A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
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
In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.
A rotary machine, such as a turbomachine of a gas turbine engine, for example, including a rotor and a rotor seal assembly. The rotor is rotatable about a rotational axis and has a rotor seal face. The rotor seal assembly includes a seal body, one or more primary fluid conduits formed in the seal body, and a retraction assembly. The seal body has a seal face and is positionable to form a fluid-bearing gap between the seal face of the seal body and the rotor seal face. The one or more primary fluid conduits are fluidly connected to the fluid-bearing gap to supply a fluid to the fluid-bearing gap. The retraction assembly is connected to the seal body to move the seal body in a retraction direction away from the rotor seal face.
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
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
4.
EROSION-SHIELDED TURBINE BLADES AND METHODS OF MANUFACTURING THE SAME
A method of forming an erosion shield for a turbine blade includes depositing a layer of filler material defining an upper surface. The method also includes depositing a layer of erosion-resistant material across the upper surface of the layer of filler material. An interface is defined between the layer of filler material and the layer of erosion-resistant material and has a shape of the upper surface. The method also includes machining the layer of filler material to produce the erosion shield. The erosion shield has the layer of erosion-resistant material, the machined layer of filler material, and the interface defined therebetween. An inner surface of the erosion shield is defined by the machined layer of filler material that is sized and shaped for attaching to a leading edge of the turbine blade. Each of the interface and the inner surface extend a length of the erosion shield.
A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
A gas turbine engine including a rotating shaft and a bearing assembly. The bearing assembly is configured to support the rotating shaft. The bearing assembly has a first bearing and a second bearing. The first bearing is configured to support an axial load of the rotating shaft when a forward thrust of the rotating shaft is greater than ten percent. The second bearing is configured to support the axial load of the rotating shaft when a thrust of the rotating shaft is between ten percent forward thrust and ten percent aft thrust, inclusive of the end points.
A seal monitoring apparatus is provided. The seal monitoring apparatus includes a temperature sensor and a controller in communication with the temperature sensor. The temperature sensor is mounted at a seal of a device. The controller is configured to receive measured temperature data from the temperature sensor and calculate expected temperature data for the seal based at least in part on operating conditions of the device. The controller is configured to determine a condition of the seal based at least in part on a temperature difference of the measured temperature data from the expected temperature data.
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p.ex. entre étages
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
8.
HYBRID-ELECTRIC PROPULSION SYSTEM EQUIPPED WITH A COUPLER FOR SWITCHING BETWEEN MODES OF OPERATION
A propulsion assembly includes a first torque source coupled with a first shaft and a second torque source coupled with a second shaft. A coupler selectively couples the first and second torque sources. When the first and second torque sources are coupled via the coupler, in response to a command to decouple the first torque source, an unloading operation is performed to decrease the torque output provided by the first torque source to a threshold, and when reached, the first shaft is decoupled from the coupler. When the first torque source is coupled with the coupler but the second torque source is not, in response to a command to couple the second torque source, a speed matching operation is performed to increase the speed of the second shaft to match a speed of the first shaft, and when the speeds are matched, the second shaft is coupled to the coupler.
A combustor including an annular liner, a dome wall, a combustion chamber, at least one fuel cup and at least one dilution passage. The fuel cup being provided on the dome wall and being fluidly coupled to the combustion chamber. The fuel cup defining a fuel cup centerline. The at least on dilution passage terminating in at least on slot opening onto the dome wall, with the at least one slot having a longitudinal body axis.
General Electric Deutschland Holding GmbH (Allemagne)
Inventeur(s)
Guijarro Valencia, Antonio
Schimmels, Scott Alan
Johnson, Steven Douglas
Abrégé
A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.
A method of manufacturing an erosion-shielded turbine blade includes providing a turbine blade for use with a rotary machine. The turbine blade includes an airfoil extending between a root and a tip. The airfoil includes a pressure side and an opposite suction side, and each of the pressure and suction sides extends between a leading edge and a trailing edge. The method also includes printing a green body part by an additive manufacturing process by selectively depositing a binder solution across a particulate erosion-resistant material, and sintering the green body part to produce a post-sintering erosion shield that includes densified erosion-resistant material. The method also includes coupling the erosion shield to the leading edge of the turbine blade.
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
B23P 6/00 - Remise en état ou réparation des objets
A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.
A rotor damping device for a turbomachine is provided. The rotor damping device includes a first fluid damper; and a second damper in communication with the first fluid damper, the second damper comprising a wire mesh, wherein the first fluid damper is transitionable between a working condition and an interruption condition, and wherein, during the interruption condition, the wire mesh of the second damper dampens vibration of the turbomachine.
Methods of forming a coating system on a surface of a cobalt-based superalloy component are provided. The method includes forming a nickel-based primer layer on the surface of the cobalt-based superalloy component; forming an intermediate nickel-containing layer on the nickel-based primer layer; and heat treating the cobalt-based superalloy component to form a diffusion coating on the surface of the cobalt-based superalloy component. The intermediate nickel-containing layer includes nickel, chromium, and aluminum. Coated cobalt-based superalloy components formed from such a method are also provided.
A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
A gas turbine engine, comprising a turbomachine and a housing at least partially encasing a portion of the turbomachine, the housing having an inner surface and defining in part a void between the inner surface and the portion of the turbomachine, the housing moveable relative to the portion of the turbomachine; and an engine component selectively coupled to the portion of the turbomachine or to the housing.
A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid communication with the pipe intake port. A temperature sensor is positioned in the manifold upstream of a cooling system. The cooling system reduces a temperature of a gas flow in the manifold, allowing use of an aspirating smoke detector. An aspirating smoke detector, which is downstream of the cooling system, draws in the gas flow and detects smoke in the gas flow. A controller generates a first alarm in response to the temperature sensor detecting a temperature of the gas flow exceeding a temperature threshold, or a second alarm in response to the aspirating smoke detector detecting smoke in the gas flow.
F02C 7/12 - Refroidissement des ensembles fonctionnels
F23N 5/02 - Systèmes de commande de la combustion utilisant des dispositifs sensibles aux variations thermiques ou à la dilatation thermique d'un agent
F23N 5/24 - Systèmes prévenant le développement de conditions anormales ou indésirables, c. à d. dispositifs de sécurité
18.
HEAT EXCHANGER ASSEMBLY FORMED OF A LATTICE STRUCTURE WITH A PLURALITY OF SHELL STRUCTURE UNIT CELLS
An additively manufactured heat exchanger assembly formed of a lattice structure with a plurality of shell structure unit cells. The plurality of shell structure unit cells each include at least one junction and a plurality of connectors coupled to the junction. The junction and the plurality of connectors form an integral surface. The heat exchanger assembly further includes a fluid boundary wall defined within the lattice structure to define an active heat exchanger portion. The active heat exchanger portion includes at least one working fluid contained within the fluid boundary wall. Further, at least one of the plurality of shell structure unit cells extends through and beyond the fluid boundary wall. Further, the shell structure unit cells may be isotropic.
F28F 7/02 - Blocs traversés par des passages pour sources de potentiel calorifique
B33Y 80/00 - Produits obtenus par fabrication additive
F28D 7/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
A combustor for a turbomachine engine. The combustor includes a combustion chamber, and a cowl having an annular shape that is symmetric around a centerline axis of the turbomachine engine. The cowl includes a hollow cavity that is in fluid communication with the combustion chamber. The hollow cavity is a damper that reduces combustion dynamics of the combustor.
F23R 3/42 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la disposition ou la forme des tubes à flamme ou des chambres de combustion
A sensor system is described with improved measurement accuracy that is achieved by reducing noise, baseline drift, or both based on processing a group of sensor element response signals. The response signals may be received in response to providing stimuli to the sensor element using different excitation frequencies over time. For example, the sensor circuitry may provide excitation signals to the sensing element with multiple excitation frequencies over time. The sensor system may include storage and processing circuitry to receive the response signals and to generate the correction values based on analyzing the received response signals. The sensor system may then provide adjusted response signals by reducing the noise, baseline drift, or both based on the correction values.
G01N 27/22 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant l'impédance en recherchant la capacité
A seal monitoring apparatus is provided. The seal monitoring apparatus includes one or more pressure sensors and a controller in communication with the one or more pressure sensors. The one or more pressure sensors is mounted at a seal of a turbine to measure pressure on a first side of the seal and/or a second side of the seal. The controller is configured to receive pressure data from the one or more pressure sensors and determine a condition of the seal based at least in part on the pressure data. The controller is configured to output a signal upon determining a change in the condition of the seal.
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
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
F02C 7/28 - Agencement des dispositifs d'étanchéité
22.
COMBINED CYCLE POWER PLANT HAVING REDUCED PARASITIC PUMPING LOSSES
A combined cycle power plant (CCPP) is provided. The CCPP includes a gas turbine that has a compressor section, a combustion section, and a turbine section. The CCPP further includes a heat recovery steam generator (HRSG) that has a first economizer. The HRSG receives a flow of exhaust gas from the turbine section. The HRSG further includes a fuel heating system that has a fuel supply line and a high temperature heat exchanger disposed in thermal communication on the fuel supply line. The fuel supply line is fluidly coupled to the combustion section. The high temperature heat exchanger is fluidly coupled to the first economizer such that the high temperature heat exchanger receives water from the first economizer. The CCPP further includes a feedwater pump that is fluidly coupled to the high temperature heat exchanger.
F01K 23/10 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de combustion provenant de l'un des cycles chauffant le fluide dans un autre cycle le fluide à la sortie de l'un des cycles chauffant le fluide dans un autre cycle
F01K 7/16 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motrices; Ensembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliers; Dispositifs de commande spécialement adaptés à ces systèmes, cycles ou phases; Utilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation les machines motrices étant uniquement du type turbine
23.
COMBINED CYCLE POWER PLANT HAVING REDUCED PARASITIC PUMPING LOSSES
A combined cycle power plant (CCPP) includes a heat recovery steam generator (HRSG) that includes a first economizer and a condensate supply line. The HRSG receives a flow of exhaust gas from the turbine section. The CCPP further includes a fuel heating system that has a fuel supply line and a high temperature heat exchanger. The fuel supply line is fluidly coupled to the combustion section. The high temperature heat exchanger is disposed in thermal communication on the fuel supply line. A high temperature input line fluidly couples the high temperature heat exchanger to the first economizer of the HRSG such that the high temperature heat exchanger receives water from the first economizer. A recirculation line fluidly coupling the high temperature heat exchanger to the condensate supply. A hydro turbine is disposed on the recirculation line.
F02C 6/18 - Utilisation de la chaleur perdue dans les ensembles fonctionnels de turbines à gaz à l'extérieur des ensembles eux-mêmes, p.ex. ensembles fonctionnels de chauffage à turbine à gaz
24.
MULTIFURCATING HEAT EXCHANGER WITH INDEPENDENT BAFFLES
A heat exchanger includes a core defining a first passageway for a first fluid flow and a second passageway for a second fluid flow. The core includes an assembly of a plurality of unit cells coupled together. Each unit cell defines a first passageway portion within an interior volume and a second passageway portion at an exterior surface. Each unit cell includes a plurality of first openings into the interior volume and forms the second passageway in volumes between the plurality of unit cells. The assembly is shaped to combine and divide the first fluid in the first passageway portion and combine and divide the second fluid in the second passageway portion during exchange of heat between the first fluid and the second fluid. Each second passageway portion receives the second fluid from three other second passageway portions. The heat exchanger further includes at least one baffle in at least one of the first passageway or the second passageway to route the first fluid flow independently from the second fluid flow.
F28D 7/16 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant espacées parallèlement
F28F 9/22 - Dispositions pour diriger les sources de potentiel calorifique dans des compartiments successifs, p.ex. aménagement des plaques de guidage
Techniques for using a pyrometer to measure one or more operating characteristics of a target are provided. In one example aspect, a pyrometer is oriented relative to a target having target elements spaced from one another such that, as the target is rotated, the pyrometer alternately i) senses a target element for a period of time; and ii) then does not sense any of the target elements for a period of time as no appreciable signal is received. The pyrometer generates an output signal having alternating target pulse widths and null widths. The target and null widths have different amplitudes. The amplitude of the null signal provides an amplitude baseline for which the amplitudes of the target widths or signals may be compared to so that a temperature or other operating characteristic associated with the target can be determined.
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
G01J 5/00 - Pyrométrie des radiations, p.ex. thermométrie infrarouge ou optique
A bearing assembly includes a bearing, an outer race located radially outward of the bearing and supporting the bearing, a bearing housing located radially outward of the outer race and supporting the bearing and the outer race, and a bearing lubricant drain including a multi-directional passage formed in one or both of the outer race or the bearing housing, the lubricant drain arranged to cause a lubricant to flow from a first location to a second location. The second location is radially outward and axially offset from the first location. A gas turbine engine includes a shaft configured to rotate about a centerline axis of the gas turbine engine and the bearing assembly configured to facilitate the rotation of the shaft.
F16C 33/66 - Pièces ou détails particuliers pour la lubrification
F16C 19/06 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec roulements à billes essentiellement du même calibre, en une ou plusieurs rangées circulaires pour charges radiales principalement avec une seule rangée de billes
27.
SYSTEM AND METHOD FOR DETERMINING PROBABILISTIC BURST
Systems and methods are provided herein that are useful to determining probabilistic burst for a component. In particular, the systems and methods generate an overspeed distribution for the component, the overspeed distribution being indicative of a probability that various overspeed values will be obtained. The method involves receiving field analytics data indicative of time the component spends in at least one operating condition and receiving overspeed data indicative of overspeed values for the component as a function of the at least one operating condition. The method further includes generating an overspeed distribution for the component based on the field analytics data and the overspeed data. A probability of burst for the component may then be determined based on the overspeed distribution.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
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
A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnel; Disposition permettant la dilatation calorifique ou le déplacement
29.
PUMP SYSTEMS HAVING DUAL-FUNCTION HEAT EXCHANGERS AND RELATED METHODS
Example pump systems having dual-function annular heat exchangers are disclosed. An example pump system to pressurize a fluid within a closed loop transport bus includes a pump to move the fluid, a conduit in fluid connection with the pump, a heat exchanger positioned around at least a portion of the conduit, the heat exchanger to receive a first electrical signal transmitted in a first direction at a first time and a second electrical signal transmitted in a second direction at a second time different from the first time, the second direction opposite the first direction.
F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
30.
IMAGING SYSTEM ISOLATION ENCLOSURE FOR PATHOGEN CONTAINMENT DURING MEDICAL IMAGING PROCEDURES
Systems are provided for an imaging system isolation enclosure for use with a medical imaging system includes a pathogen impermeable enclosure for use with one or more of radiation imaging systems and magnetic resonance imaging systems, the pathogen impermeable enclosure is configured to provide a barrier between the imaging system and at least one of a patient user and an imaging room, and an air filtration system including an inlet to supply a cooling air flow to an interior of the imaging system isolation enclosure and an outlet to output exhaust air from an interior of the imaging system isolation enclosure.
A61B 6/00 - Appareils pour diagnostic par radiations, p.ex. combinés avec un équipement de thérapie par radiations
A61G 10/02 - Locaux de traitement à usage médical avec des moyens pour maintenir une pression déterminée, p.ex. locaux exempts de germes
G01R 33/28 - Dispositions ou appareils pour la mesure des grandeurs magnétiques faisant intervenir la résonance magnétique - Détails des appareils prévus dans les groupes
This disclosure provides systems, methods and apparatuses for communication protocol enhancements in a wireless power system. Various implementations relate generally to messages for a communication protocol in a wireless power system. The communication protocol and related aspects address unexpected conditions of a Power Transmitter or a Power Receiver in a wireless power system.
H02J 50/80 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique mettant en œuvre l’échange de données, concernant l’alimentation ou la distribution d’énergie électrique, entre les dispositifs de transmission et les dispositifs de réception
H02J 50/90 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique mettant en œuvre la détection ou l'optimisation de la position, p.ex. de l'alignement
General Electric Company Polska Sp. z o.o. (Pologne)
Inventeur(s)
Kuropatwa, Michal Tomasz
Deskiewicz, Adam Wojciech
Kaminski, Robert
Kunicki, Adam
Kray, Nicholas Joseph
Abrégé
A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
A hydrocarbon fluid containment article having a wall with a surface that is wetted by hydrocarbon fluid. The surface includes an anti-coking coating. The anti-coking coating includes a copper salt, a silver salt, or a combination thereof. A gas turbine engine component including a wall having a first surface and an anti-coking coating on the first surface of the wall that is wetted by hydrocarbon fluid. The anti-coking coating including a copper salt, a silver salt, or a combination thereof that prevents the formation of gum or coke on a surface thereon. Methods for reducing the deposition of thermal decomposition products on a wall of an article are also provided.
C23C 2/04 - Procédés de trempage à chaud ou d'immersion pour appliquer le matériau de revêtement à l'état fondu sans modifier la forme de l'objet immergé; Appareils à cet effet caractérisé par le matériau de revêtement
B05D 1/12 - Application de matériaux en particules
B05D 1/18 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces par immersion
B05D 5/00 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces pour obtenir des effets, finis ou des structures de surface particuliers
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 15/18 - Produits stratifiés composés essentiellement de métal comportant du fer ou de l'acier
C09D 1/00 - Compositions de revêtement, p.ex. peintures, vernis ou vernis-laques, à base de substances inorganiques
C23C 4/04 - Revêtement par pulvérisation du matériau de revêtement à l'état fondu, p.ex. par pulvérisation à l'aide d'une flamme, d'un plasma ou d'une décharge électrique caractérisé par le matériau de revêtement
C23C 20/00 - Revêtement chimique par décomposition soit de composés solides, soit de suspensions des composés constituant le revêtement, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement
C23C 20/06 - Revêtement avec des matériaux inorganiques autres que des matériaux métalliques
C23C 20/08 - Revêtement avec des matériaux inorganiques autres que des matériaux métalliques avec des composés, des mélanges ou des solutions solides, p.ex. borures, carbures, nitrures
C23C 24/00 - Revêtement à partir de poudres inorganiques
C23C 26/00 - Revêtements non prévus par les groupes
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
F02C 7/30 - Prévention de la corrosion dans les espaces balayés par les gaz
The present approaches are generally directed to facilitating healing of wounds, including chronic wounds typically associated with slow heal times or which are persistent. In one embodiment, a method of promoting wound healing comprises positioning an ultrasound transducer at a stimulation site on a subject having a wound. Pulsed focused ultrasound (pFUS) is non-invasively applies using the transducer to cause modulation of a target anatomic site containing resident or circulating immune cells. Modulation of the target anatomic site of the subject causes migration of one or more of monocytes, macrophages, or neutrophils to a wound bed of the wound.
A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 7/06 - Aménagement des paliers; Lubrification
36.
CIRCUMFERENTIALLY VARYING FAN CASING TREATMENTS FOR REDUCING FAN NOISE EFFECTS
A rotary component for a gas turbine engine includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the gas turbine engine. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Each of the plurality of features includes one or more design parameters that are perturbed about a mean design parameter for stall performance so as to provide a circumferential variation in wake strengths associated with the plurality of rotor blades, thereby reducing operational noise of the gas turbine engine.
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
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
A gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath. The gas turbine engine also includes a turbine rear frame extending through the core air flowpath at a location downstream of the turbine section and defining a leading edge within the core air flowpath. The gas turbine engine also includes a waste heat recovery system operable to separate, at or upstream of the leading edge of the turbine rear frame, a core airflow exiting the turbine section into a primary exhaust airflow and a waste heat recovery airflow. The waste heat recovery system comprises a heat source exchanger positioned to receive the waste heat recovery airflow.
F02C 7/10 - Chauffage de l'air d'alimentation avant la combustion, p.ex. par les gaz d'échappement au moyen d'échangeurs de récupération de chaleur
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
The present approaches are generally directed to facilitating healing of wounds, including chronic wounds typically associated with slow heal times or which are persistent. In one embodiment, a method of promoting wound healing comprises positioning an ultrasound transducer at a stimulation site on a subject having a wound. Pulsed focused ultrasound (pFUS) is non-invasively applies using the transducer to cause modulation of a target anatomic site containing resident or circulating immune cells. Modulation of the target anatomic site of the subject causes migration of one or more of monocytes, macrophages, or neutrophils to a wound bed of the wound.
Phosphor materials and devices containing such phosphor materials are disclosed. An ink composition of in accordance with the present disclosure comprises a phosphor material comprising a Mn4+ doped phosphor of formula 1, Ax[MFy]:Mn4+ (I), and at least one rare earth containing Garnet phosphor, the at least one rare earth Garnet phosphor is present in the phosphor material in an amount of at least about 80 wt % based on the weight of the phosphor material, wherein the at least one rare earth containing a Garnet phosphor has a D50 particle size from about 0.5 microns to about 15 microns, where A is Li, Na, K, Rb, Cs, or a combination thereof; M is Si, Ge, Sn, Ti, Zr, Al, Ga, In, Sc, Y, La, Nb, Ta, Bi, Gd, or a combination thereof; x is the absolute value of the charge of the [MFy] ion; and y is 5, 6 or 7.
C09D 11/50 - Encres sympathiques, encres changeant de couleur ou encres similaires
C09D 11/037 - Encres d’imprimerie caractérisées par des particularités autres que la nature chimique du liant caractérisées par le pigment
C09D 11/107 - Encres d’imprimerie à base de résines artificielles contenant des composés macromoléculaires obtenus par des réactions faisant intervenir uniquement des liaisons non saturées carbone-carbone à partir d'acides non saturés ou de leurs dérivés
C09K 11/02 - Emploi de substances particulières comme liants, revêtements de particules ou milieux de suspension
C09K 11/61 - Substances luminescentes, p.ex. électroluminescentes, chimiluminescentes contenant des substances inorganiques luminescentes contenant du fluor, du chlore, du brome, de l'iode ou des halogènes non spécifiés
C09K 11/77 - Substances luminescentes, p.ex. électroluminescentes, chimiluminescentes contenant des substances inorganiques luminescentes contenant des métaux des terres rares
F21S 43/16 - Sources lumineuses où la lumière est générée par un matériau photoluminescent espacé par rapport à un élément générateur de lumière primaire
F21V 9/38 - Combinaison de plusieurs éléments photoluminescents de matériaux différents
40.
METHOD AND SYSTEM FOR INSPECTING COOLING HOLES OF A TURBINE ENGINE COMPONENT
A method of imaging a turbine engine test component with a first surface and a second surface that is spaced from the first surface. The turbine engine test component includes a plurality of film holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes flowing airflow through the plurality of film holes of the turbine engine test component, obtaining thermographic data, determining a test dataset, and calculating a performance score.
G01J 5/00 - Pyrométrie des radiations, p.ex. thermométrie infrarouge ou optique
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
G01J 5/02 - Pyrométrie des radiations, p.ex. thermométrie infrarouge ou optique - Détails structurels
41.
TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE
An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
Methods, apparatus, systems, and articles of manufacture to produce cryo-compressed hydrogen are disclosed. An example cryo-compressed hydrogen production system includes a compressor to compress an input of hydrogen, at least one heat exchanger to cool the hydrogen, and a conduit to convey the hydrogen at least partially to a storage tank for storage at a temperature less than or equal to a first threshold and greater than a second threshold, the first threshold defined by an upper temperature limit for cryo-compressed hydrogen, the second threshold defined by a hydrogen liquefaction temperature.
F25J 1/00 - Procédés ou appareils de liquéfaction ou de solidification des gaz ou des mélanges gazeux
F25J 1/02 - Procédés ou appareils de liquéfaction ou de solidification des gaz ou des mélanges gazeux nécessitant l'emploi d'une réfrigération, p.ex. de l'hélium, de l'hydrogène
43.
GRADIENT WITHIN A THERMAL BARRIER COATING AND METHODS OF THEIR FORMATION
Methods are provided for forming a thermal barrier coating having a non-linear compositional gradient and/or a non-linear porosity gradient, along with coated components formed therefrom. The method includes spraying a deposition mixture of a first composition and a second composition via a solution precursor plasma spray apparatus onto a surface of a substrate; while spraying the deposition mixture, adjusting at least one deposition parameter such that the thermal barrier coating is formed with the non-linear gradient.
A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
A turbomachine engine includes a fan section having a fan shaft, and a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine includes a low-speed shaft coupled to the power turbine and having a midshaft that extends from a forward bearing to an aft bearing. The low-speed shaft is characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-speed shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine includes a gearbox assembly that couples the fan shaft to the low-speed shaft and characterized by a gearbox assembly mode less than 95% of a midshaft mode of the midshaft or greater than 105% of the midshaft mode.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 7/06 - Aménagement des paliers; Lubrification
A gas turbine engine including: a fan assembly comprising a fan; and a turbomachine drivingly coupled to the fan and including a compressor section, a combustion section, and a turbine section arranged in serial flow order and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine; the turbomachine further including a heat exchanger and defining an annular cooling passage extending between an inlet and an outlet, the inlet in airflow communication with the working gas flowpath at a location upstream of the compressor section and the outlet in airflow communication with the bypass passage, the heat exchanger in thermal communication with an airflow through the cooling passage.
A gas turbine engine is provided. The gas turbine engine includes: a fan; a turbomachine drivingly coupled to the fan and defining in part a working gas flowpath, the gas turbine engine defining a bypass passage over the turbomachine, the turbomachine defining an annular cooling passage extending between a CP inlet and a CP outlet, the CP inlet in airflow communication with the working gas flowpath and the CP outlet in airflow communication with the bypass passage; and a variable bleed assembly including a variable bleed duct extending between a VB inlet and a VB outlet, the VB inlet in airflow communication with the working gas flowpath at a location downstream of the CP inlet and the VB outlet in airflow communication with the annular cooling passage for urging an airflow through the cooling passage.
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
49.
METHODS AND SYSTEMS FOR STARTING SECURE COMMUNICATION IN SYSTEMS WITH HIGH AVAILABILITY
A distributed control system includes an electronic control unit to establish secure communication with a distributed control module. Upon determination that a previously negotiated session key is stored on the electronic control unit, the electronic control unit transmits encrypted communications with the distributed control module using the previously negotiated session key, negotiates a new session key with the distributed control module, and stores the new session key. Upon determination that the previously negotiated session key is not stored on the electronic control unit, the electronic control unit negotiates the new session key with the distributed control module. After negotiating the new session key with the distributed control module, the electronic control unit ceases transmission of unencrypted communications with the distributed control module, transmits encrypted communications with the distributed control module using the new session key, and stores the new session key.
An apparatus and method for a degassing apparatus with a degassing chamber and a container. The container is located within the degassing chamber and defines a holding chamber with an opening. An insert for being received in the opening. The insert including at least one conduit extending between an inlet and an outlet.
A system includes a hydrogen sensor configured to generate data indicative of a level of hydrogen present within the compartment and a computing system. The computing system configured to determine at least one of the level of hydrogen present within the compartment or a rate of change of the level of hydrogen present within the compartment and compare the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment to an associated threshold value. Furthermore, when the determined at least one of the level of hydrogen present within the compartment or the rate of change of the level of hydrogen present within the compartment exceeds the associated threshold value, the computing system is configured to initiate a control action associated with reducing the level of hydrogen present within the compartment.
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
B60H 1/00 - Dispositifs de chauffage, de refroidissement ou de ventilation
F02C 7/232 - Soupapes pour combustible; Systèmes ou soupapes de drainage
F02C 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
A heat exchanger includes an inlet plenum chamber, an outlet plenum chamber fluidly coupled to the inlet plenum chamber, and a plurality of intermediate plenum chambers disposed downstream from the inlet plenum chamber and upstream from the outlet plenum chamber. The plurality of intermediate plenum chambers includes a first intermediate plenum chamber, at least one tube bundle, and a first bypass valve fluidly coupled to the first intermediate plenum chamber. The first bypass valve is configured to control fluid flow rate from the first intermediate plenum chamber to the outlet plenum chamber.
F02C 7/12 - Refroidissement des ensembles fonctionnels
F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
53.
SYSTEM AND METHOD FOR OPERATING A POWER DISTRIBUTION SYSTEM
A method and aircraft power distribution system includes a power distribution bus supplying power along an electrical line, a primary communication module including a primary transceiver and a primary controller, and a plurality of secondary communication modules including a secondary transceiver communicatively coupled to the primary transceiver and a secondary controller communicatively coupled to the secondary transceiver.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/14 - Circuits pour réseaux principaux ou de distribution, à courant alternatif pour règler la tension dans des réseaux à courant alternatif par changement d'une caractéristique de la charge du réseau par interruption, ou mise en circuit, des charges du réseau, p.ex. charge équilibrée progressivement
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
54.
ACCURATE AND FAST POWER MODULE PROPERTIES ASSESSMENT
Systems and methods for accurate and fast measurement of junction temperature for power modules are provided. Such systems and methods include a one or more power transistors that each have a respective die surface over which is positioned and electrically coupled to a conductive overlay. A temperature sensor is physically bonded to a top surface of the conductive overlay to provide a direct temperature measurement for the one or more power transistors.
H01L 23/34 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température
G01K 1/143 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers pour la mesure de la température de surfaces
G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p.ex. des thermocouples
G01K 7/16 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments résistifs
G01R 19/165 - Indication de ce qu'un courant ou une tension est, soit supérieur ou inférieur à une valeur prédéterminée, soit à l'intérieur ou à l'extérieur d'une plage de valeurs prédéterminée
H01L 23/00 - DISPOSITIFS À SEMI-CONDUCTEURS NON COUVERTS PAR LA CLASSE - Détails de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 23/538 - Dispositions pour conduire le courant électrique à l'intérieur du dispositif pendant son fonctionnement, d'un composant à un autre la structure d'interconnexion entre une pluralité de puces semi-conductrices se trouvant au-dessus ou à l'intérieur de substrats isolants
H01L 25/07 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans le même sous-groupe des groupes , ou dans une seule sous-classe de , , p.ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans le groupe
H02H 1/00 - CIRCUITS DE PROTECTION DE SÉCURITÉ - Détails de circuits de protection de sécurité
H02H 7/12 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour redresseurs pour convertisseurs ou redresseurs statiques
55.
COUNTER-ROTATING GAS TURBINE ENGINES INCLUDING TURBINE SECTIONS WITH SEPARABLE TORQUE FRAMES
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.
F02C 3/067 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux comportant des rotors contra-rotatifs
F02C 3/10 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
56.
DEVICES, SYSTEMS, AND METHODS FOR SECURELY LOADING EMBEDDED SOFTWARE USING A MANIFEST
A method for initializing an engine control system of an aircraft may include authenticating a boot loader, authenticating a manifest in response to authentication of the boot loader wherein the manifest contains hashes of one or more software components, and in response to authentication of the manifest, loading a first set of software components from among the one or more software components onto a non-transitory computer-readable medium, calculating a hash of each software component of the first set of software components, authenticating the first set of software components by comparing the calculated hash of each software component of the first set of software components to the hash of a corresponding software component in the manifest, and executing the first set of software components in response to authentication of the one or more software components. Devices and systems are also provided for initializing an engine control system of an aircraft.
G06F 21/57 - Certification ou préservation de plates-formes informatiques fiables, p.ex. démarrages ou arrêts sécurisés, suivis de version, contrôles de logiciel système, mises à jour sécurisées ou évaluation de vulnérabilité
G06F 21/44 - Authentification de programme ou de dispositif
A gas turbine engine is provided defining an axial direction, a radial direction, and a circumferential direction. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order; a fan section including a fan rotatable by the turbomachine; a nacelle enclosing the fan; and an oil tank positioned within the nacelle, wherein the oil tank defines an effective length (LT) along the axial direction, a circumference span (CS) along the circumferential direction, and a radial height (ΔrT) along the radial direction, and wherein these parameters are related by a tank sizing factor (TSF) equal to the effective length (LT) times the circumference span (CS) divided by the radial height (ΔrT) squared LT×CS/ΔrT2), wherein the tank sizing factor (TSF) is between 20 and 2200.
A rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along a central axis of the rotary component and an outer casing arranged exterior to the plurality of rotor blades in a radial direction of the rotary component. The outer casing defines a gap between a blade tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features formed into an interior surface thereof. Further, at least one feature of the plurality of features is a slot having an acoustic liner feature integrated therein to reduce operational noise of the rotary component.
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
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
A gas turbine engine includes a rotatably driven engine component including a shaft coupling. The shaft coupling defines a first axial centerline and includes an inner surface. The inner surface includes a plurality of internal splines extending radially inwardly from the inner surface with respect to the first axial centerline. The engine further includes a driving member having a driving end portion and defining a second axial centerline. The driving end portion includes an outer surface and a plurality of external splines extending radially outwardly from the outer surface with respect to the second axial centerline. The plurality of external splines is drivingly engaged with the plurality of internal splines. The plurality of internal splines or the plurality of external splines comprises bowed splines.
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F16D 1/10 - Accouplements à action rapide dans lesquels les pièces sont simplement présentées dans l'axe
An additive manufacturing apparatus includes a support configured to support a resin and a constituent material. A support plate includes a window. A stage is configured to hold one or more composite layers of the resin and the constituent material to form a composite component positioned opposite the support plate. A radiant energy device is positioned on an opposite side of the support from the stage and is operable to generate and project radiant energy in a patterned image through the window. An actuator assembly is configured to move the stage in a Z-axis direction and a Y-axis direction.
Dual-phase magnetic components include an intermixed first region and second region formed from a single material, wherein the first region includes a magnetic ferrous composition, and wherein the second region includes a non-magnetic austenite composition and a dispersion of nitride precipitates.
A cooling system for a superconducting machine includes a thermal shield, a cryocooler, and an extension member. The cryocooler is thermally coupled to the thermal shield via at least one thermal busbar and at least one flexible connector, the at least one thermal busbar secured across the at least one flexible connector. The extension member is secured to the at least one thermal busbar and the thermal shield so as to position the at least one thermal busbar at a location that minimizes a length of the at least one flexible connector.
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
H02K 55/02 - Machines dynamo-électriques comportant des enroulements qui fonctionnent à des températures cryogéniques du type synchrone
H02K 55/04 - Machines dynamo-électriques comportant des enroulements qui fonctionnent à des températures cryogéniques du type synchrone avec des enroulements à champ tournant
A dome-deflector assembly for a gas turbine includes a dome, a deflector, and at least one dome-deflector connecting assembly that includes a connecting member connecting the dome and the deflector together with a cavity being defined between the dome and the deflector. The connecting member extends through the deflector and has a first end arranged at a hot surface side of the deflector and a second end arranged to connect with the dome. The dome-deflector connecting assembly is configured to provide a flow of cooling air from the cavity to the hot surface side of the deflector to cool the first end of the connecting member on the hot surface side of the deflector.
A method for damping oscillations in a tower of a wind turbine includes determining a primary rotational frequency of the rotor (fp) that correlates to a tower resonance frequency (fr). The method defines an exclusion zone between a first rotational frequency of the rotor (f1) that is less than the primary rotational frequency (fp) and a second rotational frequency of the rotor (f2) that is greater than the primary rotational frequency (fp). At rotor frequencies below the exclusion zone, a first tower-damping force strategy is applied. At rotor frequencies above the exclusion zone, a second tower-damping force strategy is applied that is different from the first tower-damping force strategy.
F03D 7/02 - Commande des mécanismes moteurs à vent les mécanismes moteurs à vent ayant l'axe de rotation sensiblement parallèle au flux d'air pénétrant dans le rotor
65.
HOT ISOSTATIC PRESSING CONTAINER WITH ENHANCED DIRECTIONAL CONSOLIDATION
The present application provides a container for use in manufacturing a metal billet from a metal powder in a hot isostatic pressing process. The container may include a top, a bottom, a wall extending between the top and the bottom, an enhanced directional consolidation feature in the wall, and a sleeve positioned about the enhanced directional consolidation feature.
An additive manufacturing apparatus includes a feed module and a take-up module that are configured to operably couple with a foil. A stage is configured to hold one or more cured layers of a resin that form a component. A radiant energy device is positioned opposite to the at least one stage. The radiant energy device is operable to generate and project radiant energy in a predetermined pattern. An actuator is configured to change a relative position of the at least one stage and the foil. An accumulator is positioned between the feed module and the take-up module. The accumulator is configured to retain an intermediate portion of the foil to allow a first portion of the foil upstream of the accumulator to move at a first speed and a second portion of the foil downstream of the accumulator to move at a second speed during a defined time period.
B29C 64/236 - Moyens d’entraînement pour un mouvement dans une direction dans le plan d’une couche
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
F23R 3/34 - Alimentation de différentes zones de combustion
F02C 3/20 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion
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 3/36 - Alimentation en combustibles différents
68.
COMPONENT FOR A TURBINE ENGINE WITH A COOLING HOLE
An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.
A method for detecting and reducing edgewise vibrations in a rotor blade of a wind turbine includes, for a given wind speed, determining a frequency or frequency band at which edgewise vibrations are producible in the rotor blade. The method determines an electrical characteristic of the pitch actuator that correlates to an increased torque required to hold a pitch angle of the rotor blade constant at the frequency or frequency band. During an operational power-production mode of the wind turbine, the electrical characteristic of the pitch actuator is monitored. Upon the electrical characteristic reaching a predefined limit value indicative of edgewise vibrations in the rotor blade, corrective action is initiated by the wind turbine controller to reduce or prevent the edgewise vibrations.
F03D 7/02 - Commande des mécanismes moteurs à vent les mécanismes moteurs à vent ayant l'axe de rotation sensiblement parallèle au flux d'air pénétrant dans le rotor
A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.
A method for damping oscillations in a tower of a wind turbine includes determining a primary rotational frequency of the rotor (fp) that correlates to a tower resonance frequency (fr). The method defines an exclusion zone between a first rotational frequency of the rotor (fl) that is less than the primary rotational frequency (fp) and a second rotational frequency of the rotor (f2) that is greater than the primary rotational frequency (fp). At rotor frequencies below the exclusion zone, a first tower-damping force strategy is applied. At rotor frequencies above the exclusion zone, a second tower-damping force strategy is applied that is different from the first tower-damping force strategy.
72.
FOREIGN OBJECT DETECTION IN A WIRELESS POWER TRANSFER SYSTEM
This disclosure provides systems, methods and apparatuses for foreign object detection (FOD) in a wireless power transfer (WPT) system. Some implementations relate generally to the use of detection coils that are excited to measure and compare a differential current through a coil pair that includes at least two detection coils. A foreign object may cause a change in impedance for one or more detection coils compared to one or more other detection coils. By detecting the differential current of the coil pair, a detection apparatus may determine that a foreign object is in proximity to one of the detection coils of the coil pair. This disclosure provides several options for the design, construction, layout, and operations of detection coils to improve foreign object detection.
G01V 3/10 - Prospection ou détection électrique ou magnétique; Mesure des caractéristiques du champ magnétique de la terre, p.ex. de la déclinaison ou de la déviation fonctionnant au moyen de champs magnétiques ou électriques produits ou modifiés par les objets ou les structures géologiques, ou par les dispositifs de détection en utilisant des cadres inducteurs
H02J 50/60 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique sensibles à la présence d’objets étrangers, p.ex. détection d'êtres vivants
A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
F02C 7/06 - Aménagement des paliers; Lubrification
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B60L 50/16 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion avec des dispositions pour une propulsion mécanique directe séparée,
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
F02K 3/04 - 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
General Electric Deutschland Holding GmbH (Allemagne)
Inventeur(s)
Vitt, Paul Hadley
Simonetti, Michael
Sharma, Ashish
Abrégé
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
A system for spacing and fastening tubular structures, and a related method. The system includes a spacer element configured to engage a plurality of tubular structures, to spatially separate the plurality of tubular structures from one another, and to distribute stress in the plurality of tubular structures. The system further includes a fastening element configured to extend around at least a portion of an outer surface of the plurality of tubular structures, and to fasten the plurality of tubular structures to the spacer element in an adaptively spaced configuration.
F16L 3/22 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace
F16L 3/10 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection fractionnés, c. à d. à deux éléments en prise avec le tuyau, le câble ou le conduit de protection
F16L 3/233 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace pour un faisceau de tuyaux ou un ensemble de tuyaux disposés les uns à coté des autres en contact mutuel au moyen d'une bande flexible
77.
SEVERE WEATHER-DRIVEN LARGE-SCALE OUTAGE MANAGEMENT FOR EMERGENCY POWER GRID
Provided is a system and method that can safely generate and execute an outage plan for a power grid based on severe weather-driven events. In one example, the method may include receiving predicted or current operational power system state data from a power grid and weather conditions associated with the power grid, identifying one or more nodes on the power grid to de-energize based on the operational state data and the current weather conditions, determining a sequence of instructions to perform to de-energize the one or more identified nodes based on the operational state data and the current weather conditions associated with the power grid, and generating an outage plan including mitigation steps for ensuring the stability and security of the power grid which includes the determined sequence of instructions to be executed and store the outage plan in the memory.
H02J 3/14 - Circuits pour réseaux principaux ou de distribution, à courant alternatif pour règler la tension dans des réseaux à courant alternatif par changement d'une caractéristique de la charge du réseau par interruption, ou mise en circuit, des charges du réseau, p.ex. charge équilibrée progressivement
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.
F02C 7/22 - Systèmes d'alimentation en combustible
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
F02K 3/08 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande
A motorized apparatus for use in maintaining a pipe having a sidewall defining an interior cavity is provided. The motorized apparatus includes a body assembly extending along a longitudinal axis, at least one maintenance device coupled to the body assembly, and a plurality of leg assemblies coupled circumferentially around the body assembly. The motorized apparatus also includes a plurality of drive mechanisms coupled to the plurality of leg assemblies. The plurality of drive mechanisms are configured to interact with the sidewall. The plurality of drive mechanisms include at least two wheels. The plurality of drive mechanisms are arranged to move the body assembly in a first direction parallel to the longitudinal axis, move the body assembly in a second direction perpendicular to the longitudinal axis, and rotate the body assembly around the longitudinal axis.
C12Q 1/18 - Test de l'activité antimicrobienne d'un matériau
C12Q 1/686 - Réaction en chaine par polymérase [PCR]
C12Q 1/689 - Produits d’acides nucléiques utilisés dans l’analyse d’acides nucléiques, p.ex. amorces ou sondes pour la détection ou l’identification d’organismes pour les bactéries
81.
Hybrid-electric gas turbine engine and method of operating
A hybrid-electric gas turbine engine and method of operating includes independently controlling a first electric machine providing torque to a first shaft to maintain a desired clearance between a first set of blades rotatably coupled to the first shaft, and a casing.
F01D 11/18 - Régulation ou commande du jeu d'extrémité des aubes, c.à d. de la distance entre les extrémités d'aubes du rotor et le corps du stator par des moyens auto-réglables utilisant des éléments stator ou rotor ayant un comportement thermique déterminé, p.ex. isolation sélective, inertie thermique, dilatation différentielle
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
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance
82.
CLEARANCE DESIGN PROCESS AND STRATEGY WITH CCA-ACC OPTIMIZATION FOR EGT AND PERFORMANCE IMPROVEMENT
Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.
F01D 11/14 - Régulation ou commande du jeu d'extrémité des aubes, c.à d. de la distance entre les extrémités d'aubes du rotor et le corps du stator
F01D 11/10 - 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 fluide d'obturation, p.ex. de la vapeur
83.
CLOSED-LOOP COOLING SYSTEM FOR A GAS TURBINE ENGINE
A closed-loop cooling system for a gas turbine engine, comprising: a pump having a pump inlet and a pump outlet; a first plurality of stator vanes defining first cooling cavities therein; and a second plurality of stator vanes, defining second cooling cavities therein, wherein the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet.
Systems and methods for high bandwidth control of thrust response for turbofan or turboprop engines are provided. Such systems and methods include an engine control system that processes a rate command and a feedback signal from an engine to generate separate fuel and electric machine control signals that respectively control fuel and electric machine dynamics of the engine to produce engine dynamics that result in desired thrust response.
A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.
Methods for repairing a thermal barrier coating deposited on a component with localized spallation of the thermal barrier coating includes depositing a primer slurry on a thermally grown oxide of the component exposed by the localized spallation, depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes at least one of a metal and a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond between the primer and the thermally grown oxide and a second chemical bond between the primer and the ceramic material.
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 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
Flow-metering fuel systems and related methods are disclosed. An example apparatus includes a pipe defining a flow path for fuel, the pipe fluidly coupled to a combustor, a first portion of the pipe having a first cross-sectional area, a second portion of the pipe having a second cross-sectional area smaller than the first cross-sectional area, the second portion downstream of the first portion, and an actuator to adjust a flow rate of the fuel in the pipe based on a first pressure of the fuel in the first portion of the pipe, a second pressure of the fuel in the second portion of the pipe, and a temperature of the fuel.
F02C 9/26 - Commande de l'alimentation en combustible
F02C 7/22 - Systèmes d'alimentation en combustible
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
88.
SYSTEM AND METHOD FOR DISTRIBUTED QUANTUM ENTANGLEMENT
A system configured to support quantum communication using quantum technologies comprises: a plurality of electrical devices, wherein an electrical device is operationally connected with another electrical device, a first electrical device and a second electrical device of the plurality of electrical devices are configured to be entangled with each other in a quantum network for the quantum communication based on correlation state of the first electrical device and the second electrical device, and an entanglement source configured to distribute entangled quantum information over the quantum network. The first electrical device and the second electrical device are configured to receive the entangled quantum information and periodically check entangled quantum states based on the entangled quantum information to ensure the correlation state.
G06N 10/60 - Algorithmes quantiques, p.ex. fondés sur l'optimisation quantique ou les transformées quantiques de Fourier ou de Hadamard
G06N 10/70 - Correction, détection ou prévention d’erreur quantique, p.ex. codes de surface ou distillation d’état magique
G06N 10/80 - Programmation quantique, p.ex. interfaces, langages ou boîtes à outils de développement logiciel pour la création ou la manipulation de programmes capables de fonctionner sur des ordinateurs quantiques; Plate-formes pour la simulation ou l’accès aux ordinateurs quantiques, p.ex. informatique quantique en nuage
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
Apparatus, systems, and articles of manufacture are disclosed to dynamically support axial thrust in pumps. Examples disclosed herein include a thrust bearing system including a thrust disc coupled to an impeller shaft; a first thrust pad coupled to a body of the pump, the first thrust pad positioned on a forward side of the thrust disc; a second thrust pad coupled to the body of the pump, the second thrust pad positioned on an aft side of the thrust disc; and a spring-loaded assembly integrated into the first and second thrust pads, the spring-loaded assembly connected to a pump outlet via a first flowline, the first flowline to transmit a working fluid from the pump outlet to the forward side of the thrust disc or the aft side of the thrust disc based on a position of the spring-loaded assembly.
F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
F01D 3/04 - "Machines" ou machines motrices avec équilibrage des poussées axiales effectué par le fluide énergétique la poussée axiale étant équilibrée par la poussée d'un piston d'équilibrage ou d'un organe analogue
F01D 15/08 - Adaptations pour la commande des pompes ou combinaisons avec celles-ci
90.
Gas turbine engine having a heat exchanger located in an annular duct
i), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:
1 is equal to 13,200 inches per second during the high power operating condition.
A turbine system includes a foam generating assembly having an in situ foam generating device at least partially positioned within the fluid passageway of the turbine engine, such that the in situ foam generating device is configured to generate foam within the fluid passageway of the turbine engine.
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
B01F 23/235 - Mélange de gaz avec des liquides en introduisant des gaz dans des milieux liquides, p.ex. pour produire des liquides aérés pour la fabrication de mousse
B01F 25/31 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal
B01F 25/312 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal avec des éléments Venturi; Leurs détails
B01F 25/313 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal dans lesquels des composants supplémentaires sont introduits au centre du conduit
B01F 25/314 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal dans lesquels des composants supplémentaires sont introduits à la circonférence du conduit
Hybrid composite components, such as gas turbine engine containment assemblies, a hybrid composite component having an annular composite shell and an annular metallic shell joined with the composite shell. A containment assembly including a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes a first composite shell joined with a metallic shell. The metallic shell defining a first portion of the inner surface and the first composite shell defining a second portion of the inner surface.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
93.
HEAT EXTRACTION OR RETENTION DURING DIRECTIONAL SOLIDIFICATION OF A CASTING COMPONENT
A method of forming a directionally-solidified casting component using a casting system is provided. The casting system includes a chamber having a heating zone and a cooling zone separated by a baffle plate. The method includes pouring an alloy in a liquid state into a mold shell. The mold shell is positioned on a chill plate within the heating zone. The method further includes moving the mold shell from the heating zone into the cooling zone. The alloy transfers from the liquid state to a solid state within the mold shell while moving the mold shell from the heating zone to the cooling zone. The method further includes contacting the mold shell with a heat transfer member.
The present disclosure generally relates to methods and apparatuses for chemical vapor deposition (CVD) during additive manufacturing (AM) processes. Such methods and apparatuses can be used to embed chemical signatures into manufactured objects, and such embedded chemical signatures may find use in anti-counterfeiting operations and in manufacture of objects with multiple materials.
C23C 16/50 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c. à d. procédés de dépôt chimique en phase vapeur (CVD) caractérisé par le procédé de revêtement au moyen de décharges électriques
B22F 7/02 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives
B22F 7/04 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives avec une ou plusieurs couches non réalisées à partir de poudre, p.ex. à partir de tôles
B22F 7/06 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p.ex. pour former des outils à embouts rapportés
B22F 10/14 - Formation d’un corps vert par projection de liant sur un lit de poudre
B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
B22F 10/50 - Traitement des pièces ou des articles pendant leur formation, p.ex. traitements appliqués aux couches fusionnées pendant leur formation
B22F 10/62 - Traitement de pièces ou d'articles après leur formation par des moyens chimiques
B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
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 64/165 - Procédés de fabrication additive utilisant une combinaison de matériaux solides et liquides, p.ex. une poudre avec liaison sélective par liant liquide, catalyseur, inhibiteur ou absorbeur d’énergie
B29C 64/20 - Fabrication additive, c. à d. fabrication d’objets en trois dimensions [3D] par dépôt additif, agglomération additive ou stratification additive, p.ex. par impression en 3D, stéréolithographie ou frittage laser sélectif - Détails ou accessoires à cet effet
A gas turbine engine is provided. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement; and an air-to-air heat exchanger having an air-to-air heat exchanger potential defined by a product raised to a half power, the product being an effectiveness associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine, and wherein the air-to-air heat exchanger potential is between 0.028 and 0.067 for a bypass ratio associated with the gas turbine engine between 3 and 10 and the effectiveness being between 0.5 and 0.9 and is between 0.015 and 0.038 for a bypass ratio associated with the gas turbine engine between 10 and 20 and the effectiveness being between 0.3 and 0.9.
General Electric Deutschland Holding GmbH (Allemagne)
Inventeur(s)
Huh, Kum Kang
Osama, Mohamed
Abrégé
An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.
B60R 16/03 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour l'alimentation des sous-systèmes du véhicule en énergie électrique
B60L 50/13 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion utilisant des générateurs à courant alternatif et des moteurs à courant alternatif
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02K 11/042 - Redresseurs associés à des parties tournantes, p.ex. à des noyaux rotoriques ou à des arbres tournants
97.
ALUMINUM SLURRY COATINGS AND METHODS OF THEIR FORMATION AND USE
Methods for reducing a concentration of hexavalent chromium within a first aluminum slurry by adding a reducing agent to form a second aluminum slurry are provided. The reducing agent causes a chemical reduction reaction with the hexavalent chromium compound of the first aluminum slurry to form a trivalent chromium compound within the second aluminum slurry such that a first weight ratio of hexavalent chromium to trivalent chromium in the first aluminum slurry is decreased to a second weight ratio of hexavalent chromium to trivalent chromium in the second aluminum slurry, with the second weight ratio being less than the first weight ratio.
B22F 9/18 - Fabrication des poudres métalliques ou de leurs suspensions; Appareils ou dispositifs spécialement adaptés à cet effet par un procédé chimique avec réduction de mélanges métalliques
B22F 1/145 - Traitement chimique, p.ex. passivation ou décarburation
A sensor for a flexible sensor assembly includes a drive coil, a first set of sensing coils, a second set of sensing coils, and a configuration for sensing for discontinuities in a structure desired to be sensed. A method of operating the sensor can include positioning the sensor proximate to the structure, energizing the drive coil, and sensing eddy currents with the sensing coils.
G01N 27/90 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques pour rechercher la présence des criques en utilisant les courants de Foucault
An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.
A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.
B08B 7/02 - Nettoyage par des procédés non prévus dans une seule autre sous-classe ou un seul groupe de la présente sous-classe par distorsion, battage ou vibration de la surface à nettoyer
B08B 13/00 - Accessoires ou parties constitutives, d'utilisation générale, des machines ou appareils de nettoyage
