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公开(公告)号：US11371706B2
公开(公告)日：2022-06-28
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
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：US10816203B2
公开(公告)日：2020-10-27
申请号：US15838193
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 , Gilbert Otto Kraemer
Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.
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公开(公告)号：US10443854B2
公开(公告)日：2019-10-15
申请号：US15188163
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Neal William Grooms , James Harper , Yon Han Chong
Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.
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公开(公告)号：US20170363294A1
公开(公告)日：2017-12-21
申请号：US15188190
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Neal William Grooms , James Harper , Yon Han Chong
CPC classification number: F23R3/286 , F02C7/22 , F02C7/222 , F05D2220/32 , F23R3/28 , F23R3/283 , F23R3/343 , F23R2900/03343
Abstract: A premix pilot nozzle and fuel nozzle assembly are disclosed herein. The premix pilot nozzle includes a nozzle body having a forward wall axially spaced from an aft wall and an outer band that extends axially between the forward wall and the aft wall. An air tube extends coaxially within the nozzle body and defines a cooling air plenum within the nozzle body. A fuel tube extends coaxially within the nozzle body and circumferentially surrounds the air tube so as to define a fuel inlet plenum therebetween. A fuel distribution plenum is defined within the nozzle body and is in fluid communication with the fuel inlet plenum. The nozzle body further includes a plurality of premix tubes. Each premix tube extends helically around the fuel tube within the fuel distribution plenum. One or more of the premix tubes is in fluid communication with the fuel distribution plenum.
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公开(公告)号：US20170363293A1
公开(公告)日：2017-12-21
申请号：US15188163
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Neal William Grooms , James Harper , Yon Han Chong
CPC classification number: F23R3/286 , F02C7/222 , F05D2220/32 , F23R3/343 , F23R2900/03343
Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.
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Patent Agency Ranking
公开(公告)号：US20190178496A1
公开(公告)日：2019-06-13
申请号：US15838193
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 , Gilbert Otto Kraemer
Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.
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7.发明申请SYSTEM AND METHOD FOR MAINTAINING EMISSIONS COMPLIANCE WHILE OPERATING A GAS TURBINE AT TURNDOWN CONDITION 审中-公开在维修条件下运行气体涡轮时维持排放合格的系统和方法公开(公告)号：US20170058784A1
公开(公告)日：2017-03-02
申请号：US15237726
申请日：2016-08-16
Applicant: General Electric Company
Inventor： Daniel Doyle Vandale , Michael Anthony Cocca , Joseph Phillip Klosinski , Mihir Kumar Lal , James Harper
IPC: F02C9/18 , F02C7/228 , F23R3/34 , F01D25/30 , F01N3/10 , F04D29/32 , F04D29/54 , F01D5/02 , F02C3/04 , F02C3/30
CPC classification number: F02C9/18 , F01D25/30 , F01N3/106 , F02C3/30 , F02C9/20 , F04D29/541 , F04D29/563 , F05D2250/51 , F05D2270/082 , F23R3/346 , Y02E20/16
Abstract: A system and related method for maintaining emissions compliance while operating a gas turbine in turndown mode are disclosed herein. The system includes a gas turbine including a compressor, a combustor, a turbine and an exhaust section. The combustor comprises a plurality of axially staged fuel injectors positioned downstream from a plurality of primary fuel nozzles and a center fuel nozzle. The gas turbine further comprises a bleed air extraction port that is in fluid communication with at least one of the compressor, a compressor discharge casing or the combustor. The system further includes a controller programmed to bleed compressed air from the bleed air extraction port and to energize the plurality of axially staged fuel injectors during turndown operation of the gas turbine.
Abstract translation: 本文公开了一种用于在以下降模式操作燃气轮机时维持排放顺应性的系统和相关方法。 该系统包括燃气轮机，其包括压缩机，燃烧器，涡轮机和排气部分。 燃烧器包括位于多个主燃料喷嘴和中心燃料喷嘴下游的多个轴向分段的燃料喷射器。 燃气轮机还包括与压缩机，压缩机排放壳体或燃烧器中的至少一个流体连通的排气口。 该系统还包括控制器，该控制器被编程为从排气引出口排放压缩空气，并且在燃气轮机的降压操作期间激励多个轴向分级的燃料喷射器。
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8.发明申请SYSTEM AND METHOD FOR DECOUPLING STEAM PRODUCTION DEPENDENCY FROM GAS TURBINE LOAD LEVEL 审中-公开从燃气涡轮机负荷水平降低蒸汽产生依赖性的系统和方法公开(公告)号：US20170058770A1
公开(公告)日：2017-03-02
申请号：US15237694
申请日：2016-08-16
Applicant: General Electric Company
CPC classification number: F02C3/34 , F01K11/02 , F01K13/02 , F01N3/10 , F01N5/02 , F02C3/13 , Y02E20/14 , Y02E20/16 , Y02P80/15
Abstract: A system for decoupling steam production dependency from gas turbine load includes a gas turbine having an inlet system, a compressor, a combustor and a turbine. The combustor includes a plurality of axially staged fuel injectors positioned downstream from a plurality of primary fuel nozzles and a center fuel nozzle. The gas turbine further includes at least one bleed air extraction port that is in fluid communication with at least one of the compressor, a compressor discharge casing or the combustor. The system also includes a diluent injection system that is in fluid communication with the combustor and an exhaust section that is disposed downstream from the turbine. The exhaust section includes an oxidation catalyst system and a heat recovery steam generator.
Abstract translation: 用于将蒸汽生产依赖性与燃气轮机负载分离的系统包括具有入口系统，压缩机，燃烧器和涡轮机的燃气轮机。 燃烧器包括位于多个主燃料喷嘴和中心燃料喷嘴下游的多个轴向分段的燃料喷射器。 所述燃气轮机还包括至少一个与所述压缩机，压缩机排出壳体或所述燃烧器中的至少一个流体连通的排气口。 该系统还包括与燃烧器流体连通的稀释剂注入系统和设置在涡轮机下游的排气部分。 排气部分包括氧化催化剂系统和热回收蒸汽发生器。
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公开(公告)号：US20180106197A1
公开(公告)日：2018-04-19
申请号：US15295559
申请日：2016-10-17
Applicant: General Electric Company
Inventor： James Harper , Akilez Krishnamurthy Arthanari
CPC classification number: F02C9/263 , F05D2260/80
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：US20170089267A1
公开(公告)日：2017-03-30
申请号：US14865936
申请日：2015-09-25
Applicant: General Electric Company
Inventor： James Harper , Akilez Krishnamurthy Arthanari
CPC classification number: F02C7/26 , F02C9/26 , F02C9/266 , F02C9/54 , F05D2270/08 , F05D2270/0831 , G01M15/14 , Y02T50/677
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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