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公开(公告)号：US10830443B2
公开(公告)日：2020-11-10
申请号：US15391450
申请日：2016-12-27
Applicant: General Electric Company
Inventor： Akilezkrishnamurthy Arthanari , Mihir Lal , James Harper , Douglas Edward Dean , Abhijit Prabhakar Kulkarni
Abstract: This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.
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公开(公告)号：US10563594B2
公开(公告)日：2020-02-18
申请号：US15295559
申请日：2016-10-17
Applicant: General Electric Company
Inventor： James Harper , Akilez Krishnamurthy Arthanari
Abstract: A system includes a combustor assembly which receives a fuel-oxidant mixture. The system includes a control valve which controls a fuel flow into the combustor assembly. The system includes one or more sensors which measure one or more properties. The system includes a controller communicatively coupled to the one or more sensors and the control valve. The controller receives data from the one or more sensors indicative of operating conditions of the combustor assembly. The controller determines a predicted fuel flow for a first fuel line of a plurality of fuel lines based in part on the data received from the one or more sensors. The controller calculates a difference between a commanded fuel flow and the predicted fuel flow. The controller adjusts an operation of the control valve associated with a gas turbine engine when the difference is greater than a threshold.
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公开(公告)号：US10330015B2
公开(公告)日：2019-06-25
申请号：US14865936
申请日：2015-09-25
Applicant: General Electric Company
Inventor： James Harper , Akilez Krishnamurthy Arthanari
Abstract: In one embodiment, a system is provided. The system includes a turbine control system, comprising a processor. The processor is configured to receive an input for transitioning between a normal load path (NLP) of a turbine system and a cold load path (CLP) of the turbine system. The processor is additionally configured to determine a carbon monoxide (CO) setpoint based on the input. The processor is further configured to apply a temperature control based on the CO setpoint, wherein the normal load path comprises higher emissions temperatures as compared to the cold load path.
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公开(公告)号：US20190178498A1
公开(公告)日：2019-06-13
申请号：US15838149
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Matthew Bernard Wilson , James Harper , Yon Han Chong , Charlie Edmond Jones
Abstract: A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.
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公开(公告)号：US20190178497A1
公开(公告)日：2019-06-13
申请号：US15838172
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Benjamin Robert Ryan , Gilbert Otto Kraemer
Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
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Patent Agency Ranking
16.发明申请SYSTEM AND METHOD FOR OPERATING A DRY LOW NOx COMBUSTOR IN A NON-PREMIX MODE 审中-公开在非优先模式下操作干燥低NOx燃烧器的系统和方法公开(公告)号：US20170058769A1
公开(公告)日：2017-03-02
申请号：US15237676
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Daniel Doyle Vandale , Michael Anthony Cocca , James Harper
IPC: F02C3/30
CPC classification number: F02C3/30
Abstract: A system for operating a combustor in a non-Premix mode of operation includes a combustor comprising a plurality of primary fuel nozzles annularly arranged around a center fuel nozzle, a fuel supply system that is fluidly coupled to the plurality of primary fuel nozzles and the center fuel nozzle, a steam injection system that is fluidly coupled to the fuel supply system and to at least one of the plurality of primary fuel nozzles or the center fuel nozzle and a controller. The controller is electronically coupled to the fuel supply system and the steam injection system. The controller is programmed to initiate the steam injection system to inject a flow of superheated steam into a flow of fuel from the fuel supply system upstream from at least one of the plurality of primary fuel nozzles or the center fuel nozzle during a non-Premix mode of operation of the combustor.
Abstract translation: 用于在非预混合操作模式下操作燃烧器的系统包括：燃烧器，包括围绕中心燃料喷嘴环形排列的多个主要燃料喷嘴;燃料供应系统，其流体地联接到多个主要燃料喷嘴和中心 燃料喷嘴，流体耦合到燃料供应系统和多个主燃料喷嘴或中心燃料喷嘴中的至少一个的控制器的蒸汽喷射系统。 控制器电连接到燃料供应系统和蒸汽喷射系统。 控制器被编程为启动蒸汽喷射系统，以在非预混模式期间将过热蒸汽流喷射到来自多个主燃料喷嘴或中心燃料喷嘴中的至少一个上游的燃料供应系统的燃料流中 的燃烧器的操作。
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公开(公告)号：US11187415B2
公开(公告)日：2021-11-30
申请号：US15838172
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Benjamin Robert Ryan , Gilbert Otto Kraemer
Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
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公开(公告)号：US11137144B2
公开(公告)日：2021-10-05
申请号：US15838149
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Matthew Bernard Wilson , James Harper , Yon Han Chong , Charlie Edmond Jones
Abstract: A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.
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公开(公告)号：US20190186749A1
公开(公告)日：2019-06-20
申请号：US15845338
申请日：2017-12-18
Applicant: General Electric Company
Inventor： James Harper , Neal William Grooms , Yon Han Chong , Benjamin Robert Ryan
CPC classification number: F23R3/286 , F02C3/30 , F05D2240/35 , F05D2260/212 , F23D14/58 , F23R3/343
Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
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公开(公告)号：US20180149363A1
公开(公告)日：2018-05-31
申请号：US15391450
申请日：2016-12-27
Applicant: General Electric Company
Inventor： Akilezkrishnamurthy Arthanari , Mihir Lal , James Harper , Douglas Edward Dean , Abhijit Prabhakar Kulkarni
Abstract: This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor.
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