of determining simulated indicators for each simulated mapping, a step of training a mathematical model by coupling the simulated indicators with efficiency configurations, and a step of applying said mathematical model to the real indicators so as to deduce therefrom a real efficiency configuration.

Classes IPC  ?

• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction

Abrégé

The invention relates to an electric machine for an aircraft, comprising a stator (1) comprising at least three phases (10) each comprising a winding (12), a control branch (11) and a neutral branch (13), the neutral branches (13) being connected together at a neutral point (14), the electric machine (3) comprising at least one protection member (5) mounted on the neutral branch (13) of at least one phase (10), each protection member (5) comprising: an inactive state (P1), in which the protection member (5) allows the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, and a protection state (P2), in which the protection member (5) interrupts the circulation of the electric current in each phase (10) on which the protection member (5) is mounted, so as to protect the electric machine in the event of a short circuit (CC).

Classes IPC  ?

• H02H 3/08 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à une surcharge
• H02H 7/08 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour moteurs dynamo-électriques

Abrégé

A method for determining at least one minimum power margin of a hybrid drive train for a transport vehicle, each drive element being associated with at least one power source and at least one power consumer. The method including a step of acquiring measurements of power parameters, a step of comparing each measurement with at least one limitation threshold, so as to deduce therefrom at least one gross margin, a step of converting the gross margins into refined margins expressed according to the same common magnitude, a step of transposing into standardised margins at least at one reference point, a step of determining a source power margin and a consumer power margin at said reference point and a step of determining the minimum power margin by selecting the lowest power margin.

Classes IPC  ?

• B64D 43/00 - Aménagements ou adaptations des instruments
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs

Abrégé

Propulsion assembly (100) for an aircraft, in particular a multi-engine helicopter, comprising at least a first engine (1) and a second engine (2) that are configured to operate in at least one standby mode, a primary air-circulation device (30) configured to bleed air from the first engine (1) via a first bleed channel (310) and/or from the second engine (2) via a second bleed channel (320) in order to convey it to equipment of the propulsion assembly (100), and a secondary air-circulation device (40) configured, when one of the first or the second engine (1, 2) operates in standby mode, to bleed air from the other of the first or the second engine (1, 2) not operating in standby mode and to convey it to the one of the first or the second engine (1, 2) operating in standby mode.

Classes IPC  ?

• B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
• 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

Abrégé

The invention relates to a method for assembling a first metal part (21) to a second metal part (22), the first and second metal parts having different sizes, the method comprising the following operations: - a) producing (110) a slot (23) in a surface of the first metal part (22); - b) positioning (120) the second metal part (22) in line with the slot (23) of the first metal part; and - c) welding (130) the second metal part (22) to the first metal part (21) through the slot (23) using a high-energy welding beam, the slot guiding the welding beam. The invention also relates to a centrifugal diffuser for turbomachinery comprising a metal cover (21) and a plurality of metal blades (22), each blade (22) being assembled with the cover (21) by means of the method hereinbefore.

Classes IPC  ?

• F04D 29/44 - Moyens de guidage du fluide, p. ex. diffuseurs
• F04D 29/60 - MontageAssemblageDémontage
• B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
• F04D 29/62 - MontageAssemblageDémontage des pompes radiales ou hélicocentrifuges
• F04D 29/02 - Emploi de matériaux spécifiés
• B23K 15/00 - Soudage ou découpage par faisceau d'électrons
• B23K 26/00 - Travail par rayon laser, p. ex. soudage, découpage ou perçage

Abrégé

The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interior volume so as to form an air passage (40) between the insert (30) and the external enclosure (10); and at least one breakable joining part (20) connected to the insert (30) on one side and to the external enclosure (10) on the other side; wherein at least one of the mechanical breaking strength of the breakable joining part (20), the mechanical breaking strength between the breakable joining part (20) and the external enclosure (10) and the mechanical breaking strength between the breakable joining part (20) and the insert (30) is lower than the mechanical breaking strength of the external enclosure (10) and the mechanical breaking strength of the insert (30).

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue

Abrégé

One aspect of the invention relates to a method for dimensionally inspecting at least one component manufactured by means of an additive manufacturing machine, the step of additive manufacturing being carried out by successive depositions of a powder bed and by fusing the powder bed after each deposition, the method comprising the steps of: - acquiring an image of the component being manufactured after at least one step of depositing and fusing the powder bed; - comparing the image with an image of a reference template; - verifying the dimensional conformity of the component on the basis of the comparison.

Classes IPC  ?

• G06T 7/00 - Analyse d'image

Abrégé

The invention relates to a synchronous electric machine (10) for aircraft, which comprises a stator (13) and a wound rotor (38) inserted into the stator, the stator comprising two sets of stator coils (47, 49) intended to be connected to different power converters, and the wound rotor comprising a rotor shaft (11) and two rotor coils (39, 40) each intended to be supplied with a different supply current. The two sets of stator coils are arranged in the stator in such a way that when a first set of stator coils (47) fails, the second set of stator coils (49) cooperates with at least the second rotor coil (40) supplied with the associated supply current in order to generate a mechanical torque on the rotor shaft, and so that the power converter connected to the first set of stator coils does not deliver any electrical power.

Classes IPC  ?

• H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
• H02K 16/00 - Machines avec plus d'un rotor ou d'un stator
• H02P 25/022 - Moteurs synchrones
• H02K 19/12 - Moteurs synchrones pour courant polyphasé caractérisés par la disposition des enroulements d'excitation, p. ex. pour auto-excitation, compoundage ou changement du nombre de pôles
• H02K 19/26 - Génératrices synchrones caractérisées par la disposition des bobinages d'excitation

Abrégé

Disclosed is a turbomachine, comprising a gas generator (13) equipped with a first shaft (18), at least one reversible electrical machine (11), a free turbine (12) provided with a second shaft (17) and caused to rotate by a gas flow generated by the gas generator (13), an accessory gear box (14) and at least one accessory (15, 16). Said at least one electrical machine (11) is mechanically coupled to said second mechanical shaft (17) via the accessory gear box (14) during all phases of operation of the turbomachine (10), the accessory gear box (14) is coupled to the at least one accessory (15, 16) and the turbomachine (10) further comprises a single mechanical coupling means (20) for mechanically coupling said first mechanical shaft (18) to the accessory gear box (14) in a first configuration and mechanically uncoupling said first mechanical shaft (18) from the accessory gear box (14) in a second configuration.

Classes IPC  ?

• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The invention relates to a hybrid electrical architecture (101) for an aircraft (103) which comprises a turbomachine (107) and a reduction gearbox (111) intended to rotate at least one propulsion member (105) of the aircraft (103). The architecture (101) also comprises at least one low-voltage electrical network (113) with at least one low-voltage electric machine (117, 118) mounted on the reduction gearbox (111) or on the turbomachine (107) and a high-voltage electrical network (125) with high-voltage electric machines (129) mounted on the turbomachine (107).

Classes IPC  ?

• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• H02J 1/08 - Systèmes à trois filsSystèmes ayant plus de trois fils
• H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée

Abrégé

The invention relates to a collector (10) for a drained liquid for a turbine engine, comprising: - an internal cavity (54) comprising a first space (54A) for collecting the liquid and a second space (54B) for transferring the liquid, the internal cavity extending longitudinally along a first direction (Z) between a first end closed by a bottom wall (16) of the collector and a second end closed by a cover (14); and - at least one inlet (44) for the drained liquid; the first and second spaces being separated by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space; wherein the means (58) for restricting the passage of the drained liquid is mounted such that it can be removed from the collector by moving it in the direction from the bottom wall to the cover of the collector.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01D 25/32 - Recueil de l'eau de condensationDrainage
• F01M 11/04 - Remplissage ou vidange du lubrifiant des "machines" ou moteurs

Abrégé

A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position (θ i) relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

Classes IPC  ?

• B64C 27/50 - Pales repliables pour faciliter le rangement de l'aéronef
• B64C 11/28 - Pales rabattables ou repliables
• B64C 27/54 - Mécanismes pour la commande du réglage ou du mouvement de la pale par rapport à la tête du rotor, p. ex. mouvement de traînée
• B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
• B64D 35/00 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions
• B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]

Abrégé

The invention relates to a collector (10) for a drained liquid for an aircraft turbine engine, said collector comprising: - an internal cavity (54) comprising a first space (54A) for collecting the drained liquid and a second space (54B) for transferring the collected liquid to a recovery outlet (30); - at least one inlet (44) for the drained liquid, in fluid communication with the first space; and - at least one recovery outlet in fluid communication with the second space; wherein the first space and the second space are separated from each other by a partition (56) with a means (58) disposed therein for restricting the passage of the drained liquid from the first space to the second space, the air in the first space being in communication with the air in the second second space such that the air pressure in the first and second spaces is identical.

Classes IPC  ?

• F01D 25/32 - Recueil de l'eau de condensationDrainage
• F01D 25/18 - Systèmes de lubrification

Abrégé

Disclosed is a turbogenerator, in particular for an electrically-driven rotary wing aircraft, comprising a gas generator equipped with a first shaft, at least one reversible electrical machine, and a free turbine provided with a second shaft and caused to rotate by a gas flow generated by the gas generator. The second shaft is coupled to the at least one electrical machine during all phases of operation of the turbomachine, and the turbomachine further comprises a single mechanical coupling means for coupling the first mechanical shaft to the second mechanical shaft when the electrical machine is operating in motor mode and mechanically uncoupling the first mechanical shaft from the second mechanical shaft when the electrical machine is operating in generator mode.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires

Abrégé

The invention relates to an assembly for an aircraft turbomachine (20), the assembly comprising a stator section (26), a first bearing (28a), a second bearing (28b) and a holder part (32) in an oil chamber (22) delimited by an outer chamber-delimiting portion (24) incorporated into the stator section (26), the holder part (32) comprising: - a first axial end portion (34a) forming an outer ring (36) of the first bearing (28a) or supporting such a ring (36); - a second axial end portion (34b) forming an outer ring of the second bearing (28b) or supporting such a ring, an oil squeeze film damper (50) being arranged between the second portion (34b) and the stator section (26); - an intermediate ring (46) arranged axially between the first and second portions (34a, 34b) and forming a flexible connection and an oil-splash protection element.

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators

Abrégé

A turbomachine, particularly for a rotary-wing aircraft, including a gas generator provided with a rotary shaft, a first reversible electric machine, a power turbine rotationally driven by a stream of gas generated by the gas generator, at least one accessory from among an oil pump and a fuel pump, an accessory gearbox comprising a gear train configured to drive said at least one accessory, and a second electric machine. The second electric machine is reversible, said first electric machine is mechanically coupled to the gas generator, the accessory gearbox and the second electric machine are mechanically coupled to the power turbine, and the turbomachine is devoid of any kinematic coupling between the gear train of the accessory gearbox and the shaft of the gas generator.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique

Abrégé

A method for protecting coils from excessive heating in an aircraft electrical machine comprising a stator (12) and a rotor (14) configured to be rotationally driven with respect to one another, the stator including a plurality of notches (120) receiving one and the same plurality or otherwise of coils, the method including the following successive steps: inserting an electrical insulator (16) into the notches or onto the teeth of the stator, installing the coils (18) in the notches or on the teeth of the stator, casting a phase change material (20) in the notches or on the teeth equipped with the coils, the electrical insulator forming a casting mold.

Classes IPC  ?

• H02K 15/12 - Imprégnation, chauffage ou séchage des bobinages, des stators, des rotors ou des machines
• H02K 3/34 - Enroulements caractérisés par la configuration, la forme ou la réalisation de l'isolement entre conducteurs ou entre conducteur et noyau, p. ex. isolement d'encoches
• H02K 15/02 - Procédés ou appareils spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation des machines dynamo-électriques des corps statoriques ou rotoriques

Abrégé

The invention relates to a turbine engine module, in particular an aircraft turbine engine (10), comprising: - an annular casing (52) having an internal wall (53) forming a channel wall; and - a nozzle (32) surrounded by the casing and comprising an annular external platform (36) and an annular internal platform (37) between which stator blades (34) extend, the external platform having an external face (36b) that faces the internal wall of the casing and comprises an annular groove (60) oriented towards the outside and housing a sealing device (64), the sealing device coming into cylindrical contact with a track (66) of the internal wall (53) of the casing, the module being characterised in that the internal wall (53) of the casing comprises a thermal barrier (70) made of ceramic material directly above the track (66), the track being arranged between the thermal barrier and the sealing device.

Classes IPC  ?

• 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
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages

Abrégé

The invention relates to a turbomachine (100) for a hybrid aircraft, the turbomachine comprising a gas generator (12) carried by a generator shaft (14), at least one free turbine (11) carried by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), a main rotor (60), and at least one reversible electric machine (30), the turbine shaft (13) being a through-shaft and extending axially between a first end engaged with the electric machine (30) and a second end engaged with the main rotor (60).

Classes IPC  ?

• F02C 3/10 - 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 une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 3/14 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail caractérisés par l'aménagement de la chambre de combustion dans l'ensemble

Abrégé

The invention relates to an aircraft turbomachine (10) comprising: a gas generator (12) comprising an output shaft (26) as well as a first lubricating circuit (28); and equipment (14) coupled to the output shaft (26) and comprising a rotor (38) which is rotationally guided by at least one rolling bearing (40), the equipment (14) comprising a second lubricating circuit (46) which is independent of the first lubricating circuit (28) and which is configured to lubricate the rolling bearing (40), the equipment further comprising a system (50) for cooling the rolling bearing (40), the cooling system (50) being configured to circulate oil in the region of at least one ring (40b) of the rolling bearing, characterized in that the cooling system (50) is independent of the second lubricating circuit (46) and is connected to the first lubricating circuit (28).

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification
• F01D 25/12 - Refroidissement
• F16C 37/00 - Refroidissement des paliers

Abrégé

A propulsive assembly (100) for a multi-engine hybrid aircraft, comprising a first and a second gas turbine (10, 20) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21) via a first and a second main coupling means (51, 52), a first and a second reversible electric machine (30, 40) each coupled to the gas generator (12, 22) via a first deactivatable coupling means (31, 41), and each coupled to the main rotor (62) via a second deactivatable coupling means (32, 42), the first deactivatable coupling means (31, 41) being activated when the electric machines (30, 40) rotate in a first direction of rotation, and the second deactivatable coupling means (32, 42) being activated when the electric machines (30, 40) rotate in a second direction of rotation opposite to the first direction of rotation.

Classes IPC  ?

• B64D 35/08 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• 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 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

A circular modular tray for the additive manufacturing of a part with an axis of revolution on a powder bed, characterised in that it consists of an assembly of modules that are concentrically coupled along a contiguous axis in a radial direction, the modules including an annular peripheral module and a circular central module.

Classes IPC  ?

• B22F 12/37 - Plate-formes ou substrats rotatifs
• B22F 10/68 - Nettoyage ou lavage
• B22F 10/66 - Traitement de pièces ou d'articles après leur formation par des moyens mécaniques
• B29C 64/245 - Plates-formes ou substrats
• B29C 64/35 - Nettoyage
• B33Y 30/00 - Appareils pour la fabrication additiveLeurs parties constitutives ou accessoires à cet effet
• B33Y 40/20 - Posttraitement, p. ex. durcissement, revêtement ou polissage
• B33Y 10/00 - Procédés de fabrication additive