Abrégé

Methods and apparatus to control a surface of an aircraft engine are disclosed. An example system to control a surface in an aircraft engine comprises a first valve to vary a flow of cold fluid from a thermal transfer bus (TTB) to an active surface control (ASC) system based on an operating condition of the aircraft engine, the ASC system positioned adjacent to the surface, the first valve positioned upstream from the surface, and a second valve to vary a flow of hot fluid from the TTB to the ASC system based on the operating condition, the second valve positioned downstream from the surface.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor

Classes IPC  ?

• B64D 27/33 - Aéronefs électriques hybrides
• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion

Abrégé

Methods and apparatus to produce hydrogen gas turbine propulsion are disclosed. An example method includes activating at least one heat exchanger operatively coupled to a fuel line, injecting hydrogen into the fuel line to distribute heat from the at least one heat exchanger in the fuel line, and in response to a temperature of the fuel line being greater than a liquification temperature of an inert gas: injecting the inert gas into the fuel line, terminating injecting the hydrogen into the fuel line, and capturing the inert gas in the fuel line.

Classes IPC  ?

• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
• F02C 3/22 - 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 le combustible ou l'oxydant étant gazeux aux température et pression normales
• 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

Abrégé

A gas turbine engine including a connection assembly. The connection assembly includes a first component of the gas turbine engine defining a first flange. The first component has a first coefficient of thermal expansion. A second component of the gas turbine engine defines a second flange. The second component has a second coefficient of thermal expansion. An adapter includes an adapter body, a first rabbet, and a second rabbet. The adapter may be positioned between the first component and the second component. The adapter has a third coefficient of thermal expansion. The first coefficient of thermal expansion may be greater than the third coefficient of thermal expansion and the third coefficient of thermal expansion may be greater than the second coefficient of thermal expansion.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V GB . A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: V G V GB . VG is a gutter volume of the gutter and VGB is a gearbox volume.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.

Classes IPC  ?

• B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
• B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques
• H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
• H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux
• H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
• H01M 8/04694 - Procédés de commande des éléments à combustible ou des systèmes d’éléments à combustible caractérisés par les variables à commander
• H01M 8/04746 - PressionDébit
• H01M 8/10 - Éléments à combustible avec électrolytes solides

Abrégé

A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.

Classes IPC  ?

• H01M 8/04746 - PressionDébit
• H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur

Abrégé

A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.

Classes IPC  ?

• B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
• B64D 27/33 - Aéronefs électriques hybrides
• F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
• H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
• H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
• H01M 8/04746 - PressionDébit
• H01M 8/10 - Éléments à combustible avec électrolytes solides

Abrégé

An aircraft can comprise an engine, an environmental control system, an engine controller, and a plurality of sensors detecting engine or aircraft parameters. Engine or aircraft operation can be updated in real time based on input from the sensors, including airflow management or operation parameters.

Classes IPC  ?

• 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
• 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
• F04D 27/02 - Contrôle de l'emballement

Abrégé

A propulsion system for an aircraft includes a fan section having a fan; a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order; at least one electric machine; a fuel cell assembly configured to supply power to the electric machine; and a controller including a memory and one or more processors. One or both of the turbomachine and the at least one electric machine are configured to drive rotation of the fan of the fan section. The fuel cell assembly includes at least one fuel cell, a first fluid inlet for receiving a flow of pressurized air, and a second fluid inlet for receiving a flow of fuel.

Classes IPC  ?

• B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
• B64D 27/33 - Aéronefs électriques hybrides
• F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
• F02C 9/16 - Commande du débit du fluide de travail
• H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
• H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
• H01M 8/04313 - Procédés de commande des éléments à combustible ou des systèmes d’éléments à combustible caractérisés par la détection ou l'évaluation des variablesProcédés de commande des éléments à combustible ou des systèmes d’éléments à combustible caractérisés par la détection ou l'évaluation de la défaillance ou d'une fonction anormale
• H01M 8/04746 - PressionDébit
• H01M 8/10 - Éléments à combustible avec électrolytes solides
• H01M 8/2484 - Détails des groupements d'éléments à combustible caractérisés par les collecteurs d’admission externes

Abrégé

A turbofan engine for an aircraft includes a fan and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan blades are rotatable about a pitch axis. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range from 8.5 to 24 and given by A turbofan engine for an aircraft includes a fan and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan blades are rotatable about a pitch axis. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range from 8.5 to 24 and given by N FB × D FT L AXIAL × ( R TB N FB ) . A turbofan engine for an aircraft includes a fan and a fan actuation system. The fan has a plurality of fan blades coupled to a fan shaft having one or more fan bearings. The fan blades are rotatable about a pitch axis. The fan actuation system is disposed within a fan hub and includes one or more actuators for rotating the fan blades about the pitch axis and one or more radial thrust bearings. The fan actuation system is characterized by a fan actuation system length envelope in a range from 8.5 to 24 and given by N FB × D FT L AXIAL × ( R TB N FB ) . NFB is a number of the fan blades, DFT is a fan tip diameter of the fan blades, RTB is a thrust bearing radius of the radial thrust bearings, and LAXIAL is an axial length from a fan hub tip to the fan bearings.

Classes IPC  ?

• B64D 35/02 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques
• F02C 7/06 - Aménagement des paliersLubrification
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 1/46 - Systèmes consistant en plusieurs trains d'engrenages, chacun comportant des engrenages orbitaux
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A gearbox assembly includes a planet gear including an outer surface and an inner surface opposite the outer surface. A pair of circumferential oil channels are formed in the inner surface proximate opposite ends of the planet gear. A distributor channel is formed to extend in a longitudinal direction toward a center of the planet gear from each circumferential oil channel. One or more tooth channels are formed to extend from each distributor channel to the outer surface of the planet gear. A journal pin is received within the planet gear extending along an axis about which the planet gear rotates. A gap defines a journal bearing formed between the inner surface of the planet gear and the journal pin. An oil passage is provided supplying oil to the gap.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F04D 29/063 - Lubrification spécialement adaptée aux pompes pour fluides compressibles

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 paliersLubrification

Abrégé

A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a compressor, the turbine section having one or more turbines. The turbomachine includes one or more additively manufactured metal components, and a total mass of the one or more additively manufactured metal components is in a range from 1% to 50% of a total dry mass of the gas turbine engine.

Classes IPC  ?

• 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
• B33Y 80/00 - Produits obtenus par fabrication additive

Abrégé

Heat exchange systems with fluid intake control and associated methods are disclosed. An example system includes a conduit to carry a first fluid, a heat exchanger operatively coupled to the conduit, the heat exchanger to cause the first fluid to exchange thermal energy with a second fluid, a fan positioned in a portion of the conduit to drive the first fluid past the fan, wherein the fan is electrically driven, and a valve coupled to the conduit, wherein the first fluid flows through the portion of the conduit when the valve is in a first position, and wherein the valve blocks the first fluid from flowing through the portion of the conduit when the valve is in a second position.

Classes IPC  ?

• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion

Abrégé

A pitch lock system including an outer member having a centerline axis, an inner member located radially inward of the outer member with respect to the centerline axis, and a plurality of clutch elements located between the outer member and the inner member. The pitch lock system has a disengaged position and an engaged position. In the engaged position, the plurality of clutch elements are constrained between the inner member and the outer member such that relative axial direction of the plurality of clutch elements is permitted in only one direction. An engine includes a pitch actuator and the pitch lock system.

Classes IPC  ?

• F01D 7/00 - Rotors à aubes réglables en marcheLeur commande
• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques
• B64C 11/40 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques automatiques
• F15B 15/02 - Schéma mécanique de montage caractérisé par les moyens transformant le mouvement de l'élément entraîné par le fluide en mouvement de l'organe terminal qui est actionné

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.

Classes IPC  ?

• F16H 57/025 - Support des boîtes de vitesses, p. ex. bras de couple, ou attachement à d'autres dispositifs
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/023 - Montage ou installation d'engrenages ou d'arbres dans les boîtes de vitesses, p. ex. procédés ou moyens d'assemblage

Abrégé

A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a strain energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The strain energy storage system includes a spring drivingly coupled to the auxiliary pump shaft. The spring stores strain energy during normal operation of the turbine engine and releases the strain energy when the propulsor is windmilling to rotate the auxiliary pump shaft to power the auxiliary pump such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

Fuel thermal management systems and related methods are disclosed. An example system includes a flowline to carry a fluid, a waste heat recovery heat exchanger coupled to the flowline, the waste heat recovery heat exchanger to heat the fluid to a first temperature, and a feed tank coupled to the flowline, the feed tank including a first inlet and a second inlet, the first inlet to receive a first portion of the fluid from the waste heat recovery heat exchanger at the first temperature, the second inlet to receive a second portion of the fluid at a second temperature less than the first temperature, wherein the first portion of the fluid and the second portion of the fluid mixes in the feed tank to form a third portion having a third temperature between the first temperature and the second temperature.

Classes IPC  ?

• F02C 6/18 - Utilisation de la chaleur perdue dans les ensembles fonctionnels de turbines à gaz à l'extérieur des ensembles eux-mêmes, p. ex. ensembles fonctionnels de chauffage à turbine à gaz

Abrégé

Fuel thermal management systems and related methods are disclosed. An example system includes a flowline to carry a fluid, a waste heat recovery heat exchanger coupled to the flowline, the waste heat recovery heat exchanger to heat the fluid to a first temperature, and a feed tank coupled to the flowline, the feed tank including a first inlet and a second inlet, the first inlet to receive a first portion of the fluid from the waste heat recovery heat exchanger at the first temperature, the second inlet to receive a second portion of the fluid at a second temperature less than the first temperature, wherein the first portion of the fluid and the second portion of the fluid mixes in the feed tank to form a third portion having a third temperature between the first temperature and the second temperature.

Classes IPC  ?

• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• F02C 3/22 - 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 le combustible ou l'oxydant étant gazeux aux température et pression normales
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible

Abrégé

A power turbine blade for a gas turbine engine includes at least one of a third-stage blade, a fourth-stage blade, or a fifth-stage blade. The power turbine blade includes a platform and an airfoil that extends in a spanwise direction from the platform to a tip shroud. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction

Abrégé

Methods and apparatus are disclosed for a heat source for a hydrogen fuel supply system of a turbine engine. An example apparatus includes a heat source configured to burn gaseous hydrogen to produce heat energy and a byproduct of combustion, a pipeline to transport gaseous hydrogen from a hydrogen supply to the heat source, a vent coupled to the heat source to vent excess gaseous hydrogen and the byproduct of combustion, and a heat exchanger coupled to the heat source to use the heat energy of the heat source to heat liquid hydrogen in the pipeline.

Classes IPC  ?

• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• F02C 3/22 - 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 le combustible ou l'oxydant étant gazeux aux température et pression normales
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by V G V GB . A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by V G V GB . VG is a gutter volume of the gutter and VGB is a gearbox volume of the gearbox. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a tank that stores a lubricant therein, one or more lubricant pumps for generating a flow of lubricant from the tank to the gearbox assembly, and a flow rate control valve. The flow rate control valve has a flow inlet and a flow outlet and defines a variable throughput from the flow inlet to the flow outlet for controlling a flowrate of the lubricant to the gearbox assembly.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000). In some instances, a gas turbine engine also comprises a gearbox efficiency rating and/or an overall efficiency rating.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• 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 mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/025 - Support des boîtes de vitesses, p. ex. bras de couple, ou attachement à d'autres dispositifs
• H02M 1/00 - Détails d'appareils pour transformation
• H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
• H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif

Abrégé

A gas generator turbine blade for a gas turbine engine includes a platform and an airfoil. The airfoil extends in a spanwise direction from the platform to a tip. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

A fuel system for a gas turbine engine including a compressor section, a combustion section, and a turbine section includes a fuel tank for storing a fuel, a plurality of heat exchangers downstream of the fuel tank, and a valve downstream of the plurality of heat exchangers. The valve includes a fuel inlet in fluid communication with the plurality of heat exchangers, a first fuel outlet in fluid communication with a first fluid pathway, and a second fuel outlet in fluid communication with a second fluid pathway. The fuel system includes a fuel cell including an anode inlet and an anode outlet. The anode inlet is in fluid communication with the first fluid pathway. The fuel system also includes a combustion chamber of the combustion section in fluid communication with the second fluid pathway and the anode outlet of the fuel cell and a controller communicatively coupled to the valve.

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
• B64D 37/34 - Conditionnement du carburant, p. ex. réchauffage
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur

Abrégé

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output arranged in a planet configuration. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 25/18 - Systèmes de lubrification

Abrégé

Pressure regulation valves are disclosed. An example pressure regulation valve includes a valve housing, and a control body positioned in the valve housing. The control body is movable between a first position and a second position based on (a) a first pressure differential between a first variable-pressure location and a second variable-pressure location and (b) a second pressure differential between the second variable-pressure location and a control volume of the valve housing. The control body when in the first position fluidly couples the first variable-pressure location to the control volume. The control body when in the second position restricts fluid flow between the first variable-pressure location and the control volume.

Classes IPC  ?

• F16K 11/07 - Soupapes ou clapets à voies multiples, p. ex. clapets mélangeursRaccords de tuyauteries comportant de tels clapets ou soupapesAménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des tiroirs à éléments de fermeture glissant linéairement à glissières cylindriques
• F01D 11/20 - Réglage actif du jeu d'extrémité des aubes

Abrégé

An engine system for an aircraft includes a first turbofan engine and a second turbofan engine. The first turbofan engine includes a first low-pressure shaft, a first fan having a first fan shaft, and a counterclockwise gearbox assembly. The first fan shaft is drivingly coupled to the first low-pressure shaft through the counterclockwise gearbox assembly. The first low-pressure shaft rotates in a counterclockwise direction. The first fan shaft rotates in the counterclockwise direction such that the first fan rotates in the counterclockwise direction. The second turbofan engine includes a second low-pressure shaft, a second fan having a second fan shaft, and a clockwise gearbox assembly. The second fan shaft is drivingly coupled to the second low-pressure shaft through the clockwise gearbox assembly. The second low-pressure shaft rotates in the counterclockwise direction. The second fan shaft rotates in a clockwise direction such that the second fan rotates in the clockwise direction.

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

Abrégé

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T O ⁢ U ⁢ T A D ⁢ T ⁢ E ⁢ x ⁢ i ⁢ t ) 2 * EGT A HPCExit * 10 - 11 ; A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T O ⁢ U ⁢ T A D ⁢ T ⁢ E ⁢ x ⁢ i ⁢ t ) 2 * EGT A HPCExit * 10 - 11 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

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

Abrégé

Heat exchangers for cryogenic fuel distribution systems and related methods are disclosed herein. An example aircraft disclosed herein includes a cryogenic fuel system including a cryogenic fuel, a hydraulic system including a hydraulic fluid, a gas turbine engine fluidly coupled to the cryogenic fuel system, and a heat exchanger fluidly coupled to the cryogenic fuel system, the heat exchanger to exchange heat between the cryogenic fuel and at least one of (1) the hydraulic fluid or (2) a working fluid thermally coupled to the hydraulic system.

Classes IPC  ?

• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 3/22 - 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 le combustible ou l'oxydant étant gazeux aux température et pression normales
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage

Abrégé

Disclosed herein is an integrated in-line emergency lube pump assembly for a planetary gearbox, including a main lube pump, a coaxial lube pump coaxially aligned with and coupled to the planetary gearbox, and an oil tank having a main section and an auxiliary section. There is no physical boundary between the main section and the auxiliary section of the oil tank. When the detected pressure in the oil supply line is equal to or exceeds a predetermined pressure threshold, the main lube pump operates to causes the main pump to pump oil from the main section of the oil tank to the planetary gearbox. Alternatively, when the detected pressure in the oil supply line is less than the predetermined pressure threshold the main lube pump ceases operation to cause the coaxial lube pump to draw oil from the auxiliary section of the oil tank to the planetary gearbox.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A turbine engine includes a fan section including a fan, a fan shaft coupled to the fan, a turbine section including an input shaft, and a planetary gear assembly coupled to the input shaft and the fan shaft. The turbine engine further includes a lubricant transfer unit having a reservoir that has a body, a plurality of sectors angularly positioned about a circumference of the body, a plurality of dams positioned between and defining each of the plurality of sectors, at least one orifice that fluidly couples the plurality of sectors to the planetary gear assembly, and at least one opening to evacuate excess lubricant from each of the plurality of sectors. The reservoir is mounted on the fan shaft of the turbine engine, and the excess lubricant drained from the at least one opening of each of the plurality of sectors lubricates the fan shaft.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• 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

An oil bearing includes a static frame and a rotating bearing that is rotatable in a rotational direction and coaxial with the static frame. The static frame includes a frame wall defining a frame lumen extending in a longitudinal direction therethrough and a plurality of frame oil channels extending through the wall. Each of the plurality of frame oil channels is arranged at a first angle relative to a radial direction, wherein the first angle is between 45 degrees and 90 degrees.

Classes IPC  ?

• F16C 33/10 - Structures relatives à la lubrification

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.

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

Abrégé

A gear assembly for use with a turbomachine comprises a sun gear, a plurality of planet gears, and a ring gear. The gear assembly is connected to an input shaft and an output shaft. The sun gear is configured to rotate about a longitudinal centerline of the gear assembly, and is driven by the input shaft. A component of the gear assembly drives the output shaft. The gear assembly further comprises an output shaft reversal mechanism configured to reverse the rotational direction of the output shaft.

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

Abrégé

Systems, apparatus, articles of manufacture, and methods are disclosed to build and/or modify components. An additive manufacturing apparatus comprising: at least one memory; machine-readable instructions; and processor circuitry to execute machine-readable instructions to: deposit a first layer of material, the first layer of material at a first temperature; compress the first layer of material to form a first compressed layer; deposit a second layer of material, the second layer of material at a second temperature, the first compressed layer to include a first crystalline structure; compress the second layer of material into the first layer of material to form a second compressed layer; deposit a third layer of material, the third layer of material at a third temperature, the second compressed layer to include the first crystalline structure; and compress the third layer of material into the second compressed layer to form a third compressed layer.

Classes IPC  ?

• B22F 12/63 - Rouleaux
• B22F 10/28 - Fusion sur lit de poudre, p. ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
• B23K 26/342 - Soudage de rechargement
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additiveLeurs parties constitutives ou accessoires à cet effet

Abrégé

Methods and apparatus to control a surface of an aircraft engine are disclosed. An example system to control a surface in an aircraft engine comprises a first valve to vary a flow of cold fluid from a thermal transfer bus (TTB) to an active surface control (ASC) system based on an operating condition of the aircraft engine, the ASC system positioned adjacent to the surface, the first valve positioned upstream from the surface, and a second valve to vary a flow of hot fluid from the TTB to the ASC system based on the operating condition, the second valve positioned downstream from the surface.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor

Abrégé

A turbine engine including a turbo-engine, a gearbox assembly, a propulsor, and a lubrication system. The turbo-engine includes a compressor section, a combustor, a turbine section, and an input shaft. The gearbox assembly includes a first gear, a plurality of second gears, and a third gear. The propulsor has an output shaft drivingly coupled to the input shaft through the gear assembly. The lubrication system is characterized by a Gearbox Lubrication System Parameter (GLSP) between 0.2 and 140 when a mass flow rate of the lubricant is linear with a lubricant pump speed, where the GLSP is given by: The GLSP is between 0.2 and 70 when the mass flow rate of the lubricant is modulated, where the GLSP is given by: .

Classes IPC  ?

• F01D 25/18 - Systèmes de lubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance

Abrégé

A turbine engine having a turbo-engine coupled to an input shaft, a fan coupled to an output shaft, and a gearbox assembly. A torque is transferrable from the input shaft to the output shaft through the gearbox assembly. The gearbox assembly has a split sun gear rotationally coupled to the input shaft, a plurality of planet gears located radially outward of, and intermeshing with, the split sun gear, and a single piece ring gear located radially outward of, and intermeshing with, the plurality of planet gears. The split sun gear includes a forward sun gear and an aft sun gear separate from the forward sun gear, and the forward sun gear and the aft sun gear are each rotationally coupled to the input shaft.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by V G V GB . A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by V G V GB . VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

Systems, apparatus, articles of manufacture, and methods are disclosed that include a fuel distribution system for an engine, the fuel distribution system comprising: a first pump downstream of a fuel tank; a first motor coupled to the first pump; a second pump downstream of the first pump; a second motor coupled to the second pump; a third pump downstream of the second pump, the third pump having an inlet and an outlet; a bypass pathway from the outlet of the third pump to the inlet of the third pump; and a recirculation valve, the recirculation valve in line with the bypass pathway.

Classes IPC  ?

• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
• F02C 7/236 - Systèmes d'alimentation en combustible comprenant au moins deux pompes
• F17C 7/04 - Vidage des gaz liquéfiés avec changement d'état, p. ex. vaporisation

Abrégé

A method of forming a coated component is provided. The method may include forming a bondcoat on a surface of a substrate; thereafter, performing a first heat treatment on the bondcoat on the surface of the substrate; thereafter, forming a barrier coating on the bondcoat; and performing a second heat treatment on the barrier coating on the bondcoat to form the coated component. The bondcoat may comprise MCrAlX where M is Ni, Co, or a combination thereof and where X is Hf, Y, Zr, or combinations thereof.

Classes IPC  ?

• C23C 4/073 - Matériaux métalliques contenant des alliages MCrAl ou MCrAlY où M est le nickel, le cobalt ou le fer, avec ou sans éléments non métalliques
• B23K 1/00 - Brasage ou débrasage
• C23C 4/129 - Pulvérisation à la flamme
• C23C 4/134 - Pulvérisation plasma
• C23C 4/137 - Pulvérisation sous vide ou sous atmosphère inerte
• C23C 4/18 - Post-traitement

Abrégé

A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: GB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F16N 7/38 - Installations à huile ou autre lubrifiant non spécifié, à réservoir ou autre source portés par la machine ou l'organe machine à lubrifier avec pompe séparéeInstallations centralisées de lubrification

Abrégé

A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by GB is a gearbox volume. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a sump that is a primary reservoir having a first lubricant level and a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level. The lubrication system fills the secondary reservoir with a lubricant between the first lubricant level and the second lubricant level. The gear assembly collects the lubricant in the secondary reservoir to supply the lubricant to the gear assembly.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

A Directed Energy Deposition (DED) system may include a nozzle that deposits metallic powder onto a plurality of locations of a repair area. A first energy source is configured to output a first energy beam from a first output end, which is positionable by one or more actuators to direct the first energy beam onto the repair area at a first angle or a second angle relative to a cavity axis to melt deposits of the metallic powder that are located at a first set of the plurality of locations or a second set of the plurality of locations.

Classes IPC  ?

• B22F 12/46 - Moyens de rayonnement avec mouvement de translation
• B22F 10/25 - Dépôt direct de particules métalliques, p. ex. dépôt direct de métal [DMD] ou mise en forme par laser [LENS]
• B22F 12/13 - Moyens de chauffage auxiliaires pour préchauffer le matériau
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 30/00 - Appareils pour la fabrication additiveLeurs parties constitutives ou accessoires à cet effet
• B33Y 40/10 - Prétraitement

Abrégé

A gas turbine engine includes a turbomachine comprising compressor, combustion, and turbine sections. The gas turbine engine defines a maximum exhaust gas temperature, a maximum drive turbine shaft torque, and a corrected specific power. The gas turbine engine includes a controller configured to autonomously regulate performance of the gas turbine engine in response to at least one of: a thrust demand, an energy efficiency target, or a flight profile condition.

Classes IPC  ?

• F02C 6/06 - 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
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gearbox assembly including a gear assembly, an input shaft, an output shaft, and a gear brake system. The input shaft is coupled to the gear assembly. The output shaft is drivingly coupled to the input shaft through the gear assembly. The gear brake system is disposed within the gear assembly, and includes one or more brake devices. The gear brake system actuates the one or more brake devices to brake the gear assembly during a reverse torque condition of the gearbox assembly.

Classes IPC  ?

• F16H 57/10 - Dispositions propres au freinage
• F16D 51/14 - Freins avec organes de freinage se déplaçant vers l'extérieur coopérant avec la surface intérieure d'un tambour ou d'une pièce analogue ayant la forme de sabots de freins exclusivement mobiles radialement actionnés par fluide
• F16D 59/00 - Freins automatiques, p. ex. entrant en action à une vitesse prédéterminée
• 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 55/34 - Freins à un seul disque tournant actionnés par un dispositif à pression de fluide disposé dans, ou sur le frein comportant un organe flexible, expansible, rempli de fluide, coaxial avec le frein
• F16D 121/02 - Pression de fluide
• F16H 35/00 - Transmissions ou mécanismes ayant d'autres caractéristiques de fonctionnement particulières

Abrégé

A gas turbine engine has a turbomachine comprising compressor, combustion, and turbine sections. The gas turbine engine defines a maximum exhaust gas temperature, a maximum drive turbine shaft torque, and a corrected specific power. The gas turbine engine includes a nozzle vane and an engine casing defining a fluid supply plenum. The engine casing is configured to route cooling fluid from the fluid supply plenum to the nozzle vane. The routing of the cooling fluid facilitates cooling of the nozzle vane and increases an overall pressure ratio of the gas turbine engine. Integration of the cooling fluid routing within the engine casing reduces parasitic bleed air losses, enables tighter turbine stage spacing, and improves the thermal efficiency of the engine, thereby enhancing performance at elevated pressure ratios.

Classes IPC  ?

• F02C 6/06 - 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
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

• F02C 6/06 - 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
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; A gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 ⁢ 0 - 1 ⁢ 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

• F02C 6/06 - 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
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gearbox assembly for a turbine engine. The turbine engine includes an engine static structure. The gearbox assembly includes a gear assembly, an input shaft coupled to the gear assembly, an output shaft drivingly coupled to the input shaft through the gear assembly, and a gearbox assembly disengagement system. The gearbox assembly disengagement system includes a one-way clutch that engages the gearbox assembly to the engine static structure during a normal operation of the turbine engine and disengages the gearbox assembly from the engine static structure during a reverse torque condition.

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

Abrégé

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 3/067 - 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
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/025 - Support des boîtes de vitesses, p. ex. bras de couple, ou attachement à d'autres dispositifs
• H02M 1/00 - Détails d'appareils pour transformation
• H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
• H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif

Abrégé

OUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: 2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

• F02C 6/06 - 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
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A hybrid electric turboprop includes a propeller, a thermal engine, an electric motor, a gearbox, and an air inlet. The propeller is configured to rotate about a propeller axis and includes a plurality of blades extending radially outwardly from the propeller axis such that, as the propeller is rotated about the propeller axis, the plurality of blades define a substantially circular blade path area centered about the propeller axis and having a radius. The gearbox couples both the thermal engine and the electric motor to the propeller to enable each of the thermal engine and the electric motor to drive rotation of the propeller about the propeller axis. The air inlet defines an opening. A radial distance is defined from the propeller axis to a location within the opening. The radial distance is equal to or less than 60% of the radius.

Classes IPC  ?

• B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
• B64D 27/33 - Aéronefs électriques hybrides

Abrégé

OUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: 2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

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

Abrégé

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: FnTotal×EGT/(AHPCExit2×1000). In some instances, a gas turbine engine also comprises a gearbox efficiency rating and/or an overall efficiency rating.

Classes IPC  ?

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

Flow-metering fuel systems and related methods are disclosed. An example method includes determining a first flow rate of fuel in a first section of a fuel pipe, in response to the first flow rate satisfying a first flow rate threshold: determining whether the first flow rate satisfies a second flow rate threshold, in response to the first flow rate not satisfying the second flow rate threshold, adjusting the first flow rate. In response to the first flow rate satisfying the second flow rate threshold: in response to the first flow rate satisfying a third flow rate threshold, maintaining the first flow rate, and in response to the first flow rate not satisfying the third flow rate threshold, adjusting the first flow rate. In response to the first flow rate not satisfying the first flow rate threshold, adjusting the first flow rate.

Classes IPC  ?

• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor

Abrégé

An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• B64D 27/33 - Aéronefs électriques hybrides
• B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
• F02C 7/22 - Systèmes d'alimentation en combustible

Abrégé

Apparatus and associated methods to classify and adjust builds across additive manufacturing machine(s) are disclosed. An example apparatus includes learner circuitry to: process first data from a set of first builds to learn behavior; classify each build as a standard or non-standard build; model the learned behavior to form a standard reference behavior and a non-standard reference behavior, the standard reference behavior including first features and the non-standard reference behavior including second features; and output the standard reference behavior and the non-standard reference behavior to classify additional builds. The apparatus includes evaluator circuitry to: ingest second data for a second build; process the second data in comparison to the standard reference behavior and the non-standard reference behavior; classify the second build as a standard build or a non-standard build; and, when the second build is classified as a non-standard build, output a corrective action.

Classes IPC  ?

• B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
• B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive

Abrégé

A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3. The lubricant extraction volume ratio defined by: A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3. The lubricant extraction volume ratio defined by: V G V GB . V G A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3. The lubricant extraction volume ratio defined by: V G V GB . V G is a gutter volume of the gutter and VGB is a gearbox volume. The gas turbine engine includes a lubrication system that includes a lubricant tank that stores lubricant, one or more primary gearbox lubricant supply lines, one or more secondary gearbox lubricant supply lines, and a lubricant pump for supplying the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines and the secondary gearbox lubricant supply lines. The lubrication system modulates a mass flow rate of the lubricant to the gearbox assembly through the primary gearbox lubricant supply lines or the secondary gearbox lubricant supply lines.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F02C 7/06 - Aménagement des paliersLubrification
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by V G V G ⁢ B . A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3 that is defined by V G V G ⁢ B . VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly, a fan, a combustor that generates combustion gases, a turbine, a nacelle that surrounds the fan, and a steam system. The combustor and the turbine define a core air flowpath. Core air flows through the core air flowpath. The steam system that extracts water from the combustion gases, vaporizes the water to generate steam, and injects the steam into the core air flowpath to add mass flow to the core air. A bypass ratio of the gas turbine engine is in a range of 18:1 to 100:1.

Classes IPC  ?

• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
• F02K 1/38 - Introduction d'air à l'intérieur du jet

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by GB is a gearbox volume of the gearbox. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a tank that stores a lubricant therein, one or more lubricant pumps for generating a flow of lubricant from the tank to the gearbox assembly, and a flow rate control valve. The flow rate control valve has a flow inlet and a flow outlet and defines a variable throughput from the flow inlet to the flow outlet for controlling a flowrate of the lubricant to the gearbox assembly.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: VG/VGB. VG is a gutter volume of the gutter and VGB is a gearbox volume. A gas turbine engine includes the gearbox assembly. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

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 paliersLubrification
• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by GB is a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A lubrication system for a turbine engine. The turbine engine includes a propulsor and rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a kinetic energy storage system. The sump stores lubricant. The primary lubrication system supplies the lubricant from the sump to the rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump. The kinetic energy storage system includes a rotating lubricant accumulator. The auxiliary pump pumps the lubricant from the sump to the rotating lubricant accumulator to at least partially fill the rotating lubricant accumulator with the lubricant during the normal operation of the turbine engine to store kinetic energy. The rotating lubricant accumulator releases the kinetic energy when the propulsor is windmilling to supply the lubricant from the rotating lubricant accumulator to the rotating components.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F15B 1/04 - Accumulateurs

Abrégé

A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a kinetic energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The kinetic energy storage system includes a flywheel that engages the auxiliary pump shaft to power the auxiliary pump when the propulsor is windmilling such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a strain energy storage system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump including an auxiliary pump shaft. The strain energy storage system includes a spring drivingly coupled to the auxiliary pump shaft. The spring stores strain energy during normal operation of the turbine engine and releases the strain energy when the propulsor is windmilling to rotate the auxiliary pump shaft to power the auxiliary pump such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification

Abrégé

A lubrication system for a turbine engine. The turbine engine includes a propulsor and one or more rotating components. The lubrication system includes a sump, a primary lubrication system, an auxiliary lubrication system, and a fuel system. The sump stores lubricant therein. The primary lubrication system supplies the lubricant from the sump to the one or more rotating components during normal operation of the turbine engine. The auxiliary lubrication system includes an auxiliary pump. The fuel system stores hydrogen fuel. The fuel system includes a fuel cell controller that generates electricity from the hydrogen fuel. The electricity powers the auxiliary pump when the propulsor is windmilling such that the auxiliary pump pumps the lubricant from the sump to the one or more rotating components.

Classes IPC  ?

• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: GB is a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F02C 7/06 - Aménagement des paliersLubrification
• F16N 7/38 - Installations à huile ou autre lubrifiant non spécifié, à réservoir ou autre source portés par la machine ou l'organe machine à lubrifier avec pompe séparéeInstallations centralisées de lubrification

Abrégé

A gas turbine engine includes a fan, a combustor positioned in a core air flowpath that generates combustion gases, a steam system that extracts water from the combustion gases and generates steam, and a gearbox assembly. The steam system includes water storage devices that store the water therein. The water storage devices include a first state in which a level of the water increases or is maintained and a second state in which the level of the water decreases as the water flows through the water storage devices. The gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: GB is a gearbox volume.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 25/18 - Systèmes de lubrification
• F02C 7/06 - Aménagement des paliersLubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

OUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: 2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 6/06 - 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

Abrégé

A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by GB is a gearbox volume. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a sump that is a primary reservoir having a first lubricant level and a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level. The lubrication system fills the secondary reservoir with a lubricant between the first lubricant level and the second lubricant level. The gear assembly collects the lubricant in the secondary reservoir to supply the lubricant to the gear assembly.

Classes IPC  ?

• F02C 7/06 - Aménagement des paliersLubrification
• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

A gas turbine engine includes a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox, a grounded structure coupled to and supporting the power gearbox, and a torque monitoring system. The torque monitoring system includes a gearbox sensor. The gearbox sensor is coupled to the grounded structure and the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor.

Classes IPC  ?

• F02C 9/58 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance avec la commande d'une hélice à pas variable
• 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 gearbox assembly (200) includes a planet carrier (210), a planet gear (206) disposed within the planet carrier, one or more roller bearings (244) disposed within the planet gear, the one or more roller bearings including a plurality of rolling elements (245), and an integral pin (240) disposed within the planet carrier and extending through the planet gear. The integral pin includes one or more pin shoulders (272) extending from the integral pin. The plurality of rolling elements are disposed axially between the one or more pin shoulders and radially between the integral pin and the planet gear. The one or more pin shoulders axially constrain the plurality of rolling elements. The planet gear rotates about the one or more roller bearings with respect to the integral pin.

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 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators
• F02C 7/06 - Aménagement des paliersLubrification
• 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

Systems and method are provided for predicting an expected mechanical property, such as fatigue strength, for a component with a cellular structure or a portion thereof. In some embodiments, a method for predicting fatigue strength includes receiving, by a control circuit, image data for a specimen to reconstruct 3D models of the specimen. The specimen includes at least one cell of a cellular structure. The method further includes determining a local stresses for the specimen via finite element analysis of the three-dimensional models. The control circuit may then determine a fatigue strength for the specimen based on the local stresses to generate a distribution function of the fatigue strength for the at least one cell of the cellular structure. The control circuit then applies statistics of extremes to the distribution function to predict an expected fatigue strength of a number of cells in the cellular structure.

Classes IPC  ?

• G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
• B29C 64/386 - Acquisition ou traitement de données pour la fabrication additive
• B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• G06T 7/00 - Analyse d'image
• G06T 15/08 - Rendu de volume

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.

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

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.

Classes IPC  ?

• F16H 57/025 - Support des boîtes de vitesses, p. ex. bras de couple, ou attachement à d'autres dispositifs
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/023 - Montage ou installation d'engrenages ou d'arbres dans les boîtes de vitesses, p. ex. procédés ou moyens d'assemblage

Abrégé

A build table assembly for supporting a component, the build table assembly including a base having an upper surface, a frame extending from the upper surface of the base, the frame defining an upper wall; a rim formed on the upper wall of the frame, and a plurality of fixture segments positioned on the rim opposite the upper wall of the frame, the plurality of fixture segments defining an arcuate build surface on which the component is built, the plurality of fixture segments spaced apart from one another.

Classes IPC  ?

• B29C 64/245 - Plates-formes ou substrats
• B22F 12/30 - Plate-formes ou substrats
• B29C 64/236 - Moyens d’entraînement pour un mouvement dans une direction dans le plan d’une couche
• B29C 64/241 - Moyens d’entraînement pour mouvement rotatif
• B33Y 30/00 - Appareils pour la fabrication additiveLeurs parties constitutives ou accessoires à cet effet

Abrégé

A hybrid electric aircraft equipped with gyroscopic stabilization control is provided. In one aspect, a hybrid electric aircraft includes a turbo-generator having a gas turbine engine and an electric generator operatively coupled thereto for generating electrical power. The turbo-generator defines a rotation axis. The aircraft also includes one or more electrically-driven propulsors for producing thrust for the aircraft. In addition, the aircraft includes a pivot mount operatively coupled with the turbo-generator. To provide gyroscopic stabilization control of the aircraft, the pivot mount is controlled to adjust the rotation axis of the turbo-generator relative to a prime stability axis of the aircraft. Additionally or alternatively, a rotational speed of the turbo-generator can be changed to provide gyroscopic stabilization control of the aircraft.

Classes IPC  ?

• B64C 17/06 - Stabilisation des aéronefs non prévue ailleurs par gravité ou par appareil actionné par inertie par appareil gyroscopique
• B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 27/14 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur des fuselages ou fixés à ceux-ci
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• B64D 31/02 - Dispositifs amorçant la mise en œuvre

Abrégé

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur
• F16H 57/025 - Support des boîtes de vitesses, p. ex. bras de couple, ou attachement à d'autres dispositifs
• H02M 1/00 - Détails d'appareils pour transformation
• H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
• H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif

Abrégé

A lubrication system for a gear assembly. The gear assembly includes a first gear and a second gear. The first gear and the second gear mesh with each other at a mesh. The lubrication system includes one or more lubricant injectors. The one or more lubricant injectors include one or more first lubricant outlets directed to the mesh. The one or more first lubricant outlets supply a first portion of lubricant to the mesh. The one or more lubricant injectors include one or more second lubricant outlets directed to a location that is different than the mesh. The one or more second lubricant outlets supply a second portion of lubricant to the location different than the mesh.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement

Abrégé

Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.

Classes IPC  ?

• B64C 11/40 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques automatiques
• B64C 11/30 - Mécanismes de changement de pas des pales
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques
• B64C 11/44 - Mécanismes de changement de pas des pales électriques

Abrégé

Methods, apparatus, systems, and articles of manufacture are disclosed to control propeller pitch in dual acting propellers. An example propeller control system comprising: a piston including a piston rod; a first valve connected to the piston rod via a first piston line and a second piston line, wherein the first valve selectively allows, based on an input signal, hydraulic fluid to transfer to the piston via the first piston line and the second piston line, wherein in the first valve is a three-state valve; and an independent valve connected to the piston rod via a third piston line, wherein the independent valve selectively allows, based on an input signal, hydraulic fluid to transfer to the piston via the third piston line and wherein the independent valve operates independently of the first valve.

Classes IPC  ?

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

Abrégé

A gas turbine engine includes a fan section, an engine inlet, and a fan duct splitter in serial flow order. The fan duct splitter splits an airflow entering the engine inlet from the fan section into a fan duct and a core duct. The core duct includes a compressor section, a combustion section, and a turbine section in serial flow order. A duct assembly is coupled to the fan duct to extract a portion of a fan duct airflow passing through the fan duct and deliver the portion of the fan duct airflow to an active clearance control mechanism of the turbine section.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor
• F01D 11/20 - Réglage actif du jeu d'extrémité des aubes

Abrégé

A turbine engine with a turbine core that includes a compressor section having a compressor, a combustion section, a turbine section having a high pressure turbine and a low pressure turbine, and a nozzle section. A high speed shaft couples the high pressure turbine to the compressor. A first gearbox selectively coupling an output of an electric machine and the high speed shaft. A second gearbox couples an input/output of the electric machine and a low speed shaft, where the low speed shaft is coupled to the low pressure turbine.

Classes IPC  ?

• F01D 15/12 - Combinaisons avec des transmissions mécaniques

Abrégé

A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.

Classes IPC  ?

• F16H 55/08 - Profilage
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur

Abrégé

rt2 is a second stage root radius of the second stage planet gear.

Classes IPC  ?

• F16H 1/28 - Transmissions à engrenages pour transmettre un mouvement rotatif avec engrenages à mouvement orbital
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F16H 57/08 - Parties constitutives générales des transmissions des transmissions à organes à mouvement orbital
• F16H 57/02 - Boîtes de vitessesMontage de la transmission à l'intérieur

Abrégé

A gearbox assembly includes a plurality of planet gears secured by a planet carrier. The plurality of planet gears and the planet carrier rotate about a longitudinal centerline axis. A planet pin is disposed in each planet gear. One or more journal bearings are defined by the planet pin and the planet gear, each planet gear rotating about the one or more journal bearings. The gearbox assembly includes an auxiliary lubrication system that stores lubricant therein. The auxiliary lubrication system includes one or more lubricant lines that provide fluid communication between the auxiliary lubrication system and the one or more journal bearings. Rotation of the planet carrier and the one or more journal bearings generates a suction effect that causes the lubricant in the auxiliary lubrication system to flow to the one or more journal bearings during windmilling conditions and during zero gravity conditions or negative gravity conditions.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• 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

OUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows: 2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 6/06 - 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

Abrégé

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 3/067 - 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
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant

Abrégé

An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

Aerodynamically mistuned airfoils for unsteady loss reductions are disclosed herein. An example apparatus disclosed herein includes a disk, a first airfoil coupled to the disk, the first airfoil having a first geometry, and a second airfoil coupled to the disk adjacent to the first airfoil, the second airfoil having a second geometry different than the first geometry, the first airfoil and the second airfoil produce non-uniform wake passing times during operation of the disk.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 2.0-4.0.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F02C 3/067 - 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
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant

Abrégé

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, and a gearbox. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed. A gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0.

Classes IPC  ?

• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
• F01D 25/18 - Systèmes de lubrification

Abrégé

A pitch lock system including an outer member having a centerline axis, an inner member located radially inward of the outer member with respect to the centerline axis, and a plurality of clutch elements located between the outer member and the inner member. The pitch lock system has a disengaged position and an engaged position. In the engaged position, the plurality of clutch elements are constrained between the inner member and the outer member such that relative axial direction of the plurality of clutch elements is permitted in only one direction. An engine includes a pitch actuator and the pitch lock system.

Classes IPC  ?

• F01D 7/00 - Rotors à aubes réglables en marcheLeur commande
• B64C 11/06 - Montage des pales dans le cas de pales à pas variable
• B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques
• B64C 11/40 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques automatiques
• F15B 15/02 - Schéma mécanique de montage caractérisé par les moyens transformant le mouvement de l'élément entraîné par le fluide en mouvement de l'organe terminal qui est actionné

Abrégé

An oil delivery system includes a first oil delivery circuit having a first oil distribution line delivering oil to at least one first circuit component part, a first oil pump, and a first switch valve, and a second oil delivery circuit having a second oil distribution line delivering oil to at least one second circuit component part, a second oil pump, and a second switch valve. The first switch valve controls a flow of oil through the first oil delivery circuit based on a difference between a first oil pressure of the first oil delivery circuit and a second oil pressure of the second oil delivery circuit. The second switch valve controls a flow of oil through the second oil delivery circuit based on a difference between the second oil pressure of the second oil delivery circuit and the first oil pressure of the first oil delivery circuit.

Classes IPC  ?

• F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
• F02C 7/06 - Aménagement des paliersLubrification
• F16N 7/40 - Installations à huile ou autre lubrifiant non spécifié, à réservoir ou autre source portés par la machine ou l'organe machine à lubrifier avec pompe séparéeInstallations centralisées de lubrification à circuit fermé
• F16N 25/00 - Dispositifs de distribution

Abrégé

p is a planet gear pocket diameter of the plurality of planet gear pockets, L is a planet gear pocket length of the plurality of planet gear pockets, D is a planet carrier diameter of the planet carrier, and aw is a pin center distance from a longitudinal axis of the planet carrier to an axis of the pin.

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