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公开(公告)号：US20160258629A1
公开(公告)日：2016-09-08
申请号：US15059143
申请日：2016-03-02
Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.
Abstract translation: 燃气轮机系统包括涡轮机燃烧器。 涡轮机燃烧器包括耦合到涡轮机燃烧器的头端的一个或多个第一燃料喷射器，并且构造成将燃料的第一部分输送到涡轮机燃烧器的燃烧部分的第一轴向位置。 涡轮机燃烧器还包括一个或多个第二燃料喷射器，该第二燃料喷射器在头端部的轴向下游连接到涡轮机燃烧器，并且构造成将燃料的第二部分输送到涡轮机燃烧器的燃烧部分的第二轴向位置，第二轴向位置 位于第一轴向位置的下游。 燃气轮机系统还包括控制器，该控制器被配置为输送燃料的第一和第二部分，使得在涡轮机燃烧器的整个燃烧部分内的燃料和氧化剂的燃烧处于规定的当量比。
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公开(公告)号：US20150253011A1
公开(公告)日：2015-09-10
申请号：US14719356
申请日：2015-05-22
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Derrick Walter Simons , Gregory Allen Boardman , Bryan Wesley Romig , Kara Edwards , Michael John Hughes
CPC classification number: F23R3/286 , F23C7/004 , F23C2900/07001 , F23D14/08 , F23R3/14 , F23R3/343 , F23R2900/03343
Abstract: A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits where each premix conduit has an upstream end defining an opening and having a central axis and downstream end defining an outlet and having a central axis where the central axis of the downstream end is non-parallel with a central axis of a center body of the fuel/air nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix conduits and may include air jets that direct air radially outwardly from the premix conduits.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有承载至少一个燃料/空气喷嘴的头端部分。 每个燃料/空气喷嘴包括具有预混合管道的预混合先导喷嘴，其中每个预混管道具有限定开口的上游端，并且具有中心轴线和下游端限定出口，并且具有中心轴线，其中下游端的中心轴线不是 与燃料/空气喷嘴的中心体的中心轴平行。 预混合引导喷嘴可以包括从预混合管道径向向外设置的环形通道，并且可以包括从预混管道径向向外引导空气的空气射流。
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Patent Agency Ranking
3.发明申请TURBOMACHINE WITH TRANSITION PIECE HAVING DILUTION HOLES AND FUEL INJECTION SYSTEM COUPLED TO TRANSITION PIECE 有权带有过渡断面的涡轮机，具有与过渡段相连的稀释孔和燃油喷射系统公开(公告)号：US20140260261A1
公开(公告)日：2014-09-18
申请号：US13799764
申请日：2013-03-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Carey Edward Romoser , Derrick Walter Simons
IPC: F02C7/22
Abstract: A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes.
Abstract translation: 提供了一种涡轮机，其包括燃烧器和空气燃烧的燃烧器，设置用于接收来自燃烧器的燃烧产物的涡轮机，流体地介于燃烧器和涡轮机之间的过渡件，包括形成为限定稀释孔的主体 以允许空气进入燃烧器并且用于使得能够朝向从燃烧器到涡轮机的燃烧产物的主流的蒸汽喷射;以及燃料喷射系统，其被支撑地联接到过渡件，并被配置为朝向主流 燃烧产物从而恢复通过稀释孔实现的蒸汽喷射减少的燃烧产物的主流的火焰温度。
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公开(公告)号：US10480792B2
公开(公告)日：2019-11-19
申请号：US15059143
申请日：2016-03-02
IPC: F23R3/34 , F23R3/28 , F02C3/14 , F02C7/22 , F02C9/26 , F23L7/00 , F23N1/02 , F23N5/00 , F02C3/34 , F02C9/28 , F23R3/00
Abstract: A gas turbine system includes a turbine combustor. The turbine combustor includes one or more first fuel injectors coupled to a head end of the turbine combustor and configured to deliver a first portion of a fuel to a first axial position of a combustion section of the turbine combustor. The turbine combustor also includes one or more second fuel injectors coupled to the turbine combustor axially downstream of the head end and configured to deliver a second portion of the fuel to a second axial position of the combustion section of the turbine combustor, the second axial position being downstream of the first axial position. The gas turbine system also includes a controller configured to deliver the first and the second portions of the fuel such that combustion of the fuel and oxidant within the overall combustion section of the turbine combustor is at a defined equivalence ratio.
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公开(公告)号：US09291098B2
公开(公告)日：2016-03-22
申请号：US13676683
申请日：2012-11-14
Applicant: General Electric Company
Inventor： Wei Chen , Abdul Rafey Khan , Derrick Walter Simons
Abstract: A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes.
Abstract translation: 一种涡轮机，其包括燃料，其中燃料可燃以产生工作流体;涡轮机部分，其容纳用于发电操作的工作流体;其中附加燃料可燃烧的过渡件，所述过渡件被设置成运输 从燃烧器到涡轮部分的工作流体和连接到燃烧器和过渡件的分段燃烧系统。 分级燃烧系统被配置为以多种模式混合燃料和附加燃料的组分。
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公开(公告)号：US20140130477A1
公开(公告)日：2014-05-15
申请号：US13676683
申请日：2012-11-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Wei Chen , Abdul Rafey Khan , Derrick Walter Simons
Abstract: A turbomachine including a combustor in which fuel is combustible to produce a working fluid, a turbine section, which is receptive of the working fluid for power generation operations, a transition piece in which additional fuel is combustible, the transition piece being disposed to transport the working fluid from the combustor to the turbine section and a staged combustion system coupled to the combustor and the transition piece. The staged combustion system is configured to blend components of the fuel and the additional fuel in multiple modes.
Abstract translation: 一种涡轮机，其包括燃料，其中燃料可燃以产生工作流体;涡轮机部分，其容纳用于发电操作的工作流体;其中附加燃料可燃烧的过渡件，所述过渡件被设置成运输 从燃烧器到涡轮部分的工作流体和连接到燃烧器和过渡件的分段燃烧系统。 分级燃烧系统被配置为以多种模式混合燃料和附加燃料的组分。
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7.发明授权Turbomachine with transition piece having dilution holes and fuel injection system coupled to transition piece 有权具有过渡件的涡轮机具有稀释孔和连接到过渡件的燃料喷射系统公开(公告)号：US09279369B2
公开(公告)日：2016-03-08
申请号：US13799764
申请日：2013-03-13
Applicant: General Electric Company
Inventor： Carey Edward Romoser , Derrick Walter Simons
Abstract: A turbomachine is provided and includes a combustor in which fuel and air are combusted, a turbine disposed for reception of products of combustion from the combustor, a transition piece fluidly interposed between the combustor and the turbine and including a body formed to define dilution holes configured to allow air to enter the combustor and for enabling steam injection toward a main flow of the products of the combustion proceeding from the combustor to the turbine and a fuel injection system supportively coupled to the transition piece and configured to inject fuel toward the main flow of the products of the combustion to thereby restore a flame temperature of the main flow of the products of the combustion reduced by steam injection enabled by the dilution holes.
Abstract translation: 提供了一种涡轮机，其包括燃烧器和空气燃烧的燃烧器，设置用于接收来自燃烧器的燃烧产物的涡轮机，流体地介于燃烧器和涡轮机之间的过渡件，包括形成为限定稀释孔的主体 以允许空气进入燃烧器并且用于使得能够朝向从燃烧器到涡轮机的燃烧产物的主流的蒸汽喷射;以及燃料喷射系统，其被支撑地联接到过渡件，并被配置为朝向主流 燃烧产物从而恢复通过稀释孔实现的蒸汽喷射减少的燃烧产物的主流的火焰温度。
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