Patents by Inventor Jason Nathaniel Cook
Jason Nathaniel Cook has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11506389Abstract: A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.Type: GrantFiled: April 21, 2022Date of Patent: November 22, 2022Assignee: General Electric CompanyInventors: Jason Nathaniel Cook, Jason Dean Fuller, Christopher James Wenner
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Publication number: 20220243919Abstract: A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.Type: ApplicationFiled: April 21, 2022Publication date: August 4, 2022Inventors: Jason Nathaniel Cook, Jason Dean Fuller, Christopher James Wenner
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Patent number: 11384940Abstract: A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.Type: GrantFiled: January 23, 2019Date of Patent: July 12, 2022Assignee: General Electric CompanyInventors: Jason Nathaniel Cook, Jason Dean Fuller, Christopher James Wenner
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Patent number: 11203986Abstract: A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.Type: GrantFiled: June 8, 2020Date of Patent: December 21, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: David Leach, Valerie Suzanne Vernet, Jason Nathaniel Cook, Jayaprakash Natarajan
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Publication number: 20210381432Abstract: A method of operating a rotary machine below a minimum emissions compliance load in a response mode includes reducing a fuel split to zero. The fuel split apportions a total flow of fuel to the combustor between a first combustion zone and a second combustion zone. The method also includes determining a current operating temperature of the first combustion zone using a digital simulation of the rotary machine. The method further includes determining a target operating temperature of the first combustion zone. The target operating temperature enables the rotary machine to operate below a traditional Minimum Emissions Compliance Load (MECL) while still in compliance with emissions standards. The method also includes channeling a first flow of fuel to the first combustion zone. The first flow of fuel decreases the temperature of the first combustion zone to the target operating temperature.Type: ApplicationFiled: June 8, 2020Publication date: December 9, 2021Inventors: David Leach, Valerie Suzanne Vernet, Jason Nathaniel Cook, Jayaprakash Natarajan
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Publication number: 20200232645Abstract: A loading/unloading method for a gas turbine system is disclosed. The gas turbine system includes a combustion section featuring a primary combustion stage with a first plurality of fuel nozzles and a downstream, secondary combustion stage with a second plurality of fuel nozzles. For loading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a higher number of at least one of the first or second plurality of fuel nozzles; and for unloading, the method progresses through each of a plurality of progressive combustion modes that sequentially activate a lower number of at least one of the first or second plurality of fuel nozzles. During each combustion mode, regardless of whether loading or unloading, a primary combustion stage exit temperature of a combustion gas flow is controlled to be within a predefined target range corresponding to the respective combustion mode.Type: ApplicationFiled: January 23, 2019Publication date: July 23, 2020Inventors: Jason Nathaniel Cook, Jason Dean Fuller, Christopher James Wenner
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Patent number: 9777637Abstract: The fuel flow rate to a gas turbine is measured using an inert gas. The inert gas is injected into the fuel flow and the concentration of the inert gas in the fuel/inert gas mixture is later measured. The concentration of the inert gas in the fuel/inert gas mixture is then used to calculate the mass flow rate of the fuel.Type: GrantFiled: December 19, 2012Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Steven William Tillery, Jason Nathaniel Cook
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Patent number: 9556798Abstract: A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements.Type: GrantFiled: January 28, 2013Date of Patent: January 31, 2017Assignee: General Electric CompanyInventors: Sanji Ekanayake, Thomas C. Billheimer, Douglas Corbin Warwick, Alston Ilford Scipio, Dale J. Davis, Jason Nathaniel Cook, Vahid Vaezi
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Publication number: 20140208764Abstract: A method and system for measuring a flow profile in a portion of a flow path in a turbine engine is provided. The system includes a mass flow sensor assembly having a plurality of hot wire mass flow sensors, the mass flow sensor assembly disposed in the portion of the flow path at a location where the flow profile is to be measured. The system also includes a controller that converts signals from the temperature sensor, the pressure sensor and the plurality of hot wire mass flow sensors to flow profile measurements.Type: ApplicationFiled: January 28, 2013Publication date: July 31, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Sanji Ekanayake, Thomas C. Billheimer, Douglas Corbin Warwick, Alston Ilford Scipio, Dale J. Davis, Jason Nathaniel Cook, Vahid Vaezi
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Patent number: 8677761Abstract: Systems and methods for controlling compressor extraction air flows from a compressor of a turbine system during engine turn down are provided. In one embodiment, a method for controlling compressor extraction air flows from a compressor of a turbine system during turn down includes a control unit monitoring one or more operating parameters of a turbine system associated with an exit temperature of a combustor of the turbine system. The method further includes the control unit detecting one or more operating parameters meeting or exceeding a threshold associated with a decrease in the exit temperature of the combustor. In response to detecting one or more operating parameter meeting or exceeding the threshold, a control signal is transmitted to at least one variable orifice located in the turbine system causing at least one variable orifice to alter at least one extraction air flow from the compressor.Type: GrantFiled: February 25, 2009Date of Patent: March 25, 2014Assignee: General Electric CompanyInventors: David Leach, Jason Nathaniel Cook, Chi Ming Ho
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Publication number: 20130232976Abstract: The fuel flow rate to a gas turbine is measured using an inert gas. The inert gas is injected into the fuel flow and the concentration of the inert gas in the fuel/inert gas mixture is later measured. The concentration of the inert gas in the fuel/inert gas mixture is then used to calculate the mass flow rate of the fuel.Type: ApplicationFiled: December 19, 2012Publication date: September 12, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Steven William TILLERY, Jason Nathaniel COOK
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Publication number: 20130238102Abstract: Disclosed herein are methods and systems for gas turbine inlet air flow rate measurement using inert gas. In an embodiment, a gas meter may measure the concentration of an injected gas into an air flow. A processor may receive the measurement of the gas concentration and calculate an air mass flow rate based on the gas concentration.Type: ApplicationFiled: March 8, 2012Publication date: September 12, 2013Applicant: General Electric CompanyInventors: Steven William Tillery, Jason Nathaniel Cook
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Publication number: 20130170966Abstract: A turbine cooling system is provided, having a compressor for supplying cooling air, a forward turbine rotor wheel space, a high-pressure packing seal (HPPS) bypass cavity, and a metering device. The forward turbine rotor wheel space is cooled by the cooling air supplied by the compressor. The HPPS bypass cavity is in fluid communication with and receives a portion of the cooling air from the compressor, and is in fluid communication with and supplies the cooling air to the forward turbine rotor wheel space. The metering device is in operable communication with the forward turbine rotor wheel space and the HPPS bypass cavity to modulate the cooling air supplied to the forward turbine rotor wheel space from the HPPS bypass cavity. The metering device modulates the cooling air based on at least one operating condition of the turbine.Type: ApplicationFiled: January 4, 2012Publication date: July 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventor: Jason Nathaniel Cook
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Publication number: 20100215480Abstract: Systems and methods for controlling compressor extraction air flows from a compressor of a turbine system during engine turn down are provided. In one embodiment, a method for controlling compressor extraction air flows from a compressor of a turbine system during turn down includes a control unit monitoring one or more operating parameters of a turbine system associated with an exit temperature of a combustor of the turbine system. The method further includes the control unit detecting one or more operating parameters meeting or exceeding a threshold associated with a decrease in the exit temperature of the combustor. In response to detecting one or more operating parameter meeting or exceeding the threshold, a control signal is transmitted to at least one variable orifice located in the turbine system causing at least one variable orifice to alter at least one extraction air flow from the compressor.Type: ApplicationFiled: February 25, 2009Publication date: August 26, 2010Applicant: GENERAL ELECTRIC COMPANYInventors: David Leach, Jason Nathaniel Cook, Chi Ming Ho