A method is disclosed for controlling an atmosphere within an aircraft. The method includes sensing, by at least one cabin occupancy sensor, a number of empty seats within a cabin of the aircraft. Data representative of the number of empty seats from the at least one cabin occupancy sensor is communicated by the at least one cabin occupancy sensor to an electronic controller. The electronic controller is in communication with a cabin air circulation system and an environmental control system. The electronic controller sends a flow command to the environmental control system and the cabin air circulation system to adjust a rate of an air inflow into the cabin based on the number of empty seats sensed by the at least one cabin occupancy sensor.
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
2.
HIGH VOLTAGE DC CONTACTOR ISOLATION VIA ELECTROMECHANICAL ACTUATION
A high voltage DC contactor control system. The system reduces/eliminates arcing in in contactors and includes a short circuit protection system operably connected to the drive voltage configured to reducing arcing between portions of the contactor. The short circuit protection system includes a first arc prevention element and a first arc prevention driver configured to cause the first arc prevention element to be disposed between the first and second portions of the first contactor to prevent arcing between them.
A ram air turbine system of an aircraft includes a ram air turbine selectably movable between a stowed position and an extended position at an aircraft, and a retraction mechanism operably connected to the ram air turbine and configured to selectably move the ram air turbine from the extended position toward the stowed position. A stow panel is separate from the aircraft and is selectably connectible to the retraction mechanism. The stow panel is configured to signal the retraction mechanism to initiate movement of the ram air turbine from the extended position.
A water separator for use in an environmental control system of an aircraft includes a coalescing channel having a curved housing. The coalescing channel has a hollow interior. A coalescing insert is arranged within the hollow interior of the coalescing channel. The coalescing insert has an upstream end, a downstream end, and plurality of fluidly distinct flow channels extending between the upstream end and the downstream end such that the plurality of fluidly distinct flow channels receive a flow of medium in parallel.
B01D 45/08 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge par inertie par projection contre les diaphragmes séparateurs
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 9/06 - 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 43/00 - Dispositions pour la séparation ou la purification des gaz ou des liquidesDispositions pour la vaporisation des résidus de fluides frigorigènes, p. ex. par la chaleur
5.
GALVANICALLY ISOLATED GAS SENSING SYSTEM FOR AEROSPACE APPLICATIONS
An aircraft sensing system includes a power and communications module, a sensor module in optical communication with the power and communications module, the sensor module being disposed in an at least partially enclosed space within the aircraft, and at least one gas sensor in communication with the sensor module, the at least one gas sensor being disposed in the at least partially enclosed space. The at least one gas sensor is configured to sense at least one flammable gas species or non-flammable gas species, and the sensor module and the at least one gas sensor are galvanically isolated from the power and communications module.
A fuel tank system is disclosed. The fuel tank system includes a fuel tank and a detection system associated with the fuel tank. The detection system includes a source device emitting light into the fuel tank and an analysis device. The analysis device includes a collection device capturing scattered light resulting from the emitted light interacting with fuel in the fuel tank and providing an optical signal corresponding to the captured scattered light. The analysis device includes an optical detection device converting the optical signal to an electronic signal representative of properties of the captured scattered light and a computing device. In one or more embodiments, the computing device generates, based on the electronic signal, data including an indication of: a presence or absence of one or more contaminants in the fuel tank, a type of the one or more contaminants, and location information of the fuel and contaminants.
An assembly for detecting agglomeration of a powder for a fire suppression system includes a vessel configured to contain a powder and a compressed gas and a plurality of piezoelectric sensors disposed in the vessel. At least one sensor of the plurality of sensors is disposed at an interface of the powder and the compressed gas when the vessel is in a filled state.
A valve system includes a valve body defining an inlet, an outlet, and a flow path connecting the inlet in fluid communication with the outlet through one or more flow paths through the valve body. A poppet is slidingly engaged to the valve body for movement along an axis, between a first position allowing flow though the flow path, and a second position blocking flow the flow path. An electrical circuit makes a path through the valve body. A controller is operatively connected to the electrical circuit, configured to monitor electrical resistance of the electrical circuit and to output a signal indicative of open or closed state of the valve based on whether electrical resistance of the electrical circuit is at a first level or at a second level.
F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme
F16K 27/02 - Structures des logementsMatériaux utilisés à cet effet des soupapes de levage
9.
KIDNEY PORT CONFIGURATIONS IN PORT PLATES FOR BALANCED VANES
A vane pump system includes a kidney port plate engaged at an axial end of a rotor and liner. The port kidney plate includes an over vane inlet port configured to be circumferentially aligned with an inlet arc segment of a circumferential cam surface of the liner for ingress of fluid to a plurality of vanes, and an over vane discharge port configured to be circumferentially aligned with a discharge arc segment of the circumferential cam surface for discharging pressurized fluid from the plurality of vanes. The kidney port plate includes at least six kidney ports radially inward from the over vane inlet port and the over vane discharge port. The kidney ports are circumferentially spaced apart from one another. The kidney ports are configured to be radially aligned with vane slots of the rotor for pressure balancing across over vane and under vane ends of the plurality of vanes.
F04C 29/12 - Dispositions pour l'admission ou l'échappement du fluide de travail, p. ex. caractéristiques de structure de l'admission ou de l'échappement
F04C 2/344 - Machines ou pompes à piston rotatif possédant les caractéristiques couvertes par au moins deux des groupes , , , ou par l'un de ces groupes en combinaison avec un autre type de mouvement entre les organes coopérants avec à la fois le mouvement défini dans l'un des groupes ou et un mouvement alternatif relatif entre les organes coopérants les organes obturateurs ayant un mouvement alternatif par rapport à l'organe interne
F04C 18/344 - Pompes à piston rotatif spécialement adaptées pour les fluides compressibles possédant les caractéristiques couvertes par au moins deux des groupes , , , , ou par l'un de ces groupes en combinaison avec un autre type de mouvement entre les organes coopérants ayant à la fois le mouvement défini dans l'un des groupes ou et un mouvement alternatif relatif entre les organes coopérants les organes obturateurs ayant un mouvement alternatif par rapport à l'organe interne
A capacitive system includes a module circuit card assembly including a first modular keying and alignment mechanism and a second modular keying and alignment mechanism. The first and second modular keying and alignment mechanisms are configured for mechanical alignment and electrical connection with a backplane circuit card assembly (CCA). A capacitor is mounted to the module circuit card assembly and is electrically connected to each of the first and second modular keying and alignment mechanisms through a charge/discharge circuit. The circuit is configured to: charge the capacitor with the module circuit card assembly connected to the backplane CCA, discharge the capacitor with the module circuit card assembly connected to the backplane CCA for providing backup power, and discharge the capacitor through a bleed resistor of the circuit upon disconnection of the module circuit card assembly from the backplane CCA.
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p. ex. batterie tampon
H01R 12/73 - Dispositifs de couplage pour circuits imprimés rigides ou structures similaires se couplant avec la bordure des circuits imprimés rigides ou des structures similaires se raccordant à d'autres circuits imprimés rigides ou à des structures similaires
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
An impeller includes a cylindrical portion defining a fluid inlet, the cylindrical portion coaxial with a rotational axis of the impeller, a hub, a shroud extending downward and radially away from the cylindrical portion and covering the hub, a plurality of vanes extending between the shroud and the hub, a fluid outlet downstream of the plurality of vanes, a plurality of doors disposed circumferentially about the cylindrical portion proximate the inlet, and a spring element attached to and disposed between each of the plurality of doors and the cylindrical portion. Each of the plurality of doors is actuatable, via the spring element, between a first state and a second state.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
An impeller includes a cylindrical portion defining a fluid inlet, the cylindrical portion coaxial with a rotational axis of the impeller, a hub, a shroud extending downward and radially away from the cylindrical portion and covering the hub, a first plurality of vanes extending between the shroud and the hub, and an extension portion disposed between the shroud and the hub and downstream of the first plurality of vanes. The extension portion includes an outer ring, and inner ring, and a second plurality of vanes extending between the outer ring and the inner ring.
A device, having: a base having an outer boundary and a plurality of base voids, formed from a first material having a first coefficient of thermal expansion (CTE); beads that line ones of the base voids, formed from a second material having a second CTE that differs from the first CTE, wherein each of the beads has a bead void; and a thermoelectric junction around the outer boundary, or within one or more of the bead voids.
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
B64C 9/24 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile par volet unique
B64C 13/40 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide
14.
COMPRESSOR SHROUD WITH CONTROLLABLE BYPASS COMPONENT FORMED OF THERMALLY ADAPTIVE MATERIALS AND A THERMOELECTRIC JUNCTION
A compressor case having a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.
F04D 27/00 - Commande, p. ex. régulation, des pompes, des installations ou des systèmes de pompage spécialement adaptés aux fluides compressibles
H10N 10/10 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c.-à-d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck
An actuator having a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.
H02N 10/00 - Moteurs électriques utilisant des effets thermiques
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
16.
AIRFOIL FORMED OF THERMALLY ADAPTIVE MATERIALS AND A THERMOELECTRIC JUNCTION
An airfoil having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.
A locking device having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.
A flow control device, having: a flow tube extending between upstream and downstream, and a neck region between the first and second ends, wherein the flow tube includes: a wall defining an outer boundary and extending longitudinally from a first end to a second end and transversely from a first side to a second side, wherein: the wall is nonmetal; the wall defines: a first segment extending longitudinally between the first and second ends and transversely from the first side to a segment junction; and a second segment extending longitudinally between the first and second ends and transversely from the second side to the segment junction; and the first segment has a first coefficient of thermal expansion (CTE) and the second segment has a second CTE that differs from the first CTE, to define a transverse CTE gradient.
A compressor assembly is provided and includes a fluid pathway, a compressor disposed and configured to compress fluid flowing along the fluid pathway and a motor configured to drive operations of the compressor. The motor includes one or more hybrid airfoil bearings to support the shaft within a housing. Each of the one or more hybrid airfoil bearings includes airfoil bearing components including a top foil immediately surrounding the shaft and additional components and passive magnetic bearing components integrated into the shaft and the additional components of the airfoil bearing components to remove a static load of the shaft on the top foil.
An automated minimum equipment list (MEL) system for an aircraft can include a control module operatively connected to a plurality of aircraft components. The control module can be configured to receive information relating to the plurality of aircraft components, and determine that one or more inoperative components exist in the plurality of aircraft components based on the information relating to the plurality of aircraft components. The control module can be configured to automatically determine whether one or more MEL dispatch conditions exist based on a stored MEL and the one or more inoperative components. The control module can be configured to control at least one of the plurality of aircraft components to configure the plurality of aircraft components to comply with at least one MEL dispatch condition if one or more MEL dispatch conditions exist to allow the aircraft to dispatch with the one or more inoperative components.
In accordance with at least one aspect of this disclosure, a system includes, an alignment comb configured to prevent rotation of a contact pin of a connector relative to the connector. In embodiments, the alignment comb can be of a non-electrically conductive material. In embodiments, the alignment comb includes, a planar portion extending along a longitudinal axis between a first end and a second end, an aperture defined in the planar portion, and a slot defined at least partially within the planar portion. Embodiments of the slots within the alignment comb allow the comb to slide along the first and second respective contact pins such that the alignment comb can be lifted to allow for application of a conformal coating on the contact pins and/or to allow soldering the contact pins to a printed wiring board.
H01R 43/20 - Appareils ou procédés spécialement adaptés à la fabrication, l'assemblage, l'entretien ou la réparation de connecteurs de lignes ou de collecteurs de courant ou pour relier les conducteurs électriques pour assembler les pièces de contact avec le socle isolant, le boîtier ou le manchon ou pour les en désassembler
H01R 12/71 - Dispositifs de couplage pour circuits imprimés rigides ou structures similaires
22.
AIRCRAFT FLOW CONTROL DEVICE FORMED OF THERMALLY ADAPTIVE MATERIALS AND A THERMOELECTRIC JUNCTION
A flow control device having: a composition gradient defining a first coefficient of thermal expansion and a second coefficient of thermal expansion that differs from the first coefficient of thermal expansion; and a thermoelectric junction operationally coupled to the composition gradient, wherein the composition gradient is formed of either of a plurality of dissimilar metals or of plastic with fillings or fibers.
F03G 7/06 - Mécanismes produisant une puissance mécanique, non prévus ailleurs ou utilisant une source d'énergie non prévue ailleurs utilisant la dilatation ou la contraction des corps produites par le chauffage, le refroidissement, l'humidification, le séchage ou par des phénomènes similaires
B64C 9/24 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile par volet unique
B64C 13/40 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide
23.
ACTUATOR FORMED OF THERMALLY ADAPTIVE MATERIAL AND A THERMOELECTRIC JUNCTION
An actuator, having: an actuator body extending between an actuator top and an actuator bottom, a top actuator support located at the actuator top and a bottom actuator support located at the actuator bottom, wherein the actuator body includes: a wall defining an outer boundary and extending longitudinally from a first end to a second end and transversely from a first side to a second side, wherein: the wall is nonmetal; the wall defines: a first segment extending longitudinally between the first and second ends and transversely from the first side to a segment junction; and a second segment extending longitudinally between the first and second ends and transversely from the second side to the segment junction; and the first segment has a first coefficient of thermal expansion (CTE) and the second segment has a second CTE that differs from the first CTE, to define a transverse CTE gradient.
H10N 10/817 - Détails structurels de la jonction la jonction étant inamovible, p. ex. obtenue par cémentation, frittage ou soudage
H10N 10/13 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c.-à-d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck caractérisés par les moyens d'échange de chaleur à la jonction
24.
AIR CYCLE MACHINE (ACM) WITH HYBRID AIRFOIL AND AUXILIARY MAGNETIC THRUST BEARINGS
A hybrid airfoil thrust bearing is provided for a shaft including a thrust disc that rotates with the shaft. The hybrid airfoil thrust bearing includes airfoil bearing components and passive magnetic bearing components. The hybrid airfoil bearing components include a first top foil immediately adjacent to a first side of the thrust disc and surrounding the shaft, first additional components, a second top foil immediately adjacent to a second side of the thrust disc and surrounding the shaft and second additional components. The passive magnetic bearing components are integrated into the thrust disc and into the first and second additional components to remove a static load of the thrust disc on the first top foil and on the second top foil.
A line replaceable unit (LRU) includes a data communication interface configured to receive identification (ID) data from an aircraft communication bus, an aircraft systems interface configured to receive aircraft systems data corresponding to an operation of at least one aircraft system, and an LRU data interface configured to receive LRU data corresponding to the LRU. The LRU further includes a processor and a memory unit. The processor processes the aircraft systems data and the LRU data and determine at least one data category. The memory unit includes a plurality of data partitions. The processor is configured to generate at least one configuration data package by combining the ID data with one or both of the aircraft systems data and the LRU data, and to store the configuration data package in a given data partition based on the data category.
A system includes an augmentor fuel pump (AFP) configured to be connected to be driven by a gearbox of an auxiliary power unit (APU). An augmentor fuel control (AFC) is connected in fluid communication with the AFP and configured to control supply of fuel to one or more engine augmentors. A controller can be operatively connected to control the APU for a startup mode, a run mode, and a powered down mode.
A fuel system includes a main fuel pump sub-system (MFP) with an inlet for receiving a supply of fuel from an inlet line. The MFP has a main outlet line configured to supply fuel to a main fuel throttle valve assembly (MFTV), a first cross-over outlet line, and a second cross-over outlet line. An augmentor fuel pump sub-system (ABFP) has an inlet connected in fluid communication with the first cross-over outlet line, and an outlet connected in fluid communication with a main augmentor supply line. A variable displacement pump sub-system (VDPP) has an inlet connected in fluid communication with the second cross-over outlet line, a first outlet line configured to connect to supply fuel to the MFTV, and a second outlet line configured to connect to supply fuel to an actuation system.
A fuel system a main fuel pump sub-system (MFP) with an inlet for receiving a supply of fuel from an inlet line. The MFP has a main outlet line configured to supply fuel to a main fuel throttle valve assembly (MFTV), and a cross-over outlet line. A variable displacement pump sub-system (VDPP) has a first inlet connected in fluid communication with the cross-over outlet line, a second inlet connected to a branch of the main outlet line, a first outlet line configured to connect to supply fuel to the MFTV, and a second outlet line configured to connect to supply fuel to an actuation system.
A power generation system includes a rotating machine having a mechanical rotational output. An electrical generator is connected to the mechanical rotational output, and has an electrical output electrically connected to a power distribution system. A generator control unit is controllably coupled to at least the electrical generator. The generator control unit includes a memory and a processor. The generator control unit is configured to operate in conjunction with an overvoltage protection unit including a redundant overvoltage operational test system. The redundant overvoltage operational test system includes an operational amplifier configured to operate as a voltage follower during a first mode of operations, and as a point of regulation gain amplifier during a redundant overvoltage operational test.
H02P 9/10 - Commande s'exerçant sur le circuit d'excitation de la génératrice afin de réduire les effets nuisibles de surcharges ou de phénomènes transitoires, p. ex. application, suppression ou changement brutal de la charge
H02P 9/00 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie
Aircraft electric machines are described. The aircraft electric machines include a laminated rotor operably connected to a shaft, the laminated rotor comprising a plurality of rotor teeth and air gaps defined between adjacent rotor teeth about a circumference of the laminated rotor, a modular stator assembly comprising at least one stator segment having a winding wrapped about a center body of the at least one stator segment, a cooling element arranged at least one of adjacent to or within the winding, and at least one power module system comprising an active rectifier and wherein the laminated rotor and modular stator are arranged as a switched reluctance rotor-stator assembly.
H02K 3/24 - Enroulements caractérisés par la configuration, la forme ou le genre de construction du conducteur, p. ex. avec des conducteurs en barre avec des canaux ou des conduits pour un agent de refroidissement entre les conducteurs
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
H02K 9/193 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p. ex. de l'huile avec des moyens de remplissage de l'agent de refroidissementDispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p. ex. de l'huile avec des moyens pour empêcher les fuites de l'agent de refroidissement
H02K 11/04 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection pour le redressement
A fuel system a main manifold with an inlet and a plurality of main manifold branches. Each valve in a plurality of valves is connected in fluid communication with a respective one of the main manifold branches in the plurality of main manifold branches to receive flow from the main manifold. Each secondary manifold in a plurality of secondary manifolds connects a single one of the valves in the plurality of valves to a pair of secondary manifold branches. Each nozzle in a plurality of fuel nozzles includes a first inlet connected in fluid communication to one of the valves through one of the secondary manifold branches, and a second inlet connected in fluid communication to a different one of the valves through a different one of the secondary manifold branches so each of the fuel nozzles has a redundant connection to the main manifold through two of the valves.
A pressure sensing system includes a housing that houses one or more pressure transducers therein. A tube is sealed to the housing at a first end of the tube. One or more pressure transducers are in fluid communication with a second end of the tube through an inner passage of the tube for sensing pressure at the second end of the tube.
G01L 19/00 - Détails ou accessoires des appareils pour la mesure de la pression permanente ou quasi permanente d'un milieu fluent dans la mesure où ces détails ou accessoires ne sont pas particuliers à des types particuliers de manomètres
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p. ex. à la pression
33.
AN AIR COOLED ELECTRIC MOTOR HAVING AN INCREASED AIRFLOW AND A METHOD FOR INCREASING THE AIRFLOW THEREIN
A method for increasing stator cooling airflow in an air cooled electric motor is provided, wherein the air cooled electric motor includes a compressor outlet housing having a motor cavity separator wall and a separator plate defining a separator plate opening, wherein the compressor outlet housing defines a separator plate cavity and a compressor rotor back-face cavity configured to receive a back-face cavity airflow. The motor cavity separator wall separates the separator plate cavity from the compressor rotor back-face cavity and defines a motor cavity separator wall through-hole which communicates the separator plate cavity with the compressor rotor back-face cavity and a motor cooling housing including a motor cooling outlet structure which defines a stator outlet cavity, wherein the separator plate is disposed to separate the stator outlet cavity from the separator plate cavity.
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
34.
ALUMINUM SHEET WITH DIELECTRIC COATING ISOLATION BARRIER
The present disclosure provides for barrier wall assemblies (e.g., isolation barrier wall assemblies having embossed aluminum sheets coated with dielectric coatings). More particularly, the present disclosure provides for barrier wall assemblies configured to be positioned between electric power distribution components (e.g., positioned between power distribution components of different voltages or different criticality so that a fault in one section or component functional group will not affect adjacent areas).
An environmental control system of an aircraft has a plurality of inlets including a first inlet for receiving a first medium and a second inlet for receiving a second medium. A thermodynamic device includes a compressor and at least one turbine and is fluidly coupled to the second inlet. A ram air circuit has a plurality of heat exchangers including a first heat exchanger and a second heat exchanger and is fluidly coupled to both the first inlet and the thermodynamic device. In a first mode, an outlet of the thermodynamic device is fluidly connected to the ram air circuit downstream from both the first heat exchanger and the second heat exchanger. In a second mode, the outlet of the thermodynamic device is fluidly connected to an inlet of one of the plurality of heat exchangers.
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
A data-enabled aircraft generator module includes a generator and a generator memory unit. The generator is configured to power an aircraft based at least in part on at least one control signal output from a generator control unit (GCU). The generator memory unit configured to exchange data with the GCU.
A pin for a core layer of a heat exchanger past which fluid flowing through the layer passes, the pin having a leading edge, a trailing edge, a first and a second end and, an outer surface between leading edge and trailing edge and the first and second ends, and wherein the pin comprises a pin core extending from the first end to the second end and defining the leading edge and the trailing edge, and a plurality of vanes extending from the pin core each vane extending between the leading edge and the trailing edge, and the vanes arranged one above another in the direction from the first end to the second end.
F28F 3/04 - Éléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des évidements, avec des ondulations les moyens faisant partie intégrante de l'élément
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
A cooling structure for a rotary electric machine. The structure includes an annular radiator body defining an axis X between a first end and a second end. The annular body has a radially inner wall and a radially outer wall and a plurality of channels defined between the radially inner wall and the radially outer wall. Each channel extends from the first end to the second end and each channel has an inner channel wall. A plurality of vanes extending inwardly into the channel from the channel wall.
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p. ex. des ponts de chaleur
H02K 9/10 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant en circuit fermé, dont une partie est à l'extérieur de l'enveloppe de la machine
A pump assembly includes a cylinder block defining a piston bore therein extending in an axial direction. A sleeve lines the piston bore. A piston is included in the piston bore, configured to reciprocate along a stroke in the axial direction within the sleeve. A piston ring is engaged circumferentially about the piston. The piston ring is fixed to the piston and is slidingly engaged to an inner surface of the sleeve.
F16J 10/04 - Surfaces de contactChemises de cylindres
F16J 9/26 - Segments de piston, leurs logementsSegments d'étanchéité de structure similaire en général caractérisés par l'emploi de matériaux particuliers
In accordance with at least one aspect of this disclosure, a pump comprises a pump rotor having a plurality of vanes therein configured to pump a fluid from a pump inlet to a pump outlet through rotation of the rotor about a rotational axis, an input shaft operatively connected to drive rotation of the rotor, and a bearing operatively connected to the input shaft configured to facilitate rotation of the input shaft. A shaft extender is operatively connected radially between the input shaft and the bearing. The input shaft includes a conical portion and the shaft extender includes a conical portion complementary to the conical portion of the input shaft. The shaft extender interfaces with at least the conical portion of the input shaft, when on the input shaft.
F04C 15/00 - Parties constitutives, détails ou accessoires des "machines", des pompes ou installations de pompage non couverts par les groupes
F04C 2/344 - Machines ou pompes à piston rotatif possédant les caractéristiques couvertes par au moins deux des groupes , , , ou par l'un de ces groupes en combinaison avec un autre type de mouvement entre les organes coopérants avec à la fois le mouvement défini dans l'un des groupes ou et un mouvement alternatif relatif entre les organes coopérants les organes obturateurs ayant un mouvement alternatif par rapport à l'organe interne
41.
SELF-ACTUATED BLEED VALVES FOR GAS TURBINE ENGINES
A bleed valve includes a housing. The housing includes an inlet and an outlet with a cylindrical flow path defined between the inlet and the outlet. A diametral plane is defined diametrically spanning the cylindrical flow path. A butterfly disc inside the housing is rotatably mounted to the housing along a rotation axis for rotation between an open position and a closed position. A link rotatably is connected to a pivot point on the butterfly disc for relative rotation of the link and the butterfly disc along a pivot axis parallel to the rotation axis. The pivot axis is on an opposite side of the diametral plane from the rotation axis.
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
F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
A method includes detecting a modulating undervoltage state having transients above an undervoltage threshold and triggering a protection upon detecting the modulating undervoltage state. The method can include detecting a steady state undervoltage condition, wherein triggering a protection includes triggering the protection upon detecting the steady state undervoltage condition or the modulating undervoltage state. A system includes a power source including a feedback sensor at a point of regulation (POR) of the power source configured to generate feedback indicative of voltage at the POR. A controller is operatively connected to receive the feedback. The controller includes controller logic that is configured perform a method as described above.
A system for extinguishing and suppressing a fire in an aircraft includes a precooler, a heat exchanger, a condenser, a gas separator, and an accumulator. The precooler is configured to receive a bleed air from an engine of the aircraft. The heat exchanger is fluidly coupled with the precooler. The condenser is configured to receive a cabin exhaust air from a passenger cabin of the aircraft. The gas separator is fluidly coupled with the condenser and is fluidly coupled with the heat exchanger. The gas separator is configured to generate a fire suppressing agent from the bleed air and the cabin exhaust air. The accumulator is fluidly coupled with the gas separator. The accumulator is configured to receive the fire suppressing agent.
A62C 3/02 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers pour des zones d'embrasement, p. ex. des incendies de forêts, des feux souterrains
A62C 5/00 - Fabrication de substances extinctrices immédiatement avant l'emploi
A62C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
F16K 31/02 - Moyens de fonctionnementDispositifs de retour à la position de repos électriquesMoyens de fonctionnementDispositifs de retour à la position de repos magnétiques
44.
Single variable displacement fuel systems with fuel oil cooler bypass and gas generator fault accommodation
A system includes an actuation pump sub-system (APS). A fuel oil cooler (FOC) is included in a first branch of a supply line. The FOC is in fluid communication to receive flow from a second outlet of the APS. The APS includes a bypass valve (BPV) in a second branch of the supply line, in parallel with the FOC and in fluid communication to allow flow from the third outlet into the supply line bypassing the FOC. A combined main and augmentor pump sub-system (CMAPS) has a main inlet connected in fluid communication with the supply line downstream of the BPV and FOC, a gas generator (GG) outlet for supplying fuel to a downstream gas generator, and an augmentor outlet for supplying fuel to a downstream augmentor.
A fluid circuit of a heat exchanger includes a core and a first header. The core is configured to receive a fluid and includes a plurality of conduits. Each of the plurality of conduits extends along a longitudinal axis from a first end portion to a second end portion. The first header is integrally formed with and fluidly connecting the plurality of conduits. Outer walls of the plurality of conduits taper outward relative to the longitudinal axes to join the first header.
F28D 1/053 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture avec des canalisations d'échange de chaleur immergées dans la masse du fluide avec canalisations tubulaires les canalisations étant rectilignes
According to an aspect of the present disclosure, an aerosol concentration sensor calibration device includes a mixing column, a sensor, and a collection vessel. The mixing column extends in a vertical orientation between an inlet at a bottom of the mixing column and an outlet at a top of the mixing column, the mixing column configured to receive a mixture of a powder and a compressed gas at the inlet. The sensor is disposed in the mixing column and configured to measure the concentration of the powder in the mixing column. The collection vessel has an inlet fluidly coupled to the outlet of the mixing column. The collection vessel is configured to collect the powder received from the mixing column.
A generator system can include a generator control unit (GCU) configured to control a generator output of a generator. The GCU can be configured to monitor the generator output for overvoltage and attenuate an overvoltage by directing at least a portion of the generator output to a heater element. The GCU can be configured to cause voltage division of the generator output between the GCU and the heater element if an overvoltage is detected to protect one or more GCU electrical components.
An air conditioning system includes an environmental control system configured to condition a flow of medium. The environmental control system includes a thermodynamic device having a compressor and at least one turbine operably coupled by a shaft and at least one heat exchanger. A secondary system has a working fluid circulating therethrough. At least one liquid loop having at least one liquid flowing therethrough is fluidly connected to the at least one heat exchanger. The environmental control system is thermally coupled to the secondary system, via the at least one liquid loop. The at least one liquid provided at an outlet of the at least one heat exchanger is operable to cool the working fluid of the secondary system.
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 system includes a burn flow line and a flow divider valve in fluid communication with the burn flow line to split flow from the burn flow line to a primary line and to a secondary line for supplying fuel to a set of primary engine nozzles and to a set of secondary engine nozzles, respectively. A sensor operatively connected to the flow divider valve to produce a feedback signal indicative of flow split between the primary line and the secondary line. A controller is operatively connected to receive the feedback signal from the senor, compare the feedback signal to a stored flow split value for a mismatch, and output an alert message upon detecting the mismatch.
HUMAN WASTE COLLECTION SYSTEM, FOR ZERO-GRAVITY CONDITIONS, THAT AUTOMATICALLY CLOSES A USED WASTE BAG SEGMENT AND PROVIDES AN UNUSED WASTE BAG SEGMENT FROM OPERATION OF A SEAT AND FLUSH ACTUATOR
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventeur(s)
Radawiec, Rochelle
Luker, Kelly
Abrégé
A human waste collection system, for zero-gravity conditions, the collection system having: a basin having a lower end that defines a lower plane and configured for being positioned against a floor and an upper end that is spaced apart from the lower end and displaced further from the plane than the lower end; a seat positioned at the upper end of the basin, the seat having a lid pivotally connected to the seat; a bag cassette disposed under the seat; and a compression ring that is movable within the basin to automatically pull an unused bag segment from the bag cassette, and push down used bags.
Embodiments of the disclosure provide a deep-mission system that includes a processor system operable to perform processor system operations that include executing a first instance of a cognitive algorithm; generating data of the deep-mission system that can be used to fine-tune the first instance of the cognitive algorithm; and transmitting the data of the deep-mission system over a deep-mission communication path to a remote station. The remote station is operable to, based at least in part on the data of the deep-mission system, perform fine-tuning operations on a second instance of the cognitive algorithm located at the remote station; generate updates to the cognitive algorithm based on the fine-tuning operations; and transmit the updates to the cognitive algorithm over the deep-mission communication path to the deep-mission system. The processor system operations further include using the updates to the cognitive algorithm to update the first instance of the cognitive algorithm.
An electrical machine assembly includes an armature assembly defining a rotational axis and a rectifier assembly including at least one diode and defining a central rectifier axis. The armature assembly is configured and adapted to be coupled with a rotor shaft for relative rotation therewith. The central rectifier axis is at a non-parallel angle relative to the rotational axis. A rectifier assembly includes a first diode and a second diode stacked with the first diode. The rectifier assembly includes an AC terminal positioned between the first diode and the second diode and a DC positive output pin electrically coupled to the first diode. A portion of the AC terminal extends outward from the rectifier assembly at a non-parallel angle relative to the central longitudinal axis of the rectifier assembly. A central longitudinal axis of the rectifier assembly can be parallel to the DC positive output pin.
A human waste collection system having a basin defining a basin cavity and a lower end that is configured for being positioned against a floor and an upper end that is displaced further from the plane than the lower end; a storage bag system disposed in the basin cavity; a seat disposed at the upper end of the basin, the seat having a lid; a suction system having a first suction conduit extending into the basin cavity, adjacent to the upper end of the basin; a controller having a user interface that has user engageable features to select between operation modes including a first mode for removing menses and solid waste and a second mode for removing urine, wherein: in the first mode, menses and solid waste is collected in the storage bag; and in the second mode, the suction system suctions urine.
An environmental control system includes a first water collector having a first drain line and a second water collector having a second drain line. The first drain line is fluidly connected to the second drain line. The environmental control system includes also includes at least one spray nozzle. An outlet of the second drain line is fluidly connected to the at least one spray nozzle.
F28F 17/00 - Enlèvement de la glace ou de l'eau des appareils échangeurs de chaleur
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 controller for an electrical drive system includes one or more electrical drives, one or more electrical loads, and a switching component configured to connect the one or more electrical drives to the one or more electrical loads in a switching configuration. The controller includes a processing module configured to receive switching data indicative of the switching configuration and analyze the switching data to determine control data for at least one of the electrical drives. The controller further includes an output module configured to output the control data to the at least one electrical drive. The at least one electrical drive is configured to use the control data to supply the electrical load/s, via the switching component, with electrical power.
B60L 15/22 - Procédés, circuits ou dispositifs pour commander la propulsion des véhicules à traction électrique, p. ex. commande de la vitesse des moteurs de traction en vue de réaliser des performances désiréesAdaptation sur les véhicules à traction électrique de l'installation de commande à distance à partir d'un endroit fixe, de différents endroits du véhicule ou de différents véhicules d'un même train pour la commande du véhicule ou de son moteur en vue de réaliser des performances désirées, p. ex. vitesse, couple, variation programmée de la vitesse avec séquence d'opérations d'interrupteurs interdépendants, p. ex. relais, contacteurs, tambour de programme
B60L 3/12 - Enregistrement des paramètres de fonctionnement
56.
COGNITIVE, LEARNING-BASED SYSTEM FOR MONITORING AND CONTROLLING MISSION PERFORMANCE
Embodiments of the disclosure provide a system for monitoring a mission. The system includes a digital ecosystem (DE) associated with the mission and positioned at a remote station. The DE, responsive to sensed data associated with deployed products positioned locally with the mission, generates performance data associated with the deployed products. A processor is provided and includes local processor resources located at the mission, along with remote processor resources at the remote station. The processor operations are performed and include executing a first cognitive algorithm to, responsive to a portion of the performance data, generate an initial cognitive output associated with an initial cognitive output action; prior to initiating the initial cognitive output action associated with the initial cognitive output, displaying to a user the initial cognitive output; and responsive to receiving user feedback on the initial cognitive output, executing post-user-feedback operations based on the user feedback.
A system includes a main pump having a main pump shaft configured to connect to a gear box for driving the main pump with rotational power from the gear box in a run mode, and for driving the gear box with rotational power from the main pump in a start mode. The system includes a first fuel line with an inlet configured to connect to connected in fluid communication with a fuel source. The first fuel line includes a first branch in fluid communication with the main pump, and a second branch. A start pump is connected in fluid communication with the second branch of the first fuel line. A second fuel line connects the start pump in fluid communication with a pump management valve (PMV). A third fuel line connects the main pump in fluid communication with the pump management valve.
A rotor assembly is provided and includes a rotor impeller and rotor shaft. The rotor impeller includes a blade section and a forward section. The rotor shaft includes an aft section at which the rotor shaft terminates. The aft section is directly attached to the forward section of the rotor impeller. The blade section includes a converging blade configured to converge to a point with a minimized internal diameter (ID).
A rotor assembly is provided and includes a two-piece rotor impeller and a rotor shaft. The two-piece rotor impeller includes a blade section and a forward section, which is connected to the blade section. The rotor shaft includes an aft section at which the rotor shaft terminates. The aft section is directly attached to the forward section of the rotor impeller. The blade section includes a converging blade configured to converge to a point with a minimized internal diameter (ID).
F04D 29/28 - Rotors spécialement adaptés aux fluides compressibles pour pompes centrifuges ou hélicocentrifuges
F04D 17/02 - Pompes à flux radial spécialement adaptées aux fluides compressibles, p. ex. pompes centrifugesPompes hélicocentrifuges spécialement adaptées aux fluides compressibles ayant des étages non centrifuges, p. ex. centripètes
A circuit for detecting discrete inputs includes a first line replaceable unit (LRU). A second LRU includes an LRU circuit that includes a power source, a diode set coupled to the power source, a resistor R3 connecting from a node Vc between the diode set and the first LRU to ground, and a logic detection and processing circuit. The logic detection and processing circuit is operably connected to the diode set, and is configured to detect a state of the first LRU based on a detected voltage. The detected voltage is either open, or 28-Volts.
G01R 19/165 - Indication de ce qu'un courant ou une tension est, soit supérieur ou inférieur à une valeur prédéterminée, soit à l'intérieur ou à l'extérieur d'une plage de valeurs prédéterminée
H02H 1/00 - Détails de circuits de protection de sécurité
H02H 7/20 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour équipement électronique
A controller, a circuit, an aircraft electrical system and a method for controlling an isolated (inductor-inductor-capacitor) LLC power converter circuit. The circuit comprising an isolated transformer, and a first switch operable as a synchronous rectifier on a secondary side of the transformer. The controller comprises a current determination module configured to determine a primary winding current on a primary side of the isolated transformer; and a processing module configured to use the determined primary winding current in a processing algorithm to output a first control signal to configure the first switch on the secondary side of the isolated transformer to determine a waveform of a secondary winding current of the isolated transformer.
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 1/00 - Détails d'appareils pour transformation
H02M 3/00 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu
A system can include a first controllable valve configured to output a first control pressure on one or more first pressure control lines, a second controllable valve configured to output a second control pressure on one or more second pressure control lines, and a valve assembly. The valve assembly can be configured to direct the first control pressure to a first functional system and the second control pressure to a second functional system in a first state, direct the first control pressure to both of the first functional system and the second functional system in a second state, and direct the second control pressure to both of the first functional system and the second functional system in a third state.
F15B 13/044 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par des moyens commandés électriquement, p. ex. des solénoïdes, des moteurs à couple
A start-up architecture for a fuel cell includes a fuel cell having a hydrogen input and an oxygen source input and a hydrogen output for outputting residual hydrogen not used in the fuel cell reaction. The hydrogen output is connected to the hydrogen input via a mixer in a hydrogen loop. The architecture also includes a bypass loop, bypassing the mixer, between the hydrogen output and the hydrogen input and a control valve (CV1) in the bypass loop between the hydrogen output and the hydrogen input. A hydrogen start-up stored energy source is connected to the hydrogen input via a hydrogen start-up line and an oxygen source start-up stored energy source is connected to the oxygen source input via an oxygen source start-up line. During a fuel cell start up process, the architecture is configured to provide hydrogen and oxygen to the startup lines.
H01M 8/04302 - Procédés de commande des éléments à combustible ou des systèmes d’éléments à combustible appliqués pendant des périodes spécifiques appliqués pendant le démarrage
H01M 8/04014 - Échange de chaleur par des fluides gazeuxÉchange de chaleur par combustion des réactifs
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
A system can include a first controllable valve, a second controllable valve, a transfer valve, and a transfer control system. The first controllable valve can be configured to output a control pressure on one or more first pressure control lines. The second controllable valve can be configured to output a control pressure on one or more second pressure control lines. The transfer valve can be in fluid communication with the first controllable valve and the second controllable valve. The transfer valve can be configured to move between a first position, a second position, and a third position.
G05D 16/20 - Commande de la pression d'un fluide caractérisée par l'utilisation de moyens électriques
F15B 13/044 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par des moyens commandés électriquement, p. ex. des solénoïdes, des moteurs à couple
A hybrid bearing assembly is provided and includes stationary components, a shaft disposed to rotate relative to the stationary components, passive magnetic bearing components integrated into the shaft and the stationary components to generate passive magnetic force to resist radial movement of the shaft relative to the stationary components and an active damping system. The active damping system includes a stationary coil, a magnetic element rotatable with the shaft to induce current in the stationary coil and a circuit electrically coupled with the stationary coil. The circuit is configured to determine from the current an attitude change of the shaft and the magnetic element and to apply damping current to the stationary coil to resist the attitude change.
Waste management systems and capture funnels thereof are described. The waste management systems include a waste container, a reclamation system, a capture funnel, and a hose fluidly connecting the capture funnel to each of the waste container and the reclamation system. The capture funnels include a funnel having an inlet end and an outlet end, wherein the inlet end has a non-circular shape, a skirt arranged at the inlet end, and a capture insert installed within the funnel.
Hamilton Sundstrand Space Systems International, Inc. (USA)
Inventeur(s)
Radawiec, Rochelle
Luker, Kelly
Abrégé
Waste management systems and capture funnels for use therewith are described. The waste management systems include a waste container, a reclamation system, a capture funnel, and a hose fluidly connecting the capture funnel to each of the waste container and the reclamation system. The capture funnels include a funnel having an inlet end and an outlet end, a water-function trigger actuatable to dispense water into the funnel, and an air-function trigger actuatable to dispense air into the funnel.
A harmonic drive, having: a ground ring; a first flex spline extending axially from the ground ring; a first input shaft that is radially exterior to the first flex spline, the first input shaft includes a first wave generator that engages the first flex spline; a second flex spline, radially within the first flex spline and rotationally coupled to the first flex spline, a second input shaft that is radially within the second flex spline, the second input shaft includes a second wave generator that engages the second flex spline; an output shaft coupled to the second flex spline, the first flex spline includes a first spline that faces radially inward; the second flex spline includes a second spline that faces radially outward; a circular gear having a third spline that face outwardly and engages the first spline; a fourth spline that faces radially inward and engages the second spline.
A method of additively manufacturing an aircraft part, having steps of: forming a base, defining a shape of the aircraft part, out of first thermoplastic polymer; forming a lower support surface onto discrete locations of the base by printing a mixture of a second thermoplastic polymer and a catalyst compound formed with metal onto the discrete locations, such that the lower support surface is formed with cavities; and forming an upper support surface by depositing, via electrolysis deposition, a metal plating onto the lower support surface along the discrete locations, to thereby form the aircraft part.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
C25D 9/04 - Revêtement électrolytique autrement qu'avec des métaux avec des matières inorganiques
70.
METAL PLATED ADDITIVELY MANUFACTURED PLASTIC ACM ROTORS WITH INTERNAL THERMALLY ADAPTIVE STRUCTURE
A method of forming a rotor for an ACM, having steps of forming a base having: a first section adjacent to an ACM diffuser shroud when installed; a second section forming a seal disposed against an ACM aft frame member when installed; a third section connected to an ACM compressor rotor shaft when installed; a fourth section connected to an ACM tie rod when installed; a fifth section between the second and fourth sections, forming the base includes: printing thermoplastic polymer surfaces from thermoplastic polymers disposed against each other, the thermoplastic polymer surfaces having different CTEs; forming a lower support section on the base by printing along the discrete sections a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the rotor by depositing on the lower support section along the discrete sections, via electrolysis deposition, a metallic coating.
B29C 64/112 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant des gouttelettes individuelles, p. ex. de buses de jet
A method of forming a housing for an ACM, having steps of: forming a base: a first section adjacent to a seal of an ACM compressor rotor when installed; a second section that is fixed to an ACM forward frame member when installed; a third section adjacent to a bearing and sleeve disposed around an ACM compressor rotor shaft when installed, forming the base includes: printing thermoplastic polymer surfaces from thermoplastic polymers that are disposed against each other, the thermoplastic polymer surface having differing CTEs; forming a lower support section on the base by printing, layer by layer, along the plurality of discrete sections of the base a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the housing by depositing on the lower support section, along each of the discrete sections, via electrolysis deposition, a metallic coating.
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
B33Y 70/10 - Composites de différents types de matériaux, p. ex. mélanges de céramiques et de polymères ou mélanges de métaux et de biomatériaux
72.
METAL PLATED ADDITIVELY MANUFACTURED PLASTIC ACM SHAFTS WITH INTERNAL THERMALLY ADAPTIVE STRUCTURE
Forming an ACM shaft by: forming a base of (i) a thrust shaft having a first section connecting with an ACM tie rod when installed; a second section connecting with an ACM motor rotor when installed; a third section forming a shaft joint that connects adjacent portions of the thrust shaft; or (ii) a compressor rotor shaft having a fourth section connecting with an ACM tie rod support when installed; and fifth section connecting with the ACM motor rotor when installed; forming the base includes: printing polymer surfaces having differing CTSs from polymers disposed against each other; forming a lower support section on the base by printing along the discrete sections a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the shaft by depositing on the lower support section, along the discrete sections, via electrolysis deposition, a metallic coating.
B29C 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
B33Y 70/10 - Composites de différents types de matériaux, p. ex. mélanges de céramiques et de polymères ou mélanges de métaux et de biomatériaux
B33Y 80/00 - Produits obtenus par fabrication additive
73.
METAL PLATED ADDITIVELY MANUFACTURED PLASTIC ACM SHROUDS WITH INTERNAL THERMALLY ADAPTIVE STRUCTURE
Forming a shroud for an ACM by: forming a base having discrete sections including: a first section defining connecting features for connecting with a fixed ACM structure; a second section positioned adjacent to a compressor rotor when installed in the ACM; and a third section disposed adjacent to a drive ring bearing when installed in the ACM; forming the base includes: printing thermoplastic polymer surfaces, respectively from thermoplastic polymers, disposed against each other, a first thermoplastic polymer surface having a CTE, and a second thermoplastic polymer surface having a second CTE; forming a lower support section on the base by printing along the discrete sections of the base a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the shroud by depositing on the lower support section, along each of the discrete sections, via electrolysis deposition, a metallic coating.
B29C 64/30 - Opérations ou équipements auxiliaires
B29C 64/106 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux
A method of forming a seal plate for an ACM, having steps of: forming a base having a first section exposed to flow from an ACM first stage turbine inlet when installed; a second section secured to an ACM compressor shroud; a third section secured to a first stage nozzle and ACM shroud when installed; a fourth section that is adjacent to a rotor blade of the ACM compressor rotor when installed, forming the base includes: printing thermoplastic polymer surfaces from thermoplastic polymers, that are disposed against each other, the thermoplastic polymer surfaces having differing CTEs; forming a lower support section on the base by printing along the discrete sections a mixture of a third thermoplastic polymer and a catalyst formed with metal; and forming an upper support section on the seal plate by depositing on the lower support section, along the discrete sections, via electrolysis deposition, a metallic coating.
B29C 64/30 - Opérations ou équipements auxiliaires
B29C 64/106 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux
B33Y 40/20 - Posttraitement, p. ex. durcissement, revêtement ou polissage
B33Y 80/00 - Produits obtenus par fabrication additive
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
C25D 7/00 - Dépôt électrochimique caractérisé par l'objet à revêtir
In accordance with at least one aspect of this disclosure, a system includes a fuel line, an electrically driven fuel pump configured to supply fuel to a first fuel line branch and a second fuel line branch, and a selector valve disposed in the fuel line at a juncture of a first fuel line branch and a second fuel line branch configured to communicate the electrically driven fuel pump with the first fuel line branch or the second fuel line branch based on a position of the selector valve. In a first position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the first fuel line branch to supply fuel to a combustor of the engine and drive a high pressure shaft at a first speed. In a second position, the selector valve is configured to fluidly connect the electrically driven fuel pump with the second fuel line branch to drive a hydraulic rotation unit configured to drive the high pressure spool of the engine at a second speed different from the first speed.
A fuel system includes a main fuel pump sub-system (MFP) with an inlet for receiving a supply of fuel from an inlet line. The MFP has a main outlet line configured to supply fuel to a main fuel throttle valve assembly (MFTV), and a cross-over outlet line. An augmentor fuel pump sub-system (ABFP) has an inlet connected in fluid communication with the cross-over outlet line, and an outlet connected in fluid communication with a main augmentor supply line. A actuation fuel pump sub-system (AFP) has an inlet connected in fluid communication with a branch of the main outlet line, an outlet line with a first outlet line branch configured to connect to supply fuel to the MFTV, and a second outlet line branch configured to connect to supply fuel to an actuation system.
A system includes a main supply line and a thermal recirculation pump in fluid communication with the main supply line for supplying the thermal recirculation pump. The thermal recirculation pump is connected in fluid communication with a thermal recirculation line for providing fluid at an elevated pressure to the thermal recirculation line relative to the main supply line. A thermal recirculation control is connected in fluid communication to be supplied from the thermal recirculation line. A cooler system of one or more coolers is connected in fluid communication with a cooler supply line of the thermal recirculation control.
In accordance with at least one aspect of this disclosure, a pump system for an aircraft includes, a cylinder barrel configured to rotate within a pump housing of a pump, and a plurality of pistons seated within a respective bore defined in the cylinder barrel. Each piston further includes a piston ring disposed at an end thereof configured to form a hydrodynamic seal with an inner surface of the respective bore. Each respective piston ring is of silicon nitride. In embodiments, the piston ring can include a chamfer on at least a leading edge of the piston ring. In embodiments, the piston ring can include a cut therethrough configured to allow for thermal expansion of the piston ring.
F16J 9/28 - Segments de piston, leurs logementsSegments d'étanchéité de structure similaire en général caractérisés par l'emploi de matériaux particuliers de matériaux non métalliques
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
A system includes a variable displacement pump (VDP) in fluid communication with an inlet line and with an outlet line. The VDP includes a variable displacement mechanism configured to vary pressure to the outlet line. The system includes a relief valve (RV) having a control pressure port and an RV inlet port in fluid communication with the outlet line and an RV outlet in fluid communication with a bypass line. The system includes an actuator operatively connected to the control pressure port of the RV to change function of the RV between a first function and a second function. The first function is a high pressure relief valve function and the second function is as a wind milling bypass function.
A system includes a rotor shaft rotatable about an axis, a disconnect shaft nested at least partially within an interior of the rotor shaft, and a journal shaft selectively rotatably coupled to the disconnect shaft. A vibration damping mechanism is arranged between the rotor shaft and the journal shaft. The vibration damping mechanism includes a thrust journal bearing affixed to the rotor shaft and a thrust washer mounted to the journal shaft. A biasing mechanism is operably coupled to disconnect shaft to bias the thrust washer into frictional engagement with the thrust journal bearing.
A method of operating an environmental control system pack of a vehicle includes providing a thermodynamic device including a compressor and a plurality of turbines including a first turbine and a second turbine mounted to a shaft and a plurality of valves fluidly coupled to the thermodynamic device, operating at least one of the plurality of valves to supply a medium to the first turbine and the second turbine in series during a mode of operation, and operating at least one of the plurality of valves to supply a first portion of the medium to the first turbine and to supply a second portion of the medium to the second turbine independently from the first portion of the medium in location another mode of operation.
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
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 9/06 - 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 41/20 - Disposition des soupapes, p. ex. de soupapes marche-arrêt ou de soupapes de régulation de débit
82.
RADIO FREQUENCY SIGNAL AND POWER THROUGH DIELECTRIC WAVEGUIDE FOR GALVANIC ISOLATION TO HYDROGEN SENSORS
Apparatus and associated methods relate to galvanically isolating one or more sensors from a controller. Power and control signals are provided to an isolation system via RF electromagnetic waves transmitted from the controller to the isolation system via a dielectric waveguide. The received RF electromagnetic waves are converted into an RF electrical signal and then the RF electrical signal is separated into power and control signal components. The RF power signal component is rectified and regulated so as to provide power to the isolation system. A sensor interrogator is electrically connected to one or more sensors so as to receive sense signals therefrom. The sensor interrogator generates a data signal indicative of one or more physical metrics of a potentially hazardous environment in which the one or more sensors are situated. The data signal is converted to RF electromagnetic waves, which are transmitted, via the dielectric waveguide, to the controller.
A nut for use in an actuator assembly having a rotatable screw includes an outer nut portion and an inner nut portion removably coupled to the outer nut portion. The inner nut portion is rotatably couplable to the rotatable screw. At least one anti-rotation pin is positionable between the outer nut portion and the inner nut portion to restrict rotation of the inner nut portion relative to the outer nut portion.
F16B 33/00 - Caractéristiques communes aux boulons et aux écrous
F16B 39/16 - Blocage des vis, boulons ou écrous dans lequel le verrouillage s'effectue après vissage par écrous de blocage, c.-à-d. contre-écrous le filetage du contre-écrou étant différent de celui de l'écrou de serrage
84.
DC-TO-DC CONVERTER AND CONFIGURABLE OUTPUT MAGNITUDE AND POLARITY
A DC-to-DC converter includes an input configured to receive a DC input voltage, an output having a positive rail and a negative rail, wherein the negative rail is configured for connection to a negative terminal of the DC input voltage source, a bypass capacitor having first end connected to a first node and a second end connected to a second node and two coupled inductors, the two coupled inductors including a first inductor that has a first end connected to the input and a second end connected to the first end of the bypass capacitor at the first node, the two coupled inductors also including a second inductor that has a first end connected to the second end of the bypass capacitor at the second node and a second end connected to a third node. The converter includes switches that allow control of the polarity and magnitude of the output.
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
H02M 3/00 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu
A method of power switching includes receiving a command from an external aircraft controller to power an aircraft load from an aircraft voltage bus. The method includes in response to the command from the external aircraft controller, controlling a relay to connect or disconnect an aircraft voltage bus from an aircraft load. Controlling the relay includes current monitoring the relay and voltage monitoring the relay power switching. The method can include receiving temperature feedback indicative of temperature of the relay, and using the temperature feedback for at least one of controlling the relay and/or prognostic and health monitoring. The method can include outputting feedback to the external aircraft controller relating to status, operation, and health of the relay.
A system includes a solid state power controller (SSPC) including a plurality of switching devices connected in parallel. A gate driver is operatively connected to control the plurality switching devices together so all of the switching devices in the plurality of switching devices either close to pass current through the SSPC, or open to prevent current passing through the SSPC in a normal operation mode. A fail open test circuit is operatively connected to individually control a respective gate of each of the switching devices in the plurality of switching devices for testing the plurality of switching devices individually for a fail OPEN condition.
In accordance with at least one aspect of this disclosure, a rectifier assembly includes, at least, a first diode disposed between a first bus bar and a second bus bar. The rectifier assembly further includes, a first thermal management structure and a second thermal management structure. The first thermal management structure is configured to electrically connect the first bus bar to the first diode and be in thermal communication between the first bus bar and a first side of the first diode to transfer heat between the first bus bar and the first diode. The first thermal management structure is configured to transfer heat between the first bus bar and the first thermal management structure. The first thermal management structure is also configured to allow a fluid to flow therethrough to transfer heat from the first thermal management structure to the fluid flowing therethrough.
H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif
In accordance with at least one aspect of this disclosure, a system includes an airflow line, a main compressor disposed in the airflow line configured to receive a ram air flow and supply a compressed air flow to the air flow line, and a motor operatively connected to drive the main compressor. An air cycle machine is disposed in the airflow line downstream of the main compressor configured to receive the compressed airflow and supply a cooled cabin airflow to an aircraft cabin. A cooling line tap disposed in the airflow line downstream of the air cycle machine configured to communicate a flow of cooling air to the motor from the airflow line to supply a portion of the cooled cabin airflow to one or more portions of the motor as motor cooling air via a first cooling airflow line.
H02K 9/10 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant en circuit fermé, dont une partie est à l'extérieur de l'enveloppe de la machine
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
H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs
89.
ELECTROWETTING AND THERMOELECTRICS ASSISTED TWO PHASE COOLING OF POWER ELECTRONICS USING INTEGRATED COOLING
Disclosed herein is a two-phase cooling electrowetting thermosyphon assembly and method of use thereof. The two-phase cooling electrowetting thermosyphon assembly provides cooling in the absence of gravity and/or in variable orientations of gravitational forces. The assembly combines a thermosyphon with an electrowetting electrode and a condenser. In certain embodiments, a Peltier cooler is incorporated into the assembly.
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
H10N 19/00 - Dispositifs intégrés ou ensembles de plusieurs dispositifs comprenant au moins un élément thermoélectrique ou thermomagnétique couvert par les groupes
An n-level flying capacitor multi-level buck converter, for converting a DC input voltage into a DC output voltage provided at a load. The n-level flying capacitor multi-level buck converter is configured to: operate a first and second pairs of switching elements in a sequence to selectively apply a portion of the input voltage across the output filter; and operate the first and second pairs of switching elements such that each switching element turns on when a voltage across the switching element is zero.
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
H02M 1/00 - Détails d'appareils pour transformation
H02M 3/07 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des résistances ou des capacités, p. ex. diviseur de tension utilisant des capacités chargées et déchargées alternativement par des dispositifs à semi-conducteurs avec électrode de commande
A heat exchanger core layer having a first end, a second end opposite the first end, a first side extending between the first end and the second end and a second side, extending between the first end and the second end opposite the first side, and a divider extending from the first end and extending towards the second end between the first side and the second side, wherein a first flow region is formed between the first side and the divider, a second flow region is defined between the divider and the second side and a turnaround region is defined adjacent the second end between the first flow region and the second flow region; the layer having a plurality of first flow channels in the first flow region for directing a fluid flow, in use, in a first direction from the first end to the turnaround region.
F28D 7/16 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation les canalisations étant espacées parallèlement
A fuel cell system includes a fuel cell unit having an air inlet, a fuel inlet and an electrical energy outlet and a fuel cell exhaust outlet and a turbo-compressor unit to convert air from an air supply to compressed inlet air for the fuel cell unit. The turbo-compressor unit comprising a turbine and a compressor connected to a common rotatable shaft. The system also includes means for obtaining conditioned air exhausted from an enclosed space and directing the conditioned exhaust air to the turbine of turbo-compressor unit such that the conditioned exhaust air is expanded by the turbine causing rotation of the shaft and corresponding rotation of the compressor, means for providing air from the air supply to the compressor to be compressed and output from the compressor unit and provided as compressed inlet air to the air inlet of the fuel cell unit.
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
B60L 50/72 - Détails de construction des piles à combustible spécialement adaptées aux véhicules électriques
B64D 11/06 - Aménagements ou adaptations des sièges
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
H01M 8/04119 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration des réactifs gazeux avec apport simultané ou évacuation simultanée d’électrolyteHumidification ou déshumidification
Testing a gasket within a groove formed around a top of an enclosure and covered by a lid, including steps of: positioning a needle of a probe within a notch formed in an outer wall that surrounds the groove; and: injecting input current through the probe; comparing input voltage from the probe in the notch and an output voltage induced in conductive fasteners that secure the lid to the enclosure, to determine that a difference in the voltages is within a predetermined range, where voltage at the fasteners is measured with another probe; or injecting the input current into the fasteners; and comparing the input voltage at the fasteners with the output voltage induced in the gasket and measured via the probe in the notch, to determine that the difference in the voltages is within the predetermined range, where voltage at the fasteners is measured with the another probe.
An electronic rotor “lock” that can be implemented within an electric motor system by selecting closing a subset of switches within an inverter of the motor drive system to create a circulatory current path that can generate a force that acts to oppose any external movement of the rotor.
H02P 3/02 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques Détails
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques
A pin for a core layer of a heat exchanger. The pin extends from a first pin end to a second pin end and has an outer surface between the first and second pin ends. The pin includes a plurality of indentations in the outer surface and a plurality of protrusions on the outer surface.
F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
F28F 3/08 - Éléments construits pour être empilés, p. ex. pouvant être séparés pour leur nettoyage
A flapper check valve includes a valve seat body. Two flapper valve portions are each mounted on their own shaft to the valve seat body, and pivotable between open and closed positions. The flapper valve portions pivot in a common rotational direction to the open position and to the closed position. A fluid systems is also disclosed.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F16K 15/03 - Soupapes, clapets ou valves de retenue à corps de soupapes rigides guidés et élément de fermeture à charnière
97.
Surge protection and failsafe circuit for DC-DC converter
A Direct Current (DC)-DC converter includes an input capacitor connected across a positive input terminal and a return input terminal. A DC-DC converter circuit is connected across the positive input terminal and the return input terminal. A current limiting failsafe circuit includes a current limiting portion connected across the positive input terminal and the return input terminal and a failsafe portion connected to a sensed voltage output. The failsafe portion is configured to control a current limit function of the current limiting portion and configured to force the DC-DC converter circuit into an off state in response to retripping of the current limiting portion.
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02M 1/44 - Circuits ou dispositions pour corriger les interférences électromagnétiques dans les convertisseurs ou les onduleurs
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
98.
FIRE EXTINGUISHERS, FIRE SUPPRESSION SYSTEMS, AND METHODS OF CONTROLLING FLOW OF FIRE SUPPRESSANT AGENTS
A fire extinguisher includes a source conduit, a flow control device connected to the source conduit, and a supply conduit. The supply conduit is connected to the flow control device, is fluidly coupled therethrough to the source conduit, and is thermally coupled to the source conduit to communicate heat between pressurized fire suppression agent entering the flow control device through the source conduit and expanded fire suppression agent issuing from the flow control device through the supply conduit. Fire suppression systems and methods of controlling flow of fire suppressant agents are also described.
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
A62C 37/36 - Commande des installations de lutte contre l'incendie le signal de déclenchement étant émis par un détecteur distinct de la tuyère
A62C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
99.
NONUNIFORM WALL THICKNESS PROFILE FOR TEARDROP PRESSURE VESSELS
A pressure vessel includes a body defined by a cross-sectional shape along a plane transverse to a centerline. The cross-sectional shape includes an inner surface defining an interior void and a wall extending from the inner surface to an outer surface defining an exterior of the body. The inner surface includes an arcuate region and a gabled region. The gabled region forms a curved interior peak opposite a center of the arcuate region. The arcuate region and the gabled region together define a teardrop shape. The wall includes a curved segment along the arcuate region having a curved segment minimum thickness at a location opposite the interior peak, an apex aligned with the interior peak and having an apex thickness, and thickened regions adjacent intersections between gabled region and the arcuate region and having greater radial thickness than the curved segment minimum thickness.
A system for vane pitch actuation includes an electric motor with a rotary output shaft defining a drive axis. A worm shaft defines a drive axis, and is operatively connected to be driven in rotation about the drive axis by the rotary output shaft of the electric motor. A sync ring is defined about an engine axis that is orthogonal to the drive axis. The sync ring is configured to rotate about the engine axis over a range of positions for driving a plurality of variable pitch stator vanes to each have a pitch based on position of the sync ring. The sync ring includes a plurality of gear teeth for actuation of the sync ring by the electric motor.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
