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公开(公告)号：US20210301736A1
公开(公告)日：2021-09-30
申请号：US16833938
申请日：2020-03-30
Applicant: General Electric Company
Inventor： Jayaprakash Natarajan , Willy Steve Ziminsky , Mark William Pinson
Abstract: A method for selectively operating a combustor head end assembly is provided. The combustor head end assembly includes a plurality of bundled tube fuel nozzles. The method includes opening a first fuel circuit of a plurality of fuel circuits. The first fuel circuit of the plurality of fuel circuits is fluidly coupled to a first nozzle group, and the first nozzle group includes one bundled tube fuel nozzle of the plurality of bundled tube fuel nozzles. The method further includes adjusting an airflow received by the plurality of bundled tube fuel nozzles in response to opening the first fuel circuit of the plurality of fuel circuits. The airflow is adjusted based on an emissions output requirement corresponding with the first nozzle group. The method also includes firing the first nozzle group.
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公开(公告)号：US10690057B2
公开(公告)日：2020-06-23
申请号：US15496021
申请日：2017-04-25
Applicant: General Electric Company
Inventor： Donald Mark Bailey , Mark William Pinson , Lucas John Stoia
Abstract: The present disclosure is directed to an end cover assembly for a combustor of a turbomachine. The end cover assembly includes an end cover and a bundled tube fuel nozzle assembly positioned downstream from the end cover. The bundled tube fuel nozzle assembly includes a plurality of fuel nozzle tubes. A flame detector sight tube couples to the end cover. The flame detector sight tube is aligned with one of the fuel nozzle tubes.
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公开(公告)号：US20210404392A1
公开(公告)日：2021-12-30
申请号：US16916422
申请日：2020-06-30
Applicant: General Electric Company
Inventor： Steven C. Castellaw , David August Snider , Mark William Pinson , Mark Mitchell , Robert Walter Arnold , Christopher Grant Cooper
Abstract: A method of igniting liquid fuel in a turbomachine combustor is provided. The method includes a step of initiating a flow of gaseous fuel from a gaseous fuel supply to a gaseous fuel nozzle. The method further includes a step of initiating a flow of liquid fuel from a liquid fuel supply to a primary liquid fuel cartridge. After initiating both the flow of gaseous fuel and the flow of liquid fuel, the method includes a step of igniting the flow of gaseous fuel and the flow of liquid fuel with an igniter. The method further includes a step of terminating the flow of gaseous fuel from the gaseous fuel supply to the gaseous fuel nozzle.
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公开(公告)号：US20180363910A1
公开(公告)日：2018-12-20
申请号：US15625077
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Lucas John Stoia , Mark William Pinson , Geoffrey David Myers
Abstract: A system and method for igniting liquid fuel in a gas turbine combustor is provided. A liquid fuel cartridge, which is located within the head end, is in flow communication with a liquid fuel supply. A gaseous fuel nozzle is located proximate the liquid fuel cartridge and in flow communication with an auxiliary gaseous fuel supply. A controller is in communication with the liquid fuel supply, the auxiliary gaseous fuel supply, and an igniter located proximate or within the head end. The controller is configured to sequentially: initiate a gaseous fuel flow from the auxiliary gaseous fuel supply to the gaseous fuel nozzle; initiate the igniter to combust the gaseous fuel flow; initiate a liquid fuel flow from the liquid fuel supply to the liquid fuel cartridge; and terminate the gaseous fuel flow from the auxiliary gaseous fuel supply.
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5.发明授权公开(公告)号：US10982593B2
公开(公告)日：2021-04-20
申请号：US15625031
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Ronald James Chila , Mark William Pinson , Baifang Zuo , Lucas John Stoia , Timothy James Purcell
Abstract: A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein.
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Patent Agency Ranking
公开(公告)号：US20180363551A1
公开(公告)日：2018-12-20
申请号：US15625031
申请日：2017-06-16
Applicant: General Electric Company
Inventor： Ronald James Chila , Mark William Pinson , Baifang Zuo , Lucas John Stoia , Timothy James Purcell
Abstract: A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein.
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7.发明申请GAS TURBINE AND METHOD OF CONTROLLING A GAS TURBINE AT PART-LOAD CONDITION 审中-公开气体涡轮机和控制部分负荷条件下的气体涡轮机的方法公开(公告)号：US20140182297A1
公开(公告)日：2014-07-03
申请号：US13733313
申请日：2013-01-03
Applicant: GENERAL ELECTRIC COMPANY
IPC: F02C9/00
Abstract: A gas turbine includes a compressor section, a combustion section downstream from the compressor section, a turbine section downstream from the combustion section, and a controller. The controller controls the operation of the gas turbine at a reduced load, and is capable of querying a database including multiple sets of operational parameters for the gas turbine correlated with at least one measured output response at each set of operational parameters. One of the sets of operational parameters provides a desired gas turbine load that meets a target level for the output response. Related methods are also disclosed.
Abstract translation: 燃气轮机包括压缩机部分，压缩机部分下游的燃烧部分，燃烧部分下游的涡轮部分和控制器。 控制器以减小的负载控制燃气轮机的操作，并且能够查询数据库，其包括与在每组操作参数下的至少一个测量的输出响应相关的燃气轮机的多组操作参数。 一组操作参数提供满足输出响应的目标水平的期望的燃气轮机负载。 还公开了相关方法。
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公开(公告)号：US11326521B2
公开(公告)日：2022-05-10
申请号：US16916422
申请日：2020-06-30
Applicant: General Electric Company
Inventor： Steven C. Castellaw , David August Snider , Mark William Pinson , Mark Mitchell , Robert Walter Arnold , Christopher Grant Cooper
Abstract: A method of igniting liquid fuel in a turbomachine combustor is provided. The method includes a step of initiating a flow of gaseous fuel from a gaseous fuel supply to a gaseous fuel nozzle. The method further includes a step of initiating a flow of liquid fuel from a liquid fuel supply to a primary liquid fuel cartridge. After initiating both the flow of gaseous fuel and the flow of liquid fuel, the method includes a step of igniting the flow of gaseous fuel and the flow of liquid fuel with an igniter. The method further includes a step of terminating the flow of gaseous fuel from the gaseous fuel supply to the gaseous fuel nozzle.
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公开(公告)号：US20210301722A1
公开(公告)日：2021-09-30
申请号：US16833954
申请日：2020-03-30
Applicant: General Electric Company
Inventor： Willy Steve Ziminsky , Mark William Pinson , Jayaprakash Natarajan , Lucas John Stoia
Abstract: Combustors, gas turbines, and associated methods of operation are provided. A method for operating a combustor includes firing a bundled tube fuel nozzle assembly within a combustion liner of the combustor to generate combustion gases at a first temperature within a first combustion zone length. The method further includes firing a fuel injector downstream from the bundled tube fuel nozzle assembly within the combustion liner of the combustor to generate combustion gases at a second temperature within a second combustion zone length. The first combustion zone length is less than the second combustion zone length. The combustion gases travel through the first combustion zone length in a first time period and through the second combustion zone length in a second time period. The second time period is less than the first time period.
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公开(公告)号：US20140311150A1
公开(公告)日：2014-10-23
申请号：US13864708
申请日：2013-04-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Mark William Pinson , Gregory Earl Jensen , Jason Charles Terry
CPC classification number: F23R3/286 , F23D14/24 , F23D2900/14004 , F23D2900/14021 , F23R3/14 , F23R3/32
Abstract: A fuel nozzle for use in a gas turbine includes a pre-mix flow passage for directing a flow segment of a flow of a working fluid through the fuel nozzle. A first swirler vane and a second swirler vane extend within the pre-mix flow passage. The first swirler vane provides a first wake region within the flow segment. The second swirler vane provides a second wake region within the flow segment. A fuel injection peg is disposed downstream from the first swirler vane and the second swirler vane. The fuel injection peg is positioned within the flow segment between the first wake region and the second wake region.
Abstract translation: 用于燃气轮机的燃料喷嘴包括用于引导工作流体流的流动段通过燃料喷嘴的预混流动通道。 第一旋流器叶片和第二旋流器叶片在预混合流动通道内延伸。 第一旋流器叶片在流动段内提供第一尾流区域。 第二旋流器叶片在流动段内提供第二尾流区域。 燃料喷射栓设置在第一旋流叶片和第二旋流叶片的下游。 燃料喷射栓定位在第一尾流区域和第二尾流区域之间的流动段内。
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