A method of making an electrocaloric element includes dissolving or dispersing an electrocaloric polymer in an organic solvent having a boiling point of less than 100° C. at 1 atmosphere to form a liquid composition comprising the electrocaloric polymer. A film of the liquid composition is cast on a substrate, and the organic solvent is evaporated to form a film of the electrocaloric polymer. The film is removed from the substrate and disposed between electrical conductors to form an electrocaloric element.
F25B 21/00 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques
B29C 41/00 - Façonnage par revêtement d'un moule, noyau ou autre support, c.-à-d. par dépôt de la matière à mouler et démoulage de l'objet forméAppareils à cet effet
B29C 41/12 - Étalement de la matière à mouler sur un support
B29L 7/00 - Objets plats, p. ex. pellicules ou feuilles
H10N 15/10 - Dispositifs thermoélectriques utilisant le changement thermique de la constante diélectrique, p. ex. en opérant au-dessus et en-dessous du point de Curie
A control system for a hybrid electric powerplant of an aircraft can include a master controller configured to receive one or more power settings and to output a heat engine setting and an electric motor setting and a heat engine controller operatively connected to the master controller. The heat engine controller can be configured to receive the heat engine setting and to control a heat engine system as a function of the heat engine setting to control torque output by a heat engine. The system can include an electric motor controller operatively connected to the master controller. The electric motor controller configured to receive the electric motor engine setting and to control an electric motor system as a function of the electric motor setting to control torque output by an electric motor. The master controller can include a protection control module configured to provide one or more protection commands to directly control one or more heat engine protection systems and one or more electric motor protection systems.
A turbine blade has an attachment root and an airfoil. A cooling passageway system has a plurality of trunks extending from respective inlets along the root inner diameter end from a leading trunk near a first axial end to a trailing trunk near a second axial end; and a plurality of outlets along the airfoil including trailing edge outlets fed by the trailing trunk. Viewed normal to a root end-to-end centerplane: the trailing trunk has a turn passing forward and then rearward; an outside of the turn protrudes forward; and the outside of the turn has a tighter curvature than an inside of the turn.
An investment casting core system includes first and second investment casting cores. The first investment casting core has a pin and the second investment casting core has a hole and an access slot that opens to the hole. The pin is disposed in the hole such as to space the first investment casting core in a fixed position relative to the second investment casting core. A bonding agent is disposed in the access slot and around the pin in the hole.
B22C 9/22 - Moules pour pièces de forme particulière
B22C 9/10 - NoyauxFabrication ou mise en place des noyaux
B22C 21/14 - Organes auxiliaires pour le renforcement ou l'immobilisation des matériaux de moulage ou des noyaux, p. ex. crochets, supports de noyaux, goujons, barres de châssis
5.
SOLUTION BASED CORROSION INHIBITORS FOR ALUMINUM ALLOY THERMAL SPRAY COATINGS
A method (400) for applying a coating to a substrate (124) includes spraying (414) an aluminum-based coating layer (120) on the substrate. The coating layer is then infiltrated (420) with an aqueous solution (610). The solution comprises: a source of chromium; and potassium hexafluorozirconate.
C23F 11/00 - Inhibition de la corrosion de matériaux métalliques par application d'inhibiteurs sur la surface menacée par la corrosion ou par addition d'inhibiteurs à l'agent corrosif
C25D 3/02 - Dépôt électrochimiqueBains utilisés à partir de solutions
C25D 3/04 - Dépôt électrochimiqueBains utilisés à partir de solutions de chrome
C25D 3/06 - Dépôt électrochimiqueBains utilisés à partir de solutions de chrome à partir des solutions de chrome trivalent
C23C 4/00 - 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
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 4/137 - Pulvérisation sous vide ou sous atmosphère inerte
C23C 10/18 - Diffusion à l'état solide uniquement d'éléments métalliques ou de silicium dans la couche superficielle de matériaux métalliques au moyen de liquides, p. ex. au moyen de bains de sels, de suspensions dans des liquides
C23C 22/05 - Traitement chimique de surface de matériaux métalliques par réaction de la surface avec un milieu réactif laissant des produits de réaction du matériau de la surface dans le revêtement, p. ex. revêtement par conversion, passivation des métaux au moyen de solutions aqueuses
C23C 22/30 - Traitement chimique de surface de matériaux métalliques par réaction de la surface avec un milieu réactif laissant des produits de réaction du matériau de la surface dans le revêtement, p. ex. revêtement par conversion, passivation des métaux au moyen de solutions aqueuses au moyen de solutions aqueuses acides d'un pH < 6 contenant des composés du chrome hexavalent contenant aussi du chrome trivalent
C23C 22/56 - Traitement de l'aluminium ou des alliages à base d'aluminium
6.
COATING REPAIR FOR CERAMIC MATRIX COMPOSITE (CMC) SUBSTRATES
In a method for repairing a coated article, the article has: a ceramic matrix composite (CMC) substrate; and a coating system having a plurality of layers. A damage site at least partially penetrates at least one of the layers. The method includes: applying a slurry of a repair material to the damage site for repairing a first of the penetrated layers; and after the applying, heating the repair material with a plasma torch.
C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
C04B 35/571 - Céramiques fines obtenues à partir de précurseurs polymères
F01D 5/00 - AubesOrganes de support des aubesDispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
7.
SYSTEMS AND METHODS FOR AUTOMATED ADAPTIVE MANUFACTURING OF AIRFOIL CASTINGS
A system for automated adaptive manufacturing of airfoil castings is disclosed. The system may receive a three dimensional scan of a work piece. The system may compare the three dimensional scan to a digital model of the work piece. The system may identify an area of dimensional abnormality on the work piece based on the comparison. The system may alter the area of dimensional abnormality on the work piece.
G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
8.
INTERMEDIATE TEMPERATURE METAL SUPPORTED SOLID OXIDE ELECTROLYZER
A metal-supported electrolyzer includes an electrolysis cell that has, in stacked order, an electrode unit having a first solid oxide electrode layer, a solid oxide electrolyte layer that is proton-conductive in a temperature range of 650°C or lower, and a second solid oxide electrode layer. A porous metal sheet in contact with the second solid oxide electrode layer supports the electrode unit, a metal separator sheet bonded to the porous metal sheet, and a metal interconnect backing the metal separator sheet.
C25B 1/04 - Hydrogène ou oxygène par électrolyse de l'eau
C25B 9/10 - Cellules comportant des électrodes fixes de dimensions stables; Assemblages de leurs éléments de structure avec des diaphragmes comprenant une membrane d'échange d'ions dans ou sur laquelle est incrusté du matériau pour électrode
Aerospace components that are exposed to foreign particles during operation are described. The aerospace components include a substrate surface and a coating and/or means for repelling a foreign particle from the substrate surface.
B08B 17/06 - Procédés pour empêcher la salissure pour empêcher le dépôt de crasses ou de poussières en donnant aux objets susceptibles de s'encrasser une conformation ou un agencement particulier
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p. ex. nanocomposites
B82Y 40/00 - Fabrication ou traitement des nanostructures
An apparatus for countergravity casting a metallic material, comprises: a crucible for holding melted metallic material; a casting chamber for containing a mold; a fill tube capable of extending into the crucible to communicate melted metallic material to the casting chamber; a gas source coupled a headspace of the melting vessel to allow the gas source to pressurize said headspace to establish a pressure differential to force the melted metallic material upwardly through said fill tube into said mold; and means for gettering sulfur.
A combustor assembly (56) for a turbine engine includes a liner panel (64) defining a portion of an inner surface (68) of a combustor chamber (55), liner panel including an end face (70) transverse the inner surface, and at least one diffuser (84) through the end face. A liner panel and a method are also disclosed.
A method of making an electrocaloric element includes dissolving or dispersing an electrocaloric polymer in an organic solvent having a boiling point of less than 100° C. at 1 atmosphere to form a liquid composition comprising the electrocaloric polymer. A film of the liquid composition is cast on a substrate, and the organic solvent is evaporated to form a film of the electrocaloric polymer. The film is removed from the substrate and disposed between electrical conductors to form an electrocaloric element.
B29C 41/00 - Façonnage par revêtement d'un moule, noyau ou autre support, c.-à-d. par dépôt de la matière à mouler et démoulage de l'objet forméAppareils à cet effet
B29C 41/12 - Étalement de la matière à mouler sur un support
F25B 21/00 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques
H10N 15/10 - Dispositifs thermoélectriques utilisant le changement thermique de la constante diélectrique, p. ex. en opérant au-dessus et en-dessous du point de Curie
B29L 7/00 - Objets plats, p. ex. pellicules ou feuilles
14.
Method of forming electrodes on electrocaloric film
F25B 21/00 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques
F25B 41/20 - Disposition des soupapes, p. ex. de soupapes marche-arrêt ou de soupapes de régulation de débit
H01L 37/02 - Dispositifs thermoélectriques sans jonction de matériaux différents; Dispositifs thermomagnétiques, p.ex. utilisant l'effet Nernst-Ettinghausen; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives utilisant le changement thermique de la constante diélectrique, p.ex. en opérant au-dessus et en-dessous du point de Curie
F25B 49/00 - Disposition ou montage des dispositifs de commande ou de sécurité
F25B 49/02 - Disposition ou montage des dispositifs de commande ou de sécurité pour machines, installations ou systèmes du type à compression
A rotor blade for a rotary wing aircraft and a tip for the rotor blade. The rotor blade includes a blade root, a blade tip and a blade body that extends from the blade root to the blade tip. The blade tip includes: a continuously swept leading edge, a compound trailing edge, and a continuous anhedral.
A method of manufacturing a composite vessel assembly (20) includes the step of placing the composite vessel assembly (20) in a pliable containment (94) prior to curing of a resin of the composite vessel assembly (20). With the composite vessel assembly (20) in the pliable containment (94), a vacuum is applied through an orifice (96) in the pliable containment (94) to evacuate air and compact the composite vessel assembly (20).
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
An aircraft has a gas turbine engine including a compressor section that includes at least one compressor bleed. An environmental control system has an air input configured to receive pressurized cabin air. An intercooler has an input and an output. A selection valve is configured to selectively connect the bleeds to an intercooler input. At least one auxiliary compressor is connected to the intercooler output. An output of at least one auxiliary compressors is connected to an ECS air input. A controller is configured to receive contemporaneous operational data, calculate minimum configuration requirements to satisfy environmental demands, and transmit calculated configuration requirements to at least the selection valve to achieve a desired pressure and temperature for the air downstream of the auxiliary compressor. A method for supplying engine air to an environmental control system and a system for use on a turbine engine powered aircraft are also disclosed.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
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
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
18.
INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE
A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A is valve downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
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
A pyroelectric system (10) is disclosed that includes a plurality of pyroelectric modules (44, 46, 48, 50). The pyroelectric modules individually include a pyroelectric element, a first port (44a, 46a, 48a, 50a), a second port (44b, 46b, 48b, 50b), and an internal module fluid flow path (26) between the first port and the second port in thermal communication with the pyroelectric element. The pyroelectric modules are arranged along a cascade fluid flow path (51) connecting the first ports of the pyroelectric modules. A hot side inlet (28) to the cascade fluid flow path receives fluid at a first temperature from a heat source in fluid communication with the cascade fluid flow path, and the fluid is discharged from the cascade fluid flow path to a hot side outlet (34). A sink fluid flow path (53) comprises fluid at a second temperature lower than the first temperature, and is in fluid communication with the second ports of each of the plurality of pyroelectric modules.
H01L 37/02 - Dispositifs thermoélectriques sans jonction de matériaux différents; Dispositifs thermomagnétiques, p.ex. utilisant l'effet Nernst-Ettinghausen; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives utilisant le changement thermique de la constante diélectrique, p.ex. en opérant au-dessus et en-dessous du point de Curie
A rotor blade deflection sensing system including a rotor blade having a first surface, a second surface, a third surface and a fourth surface. At least two fiber optic sensor arrays are mounted to the rotor blade. At least one of the at least two fiber optic sensor arrays is mounted to one of the first surface, the second surface, the third surface and the fourth surface and another of the at least two fiber optic sensor arrays being mounted to another of the first surface, a second surface, a third surface and a fourth surface. A controller is operatively connected to the at least two fiber optic sensor arrays. The controller determines one or more of a flapwise and an edgewise displacement based on inputs from the at least two fiber optic sensor arrays.
An electrocaloric element for a heat transfer system includes an electrocaloric material of a copolymer of (i) vinylidene fluoride, (ii) an addition polymerization monomer selected from tetrafluoroethylene, trifluoroethylene, vinyl fluoride, or combinations thereof, and (iii) a halogenated addition polymerization monomer larger than vinylidene fluoride. It is also provided that: (a) the monomer (ii) includes an addition polymerization monomer smaller than trifluoroethylene, (b) at least one of the addition polymerization monomers (ii) or (iii) is a chiral monomer, and the copolymer includes syndiotactic ordered segments of chiral monomer units, and/or (c) at least one of the addition polymerization monomers (ii) or (iii) comprises chlorine, and the copolymer includes an ordered distribution of monomer units comprising chlorine along the copolymer polymer backbone.
A heat transfer system is disclosed in which, an electrocaloric material includes a copolymer of a monomer mixture including (i) vinylidene fluoride, (ii) an addition polymerization monomer selected from tetrafluoroethylene, trifluoroethylene, or a monomer smaller than trifluoroethylene, and (iii) a halogenated addition polymerization monomer different than (ii) that is larger than vinylidene fluoride. The electrocaloric material also includes an additive selected from a nucleating agent having a polar surface charge, electrocalorically active solid particles, or a combination thereof. Electrodes are disposed on opposite surfaces of the electrocaloric material, and an electric power source is configured to provide voltage to the electrodes. The system also includes a first thermal flow path between the electrocaloric material and a heat sink, and a second thermal flow path between the electrocaloric material and a heat source.
A method of making an energy storage article having a metal nitride electrode is disclosed where metal nitride is made by nitriding particles of a metal or oxide of a metal selected from vanadium molybdenum, titanium, niobium, tungsten, or combinations including any of the foregoing by contacting the particles with a gas of nitrogen and hydrogen, or ammonia, in a fluidized bed reactor to form particles of metal nitride for the electrode.
H01G 11/30 - Électrodes caractérisées par leur matériau
H01G 11/24 - Électrodes caractérisées par les propriétés structurelles des matériaux composant les électrodes ou inclus dans les électrodes, p. ex. forme, surface ou porositéÉlectrodes caractérisées par les propriétés structurelles des poudres ou particules utilisées à cet effet
H01G 11/86 - Procédés de fabrication de condensateurs hybrides ou EDL ou de leurs composants spécialement adaptés pour les électrodes
24.
DEEP CONVOLUTIONAL NEURAL NETWORKS FOR CRACK DETECTION FROM IMAGE DATA
A method includes detecting at least one region of interest in a frame of image data. One or more patches of interest are detected in the frame of image data based on detecting the at least one region of interest. A model including a deep convolutional neural network is applied to the one or more patches of interest. Post-processing of a result of applying the model is performed to produce a post-processing result for the one or more patches of interest. A visual indication of a classification of defects in a structure is output based on the result of the post-processing.
G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
25.
COMPOSITE PRESSURE VESSEL ASSEMBLY WITH AN INTEGRATED NOZZLE ASSEMBLY
A pressure vessel assembly includes a vessel having a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore that is in fluid communication with the chamber. A nozzle assembly of the pressure vessel assembly includes a tube projecting at least in-part into the through-bore, and an o-ring disposed between, and in sealing contact with, the tube and the lip.
A method of manufacturing a composite vessel assembly (20) includes the steps of filling a first chamber defined by a first liner (28,30,32) with a first granulated material (96) through a first orifice (98) in the first liner. A vacuum is then applied to the first chamber, and the first orifice is plugged. The first liner may then be enveloped with a first layer (84) for structural rigidity followed by relief of the vacuum.
B29C 33/54 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille en matière poudreuse ou granulaire
B29C 33/52 - Moules ou noyauxLeurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p. ex. des objets à contre-dépouille solubles ou fusibles
B29C 70/42 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts
F17C 1/16 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en matériaux plastiques
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
27.
COMPOSITE PRESSURE VESSEL ASSEMBLY AND METHOD OF MANUFACTURING
A composite pressure vessel assembly includes a first vessel having a first inner layer and a second vessel having a second inner layer. An outer layer of the assembly is in contact with and substantially envelopes the first and second inner layers. A junction of the assembly has outer boundaries defined by segments of the first inner layer, the second inner layer and the outer layer. A cross-layered component of the assembly is disposed in the junction, the first and second inner layers and the outer layer for adding strength to the junction and restricting delamination.
F17C 1/14 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en aluminiumRécipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en acier amagnétique
F17C 1/16 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en matériaux plastiques
28.
SYSTEMS AND METHODS FOR DETECTING ENGINE VIBRATION
Systems and methods of monitoring health of rotating engine components are provided. The systems and methods may receive a measurement from a speed sensor (44), detect the measurement from the speed sensor (44) indicates a vibration of an engine, determine the vibration of the engine persisted for a predetermined duration, and signal the vibration of the engine is detected.
A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.
F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p. ex. un élément d'usure, déformable ou contraint de façon élastique
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
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 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02C 7/28 - Agencement des dispositifs d'étanchéité
36 - Services financiers, assurances et affaires immobilières
37 - Services de construction; extraction minière; installation et réparation
Produits et services
(1) Providing extended warranties services on aircraft engines; providing extended warranties on maintenance, repair, overhaul, conversion and servicing of aircraft engines
(2) Services for aircraft engines comprising repair, maintenance, overhaul, conversion, namely, replacement of an aircraft engine with another aircraft engine on an aircraft, exchange in the nature of exchanging an aircraft engine with another aircraft engine on an aircraft or engine swapping in the nature of swapping out an aircraft engine with another aircraft engine on an aircraft and replacement of engine or components thereof; maintenance services, overhaul services, exchange services, in the nature of exchanging an aircraft engine with another aircraft engine on an aircraft, engine conversion services, namely, replacement of an aircraft engine with another aircraft engine on an aircraft, all with respect to aircraft engines
A heat transfer system is disclosed that includes a plurality of electrocaloric elements (12) including an electrocaloric film (14), a first electrode (16) on a first side of the electrocaloric film, and a second electrode (18) on a second side of the electrocaloric film. A fluid flow path (20) is disposed along the plurality of electrocaloric elements, formed by corrugated fluid flow guide elements (19).
A heat transfer system includes an electrocaloric element comprising an electrocaloric film (12). A first electrical conductor is disposed on a first side of the electrocaloric film, and a second electrical conductor is disposed on a second side of the electrocaloric film. At least one of the first and second electrical conductors is an electrically conductive liquid. An electric power source (20) is in electrical contact with the first and second electrical conductors, and is configured to provide an electrical field across the electrocaloric film. A liquid flow path (28) is disposed along the plurality of electrocaloric elements for the electrically conductive liquid.
A heat transfer system is disclosed including a plurality of modules arranged in a stack. The stack modules include electrocaloric element and electrodes on each side of the film. A fluid flow path is disposed between two or more electrocaloric elements. A first electrical bus element (18) in electrical contact with the first electrode (14), and a second electrical bus element (20) in electrical contact with second electrode (16). The first electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said first electrical bus, or the second electrical bus element is electrically connected to at least one other electrical bus of another electrocaloric element in the stack at the same polarity as said second electrical bus.
A method of making an electrocaloric element includes forming conductive layers on opposing surfaces of a film comprising an electrocaloric material to form an electrocaloric element, wherein the forming of the conductive layers includes one or more of: vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time under reduced pressure is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure for a duration of time, wherein the duration of time of exposure to conductive material deposition is less than 240 minutes; vapor deposition of the conductive layers under reduced pressure, wherein the reduced pressure is 10 -8 torr to 500 torr; or maintaining the film at a temperature of less than or equal to 200 °C during forming of the conductive layers.
H01L 37/02 - Dispositifs thermoélectriques sans jonction de matériaux différents; Dispositifs thermomagnétiques, p.ex. utilisant l'effet Nernst-Ettinghausen; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives utilisant le changement thermique de la constante diélectrique, p.ex. en opérant au-dessus et en-dessous du point de Curie
A method of making an electrocaloric element includes dissolving or dispersing an electrocaloric polymer in an organic solvent having a boiling point of less than 100°C at 1 atmosphere to form a liquid composition comprising the electrocaloric polymer. A film of the liquid composition is cast on a substrate, and the organic solvent is evaporated to form a film of the electrocaloric polymer. The film is removed from the substrate and disposed between electrical conductors to form an electrocaloric element.
B29C 41/12 - Étalement de la matière à mouler sur un support
F25B 21/00 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques
F25B 21/04 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques utilisant l'effet PeltierMachines, installations ou systèmes utilisant des effets électriques ou magnétiques utilisant l'effet Nernst-Ettinghausen réversibles
H01L 37/02 - Dispositifs thermoélectriques sans jonction de matériaux différents; Dispositifs thermomagnétiques, p.ex. utilisant l'effet Nernst-Ettinghausen; Procédés ou appareils spécialement adaptés à la fabrication ou au traitement de ces dispositifs ou de leurs parties constitutives utilisant le changement thermique de la constante diélectrique, p.ex. en opérant au-dessus et en-dessous du point de Curie
36.
COMPOSITE PRESSURE VESSEL ASSEMBLY AND METHOD OF MANUFACTURING
A composite pressure vessel assembly includes at least one liner defining a chamber. The liner is perforated such that an applied composite layer envelops the liner and at least partially extrudes into the perforations during manufacture and when the chamber is placed under a vacuum.
A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.
A pressure vessel assembly includes a composite layer surrounding at least one chamber. A heating element is embedded in the composite layer for extracting gas from the chamber.
A pressure vessel assembly includes a vessel including a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore in fluid communication with the chamber. A nozzle assembly including a tube and a flange projecting radially outward from the tube. The tube includes a first portion projecting from the flange and through the through-bore and an opposite second portion projecting outward from the flange. The flange is in contact with the wall and the first portion includes an outer surface having a contour configured to produce sealing friction between the lip and the outer surface.
An illustrative example embodiment of a grid-forming inverter system includes an inverter including a plurality of switches, the inverter being configured to be selectively connected to a power grid; and an electronic controller including a voltage magnitude module that is configured to determine a voltage magnitude reference based on a voltage of the power grid when the inverter is in an inactive mode wherein the inverter is not operating to provide power, a phase locked loop module that is configured to determine a reference angle based on a phase angle of the voltage of the power grid when the inverter is in the inactive mode, and wherein the controller uses the voltage magnitude reference and the reference angle to set an initial voltage of the inverter to be approximately synchronized with the voltage of the power grid when the inverter switches from the inactive mode into a power providing mode.
H02M 7/42 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité
An additive fabrication process includes rotating a core member about a central axis. While the core member is rotating, a first material is selectively deposited onto the core member with respect to computerized design data representing an article to form a first radial layer of the article. While the core member with the first radial layer is rotating, a second material is selectively depositing onto the first radial layer with respect to the computerized design data to form a second radial layer of the article.
B22F 5/12 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser de tubes ou de fils
B29C 67/00 - Techniques de façonnage non couvertes par les groupes , ou
G05B 15/00 - Systèmes commandés par un calculateur
42.
UNIVERSAL POWER ELECTRONIC CELL FOR DISTRIBUTED GENERATION
A method of configuring a power conversion cell for a distributed power system according to an example of the present disclosure includes: importing one or more software modules onto a controller of a conversion device configured to control power conversion with one or more of the modules selected based on one or more of a load or source device, and the results of a software simulation.
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
H02J 1/00 - Circuits pour réseaux principaux ou de distribution, à courant continu
A power factor correction system according to the present disclosure includes an inverter connected in parallel with at least one load and a controller configured to command an output voltage of the inverter to provide reactive power to the at least one load when a voltage source is available to the load and real power and reactive power to the at least one load when the voltage source is unavailable to the load.
G05F 1/565 - Régulation de la tension ou de l'intensité là où la variable effectivement régulée par le dispositif de réglage final est du type continu utilisant des dispositifs à semi-conducteurs en série avec la charge comme dispositifs de réglage final sensible à une condition du système ou de sa charge en plus des moyens sensibles aux écarts de la sortie du système, p. ex. courant, tension, facteur de puissance
G05F 1/70 - Régulation du facteur de puissanceRégulation du courant réactif ou de la puissance réactive
H02M 1/42 - Circuits ou dispositions pour corriger ou ajuster le facteur de puissance dans les convertisseurs ou les onduleurs
A cooling system includes an electrocaloric element (12) having a liquid crystal elastomer or a liquid form liquid crystal retained in an elastomeric polymer matrix. A pair of electrodes (14,16) is disposed on opposite surfaces of the electrocaloric element. A first thermal flow path (18) is disposed between the electrocaloric element and a heat sink (17). A second thermal flow path (22) is disposed between the electrocaloric element and a heat source (20). The system also includes a controller (24) configured to control electrical current to the electrodes and to selectively direct transfer of heat energy from the electrocaloric element to the heat sink along the first thermal flow path or from the heat source to the electrocaloric element along the second thermal flow path.
An energy storage assembly includes an energy storage unit. A supervisor is operable to determine a power reference set point based upon a cost function. A storage unit controller is configured to control the energy storage unit to provide electric energy to at least one load based upon a power reference input that is based upon the power reference set point and at least one dynamically changing power profile from the at least one load.
A microgrid according to an exemplary aspect of the present disclosure includes, among other things, a plurality of intelligent electronic devices configured to communicate directly with one another in a first language. Each of the intelligent electronic devices includes a controller and a gateway. The gateway is configured to convert incoming messages from the first language to a second language native to the controller. The first language is different than the second language. A method is also disclosed.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
An image processing system configured to process perceived images of an environment includes a central processing unit (CPU) including a memory storage device having stored thereon a computer model of the environment, at least one sensor configured and disposed to capture a perceived environment including at least one of visual images of the environment and range data to objects in the environment, and a rendering unit (RU) configured and disposed to render the computer model of the environment forming a rendered model of the environment. The image processing system compares the rendered model of the environment to the perceived environment to update the computer model of the environment.
A microgrid controller includes a database in communication with a processor. The processor is operable to receive at least one microgrid input, to determine a first plurality of optimal power characteristic levels at a corresponding one of a plurality of first time intervals for a first time period, and to determine a second plurality of optimal power characteristic levels of a device determined at a corresponding one of a plurality of second time intervals for a second time period. The first time intervals are found at a first frequency different than a second frequency of the second time intervals. One of the second plurality of optimal power characteristic level corresponds to one of the first plurality of optimal power characteristic levels at each first time interval. The processor is configured to control a device optimal power characteristic level in response to the second plurality of optimal power characteristic levels.
G05B 13/02 - Systèmes de commande adaptatifs, c.-à-d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
G06F 1/30 - Moyens pour agir en cas de panne ou d'interruption d'alimentation
H02J 3/06 - Commande du transfert de puissance entre réseaux connectésCommande du partage de charge entre réseaux connectés
49.
System and method to detect shutoff valve failures
The present disclosure relates generally to system and method for detecting fuel shutoff valve failures in a system including multiple fuel shutoff valves connected in series. By commanding different fuel shutoff valves to close and detecting changes in the system operating conditions, the system and method may determine if any of the fuel shutoff valves are not working properly.
F02C 1/00 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de gaz chauds ou de gaz sous pression non chauffés, comme fluide de travail
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
F02D 41/22 - Dispositifs de sécurité ou d'avertissement en cas de conditions anormales
F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
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
Disclosed is an ion-exchange membrane that includes a molecular barrier for influencing permeation selectivity through the membrane. The membrane includes fluorinated carbon backbone chains and fluorinated side chains that extend off of the fluorinated carbon backbone chains. The fluorinated side chains include acid groups for ionic conductivity. The acid groups surround and define permeable domains that are free of the fluorinated carbon backbone chains. Molecular barriers are located in the permeable domains and influence permeability through the domains.
An electrochemical device includes first and second spaced-apart electrodes. The first electrode is configured for redox reactions with a liquid electrolyte solution and the second electrode is configured for redox reactions with each of a gaseous reductant and a gaseous oxidant. An electrolyte separator is arranged between the electrodes.
A method of treating a carbon electrode includes heat treating a carbon-based electrode in an environment that is above approximately 325°C and that includes an oxidizing gas, and prior to use of the carbon-based electrode in an electro-chemical battery device, soaking the carbon-based electrode in an oxidizer solution.
A method for treating a liquid redox electrolyte solution for use in a flow battery includes feeding a liquid redox electrolyte solution into a first half-cell of an electrochemical cell and feeding a gaseous reductant into a second half-cell of the electrochemical cell, and electrochemically reducing at least a portion of the liquid redox electrolyte solution in the electrochemical cell using the gaseous reductant.
A power balancing assembly according to an exemplary aspect of the present disclosure includes, among other things, at least one sensor operable to detect a first electrical parameter and a second electrical parameter relating to a first portion of a power grid. An energy storage device is coupled to a second portion of the power grid. A controller determines that the second portion should be disconnected from the first portion based upon determining an electrical variation in the first electrical parameter, and causes the energy storage device to operate at a power level based on an instantaneous value of the second electrical parameter prior to the second portion being disconnected from the first portion of the power grid.
H02P 9/04 - Commande s'exerçant sur un moteur primaire non électrique et dépendant de la valeur d'une caractéristique électrique à la sortie de la génératrice
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p. ex. batterie tampon
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
The present disclosure provides devices and methods related to park brake systems and methods. In various embodiments, a park brake system may comprise a motor shaft having a first diameter portion and a second diameter portion, the second diameter portion having a greater diameter than the first diameter portion. A park brake system may further comprise a spring disposed at least partially around a circumference of the motor shaft, a wire coil disposed at least partially around a circumference of a bobbin, a one-way clutch disposed at least partially within the bobbin and coaxial to the motor shaft, an annular magnet disposed coaxial to the motor shaft and distal to at least a portion of the bobbin, and a clutch release mechanism disposed coaxial to the motor shaft and around the first diameter portion. In response to a first voltage being applied to the wire coil, the one-way clutch may translate axially in a first direction relative to the motor shaft and engage with the second diameter portion; in response to a second voltage applied to the wire coil, the one-way clutch may translate axially in a second direction relative to the motor shaft and engage with the clutch release mechanism.
B60T 13/74 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissanceSystèmes de freins incorporant ces moyens de transmission, p. ex. systèmes de freinage à pression d'air avec entraînement ou assistance électrique
F16D 49/02 - Freins avec un organe de freinage coopérant avec la périphérie d'un tambour, d'une jante de roue ou d'une pièce analogue ayant la forme d'une bande hélicoïdale ou d'une bobine à plusieurs spires, avec ou sans amplification de l'effort de freinage par tension de la bande ou action d'un organe de contraction
F16D 63/00 - Freins non prévus ailleursFreins combinant plusieurs des types mentionnés dans les groupes
F16D 65/16 - Mécanismes d'actionnement pour freinsMoyens pour amorcer l'opération de freinage à une position prédéterminée disposés dans, ou sur le frein
F16D 127/06 - Mécanismes de verrouillage, p. ex. agissant sur des actionneurs, des mécanismes de desserrage ou de transmission de force
56.
SENSOR DATA FUSION FOR PROGNOSTICS AND HEALTH MONITORING
A method includes converting time-series data from a plurality of prognostic and health monitoring (PHM) sensors into frequency domain data. One or more portions of the frequency domain data are labeled as indicative of one or more target modes to form labeled target data. A model including a deep neural network is applied to the labeled target data. A result of applying the model is classified as one or more discretized PHM training indicators associated with the one or more target modes. The one or more discretized PHM training indicators are output.
An assembly for detecting a grid condition according to an exemplary aspect of the present disclosure includes, among other things, a controller that determines an electrical variation of an electrical parameter, the electrical variation relating to a mechanical torque oscillation of a power generation device, and determines that the power generation device should be disconnected from the power grid if the electrical variation meets a preselected criterion. A method of detecting a grid event is also disclosed.
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
58.
MULTI-MODAL SENSOR DATA FUSION FOR PERCEPTION SYSTEMS
A method includes fusing multi-modal sensor data from a plurality of sensors having different modalities. At least one region of interest is detected in the multi-modal sensor data. One or more patches of interest are detected in the multi-modal sensor data based on detecting the at least one region of interest. A model that uses a deep convolutional neural network is applied to the one or more patches of interest. Post-processing of a result of applying the model is performed to produce a post-processing result for the one or more patches of interest. A perception indication of the post-processing result is output.
G06K 9/00 - Méthodes ou dispositions pour la lecture ou la reconnaissance de caractères imprimés ou écrits ou pour la reconnaissance de formes, p.ex. d'empreintes digitales
G06N 3/04 - Architecture, p. ex. topologie d'interconnexion
Heat pump cycle provided with a fluidic loop connecting two heat exchangers. The fluidic loop is filled with an electro-caloric liquid as a heat transfer medium. Applying electric filed in one of the heat exchangers the temperature of the electro-caloric liquid is changed.
An electrolytic capacitor comprising an anode; a cathode; a Kraft paper separator that is either coated with a polymer coating or where some of the hemicellulose and cellulose of the Kraft paper has been removed and replaced by the polymer coating, said polymer having a Tg of less than 160 degrees C, a degradation temperature of greater than 200 degree C and a conductivity of 10 to 1000 Siemens per centimeter at 20 degrees C; and a non-aqueous liquid electrolyte, said electrolyte having a vapor pressure of less than 2 mm at 20 degrees C, a boiling point equal to or greater than 200 degrees C, and a melting point equal to or less than -30 degrees C.
A composite pressure vessel assembly includes a plurality of lobes, each of the lobes having at least one interior wall and at least one curved wall, the plurality of lobes being positioned in a side by side arrangement and extending in a longitudinal direction from a first end to a second end. Also included is a plurality of end caps disposed at the ends of the lobes, wherein the plurality of lobes and end caps are formed of at least one fiber-reinforced polymer. A method of manufacturing a composite pressure vessel assembly is provided. The method includes forming a plurality of lobes consisting of at least one fiber-reinforced polymer. The method also includes forming a main body with the plurality of lobes, the lobes disposed in a side by side arrangement.
F17C 1/14 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en aluminiumRécipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en acier amagnétique
F17C 1/16 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables en matériaux plastiques
A method is disclosed for regenerating an electrode of a flow battery. The method can be executed during shutdown of the flow battery from an active charge/discharge mode to an inactive, shut-down mode in which neither a negative electrolyte nor a positive electrolyte are circulated through at least one cell of the flow battery. The method includes driving voltage of the least one cell of the flow battery toward zero by converting, in-situ, the negative electrolyte in the at least one cell to a higher oxidation state. The negative electrolyte is in contact with an electrode of the at least one cell. The higher oxidation state negative electrolyte is used to regenerate, in-situ, catalytically active surfaces of the electrode of the at least one cell.
A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.
F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines
B29C 45/00 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet
64.
Rear bearing sleeve for gas turbine auxiliary power unit
The presently disclosed embodiments utilize a rear bearing sleeve interposed between an inner surface of an exhaust housing of a gas turbine auxiliary power unit and the rear roller bearing supporting a turbine within the exhaust housing. In some embodiments, the rear bearing sleeve includes a lubricant supply channel formed in an outer surface thereof for receipt of a supply of lubricant, and at least one lubricant supply opening between the outer surface and an inner surface thereof, the inner surface of the bearing sleeve forming an outer race of the rear roller bearing. The at least one lubricant supply opening supplies the lubricant to a gap between the rear roller bearing and the rear bearing sleeve for formation of a squeeze film viscous damper therebetween.
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
F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
F16C 33/66 - Pièces ou détails particuliers pour la lubrification
F16C 27/04 - Roulements à billes ou à rouleaux, p. ex. à organes de roulement élastiques
F16C 19/26 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec roulements à rouleaux essentiellement du même gabarit, disposés dans une ou plusieurs rangées circulaires, p. ex. roulements à aiguilles pour charges radiales principalement avec une seule rangée de rouleaux
F16C 35/077 - Leur fixation sur l'arbre ou dans la carcasse d'enveloppe avec interposition d'un organe entre la carcasse d'enveloppe et la bague extérieure de roulement
An article with controllable wettability includes a substrate and a layer of a composite material supported on the substrate. The layer has an exposed surface and the composite material includes particles that have controllable polarization embedded fully or partially in a matrix. A controller is operable to selectively apply a controlled variable activation energy to the layer. The controllable polarization of the particles varies responsive to the controlled variable activation energy such that a wettability of the exposed surface also varies responsive to the controlled variable activation energy.
B01J 19/08 - Procédés utilisant l'application directe de l'énergie ondulatoire ou électrique, ou un rayonnement particulaireAppareils à cet usage
B05D 7/00 - Procédés, autres que le flocage, spécialement adaptés pour appliquer des liquides ou d'autres matériaux fluides, à des surfaces particulières, ou pour appliquer des liquides ou d'autres matériaux fluides particuliers
B82B 1/00 - Nanostructures formées par manipulation d’atomes ou de molécules, ou d’ensembles limités d’atomes ou de molécules un à un comme des unités individuelles
B82Y 30/00 - Nanotechnologie pour matériaux ou science des surfaces, p. ex. nanocomposites
The presently disclosed embodiments utilize flow from a higher-energy portion of flow within the impeller flow path and inject it into the lower-energy portion of the flow path to re-energize the flow, delaying the onset of, or minimizing, large (and inefficient, entropy-generating) re-circulation zones in the flow field. By making a spanwise cut along the chord length of the splitter blade (variable blade clearance from leading edge to trailing edge), additional secondary flow occurs within the flow passages as the higher pressure flow on the pressure side of the blade can now spill over into the low-pressure suction side of the blade.
F04D 29/66 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage
F04D 29/22 - Rotors spécialement pour les pompes centrifuges
F04D 29/28 - Rotors spécialement adaptés aux fluides compressibles pour pompes centrifuges ou hélicocentrifuges
F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
F01D 5/02 - Organes de support des aubes, p. ex. rotors
An example auxiliary power unit bracket includes, among other things, a gearbox mounting face and a compartment mounting face, the gearbox mounting face configured to attach to an auxiliary power unit gearbox below a sump level line, the compartment mounting face configured to attach to a portion of an auxiliary power unit compartment above the sump level line.
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F16M 13/02 - Autres supports ou appuis pour positionner les appareils ou les objetsMoyens pour maintenir en position les appareils ou objets tenus à la main pour être portés par un autre objet ou lui être fixé, p. ex. à un arbre, une grille, un châssis de fenêtre, une bicyclette
F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02K 1/34 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet utilisant des jets de fluide pour influencer l'écoulement du jet pour atténuer le bruit
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
The present disclosure is applicable to all gear trains using a journal bearing as a means of supporting gear shaft rotation. It is related in some embodiments to a system and method for supplying lubricant to the journal bearings of a gear-turbofan engine gear train when the fan rotor is subjected to a wind-milling condition in both directions, either clockwise or counter-clockwise.
F01D 25/20 - Systèmes de lubrification utilisant des pompes de 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
F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
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
F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
F01D 5/02 - Organes de support des aubes, p. ex. rotors
F01D 15/08 - Adaptations pour la commande des pompes ou combinaisons avec celles-ci
F01D 15/12 - Combinaisons avec des transmissions mécaniques
F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
F04C 2/344 - Machines ou pompes à piston rotatif possédant les caractéristiques couvertes par au moins deux des groupes , , , ou par l'un de ces groupes en combinaison avec un autre type de mouvement entre les organes coopérants avec à la fois le mouvement défini dans l'un des groupes ou et un mouvement alternatif relatif entre les organes coopérants les organes obturateurs ayant un mouvement alternatif par rapport à l'organe interne
F04C 13/00 - Adaptations des "machines" ou pompes pour utilisation particulière, p. ex. pour très hautes compressions
F04C 15/00 - Parties constitutives, détails ou accessoires des "machines", des pompes ou installations de pompage non couverts par les groupes
A drainage assembly (68) includes a first segment (70A) with a first inner tube (76A) defining a first inner tube passage (78A), a first outer tube (72A) concentrically disposed around the first inner tube (76A) and defining a first outer tube passage (74A), and a first fitting (80A) disposed on an end of the first segment (70A). The first fitting (80A) has a first inner passage (82A) in fluid communication with the first inner tube passage (78A) and a first outer passage (84A) in fluid communication with the first outer tube passage (74A). A plate (88) is positioned adjacent the first fitting (80A). The plate (88) has a second inner passage (90) in fluid communication with the first inner passage (82A) on one side, and a second outer passage (92) in fluid communication with the first outer passage (84A) on the one side. Also included is a drainage line (104) in fluid communication with the first outer tube passage (74A).
F16L 55/07 - Aménagement ou montage de dispositifs, p. ex. soupapes, pour ventiler ou aérer ou purger
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F02C 7/22 - Systèmes d'alimentation en combustible
71.
SYNTHESIS OF ALLOY AND DIFFUSION MATERIAL NANOPARTICLES
A method for preparing an alloy nanocellular foam includes at least partially coating a nanocellular precursor into a multiple composition nanoparticle precursor and converting the multiple composition nanoparticle precursor into an alloy via a diffusion process.
According to one aspect of the present invention, a preloaded hybrid duplex bearing assembly is disclosed. A hybrid duplex ball bearing assembly includes a forward bearing, an aft bearing, and a preload spring, the preload spring disposed adjacent the aft bearing and configured to apply an axial force to push the aft bearing toward the forward bearing, where the forward bearing and aft bearing share an inner race. The forward bearing and the aft bearing are angular contact bearings each including a contact angle, and the contact angles of the forward bearing and the aft bearing converge at a point within the bearing assembly. In one embodiment, the aft bearing is not radially loaded and carries only the axial force of the preload spring. In at least one embodiment, the forward bearing forms a radial clearance fit with the aft bearing such that the aft bearing carries no radial load.
F16C 19/18 - 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 à la fois radiales et axiales avec plusieurs rangées de billes
F16C 19/50 - Autres types de roulements à billes ou à rouleaux
F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
F16C 33/66 - Pièces ou détails particuliers pour la lubrification
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
A blade outer air seal according to an exemplary aspect of the present disclosure includes, among other things, a body to be distributed circumferentially about a blade array. The body has a plurality of grooves, which can, for example, improve the aerodynamic efficiency of a turbine. A fin is between a first groove and a second groove of the plurality of grooves. The fin extends radially from the body and terminates at a radially inner fin face that provides one or more cooling outlets.
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
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view.
An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction
Embodiments are directed to obtaining a specification comprising at least one requirement associated with a heating, ventilation, and air-conditioning (HVAC) system, and based on the specification, configuring a control system to control a movement of fluid back and forth across at least one regenerator device of the HVAC system and a mixing of the fluid with ambient air.
A gas turbine engine component comprises an airfoil with a suction side and pressure side extending from a leading edge to a trailing edge. There are a plurality of cooling holes adjacent the leading edge, with the cooling holes having a non-circular shape, with a longer dimension and a smaller dimension. The airfoil defines a radial direction from a radially outer end to a radially inner end, and radially outer of the cooling holes spaced toward the radially outer end, which have the longer dimension extending closer to parallel to the radial direction. Radially inner cooling holes closer to the radially inner end having the longer dimension extend to be closer to perpendicular relative to the radial direction compared to the radially outer cooling holes.
A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides.
Embodiments are directed to obtaining a specification comprising at least one requirement associated with a heating, ventilation, and air-conditioning (HVAC) system, and based on the specification, configuring a control system to control a movement of fluid back and forth across at least one regenerator device of the HVAC system and a mixing of the fluid with ambient air.
A septum-tied tube pack is provided that includes a first outer wall formed by a multiple of first connected radiuses. A second outer wall is formed by a multiple of second connected radiuses. A first end radius connects the first outer wall and the second outer wall. A second end radius connects the first outer wall and the second outer wall. A multiple of septum elements extend between the first outer wall and the second outer wall. A gas turbine engine is also provided that includes an engine case structure and a fluid conduit mounted to the engine case structure. The fluid conduit includes a septum-tied tube pack section.
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
F02C 7/27 - Entraînement du rotor pour le démarrage par fluide
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
An auxiliary power unit mounting system according to an exemplary aspect of the present disclosure includes, among other things, a plurality of linkages to support an auxiliary power unit, and a redundant mount to selectively support said auxiliary power unit.
A gas turbine engine component comprises a body extending between two ends and having at least two cooling passages. The body has a first wall and second wall. At least two cooling passages include a first passage that is closer to the first wall than is a second of the passages at upstream locations along a flow path. The second passage has upstream locations that are closer to the second wall than are upstream portions of the first passage. The first and second passages cross along a length of the flow path such that downstream portions of the second passage are closer to the first wall than are downstream portions of the first passage, and downstream portions of the first passage are closer to the second wall than are downstream portions of the second passage.
An illustrative example container includes a plurality of internal support members having a surface contour that at least approximates a minimum surface. The plurality of internal support members collectively provide structural support for carrying loads on the container. The plurality of internal support members collectively establish a plurality of cavities for at least temporarily containing fluid. An outer shell is connected with at least some of the internal support members. The outer shell includes a plurality of curved surfaces. The outer shell encloses the cavities.
B32B 3/12 - Produits stratifiés comprenant une couche ayant des discontinuités ou des rugosités externes ou internes, ou une couche de forme non planeProduits stratifiés comprenant une couche ayant des particularités au niveau de sa forme caractérisés par une couche discontinue, c.-à-d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p. ex. structures en nids d'abeilles
Embodiments are direc- ted to a heat pump element comprising: a thin-film polymer or ceramic material within a range of 0.1 microns - 100 mi- crons thickness, and electrodes coupled to both sides of the thin-film material to form an electroded active thin-film ma- terial, wherein the thin-film material is separated by, and in intimate contact with, a heat transfer fluid in channels within a range of 10 microns - 10 milli- meters thickness, in which the fluid is capable of being translated back and forth through the element by an im- posed pressure field.
F25B 9/14 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé caractérisés par le cycle utilisé, p. ex. cycle de Stirling
93.
SYSTEMS FOR THERMOELECTRIC COOLING FOR JET AIRCRAFT PROPULSION SYSTEMS
An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using the temperature difference of the TEC array. The system may include a controller configured to control an input power provided to each TEC of the array of TECs, such that the array of TECs facilitates controlled cooling of the aircraft jet propulsion system in response to the input power provided to each TEC of the array of TECs. The TEC array may be powered by an alternator or by a thermoelectric generator.
F25B 21/02 - Machines, installations ou systèmes utilisant des effets électriques ou magnétiques utilisant l'effet PeltierMachines, installations ou systèmes utilisant des effets électriques ou magnétiques utilisant l'effet Nernst-Ettinghausen
A mid-turbine frame for use in a gas turbine engine comprises at least one vane extending between a vane inner platform and a vane outer platform, and an inner case radially inward of the inner platform. A plurality of tie rods extend from a platform radially inward of the inner case to a radially outer location which is secured by a mount member. The tie rods are secured in the inner case by a forward bolt, and at least one rear bolt, with the forward bolt extending along an axis which is non-parallel to a center axis of the inner case. A gas turbine engine and a method for assembling a mid-turbine frame are also disclosed.
A gas turbine engine includes a fan shaft and a support which supports at least a portion of the fan shaft. The support defines at least one of a support transverse and a support lateral stiffness. A gear system drives the fan shaft. A flexible support at least partially supports the gear system, and defines at least one of a flexible support transverse and a flexible support lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. An input to the gear system defines at least one of an input transverse and an input lateral stiffness with respect to at least one of the support transverse and the support lateral stiffness. A method of designing a gas turbine engine is also disclosed.
A mid-turbine frame (MTF") for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ("HPT") and a low pressure turbine ("LPT"), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.
A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis. An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.
G01N 24/08 - Recherche ou analyse des matériaux par l'utilisation de la résonance magnétique nucléaire, de la résonance paramagnétique électronique ou d'autres effets de spin en utilisant la résonance magnétique nucléaire
A gas turbine engine includes a conduit that is configured to direct a fluid to at least one manifold that is adjacent to a turbine section. A first intake is in fluid communication with the conduit. A second intake is in fluid communication with the conduit. A valve is configured to selectively direct a fluid from at least one of the first intake and the second intake.
In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
An airfoil assembly has at least one cooling hole in an aft edge of at least one platform for cooling at least one of an axially downstream airfoil root and/or tip region. The airfoil assembly may be a high pressure turbine first stage vane coupled with a combustor operating at a low Pattern Factor.
