Systems and methods for measuring an axial position of a phonic wheel or other rotating component are provided. The system includes a phonic wheel rotatable about a rotation axis and translatable along the rotation axis, a first sensor, a second sensor and a computer. The phonic wheel includes an inclined tooth having an axially non-uniform radial height and a reference tooth having an axially uniform radial height. The first sensor generates a positioning signal indicative of a gap between the inclined tooth and the first sensor. The second sensor generates a reference signal indicative of a gap between the reference tooth and the reference sensor. The first and second sensors have different orientations. The computer generates an output indicative of the axial position of the phonic wheel based on the positioning signal and the reference signal.
F01D 17/06 - Aménagement des éléments sensibles sensibles à la vitesse
F01D 17/24 - Dispositifs utilisant des éléments sensibles ou des organes de commande terminaux ou les organes de liaison entre les deux, p. ex. commande assistée l'énergie de fonctionnement ou de puissance assistée étant essentiellement non mécanique électrique
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01D 21/14 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à d'autres conditions spécifiques
G01B 7/02 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur
G01B 7/30 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer des angles ou des cônesDispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour tester l'alignement des axes
A method is disclosed for providing a component. During this method, braze powder is deposited with a substrate. The braze powder is sintered together during the depositing of the braze powder to provide the substrate with sintered braze material. The sintered braze material is heated to melt the sintered braze material and to diffusion bond the sintered braze material to the substrate to provide braze filler material. A first object is scanned using computed tomography to provide first object scan data. The first object includes the substrate and the braze filler material diffusion bonded to the substrate. The first object scan data is compared to first object reference data to provide machining data. The first object is machined using the machining data to provide a second object.
Apparatus and associated methods relate to a bond-degradation device for testing EMI susceptibility and/or emission suppression of an electrical control system that includes a shielded cable assembly. The bond-degradation device includes a resistive annulus configured to be interposed between normally-connected first and second shielded connectors of the electrical control system. The resistive annulus introduces a resistance between shields of the normally-connected first and second shielded connectors, thereby compromising integrity of the shielding of conductive wires within the shielding of the shielded cable assembly by increasing loop resistance of the shielding.
H05K 9/00 - Blindage d'appareils ou de composants contre les champs électriques ou magnétiques
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
H01R 13/6592 - Caractéristiques ou dispositions spécifiques de raccordement du blindage aux organes conducteurs l'organe conducteur étant un câble blindé
An air cycle machine (ACM) is provided and includes a rotor. The rotor includes a rotor hub, an outlet housing and one or more bearings. The rotor hub includes rear and forward faces, a central portion axially interposed between the rear and forward faces and blades extending radially outwardly from the central portion. The rotor hub defines a pocket having an open end and forms a foil bearing shaft. The outlet housing includes a bearing support element, which is receivable in the pocket via the open end. The one or more bearings are supportively disposed within the bearing support element to support rotation of the foil bearing shaft
An air cycle machine (ACM) is provided and includes a rotor including rear and forward faces and a central portion interposed between the rear and forward faces with outwardly extending blades. The rotor defines a pocket having an open end and forms a foil bearing shaft. The ACM further includes an inlet housing partially surrounding the rotor, an outlet housing including a forward face and a bearing support element extending from the forward face and being receivable in the pocket via the open end, one or more first bearings disposed within the bearing support element to support rotation of the foil bearing shaft, a second bearing interposed between the forward face of the outlet housing and the rear face of the rotor and a third bearing interposed between the forward face of the rotor and the inlet housing.
F25B 9/06 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé utilisant des détendeurs
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
F25B 9/00 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé
6.
ECONOMIZER INJECTION IN A RECIPROCATING COMPRESSOR
A compressor includes a cylinder block having a first bore and a cylinder head overlapping the cylinder block. The cylinder head has a second bore aligned with the first bore. The second bore is separated into a plurality of distinct regions including a suction region and an economizer region. A plurality of valves includes a suction valve selectively operable to fluidly couple the suction region and the first bore, and an economizer valve selectively operable to fluidly couple the economizer region and the first bore.
F25B 1/10 - Machines, installations ou systèmes à compression à cycle irréversible à compression multi-étagée
F04B 25/04 - Pompes multiétagées spécialement adaptées aux fluides compressibles ayant des cylindres coaxiaux, parallèles ou inclinés par rapport à l'arbre principal
F04B 39/00 - Parties constitutives, détails ou accessoires de pompes ou de systèmes de pompage spécialement adaptés aux fluides compressibles, non prévus dans les groupes ou présentant un intérêt autre que celui visé par ces groupes
F04B 39/12 - Carcasses d'enveloppeCylindresCulassesConnexions des tubulures pour fluide
F04B 49/22 - Commande des "machines", pompes ou installations de pompage ou mesures de sécurité les concernant non prévues dans les groupes ou présentant un intérêt autre que celui visé par ces groupes par clapets
A casing for a gas turbine engine, including: an inner ring portion; an intermediate layer of honeycomb and/or foam secured to a radially outward surface of the inner ring portion; an outer ring portion secured to a radially outward surface of the layer of honeycomb and/or foam; and a composite containment belt secured to a radially outward surface of the outer ring portion, the composite containment belt having a central portion integrally formed with a forward ring portion and an aft ring portion, the composite containment belt including at least one single woven belt wound about the outer ring portion, the at least one single woven belt including a plurality of continuous fibers, wherein a first portion of the plurality of continuous fibers are at arranged at an angle of 45/−45 degrees or greater with respect to a circumferential direction of the composite containment belt in the central portion and a second portion of the plurality of continuous fibers are at arranged at an angle of less than 45/−45 degrees with respect to the circumferential direction of the composite containment belt in the forward ring portion and the aft ring portion.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p. ex. indiquant cette position
An assembly is provided for an aircraft motor. The assembly includes a bearing, a stationary structure and a flexible support. The bearing extends circumferentially around an axis. The stationary structure circumscribes the bearing. The flexible support is arranged radially between the bearing and the stationary structure. The flexible support includes an inner ring, an outer ring, a bridge, an open first channel and an open second channel. The inner ring radially engages the bearing. The outer ring radially engages the stationary structure. The bridge projects radially out from the inner ring to the outer ring. The bridge extends circumferentially about the inner ring. The open first channel extends axially into the flexible support from a first side of the flexible support to the bridge. The open second channel extends axially into the flexible support from a second side of the flexible support to the bridge.
A non-rotating spacer for use in a mating part of a gas turbine engine, including: a ring of material having a first contact surface and a second contact surface, the first contact surface being opposite to the second contact surface, the ring of material also having an inner ring surface and an outer ring surface; a pair of slots located in the first contact surface, the pair of slots extending from the inner ring surface to the outer ring surface, the pair of slots do not extend though to the second contact surface such that the pair of slots are defined by three surfaces of the ring of material; and at least one lug protruding radially outward from the outer ring surface, the at least one lug being located adjacent to one of the pair of slots.
An injector includes a mount, a stem, a nozzle, and a heat shield. The heat shield extends from the mount to surround the stem and at least a portion of the nozzle. The nozzle includes an exterior annular body. The distal end of the heat shield is spaced from a lip extending from the exterior annular body or a cap surrounding the nozzle to form an axial gap.
A casing for a gas turbine engine, including: an inner surface portion; a pair of wall portions extending radially outward from the inner surface portion; and a containment ring located between the pair of wall portions, the containment ring including an inner ring, an intermediate ring, and an outer ring, the intermediate ring being located between the inner ring and the outer ring, wherein the containment outer ring is mechanically decoupled from the pair of wall portions.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p. ex. indiquant cette position
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
12.
PNEUMATIC START SYSTEM WITH INTEGRATED ELECTRIC GENERATOR POWERED BY ENGINE ENVIRONMENTAL CONTROL BLEED SUPPLY
A pneumatic start system includes a compressor system and an air turbine starter (ATS) comprising an integrated electric generator. Bleed air from the compressor system flows to the air turbine starter, exciting the integrated generator. The ATS regulates a pressure of the bleed air from the compressor system via the integrated generator. The ATS is fluidly coupled to an environmental control system (ECS) bleed system. A fluid connection between the ECS bleed system and the ATS is regulated by a starter air valve (SAV). A second connection between the ECS bleed system and the ATS is regulated by an ECS shut off valve. Pressure regulated fluid flow from the compressor system is delivered to the ECS bleed system via the second fluid connection or is delivered to ambient atmosphere, via a valve fluidly connected between the ATS and the ambient atmosphere, based upon operation of the ECS shut off valve.
F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
A planetary gear carrier assembly includes a plurality of planetary gears each rotatable about a respective planet axis defined by a respective pin through the gear, and a planetary gear carrier defining an annular housing having a front face and a back face defining a housing therebetween and an annulus axis. The planetary gears are located within and spaced circumferentially around the housing. A position balancing arrangement is provided for at least one of the plurality of planetary gears, including a slot formed in the front face and back face, extending circumferentially, to receive the pin of the respective at least one of the planetary gears for circumferential movement within the slot, and a resilient element in biased engagement with the pin to adjust the position of the pin in the slot towards a desired position responsive to movement of the pin away from the desired position in the slot.
Drogue parachute systems include an ejection seat, an elastic riser operably connected to the ejection seat at a first end and a riser connection is arranged at a second end of the elastic riser, a set of suspension lines operably connected to the riser connection, and a drogue canopy attached to the set of suspension lines opposite the riser connection.
B64D 17/36 - Suspension de la charge incorporant des dispositifs de frottement ou de raccordement frangibles pour réduire le choc à l'ouverture de la coupole
A method of assembling a piston and shoe of a hydraulic pump. The method includes: inserting a shaft of the piston through an aperture of the shoe such that it extends through to the other side until a piston head of the piston is seated in the shoe. A piston and shoe assembly for a hydraulic pump. The assembly includes: a piston comprising a piston shaft and a piston head; and a shoe comprising an aperture, wherein the piston shaft is sized such that it can pass through the shoe aperture and the piston head is sized such that it cannot pass through the shoe aperture.
This magnet chuck (10) is provided with: a housing (20) comprising a magnetic chucking surface (27); and a magnet unit (56) that is provided inside the housing (20) and that is for attracting and holding a workpiece (12) to the magnetic chucking surface (27). The magnet unit (56) is formed of a plurality of permanent magnets (57). The plurality of permanent magnets (57) are arranged so that different magnetic poles are adjacent to each other. At least one permanent magnet (57) is surrounded by multiple other permanent magnets (57).
A compressor assembly has: an impeller rotatable about a central axis, the impeller mounted on a shaft; a bearing housing extending around the central axis and radially supporting the shaft; and a diffuser downstream of the impeller, the diffuser having: an annular member extending circumferentially around the central axis, vanes circumferentially distributed around the central axis and protruding from one of the annular member and the bearing housing, the vanes extending from bases at the one of the annular member and the bearing housing to tips at the other of the annular member and the bearing housing, and lug and slot connections defined between the annular member and the bearing housing to secure the annular member to the bearing housing.
An aircraft powerplant apparatus includes a rotating structure configured to rotate about an axis. The rotating structure includes a bladed rotor, a first component, a second component, a first balancing mass, a second balancing mass and a spring element. The first balancing mass and the second balancing mass are configured to rotationally balance the rotating structure about the axis. The first component include a plurality of first component teeth. The second component includes a plurality of second component teeth. The first balancing mass includes a first mass ring and a plurality of first mass teeth. The first mass teeth are meshed with the first component teeth. The second balancing mass includes a second mass ring and a plurality of second mass teeth. The second mass teeth are meshed with the second component teeth. The spring element is engaged with the first balancing mass and the second balancing mass.
A method is provided for operating a powerplant. During this method, a hydrocarbon fuel is delivered to a turbine engine for combustion within a combustion chamber of the turbine engine during initial startup operation of the turbine engine. Ammonia is at least partially cracked into hydrogen gas and nitrogen gas. A non-hydrocarbon fuel is delivered to the turbine engine for combustion within the combustion chamber of the turbine engine during post-startup operation of the turbine engine. The non-hydrocarbon fuel is or otherwise includes the hydrogen gas or a combination of the hydrogen gas and the nitrogen gas.
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 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
F23R 3/36 - Alimentation en combustibles différents
A turbine exhaust case has an inner ring structurally connected to an outer ring via a plurality of struts. An outer flange projects outwardly from the outer case. The outer flange is made of a material different from that of the outer case and includes a ring portion having an inner diameter surface joined to an outer diameter surface of the outer case at a first axial location corresponding to a junction of a leading edge of the plurality of struts and the outer case. The outer flange further includes a tubular portion projecting axially from the ring portion to a second axial location disposed upstream of the struts, and an annular mounting portion projecting outwardly from an outer surface of the tubular portion at the second axial location.
A method includes detecting an asymmetric thrust condition involving first and second engines of an aircraft. The asymmetric thrust condition is associated with one of the engines providing more thrust than another of the engines. The method also includes, in response to detecting the asymmetric thrust condition, determining a modifier for one of the engines and applying the modifier to an acceleration schedule for that engine. The modifier alters the acceleration schedule for that engine to reduce asymmetric thrust between the engines. In some cases, the first engine is associated with a first thrust controller, the second engine is associated with a second thrust controller, the first thrust controller is configured to modify an acceleration schedule of the first engine in response to the asymmetric thrust condition, and the second thrust controller is configured to modify an acceleration schedule of the second engine in response to the asymmetric thrust condition.
B64D 31/10 - Dispositifs amorçant la mise en œuvre actionnés automatiquement en réponse à une défaillance des groupes moteurs pour empêcher une poussée asymétrique
24.
PARTIAL-ADMISSION TURBINE ASSEMBLY FOR AN AIRCRAFT AND METHOD FOR CONTROLLING SAME
An assembly for an aircraft includes a fluid source, a first heat exchanger, a partial-admission turbine, a mechanical load, and a control assembly. The partial-admission turbine includes a rotational assembly and a plurality of partial-admission turbine stages. The rotational assembly includes a bladed turbine rotor. The bladed turbine rotor includes a plurality of rotor blade stages. Each of the plurality of partial-admission turbine stages includes a respective rotor blade stage of the plurality of rotor blade stages. The fluid source, the first heat exchanger, and the partial-admission turbine sequentially form a portion of a fluid flow path through the assembly. The mechanical load is coupled to the rotational assembly. The control assembly including a controller configured to determine a corrected turbine inlet flow and a corrected rotation speed for the partial-admission turbine, maintain the corrected turbine inlet flow within an inlet corrected flow threshold range, and maintain the corrected rotation speed within a corrected rotation speed threshold range.
F02C 9/48 - Commande de l'alimentation en combustible combinée avec une autre commande de 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
25.
ENVIRONMENTAL CONTROL SYSTEM OF AN AIRCRAFT CONFIGURED WITH A TWO-PHASE TURBINE ENCASED WITH A COMPRESSOR AND COUPLED TO A MOTOR HAVING A SHAFT COUPLING
An environmental control system of an aircraft, having: a cooling circuit including: a sealed housing; a turbo-compressor sealed within the housing, wherein the turbo-compressor includes: a compressor fluidly coupled to the circuit; a turbine fluidly coupled to the circuit downstream of the compressor, wherein the turbine is a flash turbine; a shaft operably coupling the compressor and the turbine; a motor generator operably coupled to the turbo-compressor; and an exterior shaft, located exterior to the housing and operably coupled to the motor generator, wherein: the motor generator is within the housing, directly coupled to the turbo-compressor and coupled to the exterior shaft via a coupling, wherein the coupling is one of: a magnetic coupling; a mechanical coupling; a geared axial flux motor; an electro-magnetic geared coupling; or a radial-axial flux permanent magnet (RADAX) motor.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
A single shaft, one piece rotor having: a hub that extends from a hub aft end to a hub forward end, wherein the hub aft end defines a first diameter and the hub forward end defines a second diameter that is smaller than the first diameter; a plurality of blade stages extending from a forward end to an aft end, wherein the blade stages are stacked, one on top of the other, radially outwardly from the hub, including an inner stage that is integral with the hub and an outer stage that is radially spaced apart from the hub; and a shroud between adjacent ones of the blade stages.
F25B 9/06 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé utilisant des détendeurs
F25B 9/00 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé
F25B 9/10 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé avec plusieurs étages de refroidissement
27.
AIRCRAFT CABIN AIR IONIZER WITH BUILT IN ION MEASUREMENT SYSTEM
A system is provided including an ionizer configured to produce and emit charged air ions into an ionization region. The system includes an ion cell configured to output a first voltage corresponding to an ion density associated with the ionization region. The system includes a signal conditioning circuit configured to output a second voltage to the ionizer based on the first voltage. The ionizer is configured to maintain or adjust a setting associated with producing and emitting the charged air ions into the ionization region, based on the second voltage.
B01D 53/32 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par effets électriques autres que ceux prévus au groupe
H01T 23/00 - Appareils pour la production d'ions destinés à être introduits dans des gaz à l'état libre, p. ex. dans l'atmosphère
A planetary gear carrier assembly includes a plurality of planetary gears each rotatable about a respective planet axis defined by a respective pin through the gear, and a planetary gear carrier defining an annular housing having a front face and a back face defining a housing therebetween and an annulus axis. The plurality of planetary gears are located within and spaced circumferentially around the housing, the pin of each planetary gear passing from the front face to the back face at a location such that the planetary gear partially extends radially outwards of the carrier periphery. The carrier is provided with compliance, the compliance provided by one or more portions of reduced stiffness in the front and back faces adjacent the location of the pin of one or more of the planetary gears.
A real-time artificial intelligence and/or machine learning (AI/ML) system for an aircraft can include an AI/ML module configured to receive one or more inputs and to calculate an AI/ML control output. The AI/ML module can include a non-deterministic model for processing the inputs and outputting the AI/ML control output. The system can include a deterministic module configured to receive one or more inputs and the AI/ML control output from the AI/ML module. The deterministic module can include a deterministic model for processing the inputs and/or AI/ML control output to calculate a deterministic condition. The deterministic module can be configured to check the AI/ML control output against the deterministic condition to determine whether to output the AI/ML control output.
Disclosed is a direct-drive refrigerant screw compressor, having: a housing; a compression chamber in the housing; a pair of rotors, each rotor of the pair of rotors being rotationally disposed in the compression chamber and including an outer surface with a screw-geared profile; a fluid being disposed in the compression chamber, the fluid consisting of a working fluid for providing lubrication to each rotor; a first port extending through the housing and configured for directing the fluid toward the compression chamber; and when the compressor is activated, each rotor rotates and the fluid is distributed about each rotor to lubricate each rotor.
F04C 29/02 - LubrificationSéparation du lubrifiant
F04C 18/16 - Pompes à piston rotatif spécialement adaptées pour les fluides compressibles du type à engrènement extérieur, c.-à-d. avec un engagement des organes coopérants semblable à celui d'engrenages dentés d'un autre type qu'à axe interne avec des pistons rotatifs dentés à dents hélicoïdales, p. ex. du type ayant la forme d'un chevron, du type à vis
F25B 1/047 - Machines, installations ou systèmes à compression à cycle irréversible à compresseur rotatif du type à vis
A casing for a gas turbine engine, including: a plurality of layers of a structural material, wherein each layer of the plurality of layers of the structural material are separated from each other by at least one layer of an impact absorbing material, the at least one layer of impact absorbing material being different from the structural material and the impact absorbing material having a radial thickness that is greater than a radial thickness of the structural material, wherein the plurality of layers of the structural material comprises at least three layers.
A casing for a gas turbine engine, including: an inner ring portion; an outer ring portion; and a plurality of blunting plates arranged circumferentially between the inner ring portion and the outer ring portion, wherein the plurality of blunting plates are positioned to overlap each other.
Systems and methods for performing dimensional inspection of components are provided. The systems and methods correct errors associated with non-contact scanning of components based on surface quality. A method of inspecting a component includes using non-contact scanning of the component to acquire a point cloud indicative of a geometry of the component, acquiring a surface quality of the component, and selecting a geometric transformation associated with the surface quality of the component from a plurality of geometric transformations respectively associated with different surface qualities. The point cloud is transformed using a selected geometric transformation associated with the surface quality of the component.
A cooling fan housing is provided. The cooling fan housing includes an inner housing and an outer housing. The inner housing includes inner forward and inner rearward flanges on either side of an inner annulus. The inner rearward flange includes a recessed portion proximate to the inner annulus and a non-recessed portion remote from the inner annulus. The outer housing includes outer forward and outer rearward flanges on either side of an outer annulus. The outer and inner forward flanges are attachable in a tight-fitting condition. The outer rearward flange and the non-recessed portion of the inner rearward flange are attachable in a tight-fitting condition with the recessed portion of the inner rearward flange forming a gap with the outer rearward flange.
A ram air journal bearing shaft includes an additively manufactured body having a main body portion and a journal bearing portion. The main body portion and the journal bearing portion are coaxial along a first axis. At least a first set of heat exchanger fins extends from an outer diameter of the ram air journal bearing shaft to an inner diameter tie rod passage. Each heat exchanger fin in the first set of heat exchanger fins is additively manufactured as an integral structure to the additively manufactured body. A set of cooling air passages is disposed circumferentially about the first axis. Each cooling air passage is defined between adjacent heat exchanger fins of the first set of heat exchanger fins. The ram air journal bearing shaft is configured such that a cooling flowpath through the cooling air passages is established.
A turbine engine for an aircraft includes a compressor with a low-pressure spool including a low-pressure tap and a high-pressure spool including a high-pressure tap and a combustor connected to the compressor. The engine includes a turbine connected to the combustor and that includes an inlet section connected to the outlet portion of the combustor and an outlet section. The engine also includes an integrated engine bleed system connected to the compressor and a plurality of aircraft sub-systems. The integrated engine bleed system connects the high/low pressure taps various aircraft sub-systems.
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
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
37.
AIR HANDLING UNIT HAVING A HEAT SHIELD FLOW DISTRIBUTOR
Described herein is an air handling unit (AHU), comprising a motor-driven fan configured to generate an airflow through a housing, one or more heat elements downstream of the fan to heat the airflow, a control box within the housing containing control electronics to control the heat elements, and a supplementary heat shield between the heat elements and the control box. The supplementary heat shield and control box form a passage for airflow, allowing the control electronics to dissipate thermal losses, and the heat shield reduces heat transfer from the heat elements.
A heat removal device operable to cool a heat-generating device includes a housing having a hollow interior and a base thermally couplable to the heat-generating device and arranged within the hollow interior of the enclosure. The base includes a cooling surface arranged at an incline. A plurality of fins protrude from the cooling surface and at least one first groove is formed in the cooling surface. A top cover is positioned upwardly adjacent to the plurality of fins. The top cover has one or more perforations formed therein.
H01L 23/427 - Refroidissement par changement d'état, p. ex. caloducs
H01L 23/373 - Refroidissement facilité par l'emploi de matériaux particuliers pour le dispositif
H01L 23/367 - Refroidissement facilité par la forme du dispositif
H01L 23/46 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température impliquant le transfert de chaleur par des fluides en circulation
H01L 23/467 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température impliquant le transfert de chaleur par des fluides en circulation par une circulation de gaz, p. ex. d'air
H01L 23/473 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température impliquant le transfert de chaleur par des fluides en circulation par une circulation de liquides
A heat management system for a thermal engine includes a source of hydrogen, a first hydrogen conduit flowing a first flow of hydrogen therethrough, the first hydrogen conduit fluidly coupling the source of hydrogen to a fuel system of the thermal engine, and a second hydrogen conduit flowing a second flow of hydrogen therethrough. The second hydrogen conduit is in thermal communication with an engine exhaust conduit to transfer heat from the engine exhaust conduit to the second hydrogen conduit. The second hydrogen conduit is also in thermal communication with the first hydrogen conduit to transfer heat from the second hydrogen conduit to the first hydrogen conduit.
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 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
41.
NON-LINEAR STIFFNESS BRACKET OF GAS TURBINE ENGINE
A mounting bracket of a gas turbine engine includes a first mounting flange configured to connect the mounting bracket to a casing of the gas turbine engine, a second mounting flange configured to connect a component to the mounting bracket, and a bracket leg extending between the first mounting flange and the second mounting flange. The mounting bracket has a first stiffness when a load is applied in a first force direction and has a second stiffness different from the first stiffness when the load is applied in a second force direction opposite the first force direction.
F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F15B 21/00 - Caractéristiques communes des systèmes de manœuvre utilisant des fluidesSystèmes de manœuvre à pression ou parties constitutives de ces systèmes, non couverts par l'un quelconque des autres groupes de la présente sous-classe
42.
HEAT EXCHANGER HAVING A MIXING CHAMBER WITH CONVERGENT SECTION
A system for an aircraft engine, has: an aircraft component; and a heat exchanger having: a housing defining a first inlet, a first outlet, a second inlet, and a second outlet; first conduits within the housing, the first conduits fluidly connecting the first inlet to the first outlet; one or more second conduit within the housing, the one or more second conduits fluidly connecting the second inlet to the second outlet, the one or more second conduit in heat exchange relationship with the first conduits; and a mixing chamber intersecting two or more of the first conduits and separating the first conduits into upstream sections and downstream sections, the mixing chamber having a peripheral wall extending around a mixing volume, the peripheral wall defining a convergent section in which a flow circulating area of the mixing volume decreases in a downstream direction relative to the flow through the first conduits.
F28F 13/12 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en créant une turbulence, p. ex. par brassage, par augmentation de la force de circulation
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
F28F 1/40 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements les moyens étant uniquement à l'intérieur de l'élément tubulaire
A system for an aircraft engine, has: an aircraft component; and a heat exchanger having: a housing defining a first inlet, a first outlet, a second inlet, and a second outlet; first conduits within the housing, the first conduits fluidly connecting the first inlet to the first outlet; one or more second conduit within the housing, the one or more second conduits fluidly connecting the second inlet to the second outlet, the one or more second conduit in heat exchange relationship with the first conduits; a mixing chamber intersecting two or more of the first conduits, the mixing chamber having a peripheral wall extending around a mixing volume and a central axis; and fins protruding from the peripheral wall into the mixing volume, the fins extending in a direction having an axial component relative to the central axis, the fins defining flow passages interspaced between the fins.
F28F 13/12 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en créant une turbulence, p. ex. par brassage, par augmentation de la force de circulation
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
F28F 1/40 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements les moyens étant uniquement à l'intérieur de l'élément tubulaire
44.
Heat exchanger having a mixing chamber and protrusions
A system for an aircraft engine, has: an aircraft component; and a heat exchanger having: a housing defining a first inlet, a first outlet, a second inlet, and a second outlet; first conduits within the housing, the first conduits fluidly connecting the first inlet to the first outlet; one or more second conduit within the housing, the one or more second conduits fluidly connecting the second inlet to the second outlet, the one or more second conduit in heat exchange relationship with the first conduits; a mixing chamber intersecting two or more of the first conduits, the mixing chamber having a peripheral wall extending around a mixing volume and a central axis; and protrusions extending from the peripheral wall into the mixing volume, the protrusions extending around the central axis and across a direction of the flow through the mixing chamber.
F28F 13/12 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en créant une turbulence, p. ex. par brassage, par augmentation de la force de circulation
A system with active pressure control includes a sensor, a valve, and a controller. The sensor interfaces with and senses a pressure within a cavity of system component. The valve is disposed along a gas discharge path in fluid communication with a gas outlet port of a separator. The controller varies open area of the valve based on the pressure measured by the sensor.
F16H 57/027 - Boîtes de vitessesMontage de la transmission à l'intérieur caractérisés par des moyens pour ventiler les boîtes de vitesses, p. ex. dispositifs d'aération
A system for accelerating a pump includes a fuel source, a pump, a drive, a turbine, and a combustor. The pump has an inlet in fluid communication with the fuel source and an outlet. The drive is rotationally coupled to the pump and configured to drive the pump to thereby pump fuel from the inlet to the outlet of the pump. The turbine rotationally coupled to the drive and the pump. The combustor fluidly communicates with the outlet of the pump and the inlet of the turbine.
A seal arrangement of a gas turbine engine includes two seal assemblies arranged in a serial relationship relative to an engine central longitudinal axis. Each seal assembly includes a seal carrier, and a primary seal element positioned in the seal carrier and configured to seal to a rotating component of the gas turbine engine abutting the primary seal element. A seal sleeve is positioned radially outboard of the seal carriers of the two seal assemblies. The seal sleeve is configured to retain the two seal assemblies in position abutting the rotating component.
A system for an aircraft engine, has: an aircraft component; and a heat exchanger having: a housing defining a first inlet, a first outlet, a second inlet, and a second outlet; first conduits within the housing, the first conduits fluidly connecting the first inlet to the first outlet; one or more second conduit within the housing, the one or more second conduits fluidly connecting the second inlet to the second outlet, the one or more second conduit in heat exchange relationship with the first conduits; a mixing chamber intersecting two or more of the first conduits, the mixing chamber having a peripheral wall extending around a mixing volume and a central axis; and louvers mounted to the peripheral wall and extending transversally to the central axis, the louvers movable between a collapsed configuration and a deployed configuration and extending across the mixing volume in the deployed configuration.
F28F 1/32 - Éléments tubulaires ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des saillies, avec des évidements ces moyens étant uniquement à l'extérieur de l'élément tubulaire et s'étendant transversalement les moyens ayant des parties engageant d'autres éléments tubulaires
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
F28F 13/12 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution en affectant le mode d'écoulement des sources de potentiel calorifique en créant une turbulence, p. ex. par brassage, par augmentation de la force de circulation
49.
METHOD OF REDUCING NOISE OF AIRCRAFT HAVING HYBRID POWER PLANTS
A propulsion system for an aircraft includes a first hybrid power plant and a second hybrid power plant, each including a thermal engine and an electrical motor. Acoustic sensors measure an initial combined noise signature, produced by the propulsion system, including first and second noise signatures respectively generated by the first and second hybrid power plants. A controller receives a signal from the acoustic sensors and determines when an initial amplitude variation of a periodically fluctuating amplitude of the initial combined noise signature is greater than an amplitude variation threshold indicative that the initial combined noise signature generates beats. A thrust produced by the second hybrid power plant is modulated to produce a modulated combined noise signature having a modulated amplitude variation less than the initial amplitude variation. A difference in thrusts generated by the first and second hybrid power plants is compensated for.
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 35/025 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride du type en parallèle
50.
CONTOURED INLET MANIFOLD FOR SUBFREEZING HEAT EXCHANGER
A component for use in an environmental control system includes an inlet portion having a longitudinal axis, an inlet formed at the inlet portion, and an outlet portion including a front side and a back side. The front side is arranged closer to the inlet portion than the back side. An outlet is formed at the outlet portion and is arranged at a non-parallel angle relative to the inlet. An intermediate portion extends between and fluidly couples the inlet portion and the outlet portion. The intermediate portion includes a reservoir spaced laterally from the back side of the outlet portion and offset from the longitudinal axis of the inlet portion.
F28F 9/02 - Boîtes de distributionPlaques d'extrémité
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
An additively manufactured heat exchanger is provided and includes first and second inlet headers which are interlaced with one another, first and second outlet headers which are interlaced with one another and a core. The core is interposed between a pair of the first and second inlet headers and a pair of the first and second outlet headers. The core includes first pathways by which a first fluid flows from the first inlet header to the first outlet header and second pathways disposed in thermal communication with the first pathways and by which a second fluid flows from the second inlet header to the second outlet header.
F28D 7/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 7/02 - Blocs traversés par des passages pour sources de potentiel calorifique
F28F 9/02 - Boîtes de distributionPlaques d'extrémité
52.
CONTROL METHOD AND CONTROL DEVICE FOR COMPRESSOR UNIT
The disclosure provides a control method and a control device for a compressor unit, in which oil levels of a first compressor and a second compressor can be adjusted without additionally arranging an oil return pipeline. A first aspect of this application provides a control method for a compressor unit, the compressor unit having a first compressor and a second compressor, and the first compressor and the second compressor being in communication with each other through a gas balance pipe and an oil balance pipe. The compressor unit has a conventional operation step and an oil level adjustment step that are alternately executed, and in the oil level adjustment step, the compressor unit changes a rotation speed of the first compressor and/or the second compressor to adjust oil levels of the first compressor and the second compressor.
This horizontal articulated robot (10) is provided with a base part (14) and a robot body (16). The robot body is provided with a first arm (30), a second arm (32), a first motor (36), a second motor (40), a first power transmission part (38), and a second power transmission part (42). The first arm is positioned below the base part, the second arm is positioned below the first arm, and the second motor is positioned so as not to interfere with the second arm in a state in which the tip (32t) of the second arm is located below the first arm.
A pressure booster (10) comprises: an inlet port (12) into which compressed air flows; drive chambers (32, 42) that drive a first piston (24) by means of the compressed air; a second piston (26) that is coupled to the first piston (24); pressure boosting chambers (34, 44) in which compression of the compressed air is performed by the second piston (26); an outlet port (14) that causes the compressed air having undergone compression in the pressure boosting chamber (44) to flow out; an exhaust part (16) through which the compressed air in the drive chamber (32) is discharged; and a selector valve (30) that connects the drive chamber (32) to the inlet port (12) or to the exhaust part (16) by switching therebetween. A common drive flow path (60) for connecting the inlet port (12) to the drive chamber (32) has a throttle part (62) that regulates the flow rate of the compressed air flowing toward the drive chamber (32) and that does not hinder the discharge of the compressed air from the drive chamber (32).
F15B 3/00 - Amplificateurs ou convertisseurs de pression de fluide, p. ex. échangeurs de pressionTransmission de la pression d'un système à fluide à un autre, sans contact entre les fluides
55.
ATTACHMENT FIXTURE FOR IONIZER, IONIZER HAVING THE SAME, AND ATTACHMENT STRUCTURE USING THE SAME
[Problem] To provide, with regard to an ionizer that has a long and narrow housing in which a plurality of discharge needles are retained in a row, an attachment fixture that increases the efficiency of the work of attaching and detaching said housing to and from an installation site, as well as to provide an ionizer having said attachment fixture, and an attachment structure using said attachment fixture. [Solution] An attachment fixture 6 that attaches a housing 20, in which a plurality of discharge needles 31 are retained in a row along a long axis L1, to an installation location F is provided with: an axial direction support member 60 that has a locking engagement piece 61 capable of being manually manipulated between a locked position, in which the same is engaged with an end section of the housing and restricts movement of the housing along the long axis, and an unlocked position, in which said engagement is released; and a suspension support member 65 that has a sliding engagement piece 66 engaging, in a freely slidable manner, with a long axis direction slide groove 28 in the housing, and supporting the housing upward from below, wherein a pair of said attachment fixtures are used to retain both end sections of the housing.
An assembly for an aircraft propulsion system includes a nacelle, at least one fan cowl actuator, at least one C-duct actuator, and a controller. The nacelle includes an outer structure including a fan cowl and a thrust reverser. The fan cowl includes at least one fan cowl door. The thrust reverser includes at least one C-duct door. The at least one fan cowl actuator is mounted to the at least one fan cowl door. The at least one C-duct actuator is mounted to the at least one C-duct door. The controller is configured to selectively direct electrical power from a power supply to (1) the fan cowl actuator electric motor to control a fan cowl position of the at least one fan cowl door and (2) the C-duct actuator electric motor to control a C-duct position of the at least one C-duct door.
An aircraft propulsion system includes a gas turbine engine and an exhaust nozzle assembly. The gas turbine engine includes a compressor section, a combustor section, a turbine section, and an exhaust section. The compressor section, the combustor section, the turbine section, and the exhaust section form a core flow path through the gas turbine engine. The exhaust nozzle assembly is disposed at the exhaust section. The exhaust nozzle assembly includes a nozzle bypass system and an exhaust treatment system. The nozzle bypass system is selectively configurable in a bypass mode or an exhaust treatment mode. The nozzle bypass system in the bypass mode directs a core combustion gas from the core flow path through the exhaust nozzle assembly bypassing the exhaust treatment system. The nozzle bypass system in the exhaust treatment mode directs the core combustion gas through the exhaust nozzle assembly and exhaust treatment system.
F02K 1/00 - Ensembles fonctionnels caractérisés par la forme ou la disposition de la tubulure de jet ou de la tuyèreTubulures de jet ou tuyères particulières à cet effet
F02C 3/20 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion
F02C 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 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
F02C 9/52 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande du flux du fluide de travail par prélèvement ou bipasse du fluide de travail
F02K 1/82 - Parois des tubulures de jet, p. ex. chemises
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
A method includes receiving a callback routine creation command at a target device. The method also includes creating a callback routine in a callback memory space included in memory of the target device after validating the same. The method also includes receiving a set breakpoint command at the target device. The method also includes, in response to the received set breakpoint command, setting a breakpoint at the target device. The method can also include identifying a breakpoint hit, generating, by an exception inducing instruction, an interrupt, identifying a breakpoint control block in an active breakpoints data structure. The method also can also include invoking the callback routine and storing an opcode at a memory address, wherein the memory address is in a predetermined memory region of the memory, and wherein the breakpoint control block stores the opcode and the memory address.
A voltage converter for converting an input voltage to an output voltage includes a controller arranged to: superpose a power line communication signal onto a target DC output voltage to provide a target output voltage; compare the output voltage of the voltage converter with the target output voltage; and adjust operation of the voltage converter so as to drive the output voltage towards the target output voltage.
H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
H02M 3/00 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu
H04B 3/54 - Systèmes de transmission par lignes de réseau de distribution d'énergie
60.
ELECTRICAL POWER SUPPLY SYSTEM FOR TRANSPORT REFRIGERATION SYSTEM
An electrical power supply system for an electric transport refrigeration unit. The electrical power supply system is for providing AC power to a refrigeration system and includes: a DC power source for providing a DC voltage via a low voltage line and a high voltage line; an inverter for receiving the DC voltage and converting it to a three phase AC voltage for powering the refrigeration system; and an electromagnetic compatibility, EMC, filter between the inverter and the refrigeration system. The EMC filter uses a common mode current path that connects to a DC link, where the DC link is provided between the high voltage line and the low voltage line of the DC power source. The common mode current path is hence coupled to the DC link in order to provide a floating current connection for common mode current from the EMC filter.
B60R 16/03 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour l'alimentation des sous-systèmes du véhicule en énergie électrique
B60P 3/20 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux pour le transport de marchandises réfrigérées
F25D 11/00 - Dispositifs autonomes déplaçables associés à des machines frigorifiques, p. ex. réfrigérateurs ménagers
H02P 27/06 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de tension d'alimentation utilisant une tension d’alimentation à fréquence variable, p. ex. tension d’alimentation d’onduleurs ou de convertisseurs utilisant des convertisseurs de courant continu en courant alternatif ou des onduleurs
H03H 7/01 - Réseaux à deux accès sélecteurs de fréquence
A chuck device (10) comprises: a first movable part (14) and a second movable part (16) for gripping a workpiece (W); and a cylinder device (18) for moving the first movable part and the second movable part closer to and away from each other. The cylinder device is disposed between the first movable part and the second movable part in a movable direction in which the first movable part and the second movable part move closer to and away from each other.
A computer system includes a controller having a computer readable storage medium having program instructions embodied therewith, the program instructions executable by controller to perform operations including generating a three-dimensional (3D) model of a product, extracting data indicative of one or more elements of the product, and assigning a FAE address to the one or more elements. The method further includes generating a grouping tree to organize the extracted elements, each extracted element organized according to the FAE address, and adding product and manufacturing information (PMI) data to one or more of the addressed FAEs in the grouping tree.
G06F 30/12 - CAO géométrique caractérisée par des moyens d’entrée spécialement adaptés à la CAO, p. ex. interfaces utilisateur graphiques [UIG] spécialement adaptées à la CAO
G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
G06F 119/18 - Analyse de fabricabilité ou optimisation de fabricabilité
A propeller propulsion system includes: a prime mover having at least one spool, a propeller arranged to be driven by the spool, a pitch adjustment subsystem comprising an electronic control unit and an electronic protection unit, a prime mover speed sensor arranged to detect a rotation speed of the spool; and an additional speed sensor arranged to detect the rotation speed of the spool or arranged to detect a rotation speed of the propeller. A first of the electronic control unit and the electronic protection unit is arranged to use an output from the prime mover speed sensor to determine the rotation speed of the propeller; and a second of the electronic control unit and the electronic protection unit is arranged to use an output from the additional speed sensor to determine the rotation speed of the propeller.
An axial flux electric motor for an aircraft includes a first motor section having a first stator and a first rotor, and a second motor section having a second stator and a second rotor. The first and second rotors are mounted on a common axle. The first rotor is secured to the common axle by a first set of connecting elements. The second rotor is secured to the common axle by a second set of connecting elements. The first set of connecting elements is arranged to break when the relative torque between the common axle and the first rotor is greater than a first particular threshold. The second set of connecting elements is arranged to break when the relative torque between the common axle and the second rotor is greater than a second particular threshold.
H02K 21/24 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants disposés axialement en face des induits, p. ex. dynamos de bicyclette du type moyeu
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
B64D 35/021 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
65.
Hybrid electric propulsion system with regeneration and method for operating the same
A method of regenerating an electric power storage unit for an aircraft hybrid electric propulsion (HEP) system is provided. The HEP system includes a thermal engine, an electric motor, an electric power storage unit, a primary gearbox, and a propulsion unit. The electric motor is configured to selectively provide rotational drive to the propulsion unit. The method includes: controlling the electric motor to operate as the generator; controlling the primary gearbox to be in an output disengaged configuration, wherein in the output disengaged configuration the primary gearbox is disengaged from driving the propulsion unit and the primary gearbox is transfers rotational drive produced by the thermal engine to the electric motor; operating the thermal engine to drive the primary gearbox in the output disengaged configuration; and regenerating the electric power storage unit by providing electrical energy produced by the electric motor to the electric power storage unit.
H02P 9/06 - Commande s'exerçant sur un embrayage ou un autre moyen mécanique de transmission de la puissance et dépendant de la valeur d'une caractéristique électrique à la sortie de la génératrice
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 35/022 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride
H02K 7/108 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des embrayages à friction
H02K 7/116 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques avec des engrenages
H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
H02P 101/25 - Adaptation particulière des dispositions pour la commande de génératrices pour moteurs à combustion
H02P 101/30 - Adaptation particulière des dispositions pour la commande de génératrices pour aéronefs
66.
Electromagnetic inducer for gas turbine rotating turbomachinery
Gas turbine engines include fan, compressor, combustor, and turbine sections. An electric machine assembly includes a rotating component comprising a plurality of airfoils and a plurality of first electric machine elements, with each airfoil including a respective first magnetic material electric machine element. A housing is arranged radially outward from the airfoils and includes a circumferential slot. A second electric machine element is arranged within the circumferential slot in the form of a circumferential winding arranged radially outward from the rotating component. A control system is electrically connected to the second electric machine element. Rotation of the rotating component causes the first electric machine elements to generate a magnetic flux and induce a current within the second electric machine element and the control system is configured to distribute the induced current to at least one of a storage device or electrical components of the gas turbine engine.
An assembly includes a rotating seal land, a seal element, a stationary seal support and a mating plate. The seal element axially overlaps, circumscribes and radially sealingly engages the rotating seal land. The stationary seal support axially overlaps and circumscribes the rotating seal land and the seal element. The stationary seal support includes a support notch, a support shoulder, a support inner interior surface and a support outer interior surface. The support notch projects axially into the stationary seal support from a distal end of the stationary seal support to the support shoulder. The support notch projects radially outward away from an axis into the stationary seal support from the support inner interior surface to the support outer interior surface. The mating plate is seated in the support notch and mounted to the stationary seal support. The mating plate axially contacts the support shoulder and the seal element.
A fluid system includes a boost pump and a variable displacement pump along a main leg configured to output fluid within a pressure range and at variable flow rates. An auxiliary leg of the fluid system includes an auxiliary pump configured to receive a portion of the fluid from the main leg and to output pressurized fluid to a control valve of the variable displacement pump and multiple actuator modules. Each actuator module includes an electromechanical actuator and a collocated control unit.
A method for fabricating a component from a hybrid raw material, comprising the steps of: forging a first portion of a raw material for the component; additive manufacturing a second portion of a raw material to the first portion to produce a hybrid raw material; and machining the hybrid raw material to produce the component. A repair method is also disclosed.
B22F 7/08 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p. ex. pour former des outils à embouts rapportés avec une ou plusieurs parties non faites à partir de poudre
B22F 10/66 - Traitement de pièces ou d'articles après leur formation par des moyens mécaniques
The method can include operating the hybrid aircraft power plant in a first mode of operation in which a plurality of controllable parameters including a fuel flow to the thermal engine and an electric power to the electric motor has a first set of values corresponding to a first power output; receiving a requested power output; determining a second set of values of the one or more of the controllable parameters to bring first power output to the requested power output; determining whether said second set of values poses a risk of undesired clutch behavior; and when the second set of values poses the risk, modulating the second set of values to avoid the risk and setting the plurality of controllable parameters to the modulated second set of values.
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
B64C 11/30 - Mécanismes de changement de pas des pales
An apparatus is provided for a powerplant. This powerplant apparatus includes a fluid filter assembly with a filter housing. The filter housing extends axially along an axis between a housing first end and a housing second end. The filter housing includes a mount and a sidewall. The mount is connected to the sidewall. The mount includes a flange, an attachment and a pilot. The flange projects radially out from the sidewall and the attachment to a flange distal outer end. The attachment extends axially between the flange and the pilot. The attachment is configured with an external threaded section. The pilot projects axially out from the attachment to the housing first end. The pilot includes a cylindrical external surface located radially inboard of the external threaded section. An axial length of the pilot is greater than an axial length of the attachment.
F16M 7/00 - Détails de fixation ou de réglage des bâtis, châssis ou pièces de supports des moteurs sur leurs fondations ou leur baseFixation des parties fixes des moteurs, p. ex. des blocs cylindres
B01D 29/11 - Filtres à éléments filtrants stationnaires pendant la filtration, p. ex. filtres à aspiration ou à pression, non couverts par les groupes Leurs éléments filtrants avec des éléments filtrants en forme de sac, de cage, de tuyau, de tube, de manchon ou analogue
A stratospheric capsule includes: a capsule interior configured to enclose occupants during a stratospheric space flight; a capsule exterior; and an environmental control system (ECS) configured to control one or more of temperature and humidity in the capsule interior during the stratospheric space flight. The ECS includes: an internal air-cooling heat exchanger that cools air within the capsule by passing air across a cooling fluid within the ECS and a phase change material (PCM) heat exchange assembly located within the capsule interior. First and second valves are arranged and configured to be controlled based on the temperature measured by the temperature sensor measuring air passing through the internal air-cooling heat.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
A MEMS densimeter may include a cantilever portion defining one or more microcapillaries. The microcapillaries may provide an enhanced response to the fluid density. The microcapillaries may include microcapillaries which are aligned with flexure of the cantilever portion, such s through-hole microcapillaries, blind-hole microcapillaries, and grid microcapillaries. The microcapillaries may also include a plate microcapillary aligned normal to the flexure of the cantilever portion.
G01N 9/34 - Recherche du poids spécifique ou de la densité des matériauxAnalyse des matériaux en déterminant le poids spécifique ou la densité en utilisant les propriétés d'écoulement des fluides, p. ex. l'écoulement à travers des tubes ou des ouvertures en utilisant des éléments se déplaçant à travers le fluide, p. ex. moulinet (ou ailette, ou aube)
74.
LEADING EDGE PLATING ON LOW PRESSURE COMPRESSOR VANE FOR WEIGHT AND STRENGTH OPTIMIZATION
A vane including an airfoil body extending from a root to a tip defining a longitudinal axis therebetween, wherein the airfoil body includes a leading edge between the root and the tip. The vane includes a pressure side and a suction side and a recess area on the leading edge. The recess area includes a pressure side recess area and a suction side recess area, and a metal is deposited on the recess area. A method of manufacturing the vane and a gas turbine engine including the vane are also disclosed.
Described herein is a transport refrigeration unit (TRU). The TRU comprises an evaporator, and a variable frequency drive (VFD) operatively coupled to a compressor and/or an evaporator fan associated with the TRU, wherein the VFD is at least partially disposed within an evaporator compartment or fully disposed within a structure separating the evaporator compartment and a condenser compartment associated with the TRU.
Described herein is a method for tampering detection in at least one passive component of a heating, ventilation, air conditioning, and refrigeration (HVAC-R) system, the method comprising attaching one or more devices to a corresponding fastener of the at least one passive component, wherein the one or more devices are configured to transmit an alert signal based on at least one of a position of a sensing element of the one or more devices, vibration detections between the one or more devices and the at least one passive component, and/or unresponsiveness of at least one neighboring device, determining, by a controller, a tamper state of the at least one passive component based on the alert signal, and transmitting, by the controller, an electronic control signal to at least one of the one or more devices and/or the HVAC-R system based on the tamper state.
A Heating Ventilation and Air Conditioning (HVAC) burner assembly is disclosed. The HVAC burner assembly includes one or more burners comprising a downstream side and an inlet disposed on an upstream side. An inlet manifold, in fluid communication with the inlet of the one or more burner, is adapted to supply a primary air-fuel mixture to the inlet of the one or more burner. At least one mechanical blower is in fluid communication with the inlet manifold. The at least one mechanical blower includes an impeller adapted to receive and mix a fuel with primary air for generating the primary air-fuel mixture.
F23D 14/04 - Brûleurs à gaz avec prémélangeurs, c.-à-d. dans lesquels le combustible gazeux est mélangé à l'air de combustion en amont de la zone de combustion du type à induction, p. ex. becs Bunsen
F23C 1/00 - Appareils à combustion spécialement adaptés à la combustion de plusieurs sortes de combustibles simultanément ou alternativement, au moins un des combustibles étant fluide ou étant un combustible solide en suspension dans l’air
F23D 14/60 - Dispositifs pour le réglage simultané du gaz et de l'air de combustion
F23L 9/02 - Passages ou ouvertures pour introduire l'air secondaire nécessaire à la combustion complète du combustible l'air étant introduit au-dessus du foyer
F23N 1/02 - Régulation de l'alimentation en combustible conjointement au réglage de l'amenée d'air
A system for identifying a failure of the primary load path in an actuator. The system includes a first strain gauge configured to be mounted to a static portion and to measure vibrations of the static portion and a second strain gauge configured to be mounted to a nut assembly and to measure vibrations of the nut assembly. The system comprises a processor configured to identify a failure of the primary load path by comparing the measured vibrations of the static portion and the measured vibrations of the nut assembly.
A gas turbine engine includes a turbine section, a turbine case, an inner case, and a damping seal baffle. The turbine section extends along a rotational axis of the gas turbine engine. The turbine case includes a cantilevered inner wall. The cantilevered inner wall extends circumferentially about the rotational axis. The cantilevered inner wall extends between and to an upstream axial end and a downstream axial end. The upstream axial end is disposed at and downstream of the turbine section. The cantilevered inner wall forms a first sealing surface and a second sealing surface. The inner case extends and the damping seal baffle extend circumferentially about the rotational axis. The damping seal baffle is mounted to the inner case. The damping seal baffle is disposed in contact with one or both of the first sealing surface or the second sealing surface.
A sensor excitation circuit includes a voltage driver circuit and a short-circuit protection circuit. The voltage driver circuit selectively conducts electrical current via a driver output in response to a first operating voltage exceeding a driver voltage threshold (V1be). The short-circuit protection circuit includes a protection semiconductor switching device and a temperature compensation circuit. The protection semiconductor switching device limits the electrical current through the voltage driver circuit in response to switching on when a second operating voltage exceeds a protection voltage threshold (V2be). The temperature compensation circuit is connected to the protection semiconductor switching device, and is configured to limit a variation of the protection threshold voltage (V2be) in response to exposing the protection semiconductor switching device to different temperatures.
H03K 17/0814 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension sans réaction du circuit de sortie vers le circuit de commande par des dispositions prises dans le circuit de sortie
H03K 17/14 - Modifications pour compenser les variations de valeurs physiques, p. ex. de la température
H03K 17/60 - Commutation ou ouverture de porte électronique, c.-à-d. par d'autres moyens que la fermeture et l'ouverture de contacts caractérisée par l'utilisation de composants spécifiés par l'utilisation, comme éléments actifs, de dispositifs à semi-conducteurs les dispositifs étant des transistors bipolaires
82.
ENVIRONMENTAL CONTROL SYSTEM WITH MIXED BLEED AND AMBIENT PACK
An air conditioning system of a vehicle includes a plurality of inlets operable to receive a plurality of mediums. The plurality of inlets include a first inlet operable to receive a first medium and a second inlet operable to receive a second medium. The air conditioning system additionally include an outlet and a thermodynamic device operably coupled to the plurality of inlets and to the outlet. The thermodynamic device includes a compressor, a first turbine, and a second turbine, operably coupled by a shaft. The second turbine includes a plurality of flow paths. The plurality of flow paths of the second turbine are fluidly coupled to an upstream component in parallel relative to a flow of the first medium.
A system is provided including a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system, wherein the first power supply is referenced to an input ground associated with the system. The system includes a programmable device configured to control at least a second output voltage of a second power supply associated with the system, wherein the second power supply is referenced to an output ground associated with the system. The programmable device is powered based on the first output voltage.
H02M 1/08 - Circuits spécialement adaptés à la production d'une tension de commande pour les dispositifs à semi-conducteurs incorporés dans des convertisseurs statiques
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
84.
EMI EMISSION CONTROL ON LOW POWER SUPPLIES IN A MOTOR DRIVE APPLICATION
A system is provided including a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system, wherein an input to the first power supply is referenced to an input ground associated with the system and the first output voltage is referenced to a first output ground associated with the system. The system includes a programmable device configured to control a second output voltage of a second power supply associated with the system, wherein an input to the second power supply is referenced to the input ground associated with the system and the second output voltage is referenced to a second output ground associated with the system. The programmable device is powered based on the first output voltage.
H02P 7/29 - Dispositions pour réguler ou commander la vitesse ou le couple de moteurs électriques à courant continu pour réguler ou commander individuellement un moteur dynamo-électrique à courant continu en faisant varier le champ ou le courant d'induit par commande maîtresse avec puissance auxiliaire utilisant des tubes à décharge ou des dispositifs à semi-conducteurs utilisant des dispositifs à semi-conducteurs commandant l'alimentation de l'induit seulement utilisant la modulation d'impulsions
85.
EMI EMISSION CONTROL ON DC-DC CONVERTERS IN A MOTOR DRIVE APPLICATION WITH MULTIPLE ISOLATED INPUT VOLTAGES AND OUTPUT VOLTAGES
A system includes a pulse width modulation controller configured to control a first output voltage of a first power supply associated with the system. The first power supply is referenced to a first input ground associated with the system and the first output voltage is referenced to a first output ground associated with the system. The system includes a programmable device configured to configured to control a second output voltage of a second power supply associated with the system. The second power supply is referenced to a second output ground associated with the system. The programmable device is powered based on the first output voltage.
H02M 1/44 - Circuits ou dispositions pour corriger les interférences électromagnétiques dans les convertisseurs ou les onduleurs
H02M 1/00 - Détails d'appareils pour transformation
H02M 1/08 - Circuits spécialement adaptés à la production d'une tension de commande pour les dispositifs à semi-conducteurs incorporés dans des convertisseurs statiques
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
An electrical power-transfer system for an engine includes first and second engine shafts. The system also includes a planetary gear system having a sun gear, a ring gear, a plurality of planetary gears enmeshed with the sun gear and the ring gear, and a carrier supporting the plurality of planetary gears, where the carrier is configured for connection to be driven by the first engine shaft. The system further includes a first electrical machine connected to be driven by the ring gear to generate electrical power, a second electrical machine connected to drive the sun gear, and a third electrical machine configured to receive electrical power generated by the first electrical machine and operable as a motor to drive the second engine shaft.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventeur(s)
Wu, Peggy
Abrégé
A course of action (CoA) monitoring system comprises a sensor and a computing system. The sensor is configured to monitor tasks included in a course of action (CoA) performed by a human operator in an environment. The computing system is in signal communication with the sensor. The computing system includes a database that stores a plurality of reference CoAs defined by reference tasks having an intended target goal, and stores a trained task-based distributional semantic model configured to determine an intent similarity of the operator performing the tasks included in the CoA during real-time. The computing system inputs the monitored tasks determined by the sensor into the trained task-based distributional semantic model to determine a deviation between the reference tasks and the monitored tasks.
Hamilton Sundstrand Space Systems International, Inc (USA)
Inventeur(s)
Zhu, Tianli
Sharon, John A.
Ventura, Anthony Patrick
Emerson, Sean C.
Dardas, Zissis A.
Zhang, Weilong
Abrégé
A method of forming a fuel cell layer includes forming a separator plate including a plurality of corrugations defining a plurality of anode flow channels at a first side of the separator plate and a plurality of cathode flow channels at a second side of the separator plate opposite the first side. A support layer is formed, including a porous portion and a solid portion at least partially surrounding the porous portion. The support layer and the separator plate are stacked, and the support layer is secured to the separator plate via a field-assisted sintering or spark plasma sintering (FAST) process.
H01M 8/0254 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs caractérisés par la forme ondulé ou dentelé
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
H01M 8/1246 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé caractérisés par le procédé de fabrication ou par le matériau de l’électrolyte l'électrolyte étant constitué d’oxydes
A method of manufacturing a fibre-reinforced polymer structure. The method comprises providing a tubular mandrel with a roughened outer surface having an average surface roughness of at least 2 μm; applying one or more tows of continuous fibre to the roughened outer surface of the tubular mandrel under tension and introducing a polymer matrix resin either with or to the continuous fibre; and curing the polymer matrix resin to form a tubular fibre-reinforced polymer casing. The roughened outer surface of the tubular mandrel provides a high friction interface with the one or more tows of continuous fibre to mitigate slipping as the one or more tows of continuous fibre are applied to the tubular mandrel.
B29C 70/32 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau sur un moule, un gabarit ou un noyau rotatifs
B29C 53/60 - Enroulement et assemblage, p. ex. enroulement en spirale hélicoïdal en utilisant des surfaces de formage internes, p. ex. des mandrins
An electromagnetic sensor system and a method for sensing distance to a conductive target. The sensor system has filtering circuitry, a first sensor having a first electromagnetic sensor coil driven with a first alternating current at a first predetermined frequency, and a second sensor having a second electromagnetic sensor coil driven with a second alternating current at a second predetermined frequency. The second predetermined frequency is offset from the first predetermined frequency by an offset amount. The first sensor outputs a first signal having a component that is that is indicative of a distance from the first electromagnetic sensor coil to the conductive target, and the filtering circuitry applies a low-pass filter to the first signal. The low-pass filter has a cut-off frequency that is below the offset amount such that a component of the first signal caused by inductance between the first and second electromagnetic sensor coils is attenuated.
G01B 7/02 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile
A flight control system for an aircraft. The flight control system includes a thrust lever configured to control a thrust magnitude for the aircraft during flight. The thrust lever is in the form of a control stick that can be moved along a first direction to control the thrust magnitude. The thrust lever is also configured to control a yaw angle of the aircraft during flight. The control stick, or at least a portion of the control stick, can be twisted to control the yaw angle of the aircraft.
A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. An ultrasonic horn is arranged on the thermoplastic patch. The thermoplastic patch is vertically between the thermoplastic aerospace component and the ultrasonic horn. The thermoplastic patch contacts the ultrasonic horn. The thermoplastic patch is continuous ultrasonic welded to the thermoplastic aerospace component using the ultrasonic horn.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29C 65/08 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des vibrations ultrasonores
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A valve unit (10) comprising: a main valve (12) that alternately connects an exhaust port (14a) and a compressed air supply source (22) to a compressed air device; a main valve casing (14) that houses the main valve (12); a dew condensation prevention cover (16) that covers the outside of the main valve casing (14) and forms a cover air flow path (18) together with the main valve casing (14); and a cover air supply port (32) that communicates with one end of the cover air flow path (18) and supplies a portion of compressed air supplied from the compressed air supply source (22).
Although it is desirable to perform imaging after knowing the state of respiration during X-ray testing, such imaging has not been carried out in actual medical sites at present. In addition, since the respiration state and information indicating under what respiration state the testing has been performed have not been stored along with a testing image, it had not been clear how much the respiration state has an effect on the test result during imaging. This X-ray imaging apparatus comprises: an X-ray imaging unit; a millimeter wave radar that irradiates a subject; a display unit that displays an X-ray image obtained by the X-ray imaging unit; and a control unit that displays, on the display unit, an output provided by the millimeter wave radar and a shutter time of the X-ray imaging unit. The X-ray imaging apparatus, by recording the state at the time of imaging instead of suppressing the movement of the body of the subject at the time of imaging, increases reproducibility, eliminates an increase in exposure amount due to re-testing, and provides great additional material when interpreting images.
A61B 6/00 - Appareils ou dispositifs pour le diagnostic par radiationsAppareils ou dispositifs pour le diagnostic par radiations combinés avec un équipement de thérapie par radiations
A61B 5/11 - Mesure du mouvement du corps entier ou de parties de celui-ci, p. ex. tremblement de la tête ou des mains ou mobilité d'un membre
A61B 5/113 - Mesure du mouvement du corps entier ou de parties de celui-ci, p. ex. tremblement de la tête ou des mains ou mobilité d'un membre se produisant au cours de la respiration
A61B 6/46 - Agencements pour l’interface avec l’opérateur ou avec le patient
A turboshaft engine is provided and includes a turbine shaft, an output shaft and a combined speed ratio stage and torque measuring system. The combined speed ratio stage and torque measuring system includes a rigid assembly, a sensor system and first and second bearings. The rigid assembly includes a torque tube, a first gear-speed ratio stage to transmit gear-reduced or gear-increased torque from the turbine shaft and to the torque tube and a second gear-speed ratio stage to transmit gear-reduced or gear-increased torque from the torque tube to the output shaft. The sensor system measures twist of the torque tube. The first and second bearings support the rigid assembly.
G01L 5/12 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de la poussée axiale d'un arbre tournant, p. ex. matériel de propulsion
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F16H 1/20 - Transmissions à engrenages pour transmettre un mouvement rotatif sans engrenages à mouvement orbital comportant plus de deux organes engrenés
F16H 57/04 - Caractéristiques relatives à la lubrification ou au refroidissement
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
96.
SYSTEM AND METHOD FOR APPLYING TRIM BALANCE TO A MODULE OF THE GAS TURBINE ENGINE
A system for applying balancing trim to a module of a gas turbine engine, the module having a compressor having a forward shaft and an aft hub, a turbine connected to the aft hub, and the turbine having a turbine case and an aft shaft, the system having: a support bracket that mounts to the turbine case and supports the module when testing for unbalances, wherein the support bracket has: an outer periphery; outer mounting apertures at the outer periphery, wherein the outer mounting apertures are sized to receive fasteners to connect the support bracket to the turbine case; a center aperture defined by an inner periphery, wherein the center aperture is sized to receive the aft hub; and weight positioning slots defined between the outer mounting apertures and the center aperture; and wherein the outer periphery and the inner periphery are axially spaced apart from each other.
An assembly for an aircraft propulsion system includes an engine, an aircraft aerostructure, and a heat exchanger. The engine includes a coolant system. The aircraft aerostructure forms a fuel tank for the engine. The aircraft aerostructure includes an aerostructure skin including an interior skin side and an exterior skin side. The interior skin side forms a bottom side of the fuel tank. The exterior skin side forms an aerodynamic surface of the aircraft aerostructure. The heat exchanger is disposed at the aerostructure skin. The heat exchanger includes a heat exchanger body forming a coolant passage. The coolant passage extends through the heat exchanger body between and to an inlet and an outlet. The inlet and the outlet are connected in fluid communication with the coolant system.
A direct current (DC) voltage monitoring circuit includes a switch mode power supply, a transformer, and a rectifier circuit. The switch mode power supply provides an input voltage. The transformer includes a primary winding in signal communication with the switch mode power supply. The transformer stores energy induced by a primary voltage applied across the transformer by the input voltage (Vin) in response to the switch mode power supply operating in the “ON” state, releases the energy as a secondary voltage to be used as an output voltage in response to the switch mode power supply operating in the “OFF” state. The rectifier circuit generates a monitored voltage indicative of the input voltage in response to the switch mode power supply operating in the “ON” state, and rectifies the output voltage generated by the transformer in response to the switch mode power supply operating in the “OFF” state.
G01R 19/00 - Dispositions pour procéder aux mesures de courant ou de tension ou pour en indiquer l'existence ou le signe
H02M 3/335 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu avec transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrodes de commande pour produire le courant alternatif intermédiaire utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
A synchronous machine includes a first set of windings, including a first winding and n−1 other windings. The synchronous machine also includes a second set of windings, including a first winding and n−1 other windings. The synchronous machine further includes first inverter circuitry electrically coupled to a second end of each of the n−1 other windings of the first set, a first switch electrically coupled between the first inverter circuitry and a second end of the first winding of the first set, second inverter circuitry electrically coupled to a second end of each of the n−1 other windings of the second set, and a second switch electrically coupled between the second inverter circuitry and a second end of the first winding of the second set. In addition, the synchronous machine includes a third switch electrically coupled between the second ends of the first windings and control circuitry configured to switch the machine between parallel and series configurations.
H02P 25/18 - Dispositions ou procédés pour la commande de moteurs à courant alternatif caractérisés par le type de moteur ou par des détails de structure caractérisés par des dispositions de circuit ou par le type de câblage avec des dispositions pour la commutation des enroulements, p. ex. par des interrupteurs mécaniques ou des relais
H02P 25/22 - Enroulements multiplesEnroulements pour plus de trois phases
A sensing system and a method of sensing. The sensing system has a sensor apparatus and a target portion for sensing by the sensor apparatus. The target portion is integral with, or configured for coupling to, a component of an assembly so as to translate along an axis, and the target portion has an outer surface which has a profile that changes with distance along the axis. The sensor apparatus is configured for non-translating mounting adjacent the target portion, and has at least one distance sensor. The method comprises sensing a distance between the distance sensor and the outer surface of the target portion, wherein the sensed distance varies as the target portion translates axially, and outputting a signal in dependence on the sensed distance.
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile
