The invention relates to an aircraft fuel cell propulsion unit (10) comprising a fuel cell system (12) that includes at least one anode (14), at least one cathode (15) and a process gas device (17) for supplying fuel and ambient air to the anode (14) and the cathode (15) and evacuating spent process gases, further comprising a ram air duct (21) through which compressed ram air (22) flows, and a heat exchanger (20) which is located in the ram air duct (21) and is designed to give off heat generated by the fuel cell system (12) to the environment.
H01M 8/04029 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur Échange de chaleur par des liquides
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyte; Humidification ou déshumidification
The present invention relates to a propulsion system (1) for an aircraft (50), having a first propulsion unit (11) which has a first power generator (21) for outputting a first electric power (P1) and a first thrust unit (31) connected to the first power generator (21) to generate thrust from the first electric power (P1), and a second propulsion unit (12) which has a second power generator (22) for outputting a second electric power (P2) and a second thrust unit (32) connected to the second power generator (22) to generate thrust from the second electric power (P2), and a connecting device (40), which, in the event of a fault of the first propulsion unit (11), is designed to connect the first thrust unit (31) or the first power generator (21) to the second propulsion unit (12) for supply.
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 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
3.
HOUSING FLANGE FOR AN ELECTRIC MOTOR HOUSING OF AN ELECTRIC MOTOR, ASSEMBLY COMPRISING A HOUSING FLANGE AND STATOR TEETH, AND METHOD FOR MANUFACTURING A HOUSING FLANGE
The invention relates to a housing flange (1) for an electric motor housing (2) of an electric motor (3), in particular for an aircraft engine, the housing flange (1) comprising a forged and/or cast round base plate (4), the base plate (4) comprising a through-opening (5) in its centre for the passage of a shaft (6) of a rotor (8) of the electric motor (3). According to the invention, a housing coolant distribution body (10), which is additively manufactured at least in some regions, is located on a first base plate main surface (9) of the base plate (4), the housing coolant distribution body (10) being in the form of a hollow cylinder, the cylinder axis (11) of which is oriented so as to be centred with respect to the through-opening (5), and the housing coolant distribution body (10) comprising one or more coolant channels (16) for the passage of a coolant.
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
H02K 9/19 - 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
The present invention relates to a fuel cell stack (1), having fuel cells (2) arranged successively in a stacking direction (3), an inner covering element (11) which follows the fuel cells (2) in the stacking direction (3), and an outer covering element (12) which follows the inner covering element (11) in the stacking direction (3) and holds the inner covering element and the fuel cells (2) together in a braced state, wherein the outer covering element (12) forms at least a first and a second spring element (15.1, 15.2) perpendicularly to the stacking direction (3), wherein each of the spring elements (15.1, 15.2) forms an arc profile (16.1, 16.2) which is convexly curved in the direction of the inner covering element (11), and the respective arc profile (16.1, 16.2) is separately suspended, and wherein the inner covering element (11) forms a respective receptacle (40.1, 40.2) for the spring elements (15.1, 15.2), each receptacle being concavely curved in the direction of the outer covering element (12) and accommodating the respective convexly curved arc profile (16.1, 16.2).
The invention relates to a fuel cell stack (1) with fuel cells (2) arranged one after another in a stacking direction (3), a cover element (5) and a hydraulic compensation element (6), wherein the hydraulic compensation element (6) and the cover element (5) are arranged following the fuel cells (2) in the stacking direction (3), wherein the cover element (5) holds the fuel cells (2) together in a state (21) in which it is tensioned against the fuel cells (2), and is curved towards the fuel cells (2) in an untensioned state (20), and wherein the hydraulic compensation element (6) is/can be applied with a fluid (11) in order to adjust a pressing force (8) transferred to the fuel cells (2) in the tensioned state (21).
A method (100) for operating an aircraft-engine turbomachine (1) having a compressor (3), through which a gas flow (6) passes in a flow direction, a combustion chamber (4), a turbine (5) and a heat exchanger (8) downstream of the turbine (5), wherein the heat exchanger (8) generates steam from water by means of energy from the gas flow (6) and the steam is fed, in particular together with fuel, into the gas flow (6) for burning in the combustion chamber (4).
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine (14), for driving the compressor (12), and a second turbine, in particular a low-pressure turbine (15) are arranged in the core flow channel (10) in the flow direction, and comprising a water system (30) for providing water via recovery from an exhaust gas from the core flow channel (10).
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 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur
The invention relates to a heat exchanger (10) for cooling a hot fluid, in particular an exhaust gas or a fuel-cell cooling fluid, by means of a cooling fluid which is at a lower temperature than the hot fluid and which has a high flow velocity, comprising a high-temperature grille (30) for guiding the hot fluid and a low-temperature grille (20) for guiding the cooling fluid. According to the invention, a heat exchanger which can improve a transfer of heat despite a high-velocity inflowing fluid and/or which can reduce the required installation space is created in that a diffuser region (24) for decelerating the cooling fluid is arranged in at least one first low-temperature channel (21), through which the cooling fluid flows, of the low-temperature grille (20), and in that the diffuser region (24) and a first high-temperature channel (31), through which the hot fluid flows, of the high-temperature grille (30) have at least one shared wall (40) for heat transfer.
F28F 1/02 - Eléments tubulaires de section transversale non circulaire
F28F 13/08 - Dispositions pour modifier le transfert de chaleur, p.ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en faisant varier la section transversale des canaux d'écoulement
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
F28F 9/02 - Boîtes de distribution; Plaques d'extrémité
A propulsion system (1) for an aircraft, comprising a gas turbine (2), with a main flow duct (10) and a bypass flow duct (20), wherein the gas turbine (2) has an outer housing (5) which surrounds the bypass flow duct (20) on the outside. The core flow of the gas turbine (2) is routed radially to the outside and at least in portions through the outer housing (5) or along the outer housing (5).
The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) with a main flow channel (10) and a bypass flow channel (20), a water system (30) and a steam system (40), wherein the water system (30) comprises at least one water separation unit (31) and a condenser (21) with at least one condenser module (23), wherein the gas turbine (2) has a housing (5, 6), in particular an outer housing (5) bordering the bypass flow channel (20) on the outside, and/or an inner housing (6) comprising the main flow channel (10). A propulsion system, with a water and steam system that is better integrated into the gas turbine, is achieved in that the water separation unit (13) is arranged in and/or on the outer housing (5), in particular in the cowling, and/or the at least one condenser module (23) is arranged in the bypass flow channel (20) and has exhaust gas channels (26) which direct an exhaust gas from the main flow channel (10), via the the bypass flow channel (20) and in and/or through the outer housing (5).
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
F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur
F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
11.
EXHAUST GAS TREATMENT APPARATUS FOR AN AIRCRAFT ENGINE
The invention relates to an exhaust gas treatment apparatus (1) for an aircraft engine (2), the exhaust gas treatment apparatus comprising an exhaust gas channel (7), through which an exhaust gas of the aircraft engine (2) can flow, a first cooling device (8) and a second cooling device (13) for cooling an exhaust gas flow (6) flowing through the exhaust gas channel (7), the second cooling device (13) being located downstream of the first cooling device (8) with respect to the exhaust gas flow (6). The invention also relates to a method for operating such a cooling device.
F02C 7/16 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
F01N 3/04 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement pour refroidir ou pour enlever les constituants solides des gaz d'échappement au moyen de liquides
12.
MASKING DEVICE FOR PRODUCING A MASKING STRUCTURE, METHOD AND MASKING STRUCTURE
The invention relates to a masking device (1) for producing a masking structure (2) on a turbomachine component (3) to be machined by means of a surface finishing method. The masking device (1) operates in an automated and adaptive manner and is configured to move at least one metering unit (8) of the masking device (1) along a predetermined masking zone of the component (3) by an application robot arm (14) of the masking device (1) in an application method step (S3), and thereby apply a first masking layer (37) of a masking agent (11) in the masking zone by means of the metering unit (8), and in a curing method step (S4) after completion of the application method step (S3), to irradiate the applied first masking layer at least in areas by an irradiation means of the masking device (1) in order to cure the masking agent (11) of the masking layer, and to repeat the application method step (S3) and the curing method step (S4) in order to produce further masking layers of the masking structure (2) until the masking structure (2) is completed.
B05C 5/02 - Appareillages dans lesquels un liquide ou autre matériau fluide est projeté, versé ou répandu sur la surface de l'ouvrage à partir d'un dispositif de sortie en contact, ou presque en contact, avec l'ouvrage
B05C 9/12 - Appareillages ou installations pour appliquer des liquides ou d'autres matériaux fluides aux surfaces par des moyens non prévus dans l'un des groupes , ou dans lesquels le moyen pour déposer le liquide ou autre matériau fluide n'est pas important pour appliquer un liquide ou autre matériau fluide et exécuter une opération auxiliaire l'opération auxiliaire étant exécutée après l'application
B05B 12/20 - Aménagements de commande de la distribution; Aménagements de réglage de l’aire de pulvérisation pour régler l’aire de pulvérisation Éléments de masquage, c. à d. éléments définissant des aires non revêtues sur un objet à revêtir
B05B 13/04 - Moyens pour supporter l'ouvrage; Disposition ou assemblage des têtes de pulvérisation; Adaptation ou disposition des moyens pour entraîner des pièces les têtes de pulvérisation étant déplacées au cours de l'opération
B05D 1/32 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces en utilisant des moyens pour protéger des parties de surface à ne pas recouvrir, p.ex. en se servant de stencils, d'enduits de protection
13.
MACHINING MACHINE, AND METHOD FOR MONITORING A DYNAMIC STIFFNESS OF A MACHINING MACHINE
The invention relates to a machining machine (10) having at least one rotatable shaft (11), said machining machine comprising: an excitation device (13) having an actuator (14) which is designed to apply an impact excitation (α) to the rotating shaft (11); a detection device (21); an evaluation device (22); and a control device (20). According to the invention, the shaft (11) is rotated and an impact excitation (α) is applied to the rotating shaft (11) in order to generate a response vibration (γ) of the shaft (11).
The invention relates to a method for processing a workpiece by means of electrochemical machining, in which i) the workpiece is introduced into a working chamber and the working chamber is closed, ii) in the working chamber, in an electrolyte fluid, material is removed from the workpiece, wherein, in addition, before the working chamber is reopened and the workpiece is taken out of the working chamber, iii) the working chamber is supplied with a fluid containing iron(II) ions as a reducing agent.
C02F 1/467 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par des procédés électrochimiques par électrolyse par désinfection électrochimique
B23H 9/10 - Usinage d'aubes de turbine ou de buses
15.
NICKEL ALLOY, POWDER FOR PRODUCING A NICKEL ALLOY, AND COMPONENT COMPRISING A NICKEL ALLOY
The invention relates to a nickel alloy (1), in particular for producing a component (3) for a thermal gas turbine, characterised by the following mass fractions of an alloy composition: 10% inclusive to 15% inclusive of chromium; 14% inclusive to 20% inclusive of cobalt; 3% inclusive to 8% inclusive of molybdenum; 2% inclusive to 6% inclusive of tungsten; 0.5% inclusive to 3% inclusive of niobium; 3% inclusive to 6% inclusive of aluminium; 3% inclusive to 6% inclusive of titanium; 0.1% inclusive to 0.2% inclusive of hafnium; 2% inclusive to 4% inclusive of tantalum; 0.01% inclusive to 0.1% inclusive of carbon; 0.02% inclusive to 0.1% inclusive of boron; 0.05% inclusive to 0.2% inclusive of zirconium; the remainder being formed by nickel.
The invention relates to a fuel treatment device (10) for a combustion system of a turbomachine, having a vapour line (13) conducting water vapour (W), a fuel line (14) and a fuel supply device (15) by means of which fuel (B) can be supplied to water vapour (W) flowing in the vapour line (13) in order to produce a vapour-fuel mixture (G). The invention also relates to a method for operating a combustion system of a turbomachine.
F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
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
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
17.
FUEL CELL APPARATUS, COMPRESSOR DEVICE, CONTROL DEVICE AND METHOD FOR OPERATING A CONTROL DEVICE
The invention relates to a fuel cell apparatus (1) for a main drive system of an aircraft, comprising at least one fuel cell device (2), and an air supply device (3) which is designed to feed a fluid (4) to the at least one fuel cell device (2), the air supply device (3) having a compressor device (6) which is designed to compress the fluid (4) to a predetermined mass flow and/or pressure. According to the invention, the compressor device (6) comprises a guide device (8), the guide device (8) having at least one adjustable guide element (9) which is designed to provide an aerodynamic narrowest cross section (10) of a main flow path (11) through the compressor device (6). The air supply device (3) has a control device (12) which is designed to control the guide device (8) in order to set the at least one narrowest cross section (10).
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
F04D 17/02 - Pompes à flux radial spécialement adaptées aux fluides compressibles, p.ex. pompes centrifuges; Pompes hélicocentrifuges spécialement adaptées aux fluides compressibles ayant des étages non centrifuges, p.ex. centripètes
F04D 17/10 - Pompes centrifuges pour la compression ou l'épuisement
The present invention relates to a flow field plate (4) for a fuel cell (3), having a plate core (20) and a metallic base layer (25.1) that is arranged on the plate core (20) and covers same, wherein the plate core (20) is made of an aluminium material, and wherein the metallic base layer has a thickness of at least 2 μm.
H01M 8/0213 - Matériaux imperméables aux gaz contenant du carbone
H01M 8/0228 - Composites sous forme de produits en couches ou enrobés
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
The invention relates to a method and to a device for determining how at least one engine module (15, 15a, 15b, 15c, 15d, 15e) impacts a deterioration in an engine performance, in particular for planning an engine maintenance. Firstly, at least one measurement value for at least one performance parameter of the at least one engine module (15, 15a, 15b, 15c, 15d, 15e) is recorded at a measurement time during a flight phase, as well as measurement values for flight parameters that characterise the engine load point at the measurement time. As a result of this, a change in at least one resulting module scaler (MS) relative to a default or model value of the module scaler (MS) is determined, wherein the at least one resulting module scaler (MS) is calculated based on a deviation of the at least one recorded measurement value for the at least one performance parameter from a default or model value of the at least one measurement value of the at least one performance parameter at an engine load point. The impact of the change of the at least one module scaler (MS) on the at least one predefined engine performance parameter (LP) is determined at the measurement time at a reference engine load point.
The invention relates to a fuel cell (1) for a fuel cell stack (40) which has a first bipolar plate (11) and a catalyst membrane layer (2), the catalyst membrane layer (2) being subdivided into at least two segments (2.1-2.3), but the first bipolar plate (11) being formed continuously and extending beyond the at least two segments (2.1-2.3), thus the at least two segments (2.1-2.3) being electrically connected in parallel, and a first channel structure (21), which is intended to supply the catalyst membrane layer (2) with a reaction gas (35, 36), being subdivided into at least two segments congruently with the at least two segments (21.1-21.3) of the catalyst membrane layer.
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
H01M 8/0267 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs comprenant des moyens de chauffage ou de refroidissement, p.ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
H01M 8/0271 - Moyens d’étanchéité ou de support autour des électrodes, des matrices ou des membranes
H01M 8/2418 - Groupement en arrangeant les éléments élémentaires dans un plan
H01M 8/249 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible comprenant plusieurs groupements d'éléments à combustible, p.ex. ensembles modulaires
The present invention relates to a fuel cell stack (1), comprising: fuel cells (2) arranged successively in a stacking direction (5); a cover element (10) which follows the fuel cells (2) in the stacking direction (5) and holds them together; and a spring element (19) which is arranged between the fuel cells (2) and the cover element (10) in the stacking direction (5), wherein the spring element (19) is a constant force spring element (20).
The invention relates to a rotor shaft (1) for an electric motor (2), in particular for an aircraft engine, wherein the rotor shaft (1) has a forged attachment flange (3), and the attachment flange (3) is designed to attach to another shaft (6) in order to transmit a force and/or a torque and comprises a first axial end (4) facing the other shaft (6) and a base (8) on a second axial end (7) opposite the first axial end (4). According to the invention, the rotor shaft (1) has a coolant distribution body (9) which is additively manufactured at least in some regions, wherein the additively manufactured coolant distribution body (9) is arranged on the base (9) of the forged attachment flange (3) in a radially centered manner, and the rotor shaft (1) has a rotor device (12), which radially surrounds the additively manufactured coolant distribution body (9) and is connected to the base (8) of the forged attachment flange (3) at least in a force-fitting manner.
H02K 1/32 - Parties tournantes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
H02K 9/19 - 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
B33Y 80/00 - Produits obtenus par fabrication additive
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p.ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
H02K 1/30 - Moyens de montage ou de fixation des parties magnétiques tournantes sur ou aux structures constituant le rotor utilisant des pièces intermédiaires, p.ex. des croisillons
The invention relates to a fuel cell (1) having at least two bipolar plates (2) and at least one membrane-electrode arrangement (3) respectively arranged between two bipolar plates (2). Arranged between at least one bipolar plate (2) and a membrane-electrode arrangement (3) is a gas-diffusion layer (4), while at least one bipolar plate (2) has on the side facing the gas-diffusion layer (4) flow channels (4) for carrying a gas and/or a fluid, and the flow channels (5) are spaced apart from one another by webs (6). The invention also relates to a stack comprising two or more fuel cells (1).
H01M 8/026 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant caractérisés par les rainures, p.ex. leur pas ou leur profondeur
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
H01M 8/0267 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs comprenant des moyens de chauffage ou de refroidissement, p.ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
H01M 8/1004 - PROCÉDÉS OU MOYENS POUR LA CONVERSION DIRECTE DE L'ÉNERGIE CHIMIQUE EN ÉNERGIE ÉLECTRIQUE, p.ex. BATTERIES Éléments à combustible; Leur fabrication Éléments à combustible avec électrolytes solides caractérisés par les ensembles membrane-électrodes [MEA]
H01M 8/24 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible
H01M 4/86 - PROCÉDÉS OU MOYENS POUR LA CONVERSION DIRECTE DE L'ÉNERGIE CHIMIQUE EN ÉNERGIE ÉLECTRIQUE, p.ex. BATTERIES Électrodes Électrodes inertes ayant une activité catalytique, p.ex. pour piles à combustible
H01M 8/00 - PROCÉDÉS OU MOYENS POUR LA CONVERSION DIRECTE DE L'ÉNERGIE CHIMIQUE EN ÉNERGIE ÉLECTRIQUE, p.ex. BATTERIES Éléments à combustible; Leur fabrication
The present invention relates to a method for introducing a recess (3) into a workpiece (1), wherein the recess (3) is introduced by electrochemical removal by means of a processing cathode (2), wherein the removal exposes a flank (3.1) which bounds the recess (3) and extends from a first face (1.1) of the workpiece (1) in the direction of an opposite, second face (1.2) of the workpiece (1), wherein a protective anode (7.1, 7.2) is arranged on at least one of the faces (1.1, 1.2) during the removal, the protective anode being assigned to the flank (1.3) and lying against the at least one face (1.1, 1.2), in electrical contact with the workpiece (1), and wherein the protective anode (7.1, 7.2) is offset with respect to the flank (1.3) in the outward direction, that is to say away from the recess (3).
B23H 3/04 - Electrodes spécialement adaptées à cet effet ou leur fabrication
B23H 9/10 - Usinage d'aubes de turbine ou de buses
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
B23H 9/00 - Usinage spécialement conçu pour le traitement d'objets métalliques particuliers ou pour obtenir des effets ou des résultats particuliers sur des objets métalliques
B23H 11/00 - Appareils auxiliaires ou détails non prévus ailleurs
25.
METHOD FOR DETECTING AN ANOMALY IN OPERATING MEASUREMENT VALUES OF A TURBOMACHINE, AND ANALYSIS DEVICE AND MACHINE MONITORING DEVICE
The invention relates to a method for detecting an anomaly in operating measurement values (3) of a turbomachine (1), in particular an aircraft turbine, comprising: recording operating measurement values (3) of respective operating parameters (4) of a turbomachine (1) several times during an operating period of the turbomachine (1) by means of sensors (2) of the turbomachine (1); determining quasi-stationary time periods (10) of the operating time by means of an analysis device (7); generating quasi-stationary operating data points (17) for the quasi-stationary time periods (10), the quasi-stationary operating data points (17) comprising averaged operating measurement values (14); determining respective expectation data points (20) which comprise respective operating expectation values (21) of the respective operating parameters (4); determining respective operating measurement value residues (23) of the respective operating parameters (4); checking the operating measurement value residues (23) of the respective quasi-stationary operating data points (17) for compliance with predetermined anomaly criteria (24B) with respect to predetermined nominal values (25) of the operating measurement value residues; and transmitting an anomaly indicator (26) comprising a violated anomaly criterion (27) of the anomaly criteria (24B) and the time (28) of the violation to a machine monitoring device (9).
F01D 19/00 - Démarrage des "machines" ou machines motrices; Dispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
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
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
26.
METHOD FOR ELECTROCHEMICALLY MACHINING A WORKPIECE
The invention relates to a method for machining a workpiece (11) by means of an electrochemical machining process (51) in which material is removed from the workpiece (11) in an electrolyte liquid (15), wherein the electrolyte liquid (15) is then filtered (52) in a membrane filter system (20) which has a membrane (21) that undergoes a relative movement in the membrane filter system (20) during the filtering process, and the filtered electrolyte liquid (15) is reused for the electrochemical machining process (51).
The invention relates to a method for operating a combustion system (2) of a turbomachine (1) for a flight propulsion system, comprising a compressor (11), a combustion chamber (4), a turbine (15), a heat exchanger (16, 17) arranged downstream of the turbine (15) and a fuel treatment system (3). According to the invention, steam is produced in the heat exchanger (17) and guided into a mixing chamber (33, 37) of the fuel treatment system (2), to which furthermore fuel is supplied. The invention further relates to a turbomachine (1) comprising a combustion system (2) in particular for using the method.
The invention relates to a fuel cell device (1) which has a fuel cell stack (2). Respective end plates (5) are arranged on the opposite end surfaces (4) of the fuel cell stack (2), and the end plates (5) are connected by a tensioning device (17) of the fuel cell device (1) in order to clamp the fuel cell stack (2). According to the invention, at least one of the end plates (5) comprises a reinforcing device (8) which comprises at least one reinforcing element (7) with a fluid line (10).
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux
H01M 8/248 - Moyens pour comprimer les empilements d’éléments à combustible
H01M 8/2484 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible - Détails des groupements d'éléments à combustible caractérisés par les collecteurs d’admission externes
29.
ADJUSTABLE GUIDE VANE FOR A GAS TURBINE, GAS TURBINE AND METHOD FOR ASSEMBLING AN ADJUSTABLE GUIDE VANE FOR A GAS TURBINE
The invention relates to an adjustable guide vane (1) for a gas turbine (2), more particularly an aircraft gas turbine (2), comprising a vane shaft (3), wherein the vane shaft (3) has a vane shaft screw thread (6) at least in a region of a radially outer vane shaft end (5). The adjustable guide vane (1) has a lever device (7), which is disposed on the vane shaft (3), and the vane shaft (3) runs through a level opening (8, 14, 23) in the lever device (7). According to the invention, an external screw thread radius (22) of the external screw thread of the vane shaft screw thread (6) corresponds to the radius (25) of the vane shaft (3), the vane shaft (3) has at least one longitudinal groove (16), which extends from the radially outer vane shaft end (5) and runs parallel to the adjustment axis (4) on the vane shaft (3) up to a longitudinal groove end (17) of the longitudinal groove (16), and the lever device (7) has at least one protrusion (18, 19), the protrusion (18, 19) being disposed in the longitudinal groove (16) and being seated at the longitudinal groove end (17) of the longitudinal groove (16).
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 9/22 - Commande du débit du fluide de travail par réglage des aubes par réglage des aubes de turbine
30.
METHOD FOR IMAGING A SURFACE OF A TURBOMACHINE AND DETECTING DAMAGE
133), thus generating only a partial image (20.1-20.3) of the surface (21); - the imaging device (9) and the surface (21) are moved relative to each other such that different portions (31.1-31.3) of the surface (21) are captured over the course of time, thus generating different partial images (20.1-20.3), and wherein the partial images (20.1-20.3) are stitched (64) together to produce an image (40) of the surface (21).
The invention relates to a supply device (10) and to a method (100) for supplying an air bearing (11) by means of a fuel cell system (12), which comprises at least one anode (14) and at least one cathode (15) and a process gas device (17) for supplying the anode (14) and cathode (15) with fuel and ambient air and for discharging used process gases.
F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
F02C 7/06 - Aménagement des paliers; Lubrification
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
F16C 32/06 - Paliers non prévus ailleurs comprenant un élément mobile supporté par un coussinet de fluide engendré, au moins en grande partie, autrement que par la rotation de l'arbre, p.ex. paliers hydrostatiques à coussinet d'air
F16C 33/10 - Structures relatives à la lubrification
32.
FUEL CELL WITH STRUCTURAL ELEMENT INTEGRALLY BONDED TO A GAS DIFFUSION ELEMENT
A description is given of a fuel cell (10) comprising an electrode-membrane unit (22) comprising a cathode and an anode, a cathodal gas diffusion element (20), an anodal gas diffusion element (18), the electrode-membrane unit (22) being accommodated between the gas diffusion elements (18, 20); a cathodal bipolar plate (14), and an anodal bipolar plate (12). Provision is made here for the cathodal gas diffusion element (10) or/and the anodal gas diffusion element (18) to have at least one structural element (30) facing the respective bipolar plate (12, 14) and integrally bonded to the relevant gas diffusion element (18, 20).
H01M 4/86 - PROCÉDÉS OU MOYENS POUR LA CONVERSION DIRECTE DE L'ÉNERGIE CHIMIQUE EN ÉNERGIE ÉLECTRIQUE, p.ex. BATTERIES Électrodes Électrodes inertes ayant une activité catalytique, p.ex. pour piles à combustible
The invention relates to an aircraft having a fuel cell (20) and an air supply device (30) for feeding air for operating the fuel cell (20) and for cooling a heat exchanger (21) connected to the fuel cell (20), wherein the aircraft (1) has at least one air channel (10), the cross-section of which expands in the direction of flow (5) of the air downstream of an air inlet opening (11) in at least one region (35) of the peripheral surface. The invention also relates to a method for operating such a fuel cell (20) of an aircraft (1) with an air supply device (30) for operating the fuel cell (20) and for cooling a heat exchanger (21) connected to the fuel cell (20).
The invention relates to a fuel cell assembly with at least two flow-field plates (10) and at least one membrane-electrode assembly (20) interposed between two flow-field plates (10) each, and at least one flow modification element (30) each of which is interposed between a flow-field plate (10) and a membrane-electrode assembly (20). The flow modification element (30) has at least one sealing device (40).
H01M 8/0273 - Moyens d’étanchéité ou de support autour des électrodes, des matrices ou des membranes avec des moyens d’étanchéité ou de support sous forme d’un cadre
H01M 8/0276 - Moyens d’étanchéité caractérisés par leur forme
35.
DATA PROCESSING SYSTEM AND METHOD FOR TEMPORALLY SYNCHRONIZING ANALOGUE AND DIGITAL DATA SETS OF PRODUCTION MACHINES
The invention relates to a data processing system (10) comprising: at least one digitally controlled production machine (12) for producing or/and manufacturing a workpiece (14); at least one analogue data acquisition sensor device (22a-d) which is designed to acquire status information about the production machine (12) or/and the workpiece (14) to be produced or/and the spatial surroundings of the production machine (12) as a status data set (ZS) at an analogue data rate; at least one analogue data acquisition device (24) which is connected to the at least one sensor device (22a-d) and which is designed to digitize analogue status data sets (ZS) that have been received and to allocate a corresponding analogue data time stamp (ts) to the digitized status data sets (ZS); at least one digital data acquisition device (26) which is connected to the at least one production machine (12) and which is designed to process digital control data sets (SDS) of the production machine (12), to generate, at a digital data rate, control data packets (SDP) each having a plurality of control data sets (SDS), and to allocate a corresponding digital data time stamp (ts) to a control data packet (SDP); at least one digital data storage device (28) which is connected to the analogue data acquisition device (24) and to the digital data acquisition device (26) and which is designed to at least temporarily store the digitized status data sets (ZS) and the digital control data packets (SDP); wherein the analogue data rate is larger than the digital data rate so that, per time unit, there are more analogue data sets (ZS) having a corresponding analogue data time stamp (ts) than there are control data packets (SDP) having a corresponding digital data time stamp (ts); and at least one data processing module (30) which is designed to determine, for the individual control data sets (SDS) of a control data packet (SDP) provided with a digital data time stamp (ts), the number and sequence of individual data set time stamps for the control data sets (SDS), so that a control data set (SDS) can be allocated to each status data set (ZS).
G05B 19/408 - Commande numérique (CN), c.à d. machines fonctionnant automatiquement, en particulier machines-outils, p.ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'u caractérisée par le maniement de données ou le format de données, p.ex. lecture, mise en mémoire tampon ou conversion de données
G05B 21/00 - Systèmes impliquant l'échantillonnage de la variable commandée
G05B 19/042 - Commande à programme autre que la commande numérique, c.à d. dans des automatismes à séquence ou dans des automates à logique utilisant des processeurs numériques
G05B 19/05 - Automates à logique programmables, p.ex. simulant les interconnexions logiques de signaux d'après des diagrammes en échelle ou des organigrammes
36.
AIR HUMIDIFIER, METHOD FOR OPERATING AN AIR HUMIDIFIER, AND SYSTEM HAVING AT LEAST ONE AIR HUMIDIFIER
The invention relates to an air humidifier (1) having a mixing chamber (5) in which an atomizing nozzle (9) is arranged which is designed to dispense a liquid (25) as a spray mist (10). The mixing chamber (5) is designed such that a gas (26) conveyed along a main flow path (8) through the mixing chamber (5) is mixed with the spray mist (10) and is discharged at an outlet opening (7) of the mixing chamber (5). The atomizing nozzle (9) has a swirl device which is designed to set droplets (11) of the spray mist (10) in a swirling motion in order to dispense the spray mist (10) as an opening straight spray circular cone (12). It is provided that the mixing chamber (5) has a separating device (16) which is designed such that droplets (11) of the spray circular cone (12) which, starting from the atomizing nozzle (9), move along a hollow cone (14) having a predetermined inner angle (15) are caught, and droplets (11) which move inside the hollow cone (14) are fed to the outlet opening (7) of the mixing chamber (5).
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyte; Humidification ou déshumidification
The invention relates to a component-classifying apparatus (1) for classifying components (3) into predefined component classes (16), comprising a camera device (6) designed to generate image data (7) relating to a component (3) to be classified and a weighing device (4) designed to generate weight data (5) relating to the component (3) to be classified. The component-classifying apparatus (1) comprises an evaluation device (12), which is designed to generate predefined image features (13) from the image data (7) by means of a predefined image-feature extraction method, to feed the image data (7) to a pre-trained first neural network, and to generate bottleneck features (14) of the image data (7) from a predefined bottleneck layer (25) of the first neural network (23). The component-classifying apparatus (1) comprises a classifying device (15), which is designed to assign at least one of a plurality of predefined components classes (16), which describe predefined component groups and/or components (3), to the component (3) by means of a predefined classification method, on the basis of the weight data (5), the image features (13), and the bottleneck features (14).
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
G06V 20/52 - Activités de surveillance ou de suivi, p.ex. pour la reconnaissance d’objets suspects
The invention relates to a device for holding a component that is to be machined, comprising a component clamping system, into which the component can be clamped, and a sensor system, the sensor system being integrated into the component clamping system.
B23Q 17/09 - Agencements sur les machines-outils pour indiquer ou mesurer pour indiquer ou mesurer la pression de coupe ou l'état de l'outil de coupe, p.ex. aptitude à la coupe, charge sur l'outil
The invention relates to a fuel cell, in particular for use in aeronautics, comprising at least two flow field plates (10) and at least one membrane electrode assembly (20) which is arranged between a pair of flow field plates (10), the flow field plate (10) having, on at least one side, at least one flow profile (11, 12) for directing a process gas on the membrane-electrode assembly (20). According to the invention, at least two separate flow profiles (11, 12) are arranged on the at least one side of the flow field plate (10).
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
H01M 8/0263 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant comprenant des chemins zigzagants ou en serpentins
H01M 8/0265 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant les canaux des réactifs ou du réfrigérant ayant des sections transversales variables
H01M 8/0267 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs comprenant des moyens de chauffage ou de refroidissement, p.ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
The present invention relates to a method for testing a tool (2) intended for machining a workpiece (4), said tool (2) being penetrated by a channel (7) for rinsing the inside of the tool, the channel (7) running into a port (8) in a surface (9) of the tool (2); in said testing method, a test fluid (35) is delivered to the channel (7) in the tool (2), and in order to test the tool, a flow rate of the test fluid (35) through the channel (7) is measured.
The present invention relates to a method for operating a flight-propulsion system (1) of an aircraft (40), the flight-propulsion system (1) having a propulsion unit (2), a water discharger (20) arranged downstream of the propulsion unit (2), and a reservoir (24) for receiving water (17), in which method the propulsion unit (2) is operated and, during a flight of the aircraft (40), water (17) resulting from the operation of the propulsion unit (2) is discharged by the water discharger (20), wherein at least some of the discharged water (17) is fed to the reservoir (24), and wherein at least some of the water (17) that is fed to the reservoir (24) is given off to the surroundings (29) while the flight is still in progress, that is to say is only temporarily stored in the reservoir (24).
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
F01D 25/32 - Recueil de l'eau de condensation; Drainage
42.
METHOD FOR PREVENTING DAMAGES DUE TO RESONANCE DURING THE CLEANING OF AN AT LEAST PARTIALLY ADDITIVELY MANUFACTURED COMPONENT, AND CLEANING DEVICE
The invention relates to a method for cleaning a component (3) from powder residues of an additive layering method using a cleaning device (1), wherein a machine plate (2) and the component (3) arranged thereon are excited during a cleaning process by a vibration actuator (4) of the cleaning device (1) with a set resonance frequency of the machine plate (2) to carry out a mechanical vibration. It is provided that the machine plate (2) is excited by predefined vibration movements of the at least one vibration actuator (4) to the predefined mechanical vibration, wherein the predefined vibration movements of the at least one vibration actuator (4) occur in parallel to a main plane (6) of the machine plate (2). The invention also relates to a cleaning device (1) for cleaning an at least partially additively manufactured component (3), in particular a component (3) of a turbomachine.
hohl1hohlhohl in a first portion (32) at the first end (31), wherein the blade (22) is gripped in the first portion (32) during joining to the main body (21).
B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
The invention relates to a method for cleaning powder residues of an additive layer build-up method away from an at least partly additively manufactured component (3) by means of a cleaning device (1), wherein a machine plate (2) and the component (3) arranged thereon are excited to mechanical oscillation during a cleaning process by a vibration actuator (4) of the cleaning device (1) with a set resonant frequency of the machine plate. According to the invention, before the cleaning process is carried out, a resonant frequency of the machine plate (2) is set to the set resonant frequency by an arrangement of a mass element (6) on a securing element of the machine plate (2), wherein the set resonant frequency is ascertained according to a predetermined selection method depending on at least one resonant frequency of the component (3), and the margin separating the set resonant frequency of the machine plate (2) from the at least one resonant frequency of the component (3) is greater than that separating the resonant frequency of the machine plate (2) without the arranged mass element (6), and at least one parameter of the mass element (6) is ascertained according to a predetermined ascertaining method depending on the set resonant frequency of the machine plate (2). The invention furthermore relates to a cleaning device (1) for cleaning an at least partly additively manufactured component (3).
The present invention relates to a method for checking a component, in particular a component of a turbomachine (1), comprising the steps of: - taking (S2) at least one X-ray image or CT image of the component (10) using an image capturing device (20); - providing (S21) metadata to the component (10), which include in particular the type of component, an operational life of the component (10), a number of remaining life cycles and/or a repair history; - classifying the component (10) based on the image taken by the image capturing device (20) and the provided metadata into a "Servicable" or a "Non-Servicable" category by means of a machine learning system (30).
G01N 23/046 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et formant des images des matériaux en utilisant la tomographie, p.ex. la tomographie informatisée
G01N 23/083 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en transmettant la radiation à travers le matériau et mesurant l'absorption le rayonnement consistant en rayons X
G01N 23/18 - Recherche de la présence de défauts ou de matériaux étrangers
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
46.
A COMPUTER-IMPLEMENTED METHOD FOR TRAINING AN ARTIFICIAL NEURAL NETWORK, METHOD FOR INSPECTING A COMPONENT, TEST SYSTEM FOR EXAMINING COMPONENTS, AND COMPUTER PROGRAM
The invention relates to a computer-implemented method for training an artificial neural network, comprising the steps of creating the artificial neural network, producing at least one test body with at least one real microstructure defect, ultrasonically measuring the test body at least region-wise while obtaining first ultrasonic measurement data, ultrasonic measuring at least at part of a preferably microstructure defect-free component while obtaining second ultrasonic measurement data, determining microstructure defect data which characterize real and/or artificial microstructure defects in the first and/or second ultrasonic measurement data, and training the artificial neural network by means of a computer system using the first ultrasound measurement data, the second ultrasound measurement data and the microstructure defect data, wherein the microstructure defect data are used as labels. The invention further relates to a method for inspecting a component (10), a test system (8) for examining components (10), a computer program, and a computer-readable storage medium.
The invention relates to an air supply device (10) and to a method for supplying at least one fuel cell (20) of an aircraft fuel cell drive with compressed air, wherein the aircraft fuel cell drive has an air supply device (10) comprising a compressor arrangement (11), wherein ambient air is compressed by means of the compressor arrangement (11) and a first part of the compressed air is supplied to the at least one fuel cell (20) and a second part of the compressed air can be diverted to a cooling device of the at least one fuel cell by means of a bypass device.
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
H01M 8/04014 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur Échange de chaleur par combustion des réactifs
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyte; Humidification ou déshumidification
The invention relates to a cooling system (10) for an aircraft, in particular for cooling at least one element of an electrical drive system (24) of the aircraft, wherein the cooling system (10) is arranged at least in part inside a wing (12) of the aircraft and comprises at least two heat exchangers (16, 42) which are connected via at least one cooling circuit (11), wherein the first heat exchanger (16) is operatively connected to the at least one element to be cooled of the electrical drive system (24), and the second heat exchanger (42) is arranged inside at least one wing (12) and is operatively connected to an upper and/or lower wing shell (46, 48) of the wing (12). The invention also relates to a method for cooling at least one element of an electrical drive system (24) of an aircraft.
The present invention relates to a method for producing a component from an alloy and to a corresponding component, wherein, in the method, first a blank (11) is built up layer-by-layer from a plurality of layers (12) by means of a generative method and the blank (11) is subsequently subjected to a shaping process by forging in order to obtain a forged part, the shaping process by forging being performed with a forging direction which is carried out transversely to the layers (12) of the blank (11).
B21J 1/06 - Méthodes ou dispositifs de chauffage ou de refroidissement spécialement adaptés aux opérations de forgeage ou de pressage
B21J 5/00 - Méthodes pour forger, marteler ou presser; Equipement ou accessoires particuliers
B22F 3/17 - Fabrication de pièces ou d'objets à partir de poudres métalliques, caractérisée par le mode de compactage ou de frittage; Appareils spécialement adaptés à cet effet par forgeage
B22F 10/64 - Traitement de pièces ou d'articles après leur formation par des moyens thermiques
B33Y 40/20 - Posttraitement, p.ex. durcissement, revêtement ou polissage
B33Y 80/00 - Produits obtenus par fabrication additive
C22C 1/04 - Fabrication des alliages non ferreux par métallurgie des poudres
C22F 1/18 - Métaux réfractaires ou à point de fusion élevé ou leurs alliages
B22F 10/66 - Traitement de pièces ou d'articles après leur formation par des moyens mécaniques
50.
METHOD FOR SCHEDULING MAINTENANCE OF AIRCRAFT ENGINES
The present invention relates to a method, in particular a computer-implemented method, for the automated creation of an optimized maintenance schedule for a fleet of aircraft engines, wherein the method comprises at least the following steps: acquiring input data (110) relating to a plurality of engines, which represents maintenance-related information for the fleet of aircraft engines individually and/or as a whole and in particular comprises a mean time between shop visits (MTB SV) or data relating to life limited parts (ELP) of the engines (E1, E2, E3, E4); providing an existing initial maintenance schedule (140) or creating an initial maintenance schedule (140) on the basis of the input data (110) acquired, in particular the MTB SV and/or ELP data, for the engines (E1, E2, E3, E4); and creating an optimized maintenance schedule for the fleet, proceeding from the initial maintenance schedule, in at least one of the following ways: (a) iteratively optimizing the maintenance schedule on the basis of algorithmically stored heuristics; (b) using a trained optimization method based on machine learning for optimizing the maintenance schedule.
G06Q 10/06 - Ressources, gestion de tâches, des ressources humaines ou de projets; Planification d’entreprise ou d’organisation; Modélisation d’entreprise ou d’organisation
G06Q 10/04 - Prévision ou optimisation spécialement adaptées à des fins administratives ou de gestion, p. ex. programmation linéaire ou "problème d’optimisation des stocks"
The invention relates to a device (10) and a method for cooling a heat exchanger (12) of a fuel cell (16) of a flight propulsion drive outside of a flight phase of an aircraft. The flight propulsion drive has an air line (20) with at least one compressor (21, 22, 23) for feeding compressed air for the operation of the fuel cell (16). A flow amplifier (40) is arranged in the region of the heat exchanger (12) and is configured to guide air onto a cooling surface (13) of the heat exchanger (12), whereby thermal energy is diverted from the cooling surface (13) off the heat exchanger (12).
The invention relates to a method for testing components (10), in particular of a continuous-flow machine. In carrying out the method, a component (10) is first provided, for example in the form of a compressor blade, and image data of the component surface (10a) are captured by means of a photogrammetry device (11) provided for this purpose. A volume model (21) of the component (10) is generated herefrom. Potential component defects (25) are then identified on said volume model (21) and actual component defects (26) are determined in particular using a human-machine interface (20).
The present invention relates to a heat engine (1), in particular an aircraft engine (3), having a first compressor (10) for supplying a combustion chamber (11) of the heat engine (1) with air and a first turbine (12) arranged downstream of the combustion chamber (11) for driving the first compressor (10), wherein the heat engine also has at least one steam supply line (24) for supplying steam from a steam source (25) into the combustion chamber (11). The heat engine (1) also has a steam supply device (2), which has a second compressor (20) and is designed to compress the working gas further by means of the second compressor (20) as a function of a mass flow conducted through the steam supply line (24), before said working gas flows into the combustion chamber (11).
The present invention relates to an exhaust-gas treatment device (1) for an aircraft engine (2), comprising: - an exhaust-gas channel (4), through which an exhaust gas (3) of the aircraft engine (2) flows; and - a first cooling unit (8) for cooling with ambient air (10); characterized by a second cooling unit (11), which is downstream of the first cooling unit (8) with respect to an exhaust-gas flow (5) in the exhaust-gas channel (4).
The present invention relates to an aircraft (5), comprising: - at least one wing (50); - at least one flight propulsion device (2); and - a retainer, more particularly an engine pylon (4), which interconnects the wing and the flight propulsion drive. The aircraft has at least one heat exchanger (30) for cooling exhaust gas of the flight propulsion drive and/or at least one water removal channel (200) having at least one removal apparatus (42, 43, 43', 45, 210, 220) for removing water from exhaust gas of the flight propulsion drive, more particularly after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means at least one flight-propulsion-drive suspension means (20, 21) and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat-exchanger suspension means (38).
The invention relates to a rotor clamping composite (10) of a turbomachine, in particular a rotor, said composite being secured against rotation, comprising at least two composite components (11) which are arranged one behind the other in the axial direction of the turbomachine and which are clamped against each other in the axial direction. Each of the composite components (11) is directly or indirectly connected in a non-positive manner in order to transmit a torque, for example by means of a frictional connection, via at least one respective rotationally symmetrical contact surface (12) which is arranged in a substantially radial manner. Each of the at least at least two composite components (11) has at least one stop surface (13, 14, 15), on which a torque transmission between the at least two composite components (11) is facilitated in the event of a failure of the non-positive connection.
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
F16D 1/033 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour liaison bout à bout de deux arbres ou de deux pièces analogues par serrage de deux surfaces perpendiculaires à l'axe de rotation, p.ex. avec des brides boulonnées
57.
METHOD FOR DETERMINING INDIVIDUAL VECTORS FOR OPEN-LOOP AND/OR CLOSED-LOOP CONTROL OF AT LEAST ONE ENERGY BEAM OF A LAYERING APPARATUS, AND LAYERING APPARATUS
The invention relates to a method for determining individual vectors for open-loop and/or closed-loop control of at least one energy beam of a layering apparatus, comprising at least the steps of a) providing layer data characterising at least one component layer of a component to be additively manufactured, b) on the basis of the layer data, determining individual vectors, according to which at least one energy beam (28) is to be moved relative to a construction and joining zone (II) of the layering apparatus (10) in order to solidify a material powder selectively to the component layer, c) determining at least one node point (40) of a plurality of individual vectors and d) adapting at least one property of at least one individual vector of the at least one node point (40), the at least one property being selected from a group comprising spatial orientation, radiation sequence in relation to at least one other individual vector, and vector length. The invention also relates to a layering apparatus (10) for the additive manufacture of at least one component region (12) of a component (14) by means of an additive layering method.
The invention relates to a guide vane (10) for arrangement in a gas duct (14) of a turbomachine (1), said guide vane comprising a guide vane blade (11) and an outer platform (12) and being arranged radially outside on the guide vane blade (11) with respect to a longitudinal axis (2) of the turbomachine (1). The outer platform (12) radially outwardly delimits the gas duct (14) with an inner wall surface (13). When viewed in an axial cross-section, the inner wall surface (13) has a curved profile with an inflection point (16), and specifically has a concave curvature (20) in a first axial section (13.1) which is located upstream of the inflection point (16) with respect to a throughflow (17) of the gas duct (14), and has a convex curvature (21) in a second axial section (13.2) which is located downstream of the inflection point (16) with respect to the throughflow (17) of the gas duct (14). The invention also relates to a compressor module and to a turbomachine.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
The invention relates to a guide vane assembly (20) for a turbomachine (1), comprising: - a guide vane (21), which has a guide vane airfoil (31); and - a guide vane holder (22). The guide vane (21) is mounted in the guide vane holder (22) such that the guide vane can be moved about an axis of rotation (28). For this purpose, the guide vane (21) has at least one axle element (25), which is inserted into the guide vane holder (22) in such a way that an outer lateral surface (25.1) of the axle element (25) faces an inner lateral surface (22.1) of the guide vane holder (22). A protective coating (47) is applied to at least parts of the guide vane airfoil (31). A protective coating (37) is applied to at least one of the lateral surfaces (22.1, 25.1). The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly (20).
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
60.
BLADE FOR A TURBOMACHINE, HAVING BLADE-TIP ARMOR PLATING AND ANTI-EROSION LAYER, AND METHOD FOR PRODUCING SAID BLADE
The present invention relates to a blade for a turbomachine, the blade having blade-tip armor plating (5) on its blade tip (4) and having an anti-erosion layer (11) over the blade-tip armor plating. The anti-erosion layer of the blade has, in the region of the blade tip, a layer thickness in the range of 5 to 100 μm, more particularly 10 to 50 μm.
C23C 28/00 - Revêtement pour obtenir au moins deux couches superposées, soit par des procédés non prévus dans un seul des groupes principaux , soit par des combinaisons de procédés prévus dans les sous-classes et
C23C 14/06 - Revêtement par évaporation sous vide, pulvérisation cathodique ou implantation d'ions du matériau composant le revêtement caractérisé par le matériau de revêtement
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
The present invention relates to a guide blade arrangement (20) for a turbomachine (1), having a guide blade aerofoil (22), and having a platform (21), wherein the guide blade aerofoil (22) is arranged on a side (21.1), which faces a gas channel, of the platform (21), wherein an opposite side (21.2), which is averted from the gas channel, of the platform (21) is contoured at least in one region (30.1, 30.2) with elevations (25) and depressions (26) which follow one another in a circumferential direction (23) in relation to a longitudinal axis (2) of the turbomachine (1), and wherein the elevations (25) and depressions (26) on the side (21.2) averted from the gas channel are implemented by means of a respectively radially measured platform thickness (3) which varies in the circumferential direction (23) and which repeatedly increases and decreases with a continuous profile.
The invention relates to a machining apparatus (10) for electrochemically removing component layers of a component (12), having at least one electrode (20), which is mounted so as to be movable along at least one infeed axis (30), and having at least one auxiliary electrode (60), which is mounted so as to be movable along an auxiliary infeed axis (70), wherein a gap (90) for arranging the component (12) for electrochemically removing the component layers extends between the at least one electrode (20) and the at least one auxiliary electrode (60). At least the infeed axis (30) and a longitudinal extension direction (92) of the gap (90) enclose an acute angle (a) with one another. The machining apparatus (10) comprises at least one oscillation device (40), which is set up at least to move the at least one electrode (20) in an oscillating manner along the infeed axis (30) and relative to the at least one auxiliary electrode (60). A further aspect of the invention relates to a method for electrochemically removing component layers of a component (12) using a machining apparatus (10).
The invention relates to a method comprising the steps: - carrying out multiple measurements on a mechanical object, the measurements each differing by one or more parameters influencing the measurement; - determining a spectrogram on the basis of the measurement data of the measurements and depending on a predefined parameter of the mechanical object; - determining one or more excitations of the mechanical object; - reproducing the excitations in the spectrogram.
The invention relates to a method for repairing a sealing-air apparatus (10) for a turbomachine (100) comprising the steps of: a) providing the sealing-air apparatus, which is designed to seal a sealing gap (50) between two components (30, 40) of the sealing-air apparatus (10) with respect to a sealing-air flow (12), a first component (30) comprising a receiving region (32), which receiving region has at least two protrusions (36, 38), between which a groove (34) for receiving a sealing ring (14) designed to seal the sealing gap extends; b) removing at least one damaged protrusion portion (37) of at least one first protrusion (36); c) arranging the sealing ring and a supporting device (20) of the sealing-air apparatus on the first component, which supporting device is designed to support the sealing ring in the direction of axial extension (A) of the first component, the supporting device being supported on a contact region (39) of the sealing-air apparatus in order to prevent relative motion (RB) away from a second protrusion (38) in the direction of axial extension between the supporting device and the second protrusion, and the sealing ring being arranged between the supporting device and the second protrusion.
F01D 11/04 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages par obturation non contact, p.ex. du type labyrinthe utilisant un fluide d'obturation, p.ex. de la vapeur
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
B23P 6/00 - Remise en état ou réparation des objets
F16J 9/00 - Segments de piston, leurs logements; Segments d'étanchéité de structure similaire en général
F16J 15/06 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre
65.
SEALING DEVICE FOR A SEALING-AIR APPARATUS OF A TURBOMACHINE, AND ASSOCIATED REPAIR METHOD
The invention relates to a sealing-air apparatus (10) for a turbomachine (100), comprising a sealing device (20) for sealing a sealing gap (50) between two components (30, 40) of the sealing-air apparatus (10) with respect to a sealing-air flow (12), at least one first component (30) of the two components (30, 40) having a receiving region (32), which is designed to hold a sealing ring (14) designed to seal the sealing gap (50). The sealing device (20) is interlockingly coupled to the first component (30) in the receiving region (32) and is at least indirectly braced to the first component (30) in the direction of radial extent (R) of the sealing device (20). Other aspects of the invention relate to a sealing device (20) for a sealing-air apparatus (10), to a turbomachine (100) and to a method for repairing a sealing-air apparatus (10).
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
F02C 7/28 - Agencement des dispositifs d'étanchéité
F16J 15/16 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre
The invention relates to a monitoring system (12) for a gas turbine (10), in particular for an aircraft engine. The monitoring system (12) comprises at least one borescope device (24) that is able to be mounted in a borescope opening (22) of a gas turbine housing (14) and has a housing (26) in which at least one optical sensor device (28) for acquiring images of at least one inner region of the gas turbine (10) is arranged, and an evaluation device (34) that is able to be coupled to the at least one borescope device (24) in order to exchange data and is designed to inspect the at least one inner region for the presence of a fault on the basis of the at least one image acquired by way of the sensor device (28). The invention furthermore relates to a borescope device (24), to an evaluation device (34) and to a gas turbine (10).
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
F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
G01N 21/954 - Inspection de la surface intérieure de corps creux, p.ex. d'alésages
G02B 23/24 - Instruments pour regarder l'intérieur de corps creux, p.ex. endoscopes à fibres
The present invention relates to a guide vane (20) for arrangement in a gas duct (2) of a turbomachine (1), having a guide vane blade (23), which, viewed in a tangential section, has a vane blade profile (24) with a leading edge radius RVK and a vane blade thickness d, wherein the vane blade profile (24) is thickened, at least in sections, specifically the vane blade thickness d is specified, in relation to the leading edge radius RVK, such that (2 d / Rvk2) - d ≤ 5.5.
The invention relates to a rotor (10) for a turbomachine (100), having at least one blade and having at least one rotor main part (20) which has at least one recess (22) in which a blade root (40) of the at least one blade is interlockingly received, wherein the blade root (40) comprises at least one depression (42) in which at least one protrusion (24) of the at least one rotor main part (20), which protrusion delimits the at least one recess (22) in regions, is received, wherein the at least one depression (42) is delimited by a first delimiting face (50) on the blade root side and the at least one protrusion (24) is delimited by a second delimiting face (30) on the rotor main part side. At least the first delimiting face (50) has at least one elevation (60) which narrows a gap (12), at least in regions, which extends between the first delimiting face (50) and the second delimiting face (30). A second aspect of the invention relates to a turbomachine (100) having a rotor (10).
The present invention relates to a method for detecting a first component (21.1) of a turbomachine (1), in which method - a first image (41) of the first component (21.1) is recorded (61); - on the basis of the first recorded image (41), any abnormalities (23) in a region (35) of the first component (21.1) are identified (62); - a second image (42) of the first component (21.1) is recorded (63), more specifically of said region (35) and with a greater resolution than the first recorded image (41); the first and the second recorded images (41, 42) being recorded by means of different recording or measurement methods.
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
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
The present invention relates to a tool (25) for machining a component (22), said tool comprising a tool head (26) and a shaft (27) on which the tool head (26) is arranged. The tool head (26) is arranged on the shaft (27) so that it can be hinged out laterally, i.e. in a hinged-in state it is arranged closer to the shaft (27) than in a hinged-out state, and, at least in the hinged-out state, the tool head (26) can be made to rotate in order to machine the component (22), a drive element (41) being provided as part of the shaft (27) in such a way that a movement of the drive element (41) via a coupling causes the tool head (26) to rotate.
B23Q 1/48 - Supports mobiles ou réglables d'outils ou de pièces utilisant des mécanismes particuliers avec des guidages en translation et des guidages en rotation
B23C 1/12 - Machines à fraiser non conçues pour des pièces particulières ou des opérations spéciales avec une broche orientable sous différents angles, p.ex. horizontalement ou verticalement
B23C 3/18 - Usinage de surfaces à double courbure pour le façonnage d'hélices, d'aubes de turbines ou de roues à ailettes
B23Q 1/54 - Supports mobiles ou réglables d'outils ou de pièces utilisant des mécanismes particuliers avec des guidages en rotation uniquement avec deux guidages en rotation uniquement
B24B 23/08 - Machines de meulage portatives conçues pour être fixées sur les pièces ou sur d'autres éléments de section particulière, p.ex. pour le meulage de commutatrices
B24B 27/00 - Autres machines ou dispositifs à meuler
B23P 6/00 - Remise en état ou réparation des objets
B23Q 5/04 - Entraînement des principaux organes de travail des arbres rotatifs, p.ex. des broches de travail
72.
METHOD AND APPARATUS FOR DETERMINING UPVALUE FACTORS FOR EXPANSION MEASUREMENTS ON MACHINE ELEMENTS
The present invention relates to an apparatus and a method for determining an upvalue factor for an expansion measurement in a machine element (1), comprising steps for measuring (S3) an expansion in a measurement surface portion (3) by means of an expansion measuring device (2); for measuring (S4) a displacement of a detection surface portion (4) of the machine element (1) by optical scanning; for determining (S5) a displacement field on a surface of the machine element (1) based on a model of the machine element (1) and the measured displacement of the at least one detection surface portion (4); for determining (S6) an expansion field on the surface of the machine element (1) based on the determined displacement field and the model of the machine element (1); and for determining (S7) an upvalue factor of the expansion measuring device (2) based on the determined expansion field and the measured expansion in the measurement surface portion (3).
G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p.ex. fléchissement de ponts ou d'ailes d'avions
G01B 21/04 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la longueur, la largeur ou l'épaisseur en mesurant les coordonnées de points
G01B 21/32 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la déformation dans un solide
G01B 11/16 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la déformation dans un solide, p.ex. indicateur optique de déformation
73.
COMPRESSOR HAVING ADJUSTMENT STATOR BLADES AND DRAINAGE OF A LEAKAGE FLOW
Proposed is a compressor, comprising a stator having at least one blade (32) and a rotor, wherein: the blade (32) of the stator is located in an annular space (20); the annular space (20) is delimited by an interior wall (21) and a housing wall (24); the blade (32) can be adjusted by means of a first adjustment plate (40) arranged in a recess of the interior wall (21) and a second adjustment plate (45) arranged in a recess of the housing wall (24), characterised in that a first flow channel (60) in the first adjustment plate (40) is designed in such a manner that fluid flows out of an intermediate space (50) between the first adjustment plate (40) and the interior wall (21) through the first adjustment plate (40) to a first outlet (64), wherein the first outlet (64) is located outside the intermediate space (50) between the first adjustment plate (40) and the interior wall (21), and/or that a second flow channel (70) in the second adjustment plate (45) is designed in such a manner that fluid flows out of an intermediate space (52) between the second adjustment plate (45) and the housing wall (24) through the second adjustment plate (45) to a second outlet (74), wherein the second outlet (74) is located outside the intermediate space (52) between the second adjustment plate (45) and the housing wall (24).
The invention relates to a seal carrier (50) for a turbomachine, in particular a gas turbine, having a carrier base (52) and at least one seal body (54), wherein the at least one seal body (54) is connected to the carrier base (52) and wherein the at least one seal body (54) is formed by a plurality of cavities (56) arranged next to one another, in particular uniformly, in the peripheral direction (UR) and in the axial direction (AR), wherein the cavities (54) extend out from the carrier base (52) in the radial direction (RR) and are delimited by a cavity wall (58). According to the invention, the seal body (54) has a plurality of damping portions (62) which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base (52) is continuous in the region of the damping portions (62).
F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p.ex. un élément d'usure, déformable ou contraint de façon élastique
The present invention relates to a guide vane arrangement (20) for a turbomachine (1), with a guide vane blade (21) which has a pressure side surface (36) and a suction side surface (35), wherein the guide vane blade (21) is mounted such that it can be rotated about a rotational axis (23) on a gas duct wall (22) which delimits a gas duct (42), and wherein, in relation to a flow around the guide vane blade (21) in the gas duct (42), the rotational axis (23) is arranged in a front section (30) of the guide vane blade (21), and a covering surface of the guide vane blade (21) delimits a gap (33) with the gas duct wall (22) in a rear section (31), wherein, as viewed in a sectional plane (46) which lies perpendicularly with respect to a mean line (45), the gap (33) widens from the pressure side surface (36) to the suction side surface (35) in such a way that it forms a diffuser (50) for a gap flow (37) which is driven by way of a pressure gradient between the pressure side surface (36) and the suction side surface (35).
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 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages par obturation non contact, p.ex. du type labyrinthe
F04D 29/16 - Joints d'étanchéité entre le côté du refoulement et celui de l'aspiration
F04D 29/56 - Moyens de guidage du fluide, p.ex. diffuseurs réglables
76.
METHOD AND APPARATUS FOR DETERMINING AT LEAST ONE MECHANICAL PARAMETER OF A MECHANICAL OBJECT
The invention relates to a method comprising the steps: - first exciting of the object by means of a multi-frequency signal; - detecting a first response signal of the object at one or more measurement points on the object; - transforming the first response signal from a time range to a frequency-dependent range; - selecting from one or more frequencies on the basis of the frequency-dependent range; - second exciting of the object on the basis of the selected frequencies; - detecting a second response signal of the object at one or more measurement points of the object; - determining a mechanical parameter on the basis of the second response signal.
The invention relates to a substrate, in particular a component of a turbomachine, made from a composite material having a ceramic matrix and having a protective layer against environmental influences, the protective layer being arranged on the ceramic matrix. The protective layer comprises a mixture of rare-earth monosilicate and rare-earth disilicate, the proportion of the monosilicate in the mixture being more than 50 mol%. A layer of this type is, in particular, able to effectively protect the substrate, at high temperatures, from attack by calcium‐magnesium‐aluminosilicates (CMASs). The invention further relates to a method for producing the substrate.
The invention relates to a method for monitoring an additive layering process by means of which at least one component (12) is produced. The method comprises at least the steps of: obtaining a plurality of layer images (10) during the layering process, each layer image characterising an energy input into a component layer that is currently being produced; generating an average value image (14) on the basis of the layer images (10) by determining, for each pixel position, an average intensity value of the obtained layer images (10); and checking, on the basis of the average value image (14), if there is a decrease in intensity which breaches a predetermined quality criterion. The invention also relates to a device for monitoring an additive layering process and to a computer program product.
B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
B22F 10/31 - Commande ou régulation des opérations Étalonnage des étapes de procédé ou réglages des appareils, p.ex. avant ou en cours de fabrication
B22F 10/85 - Acquisition ou traitement des données pour la commande ou la régulation de procédés de fabrication additive
B22F 12/90 - Moyens de commande ou de régulation des opérations, p.ex. caméras ou capteurs
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 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
G05B 19/4099 - Usinage de surface ou de courbe, fabrication d'objets en trois dimensions 3D, p.ex. fabrication assistée par ordinateur
The present invention relates to a rotor blade arrangement for a turbomachine, with a rotor blade which has a sealing tip radially on the outside, and with a seal arrangement, wherein the seal arrangement forms a radially inwardly open cavity, in which the sealing tip is arranged, to which end the seal arrangement has a first sealing element, namely a first seal carrier with a first run-in coating, and a second sealing element, wherein the first run-in coating delimits the cavity radially on the outside, and the second sealing element delimits the cavity in an axial direction, and wherein the first and the second sealing element are assembled.
F01D 5/20 - Extrémités de pales spécialement façonnées en vue d'obturer l'espace entre ces extrémités et le stator
F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p.ex. un élément d'usure, déformable ou contraint de façon élastique
F01D 5/22 - Connections aube à aube, p.ex. par emboîtement
The present invention relates to a guide vane assembly for a turbomachine, in particular a compressor stage or turbine stage of a gas turbine, comprising at least one guide vane that is adjustable about a rotational axis (D), the vane blade (10) of which guide vane is arranged between a first wall (1) and a second wall (2) and comprises a pressure side (11) and a suction side (12) that follows in a peripheral direction, wherein at least one of these walls comprises a first channel which is associated with this guide vane and has a rear flank (22) and a front flank (21) that is closer to the rotational axis, which rear flank and front flank are interconnected by a first end (23) and a second end (24), which follows in the peripheral direction, of the first channel, and wherein, in at least one position of the guide vane, in particular across at least one quarter of an adjustment range of the guide vane and/or in the design operating point, a blade-side opening (25) of the first channel and a projection, towards this wall, of an end face (13) of the vane blade of the guide vane on the side of the rotational axis, which end face faces this wall and is spaced apart therefrom, at least partly overlap one another.
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
The present invention relates to a process for producing a component for a flow machine, especially for an aircraft turbine, from a ceramic fibre composite material having an SiC-containing matrix and SiC fibres (2), wherein at least one fibre arrangement composed of SiC fibres, in each case in the form of a prepreg or preform, is first provided in the process and wherein the prepreg and/or matrix former and the preform are inserted into a press mould (1) of a high-temperature press with at least a portion of a surface contour in accordance with the component to be produced and then subjected to a two-stage processing operation in the press mould, wherein the prepreg composed of SiC fibres (2) and a slip (3) has been produced with silicon or Si alloy particles (5) and at least one auxiliary and wherein the matrix formers comprise silicon or Si alloy particles (5) and at least one auxiliary, wherein, in a first processing stage, material present in the press mould (1) is heated up to a temperature at which the auxiliary is subject to at least partial thermal breakdown and/or outgassed, and wherein, in a second processing stage, material present in the press mould (1) is heated to a temperature above the melting temperature of silicon or the Si alloy, such that the silicon or Si alloy particles (5) melt, and wherein, during the second processing stage, the material present in the press mould (1) is compressed to form a component.
C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur composition; Compositions céramiques; Traitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
The invention relates to a method for the electrochemical machining of a component (20) with at least one electrode (30) which has a first working face (31) with an outer contour (32) which is shaped so as to form a gap (33) complementary to a surface (21), to be produced by the electrochemical machining, of the component (20), and which has a second working face (36) which is able to be arranged at an edge (24) of the produced surface (21) of the component (20). In the method, first of all the component (20) is provided, and the first working face (31) of the electrode (30) is positioned in a first machining position with respect to the component (20). Then, the component (20) is machined with the first working face (31) in order to produce the surface (21), before the machining of the component (20) with the first working face (31) is ended at a predetermined position. Subsequently, the component (20) is machined with the second working face (36) of the electrode (30).
The invention describes a system with a rotor blade (40) for a gas turbine (10), more particularly an aircraft gas turbine, with: a blade foot (42), a blade neck (44) adjoining the blade foot (42) in the radial direction (RR); a blade aerofoil (46) adjoining the blade neck (44) in the radial direction (RR); a radially outer partition (48), which forms a radially inner limiting section (50) of an annular space of a gas turbine (10); an axially front partition (52) and an axially rear partition (54), which are connected to the radially outer partition (48) such that the partitions (48, 52, 54) enclose the blade neck (44) from three sides, wherein the partitions (48, 52, 54) project beyond the blade neck (44) in the circumferential direction (UR); and with a blade foot protective plate (60) provided for the arrangement on the blade foot (42). According to the invention, the blade foot protective plate (60) has at least one sealing section (62), which extends in the axial direction (AR) from the front partition (52) to the rear partition (54) and the radial outer side (62a) of which is arranged opposite the radially outer partition (48) when the blade foot protective plate (60) is arranged on the blade foot (42).
The invention relates to a spring element for high-temperature applications, in particular for continuous-flow machines, such as gas turbines or aircraft engines, as well as corresponding continuous-flow machines, wherein the spring element comprises a plurality of ceramic fibres forming at least one fibre element (4, 5), wherein the spring element has one, two or more base elements (2, 3) on which or between which at least parts of the at least one fibre element are arranged.
The invention relates to a device and a method for electrochemically treating a component (12), comprising at least one electrode (20) which has at least one working surface (21) with an outer contour (22) that is shaped so as to complement the component (12) surface (16) to be produced, thereby forming a gap (14), and comprising at least one contour surface (24) which adjoins said working surface and in which at least one cleaning opening (26) is arranged, a cleaning fluid flowing through said cleaning opening. According to the method, at least one component (12) is provided, a voltage is applied between the component (12) and the at least one electrode (20) during the electrochemical treatment, and the electrode (20) is moved relative to the component (12).
The invention relates to an ECM system (10), comprising a holder (12) for the arranging of at least one component (50) to be machined and at least one machining station (22) for the electrochemical machining of the at least one component (50) at at least one machining position. The ECM system (10) has a positioning apparatus (11), which is designed to mount, in a predefined position, a machining platform (20) arranged on the positioning apparatus, and the machining platform (20) comprises at least one machining station (22) having at least one electrode (25) arranged thereon, which electrode can be moved along a machining path in order to machine the at least one component (50) that can be arranged on the holder (12). Furthermore, the ECM system (10) has a clamping apparatus (16) for at least one component (50) to be machined, on which clamping apparatus the at least one component (50) can be arranged in a position defined in advance and which clamping apparatus can be arranged, together with the at least one component (50), on the holder (12) in a position defined in advance.
The present invention relates to a rotor blade for a compressor, which rotor blade has a blade airfoil (10). The blade airfoil has a pressure side (Ps), a suction side (Ss) and a blade tip (11). The blade tip (11) has at least one channel (1), having a front channel wall (2), a rear channel wall (3) and a channel base (4), which extend from a channel inlet opening (5, 7) in the pressure side (Ps) to a channel outlet opening (6, 8) in the suction side (Ss).
F04D 29/28 - Rotors spécialement adaptés aux fluides compressibles pour pompes centrifuges ou hélicocentrifuges
88.
METHOD AND LAYER-BUILDING DEVICE FOR THE ADDITIVE MANUFACTURE OF AT LEAST ONE COMPONENT SEGMENT OF A COMPONENT AS WELL AS COMPUTER-PROGRAM PRODUCT AND STORAGE MEDIUM
The invention relates to a method for the additive manufacture of at least one component segment (12) of at least one component (10), in particular for a flow machine, comprising at least the following steps: a) applying at least one powder layer (20) of a material (22) to at least one building-up and joining zone (60) of at least one movable building platform (70); b) irradiating the powder layer (20) by means of at least one energy beam (80) for at least partially solidifying the powder layer (20) to form the at least one component segment (12), wherein a predetermined target surface roughness (Ra_1) of at least one segment surface (14) of the at least one component segment (12) is created by a relative angle (ζ), assigned to the target surface roughness (Ra_1), being set between the energy beam (80) and a surface normal (17) of the segment surface (14), that is assigned to a point of impingement (16) of the energy beam (80) on the material (22). Further aspects of the invention concern a layer-building device (50) for the additive manufacture of at least one component segment (12) of a component (10), a computer-program product, a computer-readable storage medium (110) as well as a component (10).
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
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
The invention relates to a module (20) for a turbomachine (1), having two components (21, 22), which each extend peripherally and are segmented, wherein the components (21, 22) have an axial overlap (40) and have a radial offset (41) relative to each other such that they contact each other in a contact area (42), and wherein segment joints (23, 24) of the two components (21, 22) coincide at a rotational position (25), wherein an impact edge (21.1.1) of the first segment (21.1) of the first component (21) together with impact edges (22.1.1, 22.2.1) of the first and second segment (22. 1, 22.2) of the second component (22) forms an angle (35).
F01D 5/22 - Connections aube à aube, p.ex. par emboîtement
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
F01D 25/26 - Carcasses d'enveloppe doubles; Mesures contre les tensions thermiques dans les carcasses d'enveloppe
90.
INTERMEDIATE ELEMENT FOR A BLADE/ROTOR DISC CONNECTION IN A ROTOR OF A TURBOMACHINE, ASSOCIATED ROTOR FOR A TURBOMACHINE, AND TURBOMACHINE
The invention relates to an intermediate element (10) for a blade/rotor disc connection in a rotor of a turbomachine, in particular in a rotor of a power plant, the intermediate element (10) being adapted to the shape of a blade root (30) of the blade (35) and to a blade root receptacle of a rotor disc (40) for receiving the blade root (30) in such a way that the intermediate element (10) arranged between the blade root (30) and the rotor disc (40) prevents direct contact between the blade root (30) and the rotor disc (40). The intermediate element (10) arranged between the blade root (30) and the rotor disc (40) has, on its outer surface (11) facing the rotor disc (40), at least one projection (20-22) for reducing an air flow parallel to the axis of rotation of the rotor between the rotor disc (40) and the intermediate element (10), and the intermediate element (10) arranged between the blade root (30) and the rotor disc (40) has, on its inner surface (12) facing the blade root (30), a recess corresponding to the at least one projection (20-22) on the outer surface (11) of the intermediate element (10).
The invention relates to a rotor blade (20) for arranging in a gas channel (3) of a turbomachine (1), comprising a rotor blade sheet (23) which has a leading edge (23a) and a trailing edge (23b) downstream therefrom with respect to a flow in the gas channel (3) and which has a suction side (41) and a pressure side (42). The rotor blade sheet (23) is provided with an inclination towards the suction side (41) over at least one section (45.1) of the radial rotor blade sheet height (45), wherein the inclination is set such that during operation, a centrifugal force bending moment (46) exerted onto the rotor blade sheet (23) by the centrifugal force as a result of the inclination is greater than a gas pressure bending moment (47) acting on the rotor blade sheet (23) as a result of the circulation of the rotor blade sheet (23) in the gas channel (3).
The present invention relates to an integrally bladed rotor for a turbomachine, in particular a compressor or turbine stage of a gas turbine, to which at least one separately formed impulse body housing (40; 40') is fastened by means of at least one fastening element (30; 30'), which engages for this purpose into an opening (41) in the impulse body housing and into an opening (11) in the rotor, wherein the impulse body housing has at least one cavity (44), in which at least one impulse body (5) having movement play is received.
The invention relates to a method for machining an in particular planar component (3) by means of electrochemical machining, wherein the component (3) has internal stresses resulting in particular from preceding manufacturing steps. In a first step a) of the method, the component (3) to be machined is provided. Subsequently, in step b), at least two tools are provided in the form of electrodes (8) and, in step c), an electrolyte is provided between the component (3) and the at least two electrodes (8). In step d), a positive voltage is applied to the component (3) and a negative voltage is applied to the at least two electrodes (8). Thus, in step e), by moving the at least two electrodes (8) along their respective movement paths with respect to the component (3), electrochemical machining can take place; in the process, the gap between each electrode (8) and the component (3) is flushed with the electrolyte at least intermittently.
B23H 3/04 - Electrodes spécialement adaptées à cet effet ou leur fabrication
B23H 3/10 - Alimentation en milieu d'usinage ou régénération de celui-ci
B23H 7/26 - Appareils pour déplacement ou positionnement de l'électrode par rapport à la pièce; Montage de l'électrode
B23H 9/10 - Usinage d'aubes de turbine ou de buses
95.
LAYER CONSTRUCTION METHOD AND LAYER CONSTRUCTION DEVICE FOR ADDITIVELY MANUFACTURING AT LEAST ONE COMPONENT REGION OF A COMPONENT, AND COMPUTER PROGRAM PRODUCT AND STORAGE MEDIUM
ssminssminsmin represents a minimum melt pool width of the scan lines (40). The invention also relates to a layer construction device (10) for the additive manufacturing of at least one component region (12) of a component (14), to a computer program product, to a computer-readable storage medium, and to a component (14) having at least one additively manufactured component region (12).
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
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
B23K 15/00 - Soudage ou découpage par faisceau d'électrons
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 64/268 - Agencements pour irradiation par faisceaux d’électrons [FE]
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
The invention relates to a guide vane segment (40) for a gas turbine (10), in particular an aircraft gas turbine, comprising: at least one guide vane (46); a radially inner cover strip (44); and a radially outer cover strip (42), the at least one guide vane (46) extending between the inner cover strip (44) and the outer cover strip (42), and the inner cover strip (44) and/or the outer cover strip (42) having a support portion (48) running in the circumferential direction (UR), each support portion having an axial end face (52). Each support portion (48) on the inner cover strip (44) and/or on the outer cover strip (42) has at least one support portion rib (62) running in the radial direction (RR), which support portion rib is connected to the support portion (48), in particular is formed integrally therewith, and has a rib end face (64), which transitions into the end face (52) of the support portion (48).
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
97.
LAYER BUILDING PROCESS AND LAYER BUILDING DEVICE FOR THE ADDITIVE MANUFACTURE OF AT LEAST ONE WALL REGION OF A COMPONENT, COMPUTER PROGRAM PRODUCT, AND COMPONENT
The invention relates to a layer building process for the additive manufacture of at least one component region of a component (10). The layer building process has at least the steps of a) applying at least one powder layer of a raw material onto at least one construction and joining zone of at least one movable construction platform, b) carrying out at least one first solidification step in which the raw material is solidified by means of a selective irradiation process using at least one energy beam according to a first exposure parameter set, whereby a first layer region (14a) with a first microstructure is formed within an individual layer (12), c) carrying out at least one second solidification step in which the raw material is solidified by means of a selective irradiation process using the at least one energy beam according to a second exposure parameter set, whereby a second layer region (14b) with a second microstructure is formed within the individual layer (12), d) lowering the construction platform (24) by a pre-defined layer thickness in layers, and e) repeating steps a) to d) once or multiple times. The invention additionally relates to a layer building device, a computer program product, and a component (10) with at least one layer (12) which has a first layer region (14a) with a first microstructure and a second layer region (14b) with a second microstructure.
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
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 64/273 - Agencements pour irradiation par faisceaux d’électrons [FE] à modulation de fréquence
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de 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
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
98.
METHOD FOR DETECTING DEFECTS IN A COMPONENT, METHOD FOR TRAINING A MACHINE LEARNING SYSTEM, COMPUTER PROGRAM PRODUCT, COMPUTER-READABLE MEDIUM, AND SYSTEM FOR DETECTING DEFECTS IN A COMPONENT
The invention relates to a method for detecting defects, in particular cracks and/or pores, in a component (20), in particular in a component (20) of a turbomachine, preferably in a component (20) of a drive unit, the method comprising the following steps: applying penetration means onto at least one sub-region of the component (20), such that the penetration means penetrates into any defects, in particular cracks and/or pores, present in the component (20); cleaning the surface of the component (20) of penetration means that has not penetrated into defects, in particular cracks and/or pores, of the component (20); capturing an image, in particular an entire image, of the component (20); inputting the captured image into a machine learning system (40) trained to detect defects, in particular cracks and/or pores; and detecting defects, in particular cracks and/or pores, in the component (20) by means of the machine learning system (40) on the basis of light emitted and/or reflected by the penetration means in the defects, in particular cracks and/or pores.
The present invention relates to a method for producing a rotary disc or a blisk for a high-pressure compressor or a high-speed turbine, in particular a low-pressure turbine of an aircraft engine, in particular a geared turbofan engine, and to a corresponding geared turbofan engine, wherein the method involves providing an Ni base alloy which comprises 15.5% by weight to 16.5% by weight Cr, 14.0% by weight to 15.5% by weight Co, 4.75% by weight to 5.25% by weight Ti, 2.75% by weight to 3.25% by weight Mo, 2.25% by weight to 2.75% by weight Al, 1.00% by weight to 1.50% by weight W, optionally 0.0250% by weight to 0.0500% by weight Zr, optionally 0.0100% by weight to 0.0200% by weight B, optionally 0.0100% by weight to 0.0200% by weight C and the remainder Ni, where the Ni base alloy is shaped by forging, so that the structure and a preform of the disc or blisk is obtained, the final contour of the disc or blisk being produced by electrical discharge machining or electrochemical machining.
C22C 19/05 - Alliages à base de nickel ou de cobalt, seuls ou ensemble à base de nickel avec du chrome
B23H 1/00 - Usinage par décharge électrique, c. à d. enlèvement de métal au moyen de séries de décharges électriques à cadence élevée entre une électrode et une pièce en présence d'un fluide diélectrique
B23H 3/00 - Usinage électrochimique, c. à d. enlèvement de métal par passage de courant entre une électrode et une pièce en présence d'un électrolyte
C22F 1/10 - Modification de la structure physique des métaux ou alliages non ferreux par traitement thermique ou par travail à chaud ou à froid du nickel ou du cobalt ou de leurs alliages
F01D 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
The present invention relates to a cooling system for cooling at least one first turbine stage (1) and at least one downstream second turbine stage (2) of a gas turbine, in particular an aircraft engine gas turbine, wherein the cooling system has: - a first valve device, which is connected to the first turbine stage (1) by a cooling medium inlet (30) and a first cooling medium outlet (31), - a second valve device, which is connected to the second turbine stage (2) by a cooling medium inlet (30) and a second cooling medium outlet (32), and - an actuator (40) for adjusting the first and second valve device, wherein the actuator (40) has - a first adjusting range (a) for adjusting a standard cross section (A1) of the first valve device over a first adjusting range when the second valve device is open and - a second adjusting range (b), connecting to or spaced apart from the first adjusting range (a), for adjusting the standard cross section (A1) of the first valve device over a second adjusting range, wherein - a standard cross section (A2) of the second valve device in the second adjusting range has at most 25% of a maximum value, in particular the second valve device is closed in the second adjusting range, and a minimum value of the first adjusting range and a minimum value of the second adjusting range deviate from each other by 50% at most and/or a maximum value (A1max) of the first adjusting range and a maximum value of the second adjusting range deviate from each other by 50% at most and/or at least one value of the first adjusting range and one value of the second adjusting range deviate from each other by 10% at most; and/or - the second valve device has a first passage (23) and a cover (21) having a second passage (24), which are adjustable, in particular rotatable or slidable, relative to each other by the actuator (40), and define a standard cross section (A2) of the second valve device.
brevets
