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公开(公告)号：US10690056B2
公开(公告)日：2020-06-23
申请号：US15464394
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan , Joseph Vincent Citeno , Kevin Weston McMahan
Abstract: A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.
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公开(公告)号：US10041681B2
公开(公告)日：2018-08-07
申请号：US14452568
申请日：2014-08-06
Applicant: General Electric Company
Inventor： Joseph Vincent Citeno , Thomas Edward Johnson
Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a primary stage nozzle in communication with a linear actuator and a number of stationary secondary nozzles surrounding the primary stage nozzle in whole or in part. The linear actuator varies the position of the primary stage nozzle with respect to the stationary secondary nozzles.
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3.发明申请SYSTEMS AND METHODS FOR VARIATION OF INJECTORS FOR COHERENCE REDUCTION IN COMBUSTION SYSTEM 有权喷射系统与燃烧系统相关降低喷射器的变更方法公开(公告)号：US20150345402A1
公开(公告)日：2015-12-03
申请号：US14288875
申请日：2014-05-28
Applicant: General Electric Company
CPC classification number: F02C7/24 , F01D9/023 , F05B2260/96 , F05B2260/966 , F05D2260/96 , F23D2210/00 , F23N1/022 , F23N5/242 , F23R3/28 , F23R3/346 , F23R2900/00013 , F23R2900/00014
Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.
Abstract translation: 一种系统包括具有第一燃烧器和第二燃烧器的燃气涡轮发动机。 第一燃烧器包括具有第一多个喷射器的第一燃料管道。 第一组多个喷射器沿着第一燃料路径设置在第一燃烧器内的第一构造中，并且第一多个喷射器构造成将燃料路由到第一燃烧室。 该系统还包括具有第二燃料管道的第二燃烧器，其具有第二多个喷射器。 第二组多个喷射器沿着第二燃料路径设置在第二燃烧器内的第二构造中，并且第二多个喷射器构造成将燃料路由到第二燃烧室。 第二配置相对于第一配置具有至少一个差异。
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公开(公告)号：US10605459B2
公开(公告)日：2020-03-31
申请号：US15464419
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , Matthew Troy Hafner , Joseph Vincent Citeno
Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.
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5.发明授权公开(公告)号：US09845732B2
公开(公告)日：2017-12-19
申请号：US14288875
申请日：2014-05-28
Applicant: General Electric Company
CPC classification number: F02C7/24 , F01D9/023 , F05B2260/96 , F05B2260/966 , F05D2260/96 , F23D2210/00 , F23N1/022 , F23N5/242 , F23R3/28 , F23R3/346 , F23R2900/00013 , F23R2900/00014
Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. The first combustor includes a first fuel conduit having a first plurality of injectors. The first plurality of injectors are disposed in a first configuration within the first combustor along a first fuel path, and the first plurality of injectors are configured to route a fuel to a first combustion chamber. The system further includes a second combustor having a second fuel conduit having a second plurality of injectors. The second plurality of injectors are disposed in a second configuration within the second combustor along a second fuel path, and the second plurality of injectors are configured to route the fuel to a second combustion chamber. The second configuration has at least one difference relative to the first configuration.
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Patent Agency Ranking
公开(公告)号：US20170356344A1
公开(公告)日：2017-12-14
申请号：US15687598
申请日：2017-08-28
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency. Specifically, the compressor discharge temperature may be modified by adjusting the inlet guide vanes of the compressor or by adjusting a temperature of air entering the compressor.
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公开(公告)号：US20170299187A1
公开(公告)日：2017-10-19
申请号：US15464419
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , Matthew Troy Hafner , Joseph Vincent Citeno
CPC classification number: F23R3/286 , F01D9/041 , F02C7/18 , F02C7/24 , F05D2220/30 , F05D2240/35 , F23R3/283 , F23R3/346 , F23R2900/03341
Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.
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公开(公告)号：US20170276369A1
公开(公告)日：2017-09-28
申请号：US15464394
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan , Joseph Vincent Citeno , Kevin Weston McMahan
Abstract: A segmented annular combustion system includes an alternating arrangement of fuel nozzles and integrated combustor nozzles. The fuel nozzles deliver fuel to the primary combustion zones. The integrated combustor nozzles include an inner liner segment, an outer liner segment, and a fuel injection panel extending between the liner segments. The fuel injection panel includes injection outlets on one or both side walls to deliver a combustible mixture to the secondary combustion zones. Each fuel injection panel, which provides a boundary between adjacent primary and secondary combustion zones, includes an aft end that defines a turbine nozzle. The segmented annular combustion system is part of a gas turbine.
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公开(公告)号：US09745896B2
公开(公告)日：2017-08-29
申请号：US13777724
申请日：2013-02-26
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Matthew Durham Collier , Scott Edward Sherman , Joseph Vincent Citeno
CPC classification number: F02C7/24 , F01D25/04 , F01D25/06 , F02C9/18 , F05D2260/96 , F05D2270/083 , F05D2270/10 , F05D2270/14 , F23R2900/00013
Abstract: Systems and methods for frequency separation in a gas turbine engine are provided herein. The systems and methods for frequency separation in a gas turbine engine may include determining a hot gas path natural frequency, determining a combustion dynamic frequency, and modifying a compressor discharge temperature to separate the combustion dynamic frequency from the hot gas path natural frequency.
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公开(公告)号：US20160040884A1
公开(公告)日：2016-02-11
申请号：US14452568
申请日：2014-08-06
Applicant: General Electric Company
Inventor： Joseph Vincent Citeno , Thomas Edward Johnson
CPC classification number: F23R3/346 , F02C3/04 , F02C7/222 , F02C9/20 , F05D2220/32 , F05D2260/60 , F23C5/06 , F23R3/22
Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a primary stage nozzle in communication with a linear actuator and a number of stationary secondary nozzles surrounding the primary stage nozzle in whole or in part. The linear actuator varies the position of the primary stage nozzle with respect to the stationary secondary nozzles.
Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的燃烧器。 燃烧器可以包括与线性致动器连通的初级级喷嘴以及围绕初级级喷嘴的多个固定次级喷嘴的整体或部分。 线性致动器改变主级喷嘴相对于固定次级喷嘴的位置。
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