Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• G01J 5/14 - Leurs particularités électriques
• 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
• G01J 5/04 - Boîtiers

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

A system is provided with a controller configured to receive a computer model of a mold configured to cast a part. The computer model has a variable wall thickness of the mold thermally tailored to a geometry of the part. The controller is configured to control a manufacturing system to produce the mold based on the computer model.

Classes IPC  ?

• B22C 9/06 - Moules permanents pour pièces coulées
• B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
• B28B 17/00 - FAÇONNAGE DE L'ARGILE OU D'AUTRES COMPOSITIONS CÉRAMIQUES; FAÇONNAGE DE SCORIES; FAÇONNAGE DE MÉLANGES CONTENANT DES SUBSTANCES ANALOGUES AU CIMENT, p.ex. DU PLÂTRE - Parties constitutives ou accessoires de l'appareillage à façonner le matériau; Mesures auxiliaires prises en liaison avec un tel façonnage
• B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive

Abrégé

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.

Classes IPC  ?

• A61G 10/00 - Locaux de traitement à usage médical
• 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

Abrégé

An approach for facilitating mechanical and electrical connection of electric machines and electrical components in an electrical system using connectors with quick connect/disconnect electrical connectors is disclosed. Each quick connect/disconnect electrical connector can be placed on the end of an electrical power distribution cable that connects with an electric machine or electrical component. The electric machines and electrical components and the electrical power distribution cables can have hollow coolant passages formed therein to receive cooling fluid from a cooling device for direct cooling of the electric machines, electrical components and the electrical power distribution cables.

Classes IPC  ?

• H01R 24/28 - Pièces de couplage portant des broches, des lames ou des contacts analogues, assujetties uniquement à un fil ou un câble
• H01R 13/00 - CONNEXIONS CONDUCTRICES DE L'ÉLECTRICITÉ; ASSOCIATION STRUCTURELLE DE PLUSIEURS ÉLÉMENTS DE CONNEXION ÉLECTRIQUE ISOLÉS LES UNS DES AUTRES; DISPOSITIFS DE COUPLAGE; COLLECTEURS DE COURANT - Détails de dispositifs de couplage des types couverts par les groupes  ou
• H01R 13/05 - Fiches ou lames élastiques
• H01R 13/11 - Alvéoles élastiques
• H01R 13/52 - Boîtiers protégés contre la poussière, les projections, les éclaboussures, l'eau ou les flammes
• H01R 24/20 - Pièces de couplage portant des douilles, des pinces ou des contacts analogues, assujetties uniquement à un fil ou un câble
• H01R 24/66 - Dispositifs de couplage en deux pièces, ou l'une des pièces qui coopèrent dans ces dispositifs, caractérisés par leur structure générale avec des broches, des lames ou des contacts analogues, assujettis à l'appareil ou à la structure, p.ex. à une paroi
• H01R 24/76 - Dispositifs de couplage en deux pièces, ou l'une des pièces qui coopèrent dans ces dispositifs, caractérisés par leur structure générale avec des broches, des pinces ou des contacts analogues, assujettis à l'appareil ou à la structure, p.ex. à une paroi
• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs

Abrégé

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.

Classes IPC  ?

• 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 

Abrégé

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.

Classes IPC  ?

• 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 2/26 - Post-traitement
• 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 4/06 - Matériaux métalliques
• C23C 4/10 - Oxydes, borures, carbures, nitrures ou siliciures; Leurs mélanges
• C23C 4/18 - Post-traitement
• C23C 14/08 - Oxydes
• 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

Abrégé

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.

Classes IPC  ?

• A61N 7/02 - Hyperthermie localisée par ultrasons

Abrégé

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.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 7/06 - Aménagement des paliers; Lubrification

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.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p.ex. rotors
• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/24 - Isolation thermique ou acoustique
• 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

Abrégé

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.

Classes IPC  ?

• A61N 7/00 - Thérapie par ultrasons

Abrégé

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.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
• F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/50 - Chambres de combustion comprenant un tube à flamme annulaire à l'intérieur d'une enveloppe annulaire
• F23R 3/60 - Structures de support; Moyens de fixation ou de montage

Abrégé

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.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 7/06 - Aménagement des paliers; Lubrification

Abrégé

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.

Classes IPC  ?

• 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 43/14 - Diodes électroluminescentes [LED]
• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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).

Classes IPC  ?

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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• C23C 4/134 - Pulvérisation plasma
• C23C 4/11 - Oxydes

Abrégé

pump) to pressurize the working fluid, and wherein p_water is the density and specific heat capacity of water, respectively.

Classes IPC  ?

• F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail

Abrégé

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.

Classes IPC  ?

• H04L 9/08 - Répartition de clés

Abrégé

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.

Classes IPC  ?

• B01D 19/00 - Dégazage de liquides

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air
• F01D 25/12 - Refroidissement

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• B29C 64/245 - Plates-formes ou substrats
• B29C 64/232 - Moyens d’entraînement pour un mouvement le long de l'axe orthogonal au plan d’une couche
• B29C 64/236 - Moyens d’entraînement pour un mouvement dans une direction dans le plan d’une couche
• B29C 64/264 - Agencements pour irradiation

Abrégé

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.

Classes IPC  ?

• H02K 1/02 - MACHINES DYNAMO-ÉLECTRIQUES - Détails du circuit magnétique caractérisés par le matériau magnétique
• C22C 38/00 - Alliages ferreux, p.ex. aciers alliés
• H01F 1/147 - Alliages caractérisés par leur composition

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliers; Lubrification
• F01D 25/18 - Systèmes de lubrification

Abrégé

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.

Classes IPC  ?

• F02C 7/24 - Isolation thermique ou acoustique
• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16D 1/10 - Accouplements à action rapide dans lesquels les pièces sont simplement présentées dans l'axe

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/60 - Structures de support; Moyens de fixation ou de montage

Abrégé

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.

Classes IPC  ?

• 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
• B29C 64/245 - Plates-formes ou substrats
• B29C 64/357 - Recyclage
• B29C 64/386 - Acquisition ou traitement de données pour la fabrication additive
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
• B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau
• B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

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

Abrégé

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.

Classes IPC  ?

• B22F 3/15 - Compression isostatique à chaud
• B22F 1/054 - Particules de taille nanométrique
• B22F 3/12 - Compactage et frittage

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p.ex. rotors
• F01D 5/14 - Forme ou structure

Abrégé

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.

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• 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
• H02G 5/10 - Réfrigération
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines

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.

Classes IPC  ?

• F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail
• F01D 25/12 - Refroidissement
• F02C 7/16 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F16L 55/18 - Accessoires de réparation des tuyaux
• F16L 55/32 - Moyens de propulsion autonomes portés par le hérisson ou le chariot

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/12 - Refroidissement des ensembles fonctionnels

Abrégé

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.

Classes IPC  ?

• F02C 9/26 - Commande de l'alimentation en combustible

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F01D 5/02 - Organes de support des aubes, p.ex. rotors
• F01D 25/34 - Vireur ou dispositif de rotation par mouvements saccadés

Abrégé

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.

Classes IPC  ?

• H04B 10/70 - Communications quantiques photoniques
• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F01D 25/12 - Refroidissement
• F01D 25/14 - Carcasses d'enveloppe modifiées à cet effet

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• B22D 27/04 - Action sur la température du métal, p.ex. par chauffage ou refroidissement du moule

Abrégé

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.

Classes IPC  ?

• 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
• B22F 12/49 - Appareils de balayage
• B22F 12/67 - Lames
• B22F 12/70 - Moyens d’écoulement des gaz
• B23K 15/00 - Soudage ou découpage par faisceau d'électrons
• B23K 26/082 - Systèmes de balayage, c. à d. des dispositifs comportant un mouvement relatif entre le faisceau laser et la tête du laser
• B23K 26/342 - Soudage de rechargement
• 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
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
• B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau
• B33Y 40/20 - Posttraitement, p.ex. durcissement, revêtement ou polissage
• C23C 16/04 - Revêtement de parties déterminées de la surface, p.ex. au moyen de masques
• C23C 16/52 - Commande ou régulation du processus de dépôt

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

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.

Classes IPC  ?

• B64F 1/36 - Autres installations pour aérodromes
• 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
• G06T 7/00 - Analyse d'image

Abrégé

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.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p.ex. l'air

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.

Classes IPC  ?

• 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

Abrégé

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.

Classes IPC  ?

• 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

Abrégé

A gas control system including a positive pressure vessel, a negative pressure vessel, a first pressure control valve configured to control a flow of gas to and from a first manifold of a printhead assembly, and a second pressure control valve configured to control a flow of gas to and from a second manifold of the printhead assembly. During a normal positive pressure mode, gas flows from the positive pressure vessel to the first manifold and the second manifold through a respective one of the first pressure control valve and the second pressure control valve. During a positive pressure purge mode, gas from the positive pressure vessel bypasses the first pressure control valve and the second pressure control valve to flow to the first manifold and the second manifold.

Classes IPC  ?

• B29C 64/35 - Nettoyage
• B08B 9/032 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau
• B08B 9/035 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau par aspiration
• B29C 64/209 - Têtes; Buses
• B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
• B33Y 40/00 - Opérations ou équipements auxiliaires, p.ex. pour la manipulation de matériau

Abrégé

A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.

Classes IPC  ?

• B64D 15/04 - Dégivrage ou antigivre des surfaces externes des aéronefs par gaz chaud ou liquide amené par conduit par amenée de gaz chaud
• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
• B64D 37/02 - Réservoirs
• B64D 37/30 - Circuits de carburant pour carburants particuliers
• F02C 7/22 - Systèmes d'alimentation en combustible

Abrégé

A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p.ex. rotors

Abrégé

An apparatus and method for an inspection apparatus for inspecting a component. The inspection apparatus including a robotic arm. A micro-XRF instrument having an instrument head coupled to the robotic arm. A seat supporting the component within a scanning area during inspection; and a computer in communication with the robotic arm and the micro-XRF instrument.

Classes IPC  ?

• G01N 23/223 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en mesurant l'émission secondaire de matériaux en irradiant l'échantillon avec des rayons X ou des rayons gamma et en mesurant la fluorescence X
• G01N 35/00 - Analyse automatique non limitée à des procédés ou à des matériaux spécifiés dans un seul des groupes ; Manipulation de matériaux à cet effet

Abrégé

An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.

Classes IPC  ?

• F02K 1/48 - Tuyères ondulées
• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues

Abrégé

A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells each extending between an inlet end and an outlet end. Each fuel cell of the plurality of fuel cells includes an air channel and a fuel channel each fluidly coupled to the combustion chamber.

Classes IPC  ?

• H01M 8/2484 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible - Détails des groupements d'éléments à combustible caractérisés par les collecteurs d’admission externes
• F02C 7/22 - Systèmes d'alimentation en combustible
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• H01M 8/2425 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible avec électrolytes solides ou supportés par une matrice Éléments à haute température avec électrolytes solides

Abrégé

A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.

Classes IPC  ?

• F23R 3/16 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la configuration du flux d'air ou du flux de gaz avec des dispositifs à l'intérieur du tube à flamme ou de la chambre de combustion pour influer sur le flux d'air ou de gaz
• 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
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Produits et services

Business consulting, management, and planning services in the field of intellectual property and intellectual property licensing; business management and organization consultancy; new business venture development and formation consulting services. Venture capital advisory services; venture capital financing; venture capital services, namely, providing financing to emerging and start-up companies. Innovation consulting services, namely, advising others in the areas of intellectual property, technology transfer, product, market and business development. Consultancy relating to the management of intellectual property; consulting in the field of intellectual property licensing; intellectual property consultancy; licensing of intellectual property.

Abrégé

A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotor; Pieds de pales
• F01D 5/22 - Connections aube à aube, p.ex. par emboîtement

Abrégé

Active clearance control valves and related methods are disclosed. An example apparatus includes a pipe defining a flow path between (i) at least one of a fan section, a bypass airflow passage, or a compressor section and (ii) a turbine section of the gas turbine, the pipe including an inlet fluidly coupled to at least one of the fan section, the bypass airflow passage, or the compressor section, a valve coupled to the pipe and positioned downstream of the inlet, the valve including swing wings, the swing wings positioned around an opening in the pipe defined by the second valve when the second valve is at least partially open.

Classes IPC  ?

• F01D 11/20 - Réglage actif du jeu d'extrémité des aubes

Abrégé

A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

Classes IPC  ?

• F01D 5/18 - Aubes creuses; Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F02C 7/12 - Refroidissement des ensembles fonctionnels

Abrégé

A power generation system for an aircraft includes a first power source, a second power source, and a power dispatch module communicatively coupled with the first and second power sources. The power dispatch module includes a controller having one or more processors configured to perform a plurality of operations, including but not limited to receiving a plurality of loading data associated with the power generation system, predicting a future power demand due to future load changes using the loading data, determining first and second power setpoints for the first and second power sources, respectively, based on the future power demand due to the future load changes, and controlling first and second power outputs of the first and second power sources based on the first and second power setpoints such that the future power demand of the power generation system is shared by the first and second power sources.

Classes IPC  ?

• H02J 3/00 - Circuits pour réseaux principaux ou de distribution, à courant alternatif
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts

Abrégé

A method of producing a computer-generated image of a component part includes receiving scan data of the component part. The scan data includes a plurality of slices that change direction about a normal vector. The method further includes registering the scan data of the component part and transforming the scan data of the component part into a set of slices arranged in an x-y plane. Further, the method includes aligning the set of slices aligned along the axis along an axis in the x-y plane. In addition, the method includes adjusting the set of slices aligned along the axis using a background model for the component part, the scan data, or both. Thus, the method includes applying a directional filter to the set of slices aligned along the axis and generating the computer-generated image of the component part using the filtered set of slices aligned along the axis.

Classes IPC  ?

• G06T 15/08 - Rendu de volume
• G06T 7/00 - Analyse d'image

Abrégé

A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to: ( D ⁢ 1 eq ⁢ min D ⁢ 2 eq ⁢ min ) ⁢ ( R D ⁢ 2 eq ⁢ min ) .

Classes IPC  ?

• B22C 9/10 - Noyaux; Fabrication ou mise en place des noyaux

Abrégé

Methods, apparatus, systems, and articles of manufacture are disclosed. An example apparatus includes a tubular or cylindrical body including a shaft, a shoulder, and a neck, the shaft coupled to the shoulder, the shoulder coupled to the neck, the shoulder having a greater diameter than respective diameters of the shaft and the neck. The example apparatus includes a plug coupled to the shoulder at a first plug edge and coupled to a first fastener at a second plug edge, the first fastener including a hole. The example apparatus includes a second fastener coupled to the first fastener, the second fastener extending through the tubular body, the plug, and the first fastener.

Classes IPC  ?

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

Abrégé

Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.

Classes IPC  ?

• B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
• B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé l'air étant réchauffé ou refroidi

Abrégé

A gas turbine engine including: a turbomachine having 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 rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.

Classes IPC  ?

• B64C 11/32 - Mécanismes de changement de pas des pales mécaniques
• B64C 11/06 - Montage des pales dans le cas de pales à pas variable

Abrégé

The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.

Classes IPC  ?

• B22D 25/02 - Coulée particulière caractérisée par la nature du produit d'œuvres d'art
• B22C 1/22 - Compositions des matériaux réfractaires pour moules ou noyaux; Leur structure granulaire; Caractéristiques chimiques ou physiques de la mise en forme ou de la fabrication des moules caractérisées par l'emploi des agents liants; Mélange d'agents liants d'agents organiques de résines naturelles ou synthétiques
• B22C 9/02 - Moules en sable ou moules analogues pour pièces coulées
• B22C 9/10 - Noyaux; Fabrication ou mise en place des noyaux
• B22C 9/12 - Traitement des moules ou noyaux, p.ex. séchage, étuvage
• B22C 9/24 - Moules pour pièces de forme particulière pour pièces évidées
• B22C 13/08 - Machines à mouler pour faire des moules ou noyaux de forme particulière pour moules ou noyaux en coquilles
• B22C 13/12 - Machines à mouler pour faire des moules ou noyaux de forme particulière pour 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
• B22D 29/00 - Extraction des pièces hors du moule, non limitée à un procédé de coulée couvert par un seul groupe principal; Extraction des noyaux; Manipulation des lingots
• B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
• 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
• B29C 64/129 - 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 caractérisés par la source d'énergie à cet effet, p.ex. par irradiation globale combinée avec un masque
• B29C 64/135 - 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 caractérisés par la source d'énergie à cet effet, p.ex. par irradiation globale combinée avec un masque la source d’énergie étant concentrée, p.ex. lasers à balayage ou sources lumineuses focalisées
• F01D 5/12 - Aubes
• F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
• G03F 7/00 - Production par voie photomécanique, p.ex. photolithographique, de surfaces texturées, p.ex. surfaces imprimées; Matériaux à cet effet, p.ex. comportant des photoréserves; Appareillages spécialement adaptés à cet effet
• G03F 7/20 - Exposition; Appareillages à cet effet

Abrégé

A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includes one or more engine loads and an external electrical connection for communicating electrical power between the turbine engine and an electrical system of an aircraft. The turbine engine includes a power management system including a high voltage DC busbar configured to communicate electrical power between the first and second electric machines and the engine loads and the external electrical connection. The power management system includes a control system configured to control power offtake from and injection to the first and second electric machines, and controls power delivered to the one or more engine loads and the external electrical connection.

Classes IPC  ?

• F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique

Abrégé

The invention relates to a HVDC transformer configuration (10, 50) for use in electrical power transmission to at least a 1stAC network and a 2ndAC network, the configuration comprising: - a 3 single phase HVDC transformer, in which each phase comprises a first winding (2, 12, 22) connected to a HVDC converter (s) and a second winding (4, 14, 24) connected to both said 1stAC network and said 2ndAC network; - wherein the second winding (4, 14, 24) of each phase is configured as auto- transformer and comprises a tap connection (6, 16, 26), said tap connection being connected to a Phase Shifting Transformer (30) to regulate the power transmission to said 2nd AC network.

Classes IPC  ?

• H02J 3/18 - Dispositions pour réglage, élimination ou compensation de puissance réactive dans les réseaux
• H02J 3/36 - Dispositions pour le transfert de puissance électrique entre réseaux à courant alternatif par l'intermédiaire de haute tension à courant continu
• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs

Abrégé

A generator includes a non‑rotatable component supporting a field winding assembly and a rotatable component oriented to rotate relative to the non‑rotatable component during operation of the generator. Further, the generator includes an armature winding assembly fixedly coupled to the rotatable component so as to rotate therewith during the operation of the generator. The armature winding assembly includes a plurality of conducting coils. The generator further includes a thermal shield surrounding the field winding assembly fixedly coupled to the stationary component, a cryocooler in thermal contact with the thermal shield, and a gas tank adjacent to and in thermal contact with the thermal shield, the gas tank containing a cooling gas configured to circulate therein so as to provide uniform cooling to the thermal shield.

Classes IPC  ?

• H02K 55/04 - Machines dynamo-électriques comportant des enroulements qui fonctionnent à des températures cryogéniques du type synchrone avec des enroulements à champ tournant

Abrégé

An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.

Classes IPC  ?

• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• B64D 31/00 - Commande des groupes moteurs; Leur disposition
• B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
• B64D 47/00 - Equipements non prévus ailleurs
• 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

Abrégé

Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Classes IPC  ?

• B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
• H02P 29/032 - Prévention d’un endommagement du moteur, p.ex. détermination de limites individuelles de courant pour différentes conditions de fonctionnement