A system for aligning a rotating output shaft of a gas turbine with a rotating input shaft of a gearbox is disclosed. A turbine-side assembly has a first body configured to be attached to the casing of an engine and a rotatable alignment tool attached thereto. A gearbox-side assembly has a second body configured to be attached to the input power coupling of a gearbox and a rotatable second alignment tool attached thereto. The first alignment tool and second alignment tool are not physically coupled to one another, however, are configured to functionally communicate with each other to indicate when an output shaft and input shaft are aligned.
G01B 11/27 - Measuring arrangements characterised by the use of optical techniques for measuring angles or tapersMeasuring arrangements characterised by the use of optical techniques for testing the alignment of axes for testing the alignment of axes
F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
2.
ALIGNMENT TOOL FOR DRIVING AND DRIVEN SHAFTS IN GAS TURBINE SYSTEMS
A system for aligning a rotating output shaft 110 of a gas turbine 100 with a rotating input shaft 118 of a gearbox 102 is disclosed. A turbine-side assembly 202 has a first body configured to be attached to the casing 108 of the gas turbine 100 and a rotatable alignment tool 212 attached thereto. A gearbox-side assembly 204 has a second body configured to be attached to the input shaft 118 of the gearbox 102 and a rotatable second alignment tool 230 attached thereto. The first alignment tool 212 and second alignment tool 230 are not physically coupled to one another, however, are configured to functionally communicate with each other to indicate when an output shaft 110 and input shaft 118 are aligned.
A modular exhaust device includes a plurality of panels, wherein, when configured in either a first state or a second state, the plurality of panels is configured to direct exhaust in a predetermined direction; and, when configured in the other of the first state or the second state, the plurality of panels is configured to act as an exhaust cover. The modular exhaust device further includes a coupling mechanism associated with at least one panel of the plurality of panels. The coupling mechanism is configured to secure the at least one panel in at least one of a first position associated with the first state or a second position associated with the second state.
F01N 13/00 - Exhaust or silencing apparatus characterised by constructional features
F02B 63/04 - Adaptations of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for electric generators
A modular exhaust device includes a plurality of panels, wherein, when configured in either a first state or a second state, the plurality of panels is configured to direct exhaust in a predetermined direction; and, when configured in the other of the first state or the second state, the plurality of panels is configured to act as an exhaust cover. The modular exhaust device further includes a coupling mechanism associated with at least one panel of the plurality of panels. The coupling mechanism is configured to secure the at least one panel in at least one of a first position associated with the first state or a second position associated with the second state.
Systems including gas turbine engines generate exhaust, which may be expelled from the system in a manner that generates an undesirable sound pressure level. Accordingly, discussed herein is a solution to reduce the undesirable sound pressure level to a target sound pressure level at a predetermined distance from the exhaust-generating source. The sound-attenuating device used to reduce the sound pressure level comprises a first end having a first aperture, a second end having a second aperture, a sidewall extending between the first end and the second end, the sidewall having an inside surface and an outside surface. The sound-attenuating device further includes an interior transition region configured to reduce a sound pressure level, and a coupling region.
Systems including gas turbine engines generate exhaust, which may be expelled from the system in a manner that generates an undesirable sound pressure level. Accordingly, discussed herein is a solution to reduce the undesirable sound pressure level to a target sound pressure level at a predetermined distance from the exhaust-generating source. The sound-attenuating device used to reduce the sound pressure level comprises a first end having a first aperture, a second end having a second aperture, a sidewall extending between the first end and the second end, the sidewall having an inside surface and an outside surface. The sound-attenuating device further includes an interior transition region configured to reduce a sound pressure level, and a coupling region.
F01N 13/00 - Exhaust or silencing apparatus characterised by constructional features
F02B 63/04 - Adaptations of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for electric generators
An injector head (206) for a fuel injector (200) of an engine (100) includes an injector body (224) configured to be coupled with a fuel stem (212) of the fuel injector (200). The injector body (224) extends orthogonally relative to the fuel stem (212). The injector body (224) extends axially along a central axis (X1) and circumferentially about the central axis (X1). The injector head (206) also includes a central fuel assembly (232). The central fuel assembly (232) includes a tip portion (256) disposed proximal to a downstream end (222) of the injector body (224). The tip portion (256) includes an end portion (258), an intermediate portion (262), a plurality of support pins (266) extending between the end portion (258) and the intermediate portion (262), and a plurality of fins (272) extending radially-outward and from the intermediate portion (262) along the central axis (X1). The injector head (206) is formed by additive layer manufacturing. The plurality of support pins (266) and the plurality of fins (272) provide support for forming the injector head (206) by additive layer manufacturing.
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.
H04L 67/12 - Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
H04W 4/70 - Services for machine-to-machine communication [M2M] or machine type communication [MTC]
An injector head for a fuel injector of an engine includes an injector body configured to be coupled with a fuel stem of the fuel injector. The injector body extends orthogonally relative to the fuel stem. The injector body extends axially along a central axis and circumferentially about the central axis. The injector head also includes a central fuel assembly. The central fuel assembly includes a tip portion disposed proximal to a downstream end of the injector body. The tip portion includes an end portion, an intermediate portion, a plurality of support pins extending between the end portion and the intermediate portion, and a plurality of fins extending radially-outward and from the intermediate portion along the central axis. The injector head is formed by additive layer manufacturing. The plurality of support pins and the plurality of fins provide support for forming the injector head by additive layer manufacturing.
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.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
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 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F01N 3/00 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
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).
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.
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.
F04C 29/00 - Component parts, details, or accessories, of pumps or pumping installations specially adapted for elastic fluids, not provided for in groups
22 - Rope, netting, tents, awnings, sails and sacks; padding and stuffing materials
35 - Advertising and business services
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
17 - Rubber and plastic; packing and insulating materials
20 - Furniture and decorative products
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Cable ties, not of metal Providing management services related to one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing (may or may not be computer assisted), including fleet management, maintenance management, machinery management; purchasing and/or material procurement for others, purchasing for others; online retail services for sale of parts and components for machine and engines (other than land vehicles); online retail services for sale of parts, components, and equipment for gas turbine engines other than for land vehicles, generator sets, compressor sets, and pump sets; online retail services for sale of dowels of metal, pins of metal, washers of metal, bolts of metal, nuts of metal, rivets of metal, screws of metal, filters being parts of machines or engines, filter elements being parts of machines or engines, air filters and air filter elements being parts of machines and engines, fuel filters and fuel filter elements being parts of machines and engines, gas filters and gas filter elements being parts of machines and engines, oil filters and oil filter elements being parts of machines and engines, gaskets of metal being parts of machines and engines, gaskets for internal combustion engines, machine parts, namely, mechanical seals, bearings for use as parts of machines, bushings for use as parts of machines, spark plugs, spark plugs for internal combustion engines, kits for filters and filter elements being parts of machines and engines, kits for seals being parts of machines and engines, electric cords, electric wire and cable, electrical fuses, control system module for machines and engines (other than land vehicles), cords of rubber, gaskets made of rubber, sealing gaskets of metal, washers of rubber or vulcanized fiber, O-rings, oil seals, dowels, not of metal, pins, not of metal, washers, not of rubber or metal, bolts, not of metal, nuts, not of metal, rivets, not of metal, screws, not of metal, cable ties, not of metal Dowels of metal; pins of metal; washers of metal; bolts of metal; nuts of metal; rivets of metal; screws of metal Filters being parts of machines or engines; filter elements being parts of machines or engines; air filters and air filter elements being parts of machines and engines; fuel filters and fuel filter elements being parts of machines and engines; gas filters and gas filter elements being parts of machines and engines; oil filters and oil filter elements being parts of machines and engines; gaskets of metal being parts of machines and engines; gaskets for internal combustion engines; machine parts, namely, mechanical seals; bearings for use as parts of machines; bushings for use as parts of machines; spark plugs; spark plugs for internal combustion engines; kits for filters and filter elements being parts of machines and engines; kits for seals being parts of machines and engines Electric cords; electric wire and cable; electrical fuses, control system module for machines and engines (other than land vehicles) Cords of rubber; gaskets made of rubber; sealing gaskets of metal; washers of rubber or vulcanized fiber; O-rings; oil seals Dowels, not of metal; pins, not of metal; washers, not of rubber or metal; bolts, not of metal; nuts, not of metal; rivets, not of metal; screws, not of metal Providing maintenance information in the nature of diagnostic data, predictive maintenance recommendations, specifications, and alerts for one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing Rental services of gas turbine engines other than for land vehicles, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing Software as a service (SAAS) services featuring software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, providing on-line non-downloadable software for remote monitoring, diagnostics, optimization, physical inspection, alerts generation, and troubleshooting in the nature of diagnosing computer hardware and software problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; troubleshooting in the nature of diagnosing problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; providing remote monitoring, diagnostics, alerts, remote management of information technology systems of others, and data collection regarding the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, remote management of information technology computer hardware, software, and system access relating to the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; remote monitoring of the functioning and use of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; diagnostic services in the field of turbine equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; services related to the design of gas turbines and gas turbine packages, including proposal preparation, design and engineering, quality control; repair, service and maintenance of computer software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repair, service and maintenance of computer hardware for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; rental services of computer hardware and software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
17 - Rubber and plastic; packing and insulating materials
20 - Furniture and decorative products
22 - Rope, netting, tents, awnings, sails and sacks; padding and stuffing materials
35 - Advertising and business services
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Dowels of metal; pins of metal; washers of metal; bolts of metal; nuts of metal; rivets of metal; screws of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Gas turbine engines other than for land vehicles; internal combustion engines other than for land vehicles; parts, components, and equipment for gas turbine engines other than for land vehicles, namely, turbine blades, combustors, fuel injectors, compressors, output shafts, gearboxes, and exhausts; replacement parts and components for gas turbine engines other than for land vehicles; gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing; gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing, all for use in the oil and gas industry; internal combustion engines other than for land vehicles, and replacement parts and components therefor; filters being parts of machines or engines; filter elements being parts of machines or engines; air filters and air filter elements being parts of machines and engines; fuel filters and fuel filter elements being parts of machines and engines; gas filters and gas filter elements being parts of machines and engines; oil filters and oil filter elements being parts of machines and engines; gaskets of metal being parts of machines and engines; gaskets for internal combustion engines; machine parts, namely, mechanical seals; bearings for use as parts of machines; bushings for use as parts of machines; spark plugs; spark plugs for internal combustion engines; kits for filters and filter elements being parts of machines and engines; kits for seals being parts of machines and engines; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Machinery maintenance management system comprised of software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; hardware for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; electric cords; electric wire and cable; electrical fuses, control system module for machines and engines (other than land vehicles); all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Cords of rubber; gaskets made of rubber; sealing gaskets, not of metal; washers of rubber or vulcanized fiber; O-rings; oil seals; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Dowels, not of metal; pins, not of metal; washers, not of rubber or metal; bolts, not of metal; nuts, not of metal; rivets, not of metal; screws, not of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Cable ties, not of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Providing management services related to one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing (may or may not be computer assisted), including fleet management, maintenance management, machinery management; purchasing and/or material procurement for others, purchasing for others; online retail services for sale of parts and components for machine and engines (other than land vehicles); online retail services for sale of parts, components, and equipment for gas turbine engines other than for land vehicles, generator sets, compressor sets, and pump sets; online retail services for sale of dowels of metal, pins of metal, washers of metal, bolts of metal, nuts of metal, rivets of metal, screws of metal, filters being parts of machines or engines, filter elements being parts of machines or engines, air filters and air filter elements being parts of machines and engines, fuel filters and fuel filter elements being parts of machines and engines; online retail services for sale of gas filters and gas filter elements being parts of machines and engines, oil filters and oil filter elements being parts of machines and engines, gaskets of metal being parts of machines and engines, gaskets for internal combustion engines, machine parts, namely, mechanical seals, bearings for use as parts of machines, bushings for use as parts of machines; online retail services for sale of spark plugs, spark plugs for internal combustion engines, kits for filters and filter elements being parts of machines and engines, kits for seals being parts of machines and engines, electric cords, electric wire and cable, electrical fuses, control system module for machines and engines (other than land vehicles); online retail services for sale of cords of rubber, gaskets made of rubber, sealing gaskets of metal, washers of rubber or vulcanized fiber, O-rings, oil seals, dowels, not of metal, pins, not of metal, washers, not of rubber or metal, bolts, not of metal, nuts, not of metal, rivets, not of metal, screws, not of metal, cable ties, not of metal; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Providing maintenance information in the nature of diagnostic data, predictive maintenance recommendations, specifications, and alerts for one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repairing, servicing, maintaining, and installing of gas turbine equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repairing, servicing, maintaining, and installing of gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing; repairing, servicing, maintaining, and installing of internal combustion engines other than for land vehicles, and replacement parts and components therefor; remanufacturing of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing, to the order and/or specification of others; refurbishing, retrofitting, and converting of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Rental services of gas turbine engines other than for land vehicles, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Training related to the creation of gas turbines; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Software as a service (SAAS) services featuring software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, providing on-line non-downloadable software for remote monitoring, diagnostics, optimization, physical inspection, alerts generation, and troubleshooting in the nature of diagnosing computer hardware and software problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; troubleshooting in the nature of diagnosing problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; providing remote monitoring, diagnostics, alerts, remote management of information technology systems of others, and data collection regarding the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, remote management of information technology computer hardware, software, and system access relating to the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; remote monitoring of the functioning and use of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; diagnostic services in the field of turbine equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; inspecting of gas turbine engines, generator sets, compressor sets, and pump sets, and of parts, components, and equipment therefor; services related to the design of gas turbines and gas turbine packages, including proposal preparation, design and engineering, quality control; repair, service and maintenance of computer software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repair, service and maintenance of computer hardware for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; rental services of computer hardware and software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology.
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
17 - Rubber and plastic; packing and insulating materials
20 - Furniture and decorative products
22 - Rope, netting, tents, awnings, sails and sacks; padding and stuffing materials
35 - Advertising and business services
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Dowels of metal; pins of metal; washers of metal; bolts of metal; nuts of metal; rivets of metal; screws of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Gas turbine engines other than for land vehicles; internal combustion engines other than for land vehicles; parts, components, and equipment for gas turbine engines other than for land vehicles, namely, turbine blades, combustors, fuel injectors, compressors, output shafts, gearboxes, and exhausts; replacement parts and components for gas turbine engines other than for land vehicles; gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing; gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing, all for use in the oil and gas industry; internal combustion engines other than for land vehicles, and replacement parts and components therefor; filters being parts of machines or engines; filter elements being parts of machines or engines; air filters and air filter elements being parts of machines and engines; fuel filters and fuel filter elements being parts of machines and engines; gas filters and gas filter elements being parts of machines and engines; oil filters and oil filter elements being parts of machines and engines; gaskets of metal being parts of machines and engines; gaskets for internal combustion engines; machine parts, namely, mechanical seals; bearings for use as parts of machines; bushings for use as parts of machines; spark plugs; spark plugs for internal combustion engines; kits for filters and filter elements being parts of machines and engines; kits for seals being parts of machines and engines; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Machinery maintenance management system comprised of software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; hardware for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; electric cords; electric wire and cable; electrical fuses, control system module for machines and engines (other than land vehicles); all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Cords of rubber; gaskets made of rubber; sealing gaskets, not of metal; washers of rubber or vulcanized fiber; O-rings; oil seals; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Dowels, not of metal; pins, not of metal; washers, not of rubber or metal; bolts, not of metal; nuts, not of metal; rivets, not of metal; screws, not of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Cable ties, not of metal; all of the aforesaid goods being or for use with gas-powered equipment; none of the aforesaid goods being or for use with power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Providing management services related to one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing (may or may not be computer assisted), including fleet management, maintenance management, machinery management; purchasing and/or material procurement for others, purchasing for others; online retail services for sale of parts and components for machine and engines (other than land vehicles); online retail services for sale of parts, components, and equipment for gas turbine engines other than for land vehicles, generator sets, compressor sets, and pump sets; online retail services for sale of dowels of metal, pins of metal, washers of metal, bolts of metal, nuts of metal, rivets of metal, screws of metal, filters being parts of machines or engines, filter elements being parts of machines or engines, air filters and air filter elements being parts of machines and engines, fuel filters and fuel filter elements being parts of machines and engines; online retail services for sale of gas filters and gas filter elements being parts of machines and engines, oil filters and oil filter elements being parts of machines and engines, gaskets of metal being parts of machines and engines, gaskets for internal combustion engines, machine parts, namely, mechanical seals, bearings for use as parts of machines, bushings for use as parts of machines; online retail services for sale of spark plugs, spark plugs for internal combustion engines, kits for filters and filter elements being parts of machines and engines, kits for seals being parts of machines and engines, electric cords, electric wire and cable, electrical fuses, control system module for machines and engines (other than land vehicles); online retail services for sale of cords of rubber, gaskets made of rubber, sealing gaskets of metal, washers of rubber or vulcanized fiber, O-rings, oil seals, dowels, not of metal, pins, not of metal, washers, not of rubber or metal, bolts, not of metal, nuts, not of metal, rivets, not of metal, screws, not of metal, cable ties, not of metal; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Providing maintenance information in the nature of diagnostic data, predictive maintenance recommendations, specifications, and alerts for one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repairing, servicing, maintaining, and installing of gas turbine equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repairing, servicing, maintaining, and installing of gas turbine packages comprised of gas turbine engines other than for land vehicles, the engines consisting of fuel systems, oil lubrication systems, heat exchangers, frames, and enclosures, sold in combination with either a generator set, a compressor set, or a pump set, or a combination of the foregoing; repairing, servicing, maintaining, and installing of internal combustion engines other than for land vehicles, and replacement parts and components therefor; remanufacturing of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing, to the order and/or specification of others; refurbishing, retrofitting, and converting of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Rental services of gas turbine engines other than for land vehicles, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Training related to the creation of gas turbines; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology. Software as a service (SAAS) services featuring software for remote monitoring, diagnostics, optimization, maintenance, physical inspection, alerts generation, collaborative communication, information management, and troubleshooting of equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, providing on-line non-downloadable software for remote monitoring, diagnostics, optimization, physical inspection, alerts generation, and troubleshooting in the nature of diagnosing computer hardware and software problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; troubleshooting in the nature of diagnosing problems with turbine equipment and related assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; providing remote monitoring, diagnostics, alerts, remote management of information technology systems of others, and data collection regarding the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; computer services, namely, remote management of information technology computer hardware, software, and system access relating to the operation and condition of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; remote monitoring of the functioning and use of one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; diagnostic services in the field of turbine equipment and assets, including one or more gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; inspecting of gas turbine engines, generator sets, compressor sets, and pump sets, and of parts, components, and equipment therefor; services related to the design of gas turbines and gas turbine packages, including proposal preparation, design and engineering, quality control; repair, service and maintenance of computer software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; repair, service and maintenance of computer hardware for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; rental services of computer hardware and software for control systems, management, maintenance, diagnostics, and monitoring of gas turbine engines, internal combustion engines, compressors, generators, pumps, associated ancillary equipment, and parts, components, and equipment for all of the foregoing; all of the aforesaid services for use with or in relation to gas-powered equipment; none of the aforesaid services for use with or in relation to power generation equipment that uses a combination of liquid or gas fuel and photovoltaic technology.
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.
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 17/06 - Arrangement of sensing elements responsive to speed
F16D 1/08 - Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with clamping hubCouplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end with hub and longitudinal key
33.
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 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
G05B 19/409 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by using manual data input [MDI] or by using control panel, e.g. controlling functions with the panelNumerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control panel details or by setting parameters
37.
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.
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.
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 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02M 26/19 - Means for improving the mixing of air and recirculated exhaust gases, e.g. venturis or multiple openings to the intake system
43.
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.
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.
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.
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 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
F02C 1/00 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
48.
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.
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.
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.
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 - Walls, e.g. partitions, for buildingsWall construction with regard to insulationConnections specially adapted to walls
E04C 2/292 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels characterised by specified materials composed of materials covered by two or more of groups , , , or of materials covered by one of these groups with a material not specified in one of these groups at least one of the materials being insulating composed of insulating material and sheet metal
B32B 5/18 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by features of a layer containing foamed or specifically porous material
B32B 3/06 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for securing layers togetherLayered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
B32B 19/00 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
B32B 3/08 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
E04C 2/00 - Building elements of relatively thin form for the construction of parts of buildings, e.g. sheet materials, slabs, or panels
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, 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 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.
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 of engines for driving pumps, hand-held tools or electric generatorsPortable combinations of engines with engine-driven devices for electric generators
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 - Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities
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 - Fluid supply conduits to nozzles or the like
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
F28C 3/02 - Other direct-contact heat-exchange apparatus the heat-exchange media both being gases or vapours
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F01D 25/10 - Heating, e.g. warming-up before starting
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
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.
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 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.
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.
Gas turbine engines other than for land vehicles; parts, components, and equipment for gas turbine engines other than for land vehicles, namely, turbine blades, combustors, fuel injectors, compressors, output shafts, gearboxes, and exhausts; replacement parts and components for gas turbine engines other than for land vehicles; gas turbine packages for compressor set applications; gas turbine packages for generator set applications; gas turbines packages for mechanical drive applications, including pumping systems.
(1) Gas turbine engines for power generation, gas and fluid compression, and mechanical drive applications, other than for land vehicles; parts, components, and equipment for gas turbine engines other than for land vehicles, namely, blades for gas turbines, combustors for igniting a fuel-air mix inside a gas turbine engine, fuel injectors, centrifugal compressors, engine output shafts for delivering rotational power to equipment driven by gas turbine engines, gearboxes, and engine exhaust systems; replacement parts for gas turbine engines for power generation, gas and fluid compression, and mechanical drive applications, other than for land vehicles; gas turbine packages comprising gas turbine engines and centrifugal compressors for compressing oil and gas; gas turbine packages comprising gas turbine engines and electricity generators for power generation; gas turbines packages for mechanical drive applications, namely pumping systems.
72.
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.
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 - Investigating resistance of materials to the weather, to corrosion or to light
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups Air intakes for jet-propulsion plants
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 - Arrangements of devices for purifying liquids to be transferred, e.g. of filters, of air or water separators
B67D 7/70 - Arrangements of pumps of two or more pumps in series or parallel
B67D 7/04 - Apparatus or devices for transferring liquids from bulk storage containers or reservoirs into vehicles or into portable containers, e.g. for retail sale purposes for transferring fuels, lubricants or mixed fuels and lubricants
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 - Arrangement of sensing elements responsive to condition of working fluid, e.g. pressure
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
G01L 11/00 - Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group or
H01H 37/76 - Contact member actuated by melting of fusible material, actuated due to burning of combustible material or due to explosion of explosive material
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.
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.
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.
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.
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.
A turbine blade having a base and an airfoil, the base including a root end. The airfoil including a skin extending from the base and defining a leading edge, a trailing edge, having a tip end opposite from the root end. The turbine blade further including dividers located within the airfoil. The dividers, leading edge, trailing edge, and skin define serpentine channels within the airfoil. A first multi-bend heat exchange path and a second multi-bend heat exchange path extend through the serpentine channels to cool portion of the turbine blade.
A turbine blade (440a, 440b) having a base (442) and an airfoil (441), the base including a root end (444). The airfoil including a skin (460) extending from the base and defining a leading edge (446), a trailing edge (447), having a tip end (445) opposite from the root end. The turbine blade further including dividers (491, 492, 493, 494, 495) located within the airfoil. The dividers, leading edge, trailing edge, and skin define serpentine channels (474, 484, 507a, 507b, 508) within the airfoil. A first multi-bend heat exchange path (470) and a second multi-bend heat exchange path (480) extend through the serpentine channels to cool portion of the turbine blade.
A nozzle segment (451) for a gas turbine engine (100) with turbine airflow (15) passing through the gas turbine engine. The nozzle segment including an upper shroud (452) and an inner hub (456). The nozzle segment including a first airfoil (460a, 460b, 460c) and second airfoil (407a, 470b, 470c) extending from the upper shroud to the inner hub. The first airfoil and second airfoil including conduits (481a, 481b, 481c, 482a, 482b, 482c, 483a, 483b, 483c, 484a, 484b, 484c) for delivering secondary air (13) to displace a portion of the turbine airflow passing through the gas turbine engine.
A system and method for resource estimation of an additive manufacturing device is disclosed herein. The system includes at least one processor and one or more software modules. The processor executes the one or more software modules to determine a number of parts that can be manufactured per manufacturing run, estimate manufacturing time to manufacture a specified number of parts, and determine a total cost to manufacture the number of parts with the additive manufacturing device. The one or more software modules can compare the total cost to the cost of a current manufacturing method.
This disclosure provides an air tube for a combustor of a gas turbine engine. The air tube includes an inner tube and an outer tube to deliver discharged compressor air into a combustion chamber of the combustor. The air tube can include struts and fins that can improve the cooling performance of the air tube during operation of the gas turbine engine.
This disclosure provides a tube shaping tool for a torque mechanism to modify a tube end. The tube shaping tool can include a cup and an internal assembly. The internal tube assembly can include a stem and an internal body. The stem can be received by the torque mechanism and transmit torque generated from the torque mechanism to the components of the tube shaping tool. The tube shaping tool can roll form the outside diameter of the tube end using standard bearings and a flange bearing attached to the internal body. The flange bearing can also include a flange that can provide facing of the tube end.
A tube shaping tool (100) for a torque mechanism (50) to modify a tube end. The tube shaping tool includes an internal assembly (300). The internal tube assembly includes a stem (315) and an internal body (310). The stem can be received by the torque mechanism and transmit torque generated from the torque mechanism to the components of the tube shaping tool. The tube shaping tool roll-forms the outside diameter of the tube end using standard bearings (320) and a flange bearing (330) attached to the internal body. The flange bearing also includes a flange (325) that can provide facing of the tube end. The tube shaping tool can further comprise a cup (200).
B21C 37/30 - Finishing tubes, e.g. sizing, burnishing
B21D 19/00 - Flanging or other edge treatment, e.g. of tubes
B21D 19/04 - Flanging or other edge treatment, e.g. of tubes by continuously-acting tools moving along the edge shaped as rollers
B23B 5/16 - Turning-machines or devices specially adapted for particular workAccessories specially adapted therefor for bevelling, chamfering, or deburring the ends of bars or tubes
This disclosure provides a seal strip assembly for a sealing strip slot to reduce air leakage between gas turbine nozzle segments. The seal strip assembly includes a bimetal element and a backing plate. The bimetal element includes a first layer with a first thermal coefficient of thermal expansion and a second layer with a second coefficient of thermal expansion. The second coefficient of thermal expansion is lower than the first coefficient of thermal expansion allowing the bimetal element to expand with an increase in surrounding temperature.
This disclosure provides a seal strip assembly (700a, 700b, 700c, 700d, 700e, 701, 702, 703) for a sealing strip slot (481c, 482c) to reduce air leakage between gas turbine nozzle segments (451a, 451b). The seal strip assembly includes a bimetal element (720, 740) and a backing plate (710). The bimetal element includes a first layer (724, 742) with a first thermal coefficient of thermal expansion and a second layer (722, 743) with a second coefficient of thermal expansion. The second coefficient of thermal expansion is lower than the first coefficient of thermal expansion allowing the bimetal element to expand with an increase in surrounding temperature.
A temperature measuring system is disclosed herein. The temperature measuring system includes an optical assembly and a spectral data receiver. The temperature measuring system views passing gas and measures the radiant response of a selected gas. The measurement includes radiant intensities with respect to wavelengths in the infrared region.
