The present disclosure is directed to systems and methods for data synchronization by an edge computing device. The method includes (1) receiving, by a feedback loop interface, a request for an update of a data set via a data-acquisition-and-computing (DAC) engine in an edge computing device, (2) transmitting, by the feedback loop interface, the request for the update of the data set to an actor node in a network; (3) receiving, by the feedback loop interface, an indication regarding the update of the data set from the actor node; and (4) transmitting, by the feedback loop interface, the indication regarding the update of the data set via the DAC engine in the recurring cycle. The DAC engine includes a synchronizer to control sequences in a recurring cycle of the network. The synchronizer communicates with a configuration manager or receives configuration information from network nodes for managing the data set.
An integrated compressor comprises an electric motor that is prone to windage losses, radial loads, and recirculation flows. According to a first feature, partial grooves or riblets may be formed on the surface of a motor stator that defines the radially outward boundary of the air gap between the motor stator and the motor rotor. These partial grooves or riblets may maintain low to moderate windage losses, while reducing radial loads in the motor. According to a second feature, a support structure may be designed with a nose portion that is configured to disrupt or otherwise reduce recirculation flows within the end-winding cavity housing the end-winding of the motor. According to a third feature, the spiral orientation of the topcoil of the end-winding may be aligned with the rotation direction of the motor rotor to reduce recirculation flows within the end-winding cavity.
H02K 1/20 - Parties fixes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
H02K 3/46 - Fixation des enroulements sur la structure statorique ou rotorique
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
3.
COOLING OF STATOR AND WINDINGS OF ELECTRIC MOTOR IN INTEGRATED COMPRESSOR
An integrated compressor comprises an electric motor (130) that is prone to high temperatures. In a first cooling feature, axial and/or radial cooling channels (250, 260, 270) are provided through the stator (132) of the motor (130) to supply coolant to portions of the stator (132) that are prone to high temperatures. In a second cooling feature, jets (290, 430, 612) are used to spray coolant towards the end-windings (230) of the motor (130), to thereby cool the end-windings (230).
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
H02K 9/00 - Dispositions de refroidissement ou de ventilation
Even if the fuel pressure to a torch for igniting an air-fuel mixture in a gas turbine engine is set to an ideal value, the actual fuel pressure supplied to the torch may differ due to modifications, drift, changes in ambient temperature or pressure, fuel composition, and/or the like. This may result in failure of the gas turbine engine to ignite. Accordingly, embodiments introduce a torch active pressure control (TAPC) system (260) into the flow path of fuel to the torch (400). The TAPC system (260) is controlled to modulate fuel pressure of the fuel supplied to the torch (400), according to a modulation profile. The modulation profile may traverse a range of fuel pressures in sinusoidal, V-shaped, stepped, or other-shaped cycle(s), to increase the probability that the ideal fuel pressure, and therefore, flame height, is achieved, thereby increasing the likelihood of a successful lightoff.
A system (100) includes a compressor (200). The compressor (200) has a center body (202) and an end cap (212, 213) coupled to the center body (202) at a connection interface (214, 215). The system (100) also includes a sealing system (216). The sealing system (216) includes an annular duct (218, 219) circumferentially extending along a connection interface (214, 215) between the center body (202) and the end cap (212, 213). The sealing system (216) also includes a conduit (220, 221) coupled to the annular duct (218, 219). The system (100) further includes a vacuum source (222) in fluid communication with the annular duct (218, 219) via the conduit (220, 221). In an operational state of the vacuum source (222), the vacuum source (222) is configured to generate a vacuum in the annular duct (218, 219) to direct gases leaking through the connection interface (214, 215) in the annular duct (218, 219).
A system includes a compressor. The compressor has a center body and an end cap coupled to the center body at a connection interface. The system also includes a sealing system. The sealing system includes an annular duct circumferentially extending along a connection interface between the center body and the end cap. The sealing system also includes a conduit coupled to the annular duct. The system further includes a vacuum source in fluid communication with the annular duct via the conduit. In an operational state of the vacuum source, the vacuum source is configured to generate a vacuum in the annular duct to direct gases leaking through the connection interface in the annular duct.
A recirculation system for a gas turbine engine includes a mixing chamber including an inlet end that receives exhaust gases containing unburnt fuel and an outlet end, and at least one recirculation conduit including an inlet opening in fluid communication with the mixing chamber proximate to the outlet end and an outlet opening in fluid communication with the mixing chamber proximate to the inlet end. The recirculation system further includes a fan. The fan is operable to receive at least one of a stream of substantially fuel-free exhaust gases present and a stream of fresh air within the at least one recirculation conduit and direct at least one of a portion of the stream of substantially fuel-free exhaust gases and a portion of the stream of fresh air into the mixing chamber to reduce an amount of unburnt fuel in the exhaust gases.
F02C 3/34 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail avec recyclage d'une partie du fluide de travail, c.-à-d. cycles semi-fermés comportant des produits de combustion dans la partie fermée du cycle
F01N 3/00 - Silencieux ou dispositifs d'échappement comportant des moyens pour purifier, rendre inoffensifs ou traiter les gaz d'échappement
A recirculation system (206, 306) for a gas turbine engine (100) includes a mixing chamber (208) including an inlet end (210) that receives exhaust gases (30) containing unburnt fuel and an outlet end (214), and at least one recirculation conduit (220) including an inlet opening (222) in fluid communication with the mixing chamber (208) proximate to the outlet end (214) and an outlet opening (226) in fluid communication with the mixing chamber (208) proximate to the inlet end (210). The recirculation system (206, 306) further includes a fan (232). The fan (232) is operable to receive at least one of a stream of substantially fuel-free exhaust gases (40) present and a stream of fresh air (60) within the at least one recirculation conduit (220) and direct at least one of a portion (50) of the stream of substantially fuel-free exhaust gases (40) and a portion (70) of the stream of fresh air (60) into the mixing chamber (208) to reduce an amount of unburnt fuel in the exhaust gases (30).
The unexpected failure of a turbomachine (120) can be costly and dangerous. Processes may collect data from a turbomachine (120), calculate durations of machine events from the collected data, and apply a model to those machine-event durations to predict future machine-event durations and/or detect trends in the machine-event durations. This predictive output (350) may be utilized to inform downstream functions regarding the health of the turbomachine (120). For example, a downstream function (360) may utilize the predictive output (350) to detect degradation or a potential future failure in the turbomachine (120) and trigger remedial functions, such as alerts and/or controls, to prevent or mitigate the degradation or failure of the turbomachine (120).
Traditionally, during ignition of a gas turbine engine, the fuel control valves are controlled to be nearly closed, in order to provide the small amount of fuel that is necessary to ignite the gas turbine engine. The error that is inherent in providing fuel flow through small openings results in a higher likelihood of start-up failures. Accordingly, a lightoff fuel pressure reduction system is disclosed that uses a pressure reducing regulator on a bypass flow path to temporarily reduce the pressure of fuel supplied to the fuel control valves. In this case, the fuel control valves may be maintained in a more open position during the ignition phase, which reduces the likelihood of ignition failures.
Traditionally, during ignition of a gas turbine engine, the fuel control valves are controlled to be nearly closed, in order to provide the small amount of fuel that is necessary to ignite the gas turbine engine. The error that is inherent in providing fuel flow through small openings results in a higher likelihood of start-up failures. Accordingly, a lightoff fuel pressure reduction system (200) is disclosed that uses a pressure reducing regulator (220) on a bypass flow path (225) to temporarily reduce the pressure of fuel supplied to the fuel control valves (250). In this case, the fuel control valves (250) may be maintained in a more open position during the ignition phase, which reduces the likelihood of ignition failures.
An integrated compressor comprises an electric motor that is prone to high temperatures. In a first cooling feature, axial and/or radial cooling channels are provided through the stator of the motor to supply coolant to portions of the stator that are prone to high temperatures. In a second cooling feature, jets are used to spray coolant towards the end-windings of the motor, to thereby cool the end-windings.
Traditionally, integrated motor compressors utilize a radial penetrator that is connected to the motor stator via terminals and wires. This radial connection requires the motor stator to be installed within the compressor housing prior to the connection. In addition, the wires are subject to failure from rapid gas decompression. Accordingly, an axial penetrator is disclosed to provide a conductive path, through the housing, parallel to the longitudinal axis of an integrated motor machine (e.g., integrated motor compressor). This enables the connection to be performed prior to installation of the motor stator within the housing. This also enables the conductive path between the motor windings and axial penetrator to be formed, as a single integrated path, using the same conductive and insulative materials. In turn, this ensures that the entire conductive path behaves the same during decompression, reduces costs, simplifies the installation process, and increases the robustness of the connection.
An integrated compressor comprises an electric motor that is prone to windage losses, radial loads, and recirculation flows. According to a first feature, partial grooves or riblets may be formed on the surface of a motor stator that defines the radially outward boundary of the air gap between the motor stator and the motor rotor. These partial grooves or riblets may maintain low to moderate windage losses, while reducing radial loads in the motor. According to a second feature, a support structure may be designed with a nose portion that is configured to disrupt or otherwise reduce recirculation flows within the end-winding cavity housing the end-winding of the motor. According to a third feature, the spiral orientation of the top coil of the end-winding may be aligned with the rotation direction of the motor rotor to reduce recirculation flows within the end-winding cavity.
In a traditional bearing cap, the temperature of the oil-wetted surface that defines the oil sump may experience high temperatures, which can result in oil degradation, oil varnish, and coking. Accordingly, a bearing cap is disclosed that reduces the temperatures experienced by the oil-wetted surface. In particular, the bearing cap may comprise one or more air insulation cavities, between the surface that is exposed to heated air and the oil-wetted surface that defines the oil sump, to provide a thermal barrier between the two surfaces.
In a traditional bearing cap, the temperature of the oil-wetted surface that defines the oil sump may experience high temperatures, which can result in oil degradation, oil varnish, and coking. Accordingly, a bearing cap (300) is disclosed that reduces the temperatures experienced by the oil-wetted surface (420). In particular, the bearing cap (300) may comprise one or more air insulation cavities (430), between the surface (410) that is exposed to heated air and the oil-wetted surface (420) that defines the oil sump (425), to provide a thermal barrier between the two surfaces.
Even if the fuel pressure to a torch for igniting an air-fuel mixture in a gas turbine engine is set to an ideal value, the actual fuel pressure supplied to the torch may differ due to modifications, drift, changes in ambient temperature or pressure, fuel composition, and/or the like. This may result in failure of the gas turbine engine to ignite. Accordingly, disclosed embodiments introduce a torch active pressure control (TAPC) system into the flow path of fuel to the torch. The TAPC system is controlled to modulate the fuel pressure of the fuel supplied to the torch, according to a modulation profile. The modulation profile may traverse a range of fuel pressures in each of one or a plurality of sinusoidal, V-shaped, stepped, or other-shaped cycles, to increase the probability that the ideal fuel pressure, and therefore, flame height, is achieved, thereby increasing the likelihood of a successful lightoff.
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 7/232 - Soupapes pour combustibleSystèmes ou soupapes de drainage
System (100, 300) for injecting dry gases into one or more gas compressors (200) includes a nitrogen gas supply system (102) to generate a stream of conditioned nitrogen gas (Nl), a process gas supply system (118) to generate a stream of conditioned process gas (Pl), and a compression device (134). The compression device (134) is configured to receive and pressurize the stream of conditioned nitrogen gas (Nl) or the stream of conditioned process gas (Pl), and direct a pressurized stream of conditioned nitrogen gas (N3) or a pressurized stream of conditioned process gas (P3) towards the one or more gas compressors (200). The system (100, 300) includes a first valve (136) that provides selective fluid communication between the nitrogen gas supply system (102) and the compression device (134) to direct the stream of conditioned nitrogen gas (Nl) towards the compression device (134) or selective fluid communication between the process gas supply system (118) and the compression device (134) to direct the stream of conditioned process gas (Pl) towards the compression device (134).
A system for injecting dry gases into one or more gas compressors includes a nitrogen gas supply system to generate a stream of conditioned nitrogen gas, a process gas supply system to generate a stream of conditioned process gas, and a compression device. The compression device is configured to receive and pressurize the stream of conditioned nitrogen gas or the stream of conditioned process gas, and direct a pressurized stream of conditioned nitrogen gas or a pressurized stream of conditioned process gas towards the one or more gas compressors. The system includes a first valve that provides selective fluid communication between the nitrogen gas supply system and the compression device to direct the stream of conditioned nitrogen gas towards the compression device or selective fluid communication between the process gas supply system and the compression device to direct the stream of conditioned process gas towards the compression device.
No known single-stage dry low emissions fuel injectors are capable of effectively operating over all ranges of hydrogen concentrations in hydrogen/natural gas fuel mixtures. Accordingly, a fuel injector is disclosed that is capable of operating in both a premix mode for fuel mixtures with lower hydrogen concentrations and a micromix mode for fuel mixtures with higher hydrogen concentrations. The fuel injector may comprise premix jets (410) near an inlet (452, 812, 822, 832) of the fuel injector, optionally within one or more swirlers (630, 810, 820), and micromix jets (420) near the outlet (456) of the fuel injector. In the premix mode, fuel with lower hydrogen concentrations is provided to the premix jets (410), whereas in the micromix mode, fuel with higher hydrogen concentrations is provided to the micromix jets (420).
A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. This can make it difficult to remove the tip shroud during disassembly of the turbine. In an embodiment, to facilitate consistent and reliable removal of the tip shroud during each disassembly of the turbine, one or more, including potentially all, of the tip shoes of a tip shroud may be provided with one or more radially protruding puller hooks. Each puller hook enables an axial force to be transferred by one or more tools to an axially inner surface of the puller hook, to thereby produce axial movement of the tip shoe out of the tip shroud.
Conventionally, trim balancing for a power turbine (140) has been performed at the equipment coupling. Disclosed embodiments comprise a hub (200) that is installed on the shaft (102). This hub (200) enables trim balancing to be performed on the shaft (102) coupling, closer to the rotor, which is more effective. The disclosed hub (200) also enables unbalance corrections to remain with the power turbine (140) after uncoupling. In addition, the use of the hub (200) improves efficiency and eliminates safety risks faced by personnel in the field during coupling of the power turbine (140) to the equipment.
F01D 5/02 - Organes de support des aubes, p. ex. rotors
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 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
23.
Power turbine shaft with hub assembly for gas turbine engine
Conventionally, trim balancing for a power turbine has been performed at the equipment coupling. Disclosed embodiments comprise a hub that is installed on the shaft. This hub enables trim balancing to be performed on the shaft coupling, closer to the rotor, which is more effective. The disclosed hub also enables unbalance corrections to remain with the power turbine after uncoupling. In addition, the use of the hub improves efficiency and eliminates safety risks faced by personnel in the field during coupling of the power turbine to the equipment.
F01D 5/02 - Organes de support des aubes, p. ex. rotors
F01D 17/06 - Aménagement des éléments sensibles sensibles à la vitesse
F16D 1/08 - Accouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour montage d'un organe sur un arbre ou à l'extrémité d'un arbre avec moyeu de serrageAccouplements pour établir une liaison rigide entre deux arbres coaxiaux ou d'autres éléments mobiles d'une machine pour montage d'un organe sur un arbre ou à l'extrémité d'un arbre avec moyeu et clavette longitudinale
24.
System for coupling ducts in gas turbine engines for power generation applications
A system for coupling a first duct to a second duct configured for a gas flow with a gas turbine engine is disclosed. The system includes a first closed member and a second closed member. The first closed member is fixedly coupled to the first duct and defines an engagement surface. The second closed member is fixedly coupled to the second duct and defines a mating surface complementary to the engagement surface. The coupling of the first duct to the second duct includes one of the engagement surface and the mating surface complementarily receiving the other of the engagement surface and the mating surface such that a labyrinth interface is defined therebetween. Also, the first duct is sealed with respect to the second duct at the labyrinth interface such that a seepage of some of the gas flow through the labyrinth interface is restricted.
Fuel injection for hydrogen-gas fuels poses risks with regard to emissions, flashback, and flame-holding events in a gas turbine engine. Accordingly, embodiments of a fuel injection system (134) are disclosed that uniformly mix gas and fuel, while stabilizing a flame and facilitating maintenance. The fuel injection system (134) may comprise a plurality of micromixer panels (240), mounted in windows (340) of a frame (230) that are arranged circumferentially around a longitudinal axis (L) of the gas turbine engine (100). Each micromixer panel (240) may comprise a plurality of axial channels (612), arranged around a central pilot body (270) that is fixed in a grommet (250). Two or more internal fuel feeds (712, 714) may supply fuel to distinct subsets of fuel jets (544) within the outlets (542) of the axial channels (612), such that the fuel injection system (134) may be operated in multiple stages.
Fuel injection for hydrogen-gas fuels poses risks with regard to emissions, flashback, and flame-holding events in a gas turbine engine. Accordingly, embodiments of a fuel injection system are disclosed that uniformly mix gas and fuel, while stabilizing a flame and facilitating maintenance. The fuel injection system may comprise a plurality of micromixer panels, mounted in windows of a frame that are arranged circumferentially around a longitudinal axis of the gas turbine engine. Each micromixer panel may comprise a plurality of axial channels, arranged around a central pilot body that is fixed in a grommet. Two or more internal fuel feeds may supply fuel to distinct subsets of fuel jets within the outlets of the axial channels, such that the fuel injection system may be operated in multiple stages.
Large industrial machines, such as gas turbine engines (100), typically have a control room or control panel, acting as a single local control point from which the machine is operated. However, this prevents technicians from controlling the machine at locations that are distant from the control point, as may be necessary during servicing or operation. Accordingly, a system is disclosed that enables a wireless human-machine interface (250W) to be used to control the machine, in addition to a local human-machine interface (250L). The system may ensure that only a single human-machine interface is able to control the machine at any given time, as well as prevent unauthorized devices from controlling the machine.
G05B 19/042 - Commande à programme autre que la commande numérique, c.-à-d. dans des automatismes à séquence ou dans des automates à logique utilisant des processeurs numériques
G05B 19/409 - Commande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique caractérisée par l'utilisation de l'entrée manuelle des données [MDI] ou par l'utilisation d'un panneau de commande, p. ex. commande de fonctions avec le panneauCommande numérique [CN], c.-à-d. machines fonctionnant automatiquement, en particulier machines-outils, p. ex. dans un milieu de fabrication industriel, afin d'effectuer un positionnement, un mouvement ou des actions coordonnées au moyen de données d'un programme sous forme numérique caractérisée par les détails du panneau de commande ou par la fixation de paramètres
28.
DISTRIBUTED INDUSTRIAL CONTROL INVOLVING WIRELESS HUMAN-MACHINE INTERFACE DEVICES
Large industrial machines, such as gas turbine engines, typically have a control room or control panel, acting as a single local control point from which the machine is operated. However, this prevents technicians from controlling the machine at locations that are distant from the control point, as may be necessary during servicing or operation. Accordingly, a system is disclosed that enables a wireless human-machine interface to be used to control the machine, in addition to a local human-machine interface. The system may ensure that only a single human-machine interface is able to control the machine at any given time, as well as prevent unauthorized devices from controlling the machine.
G05B 19/05 - Automates à logique programmables, p. ex. simulant les interconnexions logiques de signaux d'après des diagrammes en échelle ou des organigrammes
A scribing device for a component includes a holder and a first scribing assembly coupled to the holder. The first scribing assembly includes a first scribing tool including a first scribing tip configured to define a first annular scribe mark on a circumferential surface of the component, and a first biasing member configured to bias the first scribing tool towards the circumferential surface of the component. The scribing device further includes a second scribing assembly. The second scribing assembly includes a second scribing tool including a second scribing tip configured to define a second annular scribe mark on the circumferential surface of the component, and a second biasing member configured to bias the second scribing tool towards the circumferential surface of the component.
In a fuel injector, the temperature differential between a distributor plate, through which relatively cool fuel passes, and the manifold to which the distributor plate is bonded causes stresses and strains that can reduce the durability and longevity of the fuel injector. In disclosed embodiments, the distributor plate is bonded to an outer arm and inner arm. These arms act as levers to take up the stresses and strains caused by the temperature differential, thereby increasing the durability and longevity of the fuel injector.
No known single-stage dry low emissions fuel injectors are capable of effectively operating over all ranges of hydrogen concentrations in hydrogen/natural gas fuel mixtures. Accordingly, a fuel injector is disclosed that is capable of operating in both a premix mode for fuel mixtures with lower hydrogen concentrations and a micromix mode for fuel mixtures with higher hydrogen concentrations. The fuel injector may comprise premix jets near an inlet of the fuel injector, optionally within one or more swirlers, and micromix jets near the outlet of the fuel injector. In the premix mode, fuel with lower hydrogen concentrations is provided to the premix jets, whereas in the micromix mode, fuel with higher hydrogen concentrations is provided to the micromix jets.
Tip shrouds or other shrouds with multi-slope geometries are generally implemented using segments, since performing the necessary cut for an alternative split-ring design is difficult given conventional cutting processes. However, a segmented design generally results in more leakage, relative to a split-ring design. Accordingly, a split-ring multi-slope design is disclosed that can be more easily manufactured. In particular, a continuous ring may be cut along a linear path to produce a split ring, and then the ends of the split ring may be machined to form complementary shiplap portions. The split ring may then be compressed for installation by overlapping the shiplap portions, to form a seal against leakage through the shroud.
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
F02C 7/28 - Agencement des dispositifs d'étanchéité
In a closed system that recirculates exhaust gas from a gas turbine engine (100), recirculated exhaust gas (255) should be mixed into inlet gas (215) in a manner that produces a uniform distribution within the mixed gas (305), while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box (300) is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box comprises mixer(s) (400) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer comprises surface apertures (422, 432) and interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.
F02C 3/34 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail avec recyclage d'une partie du fluide de travail, c.-à-d. cycles semi-fermés comportant des produits de combustion dans la partie fermée du cycle
F02M 26/19 - Moyens pour améliorer le mélange de l’air et des gaz d’échappement recyclés, p. ex. venturis ou ouvertures multiples du système d’admission
34.
SYSTEM AND METHOD FOR CONNECTING A CUSTOMER PREMISES EQUIPMENT
A system and methods for automatically and securely connecting a customer premises equipment (CPE) to a headquarters production environment are disclosed. The method includes automatically transmitting handshake messages from the CPE to a headquarters pre-enrollment server; establishing a generic VPN tunnel between the CPE and an isolated server; obtaining one or more parameters from the CPE and establish the pre-enrollment tunnel; using the one or more parameters, verifying the CPE; and establishing a production tunnel between the CPE and the production environment.
H04L 12/28 - Réseaux de données à commutation caractérisés par la configuration des liaisons, p. ex. réseaux locaux [LAN Local Area Networks] ou réseaux étendus [WAN Wide Area Networks]
H04L 61/2503 - Traduction d'adresses de protocole Internet [IP]
35.
SYSTEM AND METHOD FOR CONNECTING A CUSTOMER PREMISES EQUIPMENT
A system and methods for automatically and securely connecting a customer premises equipment (CPE) (102) to a headquarters production environment (110) are disclosed. The method includes automatically transmitting handshake messages from the CPE (102) to a headquarters pre-enrollment server (106); establishing a generic VPN tunnel (113) between the CPE (102) and an isolated server; obtaining one or more parameters from the CPE and establish the pre-enrollment tunnel (114); using the one or more parameters, verifying the CPE (102); and establishing a production tunnel (113) between the CPE (102) and the production environment (110).
A pneumatically variable nozzle vane is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more cavities in fluid communication with one or more outlets to eject a gas from the nozzle vane into a flow path of working fluid through the nozzle. Each cavity may be shaped to match an internal pressure gradient to the external pressure gradient of the nozzle vane. The gas may be ejected as a curtain, substantially perpendicular to the flow path through the nozzle, to thereby manipulate the flow of a working fluid through the nozzle in a similar manner as a mechanically variable nozzle vane. In an embodiment, each nozzle vane may have two cavities supplying outlets on both the pressure-side and suction-side of the nozzle vane.
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
A pneumatically variable nozzle vane (200) is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more cavities (220) in fluid communication with one or more outlets (230) to eject a gas from the nozzle vane into a flow path of working fluid through the nozzle. Each cavity may be shaped to match an internal pressure gradient to the external pressure gradient of the nozzle vane. The gas may be ejected as a curtain, substantially perpendicular to the flow path through the nozzle, to thereby manipulate the flow of a working fluid through the nozzle in a similar manner as a mechanically variable nozzle vane. In an embodiment, each nozzle vane may have two cavities supplying outlets on both the pressure-side and suction-side of the nozzle vane.
F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
In a closed system that recirculates exhaust gas from a gas turbine engine, recirculated exhaust gas should be mixed into inlet gas in a manner that produces a uniform distribution within the mixed gas, while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box may comprise mixer(s) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer may comprise surface apertures and/or interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.
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 1/00 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de gaz chauds ou de gaz sous pression non chauffés, comme fluide de travail
40.
MACHINE EVENT DURATION ANALYTICS AND AGGREGATION FOR MACHINE HEALTH MEASUREMENT AND VISUALIZATION
The unexpected failure of a turbomachine can be costly and dangerous. Processes may collect data from a turbomachine, calculate durations of machine events from the collected data, and apply a model to those machine-event durations to predict future machine-event durations and/or detect trends in the machine-event durations. This predictive output may be utilized to inform downstream functions regarding the health of the turbomachine. For example, a downstream function may utilize the predictive output to detect degradation or a potential future failure in the turbomachine and trigger remedial functions, such as alerts and/or controls, to prevent or mitigate the degradation or failure of the turbomachine.
It is important to accurately measure the emissions of a turbomachine for a variety of reasons. However, continuous emission monitoring systems (CEMS) can be expensive to install and maintain. Accordingly, a digital platform is disclosed that hosts physics-based and/or statistical models that can be tailored to specific turbomachines and calibrated over the life of the turbomachine. The model for a turbomachine can be applied to data collected from the turbomachine to predict the emissions of the turbomachine. This enables monitoring of emissions, remotely and without the need of a CEMS. In addition, the platform may utilize the predicted emissions for alerts, compliance monitoring, health monitoring, control of the turbomachine, reporting, and/or the like.
F23N 5/18 - Systèmes de commande de la combustion utilisant des détecteurs sensibles au débit de l'écoulement de l'air ou du combustible
F23N 5/02 - Systèmes de commande de la combustion utilisant des dispositifs sensibles aux variations thermiques ou à la dilatation thermique d'un agent
It is important to accurately measure the emissions of a turbomachine for a variety of reasons. However, continuous emission monitoring systems (CEMS) can be expensive to install and maintain. Accordingly, a digital platform (110) is disclosed that hosts physics-based and/or statistical models that can be tailored to specific turbomachines and calibrated over the life of the turbomachine. The model for a turbomachine (120) can be applied to data collected from the turbomachine (120) to predict the emissions (350) of the turbomachine (120). This enables monitoring of emissions, remotely and without the need of a CEMS. In addition, the platform (110) may utilize the predicted emissions (350) for alerts, compliance monitoring, health monitoring, control of the turbomachine (120), reporting, and/or the like.
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
F02D 45/00 - Commande électrique non prévue dans les groupes
An owner or operator of a turbomachine, such as a gas turbine engine (100), may wish to extend a service interval for the turbomachine. A framework is disclosed that enables automation of various aspects of the review process, including the generation of a risk assessment for the service interval extension. Data, including equipment data, may be aggregated from a plurality of different data silos. A physics-based model may be applied to the equipment data to calculate a remaining useful life of the equipment (222), which may then be used to generate the risk assessment. In addition, the framework may facilitate multiple levels of evaluation of the risk assessment to increase confidence in a final approval or denial of the service interval extension.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
G06Q 10/20 - Administration de la réparation ou de la maintenance des produits
44.
DIGITAL PLATFORM BASED MULTIFACETED RISK ASSESSMENT FOR EXTENSION OF TURBOMACHINERY SERVICE INTERVALS
An owner or operator of a turbomachine, such as a gas turbine engine, may wish to extend a service interval for the turbomachine. A framework is disclosed that enables automation of various aspects of the review process, including the generation of a risk assessment for the service interval extension. Data, including equipment data, may be aggregated from a plurality of different data silos. A physics-based model may be applied to the equipment data to calculate a remaining useful life of the equipment, which may then be used to generate the risk assessment. In addition, the framework may facilitate multiple levels of evaluation of the risk assessment to increase confidence in a final approval or denial of the service interval extension.
Exhaust outlets (e.g., in a gas turbine engine) are generally made from sections of thin-walled materials (e.g., sheet metal) that are joined by flanges. Due to the length of the exhaust outlet and differing thermal expansion coefficients exhibited by the flanges and the thin-walled materials, these joints are subjected to high mechanical, as well as thermal, stresses. A long-arm flange is disclosed that decouples the mechanical stress from the thermal stress in the flange and distributes the stress, to thereby reduce the stress at the flange interface. Additionally, the long-arm flange can be easily adapted to the specific geometry of any exhaust outlet.
In the turbine of a gas turbine engine, disk cavities exist between rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be integrated into the platform of a stator assembly that is downstream from a rotor assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within a disk cavity that is aft to a rotor assembly to circulate the hot gas back out into the hot gas flow path.
In the turbine of a gas turbine engine, disk cavities exist between rotor and stator assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the rotor and stator assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be integrated into the platform of a stator assembly that is downstream from a rotor assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within a disk cavity that is aft to a rotor assembly to circulate the hot gas back out into the hot gas flow path.
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
F01D 11/08 - 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
Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer (300) is disclosed that utilizes an air nozzle (200), in combination with one or more fuel jets (422), to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.
Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer is disclosed that utilizes an air nozzle, in combination with one or more fuel jets, to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.
Known micromixers for fuel injection (e.g., in a gas turbine engine) experience early burning or have limited operability. Accordingly, a micromixer (300) is disclosed that utilizes an air nozzle (200), in combination with one or more fuel jets (422), to produce short flames that minimize the emission of nitrogen oxides, while providing additional benefits, such as mechanical robustness, aerodynamic efficiency, resistance to flame damage, suitability for additive manufacturing, wider operating ranges, operation with a variety of gaseous fuels, and/or amenability to control using conventional mechanisms.
A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. Accordingly, a tip shoe is disclosed that utilizes an internal cooling cavity to supply coolant throughout the interior of the tip shoe, as well as to the slash faces of the tip shoe. In addition, features are described that increase the surface area exposed to the coolant, while remaining suitable for additive manufacturing.
An exhaust system of a turbine typically includes an exhaust collector that turns the axial flow of exhaust, output by the turbine, radially outward, with the intent of diverting the flow up an exhaust stack. However, the width of the exhaust collector may be limited by packaging engineering, which can decrease the efficiency of the exhaust system. Accordingly, an exhaust collector is disclosed that utilizes non-cylindrical conical shapes in an exhaust diffuser to maximize volume and reduce velocity in the exhaust collector, to compensate for the decrease in efficiency caused by a reduced width of the exhaust collector.
Enclosures are used to attenuate noise produced by a high decibel producing device, such as a gas turbine engine or other rotating machinery. However, enclosures that achieve high Sound Transmission Class (STC) ratings are generally expensive and immobile, whereas inexpensive and mobile enclosures are generally incapable of achieving high STC ratings. Accordingly, a composite noise-attenuating panel system is disclosed that can achieve the high STC ratings associated with immobile, site-erected enclosures, using subpanels that are separated by an air gap and an internal filler (e.g., mineral wool), while maintaining the weight, form factor, and ease of use associated with lightweight, modular mobile enclosures.
E04B 2/00 - Murs, p. ex. cloisons, pour bâtimentsStructure des murs en ce qui concerne l'isolationAssemblages spécifiques pour les murs
E04C 2/292 - 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 composés de matériaux couverts par plusieurs des groupes , , ou de matériaux couverts par un de ces groupes avec un matériau non spécifié dans l'un de ces groupes au moins un des matériaux étant isolant composés de matériau isolant et de tôle
E04B 1/86 - Éléments absorbant le son en forme de dalles
B32B 5/18 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches contient un matériau sous forme de mousse ou essentiellement poreux
B32B 3/06 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords pour lier les couches ensembleCaractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords pour attacher le produit à quelque chose d'autre p. ex. à un support
B32B 19/00 - Produits stratifiés composés essentiellement de fibres ou particules minérales naturelles, p. ex. d'amiante, de mica
B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
B32B 3/08 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p. ex. au voisinage des bords caractérisés par des éléments ajoutés à des endroits déterminés
E04C 2/00 - Éléments de construction de relativement faible épaisseur pour la construction de parties de bâtiments, p. ex. matériaux en feuilles, dalles ou panneaux
Enclosures are used to attenuate noise produced by a high decibel producing device, such as a gas turbine engine or other rotating machinery. However, enclosures that achieve high Sound Transmission Class (STC) ratings are generally expensive and immobile, whereas inexpensive and mobile enclosures are generally incapable of achieving high STC ratings. Accordingly, a composite noise-attenuating panel system is disclosed that can achieve the high STC ratings associated with immobile, site-erected enclosures, using subpanels that are separated by an air gap and an internal filler (e.g., mineral wool), while maintaining the weight, form factor, and ease of use associated with lightweight, modular mobile enclosures.
In a gas turbine engine (100), coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case (132), the nozzle of the turbine (140), and the exhaust diffuser (150). Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces (330, 430) of a combustor flange (300) and diffuser flange (400). In addition, one or more contact sealing lands (342) may be used between the combustor flange (300) and diffuser flange (400) and one or more seals (354, 544) may be provided between various components of the interface to provide additional sealing.
In a gas turbine engine (100), coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case (132), the nozzle of the turbine (140), and the exhaust diffuser (150). Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces (330, 430) of a combustor flange (300) and diffuser flange (400). In addition, one or more contact sealing lands (342) may be used between the combustor flange (300) and diffuser flange (400) and one or more seals (354, 544) may be provided between various components of the interface to provide additional sealing.
In the turbine of a gas turbine engine, disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be mounted to the stator assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within the disk cavities to circulate the hot gas back out into the hot gas flow path.
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
F04D 29/42 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges
In a gas turbine engine, coolant (e.g., cooling air) is prone to leak out of the interface between the combustor case, the nozzle of the turbine, and the exhaust diffuser. Embodiments of an interface are disclosed that provide non-fretting sealing using an interference fit between radially facing surfaces of a combustor flange and diffuser flange. In addition, one or more contact sealing lands may be used between the combustor flange and diffuser flange and one or more seals may be provided between various components of the interface to provide additional sealing.
In the compressor of a gas turbine engine, variable guide vanes are adjusted by virtue of connections to an actuation ring that can be rotated within a fixed range of degrees. The connections between the guide vanes and the actuation ring can undergo significant torsional stress. Accordingly, an actuation system is disclosed for reducing the torsional stress experienced by the actuation connections.
F01D 9/02 - InjecteursLogement des injecteursAubes de statorTuyères de guidage
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F02C 9/22 - Commande du débit du fluide de travail par étranglementCommande du débit du fluide de travail par réglage des aubes par réglage des aubes de turbine
In the turbine of a gas turbine engine, disk cavities exist between stator and rotor assemblies. These disk cavities enable hot gas from the hot gas flow path to ingress between the stator and rotor assemblies with detrimental effects to the durability of the turbine. Thus, a flow discourager is disclosed that can be mounted to the stator assembly. The flow discourager comprises a continuous external surface that defines a recirculation zone within the disk cavities to circulate the hot gas back out into the hot gas flow path.
Industrial machines positioned along a gas transmission pipeline are controlled using setpoints. Operators of such pipelines would benefit from real-time data and recommendations to guide them in optimizing performance of the pipelines. Accordingly, a compression optimization system is disclosed that monitors and provides real-time data and notifications, recommends optimal control setpoints using a machine-learning or other artificial-intelligence model, which may self-learn to realistically represent the pipeline, and executes simulations for hypothetical scenarios. The compression optimization system enables efficient management of the gas transmission pipeline.
F17D 3/00 - Dispositions pour la surveillance ou la commande des opérations de fonctionnement
F17D 3/01 - Dispositions pour la surveillance ou la commande des opérations de fonctionnement pour commander, signaler ou surveiller le transfert d'un produit
During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
During operation of a gas turbine engine, the turbine blades are subjected to extremely high temperatures. While internal cooling passages may be provided within the turbine blades to cool the airfoils, the platforms of the turbine blades also experience high temperatures. In an embodiment, cooling holes are provided in each platform to cool distressed locations in the platform and improve the durability of each turbine blade.
A turbomachinery power generation station can be too large and heavy for transportation. Thus, embodiments are disclosed for separating a full power generation station into road-ready turbine and generator trailers, as well as realigning and recoupling the trailers for operation of the power generation station at a desired destination.
F02B 63/04 - Adaptations des moteurs pour entraîner des pompes, des outils tenus à la main ou des génératrices électriquesCombinaisons portatives de moteurs avec des dispositifs entraînés par des moteurs pour génératrices électriques
A turbomachinery power generation station can be too large and heavy for transportation. Thus, embodiments are disclosed for separating a full power generation station into road-ready turbine and generator trailers, as well as realigning and recoupling the trailers for operation of the power generation station at a desired destination.
B60P 3/00 - Véhicules adaptés pour transporter, porter ou comporter des charges ou des objets spéciaux
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02B 63/00 - Adaptations des moteurs pour entraîner des pompes, des outils tenus à la main ou des génératrices électriquesCombinaisons portatives de moteurs avec des dispositifs entraînés par des moteurs
F16D 1/10 - Accouplements à action rapide dans lesquels les pièces sont simplement présentées dans l'axe
A human-machine interface (HMI) (21), HMI system (2), turbomachinery package (1), and method of modifying a partition of an HMI (21) are disclosed. The HMI (21) comprises a first partition (211) storing a first operating system exclusively supporting a primary application; and a second partition (212) storing a second operating system exclusively supporting an imaging application. The HMI system (2) comprises the HMI (21); an external computing device (22); a serial cable (23); and, optionally, a network cable (24). The turbomachinery package (1) comprises a housing (11); a gas turbine (12); a plurality of sensors (14); a plurality of actuators (15); and an HMI (21). The imaging application may be an image deploy function, an image back-up function, and/or an image restore function, any of which can be executed without the use of removable media.
G06F 21/57 - Certification ou préservation de plates-formes informatiques fiables, p. ex. démarrages ou arrêts sécurisés, suivis de version, contrôles de logiciel système, mises à jour sécurisées ou évaluation de vulnérabilité
A compact heat exchanger (170) is disclosed for re-circulating bleed air from a combustor into an inlet (110) and/or exhaust (150) of a gas turbine engine (100). In an embodiment, the heat exchanger (170) may comprise a plurality of airfoils (174) with internal passages (600) that receive bleed air. The bleed air may be forced through outlets (612) in one or a plurality of concentric passages (600) from the internal passage (630) of each airfoil (174) to an internal cavity (530) of each airfoil, and out of micro-holes (512) within a trailing surface of the airfoil (174). This enables bleed air to be mixed with gas flowing through the airfoils (174), in close proximity to the compressor (120) or turbine (140) of the gas turbine engine (100), while providing acoustic noise suppression and low thermal mixing stratification.
F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
F02C 3/06 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur le compresseur ne comprenant que des étages axiaux
F02C 7/08 - Chauffage de l'air d'alimentation avant la combustion, p. ex. par les gaz d'échappement
F28C 3/02 - Autres appareils échangeurs de chaleur à contact direct les sources de potentiel calorifique étant toutes deux des gaz ou des vapeurs
F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail
F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion
F01D 25/10 - Chauffage, p. ex. réchauffage avant démarrage
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
Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
A fuel injector (134) is disclosed for reducing flashback. In an embodiment, the fuel injector (134) may comprise an injector head (240) with purge holes (457) on a radial wall (456) along a radial axis between an assembly axis of the fuel injector (134) and a plurality of vanes (460) arranged circumferentially around the assembly axis. The plurality of vanes (460) may comprise fuel outlets (464) connecting interior fuel passages (462) to spaces between the vanes (460). The introduction of these purge holes (457) near the bases of the vanes (460) and the configuration and positioning of the fuel outlets (464) in the vanes (460) and elsewhere in the fuel injector (134) may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage (248) of the fuel injector (134) to reduce flashback. Such fuel injectors (134) may be used in the combustor (130) of a gas turbine engine (100).
A fuel injector (134) is disclosed for reducing flashback. In an embodiment, the fuel injector (134) may comprise an injector head (240) with purge holes (457) on a radial wall (456) along a radial axis between an assembly axis of the fuel injector (134) and a plurality of vanes (460) arranged circumferentially around the assembly axis. The plurality of vanes (460) may comprise fuel outlets (464) connecting interior fuel passages (462) to spaces between the vanes (460). The introduction of these purge holes (457) near the bases of the vanes (460) and the configuration and positioning of the fuel outlets (464) in the vanes (460) and elsewhere in the fuel injector (134) may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage (248) of the fuel injector (134) to reduce flashback. Such fuel injectors (134) may be used in the combustor (130) of a gas turbine engine (100).
Gas turbine engines generally comprise a first-stage nozzle guide vane. Temperatures in a trailing-edge area of the suction-side wall of such vanes can exceed material and coating limits. While an insert can be used to form passages for cooling air to flow along the inner surfaces of the vane walls, design constraints prevent the insert from extending beyond a certain point into the trailing edge of the vane. Accordingly, a fin is disclosed for insertion downstream of the insert. By eliminating sudden expansion beyond the downstream end of the insert and maintaining the speed of the cooling air across the trailing-edge area of the suction-side wall, the fin improves the cooling coefficient for the trailing-edge area, so as to prevent or reduce excessive temperatures in the trailing-edge area.
F02C 7/12 - Refroidissement des ensembles fonctionnels
F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
73.
Flashback resistant premixed fuel injector for a gas turbine engine
A fuel injector is disclosed for reducing flashback. In an embodiment, the fuel injector may comprise an injector head with purge holes on a radial wall along a radial axis between an assembly axis of the fuel injector and a plurality of vanes arranged circumferentially around the assembly axis. In addition, the plurality of vanes may comprise fuel outlets connecting interior fuel passages to spaces between the vanes. The introduction of these purge holes near the bases of the vanes and the configuration and positioning of the fuel outlets in the vanes and elsewhere in the fuel injector may alter the stoichiometry (e.g., fuel-air ratio) within the premix passage of the fuel injector to reduce flashback. A plurality of such fuel injectors may be used in the combustor of a gas turbine engine.
A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed. A case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly.
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
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
F02C 7/28 - Agencement des dispositifs d'étanchéité
75.
Stator assembly for compressor mid-plane rotor balancing and sealing in gas turbine engine
A stator assembly, at a compressor mid-plane in a gas turbine engine, to be mounted around a rotor disc, enables access to the rotor disc (e.g., for trim balancing), without requiring disassembly of the stator assembly and/or a compressor case in which the stator assembly is housed, via a removable stator vane. The stator assembly may comprise vane apertures, aligned along a radial axis, that hold the removable stator vane when inserted into the stator assembly, and provide a radial pathway to the rotor disc, when the removable stator vane is removed from the stator assembly. In addition, a case access assembly may seal the removable stator vane in place within a compressor case when engaged, and provide access to the removable stator vane and radial pathway through the compressor case when disengaged. This enables trim balancing of a mid-plane compressor rotor assembly through the stator assembly and compressor case.
F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
F01D 5/02 - Organes de support des aubes, p. ex. rotors
F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
F01D 17/16 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage en obturant les injecteurs
F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
76.
Stiffness coupling and vibration damping for turbine blade shroud
During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.
F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
77.
Thermal bridge for connecting sections with a large temperature differential under high-pressure conditions
A thermal bridge forms a connection between a cold side and a hot side that is capable of withstanding a large temperature differential while high-pressure gas (e.g., air) flows between the two sides within an internal passageway. A cold-side region and hot-side region of the thermal bridge may each have a flange with a plurality of holes. The cold-side region may also include a conical fillet with counterbore recesses to provide access to each of the plurality of holes from a low radial position.
A contamination sensor for a gas turbine engine is disclosed herein. The contamination sensor is made of a selected composition of material and includes a base alloy, an alloy for improving oxide formation, and at least one element from the transition metal group. The composition of the contamination sensor can be adjusted to react with specific contaminants at specific temperature ranges.
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p. ex. à la pression
G01N 17/02 - Systèmes de mesure électro-chimique de l'action due aux intempéries, de la corrosion ou de la protection contre la corrosion
G01N 15/00 - Recherche de caractéristiques de particulesRecherche de la perméabilité, du volume des pores ou de l'aire superficielle effective de matériaux poreux
A contamination sensor for a gas turbine engine is disclosed herein. The contamination sensor is made of a selected composition of material and includes a base alloy, an alloy for improving oxide formation, and at least one element from the transition metal group. The composition of the contamination sensor can be adjusted to react with specific contaminants at specific temperature ranges.
G01N 17/00 - Recherche de la résistance des matériaux aux intempéries, à la corrosion ou à la lumière
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
An integrated gas compressor (100) is disclosed herein. The integrated gas compressor (100) includes an integrated motor (180) with a stator (188), centrifugal impellers (122, 123), and a shaft assembly (140) with a rotor (300) and a conical transition (200). The integrated motor (180) can produce an electromotive force that is imparted by the stator (188) to rotate the rotor (300) and components coupled to the rotor (300), such as the conical transition (200) and the centrifugal impellers (122, 123). At least one of the rotor (300) and conical transition (200) have a cavity (205, 305).
An integrated gas compressor (100) is disclosed herein. The integrated gas compressor (100) includes an integrated motor (180) with a stator (188), centrifugal impellers (122, 123), and a shaft assembly (140) with a rotor (300) and a conical transition (200). The integrated motor (180) can produce an electromotive force that is imparted by the stator (188) to rotate the rotor (300) and components coupled to the rotor (300), such as the conical transition (200) and the centrifugal impellers (122, 123). At least one of the rotor (300) and conical transition (200) have a cavity (205, 305).
An integrated gas compressor is disclosed herein. The integrated gas compressor includes an integrated motor with a stator, centrifugal impellers, and a shaft assembly with a rotor and conical transition. The integrated motor can produce an electromotive force that is imparted by the stator to rotate the rotor and components coupled to the rotor, such as the conical transition and the centrifugal impellers. At least one of the rotor and conical transition have a cavity.
A magnetic bearing assembly (131) for a rotary machine (100) may lose power and fail to support the rotating assembly (120) resulting in damage to magnetic bearing assembly (131) and/or other components. An auxiliary bearing assembly (132) may be used to support the rotating assembly (120) during such a failure. The auxiliary bearing assembly (132) is located radially inwards of the magnetic bearing assembly (131) and may reduce resonance and/or whirl of the rotating assembly (120) during failure of the magnetic bearing assembly (131).
A magnetic bearing assembly for a rotary machine may lose power and fail to support the rotating assembly resulting in damage to magnetic bearing assembly and/or other components. An auxiliary bearing assembly may be used to support the rotating assembly during such a failure. The auxiliary bearing assembly is located radially inwards of the magnetic bearing assembly and may reduce resonance and/or whirl of the rotating assembly during failure of the magnetic bearing assembly.
A fuel delivery system having a base, a fuel inlet configured to receive fuel from a secondary fuel supply, a fuel outlet configured to deliver fuel to a machine, a filter assembly and a coalescer configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to a machine, a boost pump assembly and a main pump assembly configured to pressurize the fuel.
B67D 7/76 - Aménagements des dispositifs de purification des liquides à transférer, p. ex. des filtres, des séparateurs à air ou eau
B67D 7/70 - Aménagements des pompes de plusieurs pompes associées en série ou en parallèle
B67D 7/04 - Appareils ou dispositifs pour transférer des liquides à partir de récipients ou de réservoirs de stockage en vrac vers des véhicules ou des récipients portables, p. ex. pour la vente au détail pour transférer des carburants, des lubrifiants ou leurs mélanges
-25- 19-1145CA01Abstract FUEL DELIVERY SYSTEM A fuel delivery system having a base, a fuel inlet configured toreceive fuel from a secondary fuel supply, a fuel outlet configured to deliver fuel to a machine, a filter assembly and a coalescer configured to filter the fuel, a fuel controller configured to regulate pressure of the fuel that will be delivered to a machine, a boost pump assembly and a main pump assembly configured topressurize the fuel.Date Recue/Date Received 2020-12-21
A pressure capture canister (700) for a turbine engine is disclosed. The pressure capture canister (700) includes a body (720), a cap (730), and a seal (740). The cap (730) and the seal (740) are positioned within the body (720) and are arranged to allow fluid communication from outside of the pressure capture canister (700) to within the body (720). The seal (740) is selected to melt or soften at a temperature threshold and to have a forging temperature that is lower than the forging temperature of the sleeve, the cap, and the body. The pressure within the pressure capture canister can be measured when having the canister removed after operation of the engine.
F01D 17/08 - Aménagement des éléments sensibles sensibles aux conditions de fonctionnement du fluide énergétique, p. ex. à la pression
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
G01L 11/00 - Mesure de la pression permanente, ou quasi permanente d'un fluide ou d'un matériau solide fluent par des moyens non prévus dans les groupes ou
H01H 37/76 - Élément de contact actionné par fusion d'une matière fusible, actionné par combustion d'une matière combustible ou par explosion d'une matière explosive
88.
METHOD AND CONTROL SYSTEM FOR CONTROLLING COMPRESSOR OUTPUT OF A GAS TURBINE ENGINE
A method and control system for controlling shaft speed for a gas turbine engine (100) is disclosed. The power output of a gas turbine engine (100) can vary and be below desired output levels due to operating conditions such as ambient temperature and elevation. These operating conditions can lead to lower rotational speed of a gas producer shaft (120) of the turbine engine (100) and lower operating temperatures within or proximate to a turbine (400) of the gas turbine engine (100) and lead to less power output. Additional fuel can be added to increase power to the gas producer shaft (120) and increase turbine temperature of the gas turbine engine (100). A power transfer device (700) can be used to remove and add power to the gas producer shaft (120) to increase and maintain gas producer shaft (120) speed and turbine (400) temperature at maximum levels and lead to higher power output.
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
A fuel injector (600) for a combustor of a gas turbine engine (100) is disclosed herein. The fuel injector (600) includes a fuel stem assembly (620) for receiving and distributing fuel and an injector head (630) receiving fuel from the fuel stem assembly (620). The injector head (630) includes an injector body (640), swirler vanes (660), a pilot assembly (700), passages (666, 667, 726, 745, 746), and fuel galleries (646, 647, 736). The pilot assembly (700) includes a pilot tube (746) and can include pilot struts (720). The swirler vanes (660) include passages (666) to transport the pilot fuel from the fuel stem assembly (620) to the pilot tube (746).
F23R 3/14 - Aménagements de l'entrée d'air pour l'air primaire créant un tourbillon au moyen d'ailettes de tourbillonnement
F23R 3/34 - Alimentation de différentes zones de combustion
F23R 3/38 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'alimentation en combustible comprenant des moyens d'injection de combustible rotatifs
A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.
A method and control system for controlling shaft speed for a gas turbine engine (100) is disclosed. The power output of a gas turbine engine (100) can vary and be below desired output levels due to operating conditions such as ambient temperature and elevation. These operating conditions can lead to lower rotational speed of a gas producer shaft (120) of the turbine engine (100) and lower operating temperatures within or proximate to a turbine (400) of the gas turbine engine (100) and lead to less power output. Additional fuel can be added to increase power to the gas producer shaft (120) and increase turbine temperature of the gas turbine engine (100). A power transfer device (700) can be used to remove and add power to the gas producer shaft (120) to increase and maintain gas producer shaft (120) speed and turbine (400) temperature at maximum levels and lead to higher power output.
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
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
A fuel injector (600) for a combustor of a gas turbine engine (100) is disclosed herein. The fuel injector (600) includes a fuel stem assembly (620) for receiving and distributing fuel and an injector head (630) receiving fuel from the fuel stem assembly (620). The injector head (630) includes an injector body (640), swirler vanes (660), a pilot assembly (700), passages (666, 667, 726, 745, 746), and fuel galleries (646, 647, 736). The pilot assembly (700) includes a pilot tube (746) and can include pilot struts (720). The swirler vanes (660) include passages (666) to transport the pilot fuel from the fuel stem assembly (620) to the pilot tube (746).
A method and control system for controlling compressor output for a gas turbine engine is disclosed. The power output of a gas turbine engine can vary and be below desired output levels due to operating conditions such as ambient temperature and elevation. These operating conditions can lead to lower output of the gas compressor of the turbine engine and lower operating temperatures within or proximate to a turbine of the gas turbine engine and lead to less power output. Additional fuel can be added to increase power to the gas producer shaft and increase turbine temperature of the gas turbine engine. A power transfer device can be used to remove or add power to the gas producer shaft to balance the gas producer mechanical limits and turbine thermal limits at maximum levels and lead to higher power output.
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 7/22 - Systèmes d'alimentation en combustible
A damped turbine blade assembly for a gas turbine engine is disclosed. The damped turbine blade assembly includes a damper positioned within a first small slot of a first turbine blade and a second large slot of the second turbine blade. A portion of the damper can slidably mate with the second large slot providing a radial and angular connection between the first turbine blade and second turbine blade while allowing movement in a direction tangent to a radial of a center axis of the gas turbine engine. The tangential movement is resisted by friction between the damper contacting the second large slot and provides friction damping against vibrations felt by the turbine blades during operation of the gas turbine engine. The damper can be shaped and/or pre-stressed to control the normal force component of the friction between the damper and the second large slot.
A damped turbine blade assembly (490, 491, 492, 493) for a gas turbine engine (100) is disclosed. The damped turbine blade assembly (490, 491, 492, 493) includes a damper (495, 496, 497, 498) positioned within a first small slot (481a) of a first turbine blade (440a) and a second large slot (486b, c,d) of the second turbine blade (440b). A portion of the damper (495, 496, 497, 498) can slidably mate with the second large slot (486b, c,d) providing a radial and angular connection between the first turbine blade (440a) and second turbine blade (440b) while allowing movement in a direction tangent to a radial of a center axis (95) of the gas turbine engine (100). The tangential movement is resisted by friction between the damper (495, 496, 497, 498) and provides friction damping against vibrations felt by the turbine blades during operation.
This disclosure provides a seal assembly (230, 330, 431, 530, 630, 730) to provide a generally smooth transition from a combustion chamber (390) to a turbine (400) within a gas turbine engine (100). A seal body (232, 332, 32, 532, 632, 732) extends from the combustion chamber (390) towards the turbine (400) and is positioned to seal against unwanted flows between the combustion chamber (390) and a compressed air chamber (395).
A control system (600) for a gas turbine engine (100) is disclosed. In embodiments, control system (600) includes a controller (610) and a high speed recorder (660). The controller (610) obtains a sensor value from a sensor (22) connected to the gas turbine engine (100) and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder (660) checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder (660) records values provided by the tag.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
A control system (600) for a gas turbine engine (100) is disclosed. In embodiments, control system (600) includes a controller (610) and a high speed recorder (660). The controller (610) obtains a sensor value from a sensor (22) connected to the gas turbine engine (100) and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder (660) checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder (660) records values provided by the tag.
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag.
G01M 15/14 - Test des moteurs à turbine à gaz ou des moteurs de propulsion par réaction
F01D 21/00 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs
This disclosure provides an air tube (350, 390) for a combustor (300) of a gas turbine engine (100). The air tube includes an inner tube (360) and an outer tube (380) to deliver discharged compressor air into a combustion chamber (320) of the combustor. The air tube can include struts (366) and fins (386) that can improve cooling performance of the air tube during operation of the gas turbine engine.
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