Abrégé

A facility receives an indication of a rate of energy output sought from a production array of solar panels. The facility controls a power inverter to which the production array is connected to deliver to an electrical grid to which the power inverter is connected a rate of energy output that is based on the indicated rate of energy output.

Classes IPC  ?

• H02J 3/48 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante en phase
• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
• H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
• H02S 10/00 - Centrales électriques PVCombinaisons de systèmes d’énergie PV avec d’autres systèmes pour la production d’énergie électrique

Abrégé

A boiler facility includes first and second fuel transfer apparatuses for transporting fine particulate fuel to a combustor. A first fuel transfer apparatus includes a main body and a diffuser. The main body has a flow space through which fuel is transferred and an inner surface that defines the flow space of the main body and includes a lower inner surface that extends obliquely downward. The diffuser is installed at a downstream end of the main body, the diffuser having a flow space through which fuel is transferred and an inner surface that defines the flow space of the first diffuser and includes a lower inner surface that extends obliquely upward. A second fuel transfer apparatus includes a transfer pipe having a flow channel, a second diffuser installed along the inner circumferential surface of the transfer pipe, and a guide installed in the second diffuser and inclined downward.

Classes IPC  ?

• F23K 3/02 - Alimentation pneumatique, c.-à-d. par courant d'air

Abrégé

A facility receives an indication of a rate of energy output sought from a production array of solar panels. The facility controls a power inverter to which the production array is connected to deliver to an electrical grid to which the power inverter is connected a rate of energy output that is based on the indicated rate of energy output.

Classes IPC  ?

• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
• H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
• H02J 3/48 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante en phase
• H02S 10/00 - Centrales électriques PVCombinaisons de systèmes d’énergie PV avec d’autres systèmes pour la production d’énergie électrique

Abrégé

A turbine blade for a gas turbine engine. The turbine blade includes an airfoil having a tip cavity. The tip cavity has a floor bounded by a wall. A pocket opening is formed in the wall proximate a trailing edge of the turbine blade. A passageway communicates cooling medium from an internal cooling circuit to a cooling hole formed in part through the floor and in part through the trailing edge.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• B22D 25/02 - Coulée particulière caractérisée par la nature du produit par sa formeCoulée particulière caractérisée par la nature du produit d'œuvres d'art

Abrégé

Methods and systems are provided for optimizing energy management of an energy resource site. For instance, a hierarchical energy management system can provide optimized management of energy resource sites with large numbers of energy resources. In particular, the hierarchical energy management system can effectively control energy resources by allocating functionality using different tiers. For instance, one or more energy resources devices can comprise the lowest tier of the hierarchical energy management system. The next tier of the hierarchical energy management system can comprise one or more controllers that can manage the energy resource devices. The next tier of the hierarchical energy management system, a resource manager, generally manages the set of controllers.

Classes IPC  ?

• H02J 3/32 - Dispositions pour l'équilibrage de charge dans un réseau par emmagasinage d'énergie utilisant des batteries avec moyens de conversion
• G05B 15/02 - Systèmes commandés par un calculateur électriques
• G06Q 50/06 - Fourniture d’énergie ou d’eau
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
• H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau

Abrégé

An inner shroud block component for a gas turbine. The inner shroud block has a radially inward facing surface with an abradable material applied thereto. The abradable material includes a zone of ridges that extend radially inwardly from the radially inward facing surface to minimize the clearance between the inner shroud block and the blade tip of a turbine blade. The abradable material may be ceramic and may be abraded by the blade tip if contact occurs between the blade tip and the inner shroud block. The zone of ridges extend along the radially inward facing surface in parallel to a direction of rotation of the turbine blade.

Classes IPC  ?

• F01D 11/12 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator utilisant un élément de friction allongé, p. ex. un élément d'usure, déformable ou contraint de façon élastique
• F02C 7/28 - Agencement des dispositifs d'étanchéité

Abrégé

An airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

A turbomachine is provided. The turbomachine includes a casing, a first airfoil disposed inside the casing such that a fluid passes through the first airfoil while flowing through the casing, a first inner frame coupled to a radially inner end of the first airfoil, a first inner wing protruding from the first inner frame in an axial direction of the casing, a second airfoil disposed inside the casing and between adjacent first airfoils in a flow direction of a fluid, a second inner frame coupled to a radially inner end of the second airfoil and disposed adjacent to the first inner frame, a second inner wing protruding from the second inner frame along the axial direction of the casing and disposed adjacent to the first inner wing, and a plurality of rim seals disposed between the first inner wing and the second inner wing, arranged at intervals along a circumferential direction of the casing, and configured such that cooling air present inside the first and second inner wings in a radial direction flows into each rim seal through an ingress port, passes through each rim seal, and flows out through an egress port, wherein a region on a downstream side of the first airfoil in the flow direction of the fluid flowing through the casing is divided into a first region having a relatively high pressure and a second region having a relatively low pressure, a first flow passage and a second flow passage are provided in a gap between each rim seal, the first flow passage is configured such that a size in the circumferential direction increases from the ingress port to the egress port and the egress port communicates with the first region, and the second flow passage is configured such that a size in the circumferential direction decreases from the ingress port to the egress port and the egress port communicates with the second region.

Classes IPC  ?

• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F01D 25/12 - Refroidissement

Abrégé

An internal core profile for a second stage turbine nozzle airfoil of a gas turbine is provided. The turbine nozzle may include an airfoil core having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil core profile sections at each Z distance, and the plurality of airfoil core profile sections, when joined together by smooth continuous arcs, define an airfoil core shape.

Classes IPC  ?

• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 5/14 - Forme ou structure
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A turbine blade for a gas turbine engine. The turbine blade includes a cooling path for a coolant, routing the coolant through an internal cooling cavity and out through a plurality of cooling holes formed proximate a trailing edge of the turbine blade. Each of the cooling holes including a diffusing region designed so that a coolant does not separate from a radially inward sidewall of the diffusing region.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

Turbine components, such as blades, having a shank portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, Table 2, or Table 1 and Table 2. X and Y are distances in inches which, when connected by smooth continuing arcs, define shank portion profile section edges at each Z distance in inches. The shank portion profile section edges at the Z distances are joined smoothly with one another to form a complete shank shape.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

An inner shroud block component for a gas turbine. The inner shroud block has a surface with a plurality of wells formed therein. An array of protuberances extend away from a base surface of each of the wells. The array of protuberances produces convective cooling of the inner shroud block, resulting in increased cooling of the inner shroud block and better part life. The increased cooling capacity also allows the turbine to operate at higher temperatures, which results in additional power generation.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 25/26 - Carcasses d'enveloppe doublesMesures contre les tensions thermiques dans les carcasses d'enveloppe

Abrégé

An airfoil for a gas turbine engine. The airfoil includes a unique cooling path for a coolant, routing the coolant through a cooling cavity, through a column of crossover passages and through a pin array near a trailing edge of the airfoil. The crossover passages produce impingement cooling and the pin array produces convective cooling. This combination of impingement cooling and convective cooling results in increased cooling of the airfoil and better aeromechanical life objectives.

Classes IPC  ?

• F01D 25/12 - Refroidissement
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

An airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Classes IPC  ?

• 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 7/00 - 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
• F01D 5/14 - Forme ou structure

Abrégé

Methods and systems are provided for optimizing energy management of an energy resource site. For instance, a hierarchical energy management system can provide optimized management of energy resource sites with large numbers of energy resources. In particular, the hierarchical energy management system can effectively control energy resources by allocating functionality using different tiers. For instance, one or more energy resources devices can comprise the lowest tier of the hierarchical energy management system. The next tier of the hierarchical energy management system can comprise one or more controllers that can manage the energy resource devices. The next tier of the hierarchical energy management system, a resource manager, generally manages the set of controllers.

Classes IPC  ?

• G05B 15/02 - Systèmes commandés par un calculateur électriques
• G06Q 40/04 - TransactionsOpérations boursières, p. ex. actions, marchandises, produits dérivés ou change de devises
• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
• H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
• H02J 9/00 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours

Abrégé

A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner platform to an outer platform and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a plurality of vanes attached to the inner and outer platforms and the inner platform having an attached first and second endfaces and a flow surface surrounding opposing ends of a vane of the plurality of vanes, the flow surface terminating circumferentially at the first and second endfaces and terminating axially at forward and aft edges, and the inner platform may include a platform corner portion comprising the flow surface attached to the first endface at the forward edge and attached to the second endface at the aft edge.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 5/14 - Forme ou structure

Abrégé

An airfoil having a leading edge and a trailing edge is provided. The airfoil includes a rear cooling path connected to the trailing edge to discharge air to the trailing edge, a plurality of cooling fins formed in the rear cooling path, and a flow guide rod connecting the cooling fins to support the cooling fins, wherein each of the plurality of cooling fins includes an upper fin portion protruding upward from an upper portion of the flow guide rod, a lower fin portion protruding downward from a lower portion of the flow guide rod, and an intermediate fin portion inserted through the flow guide rod.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F04D 29/54 - Moyens de guidage du fluide, p. ex. diffuseurs

Abrégé

An airfoil profile for a second stage turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

A turbine vane, a turbine, and a gas turbine capable of reducing thermal stress are provided. The turbine vane may include an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, and a first passage bending part configured to connect the first cooling passage and the second cooling passage, and the first passage bending part is positioned inside the inner shroud or the outer shroud.

Classes IPC  ?

• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 25/12 - Refroidissement

Abrégé

The present disclosure relates to a system and a method for validating the validity of a sensor, in particular, validating the validity of a sensor using a control limit. The present disclosure provides a method for validating the validity of a sensor using a control limit, including inferring a posterior distribution of a parameter in a Bayesian technique using a prior distribution of the parameter of sensor data and historical data of the sensor, setting a target credible interval for the posterior distribution of the parameter and setting a control line of the sensor data using the set credible interval, and validating the validity of the sensor by monitoring whether the actual measurement data of the sensor deviates from the control line. The present disclosure relates to a system and a method for validating the validity of a sensor, in particular, validating the validity of a sensor using a control limit. The present disclosure provides a method for validating the validity of a sensor using a control limit, including inferring a posterior distribution of a parameter in a Bayesian technique using a prior distribution of the parameter of sensor data and historical data of the sensor, setting a target credible interval for the posterior distribution of the parameter and setting a control line of the sensor data using the set credible interval, and validating the validity of the sensor by monitoring whether the actual measurement data of the sensor deviates from the control line. According to the present disclosure, it is possible to set the control limit based on the Bayesian inference and validate the validity of the sensor from the actual sensor data reliably using the control limit.

Classes IPC  ?

• 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 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires

Abrégé

An airfoil profile for a turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 5/14 - Forme ou structure

Abrégé

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler including a combustion chamber and configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange with the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the combustion chamber passes, and a first air preheater configured to pass second combustion gas discharged from the first water heat exchanger and to pass air supplied to the boiler.

Classes IPC  ?

• F02C 6/18 - Utilisation de la chaleur perdue dans les ensembles fonctionnels de turbines à gaz à l'extérieur des ensembles eux-mêmes, p. ex. ensembles fonctionnels de chauffage à turbine à gaz
• F02C 7/10 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement au moyen d'échangeurs de récupération de chaleur
• F01K 21/04 - Ensembles fonctionnels de machines motrices à vapeur non prévus ailleurs utilisant un mélange de vapeur et de gazEnsembles fonctionnels produisant ou surchauffant de la vapeur en mettant en contact direct l'eau ou la vapeur avec des gaz chauds
• F01K 23/10 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de combustion provenant de l'un des cycles chauffant le fluide dans un autre cycle le fluide à la sortie de l'un des cycles chauffant le fluide dans un autre cycle

Abrégé

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange between the water and the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the boiler passes, and a fuel heat exchanger configured to pass fuel supplied to the combustor and to pass a portion of water that is returned to the water supply device from the first water heat exchanger and has a higher temperature than the water supplied to the first water heat exchanger.

Classes IPC  ?

• F02C 6/04 - 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
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• F02C 7/10 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement au moyen d'échangeurs de récupération de chaleur
• F01D 15/00 - Adaptations des "machines" ou machines motrices à des usages particuliersCombinaisons des machines motrices avec les dispositifs qu'elles entraînent
• F01K 11/02 - Ensembles fonctionnels de machines à vapeur caractérisés par des machines motrices faisant corps avec les chaudières ou les condenseurs les machines motrices étant des turbines

Abrégé

Disclosed are an air supply device and an air supply method for a hybrid power generation facility in which a gas turbine compresses air introduced from an outside, mixes the compressed air with fuel, and burns a mixture of the compressed air and the fuel to produce combustion gas. The air supply device includes a mixing chamber configured to selectively receive the combustion gas from the gas turbine, an air preheater configured to supply air to the mixing chamber, a burner configured to burn a fluid supplied from the mixing chamber, a first over-firing air supplier configured to receive a fluid from the gas turbine or the air preheater, a first pipeline connecting the gas turbine and the mixing chamber, and a second pipeline connecting the gas turbine and the first over-firing air supplier.

Classes IPC  ?

• F02C 6/10 - 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 fournissant un fluide de travail à un utilisateur, p. ex. un processus chimique, retournant le fluide de travail à une turbine de l'ensemble fonctionnel
• F01K 23/10 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de combustion provenant de l'un des cycles chauffant le fluide dans un autre cycle le fluide à la sortie de l'un des cycles chauffant le fluide dans un autre cycle
• F01K 21/04 - Ensembles fonctionnels de machines motrices à vapeur non prévus ailleurs utilisant un mélange de vapeur et de gazEnsembles fonctionnels produisant ou surchauffant de la vapeur en mettant en contact direct l'eau ou la vapeur avec des gaz chauds
• F02C 6/18 - Utilisation de la chaleur perdue dans les ensembles fonctionnels de turbines à gaz à l'extérieur des ensembles eux-mêmes, p. ex. ensembles fonctionnels de chauffage à turbine à gaz
• F22B 35/00 - Systèmes de commande pour chaudières à vapeur
• F22B 1/18 - Méthodes de production de vapeur caractérisées par le genre de chauffage par exploitation de l'énergie thermique contenue dans une source chaude la source chaude étant un gaz chaud, p. ex. des gaz d'évacuation tels que les gaz d'échappement de moteurs à combustion interne

Abrégé

A method of generating a defect image for deep learning and a system therefor are provided. The method and the system are intended to be used in generating training data for an artificial intelligence algorithm. More specifically, the training data are defect images required to train an algorithm that identifies a defect from a product.

Classes IPC  ?

• G06T 7/00 - Analyse d'image
• G06T 11/00 - Génération d'images bidimensionnelles [2D]
• G06T 5/40 - Amélioration ou restauration d'image utilisant des techniques d'histogrammes
• G06T 5/50 - Amélioration ou restauration d'image utilisant plusieurs images, p. ex. moyenne ou soustraction
• G06T 5/00 - Amélioration ou restauration d'image
• G06T 3/00 - Transformations géométriques de l'image dans le plan de l'image

Abrégé

Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

A turbine blade that allows an improvement in torque and power, and a turbine and gas turbine including the same are provided. The turbine blade includes an airfoil having a suction side and a pressure side, a platform coupled to a bottom of the airfoil, and a root protruding downward from the platform and coupled to a rotor disk, wherein the airfoil includes a cooling passage formed therein and a discharge hole connected to an upper portion of the cooling passage to discharge cooling air, and the discharge hole is inclined toward a tip of the turbine blade while extending from an inside to an outside thereof.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A sealing assembly for sealing a gap between a first component and a second component is provided. The sealing assembly includes a sealing body disposed between the first component and the second component and a pressing member disposed between the sealing body and the second component, configured to press the sealing body toward the first component, and configured to extend and compress in a circumferential direction of the first component.

Classes IPC  ?

• F16J 15/06 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
• F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines

Abrégé

A compressor blade assembly structure, a gas turbine having the same, and a method of assembling compressor blade are provided. The compressor blade assembly structure includes a compressor blade having an airfoil, a platform part, and a dovetail part, a compressor rotor disk having a dovetail slot into which the dovetail part is inserted, and a locking key mounted in a key slot formed in the dovetail slot to support the compressor blade in an axial direction.

Classes IPC  ?

• F04D 29/34 - Montage des ailettes
• 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

Abrégé

A turbine vane and a gas turbine including the same are provided. The turbine vane includes an airfoil having a pressure side and a suction side, at least one cooling channel formed radially in the airfoil, and an insert inserted into the at least one cooling channel to divide the cooling channel into a pressure side passage and a suction side passage.

Classes IPC  ?

• F01D 9/00 - Stators
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

Compressor components, such as blades and vanes, having an airfoil portion with an uncoated, nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each Z distance in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial

Abrégé

An apparatus for controlling turbine blade tip clearance is provided. The apparatus for controlling turbine blade tip clearance includes a turbine casing configured to guide a flow of combustion gas, an actuator ring rotatably mounted outside the turbine casing, a plurality of turbine blades rotatably mounted inside the turbine casing, a plurality of ring segments surrounding tips of the turbine blades and installed to form a predetermined gap with each tip, a plurality of rotary shafts each configured to have one end connected to several of the plurality of ring segments and the other end extending radially from the turbine casing, a link member configured to rotate an associated one of the rotary shafts according to circumferential rotational motion of the actuator ring, and a pusher member provided at an inner end of the rotary shaft to move the ring segments radially inward by rotation of the rotary shaft, wherein the actuator ring rotates back and forth in a predetermined angular range by an actuator installed outside the turbine casing.

Classes IPC  ?

• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor

Abrégé

A reverse osmosis apparatus for a seawater desalination system is provided. The reverse osmosis apparatus includes: a barrel in which a plurality of reverse osmosis membrane units with a reverse osmosis membrane wrapped in each reverse osmosis membrane unit are arranged; an inflow and outflow portion provided at a first end of the barrel and connected to a seawater inlet a high salinity water outlet; a partition wall configured to partition an inner space of the inflow and outflow portion into a first stage and a second stage; and a transport space portion provided in a second end of the barrel and configured to guide water being moved from a plurality of reverse osmosis membrane units arranged in the first stage to move to a plurality of reverse osmosis membrane units arranged at the second stage, wherein part of seawater fed to the inflow and outflow portion is fed around the tubes in the barrel and insulates the plurality of reverse osmosis membrane units in the barrel from external high temperature while being moved, and flows into the transport space portion.

Classes IPC  ?

• B01D 61/02 - Osmose inverseHyperfiltration
• B01D 61/04 - Prétraitement du courant d'alimentation
• B01D 61/08 - Appareils à cet effet
• C02F 1/44 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par dialyse, osmose ou osmose inverse
• C02F 103/08 - Eau de mer, p. ex. pour le dessalement
• C02F 9/00 - Traitement en plusieurs étapes de l'eau, des eaux résiduaires ou des eaux d'égout
• B01D 63/12 - Modules à membranes enroulées en spirale comprenant plusieurs ensembles enroulés en spirale
• C02F 1/00 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout

Abrégé

An apparatus for controlling tip clearance between a turbine casing and a turbine blade is provided. The apparatus for controlling tip clearance includes a casing surrounding the turbine blade, a cooling plate installed in a groove, formed in a circumferential direction in the casing, and contracted by cold air supplied thereto, the cooling plate having at least one fin formed on an outer peripheral surface thereof, and a ring segment mounted radially inside the cooling plate.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor
• F01D 25/14 - Carcasses d'enveloppe modifiées à cet effet

Abrégé

A combustor and a gas turbine capable of uniformly supplying air into a burner are provided. The combustor may include a burner including a tubular nozzle casing, a head plate coupled to an end of the nozzle casing, and a plurality of nozzles to inject fuel and air, and a duct assembly coupled to the burner, a mixture of the fuel and the air being burned in the duct assembly to produce combustion gas. Each of the nozzles may include outer nozzles and an inner nozzle installed inside the outer nozzles, each of the outer nozzles may include a nozzle tube configured to provide a channel through which air and fuel flow and a nozzle shroud configured to surround the nozzle tube, and a flow distribution member may be installed between the head plate and the nozzle shroud to distribute a flow rate of air introduced into the outer nozzle.

Classes IPC  ?

• F23R 3/26 - Commande du flux d'air
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23R 3/34 - Alimentation de différentes zones de combustion
• F23R 3/36 - Alimentation en combustibles différents

Abrégé

A turbine blade repair method is provided. The turbine blade repair method includes quantizing a position and a shape of a damaged portion of a turbine blade into numerical values, calculating a momentum loss of the turbine blade due to removal of the damaged portion, modeling a shape of a repair portion to replace the damaged portion so that the repair portion has the same momentum as the damaged portion, removing the damaged portion, and forming the modeled repair portion by performing an additive manufacturing at a position of the removed damaged portion.

Classes IPC  ?

• B23P 6/00 - Remise en état ou réparation des objets
• 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

Abrégé

An exhaust diffuser hub disposed at a longitudinal center of an exhaust diffuser is provided. The exhaust diffuser hub includes a hub extension extending from a downstream end thereof in a longitudinal direction of the exhaust diffuser. A transverse cross-sectional area of the hub extension is smaller than a transverse cross-sectional area of the hub.

Classes IPC  ?

• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
• F02K 1/78 - Autres structures des tubulures de jet
• F15D 1/04 - Agencement de déflecteurs de guidage dans les coudes des tuyaux ou les courbes des conduitsStructure des éléments de conduit pour des coudes en relation avec l'écoulement, p. ex. pour réduire les chutes de débit

Abrégé

A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

Classes IPC  ?

• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues
• F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 5/06 - Rotors à plus d'un étage axial, p. ex. du type à tambour ou à disques multiplesLeurs parties constitutives, p. ex. arbres, connections des arbres

Abrégé

The present technique presents a turbomachine component having an airfoil e.g. a vane of a gas turbine. The airfoil wall defines an internal space which includes a first and a second cooling channels having a first and a second impingement inserts, that define a first main and a first peripheral flow channels in the first cooling channel and a second main and a second peripheral flow channels in the second cooling channel, respectively. Impingement jets ejected from the main flow channels via impingement holes of the corresponding impingement inserts are received in the corresponding peripheral flow channels. A channel connecting conduit conducts a flow of the cooling air from the first cooling channel to the second cooling channel. The channel connecting conduit includes an inlet connected to an outlet of the first cooling channel, and an outlet connected to an inlet of the second cooling channel.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue

Abrégé

A stator structure and a gas turbine having the same are provided. The stator structure includes a plurality of rows of stators arranged on an inner peripheral surface of a casing, the stators being arranged alternately with a plurality of rows of blades arranged on an outer peripheral surface of a rotor, wherein each of the stators includes a vane including a first end and a second end, the first end of the vane being coupled to the inner peripheral surface of the casing by a first rotating member and a diaphragm coupled to the second end of the vane by a second rotating member. A first gap is formed between the first end of the vane and the inner peripheral surface of the casing, and a second gap is formed between the second end of the vane and the diaphragm. The vane may be provided with a slot part connected to the first and second ends of the vane to bypass a part of working fluid to the first and second gaps.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• 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

Abrégé

Disclosed is a gas turbine including a housing, a rotor rotatably provided in the housing to transfer a rotary force to a compressor, the compressor receiving the rotary force from the rotor and compressing air, a combustor mixing a fuel with the compressed air supplied from the compressor and igniting the mixture of the fuel and the air to generate combustion gas, and a turbine receiving the rotary force caused by the combustion gas generated by the combustor and rotating the rotor by using the received rotary force.

Classes IPC  ?

• F01D 5/20 - Extrémités de pales spécialement façonnées en vue d'obturer l'espace entre ces extrémités et le stator
• F01D 5/16 - Forme ou structure pour contrebalancer les vibrations des aubes
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 5/02 - Organes de support des aubes, p. ex. rotors
• F01D 5/14 - Forme ou structure

Abrégé

A strut structure with a strip for an exhaust diffuser of a gas turbine and a gas turbine having the same are provided. The strut structure with a strip for an exhaust diffuser of a gas turbine is configured to include a plurality of struts disposed along an outer circumference of a diffuser body disposed on a central side of the exhaust diffuser, and one or more strips formed on the strut, wherein an exhaust gas passing through the strut flows along the strip from a leading edge of the strut to alleviate a separated flow phenomenon, and wherein if the exhaust gas enters the strip, corner vortices are formed on the leading edge of the strut, and if the exhaust gas flows along the strip, streamwise vortices are formed to alleviate a pressure loss of the exhaust gas.

Classes IPC  ?

• F01D 25/30 - Têtes d'évacuation, chambres ou parties analogues

Abrégé

Provided are a bearing and a power generation system including the same. The bearing supporting a shaft system of a power generation system in a radial direction includes a pad disposed on an outer side of the shaft system with respect to the radial direction and including a cooling path through which oil flows. In the bearing and the power generation system including the same, the cooling flow path is formed through the pad so that the oil existing between the pad and the shaft system flows into the cooling flow path to cool the pad. Accordingly, the pad is continuously cooled during the operation of the power generation system, and the temperature of the pad is prevented from rising above the threshold value even if friction occurs between the shaft system and the pad.

Classes IPC  ?

• F16C 17/03 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges radiales uniquement avec segments supportés obliquement, p. ex. paliers Michell
• F16C 33/10 - Structures relatives à la lubrification
• F16C 37/00 - Refroidissement des paliers
• F16C 17/06 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges axiales uniquement avec segments supportés obliquement, p. ex. paliers Michell

Abrégé

Impingement insert for an airfoil of a blade/vane of a gas turbine is provided. The impingement insert includes a triple-walled section having a central wall, an outer and an inner peripheral walls, that define—a central channel at an inner surface of the central wall, an inner channel between the central wall and the inner peripheral wall, a middle channel between the inner peripheral wall and the outer peripheral wall, and an outer channel at an outer surface of the outer peripheral wall. Impingement cooling holes are provided in the outer peripheral wall that use the cooling air of the middle channel to eject impingement jets into the outer channel. The impingement insert includes at least one supply duct that fluidly connects the central channel to the middle channel for supplying the cooling air from the central channel to the middle channel, at least one extraction duct that extends between the outer and the inner peripheral walls across the middle channel, and has an inlet at the outer channel, and an outlet at the inner channel, for flowing the cooling air, after impingement, from the outer channel into the inner channel.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A ring segment having improved cooling efficiency is provided. The ring segment may include a shield plate mounted to a casing which accommodates a turbine and configured to face an inner wall of the casing, a pair of hooks configured to protrude from the shield plate toward the casing to be coupled to the casing, a cavity defined between the shield plate and the pair of hooks, a plurality of first cooling passages configured to connect the cavity and first side surfaces facing each other of the shield plate, and a plurality of second cooling passages configured to connect the cavity and second side surfaces facing each other of the shield plate, wherein the first cooling passages extend in a longitudinal direction of a central axis of the turbine, and the second cooling passages extend in a circumferential direction of the turbine.

Classes IPC  ?

• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F01D 25/12 - Refroidissement
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

Disclosed herein is a machine for cutting nozzles of reactor vessels. The machine for cutting nozzles of reactor vessels comprises a cutting unit positioned at an upper surface edge of a reactor vessel having a nozzle and having a saw blade part having different contact areas to cut the nozzle, a drive unit providing the saw blade part with rotary power, and a foreign substance suction unit provided at one end of the cutting unit in contiguity with the saw blade part to suck foreign substances generated when the nozzle is cut by the saw blade part, wherein the foreign substance suction unit sucks the foreign substances by approaching an outer peripheral surface of the nozzle when the saw blade part moves in a cutting direction of the nozzle.

Classes IPC  ?

• B23D 59/00 - Dispositifs annexes spécialement conçus pour les machines à scier ou les dispositifs de sciage
• B23D 57/00 - Machines à scier ou dispositifs de sciage non couverts par l'un des groupes
• G21D 1/00 - Détails des installations à énergie nucléaire
• B23D 53/04 - Machines à scier ou dispositifs de sciage à lames de scie à ruban se comportant, pendant l'emploi, comme un ruban sans fin, p. ex. pour découper selon des contours déterminés avec des roues pour supporter le ruban, montées de façon à pouvoir se déplacer ou pivoter, pour d'autres buts que le seul réglage
• B23D 53/08 - Machines à scier ou dispositifs de sciage à lames de scie à ruban se comportant, pendant l'emploi, comme un ruban sans fin, p. ex. pour découper selon des contours déterminés pour couper des profilés
• B23D 53/00 - Machines à scier ou dispositifs de sciage à lames de scie à ruban se comportant, pendant l'emploi, comme un ruban sans fin, p. ex. pour découper selon des contours déterminés
• B23D 55/02 - Machines à scier ou dispositifs de sciage à lames de scie à ruban, caractérisés uniquement par la structure d'organes particuliers des bâtisMachines à scier ou dispositifs de sciage à lames de scie à ruban, caractérisés uniquement par la structure d'organes particuliers des tables
• B23D 55/10 - Machines à scier ou dispositifs de sciage à lames de scie à ruban, caractérisés uniquement par la structure d'organes particuliers des dispositifs de tension des lames de scie à ruban

Abrégé

A blade coupling structure and a turbine system having the same securely couple a blade to a rotor disk. The blade coupling structure includes a root elastic member disposed between a root end of a blade root of the blade and an inner end of a coupling slot formed in the rotor disk; and a wedge member having a wedge body fitted between the root elastic member and the inner end of the coupling slot. The wedge member and the root elastic member press each other and press the root end so that the blade root is fixedly coupled to the coupling slot. A flat portion of the wedge member contacts the root elastic member, and an inclined portion of the wedge member facilitates the fitting of the wedge body. A wedge passage is formed in non-contact regions of the wedge body and passes a cooling fluid to the blade.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F01D 5/14 - Forme ou structure

Abrégé

An apparatus for optimizing control parameters of a power plant is provided. The apparatus for optimizing control parameters of a power plant includes: a model generator configured to configure a forecast model including a process model and a control model, a model corrector configured to correct a first parameter of the process model through operation data of a real power plant, and a tuner configured to tune a second parameter, which is a parameter related to a time delay of the forecast model, so as to have a target load increase rate.

Classes IPC  ?

• 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
• F01K 3/26 - Ensembles fonctionnels caractérisés par l'emploi d'accumulateurs de vapeur ou de chaleur ou bien de réchauffeurs intermédiaires de vapeur comportant des réchauffeurs avec chauffage par la vapeur
• F22G 5/12 - Commande de la température de surchauffe en abaissant la température de la vapeur surchauffée, p. ex. par injection d'eau pulvérisée
• F01K 13/02 - Commande, p. ex. arrêt ou démarrage
• F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
• F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage
• F01D 17/04 - Aménagement des éléments sensibles sensibles à la charge

Abrégé

An apparatus for automatically tuning a fluid temperature PID (proportional-integral-differential) controller is provided. The apparatus for automatically tuning a fluid temperature PID controller includes: a setter configured to calculate an initial value of a gain of a controller configured to control a fluid temperature by deriving a physical property of the fluid temperature, and a tuner configured to tune the initial value of the gain of the controller using an artificial intelligence neural network algorithm according to a control target.

Classes IPC  ?

• G05B 13/02 - Systèmes de commande adaptatifs, c.-à-d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
• G06N 3/063 - Réalisation physique, c.-à-d. mise en œuvre matérielle de réseaux neuronaux, de neurones ou de parties de neurone utilisant des moyens électroniques
• G05B 11/42 - Commandes automatiques électriques avec les dispositions nécessaires pour obtenir des caractéristiques particulières, p. ex. proportionnelles, intégrales, différentielles pour obtenir une caractéristique à la fois proportionnelle et dépendante du temps, p. ex. P.I., P.I.D.

Abrégé

A rotor of a turbine cooled by compressed air supplied from a compressor of a gas turbine prevents combustion gas from flowing between platforms and guides compressed air discharged outside the platform toward the blade airfoil. The rotor includes a disk having an outer circumferential surface; a plurality of blade airfoils arranged around the disk; and a plurality of platforms coupled to the outer circumferential surface of the disk, each platform having an outer circumferential surface to receive a corresponding blade airfoil and side-facing surfaces which are spaced apart from each other on adjacent platforms of the plurality of platforms to form a cooling passage through which the compressed air flows outward in a radial direction of the rotor, the cooling passage including a bend in a rotational direction of the rotor. The bend directs the compressed air in a direction opposite to the rotational direction of the rotor.

Classes IPC  ?

• F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• 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

Abrégé

A control device for a power generation system comprising an energy storage system (ESS) and a power plant is provided. The control device includes: a controller configured to compare a supply frequency of a supply power supplied to a consumer with a reference frequency, compare a charge amount of the ESS with a reference charge amount, and control the ESS and the power plant such that the supply power is controlled according to a result of the frequency comparison and a result of the charge amount comparison, an opening degree control device configured to control an opening degree of a steam valve disposed in the power plant by the control of the controller, and a fuel quantity control device configured to control a quantity of fuel injected into the power plant for power generation by the control of the controller.

Classes IPC  ?

• H02J 9/04 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries

Abrégé

An embodiment of the present invention provides a swirl vane-type moisture separator, which is provided in a reactor steam generator, separates moisture from wet steam, and supplies dry steam to a turbine side, the swirl vane-type moisture separator comprising a riser and a swirl vane. The riser includes: an inner tube which has a steam flow path formed therein, through which wet steam flows from a lower portion and dry steam is discharged to an upper portion, and a liquid film passage hole which is formed on the circumference of the upper end and through which a liquid film formed by droplets separated from the wet steam passes; and an outer tube that is provided so as to surround at least the upper circumference of the inner tube and forms a downcomer through which the liquid film that has passed through the liquid film passage hole flows down and is discharged. The swirl vane is rotatably provided at a predetermined position in the steam flow path, and separates the droplets by means of centrifugal force from the wet steam moving along the steam flow path.

Classes IPC  ?

• B01D 53/26 - Séchage des gaz ou vapeurs
• B01D 53/24 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par force centrifuge
• B01D 45/14 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par des pales, disques, tambours ou brosses rotatives
• F22B 37/32 - Dispositifs séparateurs de vapeur employant la force centrifuge

Abrégé

The present disclosure relates to an exhaust gas cooling device and method, and more particularly, to a device and method for installing an exhaust gas cooling device on the upper end of a duct of a heat recovery steam generator to cheaply cool the exhaust gas without occupying an additional dedicated area. An object of the present disclosure is to reduce the costs using a cheap cooling device in the cooling path for cooling the exhaust gas. In one aspect, the exhaust gas cooling device includes an exhaust gas cooling unit located on the upper end of a duct of a heat recovery steam generator connected with a gas turbine and for cooling the exhaust gas discharged from the gas turbine; and a control unit for controlling the exhaust gas cooling unit to lower the increase rate of the energy of the exhaust gas flowed into the heat recovery steam generator through the duct.

Classes IPC  ?

• F01K 23/10 - Ensembles fonctionnels caractérisés par plus d'une machine motrice fournissant de l'énergie à l'extérieur de l'ensemble, ces machines motrices étant entraînées par des fluides différents les cycles de ces machines motrices étant couplés thermiquement la chaleur de combustion provenant de l'un des cycles chauffant le fluide dans un autre cycle le fluide à la sortie de l'un des cycles chauffant le fluide dans un autre cycle
• F01K 19/10 - Refroidissement de la vapeur d'évacuation autrement que par un condenseurDispositions pour rendre la vapeur d'évacuation invisible
• F01K 13/02 - Commande, p. ex. arrêt ou démarrage

Abrégé

A boiler facility includes first and second fuel transfer apparatuses for transporting fine particulate fuel to a combustor. A first fuel transfer apparatus includes a main body and a diffuser. The main body has a flow space through which fuel is transferred and an inner surface that defines the flow space of the main body and includes a lower inner surface that extends obliquely downward. The diffuser is installed at a downstream end of the main body, the diffuser having a flow space through which fuel is transferred and an inner surface that defines the flow space of the first diffuser and includes a lower inner surface that extends obliquely upward. A second fuel transfer apparatus includes a transfer pipe having a flow channel, a second diffuser installed along the inner circumferential surface of the transfer pipe, and a guide installed in the second diffuser and inclined downward.

Classes IPC  ?

• F23B 40/02 - Appareils à combustion comportant des moyens entraînés pour alimenter en combustible la chambre de combustion le combustible étant amené et dispersé sur la surface supportant le combustible
• F23K 3/02 - Alimentation pneumatique, c.-à-d. par courant d'air

Abrégé

An apparatus and method for cleaning an oxide film using a direct current reverse polarity are provided. The apparatus for cleaning an oxide film formed on a workpiece may include a power supply configured to apply direct current power and to include a positive electrode terminal and a negative electrode terminal, the workpiece configured to be electrically connected to the negative electrode terminal to act as a negative electrode to which a current is applied, and a torch having a positive electrode, which is spaced apart from the oxide film by a predetermined distance and is electrically connected to the positive electrode terminal, the torch being installed to be movable relative to the workpiece. The oxide film formed on the workpiece may be removed by applying a reverse polarity direct current between the workpiece, serving as the negative electrode, and the positive electrode to generate an arc.

Classes IPC  ?

• B23K 10/00 - Soudage ou découpage au moyen d'un plasma
• B23K 9/167 - Soudage ou découpage à l'arc utilisant des gaz de protection et une électrode non consommable
• B23K 9/16 - Soudage ou découpage à l'arc utilisant des gaz de protection
• B23K 35/36 - Emploi de compositions non métalliques spécifiées, p. ex. comme enrobages, comme fluxEmploi 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

Abrégé

A fuel nozzle assembly and a gas turbine combustor including the same are provided. The fuel nozzle assembly may include an end plate coupled to one end of an annular casing, and a fuel nozzle configured such that one end thereof is supported by the end plate and the other end thereof extends outward. The fuel nozzle may include a center fuel nozzle and a plurality of side fuel nozzles arranged annularly to surround the center fuel nozzle. The side fuel nozzle may include a nozzle body located at a center thereof, a shroud spaced outward from the nozzle body, and a plurality of swirlers located between the nozzle body and the shroud. Each of the swirlers may include a leading edge directed toward the end plate and a trailing edge located opposite the leading edge. In each of the side fuel nozzles, distances between the leading edges are different from each other.

Classes IPC  ?

• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23R 3/34 - Alimentation de différentes zones de combustion
• F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement

Abrégé

A noise reducing wall system is provided. The noise reducing wall system includes first and second board layers facing in parallel with each other along a longitudinal direction thereof, a heat insulation member surrounded by the first and second board layers, and a stud connection structure that fastens the first and second board layers using a stud bolt passing through the heat insulation member to connect the first board layer and the second board layer. The stud bolt connects the first and second board layers in a thickness direction and has a bent portion extending in the longitudinal direction and disposed at an intermediate point in the thickness direction.

Classes IPC  ?

• E04B 1/90 - Éléments à la fois isolants acoustiques et thermiques en forme de dalles
• E04C 2/02 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux caractérisés par des matériaux spécifiés
• F24F 13/24 - Moyens pour éviter ou supprimer le bruit
• E04B 2/00 - Murs, p. ex. cloisons, pour bâtimentsStructure des murs en ce qui concerne l'isolationAssemblages spécifiques pour les murs

Abrégé

A clearance adjusting apparatus to move a thrust bearing of a gas turbine back and forth to adjust a tip clearance of a turbine is provided. The clearance adjusting apparatus includes an adjusting plate disposed to move forward from or rearward to a reference surface, a biasing cylinder disposed to selectively move the adjusting plate back and forth, a stopper disposed to be moved toward the adjusting plate after being moved forward to prevent a rearward movement of the adjusting plate, a position sensor disposed to measure a distance from the reference surface to the adjusting plate, and a controller configured to receive information about measurements from the position sensor and control an operation of the stopper and the biasing cylinder based on the received information.

Classes IPC  ?

• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F04D 29/046 - Paliers
• F01D 25/16 - Aménagement des paliersSupport ou montage des paliers dans les stators

Abrégé

A clearance adjusting apparatus disposed in front of a compressor of a gas turbine to axially move a compressor disk back and forth to adjust a tip clearance formed between a compressor blade and a compressor casing is provided. The clearance adjusting apparatus includes a hollow fastening part disposed in front of the compressor casing, a shaft disposed in the fastening part and coupled to a front side of the compressor disk, an adjusting part disposed between the fastening part and the shaft to axially move the shaft back and forth to adjust the tip clearance, and a biasing part disposed on the fastening part to bias the adjusting part back and forth to adjust a position of the adjusting part and the shaft.

Classes IPC  ?

• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor

Abrégé

A compressor blade of a gas turbine includes a compressor blade portion including a plurality of layers; and a carbon fiber reinforcement embedded in the plurality of layers of the compressor blade portion and oriented in a direction of stress fields of the compressor blade when in operation. A method of manufacturing the compressor blade includes preparing a composite material including fiber-reinforced layers; forming a first layer of the composite material to extend in a radial direction of the compressor blade; and stacking a second layer of the composite material on the first layer in an axial direction of the compressor blade. The compressor blade is 3D-printed by forming each composite material layer in a radial direction, which layers are stacked in an axial direction. Fiber reinforcement in the composite compressor blade is oriented in line with the stress fields inherent in the operation of the compressor blade.

Classes IPC  ?

• F01D 5/14 - Forme ou structure
• B33Y 10/00 - Procédés de fabrication additive
• B33Y 80/00 - Produits obtenus par fabrication additive
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• B29C 70/30 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
• 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 64/118 - Procédés de fabrication additive n’utilisant que des matériaux liquides ou visqueux, p. ex. dépôt d’un cordon continu de matériau visqueux utilisant un matériau filamentaire mis en fusion, p. ex. modélisation par dépôt de fil en fusion [FDM]
• B33Y 70/00 - Matériaux spécialement adaptés à la fabrication additive
• B29L 31/08 - Pales pour rotors, stators, ventilateurs, turbines ou dispositifs analogues, p. ex. hélices
• B29K 77/00 - Utilisation de polyamides, p. ex. polyesteramides, comme matière de moulage
• B29K 307/04 - Carbone

Abrégé

A compressor blade of a gas turbine includes a root member; an airfoil that is disposed on the root member and includes a first interior wall and a second interior wall forming a hollow space defined between the first and second interior walls; and an organic vibration stiffener (OVS) formed on at least one of the first interior wall and the second interior wall. The OVS is formed by 3D printing performed with respect to a surface of the at least one of the first interior wall and the second interior wall and includes an uneven surface formed on at least part of the at least one of the first interior wall and the second interior wall. The OVS may include a protruded or recessed portion protruding from or recessed into at least part of the at least one of the first interior wall and the second interior wall.

Classes IPC  ?

• F01D 5/16 - Forme ou structure pour contrebalancer les vibrations des aubes
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A turbine vane and a gas turbine including the same are provided. The turbine vane including an airfoil; an outer shroud formed at a top of the airfoil; and an inner shroud including a stress canceling part formed at a bottom of the airfoil and configured to cancel a stress applied to the airfoil by flowing combustion gas.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A combustor and a gas turbine including the same which can reduce a loss of pressure and enhance a cooling efficiency of a liner and transition piece are provided. The combustor may include a liner configured to define a combustion chamber, a transition piece coupled to a rear end of the liner, a flow sleeve configured to surround the liner and the transition piece, a plurality of impingement holes formed in the flow sleeve, and a plurality of inserts inserted into at least some of the impingement holes, wherein each of the inserts may include a first channel configured to guide combustion air, introduced into an associated one of the impingement holes, in a direction parallel to a direction of extension of an annular passage between the flow sleeve and the liner or an annular passage between the flow sleeve and the transition piece, and a second channel configured to guide the combustion air, introduced into the associated one of the impingement holes, in a direction transverse to the annular passage between the flow sleeve and the liner or the annular passage between the flow sleeve and the transition piece.

Classes IPC  ?

• F23R 3/06 - Disposition des ouvertures le long du tube à flamme
• F23R 3/10 - Aménagements de l'entrée d'air pour l'air primaire
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• 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 3/22 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion le combustible ou l'oxydant étant gazeux aux température et pression normales
• F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
• F02C 7/22 - Systèmes d'alimentation en combustible
• F23R 3/08 - Disposition des ouvertures le long du tube à flamme entre les sections annulaires de tubes à flamme, p. ex. tubes à flamme à sections télescopiques

Abrégé

A turbine vane, a turbine, and a gas turbine capable of reducing thermal stress are provided. The turbine vane may include an airfoil including a leading edge and a trailing edge, an inner shroud disposed at one end of the airfoil to support the airfoil, an outer shroud disposed at the other end of the airfoil to support the airfoil and configured to face the inner shroud, a first cooling passage and a second cooling passage configured to extend in a height direction thereof, and a first passage bending part configured to connect the first cooling passage and the second cooling passage, and the first passage bending part is positioned inside the inner shroud or the outer shroud.

Classes IPC  ?

• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 25/12 - Refroidissement

Abrégé

An airfoil of either of a turbine blade or a turbine vane includes a cooling passage; at least one disk body disposed on an inner wall of the cooling passage and configured to reduce a flow cross-sectional area of the cooling passage to increase a fluid pressure of cooling fluid flowing through the cooling passage; and at least one through-hole formed in each of the at least one disk body such that the cooling fluid flows through the at least one through-hole and forms a vortex on a downstream side of the at least one through-hole. The cooling passage includes an inlet supplied with the cooling fluid and an end opposite to the inlet, and the at least one disk body is disposed at the inlet of the cooling passage and is configured to increase the fluid pressure of the cooling fluid flowing into the cooling passage.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 25/12 - Refroidissement
• F02C 7/16 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur

Abrégé

A heat exchange apparatus cools air supplied from a compressor to a turbine and includes a shell housing; a heat exchanger coupled to an outer surface of the shell housing and configured to cool air passing through an air channel of the heat exchanger using a coolant passing through a coolant channel; a flow guide installed in the shell housing and connected to the air channel of the heat exchanger in order to pass the cooled air into the shell housing, the flow guide having a distal end spaced apart from an inner surface of the shell housing; and at least one air discharge port installed through a sidewall of the shell housing to communicate with the air channel via the flow guide. The heat exchanger is a printed board type including a first plate and a second plate and is formed by alternately stacking the first and second plates.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F28F 3/02 - Éléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p. ex. avec des ailettes, avec des évidements, avec des ondulations

Abrégé

A sealing structure for a gas turbine includes a turbine rotor disk, a turbine blade coupled the turbine rotor disk, and an interstage disk interposed between adjacent turbine rotor disks. The turbine blade includes a blade circumferential surface protruding axially and extending in a circumferential direction of the turbine rotor disk and mutually engaging with a disk circumferential surface formed circumferentially on the turbine rotor disk. The interstage disk includes a rim portion and a groove formed in the rim portion. A plurality of static ring seals are mounted in the groove, each static ring seal facing toward the blade circumferential surface and the disk circumferential surface. The static ring are configured such that an outer circumferential surface of all the static ring seals contact the blade circumferential surface and the outer circumferential surface of at least one of the static ring seals does not contact the disk circumferential surface.

Classes IPC  ?

• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

A combustor has an axial fuel staging system to allow a fuel-air mixture to be injected from two axially spaced stages using an injector for injection of a secondary fuel-air mixture. The combustor includes a liner defining a combustion chamber; a transition piece coupled to a rear end of the liner; a flow sleeve defining an annular channel by surrounding the liner and the transition piece; and at least one injector disposed on a circumferential position of the flow sleeve to inject a mixture of fuel and air into the combustion chamber. Each of the at least one injector includes an injection pipe extending radially and passing through both the flow sleeve and either of the liner and the transition piece; a plate coupled to the injection pipe; and a plurality of mixing passages formed through the plate. The combustor improves fuel-air mixing and prevents flash back.

Classes IPC  ?

• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F23R 3/34 - Alimentation de différentes zones de combustion
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage

Abrégé

A water treatment apparatus including an underwater plasma discharge module is provided. The water treatment apparatus includes a dissolved air flotation device configured to remove foreign matter contained in water and an underwater plasma discharge module disposed at a preceding stage of the dissolved air flotation device and configured to cause a portion of the water to be introduced into the dissolved air flotation device to perform underwater plasma discharging, wherein the dissolved air flotation device comprises a mixing and coagulation basin configured to coagulate or flocculate the foreign matter contained in the water to form and grow flocs of the foreign matter, and a flotation basin configured to raise and remove the flocs by supplying microbubbles to the water passing through the mixing and coagulation basin.

Classes IPC  ?

• C02F 9/00 - Traitement en plusieurs étapes de l'eau, des eaux résiduaires ou des eaux d'égout
• C02F 1/00 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout
• C02F 1/46 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par des procédés électrochimiques
• C02F 101/30 - Composés organiques
• C02F 1/24 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par flottation

Abrégé

A liner cooling structure of a duct assembly reduces pressure loss generated in the compressed air flow for cooling the liner. The duct assembly includes a liner, a transition piece, and a flow sleeve, and the transition piece and the flow sleeve form a transition piece channel through which a main stream of compressed air is introduced to the duct assembly. The liner cooling structure includes a first flow passage through which the main stream of compressed air passes in a first direction; and a second flow passage formed as a plurality of inlet holes in the flow sleeve to communicate with the first flow passage and configured to pass an auxiliary stream of compressed air in a second direction from outside the flow sleeve to inside the flow sleeve, the auxiliary stream joining the main stream such that the second direction forms an acute angle with the first direction.

Classes IPC  ?

• F23M 5/08 - Refroidissement des armatures, enveloppes ou paroisTubes de parois
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage

Abrégé

A method of and an apparatus for deriving a boiler combustion model by setting input and output data and using a combination of mathematical models including an artificial neural network (ANN) are provided. The method of deriving a boiler combustion model may include setting input and output data required for derivation of a boiler combustion model, deriving a boiler combustion model including an input layer configured to receive the input data, a hidden layer including multiple nodes configured to perform computation on the input data, and an output layer configured to output a computation result transferred from the hidden layer as the output data, and determining a precision of the derived boiler combustion model.

Classes IPC  ?

• G06F 30/27 - Optimisation, vérification ou simulation de l’objet conçu utilisant l’apprentissage automatique, p. ex. l’intelligence artificielle, les réseaux neuronaux, les machines à support de vecteur [MSV] ou l’apprentissage d’un modèle
• G06N 3/04 - Architecture, p. ex. topologie d'interconnexion
• G06F 30/28 - Optimisation, vérification ou simulation de l’objet conçu utilisant la dynamique des fluides, p. ex. les équations de Navier-Stokes ou la dynamique des fluides numérique [DFN]
• G06F 111/10 - Modélisation numérique

Abrégé

A combustor and a gas turbine having the same which can improve a degree of mixing of fuel and air and achieve a reduction in combustion vibration are provided. The combustor may include a fuel nozzle disposed on a nozzle tube, a center body disposed at a center of the fuel nozzle and connected to a fuel nozzle base, a plurality of swirlers circumferentially spaced apart from each other between the center body and the fuel nozzle, and a plurality of fuel pegs spaced apart from each other around the center body to inject fuel into air flowing in the fuel nozzle, wherein the plurality of fuel pegs are disposed behind the swirlers on the center body based on a combustion chamber of the combustor.

Classes IPC  ?

• 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
• F02C 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible

Abrégé

Disclosed herein is a gas turbine blade. The gas turbine blade includes a turbine blade (33) provided in a turbine, and film cooling elements (100), each including a cooling channel (110) for cooling of the turbine blade (33), an outlet (120) through which cooling air is discharged, and a plurality of ribs (130), wherein the outlet (120) extends from a longitudinally extended end of the cooling channel (110) to an outer surface of the turbine blade (33) and has a width increased from one end of the cooling channel (110) to the outer surface of the turbine blade (33), and the ribs (130) face each other on inner walls of the outlet (120).

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 5/14 - Forme ou structure
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A transition piece assembly improves the cooling of a transition piece by increasing a flow of compressed air toward a transition piece casing. The assembly includes a transition piece including an inlet and an outlet; a transition piece casing spaced apart from the transition piece, the transition piece casing enclosing the transition piece to form an annular interspace between an inner circumferential surface of the transition piece casing and an outer circumferential surface of the transition piece, the transition piece casing including an outer circumferential surface over which compressed air flows; a support member for supporting the transition piece casing, the support member inserted into the annular interspace and seated on the outer circumferential surface of the transition piece; and a guide member that is fixed with respect to the transition piece casing and includes an axially perpendicular structure to guide the compressed air toward the transition piece casing.

Classes IPC  ?

• F23R 3/60 - Structures de supportMoyens de fixation ou de montage
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Abrégé

The disclosure relates to a carbon blade for a wind turbine with multiple down conductors, and more particularly, to a carbon blade for a wind turbine with multiple down conductors that includes multiple down conductors disposed thereon to reduce or prevent a potential difference between a plurality of points to be formed thereon from being generated.

Classes IPC  ?

• F03D 80/30 - Protection contre la foudre
• F03D 1/06 - Rotors

Abrégé

A turbine blade, a turbine, and a gas turbine which have enhanced cooling performance are provided. The turbine blade may include: an airfoil having a blade shape and including a suction side formed in a convex shape and a pressure side formed in a concave shape; a platform coupled to a lower portion of the airfoil; and a root member protruding downward from the platform and coupled to a rotor disk, wherein the platform may include: a plurality of inlets through which air is drawn into the platform; a plurality of outlets through which the air is discharged from the platform; and a cooling passage connecting the inlets to the outlets and including a plurality of dispersion spaces, a width in each dispersion spaces increasing from the inlet to the outlet, and a narrow space formed between the dispersion spaces and having a width less than the width of each dispersion spaces.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A turbine vane improves cooling performance by guiding an impingement cooling fluid, introduced through a cooling hole of an inner sidewall provided inside the turbine vane, to flow while in contact with an inner surface of the turbine vane for a relatively long time. The turbine vane includes an outer sidewall configured to form an airfoil comprising a leading edge and a trailing edge; an inner sidewall disposed inside the outer sidewall to form a gap between the inner sidewall and an inner surface of the outer sidewall, the inner sidewall having a plurality of cooling holes communicating with the gap; and a plurality of spiral guides formed on the inner surface of the outer sidewall and disposed at positions facing the respective cooling holes, the plurality of spiral guides configured to guide a cooling fluid having passed through the cooling holes to impinge on the spiral guides.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• 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 7/12 - Refroidissement des ensembles fonctionnels

Abrégé

An airfoil, a turbine, and a gas turbine having enhanced cooling performance are provided. The airfoil including a leading edge and a trailing edge may include: a first cooling passage connected to the leading edge; a second cooling passage connected to the trailing edge; a third cooling passage formed between the first cooling passage and the second cooling passage; a plurality of partitions provided in the second cooling passage and configured to partition the second cooling passage into a plurality of portions in a height direction of the second cooling passage; and a perforated plate extending in the height direction of the second cooling passage, and coupled with the partitions to support the partitions.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F02C 7/12 - Refroidissement des ensembles fonctionnels
• 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 5/02 - Organes de support des aubes, p. ex. rotors

Abrégé

An airfoil, a turbine and a gas turbine having enhanced cooling performance are provided. The airfoil including a leading edge and a trailing edge may include: a first cooling passage connected to the leading edge; a second cooling passage connected to the trailing edge; a third cooling passage formed between the first cooling passage and the second cooling passage; a shock tube installed in the first cooling passage and configured to form an auxiliary cooling passage between the shock tube and the leading edge, and to include a plurality of dispersion hole in the shock tube; and a flow guide member installed on the shock tube and configured to guide a flow of air that is drawn from the third cooling passage into the first cooling passage.

Classes IPC  ?

• F01D 15/12 - Combinaisons avec des transmissions mécaniques
• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F01D 25/12 - Refroidissement
• 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 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes

Abrégé

A method of predicting membrane fouling in a reverse osmosis process includes collecting information relative to the reverse osmosis process being performed over a predetermined period of time, the collected information including a process factor and a water quality factor, the process factor including a produced water flow rate; calculating a salt removal rate and a pressure drop based on the collected information; normalizing the produced water flow rate, the salt removal rate, and the pressure drop; generating a prediction equation using normalized values of the produced water flow rate, the salt removal rate, and the pressure drop values; and predicting membrane fouling through the generated prediction equation to determine a chemical cleaning time. Process and water quality factors are normalized to temperature and/or flow rate, and the prediction equation uses the normalized factors. Both short-term and long-term predictions are made for chemical cleaning time and membrane module replacement time.

Classes IPC  ?

• B01D 65/08 - Prévention de l'encrassement de la membrane ou de la polarisation par concentration
• B01D 61/12 - Commande ou régulation
• B01D 61/58 - Procédés à plusieurs étapes
• B01D 65/02 - Nettoyage ou stérilisation de membranes
• G06F 17/11 - Opérations mathématiques complexes pour la résolution d'équations

Abrégé

A gas turbine rotor includes: a first rotor in a shaft shape extending by a predetermined length in an axial direction, and provided with an insertion hole at an end of the first rotor; a second rotor in a shaft shape extending by a predetermined length in the axial direction, and provided with an insertion part extending by a predetermined length at an end of the second rotor and corresponding to the insertion hole such that the insertion part is inserted into the insertion hole; and a connecting member mounted between the insertion hole and the insertion part to connect the first rotor and the second rotor together, and made of a material having a thermal expansion coefficient different from a thermal expansion coefficient of both the first rotor and the second rotor.

Classes IPC  ?

• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F01D 5/06 - Rotors à plus d'un étage axial, p. ex. du type à tambour ou à disques multiplesLeurs parties constitutives, p. ex. arbres, connections des arbres
• F01D 25/14 - Carcasses d'enveloppe modifiées à cet effet

Abrégé

A facility receives an indication of a rate of energy output sought from a production array of solar panels. The facility controls a power inverter to which the production array is connected to deliver to an electrical grid to which the power inverter is connected a rate of energy output that is based on the indicated rate of energy output.

Classes IPC  ?

• H02J 3/48 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante en phase
• H02S 10/00 - Centrales électriques PVCombinaisons de systèmes d’énergie PV avec d’autres systèmes pour la production d’énergie électrique
• H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
• H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs

Abrégé

An inlet flow structure can comprise: a plurality of bellmouth elements, each of the plurality of bellmouth elements including a bellmouth and a diffuser; a plurality of supply plenums, each of the plurality of supply plenums surrounding a respective one of the plurality of bellmouth elements, wherein the plurality of supply plenums are divided by a wall which provides equivalent air flow to each bellmouth element. The inlet flow structure comprises an inlet plenum disposed on the plurality of supply plenums and an outlet plenum disposed on the plurality of bellmouth elements.

Classes IPC  ?

• F15D 1/02 - Action sur l'écoulement des fluides dans les tuyaux ou les conduits
• G01F 1/42 - Orifices ou tuyères

Abrégé

Disclosed is a sequencing batch reactor (SBR) for sewage treatment. The SBR is applicable to an energy-producing sewage treatment system. The SBR includes a treatment tank and a hybrid bacterial strain screening tank. The treatment tank removes ammonium contained in supernatant liquid using anaerobic ammonium-oxidizing (anammox) bacteria. The hybrid bacterial strain screening tank screen anammox bacteria granules out by passing the supernatant liquid discharged from the treatment tank through the hybrid bacterial strain screening tank. The SBR generates biogas using the anammox bacteria and reduces the nitrogen content in the supernatant liquid. The SBR can separate the anammox bacteria granules with high separation efficiency, thereby shortening sewage treatment time and recycling activated sludge, resulting in a dramatic decrease in the amount of waste sludge.

Classes IPC  ?

• C02F 1/44 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par dialyse, osmose ou osmose inverse
• C02F 3/28 - Procédés de digestion anaérobies
• C02F 3/30 - Procédés aérobies et anaérobies
• C02F 3/34 - Traitement biologique de l'eau, des eaux résiduaires ou des eaux d'égout caractérisé par les micro-organismes utilisés
• C02F 3/20 - Procédés par les boues activées utilisant des diffuseurs
• C02F 1/38 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout par séparation centrifuge
• C02F 3/12 - Procédés par les boues activées
• C02F 101/30 - Composés organiques
• C02F 101/16 - Composés de l'azote, p. ex. ammoniac
• C02F 1/00 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout
• C02F 11/04 - Traitement anaérobieProduction du méthane par de tels procédés
• C02F 11/12 - Traitement des boues d'égoutDispositifs à cet effet par déshydratation, séchage ou épaississement

Abrégé

A device for measuring the membrane fouling index which can measure the modified fouling index (MFI) and the silt density index (SDI) at the same time and quantify the degree of membrane fouling caused by various kinds of membrane fouling materials, such as particulate materials, colloids, organic matters, and so on, in a short period of time.

Classes IPC  ?

• G01N 17/00 - Recherche de la résistance des matériaux aux intempéries, à la corrosion ou à la lumière
• B01D 65/10 - Test de membranes ou d'appareils à membranesDétection ou réparation de fuites
• B01D 61/10 - AccessoiresOpérations auxiliaires
• B01D 61/12 - Commande ou régulation

Abrégé

A system and method for configuring a boiler combustion model are provided. The system for configuring the boiler combustion model may include a model generator configured to generate the boiler combustion model using, as input/output data, data obtained based on measured data, analysis data, and controller information, a model simulator configured to simulate the generated boiler combustion model and output simulated results, and a model modifier configured to evaluate the boiler combustion model based on the simulated results and generate modification information for modifying the boiler combustion model based on the generated boiler combustion model and corresponding evaluated results.

Classes IPC  ?

• F22B 35/18 - Utilisation des machines à calculer pour la commande des chaudières à vapeur
• 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
• G06F 17/15 - Calcul de fonction de corrélation
• G06F 30/17 - Conception mécanique paramétrique ou variationnelle
• G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu

Abrégé

The present invention relates to a multistage fiber filtering apparatus capable of selectively filtering depending on turbidity of raw water, in which a first filtration mode where the raw water passes through a fiber ball medium, a second filtration mode where the raw water passes through a fiber yarn medium, or a third filtration mode where the raw water passes through both of the fiber yarn medium and the fiber ball medium may be selectively operated.

Classes IPC  ?

• B01D 24/12 - Filtration vers le bas, la substance filtrante étant supportée par des surfaces perméables
• B01D 24/40 - Dispositifs d'alimentation ou d'évacuation d'alimentation
• B01D 24/48 - Filtres à substance filtrante non agglomérée, c.-à-d. à substance filtrante sans aucun liant entre les particules ou les fibres individuelles qui la composent combinés dans une même structure à des dispositifs de commande de la filtration
• B01D 29/56 - Filtres à éléments filtrants stationnaires pendant la filtration, p. ex. filtres à aspiration ou à pression, non couverts par les groupes Leurs éléments filtrants à plusieurs éléments filtrants caractérisés par leur agencement relatif montés en série
• B01D 29/60 - Filtres à éléments filtrants stationnaires pendant la filtration, p. ex. filtres à aspiration ou à pression, non couverts par les groupes Leurs éléments filtrants combinés dans une même structure à des dispositifs de commande de la filtration
• B01D 36/02 - Combinaisons de filtres de différentes sortes
• B01D 39/02 - Substance filtrante non agglomérée, p. ex. fibres
• B01D 39/04 - Substance organique, p. ex. cellulose, coton
• C02F 1/00 - Traitement de l'eau, des eaux résiduaires ou des eaux d'égout
• B01D 24/46 - Régénération de la substance filtrante dans le filtre
• B01D 29/58 - Filtres à éléments filtrants stationnaires pendant la filtration, p. ex. filtres à aspiration ou à pression, non couverts par les groupes Leurs éléments filtrants à plusieurs éléments filtrants caractérisés par leur agencement relatif montés en série disposés de façon concentrique ou coaxiale
• B01D 29/66 - Rinçage par chasse, p. ex. rafale ascendante d'air à contre-courant
• B01D 35/10 - Filtres à brosse

Abrégé

A hot-work mold steel includes 0.37 to 0.46 wt % of carbon (C), 0.25 to 0.5 wt % of silicon (Si), 0.36 to 0.56 wt % of manganese (Mn), 2.0 to 5.0 wt % of chromium (Cr), 1.4 to 2.6 wt % of molybdenum (Mo), 0.4 to 0.8 wt % of vanadium (V), 0.0007 to 0.004 wt % of boron (B), 0.002 to 0.022 wt % of aluminum (Al), 0.001 to 0.09 wt % of titanium (Ti) and the remainder of iron (Fe) and inevitable impurities. The hot-work mold steel exhibits superior thermal conductivity, hardenability, durability, and nitriding characteristics, and increased resistance to heat check and melt-out. A die-casting mold made of the steel has improved thermal conductivity regardless of mold size and a prolonged life cycle and can improve the surface quality in manufactured parts.

Classes IPC  ?

• C22C 38/32 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du bore
• C21D 6/00 - Traitement thermique des alliages ferreux
• C22C 38/54 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du bore
• C22C 38/52 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du cobalt
• C22C 38/50 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du titane ou du zirconium
• C22C 38/48 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du niobium ou du tantale
• C22C 38/46 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du vanadium
• C21D 1/18 - DurcissementTrempe avec ou sans revenu ultérieur
• C22C 38/06 - Alliages ferreux, p. ex. aciers alliés contenant de l'aluminium
• C22C 38/04 - Alliages ferreux, p. ex. aciers alliés contenant du manganèse
• C22C 38/02 - Alliages ferreux, p. ex. aciers alliés contenant du silicium
• C22C 38/44 - Alliages ferreux, p. ex. aciers alliés contenant du chrome et du nickel et du molybdène ou du tungstène

Abrégé

A system for controlling a boiler in a power plant to ensure combust under optimized conditions is provided. The system for controlling an operation of the boiler may include an optimizer configured to perform a combustion optimization operation for the boiler using a boiler combustion model to calculate an optimum control value for at least one control object of the boiler, and an output controller configured to receive the calculated optimum control value from the optimizer and control the control object according to the optimum control value.

Classes IPC  ?

• F22B 35/18 - Utilisation des machines à calculer pour la commande des chaudières à vapeur
• G05B 13/02 - Systèmes de commande adaptatifs, c.-à-d. systèmes se réglant eux-mêmes automatiquement pour obtenir un rendement optimal suivant un critère prédéterminé électriques
• 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
• F22B 37/38 - Détermination ou signalisation des conditions de marche dans les chaudières à vapeur, p. ex. enregistrant la direction ou le débit du courant d'eau dans les tubes

Abrégé

A method of manufacturing a wing element that is provided inside a gas turbine and through which a fluid passes and a method of manufacturing a blade are provided. The method of manufacturing the wing element includes preforming the wing element; disposing the wing element inside a mold; sequentially melting the wing element inside the mold along one direction using a heating device; and solidifying the melted wing element using a cooling device.

Classes IPC  ?

• B22D 27/04 - Action sur la température du métal, p. ex. par chauffage ou refroidissement du moule
• F01D 5/14 - Forme ou structure
• B28B 1/24 - Fabrication d'objets façonnés à partir du matériau par moulage par injection
• B33Y 80/00 - Produits obtenus par fabrication additive

Abrégé

A system for controlling a boiler apparatus in a power plant to combust under optimized conditions, and a method for optimizing combustion of the boiler apparatus using the same are provided. The boiler control system may include a task manager configured to collect information on a current operating state of a boiler and determine whether to perform a combustion optimization operation for the boiler, a pre-processor configured to preprocess data collected from the boiler and supply the pre-processed data, a modeler configured to create a boiler combustion model on the basis of the pre-processed data received from the pre-processor, an optimizer configured to receive the boiler combustion model from the modeler and perform the combustion optimization operation for the boiler using the boiler combustion model to calculate an optimum control value, wherein the pre-processed data is supplied to the modeler and the optimizer by the pre-processor, and an output controller configured to receive the optimum control value from the optimizer and control an operation of the boiler by reflecting the optimum control value to a boiler control logic.

Classes IPC  ?

• G06Q 10/04 - Prévision ou optimisation spécialement adaptées à des fins administratives ou de gestion, p. ex. programmation linéaire ou "problème d’optimisation des stocks"
• 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
• G05B 17/02 - Systèmes impliquant l'usage de modèles ou de simulateurs desdits systèmes électriques

Abrégé

A system for controlling a boiler apparatus in a power plant to combust under optimized conditions, and a method for optimizing combustion of the boiler apparatus using the same are provided. The boiler control system may include a modeler configured to create a boiler combustion model, an optimizer configured to receive the boiler combustion model from the modeler and perform the combustion optimization operation for the boiler using the boiler combustion model to calculate an optimum control value, and an output controller configured to receive the optimum control value from the optimizer, and control an operation of the boiler by reflecting the optimum control value to a boiler control logic.

Classes IPC  ?

• F22B 35/18 - Utilisation des machines à calculer pour la commande des chaudières à vapeur
• 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

Abrégé

A transition piece can include: an inner transition piece including an inlet and an outlet; an outer transition piece surrounding the inner transition piece with a flow passage; an outlet fin-pin flow guide disposed on the inner transition piece and located closer to the outlet than the inlet; a first bottom fin disposed at a bottom portion of the inner transition piece; and a second bottom fin disposed at the bottom portion of the inner transition piece, wherein the first bottom fin and the second bottom fin are arranged to be inclined to each other at an acute angle.

Classes IPC  ?

• F23R 3/26 - Commande du flux d'air
• F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage

Abrégé

A gas turbine includes a rotational body including a tie rod, a plurality of rotor disks arranged in an axial direction of the tie rod, and a plurality of blades radially arranged on an outer periphery of each rotor disk; a stationary body surrounding the rotational body and defining a working fluid flow space between opposing surfaces of the rotational and stationary bodies, the stationary body including a casing accommodating the rotational body and a plurality of vanes and diaphragms arranged on an inner surface of the casing, the vanes arranged alternately with the blades; and a compressor cleaner disposed at a plurality of compressor positions in the stationary body to spray a cleaning fluid into the working fluid flow space. The compressor positions are separated from each other in the axial direction, and the cleaning fluid is spayed at low pressure to enhance cleaning efficiency while protecting compressor components.

Classes IPC  ?

• F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
• B08B 9/093 - Nettoyage de récipients, p. ex. de réservoirs par la force de jets ou de pulvérisations
• 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
• B08B 3/02 - Nettoyage par la force de jets ou de pulvérisations
• F01D 25/28 - Dispositions pour le support ou le montage, p. ex. pour les carters de turbines

Abrégé

An apparatus and method for diagnosing analysis is provided. The apparatus includes an analytic layer to divide a peripheral space of a target component into a plurality of cells and to derive analytic data by performing a numerical analysis iteration according to computational fluid dynamics for the plurality of cells; a model layer to derive an analytic model that simulates the numerical analysis iteration; a predictive layer to derive predictive data by predicting a result of the numerical analysis iteration by using the analytic model; and a diagnostic layer to diagnose an abnormality condition of numerical analysis by comparing the analytic data and predictive data during the numerical analysis iteration performed by the analytic layer. The diagnostic layer includes an early alarm to generate early alarm information by sorting a cell satisfying an early alarm condition; and an abnormality diagnostic device to determine whether the numerical analysis iteration is abnormal.

Classes IPC  ?

• G06F 30/17 - Conception mécanique paramétrique ou variationnelle
• G06F 30/20 - Optimisation, vérification ou simulation de l’objet conçu
• G06F 111/10 - Modélisation numérique
• G06F 111/20 - CAO de configuration, p. ex. conception par assemblage ou positionnement de modules sélectionnés à partir de bibliothèques de modules préconçus

Abrégé

The present disclosure relates to a heat transfer tube having rare-earth oxide deposited on a surface thereof and a method for manufacturing the same, in which the rare-earth oxide can be deposited on the surface of the heat transfer tube to implement a superhydrophobic surface even under the high temperature environment and a plurality of assembled heat transfer tubes can be coated by coating a complex shape by depositing rare-earth oxide using a method for dipping a surface of the heat transfer tube and coating the same, thereby reducing or preventing the heat transfer tubes from being damaged during the assembling of the heat transfer tubes after the coating.

Classes IPC  ?

• F28F 19/02 - Prévention de la formation de dépôts ou de la corrosion, p. ex. en utilisant des filtres en utilisant des revêtements, p. ex. des revêtements vitreux ou émaillés
• C23C 22/00 - Traitement chimique de surface de matériaux métalliques par réaction de la surface avec un milieu réactif laissant des produits de réaction du matériau de la surface dans le revêtement, p. ex. revêtement par conversion, passivation des métaux
• F28F 13/18 - Dispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution par application de revêtements, p. ex. absorbant les radiations ou les réfléchissantDispositions pour modifier le transfert de chaleur, p. ex. accroissement, diminution par application d'un traitement de surface, p. ex. un polissage
• C01F 17/235 - Oxydes ou hydroxydes de cérium
• B05D 1/18 - Procédés pour appliquer des liquides ou d'autres matériaux fluides aux surfaces par immersion

Abrégé

A turbine blade in an industrial gas turbine includes a blade surface to be cooled by a film of cooling fluid, a plurality of cooling holes on the blade surface through which cooling fluid flows, each cooling hole including an inlet portion and an outlet portion, and a trench on the blade surface surrounding at least one outlet portion of the cooling hole, the trench extending in an axial direction and a radial direction from the outlet portion of the cooling hole, wherein the outlet portion of the cooling hole has a shape configured to generate a first stage diffusion of the cooling fluid and a wall of the trench is positioned in the axial direction from the outlet portion of the cooling hole to generate a second stage diffusion of the cooling fluid, thereby forming the film of cooling fluid.

Classes IPC  ?

• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F01D 5/14 - Forme ou structure
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• C23C 8/04 - Traitement de parties déterminées de la couche superficielle, p. ex. au moyen de masques

Abrégé

A combustor can include: a combustion chamber; a cap covering the combustion chamber; a first swirler inlet cup passing through the cap and having a first length and a first bell mouth; a second swirler inlet cup passing through the cap and having a second length and a second bell mouth; and a third swirler inlet cup passing through the cap and having a third length and a third bell mouth, wherein the first length is different from the third length, and wherein the first bell mouth is different from the third bell mouth. The first, second, and third swirler inlet cups can have different diameters, respectively.

Classes IPC  ?

• F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
• F23R 3/46 - Chambres de combustion comprenant une disposition annulaire des tubes à flamme à l'intérieur d'une enveloppe annulaire commune ou d'enveloppes individuelles
• F23R 3/28 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible
• F23R 3/34 - Alimentation de différentes zones de combustion
• F23R 3/12 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon
• F23D 23/00 - Assemblages de plusieurs brûleurs