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公开(公告)号：US20210199298A1
公开(公告)日：2021-07-01
申请号：US16731207
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A combustor may include a combustor liner and flow sleeve. A high pressure air cools an outer surface of the combustor liner via openings in the flow sleeve, creating a lower pressure air in an annulus between the combustor liner and the flow sleeve. A first fuel nozzle is positioned at a primary combustion zone, and a second fuel nozzle is positioned at a secondary combustion zone of the liner. A fuel source is configured to deliver a fuel to the fuel nozzles. The fuel nozzles produce a premixture of high pressure air and the fuel, and produce a mixture of the premixture and the lower pressure air, prior to introducing the mixture to a respective primary or secondary combustion zone of the combustor. The combustor provides improved fuel premixing and is fuel flexible, and reduces pressure drop requirements. The combustor is usable in a can, annular, or segmented annular combustor assembly.
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公开(公告)号：US11047248B2
公开(公告)日：2021-06-29
申请号：US16012380
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
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公开(公告)号：US10995620B2
公开(公告)日：2021-05-04
申请号：US16014092
申请日：2018-06-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jonathan Dwight Berry , Srikanth Chandrudu Kottilingam
Abstract: The disclosure relates to turbomachine components which include one or more coating-capturing features for thermal insulation. A turbomachine component may include: a body having an exterior surface positioned within a hot gas path (HGP) section of a turbomachine; and a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises: a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature, a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and an indentation positioned between the first and second members.
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104.发明申请公开(公告)号：US20210095594A1
公开(公告)日：2021-04-01
申请号：US16587320
申请日：2019-09-30
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: Apparatuses for generating carbon particles and exhaust gas used by gas turbine systems are disclosed. One apparatus may include a decarbonization component combusting or reacting a mixture of a fuel and a mixing gas to generate the carbon particles and the exhaust gas and an exhaust conduit to receive the exhaust gas generated by the decarbonization component. The apparatus may also include a mixing duct in fluid communication with the exhaust conduit and the gas turbine system. The mixing duct may receive the exhaust gas and provide the exhaust gas to the gas turbine system to be used to produce a working fluid within the gas turbine system. The apparatus may further include a carbon particle collection component for receiving and storing the generated carbon particles.
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公开(公告)号：US10830442B2
公开(公告)日：2020-11-10
申请号：US15464400
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan
Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.
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Patent Agency Ranking
公开(公告)号：US10584880B2
公开(公告)日：2020-03-10
申请号：US15464443
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kevin Weston McMahan
Abstract: A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. An aft end portion of the fuel injection panel defines a turbine nozzle. One or more hook plates attached to the outer surfaces of the liner segments are used to mount the integrated combustor nozzle to an inner mounting ring or an outer mounting ring. A mounting strut or mounting tenon(s) attached to the liner segments may also be employed.
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公开(公告)号：US10563869B2
公开(公告)日：2020-02-18
申请号：US15464452
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F23R3/34
Abstract: The present disclosure is directed to the operation and turndown of a segmented annular combustion system. The method includes injecting, via a fuel nozzle, a combustible mixture into a primary combustion zone between an adjacent pair of integrated combustor nozzles and burning the combustible mixture. The method further includes flowing air and injecting fuel into a premixing channel defined within a first integrated combustor nozzle to produce a second combustible mixture. The second combustible mixture is injected into a secondary combustion zone where it is combusted. The flow of combustion gases is accelerated, via turbine nozzles of the integrated combustor nozzles, toward turbine blades of a downstream turbine section. The method permits turndown of the combustion system by reducing or shutting off fuel to various components of the combustion system.
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公开(公告)号：US10520194B2
公开(公告)日：2019-12-31
申请号：US15464411
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: The present disclosure is directed to a radially stacked fuel injection module for a segmented annular combustion system. The fuel injection module includes a bundled tube fuel nozzle portion and a plurality of fuel injection lances. In one instance, a first set of fuel injection lances and a second set of fuel injection lances share a housing with the bundled tube fuel nozzle. The first and second sets of fuel injection lances are radially stacked, each set of lances being in communication with a respective injector fuel plenum. The fuel injection lances deliver fuel to a respective premixing channel formed between the side walls of an integrated combustor nozzle, an aft end of which defines a turbine nozzle. In another instance, the bundled tube fuel nozzle may be provided as a radially inner fuel nozzle and a radially outer fuel nozzle, each with a respective bundled tube fuel plenum.
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公开(公告)号：US20190390553A1
公开(公告)日：2019-12-26
申请号：US16014092
申请日：2018-06-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jonathan Dwight Berry , Srikanth Chandrudu Kottilingam
Abstract: The disclosure relates to turbomachine components which include one or more coating-capturing features for thermal insulation. A turbomachine component may include: a body having an exterior surface positioned within a hot gas path (HGP) section of a turbomachine; and a coating-capturing feature mounted on the exterior surface of the body and in thermal communication with the HGP section of the turbomachine, wherein the coating-capturing feature comprises: a first member positioned on the exterior surface of the body, the first member having at least one outer sidewall defining a first perimeter of the coating-capturing feature, a second member positioned on the first member and having at least one outer sidewall defining a second perimeter of the coating-capturing feature, wherein the first member separates the second member from the exterior surface of the body, and an indentation positioned between the first and second members.
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公开(公告)号：US10352571B2
公开(公告)日：2019-07-16
申请号：US14996287
申请日：2016-01-15
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Gregory Scott Means
Abstract: A catalytic ignition system includes a gas fuel supply and a catalytic igniter that is in fluid communication with the gas fuel supply. The catalytic igniter comprises a metallic shell, a catalyst disposed within the metallic shell and a fuel tube that is oriented so as to direct a flow of gas fuel from the gas fuel supply across the catalyst and towards a downstream end of the metallic shell.
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