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
2.
METAL PLATED ADDITIVELY MANUFACTURED PLASTIC ACM HOUSINGS WITH INTERNAL THERMALLY ADAPTIVE STRUCTURE
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
3.
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 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
An assembly for maintaining the pitch angle of a flight control surface for an aircraft. The assembly includes a shaft comprising a screw thread and defining a shaft axis, and a nut. The nut includes a housing, a barrel located in the housing and comprising a screw thread for engaging with the screw thread of the shaft, and at least one locking element located in the housing. The housing comprises a radially inner cam surface adjacent to the locking element. The barrel is configured to rotate relative to the housing when the screw thread of the barrel is engaged and rotating with the screw thread of the shaft so as to move the locking element along the cam surface from a disengaged position in which the locking element is spaced from the screw thread of the shaft, to an engaged position.
B64C 13/32 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des mécanismes à cames
A method is provided during which a thermoplastic rib is arranged with a thermoplastic spar. A first flange of the thermoplastic rib is abutted against the thermoplastic spar. The first flange of the thermoplastic rib is ultrasonic welded to the thermoplastic spar using a tilted ultrasonic horn. A centerline of the tilted ultrasonic horn is angularly offset from the first flange of the thermoplastic rib by an acute angle during the ultrasonic welding.
A method includes converting audio to text, converting the text to a taxi path, and using a look-up table (LUT) to check for obstructions in the taxi path. The method includes issuing a warning if there are one or more obstructions in the taxi path based on the LUT or else refraining from issuing a warning if there are not one or more obstructions in the taxi path based on the LUT. Converting audio to text can include using a machine learning model. Before converting the audio to text, the method can include checking communications between a pilot and air traffic control (ATC) for keywords relevant to taxiing. Converting audio to text can be performed upon detecting the keywords in the audio. The audio can include words spoken by ATC to the pilot and/or words spoken by the pilot to ATC.
Apparatus and associated methods relate to improving measurement of metrics determined by laser air-data systems subject to unwanted background light. Such measurements are improved by estimating and excising the unwanted background light from the total light received by an optical receiver which receives a Doppler-shifted reflected portion of a projected beam of light backscattered by aerosols and air molecules of an atmosphere. The background light is estimated using a background-light rejection filter that receives the light received by the optical receiver after it has been filtered by a vapor cell filter and separates the light received by the optical receiver into a beam sampling portion and a complementary non-beam portion. The non-beam sampling portion is used to estimate the background light portion within the beam sampling portion, which also contains the Doppler-shifted reflected portion of the projected beam used for calculating the metrics of air data.
Apparatus and associated methods relate to improving measurement of metrics determined by laser air-data systems subject to unwanted background light. Such measurements are improved by estimating and excising the unwanted background light from the total light received by an optical receiver which receives a Doppler-shifted reflected portion of a projected beam of light backscattered by aerosols and air molecules of an atmosphere. The background light is estimated using a background-light rejection filter that separates the light received by the optical receiver into a beam sampling portion and a complementary non-beam portion. The beam sampling portion has band-pass wavelengths that include the Doppler-shifted reflected portion and a portion of the unwanted background light. The complementary non-beam portion includes background light of wavelengths outside of the band-pass wavelengths of the beam sampling portion. The non-beam sampling portion is used to estimate the unwanted background light included in the beam sampling portion.
Apparatus and associated methods relate to measuring metrics of a contrail produced by an aircraft engine. To measure such metrics, a beam of light is projected into a projection volume that intersects an exhaust path of the aircraft engine. Light from a reception volume that intersects the exhaust path of the aircraft engine is received. An intersection volume is formed by an intersection of the reception volume and the projection volume. The light received includes a reflected portion of the projected beam backscattered by the atmosphere from within the intersection volume. The reflected portion of light received is used to determine whether a contrail is forming within the intersection volume. An alert is generated in response to determination that a control is forming within the intersection volume.
Apparatus and associated methods relate to improving measurement of metrics of air data of an atmosphere outside an aircraft. Such measurements are improved by estimating a daylight portion of light received by an optical receiver configured to receive a reflected portion of the projected beam backscattered by the atmosphere. Estimation of the daylight portion is performed using a daylight filter. The daylight filter receives the light received by the optical receiver after it has been filtered by a vapor cell filter and separates the light, as filtered, into a beam sampling portion and a complementary non-sampling portion. The non-beam sampling portion includes wavelengths immediately adjacent to the beam sampling portion. The non-beam sampling portion is used to estimate the daylight portion within the beam sampling portion, which also contains the reflected portion of the projected beam used for calculating the metrics of air data.
G01S 17/95 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la météorologie
G01P 5/26 - Mesure de la vitesse des fluides, p. ex. d'un courant atmosphériqueMesure de la vitesse de corps, p. ex. navires, aéronefs, par rapport à des fluides en mesurant l'influence directe du courant de fluide sur les propriétés d'une onde optique de détection
G01S 7/481 - Caractéristiques de structure, p. ex. agencements d'éléments optiques
G01S 17/58 - Systèmes de détermination de la vitesse ou de la trajectoireSystèmes de détermination du sens d'un mouvement
In accordance with at least one aspect of this disclosure, a system includes a wiper drive shaft configured to drive a wiper arm between a start position and an end sweep position. The wiper drive shaft includes external threads defined therein and at a distal end thereof. An axial length of the external threads along the wiper drive shaft defines the start position and the end sweep position, and a total desired sweep angle between the start position and end sweep position. The wiper drive shaft includes and a first hard stop groove and a second hard stop groove, each defined at a respective first axial offset and a second axial offset from the external threads to define a first hard stop position and second hard stop position.
The present invention provides an air conditioning system comprising: a compressor, a four-way valve, a first heat exchanger, a second heat exchanger, a third heat exchanger, a reservoir, a first solenoid valve, a second solenoid valve, and a check valve connected through pipelines, wherein the four-way valve has a first port for communicating with an exhaust port of the compressor, a second port for communicating with a first end of the first heat exchanger, a third port for communicating with a first end of the second heat exchanger, and a fourth port for communicating with a second end of the third heat exchanger; wherein a second end of the first heat exchanger is connected to a first end of the reservoir, and the second end of the first heat exchanger is connected to the first end of the reservoir.
F24F 11/84 - Systèmes de commande caractérisés par leurs grandeurs de sortieDétails de construction de tels systèmes pour la commande de la température de l’air fourni en commandant l’apport en fluides échangeurs de chaleur aux échangeurs de chaleur au moyen de valves
F24F 11/65 - Traitement électronique pour la sélection d'un mode de fonctionnement
F24F 13/30 - Agencement ou montage d'échangeurs de chaleur
A sensor-equipped bolt (200A, 200B) which is used for fastening an object comprises: a bolt shaft (211A, 211B) that includes a threaded portion (211Aa, 211Ba, 211Bb) where threading is formed and a non-threaded portion (211Ab, 211Bc) where threading is not formed; and a sensor (220A, 220B) that is attached to the bolt shaft and detects deformation of the bolt shaft. The bolt shaft includes, in the outer circumferential surface of the non-threaded portion, a recess (213Aa, 213Ba) that is recessed from the outer circumferential surface of the non-threaded portion and accommodates the sensor. The cross-sectional area of the bolt shaft at the position of the recess is equal to or greater than the effective cross-sectional area of the bolt shaft at the threaded portion.
G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
F16B 31/02 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture signalant ou limitant la charge de traction
Systems and methods for cooling electric machines are provided. A method for cooling an electric machine includes receiving a flow of air, expanding and cooling the air from the flow of air using a turbine, conveying the flow of air from the turbine through the electric machine to extract heat from the electric machine using the flow of air, and drawing the flow of air through the electric machine using an air mover.
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs
16.
LUBRICANT PUMP SYSTEM AND METHOD FOR AIRCRAFT ENGINE
Lubricant pump systems and associated methods for aircraft engines are provided. The method includes receiving an input torque, dividing the input torque between a first load path receiving a first portion of the input torque, and a second load path receiving a second portion of the input torque. A first lubricant pump of the aircraft engine is driven via the first load path using the first portion of the input torque. A second lubricant pump of the aircraft engine is driven via the second load path using the second portion of the input torque. When a malfunction of the second lubricant pump occurs, the method includes ceasing to drive the first lubricant pump and the second lubricant pump using the input torque.
An assembly is provided for a gas turbine engine. This assembly includes a rotating structure of the gas turbine engine, a stationary structure of the gas turbine engine and a volume formed by and extending between the rotating structure and the stationary structure. The rotating structure is rotatable about an axis. The rotating structure includes a seal land and a fluid nozzle. The stationary structure includes a seal element. The seal element is arranged with the seal land to form a seal assembly that seals an annular gap between the stationary structure and the rotating structure. The volume is adjacent the seal element and the seal land. The fluid nozzle is configured to direct a fluid jet out from the rotating structure and into the volume.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
A speed sensor for a rotating component in an aircraft engine includes a phonic wheel, mounted for rotation with the rotating component, including a disk body having a first axial face, a second axial face axially spaced apart from the first axial face, a radial surface extending axially between the first and second axial faces and extending circumferentially, and teeth extending from the radial surface, the teeth being circumferentially spaced apart by circumferential gaps defined between the teeth. A shroud extends in a circumferential direction about the phonic wheel. The shroud extends radially to obstruct the circumferential gaps defined between the teeth of the phonic wheel the first and/or second axial faces. A sensor is mounted proximate to the phonic wheel to generate a sensor signal when the teeth of the phonic wheel pass the sensor as the phonic wheel rotates.
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
20.
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 shape forming tool for pre-carbonization compression of a fibrous preform is provided, comprising a female forming tool, a first plug, a second plug, and a wedge, each configured to be received by a die recess of the female forming tool. A first tapered surface of the wedge is configured to engage the first plug and the second tapered surface of the wedge is configured to engage the second plug. In response to the first tapered surface of the wedge engaging the first plug and the second tapered surface of the wedge engaging the second plug, the first plug and the second plug, respectively, are configured to move laterally towards opposing sides of the female forming tool and/or vertically toward a bottom side of the female forming tool to compress the fibrous preform into a shaped body.
B29C 70/46 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs"
B29C 70/54 - Parties constitutives, détails ou accessoiresOpérations auxiliaires
B29C 70/56 - Tensionnage des renforcements avant ou pendant le façonnage
B29K 105/06 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts
22.
HORIZONTAL ULTRASONIC WELDING THERMOPLASTIC MATERIAL
A repair method is provided during which a thermoplastic patch is arranged on a thermoplastic aerospace component. The thermoplastic patch contacts the thermoplastic aerospace component. The thermoplastic patch is horizontal ultrasonic welded to the thermoplastic aerospace component using an ultrasonic horn.
B29C 73/10 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p. ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés utilisant des pastilles d'obturation appliquées à la surface de l'objet
B29C 65/08 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des vibrations ultrasonores
B29C 65/72 - Assemblage d'éléments préformésAppareils à cet effet par des opérations combinées, p. ex. soudage et couture
23.
BREAKOVER VEHICLE OPERATOR SEAT CONVERTIBLE TO NON-BREAKOVER CONFIGURATION
A seat frame structure for a rotorcraft or other vehicle operator seat is convertible between non-breakover and breakover configurations. The structure includes fixed frame members mounted to the cabin floor (e.g., via floor tracks) and pivoting frame members for supporting the operator seat, the pivoting and fixed frame members connected by a bushing assembly. The seat frame structure includes a tilt controller with coupling pins extending into the fixed frame members, locking the structure into the non-breakover configuration. A control lever mounted to the seat frame structure controls the coupling pins via connecting cables; the occupant of the seat may, via the control lever, transition the seat frame structure to the breakover configuration by retracting the coupling pins into the pivoting frame members, enabling rearward rotation of the pivoting frame members (e.g., at least 80 degrees, or contact with the cabin floor).
A double-shear secured vehicle seating assembly includes an operator seat (e.g., for a pilot or operator of a rotorcraft or like vehicle) and a seat frame structure via which the operator seat is secured to floor tracks in the cabin floor. Floor track grippers attached to the underside of the seat frame structure “grip” the floor tracks by extending down and around an upper portion of the floor track. The floor track grippers are further united with the floor tracks by locking pins that extend through holes in the grippers as well as the floor track itself, which includes a rail and a plurality of evenly spaced holes extending through the rail. The locking pin fully pierces the floor track gripper on a first side, fully piercing the aligned hole in the rail, and at least partially piercing the floor track gripper on the opposing side, creating the double-shear condition.
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.
Methods and systems for failure prediction using analysis of oil or other lubricant. Raw data about feature(s) of each of a plurality of particles filtered from a fluid sample are used to categorize each particle into one of a plurality of categories, each category being defined by one or more of: chemical composition, size and morphology. Particle physical characteristics in each category are quantified to obtain a set of categorized data. The categorized data are compared with historical data. Results of the comparing are evaluated to generate a prediction of any failure or mechanism of failure.
A fuel injector is provided for a turbine engine. This fuel injector includes a fuel nozzle. The fuel nozzle includes a feed passage, a first exit passage and a gallery. The feed passage extends in the fuel nozzle to a feed passage location along the gallery. The first exit passage extends in the fuel nozzle to a first exit passage location along the gallery. The gallery extends in the fuel nozzle circumferentially about an axis from a first end of the gallery to a second end of the gallery. A size of the gallery decreases and then increases as the gallery extends circumferentially about the axis away from the feed passage location and towards the first exit passage location.
An integrally bladed rotor for an aircraft engine includes a hub and a circumferential array of blades extending from the hub. Each blade has an airfoil extending from a gaspath side of a platform provided at a periphery of the hub. The platform has a radial thickness T. An edge of the airfoil is disposed at an axial distance L1 from an adjacent axial edge of the platform. A projection extends radially inwardly from an interior side of the platform opposite to the gaspath side. The projection has an axial thickness t, a radial height h from the interior side of the platform, and an axial distance L2 from the adjacent axial edge of the platform. T is a radial thickness of the platform at an axial location of the projection, and
An integrally bladed rotor for an aircraft engine includes a hub and a circumferential array of blades extending from the hub. Each blade has an airfoil extending from a gaspath side of a platform provided at a periphery of the hub. The platform has a radial thickness T. An edge of the airfoil is disposed at an axial distance L1 from an adjacent axial edge of the platform. A projection extends radially inwardly from an interior side of the platform opposite to the gaspath side. The projection has an axial thickness t, a radial height h from the interior side of the platform, and an axial distance L2 from the adjacent axial edge of the platform. T is a radial thickness of the platform at an axial location of the projection, and
0
.
2
≤
T
t
≤
5
;
1
≤
h
t
≤
10
;
and
0
≤
L
2
L
1
≤
1
0
.
F01D 5/06 - Rotors à plus d'un étage axial, p. ex. du type à tambour ou à disques multiplesLeurs parties constitutives, p. ex. arbres, connections des arbres
An adjustable torque limiting fastener has a shank extending along an axis from a proximal end to a distal end. The fastener has a head at the proximal end of the shank. A torque limiter is integrated between the head and the shank. The torque limiter is operable to rotatably decouple the head from the shank when a torque applied to the head exceed a maximum torque. The maximum torque is set by a spring plunger integrated to the head for friction engagement with the proximal end of the shank.
F16B 31/02 - Assemblages à vis spécialement modifiés en vue de résister à une charge de tractionBoulons de rupture signalant ou limitant la charge de traction
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.
An assembly is provided for an aircraft propulsion system. This assembly includes a center body, a scarfed inlet structure and an inlet passage. The scarfed inlet structure extends circumferentially about the center body. The inlet passage is radially between and formed by at least the center body and the scarfed inlet structure. A first component of the assembly is configured to rotate about an axis relative to a second component of the assembly between: (A) a first position where a metering portion of the inlet passage has a first area; and (B) a second position where the metering portion has a second area. The first component is one of the center body or the scarfed inlet structure, and the second component is the other one of the center body or the scarfed inlet structure.
F02C 7/042 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction à géométrie variable
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
33.
METHOD AND APPARATUS FOR JOINING THERMOPLASTIC COMPOSITE COMPONENTS
A method of blind welding thermoplastic composite components is provided that includes: providing a first thermoplastic composite having a FTPC bonding surface, a second thermoplastic composite having a STPC bonding surface, and an interface layer; disposing the interface layer between the FTPC STPC bonding surfaces; applying a normal force to the outer surface of the first thermoplastic composite component; applying an electromagnetic field to at least portions of the first and second thermoplastic composite components and the interface layer while the normal force is applied, and maintaining the application of the electromagnetic field until the first and second thermoplastic composite components and the interface layer create a weld pool; and removing the application of the electromagnetic field after the weld pool is created.
B29C 65/14 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage par énergie ondulatoire ou rayonnement corpusculaire
B29C 65/34 - Assemblage d'éléments préformésAppareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p. ex. un "élément de soudage perdu"
34.
METHOD AND APPARATUS FOR JOINING THERMOPLASTIC COMPOSITE COMPONENTS
A method of blind welding thermoplastic composite components is provided. The method includes providing a first and second thermoplastic composite components each having a bonding surface. The first thermoplastic composite component has a first melting temperature and the second thermoplastic composite component has a second melting temperature; providing an interface layer having a third melting temperature; disposing the interface layer between the bonding surfaces; disposing an external susceptor adjacent to the outer surface of the first thermoplastic composite component, wherein the external susceptor includes a central segment and lateral segments that respond differently to an application of an EM field; applying a normal force to the first component external susceptor without an application of an opposing second normal force to the second thermoplastic component; and applying an electromagnetic field to the central and lateral segments using an inductor.
A porosity gradient fibrous preform includes at least one first fabric-resin layer and a second fabric-resin layer, each including a plurality of fibers and a resin. The second fabric-resin layer is positioned on top of the at least one first fabric-resin layer. A weight ratio percentage of the resin sequentially decreases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform to create a path through the porosity gradient fibrous preform for infiltration of a fluid.
C04B 35/83 - Fibres de carbone dans une matrice carbonée
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 37/18 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de feuilles ou de panneaux individualisés
A porosity gradient fibrous preform includes a plurality of fabric-resin layers and a plurality of pore formers. Each fabric-resin layer includes a plurality of fibers and a resin. A volume of the plurality of pore formers sequentially increases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform. The pore formers can be pyrolyzed from the preform to create paths through the porosity gradient fibrous preform for infiltration of a fluid.
B29C 44/02 - Moulage par pression interne engendrée dans la matière, p. ex. par gonflage ou par moussage pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés
B29C 44/34 - Éléments constitutifs, détails ou accessoiresOpérations auxiliaires
B29C 70/08 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts comprenant uniquement des renforcements, p. ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
37.
POROSITY GRADIENT PREFORM ARCHITECTURE FOR HIGH TEMPERATURE COMPOSITES
A porosity gradient fibrous preform includes a first fabric-resin layer having a first plurality of fibers and a first resin and a second fabric-resin layer having a second plurality of fibers and a second resin. The second fabric-resin layer is positioned further outward from the center of the porosity gradient fibrous preform than the first fabric-resin layer. In response to the porosity gradient fibrous preform being heated to a curing temperature, the first resin and/or the second resin is configured to separate into a fusible resin and a plurality of fugitive pore formers. Accordingly, a volume of the fugitive pore formers sequentially increases from a center of the porosity gradient fibrous preform toward an outer surface of the porosity gradient fibrous preform.
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 37/06 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par le procédé de chauffage
B32B 37/20 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de bandes continues
A windshield wiper system for an aircraft includes a wiper arm and a wiper shaft with a first end connected to a base of the wiper arm. An electric motor is coupled to the wiper shaft to rotationally drive the wiper shaft. The windshield wiper system also includes a brake system. The brake system includes an electromagnet comprising an energized mode and a de-energized mode. The brake system also includes an anti-rotation assembly with a first element and a second element. The first element is connected directly to the wiper shaft. The second element is rotationally stationary relative the wiper shaft and the first element. The second element is configured to interlock with the first element to prevent rotation of the first element and the wiper shaft when both the electromagnet is in the de-energized mode and the wiper arm is in a park position.
An in-vehicle camera rear case includes: a rear case main body that is connected to a front case in an opposed manner, is provided with an insertion hole, is opened at one surface, and has a box shape; a connector module that electrically connects an external connector to an in-vehicle camera substrate, is inserted in the insertion hole, and is engaged with the rear case main body, and at least a part of which is made of a resin; and a housing that is engaged with the connector module. The rear case main body includes: boss members that are provided on a surface of an internal surface side rear case upper surface; and crimping reception surfaces provided on an external surface side rear case upper surface. The flange reception surface boss members are crimped in a state of being engaged with the connector module.
The present application provides a vehicle thermal management system and a transportation refrigeration vehicle. The vehicle thermal management system comprises: an air conditioning system, configured with a compressor, a first three-way valve, a first outdoor heat exchanger, an indoor heat exchanger, a regulating valve, an intermediate heat exchanger, and a first throttling element, a second throttling element, and a third throttling element connected through pipelines, and a battery cooling system, configured with a second outdoor heat exchanger, a battery cooling device, and a second three-way valve connected through pipelines.
A disclosed method for controlling an aircraft propulsion system includes modeling dynamics of a propulsion system, formulating a problem for achieving the target output as system of linear equations constrained by physical limits of the propulsion system, and generating a solution to the system of linear equations with a singular value decomposition solver module that utilizes Jacobi's singular value decomposition. A control command is generated based on the solution that includes instructions for adjusting a propulsion system operating parameter toward a target output and the propulsion system us operated according to the control command.
F02C 9/50 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande du flux du fluide de travail
F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
42.
METHOD OF MITIGATING VIBRATIONS IN A SEAL COMPONENT
A method of mitigating vibrations of a seal component of a bearing cavity, the method includes: injecting gas jets into the bearing cavity to disrupt vortices causing the vibrations of the seal component, the vortices having a frequency and an amplitude, the gas jets one or more of: decreasing the amplitude of the vortices; and modifying the frequency of the vortices to be offset from a natural frequency of the seal component.
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
47.
POROSITY GRADIENT PREFORM ARCHITECTURE FOR HIGH TEMPERATURE COMPOSITES
A porosity gradient fibrous preform includes a first fabric-resin layer having a first plurality of fibers and a first resin and a second fabric-resin layer having a second plurality of fibers and a second resin, the second fabric-resin layer being positioned further outward from a center of the porosity gradient fibrous preform than the first fabric-resin layer. The first resin is different from the second resin so as to generate sequentially increasing porosity in the preform prior to a CVI densification step. The sequentially increasing porosity can be achieved, for example, by selecting resins for each layer with sequentially increasing moisture content, by selecting resins for each layer with sequentially decreasing char yield, and/or adding black carbon powder to interior located fabric-resin layers.
B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
B32B 37/18 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de feuilles ou de panneaux individualisés
The present utility model proposes a refrigeration display cabinet, comprising: a cabinet; a display rack fixed inside the cabinet; an air channel arranged at least partially surrounding the display rack; a partition mounted in the air channel to separate the air channel into an inner air channel and an outer air channel, wherein the partition is provided with an opening for connecting the inner air channel and the outer air channel; an evaporator arranged in the inner air channel, wherein the side of the evaporator is located at or near the opening; and a damper assembly fixed at the opening of the partition, wherein the damper assembly is capable of opening or closing the opening. The refrigeration display cabinet according to the present utility model can defrost the evaporator simultaneously from the bottom and side thereof during the defrosting mode, thus improving defrosting efficiency.
A detection system (10) for hazard detection is provided. The detection system (10) includes a control loop (16); an addressable base unit (18) connected to the control loop (16), the base unit (18) including a first near-field communication module (22) storing a unit address; and a mounting unit (20) removably coupled to the base unit (18), the mounting unit (20) including a second near-field communication module (24) operable to read the unit address from the first near-field communication module (22) and store the unit address so that the mounting unit (20) is thereby addressable via the control loop (16).
G08B 17/06 - Déclenchement électrique de l'alarme, p. ex. utilisant un interrupteur actionné thermiquement
G08B 25/00 - Systèmes d'alarme dans lesquels l'emplacement du lieu où existe la condition déclenchant l'alarme est signalé à une station centrale, p. ex. systèmes télégraphiques d'incendie ou de police
50.
TEST BLADE FOR GAS TURBINE ENGINE AND METHOD OF MAKING
A test blade for a blade release test, including: an airfoil extending radially from a platform; and a root portion secured to the platform, the root portion having an elongated opening extending longitudinally from a leading edge of the root portion towards a trailing edge of the root portion, wherein the elongated opening has a width extending along the leading edge of the root portion that is greater than or equal to 3 times a radial height of the elongated opening.
A gas turbine engine includes a compressor section, a combustor and a turbine section. At least one case surrounds at least one of the compressor section and the turbine section. The case is formed from sheet metal and includes a case wall and at least one potential displacement location due to vibration. At least one retaining ring is assembled to the case and biased against the case wall at the at least one potential displacement location to dampen vibration.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
A housing assembly for a rotary engine, has: a rotor housing having a peripheral inner face, a first face and a second face; a first side housing secured to the first side and defining a first inner side face fac; and a second side housing secured to the second side and defining a second inner side face, the rotor cavity bounded axially between the first side housing and the second side housing, one or more of the rotor housing, the first side housing, and the second side housing having: a main body made of a base material; and an external layer made of an alloy including the base material, a wear-resistance of the alloy greater than that of the base material, the external layer defining one or more of the first face, the second face, the first inner side face, and the second inner side face.
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
54.
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 refrigerant circuit for cooling a Variable Frequency Drive (VFD) unit of an air conditioning system includes a condenser for condensing refrigerant vapor. A heat sink includes a supply conduit assembly adapted to receive a first portion of a subcooled refrigerant fluid from the condenser and a discharge conduit assembly adapted to discharge a superheated refrigerant vapor to an accumulator. The subcooled refrigerant fluid transitions to the superheated refrigerant vapor upon absorbing heat from the VFD unit thermally coupled to the heat sink. The accumulator supplies the superheated refrigerant vapor to a compressor. An expansion valve expands a second portion of the condensed refrigerant fluid. An evaporator evaporates the expanded second portion of the refrigerant fluid. A compressor compresses the evaporated refrigerant vapor from the evaporator and the superheated refrigerant vapor received from the accumulator.
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
F25B 49/02 - Disposition ou montage des dispositifs de commande ou de sécurité pour machines, installations ou systèmes du type à compression
An air conditioning system includes a vapor compression cycle having a plurality of components including a compressor, an expansion device, and at least one heat exchanger. A heat transfer fluid is configured to circulate within the vapor compression cycle. An energy storage device is selectively operable to supply power to one of the plurality of components. The energy storage device is thermally coupled to the vapor compression cycle.
An engine housing for an aircraft rotary engine includes a rotor housing and a side housing assembly. The rotor housing includes a rotor housing body. The rotor housing body extends about an axis to form a rotor cavity of the engine housing. The rotor housing body extends between and to a first axial end and a second axial end. The side housing assembly includes a side housing body, a side plate, and a seal assembly. The side housing body is disposed at the first axial end. The side plate includes an inner side, an outer side, and a perimeter edge extending from the inner side to the outer side. The seal assembly includes a support ring and a spacer. The support ring and the spacer extend about the axis. The support ring is mounted to the perimeter edge by a braze joint. The spacer extends between and to a first axial spacer end and a second axial spacer end. The first axial spacer end is disposed at the support ring and the outer side.
A gas turbine engine includes a compressor, a combustor and a turbine. A compressor section has an exit upstream of the combustor. A temperature probe extends through a compressor exit housing surrounding the compressor section exit. The temperature probe taps air downstream of the exit into a probe body having a passage leading to a temperature sensor. There is a controlled leakage also allowing air from within the compressor exit housing to leak. A method and a test probe are also disclosed.
G01K 13/024 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de fluides en mouvement ou de matériaux granulaires capables de s'écouler de gaz en mouvement
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
G01K 1/14 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers
G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p. ex. des thermocouples
59.
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
64.
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
65.
SYSTEMS AND METHODS FOR DETECTING OCCUPANCY OF ROOMS
Embodiments of the disclosure describe systems and methods for detecting an occupancy of a room. The method comprises receiving, from a plurality of sensors located within the room, sensor readings indicative of corresponding occupancy parameters. The plurality of sensors are configured to measure the corresponding occupancy parameters. The method further comprises determining, based on the received sensor readings, one or more of an occupancy status of the room, and a confidence value associated with the determined occupancy status. The occupancy status is indicative of one of a positive status indicating occupancy of the room and a negative status indicating non-occupancy of the room. The method further comprises, in response to determining the occupancy status, triggering a control action associated with the room based on the determined occupancy status.
G06V 40/10 - Corps d’êtres humains ou d’animaux, p. ex. occupants de véhicules automobiles ou piétonsParties du corps, p. ex. mains
G06V 10/764 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant la classification, p. ex. des objets vidéo
G06V 10/82 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant les réseaux neuronaux
66.
START-UP DEVICE, MOTOR SYSTEM AND METHOD FOR REDUCING DC MOTOR START-UP CURRENT
The present application relates to a motor control technology, and in particular to a start-up device for a DC motor, a motor system comprising the start-up device, a method for reducing DC motor start-up current and a computer-readable storage medium with a computer program stored thereon for implementing the above method. The start-up device for a DC motor according to one aspect of the present application includes: a switching element connected in series within a circuit comprising the DC motor and a DC power supply; and a control unit configured to cause the switching element to periodically switch between an ON state and an OFF state in a predetermined time interval to reduce the peak value of a start-up current flowing through the DC motor, and to cause the switching element to maintain the ON state after the predetermined time interval ends.
H02P 1/18 - Dispositions de démarrage de moteurs électriques ou de convertisseurs dynamo-électriques pour faire démarrer des machines dynamo- électriques ou des convertisseurs dynamo-électriques pour faire démarrer individuellement un moteur à courant continu
H02P 1/02 - Dispositions de démarrage de moteurs électriques ou de convertisseurs dynamo-électriques Détails
H02P 7/291 - Dispositions pour réguler ou commander la vitesse ou le couple de moteurs électriques à courant continu pour réguler ou commander individuellement un moteur dynamo-électrique à courant continu en faisant varier le champ ou le courant d'induit par commande maîtresse avec puissance auxiliaire utilisant des tubes à décharge ou des dispositifs à semi-conducteurs utilisant des dispositifs à semi-conducteurs commandant l'alimentation de l'induit seulement utilisant la modulation d'impulsions par commande marche-arrêt entre deux points de consigne, p. ex. commande par hystérésis
67.
PORTABLE AC-DC POWER CONVERTER AND ON-BOARD POWER SUPPLY MANAGEMENT DEVICE
The present application relates to a portable AC-DC power converter for an on-board refrigeration unit and an on-board power supply management device suitable for use in conjunction with the aforementioned portable AC-DC power converter. A portable AC-DC power converter for on-board electrical equipment according to one aspect of the present application comprises: an AC-DC conversion unit; one or more AC power plugs connected to an input terminal of the AC-DC conversion unit; and one or more connectors connected to an output terminal of the AC-DC conversion unit, wherein the connector comprises a DC output interface and a conductor, where the conductor is configured to short circuit contacts arranged on the refrigeration unit on the vehicle side when the DC output interface is engaged with a DC input interface of an on-board connector to generate a trigger signal to disconnect the on-board electrical equipment from an on-board power source.
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
B60R 16/033 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour l'alimentation des sous-systèmes du véhicule en énergie électrique caractérisé par l'utilisation de cellules électriques ou de batteries
68.
OUTDOOR UNIT FOR REFRIGERATION CABINET AND REFRIGERATION CABINET
The present invention relates to an outdoor unit for a refrigeration cabinet and a refrigeration cabinet. The outdoor unit comprises: a first unit comprising a compressor; a second unit comprising a condenser; wherein, the outdoor unit is configured to be installed in a first mode or a second mode; where in the first mode, the first unit and the second unit are installed adjacent to each other and connected with each other through fasteners, and the first unit and the second unit are connected through a first fluid pipeline passing through an adjacent surface between the first unit and the second unit; where in the second mode, the first unit and the second unit are respectively installed at a first position and a second position spaced apart, and the first unit and the second unit are connected through a second fluid pipeline extending between the first and second positions.
An air conditioning system includes a vapor compression cycle having a heat transfer fluid circulating between a compressor, an expansion device, and at least one heat exchanger. A flow of air is associated with the at least one heat exchanger of the vapor compression cycle. An energy storage device is selectively operable to supply power to the compressor and the flow of air is operable to cool the energy storage device.
F24F 11/37 - Aménagements de commande ou de sécurité en relation avec le fonctionnement du système, p. ex. pour la sécurité ou la surveillance réagissant aux dysfonctionnements ou aux situations critiques pour la remise en route, p. ex. après une coupure de courantDémarrage d'urgence
F24F 11/46 - Amélioration de l’efficacité électrique ou économie d’énergie électrique
A windshield wash system includes a pump with an inlet and an outlet, and a fluid reservoir fluidically connected to the inlet of the pump. A fluid delivery line is fluidically connected to the outlet of the pump and at least one nozzle is fluidically connected to the fluid delivery line. An electronic control unit is in controlling communication with the pump. A pressure sensor is in the fluid delivery line and is in communication with the electronic control unit.
A method of braking a rotational air mover portion of an aircraft propulsion system is provided. The method includes: using an electrical device to apply a torque to a propulsion unit driven by a propulsion system of an aircraft, the propulsion unit including a rotational air mover configured to provide thrust for propelling the aircraft, wherein the electrical device is configured to produce electrical energy during the process of applying the torque to the propulsion unit; controlling the electrical device to apply an amount of the torque that is sufficient to cause the rotational air mover to decelerate or to maintain the rotational air mover non-rotational; and directing the electrical energy produced by the electrical device to an aircraft component.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
B64D 35/022 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride
F01D 13/00 - Combinaisons de plusieurs "machines" ou machines motrices
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
An aircraft engine comprises a rotating component and a reduction gearbox connected thereto. A rotating shaft extending along an axis is coupled to the gearbox. A thrust bearing disposed in a bearing housing extends around the shaft and supports the shaft. The bearing housing defines a piston chamber. A piston therein axially secured to the shaft and in sealing engagement with the bearing housing divides the chamber into two cavities. The piston has opposite first and second axial faces exposed to respective cavities. The first face faces axially away from the thrust bearing. A compressed air source is in fluid communication with the first cavity with air at a first pressure exerting a first force against the first axial face. The second cavity is at a second pressure exerting a second force against the second axial face. The first force is greater than the second.
A battery replacement system for controlling a battery pack loadout for an aircraft having at least one installed battery pack includes a vehicle including a battery storage assembly, a controller, and a battery transfer assembly. The battery storage assembly is configured for storing at least one stored battery pack. The controller is configured to identify a state of charge for each of the at least one installed battery pack installed on the aircraft, identify an energy storage prerequisite for a flight or series of flights of the aircraft, and identify a battery pack loadout plan for the aircraft. The battery pack loadout plan identifies one or more of the at least one stored battery pack to be installed on the aircraft. The controller is further configured to control the battery pack loadout for the aircraft by controlling the battery transfer assembly to install the one or more of the at least one stored battery pack into the aircraft.
B60L 58/12 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries en fonction de l'état de charge [SoC]
B60L 58/18 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries de plusieurs modules de batterie
B64D 27/357 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles
H01M 50/244 - Boîtiers secondairesBâtisDispositifs de suspensionDispositifs de manutentionSupports caractérisés par leur procédé de montage
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
H01M 50/256 - Dispositifs de transport, p. ex. courroies
74.
STRUCTURAL CASING FOR GAS TURBINE ENGINE AND METHOD FOR ADJUSTING TIP CLEARANCE IN A GAS TURBINE ENGINE
An outer structural case of a turbine casing assembly, including: a plurality of threaded adjustment openings located about a periphery of the outer structural case, the plurality of threaded adjustment openings extending completely through the periphery of the outer structural case; and a plurality of threaded securement openings arranged orthogonally with respect to the plurality of adjustment openings.
A gas turbine engine under this disclosure could be said to include a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal, and has at least one potential peak displacement point due to vibration across a speed range of the at least one of the compressor and turbine section. A stiffening element is fixed to a wall of the casing at the at least one potential peak displacement point. A method is also disclosed.
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
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
A battery replacement system for controlling a battery pack loadout for an aircraft includes a vehicle including a battery storage assembly, a controller, and a battery transfer assembly. The battery storage assembly is configured for storing at least one stored battery pack. The controller is configured to identify an energy storage prerequisite for a flight or series of flights of the aircraft using flight information for the aircraft and to identify a battery pack loadout plan for the aircraft using the energy storage prerequisite. The battery pack loadout plan identifies one or more of the at least one stored battery pack to be installed on the aircraft. The controller is further configured to control the battery pack loadout for the aircraft by controlling the battery transfer assembly to receive the one or more of the at least one stored battery pack from the battery storage assembly and install the one or more of the at least one stored battery pack into the aircraft.
B60L 58/12 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries en fonction de l'état de charge [SoC]
B60L 58/18 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries de plusieurs modules de batterie
B64D 27/357 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles
H01M 50/244 - Boîtiers secondairesBâtisDispositifs de suspensionDispositifs de manutentionSupports caractérisés par leur procédé de montage
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
H01M 50/256 - Dispositifs de transport, p. ex. courroies
A gas turbine engine includes a turbine for driving a shaft to in turn drive a rotor. A combustor receives compressed air, and combusts the compressed air. The shaft is supported by at least one bearing. An oil delivery system is associated with the at least one bearing including an oil scoop rotating with the at least one shaft and a stationary oil jet provided with a source of lubricant. A mixed fluid chamber is within the shaft. The mixed fluid chamber is connected to an air exit. There further is an oil chamber radially outward of the mixed fluid chamber. The oil chamber is connected to the at least one bearing.
A gas turbine engine includes a compressor section, a combustor and a turbine section. At least one casing surrounds at least one of the compressor and turbine section. The at least one casing is formed of sheet metal. The at least one casing has at least one potential peak displacement point due to vibration across a speed range of the one of the compressor and turbine section. A damper is placed on the casing at the at least one potential peak displacement point. The damper has one end fixed to the casing, and a second end not fixed to the casing and the second end provides an interference fit such that the second end cannot move to a relaxed position of the second end due to the wall of the casing. A method is also disclosed.
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
F16F 15/02 - Suppression des vibrations dans les systèmes non rotatifs, p. ex. dans des systèmes alternatifsSuppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif
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
84.
SYSTEM AND METHOD FOR TESTING AN INTEGRITY OF A FACE SEAL IN AN ELECTRICAL SYSTEM
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.
A shell-and-tube heat exchanger assembly including a first tube sheet, a second tube sheet, and a plenum, is disclosed. The first tube sheet is adapted to be secured to a shell of the shell-and-tube heat exchanger assembly. The first tube sheet includes a plurality of first holes adapted to support a plurality of tubes extending through the shell. The second tube sheet is adapted to be fastened to a front surface of the first tube sheet and fastened to a rear surface of the plenum. The second tube sheet includes a plurality of second holes adapted to support the plurality of tubes extending through the plurality of first holes. The second tube sheet is made of a metal adapted to limit a corrosion response of the plurality of tubes when exposed to a chiller fluid.
F28F 21/08 - Structure des appareils échangeurs de chaleur caractérisée par l'emploi de matériaux spécifiés de métal
F28D 7/10 - 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 disposées l'une dans l'autre, p. ex. concentriquement
86.
MOTOR DRIVE SYSTEM AND CONTROL METHOD FOR CHILLER UNIT
The present application relates to air conditioning technology and motor control technology, and in particular to a motor drive system for a chiller unit, a chiller unit comprising the motor drive system, a control method for a chiller unit, and a computer-readable storage medium on which is stored a computer program for implementing the method. A motor drive system for a chiller unit according to an aspect of the present application comprising: a variable frequency drive unit configured to drive a first motor; a power frequency drive unit configured to drive a second motor; and a control unit configured to adapt a load demand of the chiller unit by controlling output power of the variable frequency drive unit and the power frequency drive unit.
A transport refrigeration system includes a transport refrigeration unit, an energy storage device, a supply refrigerant tube, a return refrigerant tube and at least one electrical pathway. The transport refrigeration unit is adapted to cool a container. The energy storage device is adapted to provide electrical energy for operating the transport refrigeration unit. The supply refrigerant tube flows a refrigerant from the transport refrigeration unit to the energy storage device, and the return refrigerant tube flows the refrigerant from the energy storage device back to the transport refrigeration unit. The electrical pathway extends between the transport refrigeration unit and the energy storage device, and supplies at least electrical energy to the transport refrigeration unit.
A smart sensor can include a plurality of analog-to-digital converters (ADCs) configured to receive analog signals from a sensor module, and a plurality of channel modules. Each channel module can be connected to a respective ADC and each channel module can include a limited data processing module configured to provide initial processing. The sensor can include a data control module operatively connected to each of the plurality of channel modules and configured to select a selected channel of the plurality of channels to receive initially processed data from the limited data processing module of the selected channel. The data control module can be configured to interface with external memory to store data to the external memory and/or to read data from the external memory. The sensor can include a batch processing module operatively connected to the data control module and configured to receive the initially processed data of the selected channel from the data control module to provide further processing of the initially processed data.
H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p. ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
H04L 67/10 - Protocoles dans lesquels une application est distribuée parmi les nœuds du réseau
H04Q 9/00 - Dispositions dans les systèmes de commande à distance ou de télémétrie pour appeler sélectivement une sous-station à partir d'une station principale, sous-station dans laquelle un appareil recherché est choisi pour appliquer un signal de commande ou pour obtenir des valeurs mesurées
The power plant can have a structure; an output shaft connectable to a load, the output shaft rotatable about an axis relative the structure; a thermal engine secured to the structure, the thermal engine having a thermal engine shaft; an electric motor having a stator and a rotor shaft, the stator secured to the structure; an epicyclic gearing having a sun gear coaxial to a ring gear, a plurality of planet gears meshed between the sun gear and the ring gear, and a carrier coaxial to the sun gear and to the ring gear, the sun gear, carrier, and ring gear being rotatable relative the casing structure, the output shaft and the rotor shaft both coupled to the carrier, and the thermal engine shaft coupled to sun gear and the carrier; and an overrunning clutch operable to prevent the rotation of the ring gear in one angular direction.
B64D 35/022 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques du type électrique-hybride
F16H 3/72 - Transmissions à engrenages pour transmettre un mouvement rotatif à rapport de vitesse variable ou pour inverser le mouvement rotatif utilisant des engrenages à mouvement orbital avec entraînement secondaire, p. ex. un moteur régulateur, pour faire varier la vitesse d'une manière continue
An integrated blade rotor (IBR) is provided and includes a disc, blades integrally formed with the disc and radially outwardly facing surfaces of the disc. Each radially outwardly facing surface is disposed adjacent to a corresponding blade and includes a curved profile.
[Problem] To provide a selector valve block assembly and an air supply/exhaust block in which different types of selector valve blocks can be mixed-mounted to the air supply/exhaust block. [Solution] In a selector valve block assembly 1, first and second selector valve blocks 60A, 60B having output ports 64a, 64b and a first air supply/exhaust block 10 having air supply and exhaust ports 12, 13 are connected. The first air supply/exhaust block has a first air supply and first exhaust opening in one side surface, and has a second air supply and second exhaust opening in the other side surface. The first and second air supply openings communicate with an air supply port, and the first and second exhaust openings communicate with an exhaust port. The centers of the openings are arranged on different axes. When the first selector valve block is coupled to one side surface of the first supply/exhaust block, the supply air and the exhaust flow path are connected to the first air supply and second exhaust opening, and when the second switching valve block is coupled to the other side surface of the first air supply and exhaust block, the air supply and the exhaust flow path are connected to the second air supply and second exhaust opening.
[Problem] To surely mount a packing on a valve rod so that the packing does not fall off from the valve rod during operation of the selector valve in a poppet valve. [Solution] In a state where one lateral surface 26d of a ring-shaped packing 26 is brought into contact with a packing mounting surface 27 formed in a packing mounting part 17 of a valve rod 11, and an inner circumferential part 26a of the packing 26 is fitted into a packing support groove 29 formed at the inner diameter end of the packing mounting surface 27, an outer circumferential part 26b of the packing 26 is held between the packing mounting surface 27 and a packing pressing member 30 attached to the packing mounting part 17, whereby the packing 26 is brought into contact with the packing mounting surface 27.
[Problem] To provide a spool-type switching valve which is capable of efficiently linking a spool valve and a piston. [Solution] This spool-type switching valve comprises first and second piston chambers 32 which are respectively at both end parts of a spool hole 25 that extends in the axis L direction, wherein first and second spool valves 11b are accommodated in the spool hole, and first and second pistons 33 are accommodated in the piston chambers. First and second connection parts 70b are provided between valve end surfaces 34 formed at end parts of respective spool valves and piston end surfaces 33a of respective pistons which face the valve end surfaces 34. The connection parts each have a protruding part 72 that protrudes from a respective valve end surface and an insertion recess part 77 on the inner side of a wall part 36 that is provided upright at a respective piston end surface. An engagement groove part 73 is provided to each protruding part. Each wall part has a cutout groove part that is cut out in the axial direction, a leg part that is disposed on the inside of the cutout groove part, and an engagement claw part 47 that is provided to the tip end part of the leg part. In a state where the protruding part is inserted in the insertion recess part, the engagement claw part and the engagement groove part engage to link a respective spool valve and piston.
F16K 3/24 - Robinets-vannes ou tiroirs, c.-à-d. dispositifs obturateurs dont l'élément de fermeture glisse le long d'un siège pour l'ouverture ou la fermeture à faces d'obturation en forme de surfaces de solides de révolution avec corps de tiroir cylindrique
F16K 11/07 - Soupapes ou clapets à voies multiples, p. ex. clapets mélangeursRaccords de tuyauteries comportant de tels clapets ou soupapesAménagement d'obturateurs et de voies d'écoulement spécialement conçu pour mélanger les fluides dont toutes les faces d'obturation se déplacent comme un tout comportant uniquement des tiroirs à éléments de fermeture glissant linéairement à glissières cylindriques
95.
Labyrinth seal and removal from gas turbine engine
A seal of a gas turbine engine includes a rotationally stationary seal element secured to a rotationally fixed component of the gas turbine engine, and a labyrinth seal element secured to and rotatable with a rotational component of the gas turbine engine. The labyrinth seal element includes a seal base, and a plurality of seal fins extending outwardly from the seal base, the plurality of seal fins configured to define a seal interface between the plurality of seal fins and the rotationally stationary seal element to prevent airflow therethrough. A removal face is defined integral to an end fin of the plurality of seal fins. The removal face is configured for application of a removal force thereto to remove the labyrinth seal from an installed position in the gas turbine engine.
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
