A system for coating ceramic fibers for use in manufacturing a ceramic matric composite (CMC) article includes a frame having a plurality of frame members arranged so as to create a void therebetween. At least one of frame members includes a hollow body and at least one perforated hole defined in the hollow body. Thus, the ceramic fibers are securable at respective ends of the frame and extend across the void. The frame also includes an inlet in fluid communication with the perforated hole(s) so as to allow a coating material to flow into and through the hollow body and out of the perforated hole(s) at a location of at least a portion of one of the ceramic fibers. As such, the coating material is configured to cause the portion of one of the ceramic fibers to separate from the frame such that the portion is uniformly coated with the coating material.
An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.
B64C 1/16 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés spécialement adaptés pour le montage du groupe propulseur
B64C 21/01 - Propulsion par ingestion de la couche limite [BLI]
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 33/02 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des entrées d'air de combustion
B64D 33/04 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des sorties d'échappement ou des tuyères
3.
SYSTEM AND METHOD FOR CONTROLLING BLADE PITCH OF WIND TURBINE ROTOR BLADES TO REDUCE VIBRATIONS AND LIMIT LOADS IN A LOCKED CONDITION OF THE ROTOR HUB
A system and method are provided for reducing vibrations and loads in one or more rotor blades of a wind turbine when the rotor hub is locked against rotation, The method detects that the rotor blades are vibrating above a threshold limit, and determines one or more wind parameters for wind impacting the rotor blades. An initial orientation of the blades is also determined. Based on the wind parameters and initial blade orientation, a first angle of attack for the rotor blades is determined that will reduce the vibrations in the rotor blades. The method then determines if expected loads induced at one or more wind turbine components will exceed a threshold limit at the first angle of attack for the rotor blades. The first angle of attack is modified when the expected loads exceed the threshold limit to reduce the expected loads to below the threshold limit. A controller pitches the rotor blades to achieve the first angle of attack.
F03D 7/02 - Commande des mécanismes moteurs à vent les mécanismes moteurs à vent ayant l'axe de rotation sensiblement parallèle au flux d'air pénétrant dans le rotor
4.
SYSTEM AND METHOD FOR CONTROLLING BLADE PITCH OF WIND TURBINE ROTOR BLADES IN AN IDLING STATE OF THE ROTOR HUB
A proactive method prevents vibrations in one or more rotor blades of a wind turbine when the wind turbine is in a standstill idling state with a rotor hub free to rotate. The method determines a minimum revolution rate of the rotor blades that prevents vibrations of the rotor blades and that the actual revolution rate of the rotor blades is below the minimum revolution rate. A wind parameter is detected and determined to be above a threshold limit. The method also detects if grid power is available for pitching the rotor blades. Based on the wind parameter, a controller determines a pitch angle for one or more of the rotor blades to increase rotation of the blades to at least the minimum revolution rate. The controller initiates pitching the rotor blades to increase the revolution rate of the rotor blades prior to vibrations being induced in the rotor blades.
F03D 7/02 - Commande des mécanismes moteurs à vent les mécanismes moteurs à vent ayant l'axe de rotation sensiblement parallèle au flux d'air pénétrant dans le rotor
5.
BOND COAT INCLUDING COARSE OXYGEN GETTER PARTICLES
A coated component (100), along with methods of its fon-nation, are provided. The coated component (100) may include a ceramic matrix composite substrate (102) comprising silicon carbide and having a surface (103), a bondcoat (104) on the surface (103) of the substrate (102), and an environmental barrier coating (108) on the bondcoat (104). The bondcoat (104) includes a plurality of discrete particles (110) dispersed within a matrix phase (112), with the matrix phase (112) formed from mullite and defining 60% to 98% by volume of the bondcoat (104). The plurality of discrete particles (110) include an oxygen getter and has 50% of its volume or greater formed from particles having an average size of 10 [tm to 100 i.tm.
A starter/generator system (100) for a gas turbine engine (10) is provided. The gas turbine engine includes a core gas turbine engine (13) and a low-pressure turbine (20) coupled to the core gas turbine engine. The starter/generator system includes a starter (102) coupled to the core gas turbine engine, and a generator (104) coupled to the low-pressure turbine.
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
7.
LASER NET SHAPE MANUFACTURING USING AN ADAPTIVE TOOLPATH DEPOSITION METHOD
A method is disclosed for laser cladding a substrate, comprising providing the substrate; depositing a first determined variable bead width of a material along a toolpath upon the substrate; depositing a second adjacent determined variable bead width of a material along the toolpath which overlaps the first determined variable bead width of deposited material; continuing to deposit a plurality of overlapping predetermined adjacent variable bead widths of a material until a first material layer is complete; forming a second material layer by depositing a plurality of overlapping predetermined variable bead widths of a material on top of the first material layer; and continuing to deposit material layers on top of deposited material layers until the cladding is complete; wherein the variable bead width of the deposited material is controlled by a computer having a plurality of input parameters to maintain an approximately constant percent of bead width overlap.
A method and tooling for inspecting a contour of an edge of a cutout formed in a disk (200), each cutout fixedly receiving a turbine blade (220). A first device (12) receives the disk (200) containing the cutouts. A second device (14) has a sensor associated with the movement of an instrument, the first device (12) securing the disk (200) at a predetermined orientation to the sensor. The disk (200) is secured to the first device (12), the instrument being directed along the cutout defining a path substantially parallel to a surface of the contour, the instrument remaining in physical contact with the surface of the contour. The sensor transmits a signal associated with instrument movement to an algorithm to convert the signal to two-dimensional positions along the tangent path along the surface of the contour. The acceptability of the edge contour of the cutout is determined by comparing the two-dimensional positions to predetermined ranges of values.
F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
G01B 5/20 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer des contours ou des courbes
G01B 13/00 - Dispositions pour la mesure caractérisées par l'utilisation de fluides
G01B 15/00 - Dispositions pour la mesure caractérisées par l'utilisation d'ondes électromagnétiques ou de radiations de particules, p. ex. par l'utilisation de micro-ondes, de rayons X, de rayons gamma ou d'électrons
9.
METHOD FOR REMOVING ENGINE DEPOSITS FROM TURBINE COMPONENTS AND COMPOSITION FOR USE IN SAME
A method and cleaning composition for removing engine deposits (58) from turbine components (10), in particular turbine disks (10) and turbine shafts (10). This method comprises the following steps: (a) providing a turbine component (10) having a surface (14) with engine deposits (58) thereon, wherein the turbine component (10) comprises a nickel and/or cobalt-containing base metal (50); and (b) treating the surface (14) of the turbine component (10) with a cleaning composition to convert the engine deposits (58) thereon to a removable smut without substantially etching the base metal (50) of the turbine component (10). The cleaning composition comprises an aqueous solution that is substantially free of acetic acid and comprising: a nitrate ion source in an amount, by weight of the nitrate ion, of from 470 to 710 grams/liter; and a bifluoride ion source in an amount, by weight of the bifluoride ion, of from 0.5 to 15 grams/liter. The smut that is formed can be removed from the surface (14) of the turbine component (10) in a manner that does not substantially alter the surface (14) thereof.
An apparatus (100) for producing tractive effort, the apparatus (100) comprising: an energy source (110) adapted for generating a high DC voltage (120); a motor drive (130) adapted for generating a motor voltage (140) from the high DC voltage (120); and a motor (150) adapted for producing the tractive effort from the motor voltage (140), the energy source (110) comprising: a heat engine (160) adapted for generating mechanical power (170) by burning a fuel; an alternator (180) adapted for generating an alternating voltage (190) from the mechanical power (170); a rectifier (200) adapted for rectifying the alternating voltage (190) and producing a low DC voltage (210); an energy battery (220) adapted for storing and delivering energy derived from the low DC voltage (210); and a traction boost converter (230) adapted for boosting the low DC voltage (210) to produce the high DC voltage (120), the motor drive (130) comprising: a power battery (240) adapted for storing energy and delivering power at the high DC voltage (120); and a traction converter (250) adapted for generating the motor voltage (140) from the high DC voltage (120) during motoring operation and for generating the high DC voltage (120) from the motor voltage (140) during braking operation.
11.
RTV SILICONE COMPOSITION OFFERING RAPID BOND STRENGTH
The present invention provides for a room temperature vulcanizable silicone sealant composition that rapidly achieves a usable green strength shortly after application. Such a composition that develops a usable green strength is useful in the manufacture of architectural elements employing glazing such as windows and doors and when such a composition is used in a manufacturing process, the manufacturing process can be accelerated relative to a process that uses a silicone sealant that does not rapidly achieve a usable green strength.
In certain embodiments, an electromechanical device includes a rotor (54) having a rotational axis (26), and a stator (10) disposed about the rotor (54). The stator (10) may include a circumferentially laminated section (14) comprising a plurality of circumferential segments (28, 30) disposed one after another in a circumferential direction relative to the rotational axis (26). The stator (10) also may include a radially laminated section (16) comprising a plurality of radial segments (40) disposed one after another in a radial direction relative to the rotational axis (26). In addition, the stator (10) may include an axially laminated section (12) comprising a plurality of axial segments (18, 20) disposed one after another in an axial direction relative to the rotational axis (26).
A composite blading member (10) includes an airfoil (12) and a base (20) of composite material layers (40) and a platform (38) of composite material layers (40) interfused with the airfoil (12) and base (20). The platform (38) comprises a platform shelf (42) and a plurality of spaced-apart platform supports (44,46) integral with the platform shelf (42) and interfused with surfaces (26,28) of the base. Such blading member (10) was made by providing a partially cured airfoil-base preform (36) and a platform perform (38), including an airfoil shaped opening (43) therethrough and preforms of the platform supports (44,46). The airfoil-base preform (36) was inserted through the airfoil shaped opening (43) whereby cooperating surfaces of the platform perform (38) and airfoil-based preform (36) were in juxtaposition. The performs (36,38) were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms (36,38) under conditions to substantially fully cure the structures.
B32B 5/12 - 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 caractérisés par la disposition relative des fibres ou filaments des couches adjacentes
A vehicle propulsion (100) includes an alternating current (AC) traction drive (147), a first energy storage system electrically coupled to the traction drive through a direct current (DC) link (114), a second energy storage system electrically coupled to the traction drive such that the voltage output from the second energy storage system is decoupled from the DC link using a bi-directional boost converter (120), and an energy management system configured to control said first and second energy storage systems when the vehicle is operating in at least one of a pre-charge mode and a normal operation mode with the traction drive system (147) enabled.
B60W 10/26 - Commande conjuguée de sous-ensembles de véhicule, de fonction ou de type différents comprenant la commande des moyens de stockage d'énergie pour l'énergie électrique, p. ex. des batteries ou des condensateurs
15.
METHOD AND APPARATUS TO DETERMINE MOISTURE CONTENT IN SOLID INSULATION
Disclosed herein is a method that relates to determining water content of a solid insulation (18, 22) at a specific location within a transformer (10). The method comprising, determining a temperature of the solid insulation (18, 22) at a specific location, calculating a relative moisture saturation of the oil (30) at the specific location, calculating the ultimate water content in the solid insulation (18, 22) at the specific location, and calculating an actual water content in the solid insulation (18, 22) at the specific location.
Rotor and stator assemblies that utilize magnetic bearings for supporting the rotor shaft during operation can be suitably used in corrosive environments, such as sour gas. The rotor and stator assemblies include NACE compliant magnetic bearing arrangements for sour gas applications. One embodiment includes an encapsulated stator assembly (60) that comprises a stator sleeve (154) formed of a magnetic material, a sleeve extender (152) coaxial to the stator sleeve (154) formed of a non--magnetic material fixedly attached to each end of the stator sleeve (154), wherein a point of attachment is heat treated, and a wall (70) formed of the non- magnetic material fixedly attached to the sleeve extender (152) configured to hermetically house a stator and form the encapsulated stator assembly (60).
F16C 32/04 - Paliers non prévus ailleurs faisant usage de moyens de support magnétiques ou électriques
H02K 1/02 - Détails du circuit magnétique caractérisés par le matériau magnétique
H02K 5/10 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des dispositions empêchant l'introduction de corps étrangers, p. ex. de l'eau ou des doigts
17.
COUNTER-ROTATABLE FAN GAS TURBINE ENGINE WITH AXIAL FLOW POSITIVE DISPLACEMENT WORM GAS GENERATOR
A counter-rotatable fan turbine engine (10) includes a counter-rotatable fan section (112), a worm gas generator (100), and a low pressure turbine (120) to power the counter-rotatable fan section (112). The low pressure turbine (120) maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section (112) through a gearbox (224). The gas generator (100) has inner and outer bodies (12, 14) having offset inner and outer axes (16, 18) extending through first, second, and third sections (24, 26, 28) of a core assembly (15). At least one of the bodies is rotatable about its axis. The inner and outer bodies (12, 14) have intermeshed inner and outer helical blades (17, 27) wound about the inner and outer axes (16, 18) and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes (34, 36, 38) in the first, second, and third sections (24, 26, 28) respectively. A combustor section (40) extends through at least a portion of the second section (26).
F02C 3/067 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux comportant des rotors contra-rotatifs
F02K 3/072 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comportant des rotors contra-rotatifs
18.
SYSTEM AND METHOD FOR FIELD CALIBRATION OF FLOW METERS
A calibration system for a flow meter includes a flow simulator, the flow simulator including a receiver configured to receive flow meter transducer signals from a flow meter. A simulation subsystem is configured to create simulated transit time signal pulses, and to transmit the simulated transit time signal pulses to the flow meter at preselected time intervals. A calibration subsystem is configured to receive from the flow meter a transit time differential value generated by the flow meter based on the simulated transit time signal pulses and output a calibration factor to the flow meter.
A method of operating a vehicle having an electric drive is provided. The method includes defining a first zone and a second zone. The first zone has an associated first characteristic and the second zone has an associated second characteristic that differs from the first characteristic. The method further includes switching an operating mode of a vehicle from a first operating mode in the first zone to a second operating mode in the second zone in response to the vehicle translating from the first zone to the second zone. Associated vehicles and systems are provided also.
B60L 50/50 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible
B60W 20/00 - Systèmes de commande spécialement adaptés aux véhicules hybrides
B60W 40/00 - Calcul ou estimation des paramètres de fonctionnement pour les systèmes d'aide à la conduite de véhicules routiers qui ne sont pas liés à la commande d'un sous-ensemble particulier
20.
MEMS MICROSWITCH HAVING A DUAL ACTUATOR AND SHARED GATE
In accordance with one aspect of the present invention, a MEMS switch (10,30,40) is provided. The MEMS switch (10,30,40) includes a substrate (12), a first (21,41) and a second (22,42) actuating element electrically coupled together, an anchor (18) mechanically coupled to the substrate (12) and supporting at least one of the first (21,41) and second (22,42) actuating elements, and a gate driver (6) configured to actuate the first (21,41) and second (22,42) actuating elements.
B81B 7/02 - Systèmes à microstructure comportant des dispositifs électriques ou optiques distincts dont la fonction a une importance particulière, p. ex. systèmes micro-électromécaniques [SMEM, MEMS]
A fuel cell sensor (100) is provided for detecting the presence of acetylene and hydrogen in a fluid. The sensor includes a sensing element (4-1) having first and second gas diffusing electrodes spaced from one another. The first gas diffusing electrode can be used for sensing acetylene. The second gas diffusing electrode can be used for sensing hydrogen. A fuel cell spacer (15) having an acidic electrolyte is disposed between the sensing element and a common electrode (4-2). The sensing element can be configured to have a specific ratio of the area between the first gas diffusing electrode in relation to the area of the second gas diffusing electrode.
A combustor nozzle (72) is provided. The combustor nozzle includes a first fuel system (74) configured to introduce a syngas fuel into a combustion chamber to enable lean premixed combustion within the combustion chamber and a second fuel system (76) configured to introduce the syngas fuel, or a hydrocarbon fuel, or diluents, or combinations thereof into the combustion chamber to enable diffusion combustion within the combustion chamber.
F02C 3/28 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant solide ou pulvérulent, p. ex. mélangé avec un liquide ou en suspension utilisant un générateur de gaz séparé pour gazéifier le combustible avant la combustion
F02C 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
F23C 7/00 - Appareils à combustion caractérisés par des dispositions pour l'amenée d'air
F23D 14/06 - Brûleurs à gaz avec prémélangeurs, c.-à-d. dans lesquels le combustible gazeux est mélangé à l'air de combustion en amont de la zone de combustion du type à induction, p. ex. becs Bunsen avec les orifices de sortie disposés radialement dans la tête du brûleur
F23D 14/20 - Brûleurs à gaz sans prémélangeur, c.-à-d. dans lesquels le combustible gazeux est mélangé à l'air de combustion à l'arrivée dans la zone de combustion
F23N 1/00 - Régulation de l'alimentation en combustible
F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
23.
ELECTRONIC STATOR END WINDING ACCELEROMETER SENSOR
An insulated accelerometer assembly (10) is provided for attachment to a vibrated component (12). A base (16) has a portion for engagement and connection with the vibrated component (12) and to transmit vibration. An accelerometer (34) senses vibration and is located at least partially within the base (16). A housing (16) at least partially encloses the accelerometer (34) and inhibits voltage discharge, corona damage, and voltage tracking on the accelerometer (34). The housing (16) is made of an insulating material and has an interior for the accelerometer (34). The housing (16) has a plurality of raised fins (60) on the exterior. A mounting cap (42) also inhibits voltage discharge, corona damage, and voltage tracking and secures the housing (36). The mounting cap (42) is made of insulating material and has an exterior that includes a plurality of raised fins (52). A cable (70) has an electrically conductive wire (82) and has a shield (80) to inhibit electrical noise.
Self-calibration of a multiple channel clearance sensor system (110), which in one embodiment includes at least one sensor (40) for measuring at least one clearance parameter signal between a stationary object and a rotating object of a rotating machine. The sensor output is processed as a clearance parameter by an offset correction section (137) configured to determine an offset error in the clearance parameter signal, which is used by a level shifter (120). The level shifter is also switchably coupled to the clearance parameter signal wherein the output of the level shifter, which may be amplified and digitally converted, is processed by a signal level analyzer (154) to determine a channel gain signal.
G01B 7/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la distance ou la marge entre des objets ou des ouvertures espacés
G01B 11/14 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour mesurer la distance ou la marge entre des objets ou des ouvertures espacés
G01B 15/00 - Dispositions pour la mesure caractérisées par l'utilisation d'ondes électromagnétiques ou de radiations de particules, p. ex. par l'utilisation de micro-ondes, de rayons X, de rayons gamma ou d'électrons
G01B 21/16 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la distance ou le jeu entre des objets espacés
25.
ROTOR/STATOR RELATIVE POSITION DETERMINING METHOD AND APPARATUS
A data signal indicative of a gap between a sensor and at least one of a surface of a rotor and a surface of a stator rotating relative to the sensor is sent to a computer processor. The computer implements defining a plurality of lowest values of the data signal over a revolution of relative rotation between the rotor and the stator, and displaying the plurality of lowest values for assessment of the distance between the sensor and a surface of at least one of the rotor and the stator in order to determine a position of the rotor relative to the stator.
A computer-implemented method for managing data for a clinical decision support system includes providing a computer management system including a server and a database, and downloading the decision support system onto the computer management system. The decision support system includes a plurality of rules and receives data. The method also includes accessing the decision support system and issuing an alert associated with a predetermined data pattern to at least one client system according to the rules, receiving a request for additional information from the at least one client system in response to the issued alert, determining additional data that has been requested, and retrieving the additional information associated with the issued alert.
G16H 10/60 - TIC spécialement adaptées au maniement ou au traitement des données médicales ou de soins de santé relatives aux patients pour des données spécifiques de patients, p. ex. pour des dossiers électroniques de patients
G16H 50/20 - TIC spécialement adaptées au diagnostic médical, à la simulation médicale ou à l’extraction de données médicalesTIC spécialement adaptées à la détection, au suivi ou à la modélisation d’épidémies ou de pandémies pour le diagnostic assisté par ordinateur, p. ex. basé sur des systèmes experts médicaux
G16H 50/70 - TIC spécialement adaptées au diagnostic médical, à la simulation médicale ou à l’extraction de données médicalesTIC spécialement adaptées à la détection, au suivi ou à la modélisation d’épidémies ou de pandémies pour extraire des données médicales, p. ex. pour analyser les cas antérieurs d’autres patients
27.
METHOD AND SYSTEM FOR PRECISE DRILLING GUIDANCE OF TWIN WELLS
A method to guide a drilling path of a second well (12, 80) in close proximity to a first well (10, 102) including: electrically connecting a source of a time varying electrical current (26, 70) to both a proximal end and a distal end (106) of a conductive casing (68) or liner; applying the time varying electrical current directly to the conductive casing or liner of the first well such that current (62, 114) flows in a common direction through substantially an entire length of the casing or liner, wherein the electrical current is injected at one end of the casing or liner and flows to an opposite end of the casing or liner; drilling the second well (12) along a drilling trajectory (86); from the second well, sensing (44, 46, 48, 52, 88) an electromagnetic field generated by the time varying electrical current in the casing or liner of the first well, while the time varying electrical current is applied to the casing or liner of the first well; determining a distance and a direction between the first well and the second well, and guiding the drilling trajectory of the second well using the determined distance and direction to maintain a separation between the second well and the first well.
E21B 7/06 - Modification de la direction du trou de forage
E21B 47/0228 - Détermination de l'inclinaison ou de la direction du trou de forage, p. ex. à l'aide de géomagnétisme utilisant l'énergie électromagnétique ou des détecteurs y étant adaptés
28.
GATE DRIVE CIRCUITRY FOR NON-ISOLATED GATE SEMICONDUCTOR DEVICES
One embodiment is a gate drive circuitry (60) for switching a semiconductor device (62) having a non-isolated input, the gate drive circuitry (60) having a first circuitry (64) configured to turn-on the semiconductor device (62) by imposing a current on a gate of the semiconductor device (62) so as to forward bias an inherent parasitic diode of the semiconductor device (62). There is a second circuitry (66) configured to turn--off the semiconductor device (62) by imposing a current on the gate of the semiconductor device (62) so as to reverse bias the parasitic diode of the semiconductor device (62) wherein the first circuitry (64) and the second circuitry (66) are coupled to the semiconductor device (62) respectively through a first switch and a second switch.
H03K 17/60 - Commutation ou ouverture de porte électronique, c.-à-d. par d'autres moyens que la fermeture et l'ouverture de contacts caractérisée par l'utilisation de composants spécifiés par l'utilisation, comme éléments actifs, de dispositifs à semi-conducteurs les dispositifs étant des transistors bipolaires
H03K 17/687 - Commutation ou ouverture de porte électronique, c.-à-d. par d'autres moyens que la fermeture et l'ouverture de contacts caractérisée par l'utilisation de composants spécifiés par l'utilisation, comme éléments actifs, de dispositifs à semi-conducteurs les dispositifs étant des transistors à effet de champ
29.
WATER BASED SLURRY COMPOSITIONS FOR MAKING ENVIRONMENTAL BARRIER COATINGS AND ENVIRONMENTAL BARRIER COATINGS COMPRISING THE SAME
Water based slurry compositions for making an environmental barrier coating including from about 1wt% to about 99.9wt% water; from about 0.1 wt% to about 72wt% primary material; and from about 0.1 wt% to about 25wt% slurry sintering aid.
Environmental barrier coatings for high temperature ceramic components including: a bond coat layer; an optional silica layer; and at least one transition layer including: from about 85% to about 100% by volume of the transition layer of a primary transition material selected from a rare earth disilicate, or a doped rare earth disilicate; and from 0% to about 15% by volume of the transition layer of a secondary material selected from Fe2O3, iron silicates, rare earth iron oxides, Al2O3, mullite, rare earth aluminates, rare earth aluminosilicates, TiO2, rare earth titanates, Ga2O3, rare earth gallates, NiO, nickel silicates, rare earth nickel oxides, Lnb metals, Lnb2O3, Lnb2Si2O7, Lnb2SiO5, borosilicate glass, alkaline earth silicates, alkaline earth rare earth oxides, alkaline earth rare earth silicates, and mixtures thereof; where the transition layer is applied to the component as a slurry including at least water, the primary transition material and at least one slurry sintering aid, and where a reaction between the slurry sintering aid and the primary transition material results in the transition layer having a porosity of from 0% to about 15% by volume of the transition layer.
A rankine cycle system includes a heater configured to circulate a working fluid in heat exchange relationship with a hot fluid to vaporize the working fluid. A hot system is coupled to the heater. The hot system includes a first heat exchanger configured to circulate a first vaporized stream of the working fluid from the heater in heat exchange relationship with a first condensed stream of the working fluid to heat the first condensed stream of the working fluid. A cold system is coupled to the heater and the hot system. The cold system includes a second heat exchanger configured to circulate a second vaporized stream of the working fluid from the first system in heat exchange relationship with a second condensed stream of the working fluid to heat the second condensed stream of the working fluid before being fed to the heater.
F01K 7/00 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation
F01K 17/06 - Récupération dans le cycle de fonctionnement de l'énergie de la vapeur, sous forme dégradée, p. ex. utilisation de la vapeur d'évacuation pour sécher le combustible solide utilisé dans l'ensemble fonctionnel
F01K 25/00 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs
A unitary swirler (200) is disclosed, comprising a body (201) having a swirler axis (11), and a plurality of vanes (208) arranged in a circumferential direction around the swirler axis (11), wherein the swirler (200) has a unitary construction. In one embodiment, the unitary swirler (200) has a rim (240) located coaxially with the swirler axis (11), and a wall (260) extending between a portion of the rim (240) and a portion of the hub (205). In another embodiment, the unitary swirler (200) has an adaptor (250) having a passage (254) that is configured to direct a flow of air towards at least some of the plurality of vanes (208). A method (500) for fabricating a unitary swirler (200) is disclosed, the method comprising the steps of determining three-dimensional information of the unitary swirler (200) having a plurality of vanes (208) arranged in a circumferential direction on a body (201) around a swirler axis (11) and a wall (260) extending between a rim (240) and a portion of the body (201), converting the three- dimensional information into a plurality of slices that each define a cross-sectional layer of the unitary swirler (200), and successively forming each layer of the unitary swirler (200) by fusing a metallic powder using laser energy. Exemplary embodiments are disclosed, showing a unitary swirler (200) made by using a rapid manufacturing process. In one aspect of the invention, the rapid manufacturing process is a laser sintering process.
A method for fabricating a unitary conduit (105) is disclosed, the method comprising the steps of determining three-dimensional information of the unitary conduit (105) having at least one flow passage (108), converting the three-dimen-sional information into a plurality of slices that each define a cross-sectional layer of the unitary conduit (105), and successively forming each layer of the unitary conduit (105) by fusing a metallic powder using laser energy. A unitary conduit (105) is disclosed, comprising a body (106) and a flow passage (108), wherein the flow passage (108) and the body (106) have a unitary construction, and made by using a rapid manufacturing process. In another embodiment, a unitary conduit (105) has a flow passage wherein the cross sectional shape of the flow passage changes from a first cross sectional shape to a second cross sectional shape. In another embodiment, the exterior contour (140) of the body (106) generally conforms to the interior contour (141) of the flow passage (108). In another embodiment, the flow passage (108) branches to a plurality of sub-passages (109).
A unitary distributor (300) is disclosed, comprising at least one main flow passage (307) located within a distributor ring body (301), the main flow passage (307) having an arcuate portion (305) oriented in a circumferentialdirection around a distributor axis (11). A fuel distributor (100) is disclosed, comprising a fuel conduit (105) and a distributor (300) wherein the fuel distributor (100) has a unitary construction. A method for fabricating a unitary distributor (100) is disclosed, the method comprisingthe steps of determining three-dimensional informationof the unitary distributor (300) having at least one flow passage (307) having an arcuate portion (305) located within a distributor ring body (301) having an axis (11), converting the three-dimensional information into a pluralityof slices that each define a cross-sectional layer of the unitary distributor (300) and successively forming each layer of the unitary (distributor 300) by fusing a metallic powder using laser energy. A unitary fuel distributor (100) comprising a fuel conduit (105) and a distributor (300) is disclosed wherein the unitary fuel distributor (100) is made by using a rapid manufacturing process.
A thermal inspection system (10) includes a fluid source (12) configured to supply a warm flow and a cool flow, indirectly or directly, to internal passage(s) of a component. The system includes an imager (16) configured to capture a time series of images corresponding to a transient thermal response of the component to the warm and cool flows. The system further includes at least one flow meter (24) configured to measure the warm and cool flows supplied to the component and a processor (22) operably connected to the imager. The processor determines the transient thermal response of the component around a transition time. The flow supplied to the component switches from the warm flow to the cool flow at the transition time. The processor compares the transient thermal response around the transition time with one or more baseline values or with an acceptable range of values to determine if the component meets a desired specification.
A counter-rotatable generator includes a generator stator concentric with concentric counter-rotatable radially inner pole and outer magnet rotors. The magnet rotor encircles the pole rotor and the pole rotor encircles the generator stator. A rotor air gap is disposed between the magnet and pole rotors, and a transformer air gap is disposed between the pole rotor and the stator. The magnet rotor includes a circular array of magnets having circumferentially alternating north/south and south/north orientations, retained within a magnet retention ring, and the magnets are circumferentially separated from each other by non-magnetic material spacers. One stator includes an annular hub, axial windings around equi- distantly spaced axial poles on the annular hub, radial cores extending radially outwardly from and equi- angularly spaced about a pole hub on the annular hub between the first and second axial windings, and radial windings around the radial cores.
Methods and kits for generating circular nucleic acids in a cell-free system, and uses for the generated circular nu-cleic acids are provided. The methods comprise in vitro amplification of a nucleic acid template comprising a recombination site to produce tandem repeat nucleic acid sequence, and employ a recombination protein to generate the circular nucleic acids from the tandem repeat nucleic acid sequence.
Erosion- and impact-resistant ceramic coatings suitable for protecting surfaces subjected to collisions with particles, including nominally round particles that typically inflict impact damage and more aggressive irregular-shaped particles that typically inflict erosion damage. The ceramic coating is formed to have one of three compositions: at least one layer of titanium aluminum nitride (TiA1N) having a thickness of about 25 to about 100 micrometers; multiple layers of chromium nitride (CrN) and TiA1N, each layer having a thickness of about 0.2 to about 1.0 micrometers to yield a total coating thickness of at least about 3 micrometers; and at least one layer of titanium silicon carbonitride (TiSiCN) having a thickness of about 15 to about 100 micrometers. The ceramic coating preferably has a total coating thickness of up to about 100 micrometers, and is deposited by a physical vapor deposition process to have a columnar and/or dense microstructure.
B32B 18/00 - Produits stratifiés composés essentiellement de céramiques, p. ex. de produits réfractaires
C23C 14/06 - Revêtement par évaporation sous vide, pulvérisation cathodique ou implantation d'ions du matériau composant le revêtement caractérisé par le matériau de revêtement
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
A system and method for sensing the periodic proximity of one or more objects, such as the relating blades of a gas turbine. The system includes a passive eddy current sensing unit (variable reluctance sensor) having first and second magnets and first and second coilwound cores coupled to generate and detect first and second magnetic fields. The sensing unit is positioned relative to the object such that the first and second coilwound cores produce outputs in response to the object periodically passing through the first and second magnetic fields, respectively. Circuitry electronically combines the outputs of the first and second coil-wound cores to produce output signals corresponding to the proximity and timing of the object as it periodically passes through the first and second magnetic fields Electromagnetic interference noise (common mode signals) present in the outputs of the first aid second coil-wound cores is eliminated from the output signals of the circuitry.
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile
G01D 5/22 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile influençant deux bobines par une action différentielle
G01P 3/488 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions délivrés par des détecteurs à réluctance variable
A system and method for sensing the periodic position of one or more objects, such as rotating blades of a turbine. The system includes a passive eddy current sensing unit (variable reluctance sensor) having one or more magnets and first and second cores around which first and second coils are wound, respectively, which together generate first and second magnetic fields. The sensing unit is positioned so that the object periodically passes through the first and second magnetic fields in succession, and the first and second coils consequently produce first and second output signals, respectively. Each coil is individually connected to a processing circuitry that receives each of the first and second output signals. The circuitry electronically combines the first and second output signals so that common mode signals thereof electronically subtract from each other to eliminate from output of the circuitry any electromagnetic interference noise (common mode signals) present in the first and second output signals.
G01D 5/20 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile
G01D 5/22 - Moyens mécaniques pour le transfert de la grandeur de sortie d'un organe sensibleMoyens pour convertir la grandeur de sortie d'un organe sensible en une autre variable, lorsque la forme ou la nature de l'organe sensible n'imposent pas un moyen de conversion déterminéTransducteurs non spécialement adaptés à une variable particulière utilisant des moyens électriques ou magnétiques influençant la valeur d'un courant ou d'une tension en faisant varier l'inductance, p. ex. une armature mobile influençant deux bobines par une action différentielle
G01P 3/488 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions délivrés par des détecteurs à réluctance variable
A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment (12) comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls (18, 20), and opposed inner and outer walls (14, 16), the walls extending between opposed first and second end faces (48) of the shroud segment (12); and (b) a first seal assembly received in at least one slot formed in the first end face (48), the first seal assembly comprising one or more spline seals which protrude from the first end face (48) and which are arranged to define a continuous sealing surface around the perimeter of the first end face (48).
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
F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p. ex. un élément d'usure, déformable ou contraint de façon élastique
42.
GAS TURBINE ENGINE COMBUSTOR WITH CMC HEAT SHIELD AND METHODS THEREFOR
A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.
F02C 3/14 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail caractérisés par l'aménagement de la chambre de combustion dans l'ensemble
F23R 3/42 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la disposition ou la forme des tubes à flamme ou des chambres de combustion
43.
LOW-DUCTILITY TURBINE SHROUD AND MOUNTING APPARATUS
A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments (24, 124) arranged forming an annular shroud, each of the shroud segments (24, 124) comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls (38, 138, 40, 140), and opposed inner and outer walls (34, 134, 36, 136), the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls (38, 138, 40, 140) is oriented at an acute angle to the outer wall (36, 136), and radially inner ends of the forward and aft walls (3 8, 13 8, 40, 140) are substantially closer together than radially outer ends thereof. An annular stationary structure includes substantially rigid annular forward and aft bearing surfaces (70, 60) which bear against the forward and aft walls (38, 138, 40, 140), respectively, of the shroud segment (24, 124), so as to restrain the shroud segments (24, 124) from axial movement and radially inward movement relative to the stationary structure.
Methods of making components having calcium magnesium aluminosilicate (CMAS) mitigation capability including providing a component; applying an environmental barrier coating to the component, the environmental barrier coating having a separate CMAS mitigation layer including a CMAS mitigation composition selected from the group consisting of zinc aluminate spinel, alkaline earth zirconates, alkaline earth hafnates, rare earth gallates, beryl, and combinations thereof.
C04B 41/89 - Revêtement ou imprégnation pour obtenir au moins deux revêtements superposés de compositions différentes
C23C 28/00 - Revêtement pour obtenir au moins deux couches superposées, soit par des procédés non prévus dans un seul des groupes principaux , soit par des combinaisons de procédés prévus dans les sous-classes et
C23C 28/04 - Revêtements uniquement de matériaux inorganiques non métalliques
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
45.
RESILIENT MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD
A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath,component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.
Apparatus and systems are provided for aircraft gas turbine engine counter-rotatable propellers for lighter and more robust pitch change actuation across an exhaust flowpath. Axially spaced counter-rotatable forward and aft rows of forward and aft propellers mounted on forward and aft rotatable frames include a flowpath passing through the forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators mounted on the aft rotatable frames are mounted radially inwardly of the flowpath in a one to one ratio with forward and aft rotatable struts extending radially across the flowpath and connected to and operable for controlling and setting pitch of the aft propellers. Rotatable shafts extend through the rotatable struts and connect the pitch change actuators to the propellers. The pitch change actuators may be ganged together by unison rings having ring teeth engaging gear teeth on gears connected to the actuators or the rotatable shafts.
B64C 11/38 - Mécanismes de changement de pas des pales par fluide, p. ex. hydrauliques
F01D 1/24 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur caractérisées par des rotors contra-rotatifs soumis au même courant de fluide énergétique sans aubes ou structures analogues intermédiaires sur les stators
Systems and a method for storing data are provided. The protected memory system includes a memory array in-cluding a plurality of memory modules each separately located with respect to each other and a memory controller configured to receive data to be stored from the data acquisition unit, store the received data in corresponding memory locations in each of the plurality of memory modules wherein the stored data including error checking information, read data from a first one of the plural-ity of memory modules until a data error is detected at a first memory location, read data from a second memory location of a sec-ond one of the plurality of memory modules wherein the data read from the second memory location corresponds to the data read from the first memory location, and replace the data read from the first memory location with the data read from the second mem-ory location.
A power generation system is provided. The system includes a carbon-dioxide waste heat recovery Rankine cycle, integrated with an absorption chiller cycle. The Rankine cycle includes a condenser and a desorber. The condenser of the Rankine cycle is combined with the evaporator of the absorption chiller cycle. The Rankine cycle and the absorption chiller cycle can be integrated at the desorber.
F01K 13/00 - Dispositions générales ou processus généraux de fonctionnement des installations complètes d'ensembles fonctionnels de machines à vapeur
F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
F01K 27/02 - Ensembles fonctionnels modifiés pour utiliser la chaleur perdue autre que celle provenant de l'évacuation, p. ex. la chaleur de frottement à l'intérieur de la machine motrice
49.
MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD
A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment (24) comprising low-ductility material and having a cross- sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure (72) surrounding the shroud segment (24); and a load spreader (92) received in the shroud cavity of the shroud segment (24) and mechanically coupled to the stationary structure (72). The load spreader (92) includes: a laterally-extending plate (96) with opposed inner and outer faces; and a boss (102) which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments (24). A fastener engages the boss (102) and the stationary structure (72), so as to clamp the boss (102) against the stationary structure (72) in a radial direction.
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
F01D 25/26 - Carcasses d'enveloppe doublesMesures contre les tensions thermiques dans les carcasses d'enveloppe
F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
The present invention relates to methods for myelin basic protein detection comprises identifying a subject at risk of or diagnosed with a myelin-associated neuropathy, parenterally administering to the subject the agent, and determining myelination in the subject by detecting binding to myelin basic protein. Methods for the detection of myelin and a quantitative measurement of its local concentration in a sample using an agent with specific binding to myelin basic protein are also provided as is a kit containing the agent or its derivatives for use in detecting myelin basic protein.
A system for optimal planning of electric power demand is presented. The system includes a node having one or more smart charging plug-in electric vehicles (SCPEVs), a processing subsystem. The processing subsystem receives relevant data from one or more sources; and determines an optimized SCPEV load and optimal charging schedule for the node by applying an operations research technique on the relevant data.
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
A multi-frequency eddy current (MFEC) inspection system is provided for inspection of case hardening depth on a part. The MFEC inspection system comprises a generator configured to generate one or more multi-frequency excitation signals and an eddy current probe configured to be disposed at one side of the part. The eddy current probe comprises one or more drivers and one or more pickup sensors. The one or more drivers are configured to receive the one or more multi- frequency excitation signals to induce eddy currents in the part. The one or more pickup sensors are configured to detect the induced eddy currents within a local area of the part to generate one or more multi-frequency response signals. The MFEC system further comprises a processor configured to receive the one or more multi- frequency response signals for processing to determine a case hardening depth of the local area of the part. A pulse eddy current inspection system and an eddy current inspection method are also presented.
G01B 7/06 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques pour mesurer la longueur, la largeur ou l'épaisseur pour mesurer l'épaisseur
53.
TRANSDUCER APPARATUS AND METHOD FOR ASSEMBLING A TRANSDUCER APPARATUS
According to one aspect of the invention, a transducer apparatus is provided that includes a core section, a transducer disposed in the core section, the transducer configured to transmit or receive signals and a tubular member mounted to the core section for relative rotation, wherein a fluid is disposed in the tubular member. The apparatus further includes a weight reduction device disposed inside the tubular member to occupy a volume inside the tubular member, wherein the weight reduction device is configured to provide a transmission path from the transducer to the tubular member via the fluid.
A device (20) is disclosed that, in an illustrative embodiment, includes an input line (201), a main gain component (229), a first local gain component (221), and a second local gain component (222). The main gain component (229), the first local gain component (221), and the second local gain component (222) each have a communicative connection with the input line (201). The main gain component (229) is configured for applying a main gain to an ultrasonic wave signal received via the input line (201), thereby providing a main gain signal (151,157). The first local gain component (221) is configured for applying a first local gain to a portion of the ultrasonic wave signal within a first signal gate (113), and thereby providing a first local gain signal (153). The second local gain component (222) is configured for applying a second local gain to a portion of the ultrasonic wave signal within a second signal gate (115), and thereby providing a second local gain signal (155).
A ceramic shroud assembly (99) includes a tip shroud (88) having an outer platform (86) supporting at least one seal tooth (91), a shroud cap (96) less brittle than the outer platform (86) and including a shroud cap base (98) on the outer platform (86), and clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces (152, 153) located at clockwise and counter-clockwise distal ends (124, 126) respectively of the base. A rotor (34) assembly may include a circumferential row (38) of turbine blades (70) made of a ceramic material and extending radially outwardly from a disk (73) of a turbine rotor (34). The turbine blades (70) include airfoils (72) having the airfoil tip shrouds (88) and the shroud caps (96) at blade tips (77). The clockwise and counter-clockwise contact surfaces (152, 153) of circumferentially adjacent ones (71) of the shroud caps (96) contact each other. The shroud (88) and the platform (86) may be made of a ceramic or ceramic matrix composite material and the shroud cap (96) may be made of a metallic material.
In one embodiment, the invention comprises a MOSFET comprising individual MOSFET cells. Each cell comprises a U-shaped well (228) (P type) and two parallel sources (260) (N type) formed within the well. A plurality of source rungs (262) (doped N) connect sources (260) at multiple locations. Regions between two rungs (262) comprise a body (252) (P type). These features are formed on an N-type epitaxial layer (220), which is formed on an N-type substrate (216). A contact (290) extends across and contacts a plurality of source rungs (262) and bodies (252). Gate oxide and a gate contact overlie a leg of a first well and a leg of a second adjacent well, inverting the conductivity responsive to a gate voltage. A MOSFET comprises a plurality of these cells to attain a desired low channel resistance. The cell regions are formed using self- alignment techniques at several states of the fabrication process.
An imaging system includes a positionable device configured to axially shift an image plane, wherein the image plane is generated from photons emanating from an object and passing through a lens, a detector plane positioned to receive the photons of the object that pass through the iens, and a computer programmed to characterize the lens as a mathematical function, acquire two or more elemental images of the object with the image plane of each elemental image at different axial positions with respect to the detector plane, determine a focused distance of the object from the lens, based on the characterization of the lens and based on the two or more elemental images acquired, and generate a depth map of the object based on the determined distance.
A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.
B23P 15/04 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe d'aubes de turbine ou d'organes équivalents, en plusieurs pièces
F01D 5/16 - Forme ou structure pour contrebalancer les vibrations des aubes
F01D 5/26 - Dispositifs antivibratoires non limités à la forme ou à la structure des pales ou aux connections aube à aube
F01D 5/30 - Fixation des aubes au rotorPieds de pales
59.
METHOD FOR REFURBISHING PTAL COATING TO TURBINE HARDWARE REMOVED FROM SERVICE
A method of repairing airfoils damaged during operation and removed from service. The method comprises the steps of stripping any thermal barrier coatings from the airfoil. After the thermal barrier coatings are removed, cracks are removed from the airfoil. Cracks usually appear in the bond coat area over the fillet portion of the airfoil, which are removed by locally grit blasting the fillet portion of the airfoil. This operation also usually results in locally removing the bond coating from the fillet portion. Cracks and other foreign-object induced damage may be sustained by the airfoil tip, which is removed and replaced by welding superalloy material. The airfoil then may be cleaned by thermal etching. The airfoil is then placed in a plating tool that permits preferential plating of areas of the airfoil from which plating has been removed. After plating, the airfoil is then diffusion heat treated to diffuse the platinum coating with the superalloy substrate materials. The diffusion heat treated airfoil is then aluminided by any aluminiding process to form a PtAl coating.
B23P 6/00 - Remise en état ou réparation des objets
C23C 8/06 - Diffusion à l'état solide uniquement d'éléments non métalliques dans la couche superficielle de matériaux métalliquesTraitement chimique de surface par réaction entre le matériau métallique de la surface et un gaz réactif, laissant dans le revêtement des produits de la réaction, p. ex. revêtement de conversion, passivation des métaux au moyen de gaz
C23C 28/00 - Revêtement pour obtenir au moins deux couches superposées, soit par des procédés non prévus dans un seul des groupes principaux , soit par des combinaisons de procédés prévus dans les sous-classes et
C25D 3/50 - Dépôt électrochimiqueBains utilisés à partir de solutions de métaux du groupe du platine
A turbine power generation system with enhanced stabilization of refractory carbides provided by hydrocarbon from high carbon activity gases is disclosed. The disclosure also includes a method of using high carbon activity gases to stabilize hot gas path components.
A method to develop a software based sequencer for a turbine including: selecting a general purpose sequencer software module having standardized software for sequencing turbines through defined states of operation; selecting options from predefined settings presented by the sequencer software module, wherein the selected options define operational events of the turbine which trigger the sequencer to transition the turbine from one of the defined states to the next defined state, and using the general purpose sequencer software configured with the selected options for the settings.
F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
F01K 7/00 - Ensembles fonctionnels de machines à vapeur caractérisés par l'emploi de types particuliers de machines motricesEnsembles fonctionnels ou machines motrices caractérisés par un circuit de vapeur, un cycle de fonctionnement ou des phases particuliersDispositifs de commande spécialement adaptés à ces systèmes, cycles ou phasesUtilisation de la vapeur soutirée ou de la vapeur d'évacuation pour le réchauffage de l'eau d'alimentation
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
G05B 19/045 - Commande à programme autre que la commande numérique, c.-à-d. dans des automatismes à séquence ou dans des automates à logique utilisant des machines à états logiques composées uniquement d'une mémoire ou d'un dispositif logique programmable contenant la logique de la machine commandée et dans lesquelles l'état de ses sorties dépend de l'état de ses entrées, ou d'une partie des états de sa propre sortie, p. ex. contrôleurs de décision binaire, automates finis
62.
MOLD AND FACECOAT COMPOSITIONS AND METHODS FOR CASTING TITANIUM AND TITANIUM ALUMINIDE ALLOYS
The disclosure relates generally to mold compositions and methods of molding and the articles so molded. More specifically, the disclosure relates to mold compositions, intrinsic facecoat compositions, and methods for casting titanium-containing articles, and the titanium-containing articles so molded.
B22D 15/00 - Coulée utilisant un moule ou un noyau dont une partie importante, pour le procédé, est de conductibilité thermique élevée, p. ex. coulée contre refroidisseursMoules ou accessoires spécialement adaptés à cette technique
255324AB STRACTA method of processing a titanium aluminide intermetallic composition based on a TiAl intermetallic compound to yield a duplex microstructure containing equiaxed and lamellar morphologies of a gamma TiAl phase. The method includes hot isostatic pressing the titanium aluminide intermetallic composition in an inert atmosphere at a temperature of at least 1260 C, cooling the titanium aluminide intermetallic composition to a temperature of not less than 1120 C, heat treating the titanium aluminide intermetallie composition at a temperature of 1150 to 1200 C and then cooling the titanium aluminide intermetallic composition to room temperature. The titanium aluminide intermetallic composition exhibits the duplex microstructure following the step of cooling the titanium aluminide intermetallic composition to room temperature. The titanium aluminide intermetallic composition consists of titanium and aluminum in amounts to yield the TiAl intermetallic compound, one or more of chromium, niobium and tantalum, and incidental impurities.CA 2809444 2020-02-19
A process for producing silicon-containing CMC articles. The process entails producing a matrix slurry composition that contains at least one resin binder and a SiC powder. The SiC powder is a precursor for a SiC matrix of the CMC article and the resin binder is a precursor for a carbon char of the matrix. A fiber reinforcement material is impregnated with the slurry composition to yield a preform, which is then heated to form a porous preform that contains the SiC matrix and porosity and to convert the resin binder to the carbon char that is present within the porosity. Melt infiltration of the porosity is then performed with molten silicon or a molten silicon-containing alloy to react the carbon char and form silicon carbide that at least partially fills the porosity within the porous preform. The carbon char constitutes essentially all of the elemental carbon in the porous preform.
C04B 35/653 - Procédés comportant une étape de fusion
C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
C22C 47/08 - Fabrication d'alliages contenant des fibres ou des filaments métalliques ou non métalliques par mise en contact des fibres ou des filaments avec un métal fondu, p. ex. en imprégnant les fibres ou les filaments placés dans un moule
65.
HYDRAULIC SYSTEM FOR FAN PITCH CHANGE ACTUATION OF COUNTER-ROTATING PROPELLERS
Spaced apart counter-rotatable forward and aft rows of forward and aft propellers are mounted on forward and aft rotatable frames. Hydraulic rotary forward and aft pitch change actuators on the frames are operable for controlling pitch of the propellers. A hydraulic fluid supply outboard of the frames is connected to forward and aft rotary unions which are operable for transferring hydraulic fluid between forward and aft union stators to forward and aft union rotors mounted within the forward and aft rotary unions. The forward union rotor is operable to transfer the hydraulic fluid from the forward rotary union to the aft pitch change actuators and the aft union rotor is operable to transfer the hydraulic fluid from the aft rotary unions to the forward pitch change actuators. The forward and aft rotatable frames counter-rotatably mounted on a structural frame located forward or aft of the propellers.
A method for operating a wind turbine is provided. The method includes determining a wind condition, determining for the wind condition expected azimuthal positions of a rotating wind rotor of the wind turbine, and determining for the wind condition desired azimuthal positions of the rotating wind rotor so that at least one of a load balance of the rotating wind rotor and a power uptake of the rotating wind rotor is improved compared to the expected azimuthal positions.
An eddy current probe, for detecting a defect in a test object is constructed with four coils in a wheatstone bridge configuration. A first coil and a second coil are electrically connected to a first voltage terminal for receiving a drive voltage, and a third coil and a fourth coil are electrically connected to a second voltage terminal for being coupled to a ground. The first and the second coils are drive coils and the third and the fourth coils are receive coils. The first coil is electrically connected to the third coil at a first bridge terminal, and the second coil is electrically connected to the fourth coil at a second bridge terminal. A voltage difference between the first and second bridge terminals indicates the defect in the test object when the four coils of the probe are inside the test object.
G01N 27/904 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant des variables magnétiques pour rechercher la présence des criques en utilisant les courants de Foucault avec plusieurs capteurs
68.
DEVICE HAVING REDUCED BIAS TEMPERATURE INSTABILITY (BTI)
A semiconductor device is disclosed along with methods for manufacturing such a device. In certain embodiments, the semiconductor device includes a source electrode formed using a metal that limits a shift. such as due to bias temperature instability, in a threshold voltage of the semiconductor device during operation. In certain embodiments the semiconductor device may be based on silicon carbide.
Imaging agents comprising an isolated polypeptide conjugated with a radionucleide and a chelator; wherein the isolated polypeptide binds specifically to HER2, or a variant thereof; and methods for preparing and using these imaging agents.
C07K 14/31 - Peptides ayant plus de 20 amino-acidesGastrinesSomatostatinesMélanotropinesLeurs dérivés provenant de bactéries provenant de Micrococcaceae (F) provenant de Staphylococcus (G)
70.
DEVICE AND METHOD FOR PREVENTING LEAKAGE OF AIR BETWEEN MULTIPLE TURBINE COMPONENTS
A turbine comprising a first turbine component being of a first material having a first coefficient of thermal expansion. A second turbine component being of a second material having a second coefficient of thermal expansion, said second turbine component adjacent said first turbine component. A space between said first and second turbine components. A seal assembly sealing said space, wherein at least a portion of said seal assembly has a coefficient of thermal expansion substantially similar to at least one of said first or second turbine components to thereby maintain a seal in said space during thermal expansion or contraction of said first and second turbine components.
A method for repairing" a degraded bolt hole in a casing flange by reaming and removing at least some corrosion on an inside and around the hole to form a reamed hole, mounting the flange to float relative to upper and lower electrodes of a welding machine, radially and axially clamping an area of the flange surrounding the reamed hole, placing upper and lower filler slugs in the reamed hole, placing the electrodes against upper and lower filler slugs and applying a welding current through the electrodes while applying pressure to the filler slugs with the electrodes and resistively heating- and melting- the filler slugs to form a weldment, and pulsing the welding current on and off. Pulsing may be performed with progressively increasing amounts of current. In situ tempering under the pressure of the electrodes may be performed on a substantially liquid pool formed by the welding current.
A semiconductor device includes a drift layer disposed on a substrate. The drift layer has a non-planar surface having a plurality of repeating features oriented parallel to a length of a channel of the semiconductor device. Further, each the repeating features have a dopant concentration higher than a remainder of the drift layer.
H01L 21/04 - Fabrication ou traitement des dispositifs à semi-conducteurs ou de leurs parties constitutives les dispositifs ayant des barrières de potentiel, p. ex. une jonction PN, une région d'appauvrissement ou une région de concentration de porteurs de charges
H10D 62/60 - Distribution ou concentrations d’impuretés
73.
METAL-OXIDE-SEMICONDUCTOR (MOS) DEVICES WITH INCREASED CHANNEL PERIPHERY AND METHODS OF MANUFACTURE
A semiconductor device includes a silicon carbide (SiC) drift layer disposed on a (0001) oriented SiC substrate. The SiC drift layer has a non-planar surface including a plurality of repeating features that are oriented parallel to a length of a channel of the semiconductor device. Further, the channel region is disposed in a particular crystallographic plane of the SiC drift layer.
One method for developing a data loss prevention model includes receiving, at a processing device, an event record corresponding to an operation performed on a computing device. The event record includes an event type and event data. The method also includes transforming, using the processing device, the event type to an event number corresponding to the event type. The method includes transforming, using the processing device, the event data to a numerical representation of the event data. The method includes associating an indication of whether the event type and the event data correspond to a data loss event with the event number and the numerical representation. The method also includes determining the data loss prevention model using the indication, the event number, and the numerical representation.
Systems and methods of the invention relate to circuitry that isolates low power circuitry of a battery management system. One or more circuits can be utilized with a battery management system to provide isolation of low power circuitry from at least one of a high voltage, noise interference from a battery, noise interference from a high voltage, sensor signals, control signals, among others. The circuitry further provides high voltage from a grid to be stepped-down to a voltage level usable by circuitry, port(s), and/or a processor.
H02J 1/00 - Circuits pour réseaux principaux ou de distribution, à courant continu
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02M 3/04 - 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
76.
METHOD AND SYSTEM FOR CONTROLLING ENERGY STORAGE DEVICE
A system and method of use including a controller responsive to a deviation in absolute value or relative slope and operable to terminate a discharge operation in an energy storage device is provided. The absolute value or relative slope is determined at sampling frequency based upon a combination of measured operating parameters, for example, potential and current. Any deviation in the absolute value or relative slope indicates that a threshold limit in the available energy of the system has been reached, for example when active materials in the device are at a point of depletion, indicating a need to cease the discharge operation. The system and method operate on a real-time basis, providing instantaneous SOH information with regard to the device.
THE UNITED STATES OF AMERICA, AS REPRESENTED BY THE SECRETARY, DEPARTMENT OF HEALTH AND HUMAN SERVICES (USA)
Inventeur(s)
Skloss, Timothy William
Murray, Jonathan Alan
Ardenkjaer Larsen, Jan Henrik
Cherukuri, Murali Krishna
Bernardo, Marcelino
Devasahayam, Nallathamby
Abrégé
A system and method for transporting a hyperpolarized substance is disclosed. A transport vessel for transporting such a hyperpolarized substance includes a vessel housing, a chamber formed within the vessel housing that is configured to receive a container holding a hyperpolarized substance, and an electromagnet configured to generate a magnetic containment field about the chamber when a current is supplied thereto, the magnetic containment field comprising a homogeneous magnetic field. The transport vessel also includes a non-magnetic power source to supply the current to the electromagnet and a control circuit configured to selectively interrupt the supply of current to the electromagnet so as to control generation of the magnetic containment field, with the transport vessel being magnetically inert when the supply of current to the electromagnet is interrupted by the control circuit.
A compression system (40) is disposed in a container (120) and shipped to a location having a supply of natural gas (140,142). The compressionsystem connects to the natural gas supply (14) for eample from the natural gas network, compresses (40, 44, 60, 76, 88) gas from the supply, and provides compressed gas to a consumer (after 144, 146). The container, which can be a standardized ISO shipping container, is fitted with removable vents (164, 168, 172) at designated locations. Strategic positioning of com-pression system components in combination with the removable vents allows for ready access to the compression system for repair and maintenance.
F17C 5/00 - Procédés ou appareils pour remplir des récipients sous pression de gaz liquéfiés, solidifiés ou comprimés
F17C 5/06 - Procédés ou appareils pour remplir des récipients sous pression de gaz liquéfiés, solidifiés ou comprimés pour le remplissage avec des gaz comprimés
F17C 13/08 - Dispositions de montage des récipients
F17C 13/12 - Aménagements ou montage de dispositifs pour prévenir ou atténuer les effets d'explosion
CENTRE FOR PROBE DEVELOPMENT AND COMMERCIALIZATION (Canada)
Inventeur(s)
Carter, Randall Lee
Johnson, Bruce Fletcher
Sood, Anup
Rishel, Michael James
Stephenson, Karin Ann
Valliant, John Fitzmaurice
Wu, Tao
Yang, Yang
Abrégé
The present invention relates to radioiodinated vectors, especially radioiodinated radiopharmaceuticals and methods for their preparation. The invention provides methods that enable the preparation and purification of radioiodinated vectors, wherein the method comprises contacting a biotin-containing tin precursor with a radioactive iodide and an oxidant to form a reaction mixture and scavenging of biotin by avidin or streptavidin in the preparation of radioiodinated compounds, without the need for HPLC purification, as well as precursors which include biotin-like substituents useful in such methods.
A process for producing components containing ceramic materials. The process entails forming a first region of a component with plies containing a reinforcement material in a precursor of a ceramic material. The plies include at least a first set of plies between at least second and third sets of plies. Distal portions of the second and third sets of plies are then folded away from the first set of plies so that they are oriented transverse to the first set of plies. A fourth set of plies is then interleaved among the folded distal portions of the second and third sets of plies.
B29B 11/16 - Fabrication de préformes caractérisées par la structure ou la composition comprenant des charges ou des agents de renforcement
B29C 70/24 - 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 caractérisées par la structure des renforcements fibreux utilisant des fibres de grande longueur, ou des fibres continues orientées dans au moins trois directions formant une structure tridimensionnelle
B32B 3/04 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords caractérisés par une couche pliée au bord, p. ex. par-dessus une autre couche
B32B 18/00 - Produits stratifiés composés essentiellement de céramiques, p. ex. de produits réfractaires
B32B 37/14 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
B32B 38/00 - Opérations auxiliaires liées aux procédés de stratification
C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
A gearbox support apparatus includes: a gearbox carrier (16) having a central axis, the carrier (16) configured to mount one or more rotating gears (12, 18, 22) therein, the carrier (16) including spaced-apart forward and aft walls (26, 28), and a flexible center plate structure (58) disposed between the forward and aft walls (26, 28), an annular support ring (60) disposed axially adjacent to the carrier (16); and a plurality of axially- extending torque fingers (68) interconnecting the support ring (60) and the center plate structure (58).
A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.
A method is provided for forming a composite article to have a primary composite structure and an integral secondary composite structure that extends out of a plane defined by the primary composite structure. The method includes laying-up first plies to construct the primary composite structure. The first plies contain continuous reinforcement material and extend from a first zone that will define the primary composite structure into a second zone that will define the secondary composite structure. During laying-up of the first plies, additional plies are interleaved with the first plies within the second zone but not the first zone. The additional plies originate within a build-up zone between the first and second zones and extend therefrom into the second zone. After interleaving the plies, the build-up zone is deformed to orient the second zone and form the secondary composite structure that extends out of the plane defined by the continuous reinforcement material of the first plies.
B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
84.
SEMICONDUCTOR DEVICE WITH JUNCTION TERMINATION EXTENSION
A semiconductor device (200) is provided and includes a substrate (202) comprising silicon carbide; a drift layer (214) disposed over the substrate and comprising a drift region (214) doped with a first (n-type) dopant type, so as to have a first conductivity type; and a second region (216) adjacent to the drift region and proximal to a surface (204) of the drift layer. The second region is doped with a second (p-type) dopant type, so as to have a second conductivity type. The semiconductor device further includes a junction termination extension (JTE) (220) disposed adjacent to the second (well) region. The JTE has a width Wjte and comprises a number of discrete regions (221) separated in a first direction and in a second direction and doped with varying concentrations of the second (p-type) dopant type, so as to have an effective doping profile of the second conductivity type of a functional form that generally decreases along a direction away from the edge of the primary blocking junction (230). The width wjte is less than or equal to a multiple of five times the width of the one- dimensional depletion width (Wdepi ID), and the charge tolerance of the semiconductor device is greater than 1.0 xl013 per cm2.
H01L 21/266 - Bombardement par des radiations ondulatoires ou corpusculaires par des radiations d'énergie élevée produisant une implantation d'ions en utilisant des masques
85.
SYSTEM AND METHOD FOR ULTRASONIC TESTING WITH A SINGLE CHANNEL ULTRASONIC TEST UNIT
A device and method for ultrasonic inspection of a test object is disclosed. A plurality of ultrasonic transducer elements and electrical pulser circuits are provided for generating and transmitting electrical pulses. The device has an interface configured to communicate with a single channel ultrasonic testing unit.
A process for producing airfoil components containing ceramic-basedmaterials and having a tip cap. The process entails forming an airfoil portion of the component from an airfoil portion material that contains a precursor of a ceramic-based material. The airfoil portion material defines concave and convex walls of the airfoil portion, and the concave and convex walls define a tip region of the airfoil portion and at least one cavity within the airfoil portion. At least a first ply is formed that contains a precursor of a ceramic-based material, and the first ply at least partially closes the cavity at the tip region of the airfoil portion. The airfoil portion material and the first ply are then cured so that the first ply forms a tip cap that closes the cavity and the precursors of the airfoil portion material and first ply are converted to the ceramic-based materials thereof.
The method includes: dividing the wind farm into a first group of wind turbines to be operated in a non-curtailed mode and a second group of wind turbines to be operated in a curtailed mode for providing a power reserve for the wind farm; determining an actual power production of the first group of wind turbines; estimating a possible maximum power production of the second group at a given environmental condition; estimating a possible maximum power output of the wind farm using the actual power production of the first group and the possible maximum power production of the second group; estimating the power reserve using the possible maximum power output; and updating a power setpoint for at least one wind turbine of the second group so that an expected power production of the second group of wind turbines substantially matches a difference between the possible maximum power production and the power reserve Furthermore, a wind farm is provided.
F03D 7/00 - Commande des mécanismes moteurs à vent
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
H02P 9/04 - Commande s'exerçant sur un moteur primaire non électrique et dépendant de la valeur d'une caractéristique électrique à la sortie de la génératrice
88.
SYSTEM AND METHOD FOR GENERATING AN ACTIVITY SUMMARY OF A PERSON
In accordance with one aspect of the present technique, a method includes receiving one or more videos from one or more image capture devices. The method further includes generating a video- loop of the person from the one or more videos. The video-loop depicts the person in the commercial site. The method also includes generating an action clip from the video-loop. The action clip includes a suspicious action performed by the person in the commercial site. The method further includes generating an activity summary of the person including the video-loop and the action clip.
A journal bearing 11 for use in an epicyclical gearbox 10 including a journal pin 14, a journal bearing body 25 into which the journal pin 14 is disposed and at least one lubricating fluid inlet. The lubricating fluid inlet is configured to provide for an input of a lubricating fluid in a loaded arc portion proximate at least one high pressure point exerted upon the journal bearing body 25 during a high pressure event, thereby permitting a free flow of a lubricating fluid there between the journal pin 14 and the journal bearing body 25 during the high pressure event. In an embodiment, the journal pin 14 is configured to mimic the shape of the journal bearing body 25 at least at a high pressure point exerted upon the journal bearing body 25 during a high pressure event. An epicyclical gearbox 10 including the journal bearing 11 and method of facilitating a hydrodynamic oil flow in the planet gear journal bearing.
A nickel-based superalloy composition includes from about 5 to about 7 wt% aluminum, from about 4 to about 8 wt% tantalum, from about 3 to about 8 wt% chromium, from about 3 to about 7 wt% tungsten, from 1 to about 5 wt% molybdenum, from 1.5 to about 5 wt% rhenium, from 5 to about 14 wt% cobalt, from about 0 to about 1 wt% hafnium, from about 0.01 to about 0.03 wt% carbon, from about 0.002 to about 0.006 wt% boron, and balance nickel and incidental impurities. The composition may exhibit a sustained peak low cycle fatigue life at 1800°F/45 ksi of at least about 4000 cycles. The nickel-based superalloy composition may be used in single- crystal or directionally solidified superalloy articles, such as a blade, nozzle, a shroud, a splash plate, and a combustor of a gas turbine engine.
An ultrasonic signal coupler includes a pipe having a first ultrasonic waveguide and a second ultrasonic waveguide penetrating the pipe so that ultrasonic transducers attached to ends of the ultrasonic waveguides communicate ultrasonic signals through the ultrasonic waveguides directly through a fluid traveling through the pipe.
92.
THRUST REVERSER SYSTEM WITH TRANSLATING-ROTATING CASCADE AND METHOD OF OPERATION
A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumferential opening. The cascade system is deployed from a stowed position as the translating cowl and the cascade system are translated in the aft direction. During deployment of the cascade system, a fore end thereof translates in the aft direction and an aft end thereof initially translates in the aft direction and then subsequently rotates about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to a deployed position and divert bypass air within a bypass duct of the engine through the circumferential opening.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending incompletely between the first lateral wall and the second lateral wall in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, to provide a gap between the vorticor pin and the ceiling, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.
A thrust reverser system and operation suitable for turbofan engines. Blocker doors of the thrust reverser system have stowed positions in which each door is disposed between a fixed structure and a translating cowl of the engine. The translating cowl is translated in an aft direction of the engine to define at least one opening with the fixed structure, after which the translating cowl is further translated aft to deploy linkage mechanisms that are received in slots recessed into the blocker doors and pivotably connect the doors to the fixed structure. Deployment of the linkage mechanisms from the slots causes the blocker doors to rotate to a deployed position in which each door extends across a bypass duct of the engine and diverts bypass air within the duct through the opening.
F02K 1/72 - Inversion du flux de la soufflante utilisant des volets inverseurs de poussée ou des portes montées sur le carter de la soufflante la partie arrière du carter de la soufflante étant mobile pour découvrir des ouvertures d'inversion de poussée dans le carter de la soufflante
95.
METHODS AND SYSTEMS FOR REDUCING SILICA RECESSION IN SILICON-CONTAINING MATERIALS
The present disclosure relates to a method and a system for reducing silica recession of silicon-containing ceramics or silicon-containing ceramic composites, particularly those exposed to a combustion gas or to combustion gas environments, including those exposed to high temperature combustion gas environments. The method and system involve removal of moisture from compressed air prior to co-mingling the treated compressed air with the combustion gas to which the silicon-containing ceramics or silicon-containing ceramic composites are exposed.
C04B 41/80 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle de céramiques uniquement
F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
96.
ENVIRONMENTAL BARRIER COATINGS AND METHODS THEREFOR
An article includes a silicon-containing region including surface features on a surface thereof. The surface features include depressions, protuberances, or combinations thereof. At least one outer layer overlies the surface of the silicon- containing region. A constituent layer is provided on the surface of the silicon-containing region and between and contacting the silicon-containing region and the at least one outer layer. The constituent layer is formed by constituents of the silicon-containing region and is susceptible to creep within an operating environment of the article. The surface features physically interlock the at least one outer layer with the silicon- containing region through the constituent layer.
A method of fabricating a semiconductor device cell at a surface of a silicon carbide (SiC) semiconductor layer includes forming a segmented source and body contact (SSBC) of the semiconductor device cell over the surface of the SiC semiconductor layer. The SSBC includes a body contact portion disposed over the surface of the semiconductor layer and proximate to a body contact region of the semiconductor device cell, wherein the body contact portion is substantially disposed over the center of the semiconductor device cell. The SSBC also includes at least one source contact portion disposed over the surface of the semiconductor layer and proximate to a source contact region of the semiconductor device cell, wherein the at least one source contact portion only partially surrounds the body contact portion of the SSBC.
H10D 62/13 - Régions semi-conductrices connectées à des électrodes transportant le courant à redresser, amplifier ou commuter, p. ex. régions de source ou de drain
98.
CRYOGENIC TANK ASSEMBLY WITH A RECIRCULATION CONDUIT
A cryogenic tank assembly includes a cryogenic tank having an internal volume that is configured to contain liquefied natural gas (LNG). The cryogenic tank includes an inlet and an outlet that are each fluidly connected to the internal volume. The assembly includes a recirculation conduit coupled in fluid communication between the inlet and the outlet. The recirculation conduit extends along a path between the inlet and outlet external to the internal volume of the cryogenic tank such that the path is configured to be exposed to an ambient environment of the cryogenic tank. The recirculation conduit is configured to: receive a flow of LNG from the internal volume through the outlet; transfer heat from the ambient environment to the LNG flow to change the LNG flow to a flow of natural gas; and inject the natural gas flow into the internal volume of the cryogenic tank through the inlet.
A non-transitory computer readable medium may include executable instructions which, when executed by a processor, cause the processor to transmit device identification information and to receive a space requirement based on a digital content. The instructions further cause the processor to compare a memory space to the space requirement, and if the memory space is greater than the space requirement, receive a digital content based on the device identification, wherein the digital content is configured to be executed by, used by, or displayed by a non-destructive testing (NDT) device, or a combination thereof.
A system includes a non-destructive testing (NDT) system having an NDT probe and a processor. The NDT probe includes a testing sensor and a motion sensor. The testing sensor is configured to capture sensor data from an inspection area, and the motion sensor is configured to detect a measurement speed at which the NDT probe moves relative to the inspection area. The processor is configured to determine a speed comparison between the measurement speed and a reference speed range.
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