Abrégé

The invention relates to a dihydrogen injection device (2) having a longitudinal axis (X), intended to be mounted on an annular base of an annular combustion chamber (4) of a turbomachine, comprising an inner channel (6) for circulating dihydrogen, and an annular outer channel (8) for circulating a mixture at least comprising air, the inner channel (6) and the annular outer channel (8) being coaxial, an inner swirler (14) being provided in the inner channel (6) and an outer swirler (28) being provided in the annular outer channel (8), a downstream end (16) of the inner channel (6) being arranged upstream, at a distance r, from a downstream end (24) of the annular outer channel (8). Such combustion of dihydrogen makes it possible to eliminate carbon-containing polluting emissions such as carbon monoxide, unburned hydrocarbons or fine particles and smoke particles.

Classes IPC  ?

• F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
• 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

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 5/14 - Forme ou structure
• F01D 5/18 - Aubes creuses; Dispositifs 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

The invention relates to a turboprop (10) comprising a propeller (12), a propeller shaft (13) carrying the propeller (12), the propeller being a variable-pitch propeller having a propeller pitch, a rotating electric machine (19) having at least a first configuration in which it is mechanically coupled to the propeller shaft (13) and at least one oil pump (21, 21B) configured to supply a hydraulic circuit for adjusting the pitch of the propeller (12). The oil pump is configured to be electrically operated. The invention further relates to an aircraft comprising such a turboprop (10) and to the methods for controlling such a turboprop (10) and such an aircraft.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

The invention relates to a device (136) for controlling a power-transfer system (124) for the transfer of power between a high-pressure shaft (108) and a low-pressure shaft (116) of a turbomachine (104) of an aircraft (102), comprising: - a fatigue analysis module (142) analysing the fatigue of the turbomachine (104) and designed to determine, from between two indicators (D1, D2) respectively measuring two fatigues of the turbomachine (104), which is the one that is the most advanced, which is to say which is the one at risk of being first to reach a respective upper limit (D1max, D2max); and - a control module (140) controlling the power transfer system (124) and designed to slow the fatigue measured by the more advanced indicator (D1, D2).

Classes IPC  ?

• 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
• 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 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
• F02C 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance

Abrégé

A device (110) for guiding a main air flow (F1) for an aircraft turbine engine (22), said device comprising: a first air flowing pipe (112) of a main air flow (F1), said first pipe having a main axis (A), - a plurality of ejectors (114) of a secondary air flow (F2) located within the first pipe (112) and configured to eject a secondary air flow (F2) and force the flow of the main air flow (F1) into said first pipe (112), the ejectors (114) being distributed around the main axis (A), and - a second air flowing pipe (116) located at the outlet of the ejectors (114) and comprising one end (116a) which is connected to one end (112a) of the first pipe (112), characterised in that the second pipe (116) comprises a narrow end (134).

Classes IPC  ?

• F02C 7/052 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des dispositifs séparateurs de poussière
• 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
• F04F 5/46 - Aménagements des tuyères

Abrégé

The invention relates to an assembly (1) for transmitting and measuring a torque transmitted between a first member and a second member (16) of a turbomachine, comprising a pinion (2) which includes a first annular portion (5) and a second annular portion (6) joining together at a connecting portion (7) supporting a gear system (4) of the pinion (2), the first and second annular portions (5, 6) extending axially along an axis of rotation (X) of the pinion (2) in directions (D1, D2) opposite from the connecting portion (7), the rotation of at least one of the the annular portions (5, 6) being guided via a bearing (8, 9) for guiding the pinion (2), the pinion further comprising an axially extending power shaft (10), the power shaft (10) comprising a first area (11) rotatably coupled to the first annular portion (5) of the pinion (2), and a second area (12) intended to be rotatably coupled to the second member (16) of the turbomachine, the first area being axially spaced apart from the second area, and means for measuring the torsion of the power shaft (10) which are arranged in a third area of the power shaft (10) located between the first and second areas (11, 12), the measuring means comprising at least one tone wheel (20, 25) and acquisition means capable of engaging with the tone wheel (20, 25), characterised in that the measuring means comprise a first tone wheel (20) provided in the third area of the power shaft (10) and a second tone wheel (25) provided in the second annular portion (6) of the pinion (2) and located axially opposite the first tone wheel (20), the acquisition means being arranged axially opposite the first tone wheel (20) and the second tone wheel (25) and being configured to supply a signal representative of an angular variation between the first tone wheel (20) and the second tone wheel (25).

Classes IPC  ?

• G01L 3/10 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple comporte un arbre élastique en torsion impliquant des moyens électriques ou magnétiques d'indication

Abrégé

Propulsion system for a helicopter, comprising a main engine, a main rotor, a main transmission gearbox comprising an outlet mechanically connected to the main rotor, a reducer mechanically coupled between the main engine and a first input in the main transmission gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reducer and configured to function as an electric generator to extract energy produced by the main engine, and a second electric machine mechanically coupled to a second input in the main transmission gearbox, the second electric machine being supplied with electricity from the first electric machine and configured to function as an electric motor for delivering additional mechanical power to the main transmission gearbox.

Classes IPC  ?

• B64C 27/04 - Hélicoptères
• B64C 27/14 - Entraînement direct entre groupe propulseur et moyeu du rotor
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs

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

Abrégé

The invention relates to 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 comprising a step of acquiring (ET1) measurements (Pv) of power parameters (PARi), a step of comparing (ET2) each measurement (Pv) with at least one limitation threshold, so as to deduce therefrom at least one gross margin (Pmb), a step of converting (ET3) the gross margins (Pmb) into refined margins (Pma) expressed according to the same common magnitude, a step of transposing (ET4) into standardised margins (Pmn) at least at one reference point, a step of determining (ET5) a source power margin (MIndS) and a consumer power margin (MIndC) at said reference point and a step of determining (ET6) the minimum power margin (MInd) by selecting the lowest power margin.

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs

Abrégé

A turbomachine (10), in particular for a rotary-wing aircraft, having a gas generator (13) provided with a rotary shaft (18), a reversible first electric machine (11), a free turbine (12) driven in rotation by a flow of gas generated by the gas generator (13), at least one accessory (15, 16) selected from an oil pump and a fuel pump, an accessories gearbox (14) comprising a gear train configured to drive said at least one accessory (15, 16), and a second electric machine (19). The second electric machine (19) is reversible, said first electric machine (11) is mechanically coupled to the gas generator (13), the accessories gearbox (14) and the second electric machine (19) are mechanically coupled to the free turbine (12), and the turbomachine (10) does not have a kinematic link between the gear train of the accessories gearbox (14) and the shaft (18) of the gas generator (13).

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

Abrégé

The invention relates to a method for determining an efficiency fault (R11-R15) of at least one module (11-15) of a turboshaft engine (T) of an aircraft (A), the method for determining comprising: ? A step of determining an estimated real mapping (CARE), ? A step of determining real indicators (IRE) from the estimated real mapping (CARE), ? A step of determining (E3) a plurality of simulated mappings from a simulation of a theoretical model of the turboshaft engine (T) for different efficiency configurations, ? A step of determining (E4) simulated indicators (ISx) for each simulated mapping (CARSx), ? A step of training (E5) a mathematical model (CLASS) by coupling the simulated indicators (ISx) with efficiency configurations (CR), and ? A step of applying (E6) said mathematical model (CLASS) to the real indicators (IRE) so as to deduce therefrom a real efficiency configuration (CR).

Classes IPC  ?

• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
• G05B 23/02 - Test ou contrôle électrique

Abrégé

The invention relates to 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 comprising an annular peripheral module (3) and a circular central module (2).

Classes IPC  ?

• B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
• B29C 64/245 - Plates-formes ou substrats
• B29C 64/30 - Opérations ou équipements auxiliaires
• B29C 64/379 - Manutention des objets en 3D obtenus, p.ex. à l’aide de robots
• B29C 64/40 - Structures de support des objets en 3D pendant la fabrication, lesdites structures devant être sacrifiées après réalisation de la fabrication
• B33Y 40/20 - Posttraitement, p.ex. durcissement, revêtement ou polissage
• B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 10/37 - Commande ou régulation des opérations des caractéristiques du lit de poudre, p.ex. de la densité
• B22F 10/47 - Structures destinées à soutenir des pièces ou des articles pendant la fabrication et retirées par la suite caractérisées par des caractéristiques structurelles
• B22F 10/60 - Traitement de pièces ou d'articles après leur formation

Abrégé

This electromechanical installation (100) for an aircraft comprises: - an electrical network (102) comprising electrical subnetworks (104, 106); - a turbogenerator (118) comprising a gas turbine (120), an electricity generator (122) with permanent magnets having phase groups (126, 128) respectively connected to the electrical subnetworks (104, 106), and, for each phase group (126, 128), an isolation device (134, 136); and - a control device (140) designed to detect a short circuit in at least one of the phase groups, each phase group in which a short circuit is detected being described as defective and each other phase group being described as healthy, and, in response to the detection of the short circuit, to disconnect this defective phase group (126, 128) from its associated electrical subnetwork (104, 106) and to command the shutdown of the gas turbine (120). The control device (140) is also designed, in response to the detection of the short circuit, to keep each healthy phase group (126, 128) connected to its electrical subnetwork (104, 106).

Classes IPC  ?

• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• H02H 7/06 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour compensateurs synchrones
• H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
• H02P 3/00 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci

Abrégé

The invention relates to a turbomachine having a compressor comprising variable pitch stator vanes (11) each extending radially between a rotating hub (6) and a stationary casing (3) surrounding this rotating hub (6), each variable pitch vane (11) comprising a blade (12) having a base (14) spaced by a first radial clearance (J1) from a stationary wall (2) of the casing (3), and a tip (17) spaced by a second radial clearance (J2) from a rotating wall (4) of the rotating hub (6). The stationary wall of the casing (3) or the rotating wall (4) of the rotating hub (6) has a shape treatment opposite the blade (12) for channeling an air leak passing through the corresponding clearance.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• 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 29/52 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes axiales
• F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analogues; Equilibrage en agissant sur les couches limites

Abrégé

System (11) for balancing at least one parameter to be balanced of an electric motor of a propulsion system (1), in particular of an aircraft, comprising at least two electric motors (3, 4) and a propulsion member (2) driven in rotation by said electric motors. The balancing system is configured to calculate a correction of the speed setpoint (Corr_Cons_VI, Corr_Cons_V2) as a function of a correction factor (F1, F2) of the speed setpoint depending on a parameter (P1, P2) of the associated electric motor that is intended to be balanced and on a speed setpoint (Cons_VH) of the propulsion member (2).

Classes IPC  ?

• B64C 11/00 - Hélices, p.ex. du type caréné; Caractéristiques communes aux hélices et aux rotors pour giravions
• B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• H02P 5/68 - Dispositions spécialement adaptées à la régulation ou la commande de la vitesse ou du couple d’au moins deux moteurs électriques pour commander au moins deux moteurs dynamo-électriques à courant continu

Abrégé

Disclosed is a method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request (100) by a pilot of the helicopter to quickly stop the engine, the following steps managed by the control unit of the turbomachine: - detecting (110) the absence of a thermal stabilisation phase of the gas generator of at least one turbomachine, - controlling (130) the extinguishing of the combustion chamber of the gas generator of at least one turbomachine, - maintaining the rotation of the gas generator (140) whose combustion chamber has been extinguished by means of the at least one electrical machine in order to ventilate the gas generator, and - stopping (160) the main rotor of the helicopter by means of a mechanical brake.

Classes IPC  ?

• F01D 21/12 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à la température
• F02C 7/25 - Prévention ou protection contre l'incendie
• F02C 9/46 - Commande de secours de l'alimentation en combustible

Abrégé

Fuel injector (110) for an aircraft turbine engine, comprising a tubular body (112) having an axis of elongation (A) and comprising a first longitudinal end (114) for supplying with fuel and a second longitudinal end (116) for ejecting a jet of fuel, said body further comprising an integrated purge-air circuit which comprises an internal cavity (122) which is connected to air inlet orifices (124) situated on the body and to at least one air outlet situated at said second end, characterized in that air-flow disruptors (150, 156) are provided, projecting into said cavity.

Classes IPC  ?

• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible

Abrégé

A component (1, 2) for supporting at least one bearing (3) for a turbine engine (10) comprising: - two coaxial walls, internal (4) and external (5) walls respectively, defining a gas flow vein (6) between them and interconnected by a row of arms (7); - an external ferrule (50) comprising an internal peripheral edge (51) connected to the external wall (5) and an external peripheral edge (52) connected to an external mounting flange (53); - an internal ferrule (40) comprising an external peripheral edge (41) connected to the internal wall (4) and an internal peripheral edge (42) comprising an internal mounting flange (43); - at least one of the ferrules (4, 5), which at the peripheral edge (41, 51) thereof is connected to the corresponding wall (4, 5), having a general shape which is corrugated about an axis (X-X) of the component (1, 2).

Classes IPC  ?

• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• F02C 7/06 - Aménagement des paliers; Lubrification

Abrégé

The invention relates to a method for manufacturing a flame tube (1) for a turbomachine, the flame tube (1) extending around an axis (X) and comprising a radially inner annular wall (2) and a radially outer annular wall (3), connected to one another by an end wall (4) or head wall, the inner wall (2), the outer wall (3) and the end wall (4) defining an internal space (5), at least one portion of said end wall (4) forming a double wall (6) comprising a first portion (7) and a second portion (8) connected to one another and spaced apart from one another so as to define a flow channel (9) for a cooling air flow opening into said internal space (5), the flow channel (9) comprising at least one air inlet opening (13), the first and second portions (7, 8) of the double wall (6) being connected by connecting areas or bridges (10) extending into the flow channel of the cooling air stream (9), the flame tube (1) being produced by additive manufacturing.

Classes IPC  ?

• F23R 3/02 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la configuration du flux d'air ou du flux de gaz
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
• F23R 3/50 - Chambres de combustion comprenant un tube à flamme annulaire à l'intérieur d'une enveloppe annulaire

Abrégé

The invention relates to a module (50) of an aircraft turbine engine, said module comprising: - at least one annular housing (24, 32) of an annular combustion chamber (16), - at least one sealing ring (36, 38) for a turbine wheel (26), and - at least one annular bearing support (42), characterized in that this module is made in one piece.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
• B33Y 80/00 - Produits obtenus par fabrication additive
• B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• F23R 3/50 - Chambres de combustion comprenant un tube à flamme annulaire à l'intérieur d'une enveloppe annulaire
• F23R 3/54 - Chambres de combustion à retournement
• F23R 3/60 - Structures de support; Moyens de fixation ou de montage

Abrégé

The invention relates to a turbine vane of a turbine engine which comprises a blade (11) and a root (12), the root comprising a stilt (13) having lateral flanks with a curvilinear profile, said stilt comprising a frangible zone suitable for undergoing a breakage of the stilt if radial forces higher than a threshold are exerted on the vane, in particular centrifugal forces during an overspeed state of the turbine. The frangible zone comprises at least one oblong frangibility recess (17) formed on at least one of the lateral flanks of the stilt, said oblong recess extending in an axial direction of the stilt along a longitudinal axis (X-X') parallel to or included in a minimum cross-sectional plane (P) which contains a minimum cross-section of the stilt.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales
• F01D 21/02 - Arrêt répondant à une survitesse
• F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position

Abrégé

The invention relates to a pre-vaporizing pipe (5) for a combustion chamber of a turbomachine, comprising a generally elongate main body (50), comprising a first end portion (51) delimiting an inlet duct (52) in which a fuel injector is to be mounted, the body (50) having an external surface (500) having a first length (L1) that extends from the portion (51) to at least one first fuel outlet end piece (53), and a second length (L2) that extends the first length (L1) from the end piece (53) and that extends from the end piece (53) to a second fuel outlet end piece (54). According to the invention, inside the body (50) there is a first channel (55) connecting the duct (52) to the end piece (53) and a second channel (56) which is distinct from the first channel (55) and which connects the duct (52) to the end piece (54).

Classes IPC  ?

• F23R 3/32 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible comprenant des dispositifs destinés à prévaporiser le combustible tubulaires

Abrégé

The invention relates to a hybrid propulsion system (10) for a vertical take-off and landing (VTOL) aircraft comprising at least one combustion engine (120, 140) driving an electricity generator (122, 142), at least one electrical energy storage assembly (16; 18A, 18N) associated with each electricity generator and defining with each electricity generator an energy branch, a plurality of electric motors (200, 220, 240, 260) actuating a same plurality of rotors (202, 222, 242, 262) providing together the propulsion and/or the lift of the aircraft, and an electrical power and distribution unit (28) supplying power to the plurality of electric motors from the electricity generator and/or the electrical energy storage assembly according to a pre-established flight phase, the system comprising at least two energy branches having an asymmetrical configuration and each selectively supplying, via the power and electrical distribution unit (28), all or part of the plurality of electric motors and in which the electricity generators of the internal combustion engines have between them a power ratio of between 1.2 and 1.4 so as to allow the most powerful to alone supply the electrical power required by the aircraft in all flight conditions.

Abrégé

The invention relates to a system for monitoring the health of a helicopter, comprising a helicopter and a device for determining a change in state of the engine that is configured to collect data measured by engine sensors and external conditions during a stable flight phase and to process said measured data in the following way: comparing said measured data with a reference model of the engine, determining, at each time interval, an instantaneous discrepancy between each item of data measured and each item of data estimated by the reference model of the engine, determining, throughout the stable flight phase, an overall discrepancy between the measured data and the data estimated by the reference model of the engine, determining, at each time interval of the stable flight phase, an intrinsic residual corresponding to a difference between the instantaneous discrepancy and the overall discrepancy, determining a deviating portion corresponding to the part of the intrinsic residual that does not satisfy a predetermined criterion, each deviating portion containing an item of information relating to a pilot action that is not recorded, and determining a corrected residual corresponding to the instantaneous discrepancy from which the deviating portion has been subtracted, the corrected residual being analysed in order to determine whether the state of the engine has changed.

Classes IPC  ?

• G01M 15/00 - Test des moteurs
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

Abrégé

The invention relates to a hybrid propulsion system (100) for a multi-rotor rotary-wing aircraft, comprising: an internal combustion engine (12), an electric machine (14) coupled to the internal combustion engine, a rectifier (16) connected to the electric machine, conversion means (18a, 18b, 18c, 18d), an electric network (20) connecting the rectifier to the conversion means, electric motorss (22a, 22b, 22c, 22d) connected to the conversion means, rotary-blade assemblies (24a, 24b, 24c, 24d) coupled to the electric motors, the system being characterized in that it comprises: detection means configured to detect a reduction in a demand for electrical power within the system to below a predetermined value, bypass means configured to bypass the electric machine when the detection means detects a reduction in the demand for electrical power.

Classes IPC  ?

• B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord
• B64D 27/33 - Aéronefs électriques hybrides
• B64D 31/18 - pour les groupes moteurs hybrides-électriques

Abrégé

The invention concerns a hybrid propulsion installation (100) for an aircraft, comprising: an internal combustion engine comprising at least one combustion chamber (114); at least one electricity generator (134a, 134n); an electrical propulsion system (138); electromechanical protection means (136a, 136n) arranged between the or each electricity generator and the electrical propulsion system; characterised in that the installation also comprises: an electronic computer (132) configured to: receive at least one piece of information on a position of the electromechanical protection means; receive at least one piece of information on a speed of rotation of a shaft (124) of the internal combustion engine; and control the flow of fuel supplying the combustion chamber depending on the information received.

Classes IPC  ?

• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B60L 50/10 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion
• B60L 3/04 - Coupure de l'alimentation en énergie en cas de fausse manœuvre
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
• F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant

Abrégé

A connection (100) comprising a widened reinforcement harness (30) which comprises a reinforced harness (10), a non-deformable ferrule (46) and a reinforcement portion (40) which has a greater diameter than the reinforcement (20) of the harness (10), the non-deformable ferrule (46) being arranged around the harness (10) with the reinforcement (20) of the harness (10) folded on the outer side of the non-deformable ferrule (46), a first end (41) of the reinforcement portion (40) being attached around the folded portion (22) of the reinforcement (20) of the harness (10), the connection further comprising an integrated coupling connector (50), a second end (42) of the reinforcement portion (40) of the widened reinforcement harness (30) being attached to a section (55) of the integrated coupling connector (50). This connection (100) is particularly advantageous for the small harness (10), wherein the reinforcement of the harness (20) has a diameter which is too small to surround the section (55) of an integrated coupling connector (50).

Classes IPC  ?

• H01R 13/6592 - Caractéristiques ou dispositions spécifiques de raccordement du blindage aux organes conducteurs l'organe conducteur étant un câble blindé

Abrégé

A method for controlling a non-propulsive power generation turbine engine (T) configured to supply power to a plurality of propulsion rotors (R1-R4) of an aircraft, each propulsion rotor (R1-R4) being connected to a power distribution module (30) through at least one power supply bus (B1-B4), the turbine engine (T) supplying each power supply bus (B1-B4) via the power distribution module (30) at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus (B1-B4) depending on the power requirement (P1-P4) of each propulsion rotor (R1-R4), a step of determining the basic power requirement of each power supply bus (B1-B4), a step of determining the overall power requirement (Pglob) based on all the basic power requirements of the power supply buses (B1-B4) and a step of determining an anticipation parameter (N1ap) based on the overall power requirement (Pglob).

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 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• F02C 9/26 - Commande de l'alimentation en combustible

Abrégé

The invention relates to a hybrid propulsion unit (100) for an aircraft with multi-rotor rotary wings: an electrical generator (114) driven by an internal combustion engine (112), a rectifier (116) configured to convert an AC current sent by the electrical generator into DC current, means for converting (118a, 118b, 118c, 118d) DC current into AC current, an electrical network (120) connecting the rectifier to the conversion means and including a high-voltage DC current bus, electric motors (122a, 122b, 122c, 122d) powered by the propeller conversion means (124a, 124b, 124c, 124d) coupled to the electric motors, the unit being characterized in that it comprises means for storing electrical energy (126) connected to the electrical network, the storage means comprising at least one primary storage element (138) and at least one secondary storage element (140).

Classes IPC  ?

• B64D 27/33 - Aéronefs électriques hybrides
• B64C 27/12 - Entraînements des rotors
• B64D 31/18 - pour les groupes moteurs hybrides-électriques

Abrégé

The invention relates to a tubular ventilation sleeve (1) for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and comprising a perforated tubular wall (1a) around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall (1b), characterized in that it further comprises support beams (7) when the sleeve (1) is made by additive manufacturing, said beams (7) extending inside the sleeve (1) between the tubular wall (1a) and the bottom wall (1b) and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall (1a) and the bottom wall (1b) and the last side of which is free and extends inside the sleeve, perforations (2) in the tubular wall (1a) being provided between the support beams (7).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

In order to master the consequences of a decoupling event on an axial toothed coupling mechanism (47) of an assembly of rotary elements (33, 35) of a gas turbine, and in a situation of initiation of axial decoupling, an excrescence (51) positioned on one of the fluted teeth of the assembly, away from the coupling axis (X), will cause the two coupling halves to pivot relative to one another about said excrescence.

Classes IPC  ?

• 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 5/02 - Organes de support des aubes, p.ex. rotors
• F01D 5/06 - Rotors à plus d'un étage axial, p.ex. du type à tambour ou à disques multiples; Leurs parties constitutives, p.ex. arbres, connections des arbres
• F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
• 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

Abrégé

Disclosed is a hybrid/electric propulsion architecture (100) for a multi-rotor rotary wing aircraft, comprising: an electricity generator (114) driven by an internal combustion engine (112), and configured to operate in motor mode, a rectifier (116) configured to convert an alternating current delivered by the electricity generator into direct current, an electrical network (120) comprising a high voltage direct current (HVDC) bus, electrical energy storage means (126) connected to the electrical network, during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means (126): the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.

Classes IPC  ?

• B60L 15/20 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p.ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désirées; Adaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p.ex. vitesse, couple, variation programmée de la vitesse
• B60L 50/61 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries par des batteries chargées par des générateurs entraînés par le moteur, p.ex. des véhicules électriques hybrides du type série
• B60L 58/12 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries en fonction de l'état de charge [SoC]
• B60L 7/02 - Freinage dynamo-électrique par résistance
• B60L 7/14 - Freinage dynamo-électrique par récupération pour véhicules propulsés par moteurs à courant alternatif
• B60L 7/20 - Freinage par fourniture d'énergie de récupération au moteur primaire sur les véhicules comportant des générateurs entraînés par le moteur

Abrégé

The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members (18) of a turbomachine (10), the members (18) being configured to travel over an operating area comprising a first position P1 and a second position P2, the method comprising the steps of: -(E23) determining a first pivoting speed V1 from the first position P1 to the second position P2; -(E25) determining a second pivoting speed from the second position P2 to the first position P1; and -(E26) determining an anomaly in the operation of the system for positioning the members (18) if the first speed V1 is lower than a first determined speed threshold and/or if the second speed V2 is lower than a second determined speed threshold.

Classes IPC  ?

• F04D 27/00 - Commande, p.ex. régulation, des pompes, des installations ou des systèmes de pompage spécialement adaptés aux fluides compressibles
• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F02C 9/20 - Commande du débit du fluide de travail par réglage des aubes
• F04D 29/54 - Moyens de guidage du fluide, p.ex. diffuseurs
• F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
• 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 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
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 9/54 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande du flux du fluide de travail par étranglement du passage du fluide de travail, par réglage des aubes

Abrégé

The present invention relates to an electric machine for an aircraft, comprising a stator and a rotor that is rotationally mobile with respect to the stator, the rotor or the stator comprising a plurality of permanent magnets, the machine comprising a device for demagnetising a permanent magnet, suitable for achieving a temporary increase in the temperature of the permanent magnet, in order to limit, during the temporary increase in temperature, an exciting magnetic flux generated by the permanent magnet. The present invention furthermore relates to an assembly comprising an assembly comprising such an electric machine and a hot-fluid source suitable for delivering hot fluid to the demagnetising device of the electric machine. The hot-fluid source may be a gas stream of a turbine engine.

Classes IPC  ?

• H02K 21/02 - Moteurs synchrones à aimants permanents; Génératrices synchrones à aimants permanents - Détails
• H02K 15/12 - Imprégnation, chauffage ou séchage des bobinages, des stators, des rotors ou des machines

Abrégé

The invention relates to an assembly for a multistage turbine (10) of a turbomachine, the assembly comprising a static sealing device, a turbine stator (22) comprising a radially outer end and an outer casing (16) surrounding the stator (22), the static sealing device being arranged radially between a radially outer end of the stator (22) and the outer casing (16), and comprising an annular seal (44) borne by the stator (22) and an annular structure (60) defining a plurality of radial annular walls (68) axially spaced apart from one another, at least one first wall of said radial annular walls (68) being in annular contact radially inwardly with the annular seal (44) and its longitudinal dimension being less than the longitudinal dimension of the seal (44).

Classes IPC  ?

• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères 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 concerns a centrifugal degasser of an air-oil mixture of a turbine engine comprising a hollow shaft (12) extending along an X axis and a pinion (28) for rotating the hollow shaft (12), and an annular chamber (10) for centrifugal separation of said mixture. The chamber (10) is arranged around the hollow shaft (12) and forms a fluid passage area, an inlet (18) of which is oriented axially for feeding the chamber (10) with said mixture, and a first outlet (20) of which is oriented radially inwards for the outlet of the de-oiled air separated from said mixture. The chamber (10) also includes at least one second oil outlet (22) oriented radially outwards and intended for discharging the oil separated from said mixture to the outside of the degasser. The degasser is characterised in that the chamber (10) and the pinion (28) form a single piece.

Classes IPC  ?

• F01M 11/08 - Séparation du lubrifiant de l'air ou du mélange air-carburant avant introduction dans le cylindre
• B04B 5/08 - Centrifugeurs pour séparer des mélanges essentiellement gazeux
• B04B 7/08 - Tambours rotatifs
• B04B 9/08 - Agencements des mécanismes de transmission
• F01D 25/18 - Systèmes de lubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F01M 11/03 - LUBRIFICATION DES "MACHINES" OU MACHINES MOTRICES EN GÉNÉRAL; LUBRIFICATION DES MOTEURS À COMBUSTION INTERNE; VENTILATION DU CARTER - Parties constitutives, détails ou accessoires non couverts par les groupes ou présentant un intérêt autre que celui visé par ces groupes Éléments constitutifs des moyens d'épuration du lubrifiant

Abrégé

The invention relates to an aircraft propulsion system, comprising a main transmission unit (12) and at least two turbojet engines connected to the main transmission unit (12), respectively a first turbojet engine (14a) and a second turbojet engine (14b), each turbojet engine comprising a free turbine (24a, 24b), characterized in that the first turbojet engine (14a) comprises a heat exchanger (30) configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer (28a, 28b) configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine (14a) when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger (30).

Classes IPC  ?

• F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• 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
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels

Abrégé

The invention relates to an aircraft power architecture comprising a power transmission gearbox (12), located in a first compartment (30), a gas turbine (14), located in a second compartment (32) comprising a gas generator (18) and a free turbine (22) connected to the power transmission gearbox (12) by a power shaft (26) of the gas turbine (14), and an accessory gearbox (16), the gas turbine (14) being set into the main transmission gearbox (12), characterized in that the gas turbine (14) comprises a first electric machine (38), and in that the accessory gearbox (16) is placed in the first compartment (30) and comprises a second electric machine (42) configured to supply energy to the accessory equipment and to receive electrical energy transmitted via the first electric machine (38).

Classes IPC  ?

• B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
• B64C 27/04 - Hélicoptères
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 35/04 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission entraîne plusieurs hélices ou rotors
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• 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

Assembly for a turbomachine (1), comprising an annular channel (6) designed to form a flow duct for a flow of gas between two turbine stages (2, 3) of the turbomachine (1), said channel (6) being bounded by a radially inner annular wall (7) and a radially outer annular wall (8), said walls (7, 8) being connected by hollow arms (16) that extend radially, a support (17) comprising a radially outer annular part (9) that is located radially outside the outer annular wall (8) of the annular channel (6), and a radially inner annular part (12) that is located radially inside the inner annular wall (7) of the annular channel (6), the outer and inner parts (9, 12) of the support (17) being connected by connecting parts (18) that extend radially, each connecting part (18) passing through one of the hollow arms (16) of the annular channel (6), in which at least one of the connecting parts (18) of the support (17) and the corresponding hollow arm (16) are connected to one another by at least one connecting partition (22), said connecting partition (22) comprising a frangible part (23) that is able to rupture when the mechanical stresses in said connecting partition (22) are greater than a certain value.

Classes IPC  ?

• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators

Abrégé

An electrical generator (9) is housed in an annular cavity (14) between the casing (15) and the propeller shaft (3) of a turboprop, while imposing little or no additional space requirement and with lightweight ancillary equipment (16) and (25). The rotor (10) of the generator is mounted on an autonomous shaft end (16). A flange (20) of the outer casing (5) is removable in order to access the generator and to enable its easy removal and remounting.

Classes IPC  ?

• B64C 11/02 - Construction du moyeu
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines

Abrégé

The invention relates to a component for a centrifugal breather for removing gas from a turbomachine air/oil mixture, which component is intended to rotate about an axis of symmetry (X), comprising a structural part (2, 3) configured to delimit a flow path (4) for the flow of said mixture comprising: a circumferential chamber (10) for the centrifugal separation of said mixture; an axial inlet (6) for said air/oil mixture into said chamber (10); radial oil outlets (9), an outlet (16) for oil-free air, further comprising at least one cellular structure (5) made for example from a material of the metallic foam type, configured to filter the oil while allowing the air to pass and occupying at least a space (17) in said flow path (4) which closes the communication between the axial inlet (6) and the internal radial outlet (12), characterized in that the structural part (2, 3) and the cellular structure (5) are formed as a single component. The invention also relates to a method for the additive manufacture of said component.

Classes IPC  ?

• B01D 45/12 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge
• B01D 19/00 - Dégazage de liquides
• B01D 45/14 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par des pales, disques, tambours ou brosses rotatives
• B01D 46/26 - Séparateurs de particules utilisant des corps filtrants creux et rigides, p.ex. appareils de précipitation de poussières rotatifs
• 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

Abrégé

A flat-jet fuel injector for an aircraft turbine engine, comprising a body (112) having a generally elongate shape having a longitudinal axis A, said body comprising a main pipe (118) having a generally elongate shape having a longitudinal axis B substantially perpendicular to said longitudinal axis A, the two longitudinal ends (120) of said main pipe being connected directly and respectively to longitudinal ends of two secondary pipes (119) having a generally elongate shape having a longitudinal axis C at least substantially parallel to said longitudinal axis A, and being configured to form, respectively, two separate fuel flow inlets intended to meet substantially at the middle of said main pipe which comprises at least one ejection slot (124) for ejecting said fuel jet, characterised in that at least one of said main and secondary pipes defines a flow area, at least one geometric parameter of which, such as the shape or a dimension, varies along said pipe and/or is different from the same geometric parameter defined by a flow area of another of said pipes.

Classes IPC  ?

• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23D 11/38 - Ajutages; Dispositifs de nettoyage des ajutages

Abrégé

Electric machine comprising a stator (1) and a rotor (2) configured to be driven in rotation in relation to one another, the rotor (2) comprising a plurality of permanent magnets (5), the stator further comprising a magnetic circuit (3) comprising poles (7) extending toward the rotor (2), the machine comprising windings of conducting elements around each pole (7) and at least one heat sink (8) arranged inside a conducting element and/or between the conducting elements, the heat sink comprising a phase change material.

Classes IPC  ?

• H02K 3/22 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre formés de conducteurs creux
• H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p.ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
• H02K 9/20 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile dans lesquels l'agent de refroidissement se vaporise dans l'enveloppe de la machine

Abrégé

The invention concerns a method (100) for checking the maximum available power of a turbine engine (11, 12) of an aircraft (10) equipped with two turbine engines (11, 12) configured to operate in parallel and together to supply a necessary power (P1 +2) to the aircraft during a flight phase, said method comprising the following steps:- placing one of the turbine engines (11, 12) in a maximum take-off power regime (PMD), and - adjusting a power (P2 , P1) supplied by the other turbine engine (12, 11), such that the turbine engines (11, 12) continue to supply the necessary power (P1 +2) to the aircraft during the flight phase; - determining a power (P1, P2) supplied by the turbine engine (11, 12) placed in the maximum take-off power regime (PMD), and - processing the supplied power (P1, P2) determined in this way, in order to deduce a piece of information relating to the maximum available power.

Classes IPC  ?

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

Abrégé

A device for temporarily increasing power (13) for increasing the power of at least one first turbomachine (5A) and at least one second turbomachine (5B), said device comprising a coolant reservoir (14), a first injection circuit (16A), connected to said reservoir (14) and opening onto at least one injection nozzle (22) configured to be installed upstream from the first turbomachine (5A), a second injection circuit (16B), connected to said reservoir (14) and opening onto at least one injection nozzle (22) configured to be installed upstream from the second turbomachine (5B), the first injection circuit (16A) and the second injection circuit (16B) each comprising at least one first valve (23) and at least on second valve (29) arranged upstream from said at least one first valve (23), and a bypass pipe (40) connecting the first injection circuit (16A) and the second injection circuit (16B), upstream from the first valve (23) of same and downstream from the second valve (29) of same.

Classes IPC  ?

• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F02C 3/30 - Addition d'eau, de vapeur ou d'autres fluides aux composants combustibles ou au fluide de travail avant l'échappement de la turbine
• F02C 7/143 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail avant ou entre les étages du compresseur

Abrégé

The invention relates to a test specimen (200) for validating operating parameters of a method for the additive manufacturing of a part by laser melting on powder beds, said test specimen having at least one upper face (210), at least one lower face (212) and side faces (214, 216, 218, 220), including a front face (214) and a rear face (216) that are substantially on opposite sides from one another, said test specimen also having at least one recess (217) opening onto said front and rear side faces, said recess having a substantially triangular shape in cross section and being delimited by three internal faces, including a first, lower internal face (222) oriented upwards, a second, upper internal face (224) oriented downwards, and a third, upper internal face (226), which defines a narrow wall (228) with one other (220, 220b) of said side faces, which is inclined.

Classes IPC  ?

• B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
• B33Y 10/00 - Procédés de fabrication additive
• B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
• B28B 1/00 - Fabrication d'objets façonnés à partir du matériau

Abrégé

The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing (10) for the centrifugal separation of said mixture, arranged around a hollow shaft (11) and defined by an outer annular wall (12) and an inner annular wall (11); axial inlets (14) for the inflow of said air/oil mixture into said housing (10); a pinion (20) for rotating said housing (10), comprising a web (21) that is securely connected to said hollow shaft (11) and to said inner (13) and outer (12) annular walls; radial oil outlets (15) in said outer wall (12); and oil-free air outlets (16) in said inner wall (13), characterised in that said axial mixture inlets (14) and said radial oil outlets (15) are axially arranged either said of said web (21) of said pinion (20) so as to prevent said axial mixture inlets (14) reintroducing oil evacuated by said radial oil outlets (15) into the enclosure (10). In one of the modes of embodiment, the cells of the deaerator can contain a metal filter.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliers; Lubrification

Abrégé

The invention relates to a centrifugal deaerator for an air/oil mixture of a turbomachine, comprising: an annular housing (10) for the centrifugal separation of said mixture, arranged around a hollow shaft (11); axial inlets (14) for the flow of said air/oil mixture into said housing (10); a pinion (20) for rotating said housing (10); and radial oil outlets (15) and oil-free air outlets (16), characterised in that it comprises a metal foam (50) housed in said housing (10) by partially extending along the axial direction (XX') so as to define two successive spaces, a foam-free space (51) and a foam-lined space (52), said foam-free space opening up towards said axial inlets. A device can be advantageously added to the hollow shaft in order to reduce the free-vortex phenomenon and to thereby significantly reduce the load losses of the deaerator.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliers; Lubrification

Abrégé

The invention relates to a temperature measurement device comprising at least three probes, a computer, the computer being configured to estimate a temperature on the basis of voltage measurements at the output of the probes, characterised in that the probes are connected together in a plurality of meshes mounted in series, with at least one mesh comprising at least two probes mounted in parallel and at least one other mesh comprising a probe or a plurality of probes mounted in parallel.

Classes IPC  ?

• G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p.ex. des thermocouples
• G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
• G01K 7/12 - Dispositions relatives à la jonction froide, p.ex. empêchant l'influence de la température de l'air environnant

Abrégé

The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.

Classes IPC  ?

• B64D 31/00 - Commande des groupes moteurs; Leur disposition
• B64C 27/00 - Giravions; Rotors propres aux giravions

Abrégé

Propulsion system (8) for a single-engine helicopter (1), comprising: a main engine (9) connected to a front drive shaft (5) and a rear drive shaft (7), respectively, suitable for driving a main gearbox (4) referred to as MGB (4) and a tail gearbox (6) referred to as TGB (6); an assistance device (10) attached to the main engine (9); characterised in that said propulsion system (8) is designed in order that the assistance device (10) can mechanically drive the TGB and MGB (6, 4) by introducing power to the rear drive shaft (7).

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The invention relates to a blade of a high-pressure turbo-engine turbine, comprising: - a blade airfoil (13) extending in a span direction (EV), terminating in an apex (S) and comprising a lower surface (16) and an upper surface (17) joined by a leading edge (18) and trailing edge (19), and - an internal cooling circuit (25) having only an upstream duct (26) and a central chamber (27) for cooling the blade by circulating air; - wherein the upstream duct (26) and the central chamber (27) are separately supplied with air; - the upstream duct (26) cools the leading edge (18) and the upper surface (17); - and the central chamber (27) cools the lower surface (16) and the trailing edge (19), and is provided with bridge elements (51) interconnecting the lower surface (16) and the upper surface (17).

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales

Abrégé

The invention relates to a wheel blade (40) for a turbomachine compressor. The blade (40) comprises a body (41) extending between the root (P) of the blade in the direction of the height (Y-Y) of the blade. The body (41) extends from a leading-edge (BA) to a trailing edge (BF) in a direction of the camber line (S-S) of the blade. The blade (40) comprises a winglet (50) located in the extension of the body (41) in the direction of the height (Y-Y). The winglet (50) is located at the tip (S) of the blade and at the leading edge (BA) of the blade. The body (41) has a curvature oriented in a first direction of rotation with respect to the direction of the camber line (S-S), the winglet (50) having a curvature in a second direction of rotation counter to the first direction of rotation.

Classes IPC  ?

• F04D 17/06 - Pompes hélicocentrifuges
• F01D 5/04 - Organes de support des aubes, p.ex. rotors pour "machines" ou machines à flux radial
• F01D 5/14 - Forme ou structure
• F04D 17/10 - Pompes centrifuges pour la compression ou l'épuisement
• F04D 29/30 - Aubes
• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analogues; Equilibrage en agissant sur les couches limites

Abrégé

The invention relates to a method for producing a shielding cartridge (1) of a turbomachine element (10), said method comprising a step of winding a carbon wire (3) comprising a plurality of fibres about a longitudinal axis and a step of trapping and preserving the outside surroundings of the wound-up wire (3) in a housing (2).

Classes IPC  ?

• B29C 70/32 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
• B29C 70/86 - Incorporation dans des couches de renforcement imprégnées cohérentes
• B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
• F41H 5/04 - Structure des plaques composées de plus d'une couche

Abrégé

The invention relates to the field of pyrotechnic devices and more specifically to a pyrotechnic device (1) comprising a main pyrotechnic charge (3), a firing device (2) for firing the main pyrotechnic charge (3), a discharge channel (5) for discharging gases generated by firing the main pyrotechnic charge (3) and an injection device (9) configured to inject a cooling fluid (10) into said gas discharge channel (5) so as to supply gases, particularly for driving turbines, at relatively low temperatures. The invention also relates to a method for cooling the gases generated by the firing of the main pyrotechnic charge (3) by injecting the cooling fluid (10).

Classes IPC  ?

• F02C 7/272 - Entraînement du rotor pour le démarrage par fluide produit par des cartouches

Abrégé

Method for collecting operational data of an aircraft (1), this aircraft comprising a screen (2) for displaying operational data (3). The method is characterised in that: - by means of a mobile terminal (4) provided with at least one optical sensor, images (5) of said display screen (2) are acquired so that at least some of the images acquired show operational data displayed on the display screen; by means of an optical character recognition (OCR) module associated with said mobile terminal (4), strings of characters (C1, C2), each representing one of said operational data (3) displayed on the display screen (2) are identified in the images (5) acquired; - by means of a report generating module and said strings of characters (C1, C2) identified, an electronic report (6) containing at least some of said operational data (3) of the aircraft (1) is generated.

Abrégé

The invention relates to a process for manufacturing a turbomachine blade (P) of the type having at least one 3D cavity (7), characterized in that said blade is produced by a succession of depositions and selective consolidations of layers of a metal additive manufacturing powder based on an alloy of copper and nickel, said alloy comprising from 2% to 7% of nickel. It also relates to a turbomachine blade, characterized in that it is manufactured by metal additive manufacturing using said process.

Classes IPC  ?

• B22F 5/04 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser d'aubes de turbines
• C22C 9/06 - Alliages à base de cuivre avec le nickel ou le cobalt comme second constituant majeur
• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• 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

Abrégé

The invention relates to a method for monitoring the soundness of helicopters comprising the determination of the severity of a plurality of flight missions of a plurality of helicopters, comprising a step for acquiring and storing flight data from helicopter flight missions, and a step for acquiring and storing maintenance data from the plurality of helicopters. The method is characterised in that said determination comprises a mission-type construction step, comprising a sub-step for constructing descriptors, a sub-step for partitioning the descriptors and a sub-step for allocating a mission type to each flight by associating the descriptor of said flight and a sub-set, in which this descriptor is found, and a step for interpreting the severity of the mission types, comprising a sub-step for estimating the severity models, and a sub-step for associating a severity model with each mission type determined in the mission type construction step.

Classes IPC  ?

• B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
• B64C 27/04 - Hélicoptères
• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules

Abrégé

The invention relates to a superalloy based on nickel, comprising, in mass percentages, 4.0 to 6.0 % of chromium, 0.4 to 0.8 % of molybdenum, 2.5 to 3.5 % of rhenium, 6.2 to 6.6 % of tungsten, 5.2 to 5.7 % of aluminium, 0.0 to 1.6 % of titanium, 6.0 to 9.9 % of tantalum, 0.0 to 0.7 % of hafnium, and 0.0 to 0.3 % of silicon, the rest consisting of nickel and potential impurities. The invention also relates to a monocrystalline blade (20A, 20B) comprising such an alloy and to a turbomachine (10) comprising such a blade (20A, 20B).

Classes IPC  ?

• C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome

Abrégé

The electrical machine according to the invention is a dual machine, and comprises a first machine (32, 33, 34) which can be reversed and a second machine (30, 35) functioning through induction between two windings. The second machine can be used for de-icing a propeller, the induction-receiving winding (30) being mounted on the propeller shaft (2). The first electrical machine can function as an electrical engine to 'taxi' the aircraft. In certain embodiments, the winding mounted on the stator (31) is common to the two machines and different magnetic flows are utilised to control them. A separate functioning of the two machines and a very good integration into the aircraft engine, with space-saving and low mass, are possible.

Classes IPC  ?

• H02K 21/48 - Génératrices à plusieurs sorties
• H02K 16/02 - Machines avec un stator et deux rotors

Abrégé

The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to allow a flow of heat from the electronic module (14, 14a, 14b) to the fuel supply circuit (15, 15a, 15b), the assembly being characterised in that the electronic module (14, 14a, 14b) comprises a phase-change material (PCM), configured to change state when the temperature of same reaches a predetermined phase-change temperature (Tf).

Classes IPC  ?

• B64D 37/34 - Conditionnement du carburant, p.ex. réchauffage
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• H01L 23/367 - Refroidissement facilité par la forme du dispositif

Abrégé

Actuating system for an aircraft including: an electro mechanical actuator, (25) which includes a non volatile memory (60) in which are kept stored data (61) including configuration data (62) specific to the electro mechanical actuator; a control unit (22) using configuration data to implement a feedback control loop having as an output signal a digital command signal of the electro mechanical actuator's electric motor; at least one digital transmission channel (50) connecting the control unit and the electro mechanical actuator.

Classes IPC  ?

• G05B 19/4062 - Contrôle de boucle d'asservissement, p.ex. surcharge de servomoteur, perte de réaction ou de référence
• B64C 13/50 - Dispositifs de transmission avec amplification de puissance utilisant l'énergie électrique
• B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet

Abrégé

The invention relates to an aircraft engine part (1) comprising at least one metal substrate (2) and an erosion protective coating (3) present on the substrate, the coating comprising at least one phase (4) comprising at least chromium in an atomic content greater than or equal to 45% and carbon in an atomic content between 5% and 20%, said phase comprising chromium carbides Cr7C3 and Cr23C6. The invention also relates to a process for manufacturing such a part in which a coating composition is deposited on the part by electrodeposition and the part is heat treated at a temperature between 250°C and 700°C.

Classes IPC  ?

• C25D 5/50 - Post-traitement des surfaces revêtues de métaux par voie électrolytique par traitement thermique
• B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
• B32B 15/16 - Produits stratifiés composés essentiellement de métal adjacent à une couche particulaire
• B32B 33/00 - Produits stratifiés caractérisés par des propriétés particulières ou des caractéristiques de surface particulières, p.ex. par des revêtements de surface particuliers; Produits stratifiés conçus pour des buts particuliers non couverts par une seule autre classe
• C25D 3/06 - Dépôt électrochimique; Bains utilisés à partir de solutions de chrome à partir des solutions de chrome trivalent

Abrégé

The invention relates to a particle-trapping device (2) for a turbomachine, said particles being contained in an air stream flowing inside a turbomachine, in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterised in that it comprises: - at least two particle deflectors (3, 3a, 3b, 3c), - a member (5) for collecting and storing the particles deflected by said deflector, - and means (6) for attaching said trapping device (2) to a part of the turbomachine.

Classes IPC  ?

• F23R 3/04 - Aménagements de l'entrée d'air
• F01D 25/32 - Recueil de l'eau de condensation; Drainage
• 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
• F02C 7/052 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des dispositifs séparateurs de poussière

Abrégé

The invention relates to the field of magnetohydrodynamic generators, and more specifically to such a generator (10) including a flow duct (11) for a working fluid, delimited by a first wall (12) and a second wall (13), a working fluid ionization device (14), a pair of arms (15), each connecting the first and second walls (12, 13) downstream of said ionization device (14) so as to define, between said arms (15) and said walls (12, 13), a channel (16) in the flow duct (11), said channel (16) being arranged so as to have some of the working fluid passing therethrough after the ionization thereof, a magnet for generating a magnetic field (B) oriented perpendicularly to the flow of the working fluid in the channel (16) delimited by the pair of arms (15) and said walls (12, 13), and at least one pair of electrodes (17). Each electrode (17) of each pair is arranged on one side of the channel (16) delimited by the pair of arms (15) and said walls (12, 13). Said electrodes (17) of each pair are spaced apart from one another perpendicularly to said magnetic field (B) and the flow of the working fluid in the channel (16) delimited by the pair of arms (15) and said walls (12, 13).

Classes IPC  ?

• H02K 44/12 - Générateurs magnétohydrodynamiques - Détails de structure des canaux de fluide
• H02K 44/08 - Générateurs magnétohydrodynamiques

Abrégé

The invention relates to a device for controlling a propeller, having variable-pitch blades, of a turboprop engine, including a first hydromechanical device (10) for controlling the pitch of the blades of the propeller and a second hydromechanical device (20) for controlling the speed of rotation of the propeller, characterised in that said device includes a single electromechanical actuator (30) including a movable actuator member (31, 36) mechanically connected both to said first hydromechanical device (10) for controlling the pitch, in order to manage the pitch setpoint, and to said second hydromechanical device (20) for controlling the speed, in order to manage the speed setpoint.

Classes IPC  ?

• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p.ex. hydrauliques

Abrégé

The invention relates to a torque meter comprising a casing (12) in which a translationally movable part (14) may move in a longitudinal direction under the effect of an axial pressure representative of the torque to be measured. The torque meter is characterised in that it comprises: a bearing surface (22) connected to the casing (12) via at least one of its ends and lying at least partially in a plane substantially perpendicular to the longitudinal direction, one longitudinal end of said movable part (14), which end is called the contact end (24), being suitable for being brought into contact with said bearing surface (22) so that a longitudinal movement of the movable part (14) leads to a deformation of the bearing surface (22); and means (26) for measuring the deformation of the bearing surface (22).

Classes IPC  ?

• G01L 3/14 - Dynamomètres de transmission rotatifs dans lesquels l'élément transmettant le couple est autre qu'un arbre élastique en torsion
• 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 a turboshaft engine for a helicopter, comprising a case (5) inside which a gas generator (6) and a turbine (7) are accommodated, the turbine (7) being mounted on a power shaft (8) that extends along a longitudinal direction (X'X), the turboshaft engine further comprising means for removably mounting the power shaft (8) into a reduction gearbox (10) inside which at least one gear (11) of a first reduction stage is accommodated; the means for removably mounting the power shaft include a pinion (12) having a central bore, the shape of which is adapted to that of the power shaft (8) in such a way that the pinion (12) can slide over the power shaft (8); furthermore, the contour of the pinion (12) is adapted to the shape of the gear (11) of the first stage in such a way that the pinion (12) can form a leading input pinion of the gearbox in said gear once the power shaft (8) has been mounted in the reduction gearbox (10).

Classes IPC  ?

• 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
• F16H 57/023 - Montage ou installation d'engrenages ou d'arbres dans les boîtes de vitesses, p.ex. procédés ou moyens d'assemblage
• B64C 27/12 - Entraînements des rotors
• B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
• F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
• 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

The invention relates to a flow limiter which comprises a body (1) comprising a fluid intake (2) and a fluid outlet (3), in which body a pipe (5) for circulating the fluid is provided, comprising a series of chambers having different cross-sections, connected to the fluid intake as well as to the fluid outlet, the pipe being generally tubular, and the pipe having a bottom which has a regular curve so that the pipe does not have one or more areas that retain the fluid circulating in the pipe.

Classes IPC  ?

• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 9/32 - Commande de l'alimentation en combustible caractérisée par l'étranglement de l'admission du combustible
• F15C 1/02 - Eléments de circuits n'ayant pas de parties en mouvement - Parties constitutives
• F15C 1/16 - Dispositifs à tourbillon, c. à d. dispositifs utilisant une chute de pression au moment où le fluide devient tourbillonnaire

Abrégé

The invention relates to a device for controlling an auxiliary engine (8) including a gas generator and a free turbine suitable for being connected mechanically to the rotor (12) of a helicopter in order to supply same with thrust power, characterised in that said control device includes a proportional-plus-integral controller (30) having proportional gain (Kp) and integral gain (Ki), which are functions of the speed of rotation of said gas generator, said controller (30) being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (Sc) for correcting the drive speed of said gas generator obtained by adding a signal which is proportional to said error signal according to said proportional gain (Kp), and an integrated signal (Si), resulting from adding a signal which is proportional to said error signal according to said integral gain (Ki) and a memory signal (Sm), provided by a feedback loop (31) of said integrated signal (Si), said memory signal (Sm) being dependent on a measurement that represents the speed of rotation of said free turbine.

Classes IPC  ?

• B64C 27/04 - Hélicoptères
• B64C 27/12 - Entraînements des rotors
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune

Abrégé

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8, 9) and a receiver unit (10), each rotating about a same axis (7) of rotation, said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation, once the fuse is mounted between said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.

Classes IPC  ?

• F16D 9/06 - Accouplements avec organe de sécurité pour le désaccouplement par rupture due au cisaillement
• 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
• F01P 5/14 - Moyens de sécurité contre, ou entrant en jeu à toute défaillance de l'entraînement des pompes de refroidissement, p.ex. mise hors circuit du moteur; Dispositifs indicateurs du fonctionnement des pompes pour l'agent de refroidissement
• F16D 1/06 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour montage d'un organe sur un arbre ou à l'extrémité d'un arbre

Abrégé

The invention relates to an air supply plenum (12) for an engine, the plenum being disposed upstream of an air intake (2) of said engine, the air intake being provided in a casing (3) of said engine. The air supply plenum (12) comprises a first lateral wall (121) and a second lateral wall (122) which together form a conduit in which an air flow (7) flows as the engine functions. The invention is characterized in that each lateral wall (121, 122) comprises a step (8) which forms a transverse recess relative to the direction of the air flow (7) in the air supply plenum (12), such that an aerodynamic separation (6) occurs in the step (8) when the engine is operating.

Classes IPC  ?

• F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
• B64C 27/04 - Hélicoptères
• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• F02C 7/055 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des grilles, des écrans ou des dispositifs protecteurs

Abrégé

The invention relates to a propulsion unit (10), notably for an aircraft, comprising - a turbomachine (12); - a propeller (14) that can be selectively coupled to said turbomachine (12); - a rotary electrical machine (16) able to drive at least the turbomachine (12), characterized in that it comprises means (20) of selective coupling of the rotary electric machine (16) to the propeller (14) and/or the turbomachine (12), which means are able to couple only the propeller (14) to the rotary electric machine (16) during a defined stage of operation of the propulsion unit (10) and which are able to couple or not couple the rotary electric machine (16) to a gas generator and/or a free turbine of the turbomachine (12).

Classes IPC  ?

• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements 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, l'électricité ou l'énergie de ressorts
• 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 7/36 - 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 hybrid propulsion system for a multi-engine aircraft comprises a plurality of free turbine turbomachines each one equipped with a gas generator, these including at least one first turbomachine (1) or hybrid turbomachine able to operate in at least a standby state during a stabilized flight of the aircraft, while other turbomachines of the plurality of turbomachines operate alone during the course of this stabilized flight. The hybrid turbomachine (1) is associated with first and second identical electrotechnical sequences each comprising an electric machine (2, respectively 3) that can operate as a starter and as a generator, and is itself connected to a power electronics module (4, respectively 5) itself selectively connected to a specific electrical energy supply network (8), such as an onboard network, and to at least one electrical energy storage member (6, respectively 7). Each of the electrotechnical sequences is designed to deliver a maximum power at least equal to half the total power (Prr) needed for rapid reactivation of the hybrid turbomachine (1).

Classes IPC  ?

• B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
• B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• B64C 27/12 - Entraînements des rotors

Abrégé

The invention relates to a removable pack for reactivating a helicopter turboshaft engine (6), including a gas generator (7) provided with a drive shaft (12). Said turboshaft engine (6) is capable of operating in at least one standby mode during a stabilized flight of the helicopter. Said removable pack includes: a removable housing (30) including a housing output shaft (31); controlled means (32, 33) for rotating said housing output shaft (31), said means being a so-called means for reactivating said turboshaft engine; and mechanical means (14) for reversibly coupling said housing output shaft (31) with said shaft (12) for driving said gas generator.

Classes IPC  ?

• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

The invention relates to an architecture for a propulsion system of a multi-engine helicopter including turboshaft engines connected to a power gearbox. Said architecture is characterized in that it includes: - at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stabilized coasting flight of the helicopter; - at least two chains (30, 40) for controlling each hybrid turboshaft engine (20), each chain (30, 40) including an electrical machine (31, 41) connected to the hybrid turboshaft engine (20) and being suitable for rotating a gas producer thereof; and - at least one source (33, 43) for supplying electrical power to said electrical machine (31, 41). Each reactivation chain (30, 40) is configured so as to be able to drive said turboshaft engine (20) in at least one operation mode from among a plurality of predetermined modes.

Classes IPC  ?

• B64D 31/00 - Commande des groupes moteurs; Leur disposition
• B64C 27/12 - Entraînements des rotors
• B64C 27/24 - Giravions complexes, c. à d. aéronefs utilisant en vol à la fois les caractéristiques de l'avion et celles du giravion avec pales du rotor fixes en vol de façon à agir comme surfaces de sustentation
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F01D 13/00 - Combinaisons de plusieurs "machines" ou machines motrices
• F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
• 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
• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
• F02C 9/44 - Commande de l'alimentation en combustible sensible à la vitesse de l'aéronef, p.ex. commande du nombre de Mach, optimisation de la consommation en combustible

Abrégé

Method for notifying an authorization to completely shut down an aircraft gas turbine engine and aircraft gas turbine engine comprising a device for such notification, the method comprising, following the detection (E10) that the engine has switched to low idle: (a) a step (E20) of evaluating, from a value of a first engine operating parameter, a value of a second parameter T45MG characterizing a thermal behaviour of an engine component subject to coking; (b) a step (E30) of comparing the value of the second parameter T45MG against a predefined threshold value T45threshold corresponding to a value of the second parameter that does not cause coking of said component; and (c) a step (E50) of notifying authorization to completely shut down the engine if the value of the second parameter T45MG is below the predefined threshold value T45threshold, steps (a) to (c) being reiterated if not.

Classes IPC  ?

• F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
• F02C 9/26 - Commande de l'alimentation en combustible

Abrégé

The invention relates to a device for testing the integrity of a rapid restart system for a helicopter turbine engine (5) comprising a pneumatic turbine connected mechanically to said turbine engine (5) and supplied with gas, on demand, by a pneumatic supply circuit (8) so as to be able to spin said turbine engine (5) and reactivate it, said test device being characterized in that it comprises means (21, 22) of bleeding pressurized air from the turbine engine (5); a pipe (23) for conveying this bled air to said pneumatic circuit (8) for supplying gas to said pneumatic turbine; and means for determining the rotational speed of said pneumatic turbine.

Classes IPC  ?

• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• B64C 27/00 - Giravions; Rotors propres aux giravions
• F02C 7/262 - Redémarrage après extinction

Abrégé

The present invention concerns a flight control system of an aircraft comprising: -a first processing unit (1), -a second processing unit (2), -communication means configured to establish a first two-way digital link (3) and a second two-way digital link (4) between the first processing unit (1) and the second processing unit (2), said second link (4) being redundant with the first link (3), and said first link (3) and second link (4) being likely to be active concomitantly, said system further comprising backup communication means enabling data exchanges between the first processing unit (1) and the second processing unit (2) in the case of a failure in the first link (3) and second link (4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14).

Classes IPC  ?

• B64D 31/00 - Commande des groupes moteurs; Leur disposition
• G05B 9/03 - Dispositions de sécurité électriques avec une boucle à canal multiple, c. à d. systèmes de commande redondants

Abrégé

The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: - sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, - receiving, from the opposite processing unit (2,1), acquisition data relative to the at least one opposite sensor and actuator data relative to the at least one opposite actuator, - receiving an item of opposite health data and determining an item of local health data, - switching said local processing unit (1,2) from a first state to a second state chosen from an active state (15), a passive state (16) and a slave state (18), depending on the opposite health data received and the local health data determined.

Classes IPC  ?

• B64D 31/00 - Commande des groupes moteurs; Leur disposition
• G05B 9/03 - Dispositions de sécurité électriques avec une boucle à canal multiple, c. à d. systèmes de commande redondants

Abrégé

The quick-assist device applies to a free-turbine turbomachine (11) of an aircraft comprising at least a first free-turbine turbomachine (11) provided with a gas generator, combined with an electric machine (12) that can operate as a starter and as a generator, the first turbomachine (11) being capable of being brought into idle mode or into unwanted switch-off mode, the electric machine being powered from an onboard power supply network (17). The device further comprises at least one electric power storage unit (14) suitable for being electrically connected to the electric machine (12) combined with the first turbomachine (11) in order to provide punctual assistance to the gas generator of said turbomachine (11). The electric power storage unit (14) constitutes a so-called "primary" power storage unit that is non-rechargeable and single-use. The device comprises a system for activating the electric power storage unit (14) and a device (15) for coupling the electric power storage unit with a power supply system (13, 16) of the electric machine (12).

Classes IPC  ?

• F02C 7/26 - Démarrage; Allumage
• B64C 27/12 - Entraînements des rotors
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• 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 7/262 - Redémarrage après extinction
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• H01M 10/46 - Accumulateurs combinés par structure avec un appareil de charge

Abrégé

The invention relates to a device for rapidly reactivating a helicopter turbine engine (6). Said device is characterized in that it includes an air turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure the reactivation thereof; - a pneumatic storage device (9) connected to said air turbine (7) by means of a pneumatic circuit (10) for supplying pressurized gas to said air turbine (7); and - a controlled, rapid-opening air valve (11) arranged on the pneumatic circuit (10) between said storage device (9) and said air turbine (7) and controllable at least in an open position, wherein the gas can be supplied to said air turbine (7), or in a closed position, wherein said air turbine (7) is no longer supplied with pressurized gas.

Classes IPC  ?

• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
• F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
• F02C 7/262 - Redémarrage après extinction

Abrégé

The invention relates to an overspeed protection device of an aircraft engine comprising a fuel supply system of said aircraft engine, the protection device comprising a voltage source configured to deliver voltage according to negative or positive polarization via a polarizer mounted in parallel with the voltage source, said polarizer being configured to polarize voltage coming from the voltage source; a logic control device connected in series with the voltage source, said logic control device being configured to open or close the supply system as a function of the polarization of the delivered voltage.

Classes IPC  ?

• F01D 21/02 - Arrêt répondant à une survitesse
• F02C 7/232 - Soupapes pour combustible; Systèmes ou soupapes de drainage
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
• F02C 9/46 - Commande de secours de l'alimentation en combustible

Abrégé

The present invention relates to an assembly for a turbomachine combustion chamber (20), comprising: -a boss (32) for turbomachine combustion chamber (20), comprising a tubular body (33) configured to be inserted in a receiving orifice (29) formed in an annular wall (25) of a flame tube (24) and to accommodate a shank (27) of a connecting pin (26) for connecting the flame tube to an external casing (21), a first end (34) of the boss comprising an annular flange (35) configured to prevent radial translational movement of the boss in a first direction (A), and a second end (37) of the boss being configured to be crimped to the wall (25) of the flame tube (25) so as to prevent radial translational movement of the boss in a second direction (B), and -an annular element (39) configured to fit coaxially with the receiving orifice (29) and in radial contact with the annular wall (25) of the flame tube (24) on the one hand and with the annular flange (35) of the boss (32) on the other.

Classes IPC  ?

• B23P 11/00 - Assemblage ou désassemblage de pièces ou d'objets métalliques par des processus du travail du métal non prévus ailleurs
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/06 - Disposition des ouvertures le long du tube à flamme
• F23R 3/60 - Structures de support; Moyens de fixation ou de montage

Abrégé

The invention relates to a device intended for implementation of an anodization treatment of a part, the device comprising: - a treatment chamber comprising a part to be treated and a counter electrode situated opposite the part to be treated, the part to be treated constituting a first wall of the treatment chamber, - a generator, a first terminal of the generator being electrically connected to the part to be treated and a second terminal of the generator being electrically connected to the counter electrode, and - a system for storage and circulation of an electrolyte, the system comprising: a storage tank, different from the treatment chamber, intended to contain the electrolyte, and an electrolyte circulation circuit intended to allow the electrolyte to flow between the storage tank and the treatment chamber.

Classes IPC  ?

• C25D 11/02 - Anodisation
• C25D 17/02 - Cuves; Installations s'y rapportant
• C25D 21/06 - Filtration
• C25D 21/18 - Régénération des bains d'électrolytes

Abrégé

The invention relates to a turbine engine compressor (10'), comprising at least one annular row of variable-pitch stator blades (12), wherein said blades are substantially radial and comprise pivots (22, 24) at the radial ends thereof, the radially external pivots of the blades being inserted in first openings of a stator housing (20) and the radially internal pivots being inserted in second openings of a floating ring (60) that surrounds a rotor (18) of the compressor, characterized in that an annular stator part (62) is inserted between the floating ring and the compressor rotor, and in that first sealing means are mounted between the stator part and the compressor rotor, and second sealing means are mounted between the floating ring and the stator component.

Classes IPC  ?

• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
• 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
• F02C 7/28 - Agencement des dispositifs d'étanchéité
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur

Abrégé

The invention concerns a device for assisting a propulsion system of a single-engine helicopter comprising an engine linked to a power transmission unit (15) suitable for rotating a rotor of the helicopter, characterised in that it comprises: a turbine (18) for driving the rotation of an output shaft (34) linked mechanically to said power transmission unit (15); and controlled means (16) for supplying said turbine (18) with pressurised fluid in order to allow said turbine (18) to convert the energy from said pressurised fluid into mechanical energy for rotating said output shaft (34).

Classes IPC  ?

• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
• B64C 27/12 - Entraînements des rotors
• 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

Compresseur (10') de turbomachine, comportant au moins une rangée annulaire d'aubes de stator (12) à calage variable, ces aubes étant sensiblement radiales et comportant à leurs extrémités radiales des pivots (22, 24), les pivots radialement externes des aubes étant logés dans des premiers orifices d'un carter de stator (20) et les pivots radialement internes étant logés dans des seconds orifices d'un anneau flottant (60) qui entoure un rotor (18) du compresseur, caractérisé en ce qu'une pièce annulaire (62) de stator est intercalée entre l'anneau flottant et le rotor du compresseur, et en ce que des premiers moyens d'étanchéité sont montés entre la pièce de stator et le rotor du compresseur, et des seconds moyens d'étanchéité sont montés entre l'anneau flottant et la pièce de stator.

Classes IPC  ?

• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• 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
• F02C 7/28 - Agencement des dispositifs d'étanchéité

Abrégé

Assistance device (100) for an aircraft free turbine turbomachine (TAG1), the device comprising means (K11, CVS1) for electrically powering a coil (SU) of a rotary starter machine (GD1), referred to as first coil, in order to provide a first acceleration assistance to the gas generator of the turbomachine (TAG1). The device further comprises monitoring means (110) for monitoring the first assistance and means (K12, CVS2) for electrically powering a second coil (S12) of a rotary machine, so as to provide a second acceleration assistance to said gas generator if the monitoring means (110) observe the first assistance as insufficient.

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• 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 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
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels

Abrégé

The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4, 5) comprising protection end stops regulated by a regulating device which define a maximum power speed, characterized in that it comprises: a step (10) of detecting a fault index of said faulty engine (4); a step (11) of modifying said end stops for protecting said sound engine (5) to protection end stops corresponding to a maximum power single-engine speed, in the event of a fault index being detected; a step (12) of confirming a fault with said faulty engine (4); a step (13) of commanding an increase in the rate of supply of fuel to said sound engine (5) in the event of the fault being confirmed.

Classes IPC  ?

• F02C 9/46 - Commande de secours de l'alimentation en combustible
• B64D 31/12 - Dispositifs amorçant la mise en œuvre actionnés automatiquement pour équilibrer ou synchroniser les groupes moteurs
• 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 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance
• F02K 3/12 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant caractérisés par le fait de comporter plus d'une turbine à gaz

Abrégé

The aircraft turbine engine rapid reactivation system includes an electrical machine (60) supplied with DC power by an onboard electrical power supply network (10). The system also includes: - a switch (50) positioned between the onboard network (10) and the electrical machine (60); - an additional assembly (30) including a plurality N of electrical power storage elements (30a,,30n); and - a control unit (20) for controlling a device (40) for discharging the storage elements. Said control unit is suitable for placing the onboard network (10) in parallel with a series circuit including at least a portion of the N electrical power storage elements (30a,,30n) such that, when the rapid reactivation system is in operation, the electrical machine (60) is supplied with power at a voltage level above that of the nominal characteristics thereof.

Classes IPC  ?

• F02C 7/268 - Entraînement du rotor pour le démarrage
• 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 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/262 - Redémarrage après extinction
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels
• F02N 11/08 - Circuits spécialement adaptés pour le démarrage des moteurs

Abrégé

Assistance device (100) for a free turbine turbomachine (TAG1) of an aircraft comprising at least two free turbine turbomachines (TAG1, TAG2), the device comprising an electric starter machine (D1) for providing prolonged assistance to the gas generator of a first turbomachine (TAG1) using energy produced by an electric generator machine (G2) driven by the second turbomachine (TAG2), the device additionally comprising at least one electrical storage member (S1) electrically connected to said electric starter machine (D1) to provide short-term assistance to said gas generator, in which the electric starter machine (D1) is powered by a first power converter (CVS1) that allows it to exchange energy with the storage member (S1) for the short-term assistance, and that transmits to it energy supplied by a second power converter (CVS2) for the prolonged assistance.

Classes IPC  ?

• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels
• B64C 27/04 - Hélicoptères
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• 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 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 7/262 - Redémarrage après extinction
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• 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 an emergency start device for a helicopter turbine engine (6). Said device is characterized in that it includes: - a hydraulic engine (7) mechanically connected to said turbine engine (6); - a hydropneumatic storage device (9) connected to said hydraulic engine (7) via a hydraulic system (10) for supplying pressurized liquid to said hydraulic engine (7); and - a controlled quick-opening hydraulic valve (11) arranged on the hydraulic system (10), between said storage device (9) and said hydraulic engine (7), and suitable for being placed, on command, at least in an open position, wherein the liquid can be supplied to said hydraulic engine (7), or in a closed position, wherein said hydraulic engine (7) is no longer supplied with pressurized liquid.

Classes IPC  ?

• F02C 7/27 - Entraînement du rotor pour le démarrage par fluide
• F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
• F02C 6/14 - Ensembles fonctionnels de turbines à gaz comportant des moyens pour emmagasiner l'énergie, p.ex. pour faire face à des pointes de charge

Abrégé

The invention concerns an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5), capable of operating in at least one standby mode during a stabilised flight of the helicopter, the other turboshaft engines (6) operating alone during said stabilised flight; an air turbine (30) linked mechanically to the gas generator (17) of the hybrid turboshaft engine (5) and suitable for rotating said gas generator (17); means for collecting pressurised air on the gas generator (27) of a turboshaft engine (6) that is running; and a conduit (31) for conveying said collected air to said air turbine (30).

Classes IPC  ?

• F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine

Abrégé

The invention relates to a method and a device for optimized global management of an energy network of an aircraft comprising a plurality of energy-related equipment, characterized in that it comprises a module 40 for selecting at least one optimization objective (19) from among a plurality of predetermined objectives, a module (42) for receiving data from equipment, a module (41) for receiving aircraft data, and a module (43) for determining operating settings (22) of the energy-related equipment on the basis of the data (21) of equipment and of aircraft data (20) that are adapted to achieve at least one selected optimization objective (19).

Classes IPC  ?

• G05B 13/02 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
• B64C 19/00 - Dispositifs de commande des aéronefs non prévus ailleurs

Abrégé

The invention relates to an architecture of a multiple-engine helicopter propulsion system comprising turbine engines (1, 2) which are connected to a power transmission gearbox (3), comprising: a hybrid turbine engine (1) able to operate in at least one standby state during steady stabilized flight of the helicopter; a pack (5, 6) with a rapid restarting of said hybrid turbine engine (1) to cause it to exit said standby state and attain a nominal operating state; an auxiliary power unit (11) connected to said electro­technical restart pack (5, 6) via a first (10) AC/DC converter designed, on demand, to supply said restart pack (5, 6) with the power required to cause said hybrid turbine engine (1) to leave said standby state.

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• B64C 27/04 - Hélicoptères
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels

Abrégé

The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator (5). The turboshaft engine is characterised in that it comprises a device (20) for the spontaneous mechanical coupling of the gas generator (5) and the free turbine (6), said device being adapted to connect the gas generator (5) and the free turbine (6) in a spontaneous and mechanical manner once the ratio of the rotation speed (NGG) of the gas generator to the rotation speed (NTL) of the free turbine reaches a pre-determined threshold value.

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 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 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 an architecture of a multi-engine helicopter propulsion system comprising turbine engines (1, 2) connected to a power transmission gearbox (3), and a low-voltage on-board DC network (7) intended to power helicopter equipment during flight, characterized in that the architecture comprises: a hybrid turbine engine (1) able to operate in at least one standby state during steady stabilized flight of the helicopter; an electrotechnical pack (20) for the rapid restart of said hybrid turbine engine in order to cause it to exit said standby state and attain a state in which it supplies mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) for electrically powering said on-board network (7).

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• B64C 27/04 - Hélicoptères
• B64D 35/08 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le fait que la transmission est entraînée par plusieurs groupes moteurs
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
• F02C 9/42 - Commande de l'alimentation en combustible spécialement adaptée à la commande simultanée d'au moins deux ensembles fonctionnels

Abrégé

The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator. The turboshaft engine is characterised in that it comprises a device (40) for the controlled mechanical coupling of the gas generator (5) and the free turbine (6), said device being designed to connect the gas generator (5) and the free turbine (6) mechanically, on command, once the rotation speed of the gas generator (5) reaches a pre-determined threshold speed.

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 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 7/36 - 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

A transmission assembly for an aircraft and a helicopter comprising such an assembly for independently adjusting the speed of rotation of an engine and a torque receiver. According to the invention, the assembly comprises a first input shaft (10a), configured to receive mechanical torque from a first engine (10), an output shaft (60a), configured to transmit mechanical torque to a torque receiver (60), a first transmission member (20) having at least two degrees of mobility comprising first, second and third movable parts, a first regulating reversible electric machine (30), and a first balancing reversible electric machine (40), in which the input shaft (10a) is coupled to the first movable part, the output shaft (60a) is coupled to the second movable part, the first regulating electric machine (30) is coupled to the third movable part, and the first balancing electric machine (40) is coupled in series to the input shaft or the output shaft (60a).

Classes IPC  ?

• B64C 27/12 - Entraînements des rotors
• F16H 3/72 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif utilisant des engrenages à mouvement orbital avec entraînement secondaire, p. ex un moteur régulateur, pour faire varier la vitesse d'une manière continue