An aircraft engine is provided. The aircraft engine includes a compressor section having a compressor. A turbine section is downstream of the compressor section. The turbine section includes a turbine having turbine blades arranged in counter rotating stages. The aircraft engine further includes one or more fluid supply lines and a fuel cell assembly fluidly coupled to the one or more fluid supply lines for receiving one or more input fluids. The fuel cell assembly is in fluid communication with the turbine section to provide one or more output products to the turbine section. The aircraft engine further includes a heat exchanger in fluid communication with the turbine downstream of the counter rotating stages of turbine blades to receive exhaust gases from the turbine. The heat exchanger is thermally coupled to the one or more fluid supply lines of the fuel cell assembly.
F02C 7/22 - Systèmes d'alimentation en combustible
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
F02K 3/08 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande
A turbomachine engine including a high-pressure compressor, a high-pressure turbine, a combustion chamber in flow communication with the high-pressure compressor and the high-pressure turbine, and a power turbine in flow communication with the high-pressure turbine. At least one of the high-pressure compressor, the high-pressure turbine, and the power turbine comprises a ceramic matrix composite (CMC) material. The turbomachine engine includes a low-pressure shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. The low-pressure shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). The turbomachine engine is configured to operate up to the redline speed without passing through a critical speed associated with a first-order bending mode of the low-pressure shaft.
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
F02C 7/06 - Aménagement des paliers; Lubrification
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
3.
METHODS OF JOINING BLADE COMPONENTS OF WIND TURBINE ROTOR BLADES USING POSITIONING ELEMENTS
A method of joining first and second blade components of a rotor blade of a wind turbine includes providing corresponding first and second positioning elements at an interface of the first and second blade components. The method also includes aligning and securing the first positioning element of the first blade component with the second positioning element of the second blade component so as to temporarily secure the first and second blade components together. Further, the corresponding first and second positioning elements maintain a desired spacing between the first and second blade components. Moreover, the method includes permanently securing the first and second blade components together such that the desired spacing is maintained between the first and second blade components.
A system for spacing and fastening tubular structures, and a related method. The system includes a spacer element configured to engage a plurality of tubular structures, to spatially separate the plurality of tubular structures from one another, and to distribute stress in the plurality of tubular structures. The system further includes a fastening element configured to extend around at least a portion of an outer surface of the plurality of tubular structures, and to fasten the plurality of tubular structures to the spacer element in an adaptively spaced configuration.
F16L 3/22 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace
F16L 3/10 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection fractionnés, c. à d. à deux éléments en prise avec le tuyau, le câble ou le conduit de protection
F16L 3/233 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers spécialement adaptés pour supporter un certain nombre de tuyaux parallèles séparés par un espace pour un faisceau de tuyaux ou un ensemble de tuyaux disposés les uns à coté des autres en contact mutuel au moyen d'une bande flexible
5.
FOREIGN OBJECT DETECTION IN A WIRELESS POWER TRANSFER SYSTEM
This disclosure provides systems, methods and apparatuses for foreign object detection (FOD) in a wireless power transfer (WPT) system. Some implementations relate generally to the use of detection coils that are excited to measure and compare a differential current through a coil pair that includes at least two detection coils. A foreign object may cause a change in impedance for one or more detection coils compared to one or more other detection coils. By detecting the differential current of the coil pair, a detection apparatus may determine that a foreign object is in proximity to one of the detection coils of the coil pair. This disclosure provides several options for the design, construction, layout, and operations of detection coils to improve foreign object detection.
G01V 3/10 - Prospection ou détection électrique ou magnétique; Mesure des caractéristiques du champ magnétique de la terre, p.ex. de la déclinaison ou de la déviation fonctionnant au moyen de champs magnétiques ou électriques produits ou modifiés par les objets ou les structures géologiques, ou par les dispositifs de détection en utilisant des cadres inducteurs
H02J 50/60 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique sensibles à la présence d’objets étrangers, p.ex. détection d'êtres vivants
A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B60L 50/16 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion avec des dispositions pour une propulsion mécanique directe séparée,
B64C 21/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires en vue de l'aspiration
B64D 27/12 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur de la voilure ou fixés à celle-ci
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
F02K 3/04 - 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
General Electric Deutschland Holding GmbH (Allemagne)
Inventeur(s)
Vitt, Paul Hadley
Simonetti, Michael
Sharma, Ashish
Abrégé
A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway and another of the multiple guide vanes includes a heated fluid passageway.
Provided is a system and method that can safely generate and execute an outage plan for a power grid based on severe weather-driven events. In one example, the method may include receiving predicted or current operational power system state data from a power grid and weather conditions associated with the power grid, identifying one or more nodes on the power grid to de-energize based on the operational state data and the current weather conditions, determining a sequence of instructions to perform to de-energize the one or more identified nodes based on the operational state data and the current weather conditions associated with the power grid, and generating an outage plan including mitigation steps for ensuring the stability and security of the power grid which includes the determined sequence of instructions to be executed and store the outage plan in the memory.
H02J 3/14 - Circuits pour réseaux principaux ou de distribution, à courant alternatif pour règler la tension dans des réseaux à courant alternatif par changement d'une caractéristique de la charge du réseau par interruption, ou mise en circuit, des charges du réseau, p.ex. charge équilibrée progressivement
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 réseau; Circuits 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
9.
DISPATCH ADVISOR TO ASSIST IN SELECTING OPERATING CONDITIONS OF POWER PLANT THAT MAXIMIZES OPERATIONAL REVENUE
A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.
G06Q 10/0631 - Planification, affectation, distribution ou ordonnancement de ressources d’entreprises ou d’organisations
G05B 13/04 - Systèmes de commande adaptatifs, c. à d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques impliquant l'usage de modèles ou de simulateurs
G06Q 10/20 - Administration de la réparation ou de la maintenance des produits
G06Q 30/018 - Certification d’entreprises ou de produits
G06Q 40/02 - Opérations bancaires, p.ex. calcul d'intérêts ou tenue de compte
G06Q 50/06 - Fourniture d'électricité, de gaz ou d'eau
10.
SYSTEMS AND METHODS FOR PILLAR EXTENSION IN TERMINATION AREAS OF WIDE BAND GAP SUPER-JUNCTION POWER DEVICES
A super-junction (SJ) device includes a first epitaxial (epi layer) that forms a first SJ layer of the SJ device and includes a second epi layer disposed on the first SJ layer that forms a device layer of the SJ device. An active area and a termination area of the first epi layer includes a first set of SJ pillars that have a particular doping concentration of a first conductivity type and a second set of SJ pillars that have the particular doping concentration of a second conductivity type. A termination area of the second epi layer includes one or more implanted regions that form a junction termination that overlaps with at least one SJ pillar of the first set of SJ pillars or the second set of SJ pillars in the termination area of the first epi layer.
H01L 29/06 - Corps semi-conducteurs caractérisés par les formes, les dimensions relatives, ou les dispositions des régions semi-conductrices
H01L 29/10 - Corps semi-conducteurs caractérisés par les formes, les dimensions relatives, ou les dispositions des régions semi-conductrices avec des régions semi-conductrices connectées à une électrode ne transportant pas le courant à redresser, amplifier ou commuter, cette électrode faisant partie d'un dispositif à semi-conducteur qui comporte trois électrodes ou plus
H01L 29/66 - Types de dispositifs semi-conducteurs
H01L 29/78 - Transistors à effet de champ l'effet de champ étant produit par une porte isolée
A motorized apparatus for use in maintaining a pipe having a sidewall defining an interior cavity is provided. The motorized apparatus includes a body assembly extending along a longitudinal axis, at least one maintenance device coupled to the body assembly, and a plurality of leg assemblies coupled circumferentially around the body assembly. The motorized apparatus also includes a plurality of drive mechanisms coupled to the plurality of leg assemblies. The plurality of drive mechanisms are configured to interact with the sidewall. The plurality of drive mechanisms include at least two wheels. The plurality of drive mechanisms are arranged to move the body assembly in a first direction parallel to the longitudinal axis, move the body assembly in a second direction perpendicular to the longitudinal axis, and rotate the body assembly around the longitudinal axis.
A guide for cutting a dowel pin of a rotor assembly is provided. The guide includes a catch basin, including a first catch basin portion and a second catch basin portion, and a shim. The first catch basin portion and the second catch basin portion form a cutting tool receiver. The shim extends from a first edge having a cross-section that is complementary to a surface of the rotor assembly. The first catch basin portion and the second catch basin portion form a receptacle that accommodates and retains portions of a dowel pin during and after removal of the dowel pin from the rotor assembly. The cutting tool receiver is defined by a receiver edge configured to guide a cutting surface of a cutting tool through a cross-section of a dowel pin.
A hybrid-electric gas turbine engine and method of operating includes independently controlling a first electric machine providing torque to a first shaft to maintain a desired clearance between a first set of blades rotatably coupled to the first shaft, and a casing.
F01D 11/18 - Régulation ou commande du jeu d'extrémité des aubes, c.à d. de la distance entre les extrémités d'aubes du rotor et le corps du stator par des moyens auto-réglables utilisant des éléments stator ou rotor ayant un comportement thermique déterminé, p.ex. isolation sélective, inertie thermique, dilatation différentielle
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/56 - Commande de l'alimentation en combustible combinée avec une autre commande de l'ensemble fonctionnel avec la commande de la transmission de puissance
14.
CLOSED-LOOP COOLING SYSTEM FOR A GAS TURBINE ENGINE
A closed-loop cooling system for a gas turbine engine, comprising: a pump having a pump inlet and a pump outlet; a first plurality of stator vanes defining first cooling cavities therein; and a second plurality of stator vanes, defining second cooling cavities therein, wherein the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet.
Systems and methods for high bandwidth control of thrust response for turbofan or turboprop engines are provided. Such systems and methods include an engine control system that processes a rate command and a feedback signal from an engine to generate separate fuel and electric machine control signals that respectively control fuel and electric machine dynamics of the engine to produce engine dynamics that result in desired thrust response.
Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.
F01D 11/14 - Régulation ou commande du jeu d'extrémité des aubes, c.à d. de la distance entre les extrémités d'aubes du rotor et le corps du stator
F01D 11/10 - 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 fluide d'obturation, p.ex. de la vapeur
17.
MATERIAL SYSTEMS FOR REPAIR OF THERMAL BARRIER COATING AND METHODS THEREOF
Methods for repairing a thermal barrier coating deposited on a component with localized spallation of the thermal barrier coating includes depositing a primer slurry on a thermally grown oxide of the component exposed by the localized spallation, depositing a ceramic slurry on the primer slurry, and heating the primer slurry and the ceramic slurry. The primer slurry includes a primer that includes at least one of a metal and a metal oxide. The ceramic slurry includes a ceramic material, a ceramic slurry binder material, and a ceramic slurry fluid carrier. Heating the primer slurry and the ceramic slurry forms a first chemical bond between the primer and the thermally grown oxide and a second chemical bond between the primer and the ceramic material.
F01D 5/00 - Aubes; Organes de support des aubes; Dispositifs de chauffage, de protection contre l'échauffement, de refroidissement, ou dispositifs contre les vibrations, portés par les aubes ou les organes de support
F01D 5/28 - Emploi de matériaux spécifiés; Mesures contre l'érosion ou la corrosion
Flow-metering fuel systems and related methods are disclosed. An example apparatus includes a pipe defining a flow path for fuel, the pipe fluidly coupled to a combustor, a first portion of the pipe having a first cross-sectional area, a second portion of the pipe having a second cross-sectional area smaller than the first cross-sectional area, the second portion downstream of the first portion, and an actuator to adjust a flow rate of the fuel in the pipe based on a first pressure of the fuel in the first portion of the pipe, a second pressure of the fuel in the second portion of the pipe, and a temperature of the fuel.
F02C 9/26 - Commande de l'alimentation en combustible
F02C 7/22 - Systèmes d'alimentation en combustible
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
A gas turbine engine includes a compressor rotor shaft assembly, an accessory gearbox, and a bowed-rotor mitigation drive device drivingly coupled with the accessory gearbox. The bowed-rotor mitigation drive device is driven during an engine startup phase so as to induce a mechanical load (mechanical energy) to the bowed-rotor mitigation drive device. The mechanical load (mechanical energy) is retained within the bowed-rotor mitigation drive device during operation of the gas turbine engine. The mechanical load (mechanical energy) retained within the bowed-rotor mitigation drive device is periodically released by the bowed-rotor mitigation drive device in a plurality of periods so as to provide, in each period, a driving force to the accessory gearbox, which provides the driving force to the compressor rotor shaft assembly to periodically rotate the compressor rotor shaft assembly.
i), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:
1 is equal to 13,200 inches per second during the high power operating condition.
Apparatus, systems, and articles of manufacture are disclosed to dynamically support axial thrust in pumps. Examples disclosed herein include a thrust bearing system including a thrust disc coupled to an impeller shaft; a first thrust pad coupled to a body of the pump, the first thrust pad positioned on a forward side of the thrust disc; a second thrust pad coupled to the body of the pump, the second thrust pad positioned on an aft side of the thrust disc; and a spring-loaded assembly integrated into the first and second thrust pads, the spring-loaded assembly connected to a pump outlet via a first flowline, the first flowline to transmit a working fluid from the pump outlet to the forward side of the thrust disc or the aft side of the thrust disc based on a position of the spring-loaded assembly.
F01D 25/16 - Aménagement des paliers; Support ou montage des paliers dans les stators
F01D 3/04 - "Machines" ou machines motrices avec équilibrage des poussées axiales effectué par le fluide énergétique la poussée axiale étant équilibrée par la poussée d'un piston d'équilibrage ou d'un organe analogue
F01D 15/08 - Adaptations pour la commande des pompes ou combinaisons avec celles-ci
A turbine system includes a foam generating assembly having an in situ foam generating device at least partially positioned within the fluid passageway of the turbine engine, such that the in situ foam generating device is configured to generate foam within the fluid passageway of the turbine engine.
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
B01F 23/235 - Mélange de gaz avec des liquides en introduisant des gaz dans des milieux liquides, p.ex. pour produire des liquides aérés pour la fabrication de mousse
B01F 25/31 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal
B01F 25/312 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal avec des éléments Venturi; Leurs détails
B01F 25/313 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal dans lesquels des composants supplémentaires sont introduits au centre du conduit
B01F 25/314 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal dans lesquels des composants supplémentaires sont introduits à la circonférence du conduit
Hybrid composite components, such as gas turbine engine containment assemblies, a hybrid composite component having an annular composite shell and an annular metallic shell joined with the composite shell. A containment assembly including a containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine. The containment case has an inner surface and an outer surface spaced apart along a radial direction and includes a first composite shell joined with a metallic shell. The metallic shell defining a first portion of the inner surface and the first composite shell defining a second portion of the inner surface.
F01D 21/04 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p.ex. indiquant cette position
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
24.
HEAT EXTRACTION OR RETENTION DURING DIRECTIONAL SOLIDIFICATION OF A CASTING COMPONENT
A method of forming a directionally-solidified casting component using a casting system is provided. The casting system includes a chamber having a heating zone and a cooling zone separated by a baffle plate. The method includes pouring an alloy in a liquid state into a mold shell. The mold shell is positioned on a chill plate within the heating zone. The method further includes moving the mold shell from the heating zone into the cooling zone. The alloy transfers from the liquid state to a solid state within the mold shell while moving the mold shell from the heating zone to the cooling zone. The method further includes contacting the mold shell with a heat transfer member.
The present disclosure generally relates to methods and apparatuses for chemical vapor deposition (CVD) during additive manufacturing (AM) processes. Such methods and apparatuses can be used to embed chemical signatures into manufactured objects, and such embedded chemical signatures may find use in anti-counterfeiting operations and in manufacture of objects with multiple materials.
C23C 16/50 - Revêtement chimique par décomposition de composés gazeux, ne laissant pas de produits de réaction du matériau de la surface dans le revêtement, c. à d. procédés de dépôt chimique en phase vapeur (CVD) caractérisé par le procédé de revêtement au moyen de décharges électriques
B22F 7/02 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives
B22F 7/04 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives avec une ou plusieurs couches non réalisées à partir de poudre, p.ex. à partir de tôles
B22F 7/06 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de pièces ou objets composés de parties différentes, p.ex. pour former des outils à embouts rapportés
B22F 10/14 - Formation d’un corps vert par projection de liant sur un lit de poudre
B22F 10/28 - Fusion sur lit de poudre, p.ex. fusion sélective par laser [FSL] ou fusion par faisceau d’électrons [EBM]
B22F 10/50 - Traitement des pièces ou des articles pendant leur formation, p.ex. traitements appliqués aux couches fusionnées pendant leur formation
B22F 10/62 - Traitement de pièces ou d'articles après leur formation par des moyens chimiques
B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
B29C 64/165 - Procédés de fabrication additive utilisant une combinaison de matériaux solides et liquides, p.ex. une poudre avec liaison sélective par liant liquide, catalyseur, inhibiteur ou absorbeur d’énergie
B29C 64/20 - Fabrication additive, c. à d. fabrication d’objets en trois dimensions [3D] par dépôt additif, agglomération additive ou stratification additive, p.ex. par impression en 3D, stéréolithographie ou frittage laser sélectif - Détails ou accessoires à cet effet
A sensor for a flexible sensor assembly includes a drive coil, a first set of sensing coils, a second set of sensing coils, and a configuration for sensing for discontinuities in a structure desired to be sensed. A method of operating the sensor can include positioning the sensor proximate to the structure, energizing the drive coil, and sensing eddy currents with the sensing coils.
G01N 27/90 - 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
An airfoil assembly extends along a radial direction between a root and a tip, the airfoil assembly comprising: a first blade segment positioned proximate the root of the airfoil assembly; a second blade segment positioned adjacent the first blade segment along the radial direction; and a tensioning assembly comprising a plurality of tensioning strings that extend between and mechanically couple the first blade segment and the second blade segment.
A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.
B08B 7/02 - Nettoyage par des procédés non prévus dans une seule autre sous-classe ou un seul groupe de la présente sous-classe par distorsion, battage ou vibration de la surface à nettoyer
B08B 13/00 - Accessoires ou parties constitutives, d'utilisation générale, des machines ou appareils de nettoyage
A method and system for aligning a component within a turbine casing, and a related turbine casing, are disclosed. In a top-on position, a location of a reference point and another, vertically spaced reference point on the lower casing are measured. After removing at least the upper casing, the reference points' locations are measured again, and the locations of a reference point on an upper surface of the HJ flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a HJ flange surface distortion adjustment. The component support position is adjusted by the prediction offset value to improve alignment.
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
F01D 21/00 - Arrêt des "machines" ou machines motrices, p.ex. dispositifs d'urgence; Dispositifs de régulation, de commande ou de sécurité non prévus ailleurs
F01D 25/28 - Dispositions pour le support ou le montage, p.ex. pour les carters de turbines
30.
AIR-TO-AIR HEAT EXCHANGER POTENTIAL IN GAS TURBINE ENGINES
A gas turbine engine is provided. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement; and an air-to-air heat exchanger having an air-to-air heat exchanger potential defined by a product raised to a half power, the product being an effectiveness associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine, and wherein the air-to-air heat exchanger potential is between 0.028 and 0.067 for a bypass ratio associated with the gas turbine engine between 3 and 10 and the effectiveness being between 0.5 and 0.9 and is between 0.015 and 0.038 for a bypass ratio associated with the gas turbine engine between 10 and 20 and the effectiveness being between 0.3 and 0.9.
General Electric Deutschland Holding GmbH (Allemagne)
Inventeur(s)
Huh, Kum Kang
Osama, Mohamed
Abrégé
An AC electrical system for a vehicle and methods of operating the same are provided. In one aspect, an AC electrical system includes a first electric machine mechanically coupled with a first spool of a gas turbine engine and a second electric machine mechanically coupled with a second spool of the gas turbine engine. The system also includes a first AC bus and a second AC bus. A first electrical channel electrically couples the first electric machine to the first AC bus and a second electrical channel electrically couples the second electric machine to the second AC bus. The system also includes one or more connection links and one or more power converters for selectively electrically coupling the first and second electrical channels so that electrical power generated by one electric machine can be converted and shared with the other electric machine and electrical loads of the other channel.
B60R 16/03 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques pour l'alimentation des sous-systèmes du véhicule en énergie électrique
B60L 50/13 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion utilisant des générateurs à courant alternatif et des moteurs à courant alternatif
B64D 27/18 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à réaction à l'intérieur de la voilure ou fixés à celle-ci
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02K 11/042 - Redresseurs associés à des parties tournantes, p.ex. à des noyaux rotoriques ou à des arbres tournants
32.
ALUMINUM SLURRY COATINGS AND METHODS OF THEIR FORMATION AND USE
Methods for reducing a concentration of hexavalent chromium within a first aluminum slurry by adding a reducing agent to form a second aluminum slurry are provided. The reducing agent causes a chemical reduction reaction with the hexavalent chromium compound of the first aluminum slurry to form a trivalent chromium compound within the second aluminum slurry such that a first weight ratio of hexavalent chromium to trivalent chromium in the first aluminum slurry is decreased to a second weight ratio of hexavalent chromium to trivalent chromium in the second aluminum slurry, with the second weight ratio being less than the first weight ratio.
B22F 9/18 - Fabrication des poudres métalliques ou de leurs suspensions; Appareils ou dispositifs spécialement adaptés à cet effet par un procédé chimique avec réduction de mélanges métalliques
B22F 1/145 - Traitement chimique, p.ex. passivation ou décarburation
33.
GAS CONTROL SYSTEMS FOR PURGING A PRINTHEAD MANUFACTURING APPARATUS
A gas control system including a positive pressure vessel, a negative pressure vessel, a first pressure control valve configured to control a flow of gas to and from a first manifold of a printhead assembly, and a second pressure control valve configured to control a flow of gas to and from a second manifold of the printhead assembly. During a normal positive pressure mode, gas flows from the positive pressure vessel to the first manifold and the second manifold through a respective one of the first pressure control valve and the second pressure control valve. During a positive pressure purge mode, gas from the positive pressure vessel bypasses the first pressure control valve and the second pressure control valve to flow to the first manifold and the second manifold.
B08B 9/032 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau
B08B 9/035 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau par aspiration
A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.
A turbomachine including a turbine rotor, a compressor rotor, and a shaft, and at least one balance weight assembly connected to the shaft. The shaft drivingly connects the turbine rotor with the compressor rotor to rotate the compressor rotor about a rotational axis when the turbine rotor rotates about the rotational axis. The at least one balance weight assembly including a first chamber, at least one additional chamber, and a balance weight movable between the first chamber and the at least one additional chamber.
An apparatus and method for an inspection apparatus for inspecting a component. The inspection apparatus including a robotic arm. A micro-XRF instrument having an instrument head coupled to the robotic arm. A seat supporting the component within a scanning area during inspection; and a computer in communication with the robotic arm and the micro-XRF instrument.
G01N 23/223 - Recherche ou analyse des matériaux par l'utilisation de rayonnement [ondes ou particules], p.ex. rayons X ou neutrons, non couvertes par les groupes , ou en mesurant l'émission secondaire de matériaux en irradiant l'échantillon avec des rayons X ou des rayons gamma et en mesurant la fluorescence X
G01N 35/00 - Analyse automatique non limitée à des procédés ou à des matériaux spécifiés dans un seul des groupes ; Manipulation de matériaux à cet effet
An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells each extending between an inlet end and an outlet end. Each fuel cell of the plurality of fuel cells includes an air channel and a fuel channel each fluidly coupled to the combustion chamber.
H01M 8/2484 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible - Détails des groupements d'éléments à combustible caractérisés par les collecteurs d’admission externes
F02C 7/22 - Systèmes d'alimentation en combustible
F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
H01M 8/2425 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible avec électrolytes solides ou supportés par une matrice Éléments à haute température avec électrolytes solides
39.
Trapped vortex reverse flow combustor for a gas turbine
A trapped vortex reverse flow combustor for a gas turbine includes a first dome structure having a plurality of first-dome vortex driver airflow openings for providing a first vortex generating mid airflow therethrough to a trapped vortex cavity. A second dome structure is arranged downstream of the first dome structure and includes a plurality of second-dome vortex driver airflow openings providing a first vortex generating outer airflow therethrough to the trapped vortex cavity, and a plurality of primary driver airflow openings providing a primary driver airflow therethrough radially inward of the trapped vortex cavity.
F23R 3/16 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la configuration du flux d'air ou du flux de gaz avec des dispositifs à l'intérieur du tube à flamme ou de la chambre de combustion pour influer sur le flux d'air ou de gaz
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
A rotor blade assembly for a turbine engine, including an airfoil blade including an inner diameter end and an outer diameter end, a lower blade carrier coupled to the inner diameter end of the airfoil blade and rigidly coupled to a disk via a pin, an upper blade carrier coupled to the outer diameter end of the airfoil blade, and an outer drum coupled to the upper blade carrier via a radial joint. The radial joint supports radial motion of the upper blade carrier relative to an axis extending through a center of the rotor blade assembly.
Active clearance control valves and related methods are disclosed. An example apparatus includes a pipe defining a flow path between (i) at least one of a fan section, a bypass airflow passage, or a compressor section and (ii) a turbine section of the gas turbine, the pipe including an inlet fluidly coupled to at least one of the fan section, the bypass airflow passage, or the compressor section, a valve coupled to the pipe and positioned downstream of the inlet, the valve including swing wings, the swing wings positioned around an opening in the pipe defined by the second valve when the second valve is at least partially open.
A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.
A power generation system for an aircraft includes a first power source, a second power source, and a power dispatch module communicatively coupled with the first and second power sources. The power dispatch module includes a controller having one or more processors configured to perform a plurality of operations, including but not limited to receiving a plurality of loading data associated with the power generation system, predicting a future power demand due to future load changes using the loading data, determining first and second power setpoints for the first and second power sources, respectively, based on the future power demand due to the future load changes, and controlling first and second power outputs of the first and second power sources based on the first and second power setpoints such that the future power demand of the power generation system is shared by the first and second power sources.
A method of producing a computer-generated image of a component part includes receiving scan data of the component part. The scan data includes a plurality of slices that change direction about a normal vector. The method further includes registering the scan data of the component part and transforming the scan data of the component part into a set of slices arranged in an x-y plane. Further, the method includes aligning the set of slices aligned along the axis along an axis in the x-y plane. In addition, the method includes adjusting the set of slices aligned along the axis using a background model for the component part, the scan data, or both. Thus, the method includes applying a directional filter to the set of slices aligned along the axis and generating the computer-generated image of the component part using the filtered set of slices aligned along the axis.
A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
(
D
1
eq
min
D
2
eq
min
)
(
R
D
2
eq
min
)
.
Methods, apparatus, systems, and articles of manufacture are disclosed. An example apparatus includes a tubular or cylindrical body including a shaft, a shoulder, and a neck, the shaft coupled to the shoulder, the shoulder coupled to the neck, the shoulder having a greater diameter than respective diameters of the shaft and the neck. The example apparatus includes a plug coupled to the shoulder at a first plug edge and coupled to a first fastener at a second plug edge, the first fastener including a hole. The example apparatus includes a second fastener coupled to the first fastener, the second fastener extending through the tubular body, the plug, and the first fastener.
Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.
B64D 27/26 - Aéronefs caractérisés par la structure du montage du groupe moteur
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé l'air étant réchauffé ou refroidi
48.
PITCH CHANGE MECHANISM FOR A FAN OF A GAS TURBINE ENGINE
A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.
The present disclosure generally relates to partial integrated core-shell investment casting molds that can be assembled into complete molds. Each section of the partial mold may contain both a portion of a core and portion of a shell. Each section can then be assembled into a mold for casting of a metal part. The partial integrated core-shell investment casting molds and the complete molds may be provided with filament structures corresponding to cooling hole patterns on the surface of the turbine blade or the stator vane, which provides a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.
B22D 25/02 - Coulée particulière caractérisée par la nature du produit d'œuvres d'art
B22C 1/22 - Compositions des matériaux réfractaires pour moules ou noyaux; Leur structure granulaire; Caractéristiques chimiques ou physiques de la mise en forme ou de la fabrication des moules caractérisées par l'emploi des agents liants; Mélange d'agents liants d'agents organiques de résines naturelles ou synthétiques
B22C 9/02 - Moules en sable ou moules analogues pour pièces coulées
B22C 9/10 - Noyaux; Fabrication ou mise en place des noyaux
B22C 9/12 - Traitement des moules ou noyaux, p.ex. séchage, étuvage
B22C 9/24 - Moules pour pièces de forme particulière pour pièces évidées
B22C 13/08 - Machines à mouler pour faire des moules ou noyaux de forme particulière pour moules ou noyaux en coquilles
B22C 13/12 - Machines à mouler pour faire des moules ou noyaux de forme particulière pour noyaux
B22C 21/14 - Organes auxiliaires pour le renforcement ou l'immobilisation des matériaux de moulage ou des noyaux, p.ex. crochets, supports de noyaux, goujons, barres de châssis
B22D 29/00 - Extraction des pièces hors du moule, non limitée à un procédé de coulée couvert par un seul groupe principal; Extraction des noyaux; Manipulation des lingots
B28B 1/00 - Fabrication d'objets façonnés à partir du matériau
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
B29C 64/129 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective caractérisés par la source d'énergie à cet effet, p.ex. par irradiation globale combinée avec un masque
B29C 64/135 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective caractérisés par la source d'énergie à cet effet, p.ex. par irradiation globale combinée avec un masque la source d’énergie étant concentrée, p.ex. lasers à balayage ou sources lumineuses focalisées
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
G03F 7/00 - Production par voie photomécanique, p.ex. photolithographique, de surfaces texturées, p.ex. surfaces imprimées; Matériaux à cet effet, p.ex. comportant des photoréserves; Appareillages spécialement adaptés à cet effet
Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.
B64D 31/06 - Dispositifs amorçant la mise en œuvre actionnés automatiquement
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
H02P 29/032 - Prévention d’un endommagement du moteur, p.ex. détermination de limites individuelles de courant pour différentes conditions de fonctionnement
51.
APPARATUS AND SYSTEMS FOR SEPARATING PHASES IN LIQUID HYDROGEN PUMPS
Methods, apparatus, systems, and articles of manufacture are disclosed herein that include a cryogenic pump system comprising: a cryogenic liquid tank; a cryogenic pump including a suction adapter, the suction adapter connected to the cryogenic liquid tank via a liquid supply line and a gaseous return line; and a phase separator connected downstream of the cryogenic liquid tank and upstream of the cryogenic pump, the phase separator including a filtration structure integrated into the liquid supply line to separate vapor from cryogenic liquid, the phase separator connected to the gaseous return line to direct the vapor to the cryogenic liquid tank.
B01D 39/20 - Autres substances filtrantes autoportantes en substance inorganique, p.ex. papier d'amiante ou substance filtrante métallique faite de fils métalliques non-tissés
F17C 1/00 - Récipients sous pression, p.ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables
52.
AIRCRAFTS, SYSTEMS, AND METHODS FOR PROVIDING CONSTANT TORQUE ON TAKEOFF
An aircraft includes a gas turbine engine, an electric motor, and a propulsion device. The gas turbine engine and the electric motor are configured to provide a target cumulative output to the propulsion device. An electronic control unit is configured to set the gas turbine engine to a first engine mode to provide a first engine output to the propulsion device, set the electric motor to a first motor mode to provide a first motor output to the propulsion device, a sum of the first engine output and the first motor output being within a predetermined range of the target cumulative output, and in response to a speed of the aircraft reaching a target speed and the first engine output increasing to a second engine output, set the electric motor to a second motor mode.
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
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
53.
Trunnion-to-disk connection for an open fan configuration aircraft powerplant
A trunnion-to-disk connection for use on an open fan configuration of a gas turbine engine may include an integral trunnion and blade spar inserted through a trunnion aperture of a fan disk and supported by top bearing and a bottom bearing. A cavity can be provided between a trunnion of the integral trunnion and blade spar and the fan disk, as well as between the top bearing and bottom bearing. Pressurized hydraulic fluid can be supplied to the cavity to urge the integral trunnion and blade spar in a direction to preload the bearings. Prior to pressurization, and prior to installation of the bottom bearing, the trunnion can be inserted into a trunnion aperture of the fan disk such that an end of the trunnion extends past the fan disk to provide sufficient space to insert the bottom bearing from within the open interior of the fan disk.
F02K 3/08 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant avec réchauffage supplémentaire du fluide de travail; Leur commande
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
A fuel cell assembly includes a plurality of fuel cells. The fuel cell includes a bipolar separator plate disposed between each fuel cell of the plurality of fuel cells. The bipolar separator plate includes one or more fuel cell sub-units each comprising a plurality of unit-cells. Each unit-cell in the plurality of unit-cells has an outer surface and defines an internal volume that extends in multiple directions between a plurality of openings defined on the outer surface. Each unit-cell in the plurality of unit-cells is disposed adjacent to a neighboring unit-cell in the plurality of unit-cells such that the plurality of unit-cells collectively define one or more channels.
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
H01M 8/0267 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs comprenant des moyens de chauffage ou de refroidissement, p.ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
H01M 8/0247 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la forme
H01M 8/2483 - Groupement d'éléments à combustible, p.ex. empilement d'éléments à combustible - Détails des groupements d'éléments à combustible caractérisés par les collecteurs d’admission internes
H01M 8/04111 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux utilisant un assemblage turbine compresseur
H01M 8/04014 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur Échange de chaleur par combustion des réactifs
A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
F01D 25/24 - Carcasses d'enveloppe; Eléments de la carcasse, p.ex. diaphragmes, fixations
F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
F01D 9/04 - Injecteurs; Logement des injecteurs; Aubes de stator; Tuyères de guidage formant une couronne ou un secteur
56.
CASCADE THRUST REVERSER ACTUATION ASSEMBLY FOR A TURBOFAN ENGINE
A cascade thrust reverser assembly is provided for a turbofan engine. The turbofan engine includes a nacelle assembly defining a bypass passage, and the cascade thrust reverser assembly includes at least one cascade assembly configured to be at least partially enclosed by the nacelle assembly. The cascade assembly may further include a plurality of cascade segments and an actuation assembly operably connected to the plurality of cascade segments, wherein the actuation assembly is configured to increase an axial extent of the cascade assembly and rotate the plurality of cascade segments.
F02K 1/76 - Commande ou régulation des inverseurs de poussée
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 joined part comprises a first portion and a second portion. The first portion comprises a guide slot at least partially defined by a porous structure. A joint material is disposed within the porous structure. The second portion is disposed within the guide slot and contacts the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion. A method of manufacturing the joined part includes disposing a joint material into a porous structure of a guide slot of a first portion, inserting a second portion into the guide slot, and contacting the porous structure and the joint material disposed therein to form an interfacial joint between the first portion and the second portion.
B23K 20/00 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage
B23K 35/00 - Baguettes, électrodes, matériaux ou environnements utilisés pour le brasage, le soudage ou le découpage
B23K 35/36 - Emploi de compositions non métalliques spécifiées, p.ex. comme enrobages, comme flux; Emploi de matériaux de brasage ou de soudage spécifiés associé à l'emploi de compositions non métalliques spécifiées, dans lequel l'emploi des deux matériaux est important
C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage
58.
CLEANING SOLUTION AND METHODS OF CLEANING A TURBINE ENGINE
A cleaning solution for a turbine engine includes water; a first organic acidic component that comprises citric acid; a second organic acidic component that comprises glycolic acid; isopropylamine sulphonate; alcohol ethoxylate; triethanol amine; and sodium lauriminodipropionate. The cleaning solution has a pH value between about 2.5 and about 7.0.
C11D 3/20 - Composés organiques contenant de l'oxygène
C11D 11/00 - Méthodes particulières pour la préparation de compositions contenant des mélanges de détergents
C23G 1/06 - Nettoyage ou décapage de matériaux métalliques au moyen de solutions ou de sels fondus avec des solutions acides avec emploi d'inhibiteurs inhibiteurs organiques
C11D 3/34 - Composés organiques contenant du soufre
C23G 1/02 - Nettoyage ou décapage de matériaux métalliques au moyen de solutions ou de sels fondus avec des solutions acides
F01D 25/00 - "MACHINES" OU MACHINES MOTRICES À DÉPLACEMENT NON POSITIF, p.ex. TURBINES À VAPEUR - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
59.
SYSTEMS AND METHODS FOR ADDITIVE MANUFACTURING USING PIXEL SHIFTING
An additive manufacturing apparatus includes a support plate defining a window and a resin support configured to support an uncured layer of resin. A stage is configured to hold one or more cured layers of the resin to form a component positioned opposite a support plate. A radiant energy device is positioned on an opposite side of the resin support from the stage and is operable to project radiant energy in a grid through the window. The grid and/or pixels thereof are intelligently shifted to efficiently print one or more layers of a component.
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 64/282 - Agencements pour irradiation utilisant des moyens de rayonnement multiples, p.ex. des micro-miroirs ou des diodes électroluminescentes multiples [LED] du même type, p.ex. utilisant des niveaux d’énergie différents
A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.
An additive manufacturing apparatus includes a stage configured to hold a component. A radiant energy device is operable to generate and project radiant energy in a patterned image. An actuator is configured to change a relative position of the stage relative to the radiant energy device. A resin management system includes a material deposition assembly upstream configured to deposit a resin on a resin support. The material deposition assembly includes a reservoir configured to retain a first volume of the resin and define a thickness of the resin on the resin support as the resin support is translated in an X-axis direction. The material deposition assembly further includes a vessel positioned above the reservoir in a Z-axis direction and configured to store a second volume of the resin. In addition, the material deposition assembly includes a conduit configured to direct the resin from the vessel to the reservoir.
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
A turbofan engine is provided. The turbofan engine includes a low pressure spool; a fan mechanically coupled with the low pressure spool; a high pressure spool; an accessory gearbox mechanically coupled with the high pressure spool; a hydraulic pump mechanically coupled with the accessory gearbox; and one or more heat exchangers tied to the accessory gearbox, the one or more heat exchangers having a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying an average heat exchanger effectiveness of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a hydraulic pump power of the hydraulic pump, a fan diameter of the fan, an engine length of the turbofan engine, and an overall pressure ratio of the turbofan engine.
A gas turbine engine includes a turbomachine comprising a low pressure (LP) spool and a high pressure (HP) spool that rotate about a central axis, an electric motor mechanically coupled to the LP spool for selectively rotating the LP spool, a starter assembly mechanically coupled to the HP spool for selectively rotating the HP spool, and a controller in operative communication with the electric motor and the starter assembly, the controller being configured to operate the electric motor to rotate the LP spool and operate the starter assembly to rotate the HP spool during engine startup.
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gaz; Combinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareils; Adaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
A turbomachine for an aircraft is provided. The turbomachine includes a plurality of radially-extending blades and an annular endwall opposite the radially-extending blades. The endwall includes an endwall treatment recessed into the endwall. The endwall treatment is characterized by a casing treatment volume compressibility factor (CTVCF), and a casing treatment normalized volume (CTNV), and a blade tip Mach number (Mtip).
An additive manufacturing apparatus includes a support plate defining a window and a resin support configured to support an uncured layer of resin. A stage is configured to hold one or more cured layers of the resin to form a component positioned opposite a support plate. A radiant energy device is positioned on an opposite side of the resin support from the stage and is operable to project radiant energy in a grid through the window. The grid and/or pixels thereof are intelligently shifted to efficiently print one or more layers of a component.
An additive manufacturing apparatus includes a support plate defining a window and a resin support configured to support an uncured layer of resin. A stage is configured to hold one or more cured layers of the resin to form a component positioned opposite a support plate. A radiant energy device is positioned on an opposite side of the resin support from the stage and is operable to project radiant energy in a grid through the window. The grid and/or pixels thereof are intelligently shifted to efficiently print one or more layers of a component.
B29C 64/188 - Procédés de fabrication additive impliquant des opérations supplémentaires effectuées sur les couches ajoutées, p.ex. lissage, meulage ou contrôle d’épaisseur
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
An additive manufacturing apparatus includes a support plate defining a window and a resin support configured to support an uncured layer of resin. A stage is configured to hold one or more cured layers of the resin to form a component positioned opposite a support plate. A radiant energy device is positioned on an opposite side of the resin support from the stage and is operable to project radiant energy in a grid through the window. The grid and/or pixels thereof are intelligently shifted to efficiently print one or more layers of a component.
B29C 64/393 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
68.
SYSTEMS AND METHODS FOR ELECTRON BEAM FOCUSING IN ELECTRON BEAM ADDITIVE MANUFACTURING
A system for melting, sintering, or heat treating a material is provided. The system includes a cathode, an anode, and a focus coil assembly having a quadrupole magnet. The quadrupole magnet includes four poles and a yoke. The four poles are spaced apart and surround a beam cavity. Each of the four poles includes a pole face proximate the beam cavity and an end opposite the pole face. The first and third poles are aligned along an x-axis and configured to have a first magnetic polarity at their respective pole faces and a second magnetic polarity opposite the first magnetic polarity at their respective ends. The second and fourth poles are aligned along a y-axis and configured to have the second magnetic polarity at their respective pole faces and the first magnetic polarity at their respective ends. The yoke surrounds the poles and is coupled to the poles.
H01J 29/68 - Lentilles magnétiques utilisant uniquement des aimants permanents
B29C 64/153 - Procédés de fabrication additive n’utilisant que des matériaux solides utilisant des couches de poudre avec jonction sélective, p.ex. par frittage ou fusion laser sélectif
B29C 64/273 - Agencements pour irradiation par faisceaux d’électrons [FE] à modulation de fréquence
H01J 37/30 - Tubes à faisceau électronique ou ionique destinés aux traitements localisés d'objets
H01J 37/305 - Tubes à faisceau électronique ou ionique destinés aux traitements localisés d'objets pour couler, fondre, évaporer ou décaper
Systems and methods are disclosed for automated power plant unit trip prediction and control. Power plant controls may have limited time to manage the plant loads when one of the units trips unexpectedly. To mitigate any consequences on a power grid associated with a trip event, these systems and methods may allow for prediction of such trip events. The predictions may allow a signal to be provided to a controller in sufficient time for the controller to automatically take any necessary action to mitigate any impacts of the future trip event.
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 réseau; Circuits 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 gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.
A gas turbine engine includes: a turbomachine including a combustion section and an exhaust assembly arranged in serial flow order; and a fuel system. The fuel system includes: a hydrogen fuel tank for holding a hydrogen fuel in a liquid phase; and a hydrogen delivery assembly in thermal communication with the exhaust assembly. The hydrogen delivery assembly includes: a liquid hydrogen line in fluid communication with the hydrogen fuel tank; a gaseous hydrogen line in fluid communication with the combustion section of the gas turbine engine; and a heat exchanger tubing positioned within the exhaust assembly downstream of the liquid hydrogen line and upstream of the gaseous hydrogen line.
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
F02C 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
An additive manufacturing machine and an energy beam system including an energy beam generator configured to output an energy beam through a first optical element along a first direction is provided. The energy beam system includes an optical translation system positioned to receive the energy beam through a steering optic. The steering optic is positioned within a translator apparatus. The translator apparatus is configured to translate the steering optic along a plane perpendicular to the first direction.
Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.
F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p.ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
A combustor for a gas turbine includes a dome structure including a dome-side swirler opening therethrough, and a deflector connected to the dome structure. The deflector includes a deflector-side swirler opening therethrough and a deflector-dome connecting member arranged at the deflector-side swirler opening. The deflector-dome connecting member is connected with the dome-side swirler opening via a snap-fit type connection.
F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
F23R 3/16 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par la configuration du flux d'air ou du flux de gaz avec des dispositifs à l'intérieur du tube à flamme ou de la chambre de combustion pour influer sur le flux d'air ou de gaz
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
A gearbox assembly includes a first gear and a second gear. The first gear includes a plurality of first gear teeth. The second gear includes a plurality of second gear teeth. The plurality of first gear teeth and the plurality of second gear teeth mesh with each other as the first gear and the second gear rotate. A profile shape of at least one first gear tooth of the first gear is characterized by a total profile modification between 66 micrometers and 120 micrometers.
A green body part comprises a first green portion, a second green portion, an interfacial joint between the first green portion and the second green portion, and a joint material disposed within the interfacial joint. The joint material comprises a powder having a particle size distribution than or equal to 1 μm and less than or equal to 50 μm. A method of manufacturing a joined part includes applying a joint material on a face of the first green portion and contacting the second green portion to the joint material on the face of the first green portion to form a joined green body part.
B22F 7/02 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives
C04B 37/00 - Liaison des articles céramiques cuits avec d'autres articles céramiques cuits ou d'autres articles, par chauffage
Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate including a first surface and a second surface that is radially inward relative to the first surface; an actuator structure coupled to the second surface of the annular substrate; and a smart structure cantilevered from the second surface of the annular substrate, the smart structure including: a support structure, a first region of the support structure coupled to the second surface of the annular substrate, a second region of the support structure coupled to the actuator structure; and a radially inward surface defining a variable surface, the support structure to move the variable surface in a radial direction.
Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.
F01D 5/16 - Forme ou structure pour contrebalancer les vibrations des aubes
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
General Electric Company Polska Sp. z o.o. (Pologne)
Inventeur(s)
Cafaro, Stefan Joseph
Khalid, Inenhe Mohammed
Reepmeyer, James Ryan
Zutshi, Amit
Mollmann, Daniel Edward
Hegeman, Arjan Johannes
Sarba, Rafal
Abrégé
A method of controlling an aeronautical gas turbine engine may be performed with an electronic controller. The method may include determining an airfoil pitch control command for at least one of a plurality of airfoils of the aeronautical gas turbine engine based at least in part on an excitation load acting upon the aeronautical gas turbine engine, and outputting the airfoil pitch control command to one or more actuators actuatable to change a pitch angle of the at least one of the plurality of airfoils. The airfoil pitch control command may be configured to augment and/or compensate for the excitation load acting upon the aeronautical gas turbine engine. The method may be embodied by a non-transitory computer-readable medium that includes computer-executable instructions, which when executed by a processor associated with the electronic controller, cause the electronic controller to perform the method.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 7/00 - Rotors à aubes réglables en marche; Leur commande
81.
CONTROLLING EXCITATION LOADS ASSOCIATED WITH OPEN ROTOR AERONAUTICAL ENGINES
General Electric Company Polska Sp. z o.o. (Pologne)
Inventeur(s)
Zutshi, Amit
Sarba, Rafal
Reepmeyer, James Ryan
Cafaro, Stefan Joseph
Khalid, Inenhe Mohammed
Mollmann, Daniel Edward
Hegeman, Arjan Johannes
Abrégé
An open rotor engine includes a core engine, a plurality of guide vanes positioned within or extending from the core engine; and a pitch change assembly operably coupled to the plurality of guide vanes. The pitch change assembly includes one or more actuators configured to change a pitch angle of respective ones of the plurality of guide vanes, and a plurality of linkage arms that are respectively movable by actuation of at least one of the one or more actuators. The plurality of linkage arms are directly or indirectly coupled to a corresponding one of the plurality of guide vanes. The plurality of linkage arms may have a length that differs from one another, and such length may orient a displacement or a range of motion of the respective linkage arm to an envelope of rotation about a guide vane axis that differs as between the plurality of guide vanes.
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
82.
CONTROLLING EXCITATION LOADS ASSOCIATED WITH OPEN ROTOR AERONAUTICAL ENGINES
General Electric Company Polska Sp. z o.o. (Pologne)
Inventeur(s)
Zutshi, Amit
Sarba, Rafal
Reepmeyer, James Ryan
Cafaro, Stefan Joseph
Khalid, Inenhe Mohammed
Mollmann, Daniel Edward
Hegeman, Arjan Johannes
Abrégé
An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
A system includes a computing device including at least one processor in communication with at least one memory. The at least one processor is programmed to (a) store a plurality of historical time series data; (b) randomly select a sequence; (c) randomly select a mask length for a mask for the selected sequence; (d) apply the mask to the selected sequence, wherein the mask is applied to the plurality of forecast variables in the selected sequence; (e) execute a model with the masked selected sequence to generate predictions for the masked forecast variables; (f) compare the predictions for the masked forecast variables to the actual forecast variables in the selected sequence; (g) determine if convergence occurs based upon the comparison; and (h) if convergence has not occurred, update one or more parameters of the model and return to step b.
A combustor for a gas turbine engine has an annular inner liner and an annular outer liner forming a combustion chamber therebetween. A dilution horn pair includes dilution horns that provide a flow of an oxidizer gas into the combustion chamber in a dilution zone. At least one of the dilution horns forming the dilution horn pair is arranged so as to provide a lateral flow component of the flow of oxidizer gas therethrough into the combustion chamber, the lateral flow component having a flow direction extending laterally across and non-orthogonal to an axial flow direction of combustion gases within the combustion chamber.
An aircraft equipped with a distributed fan propulsion system and methods of operating such aircraft are provided. In one aspect, an aircraft includes a wing having a top surface and a bottom surface. The aircraft also has a distributed propulsion system that includes a suction fan array having one or more fans mounted to the wing and a pressure fan array having one or more fans mounted to the wing. The fans of the suction fan array are each positioned primarily above the top surface of the wing and the fans of the pressure fan array are each positioned primarily below the bottom surface of the wing. The fans of the suction fan array are controllable independent of the fans of the pressure fan array so that the air pressure above and/or below the wing can be locally controlled, allowing for adjustment of lift on the wing.
A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.
An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
A cryogenic system includes a cryogenic tank containing a liquid cryogen and a vacuum vessel surrounding the cryogenic tank and providing a vacuum space between an inner surface of the vacuum vessel and an outer surface of the cryogenic tank. The cryogenic system further includes a suspension system arranged within the vacuum space so as to support the cryogenic tank within the vacuum vessel and to maintain the cryogenic tank within the vacuum vessel in a desired position. The suspension system includes a plurality of roller elements arranged within the vacuum space and contacting the inner surface of the vacuum vessel and the outer surface of the cryogenic tank.
F17C 1/12 - Récipients sous pression, p.ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables avec des moyens pour assurer une isolation thermique
A turbomachinery engine comprises a ducted fan, a high-pressure compressor, a low-pressure turbine, a gearbox, and a ducted engine correlation parameter (DECP). The DECP is within a range of 0.10-0.25 and is defined as 10*D/GR/NLPT/NHPC, where D is a fan blade tip diameter at a leading edge of the ducted fan measured in feet, GR is a gear ratio of the gearbox, NLPT is a stage count of the low-pressure turbine, and NHPC is a stage count of the high-pressure compressor.
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
An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.
A fuel system for a gas turbine engine is provided. The gas turbine engine including an exhaust assembly. The exhaust assembly including a tail cone and defining a radial direction, a circumferential direction, an axial direction, a working gas flow path, and an outer bypass flow path, the fuel system including: a hydrogen fuel tank for holding a hydrogen fuel; a heat exchanger configured to be coupled to or integrated into the tail cone of the exhaust assembly, the heat exchanger including: a first axial flow path in flow communication with the hydrogen fuel tank; a second axial flow path in flow communication with a combustion section of the gas turbine engine; and a radial flow path.
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
F02K 1/82 - Parois des tubulures de jet, p.ex. chemises
F02C 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.
F02K 3/065 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant des soufflantes avant et arrière
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
This disclosure is directed to cooling systems for turbomachine seal assemblies. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. During operation of the turbomachine, the components of the seal assemblies generate heat, which is removed from the seal assembly by the cooling systems of this disclosure. In some examples, the cooling system includes a reservoir of lubricant that is distributed to a face of one of the components of the seal assembly. In other examples, the cooling system includes a lattice structure capable of retaining lubricant against the components of the seal assembly, or a pressurized jet of lubricant directed against the components of the seal assembly. The cooling systems can further include a combination of deflectors, hairpin members, and channels for distributing the lubricant to the components of the seal assemblies.
The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
A charging pad (130) for charging one or more receiver devices (106, 108) is disclosed. The charging pad (130) includes a power drive unit (110) configured to generate a first AC voltage signal having a first frequency and a second AC voltage signal having a second frequency. Further, the charging pad (130) includes a transmitting unit (114) including a single power exchange coil (120) coupled to the power drive unit (110), wherein the single power exchange coil (120) includes a first coil segment (212) configured to transmit the first AC voltage signal having the first frequency when the first AC voltage signal is received from the power drive unit (110). Also, the single power exchange coil (120) includes a second coil segment (214) configured to transmit the second AC voltage signal having the second frequency when the second AC voltage signal is received from the power drive unit (110).
H02J 50/12 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant un couplage inductif du type couplage à résonance
H02J 50/40 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant plusieurs dispositifs de transmission ou de réception
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
96.
CONTROL SYSTEMS AND METHODS FOR ADDITIVE MANUFACTURING
An additive manufacturing apparatus includes a first print module includes a first stage configured to hold a first component and a first radiant energy device. The resin support is configured to be positioned between the first stage and the first radiant energy device. A second print module includes a second stage configured to hold a second component and a second radiant energy device. The resin support is configured to be positioned between the second stage and the second radiant energy device. A control system is configured to translate the resin support based on a condition of the first print module and the second print module through the first print module and the second print module.
B33Y 30/00 - Appareils pour la fabrication additive; Leurs parties constitutives ou accessoires à cet effet
B33Y 50/02 - Acquisition ou traitement de données pour la fabrication additive pour la commande ou la régulation de procédés de fabrication additive
B29C 64/124 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p.ex. dépôt d’un cordon continu de matériau visqueux utilisant des couches de liquide à solidification sélective
B29C 64/282 - Agencements pour irradiation utilisant des moyens de rayonnement multiples, p.ex. des micro-miroirs ou des diodes électroluminescentes multiples [LED] du même type, p.ex. utilisant des niveaux d’énergie différents
A combustor for a turbomachine engine includes a combustion chamber, a liner forming a boundary of the combustion chamber, and multiple dilution holes through the liner to permit airflow into the combustion chamber. The dilution holes include converging dilution holes and diverging dilution holes, the converging dilution holes having a converging cross-sectional profile and the diverging dilution holes having a diverging cross-sectional profile.
A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system can be controlled to adjust one or more parameters of the fuel based on data received from the sensors.
F02C 7/22 - Systèmes d'alimentation en combustible
F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur
A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
100.
Core Air Leakage Redirection Structures for Aircraft Engines
A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.