GE Vernova Technology Patente

A method of determining submodule capacitor degradation. The method comprising the step of determining voltage change of at least one submodule capacitor during a control cycle whilst the at least one submodule is switched into a valve circuit and assigning the voltage change as dV_vsm. The method further comprising the step of determining average voltage change across all in-circuit submodules during said control cycle and assigning the average voltage change as dV_average. The method further comprising the step of determining relative capacitance of all in-circuit submodules by comparing dV_vsm to the dV_average of all in-circuit submodules. The method may further comprise the step of determining capacitance deviation of all in-circuit submodules to quantify how much the capacitance of each in-circuit submodule deviates from the average voltage change dV_average across all in-circuit submodules. The method may further comprise the step of comparing the determined capacitance deviation against a pre-defined threshold value to identify degraded in-circuit submodules. The method may further comprise step of filtering dV_vsm and dV_average or functions of them to achieve higher accuracy of the relative capacitance determination and capacitor degradation determination.

Disclosed is a system for removably mounting hardware, like a probe, to a stationary structure, like a casing element of a turbine section. A receptacle element includes a base configured to be fixed to the stationary structure and a collar extending from the base. The collar includes an internal opening to receive the hardware and a locking element aperture. A locking element is movable in the locking element aperture between a locked position fixedly engaging the hardware and an unlocked position allowing the hardware to be removed. An attachment element is movable relative to the receptacle element and has a tapered portion to move the locking element into the locked position. A disk spring element is configured to force the attachment element relative to the receptacle element toward the locked position of the locking element, providing an intrinsic anti-rotation and anti-loosening feature.

A fuel injector (200) for a gas turbine combustor (17) is provided. The fuel injector (200) includes an annular main body (300) extending from a first end (301) to a second end (302). The annular main body (300) defines a centerline axis (303) extending from the first end (301) to the second end (302), and at least a portion of a fuel circuit (320) extends along the centerline axis (303). A first plurality of fluid inlets (345) is disposed about the fuel circuit (320), and a second plurality of fluid inlets (350) is disposed about the first plurality of fluid inlets (345). The fuel circuit (320) includes a fuel inlet (324) and a fuel outlet (330) in fluid communication with the fuel inlet (324). An exterior surface of the fuel outlet (330) forms a fuel outlet angle (500) relative to the centerline axis (303).

A fuel injection assembly (80) for a gas turbine engine (10) includes a housing (300) having a first housing portion (305) adjacent a first end (301) and a second housing portion (310) adjacent a second end (302) opposite the first end (301). The first housing portion (305) defines at least one fuel chamber (320), and the second housing portion (310) defines at least one mixing chamber (335). The fuel injection assembly (80) includes fuel channels (330) extending along a central axis (510) between the first housing portion (305) and the second housing portion (310). The fuel channels (330) are spaced apart along a length of the housing (300) and are in fluid communication with the at least one fuel chamber (320) and the at least one mixing chamber (335). Fluid channels (340, 345) are disposed in the second housing portion (310) and in fluid communication with the at least one mixing chamber (335) to promote mixing of fuel and air. A combustor (17) having the fuel injection assembly (80) is also provided.

A hydrogen capable fuel injector (200, 500) for a combustor (17) of a gas turbine engine (10) is provided. The fuel injector (200, 500) includes an annular body (300) extending from a first end (301) to a second end (302) and a fuel circuit (340) at least partially disposed in the annular body (300). The annular body (300) defines a centerline axis (303) extending from the first end (301) to the second end (302). The fuel circuit (340) includes a fuel plenum (345), a primary fuel outlet (348) in fluid communication with the fuel plenum (345) and extending along the centerline axis (303), and a plurality of secondary fuel outlets (350) in fluid communication with the fuel plenum (345) and disposed radially about the primary fuel outlet (348). The fuel injector (200, 500) also includes a first plurality of fluid channels (325) radially disposed about the centerline axis (303) and a second plurality of fluid channels (330) radially disposed about the first plurality of fluid channels (325).

There is provided a computer-implemented method (400) of controlling an energy dissipation means for dynamic braking in a power transmission network, the method (400) comprising: monitoring (410) one or more first parameters associated with the power transmission network; determining (420), based on the one or more first parameters, a fault status of the power transmission network; and controlling (430), based on the fault status, the energy dissipation means to perform dynamic braking for the power transmission network; wherein the controlling (430), based on the fault status, the energy dissipation means, comprises adaptively controlling by either of: adjusting (430a) a threshold voltage for activating the energy dissipation means or controlling (430b) the energy dissipation means to perform dynamic braking until the MCB is determined to be in a non-conducting state.

Systems, methods, and computer-readable media are disclosed for impedance-based broken conductor detection in electric distribution systems. Upon the detection of a broken conductor, the affected overhead line will be de-energized before it hits the ground. An example method may include determining, during a first time period, a first impedance value measured by a first IED, and may further include determining, during a second time period that after the first time period, a second impedance value measured by the first IED. The method may further include determining a first ratio based on dividing a difference between the first impedance value and the second impedance value by the first impedance value, and may further include determining that the first ratio deviates from a threshold setpoint, and determining that a broken conductor condition occurs based on the first ratio deviating from the threshold setpoint.

A tool (170) for separating adjacent component segments (102A, 102B) in a stage (165) of a turbine section (116) is disclosed. The tool (170) includes a base (172) and first and second curved plates (180, 182). The first plate (180) includes a first end (184) to engage a portion (166) of a component segment (102A), and the second plate (182) includes a first end (186) to engage a fixed element (188), such as the other component segment (102B) or a half casing (150H) of the turbine section (116). A coupler (220) couples the first plate (180) to the base (172), and a linear actuator (250) is between the base (172) and the second plate (182). The linear actuator (250) linearly moves the second plate (182) between a first position in which the first ends (184, 186) of the first and second plates (180, 182) are retracted and a second position in which the first ends (184, 186) of the first and second plates (180, 182) are extended a distance from one another to force the adjacent component segments (102A, 102B) to separate.

An integration system for use with a gas turbine engine includes an exhaust gas recirculation (EGR) system in flow communication with a gas turbine section of the gas turbine engine. The EGR system includes an EGR conduit fluidly coupled to an exhaust line of the gas turbine engine and fluidly coupled to an EGR manifold upstream from an inlet of a compressor section of the gas turbine engine. The EGR conduit is oriented to provide a portion of exhaust gases discharged from the gas turbine section to the EGR manifold. Additionally, the EGR system also includes a flow restriction component in flow communication with the exhaust line of the gas turbine engine. The flow restriction component is downstream from the EGR conduit of the EGR system. The flow restriction component facilitates increasing a pressure of the exhaust gases discharged from the gas turbine section.

A system includes a fuel heating system having a first heat exchanger. The first heat exchanger is fluidly coupled to a steam turbine system, a gas turbine system, a carbon capture system, and a heat recovery steam generator (HRSG). The first heat exchanger is configured to receive steam from the HRSG, the steam turbine system, or a combination thereof. The first heat exchanger is also configured to receive a fuel. The first heat exchanger is also configured to place the steam in a first heat exchange relationship with the fuel to produce a first heated fuel and a first cooled steam. The first heat exchanger is also configured to send the first cooled steam to the carbon capture system. The first heat exchanger is also configured to send the first heated fuel to the gas turbine system, a duct burner, or a combination thereof.

The present invention refers to circuit breaker (10) comprising a first electrical contact (11) and a second electrical contact (12) that are arranged movably relative to one another in a movement direction (D). Preferably, the first electrical contact (11) is a pin (20) and second electrical contact (12) is a socket (21). In a contact position (CP) an outer contact surface (14) of first electrical contact (11) is in mechanical and electrical contact with an inner contact surface (15) of second electrical contact (12). Inside the first electrical contact (11) an interior hollow space (27) is provided that is in fluidic connection with at least one gas flow opening (24) provided in the area of a distal end (16) of first electrical contact (11). The interior hollow space (27) is in fluidic connection with a gas flow creating device (30). During a relative movement of the first electrical contact (11) and the second electrical contact (12) in movement direction (D) a gas flow (G) may be created through the interior hollow space (27) and the at least one gas flow opening (24) for cooling at least the distal end (16) of first electrical contact (11) in order to avoid creation of an electrical arc between the two electrical contacts (11, 12) or at least terminate the electrical arc as quickly as possible.

A turbine blade (114) and related method for forming an outermost abrasive layer (170) are disclosed. The blade includes an airfoil body (124) having a radial outermost surface (160) relative to a turbine rotor, a bond coat (172) over the radial outermost surface, and the outermost abrasive layer over the bond coat. The outermost abrasive layer (170) includes a graded oxide ceramic layer (174) or a graded metal ceramic layer (176). The outermost abrasive layer is vacuum heat treated to harden the layer, resulting in increased rub and improved clearance between the blade tip, creating a smaller tip gap and lower leakage. The heat-treated abrasive layer is also resistant to oxidation at higher temperatures, e.g. greater than 1090°C (~2000°F), caused by the increased use of higher temperature fuels, such as hydrogen. The vacuum heat treatment also results in thermal cycle testing improvements.

A visual indicator (110) for an electrical assembly (100), the electrical assembly (100) comprising a housing (120), and an electrical discharge mechanism (130) arranged within the housing (120); the electrical discharge mechanism (130) configured such that movement of the electrical discharge mechanism (130) from a first position to a second position allows electrical components (140) of the electrical assembly (100) to electrically discharge. The visual indicator (110) comprises a display component (112) arranged to display a visual indication external to the housing (120); and a mechanical coupling means (114) configured to mechanically couple the display component (112) to the electrical discharge mechanism (130), such that movement of the electrical discharge mechanism (130) causes movement of the visual indication of the display component (112). When the electrical discharge mechanism (130) is in the first position, the display component (112) displays a first visual indication, and when the electrical discharge mechanism (130) is in the second position, the display component (112) displays a second visual indication.

A method (300) for repairing a steel alloy article is provided. The method includes depositing (302), using a first welding process, a first weld repair layer across a surface of the steel alloy article to be repaired. The first weld repair layer forms a heat-affected zone (HAZ) in the steel alloy article beneath the surface. The method also includes tempering (304) the heat-affected zone by depositing (358), using a second welding process, a second weld repair layer across the first weld repair layer. The first welding technique is different than the second welding process and induces a lower heat input into the steel alloy article than the second welding process, wherein a thickness of the first weld repair layer is thinner than a thickness of the second weld repair layer.

There is provided a method (300), and a controller (160), for controlling a plurality of submodules (212) in a valve (224) of a power electronics device (290). The method comprises determining, by the controller (160), a time period in which selected submodules of the plurality of submodules (212) are to be switched in order to control an output voltage of the valve (224); determining, by the controller (160), for each of the selected submodules, a respective switching time, within the time period, based on a voltage demand for the time period and a voltage of each of the selected submodules, wherein at least one of the respective switching times is different to another of the respective switching times; generating, by the controller (160), a respective switching command (270) for each of the selected submodules; and providing, by the controller, the respective switching commands (270) to the valve (224), whereby to control the selected submodules to switch at the respective switching times within the time period.

There is provided a method, and a controller, for controlling a plurality of submodules (212) in a valve (224) of a power converter (120), the method comprising: determining, by a controller (160), a first switching time for a first submodule of the plurality of submodules (212); determining, by the controller (160), a second switching time for a second submodule of the plurality of submodules (212), wherein the first switching time differs from the second switching time by a time difference; wherein the time difference is based on a property of resonance in the power converter (120), wherein the resonance in the power converter is that caused by switching at least one submodule of the plurality of submodules (212) in the valve (224); and providing, by the controller (160), one or more switching commands to the valve (224) to cause the first submodule to switch at the first switching time and the second submodule to switch at the second switching time.

Methods and systems are provided for servicing a turbomachine having a rotor with a plurality of hook elements for receiving a retention device. Current data indicating each current hook element having a dowel pin hole and a respective current number of stakes, a defined spacing rule, and a maximum number of stakes per dowel pin hole are received. For each current hook element, first potential combinations with other hook elements are determined based on the defined spacing rule, and the current number of stakes. First solution combinations are identified from the first potential combinations, the current number of stakes at each of the hook elements in each of the first solution combinations being less than the maximum number of stakes. A user interface is controlled to indicate at least one desired solution of the first solution combinations having a highest number of potential future services.

A system for monitoring for a combustor anomaly in a gas turbine system (GT, 100) is provided. The system includes an emissions probe (180) for each combustor element (116) in the GT system and emissions analyzer(s) (190) operatively coupled to the emissions probes to periodically measure an emissions level of the exhaust flow from each emissions probe. A combustor anomaly detection system is connected to the emissions analyzer(s) and determines whether the emissions level at a select emissions probe of the emissions probes deviates from an expected emissions level by more than a predetermined threshold. Where the emissions level so deviates, the system identifies that a combustor element anomaly exists for the combustor element from which the exhaust flow originates and adjusts operation of the combustor element having the combustor element anomaly. The system provides accurate identification of combustor anomalies without the use of a large number of temperature and/or pressure sensors.

A system (150) for controlling ventilation to a turbine enclosure (92) includes an air inlet filter system (152), a ventilation fan (154) to extract an air flow (156) from the air inlet filter system (152), and an air delivery system (160) including a plurality of conduits (162). Each conduit (162) delivers the air flow (156) to one of a plurality of ventilation inlets (164) defined in the turbine enclosure (92). A motorized volume control damper (170) is operably coupled to each of the plurality of ventilation inlets (164) and is configured to control a volume of air flow (156) entering a respective ventilation inlet (164) through a respective conduit (162). A controller (180) is configured to control each motorized volume control damper (170) to evenly distribute the air flow (156) to each of the plurality of ventilation inlets (164) regardless of a pressure drop (ΔP) across the ventilation fan (154).

Systems (100) and methods are provided for calibrating a hydraulic starter (50) for a turbomachine (10). A hydraulic fluid source (54) supplies fluid at a high pressure or at a low pressure for rotatably driving the hydraulic starter, and a valve (64) is movable to adjust a flow rate of the fluid supplied from the hydraulic fluid source to the hydraulic starter. The hydraulic fluid source and operation of the valve are automatically controlled by a computing system (102) to sequentially perform a plurality of base modes with the valve (64) being in either a fully closed position or a fully opened position. The plurality of base modes includes at least one standby mode test and at least one crank speed mode test. A rotational speed of the turbomachine detected by a speed sensor (66) during each of the plurality of base modes is monitored by the computing system for calibrating the hydraulic starter.

A method (300) for repairing a steel alloy article is provided. The method includes depositing (302), using a first welding process, a first weld repair layer across a surface of the steel alloy article to be repaired. The first weld repair layer forms a heat-affected zone (HAZ) in the steel alloy article beneath the surface. The method also includes tempering (304) the heat-affected zone by depositing (358), using a second welding process, a second weld repair layer across the first weld repair layer. The first welding technique is different than the second welding process and induces a lower heat input into the steel alloy article than the second welding process, wherein a thickness of the first weld repair layer is thinner than a thickness of the second weld repair layer.

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A vibration damping system (120) includes a vibration damping element (166) for a turbine nozzle (112) or blade (114). A body opening (160) extends through the turbine nozzle (112) or blade (114) between the tip end (132) and the base end (130) thereof, e.g., through the airfoil (134) among potentially other parts of the nozzle (112) or blade (114). A vibration damping element (166) includes a plurality of stacked plate members (170) within the body opening (160). Each plate member (170) is in surface contact with at least one adjacent plate member (170) to cause friction that dampens vibration of the nozzle (112) or blade (114). The body opening (160) has an inner dimension and each plate member (170) has an outer dimension sized to frictionally engage the inner dimension of the body opening (160) to damp vibration. Plate members (170) may each include a central opening (180) therein, and a fixed elongated body (186) may extend through the central opening (180).

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