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    Automated tuning of gas turbine combustion systems
    11.
    发明授权
    Automated tuning of gas turbine combustion systems 有权
    燃气轮机燃烧系统自动调谐

    公开(公告)号：US09267443B2

    公开(公告)日：2016-02-23

    申请号：US13542222

    申请日：2012-07-05

    Applicant: Christopher Chandler

    Inventor： Christopher Chandler

    IPC: F01D17/00 ,  F02C9/28 ,  F23N1/00 ,  F23N5/00 ,  F23N5/24 ,  F23R3/34

    CPC classification number: F02C9/28 ,  F05D2220/32 ,  F05D2260/80 ,  F05D2270/082 ,  F05D2270/083 ,  F05D2270/20 ,  F05D2270/303 ,  F05D2270/31 ,  F23N1/002 ,  F23N5/003 ,  F23N5/242 ,  F23N2041/20 ,  F23R3/34 ,  F23R2900/00013 ,  G05B13/021

    Abstract: The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

    Abstract translation: 本公开提供了一种用于调节燃气轮机的操作的调谐系统。 该系统包括用于控制涡轮机的操作控制元件的操作涡轮机控制器，其包括涡轮机燃料分配或燃料温度中的至少一个。 该系统还具有与涡轮机控制器通信的调谐控制器。 调谐控制器被配置为根据以下步骤调整涡轮机的操作：接收关于涡轮机的操作数据，提供调谐问题的层级，确定感测到的操作数据是否在预定操作限度内并产生一个或多个指示器。 如果操作数据不在预定的操作限制内，则调谐控制器将对一个或多个指示器进行排序以确定主要调谐问题，并且基于主要调谐关注调整涡轮机的运行。 本文还提供了一种用于调谐的方法和计算机可读介质。

    System and method for reducing combustion dynamics in a combustor
    13.
    发明授权
    System and method for reducing combustion dynamics in a combustor 有权
    用于减少燃烧器中的燃烧动力学的系统和方法

    公开(公告)号：US09121612B2

    公开(公告)日：2015-09-01

    申请号：US13409309

    申请日：2012-03-01

    Applicant: Jong Ho Uhm ,  Thomas Edward Johnson ,  Baifang Zuo ,  William David York

    Inventor： Jong Ho Uhm ,  Thomas Edward Johnson ,  Baifang Zuo ,  William David York

    IPC: F23R3/28 ,  F23R3/00 ,  F02C3/30 ,  F23R3/54 ,  F23R3/32 ,  F23D14/62

    CPC classification number: F23R3/286 ,  F02C3/30 ,  F23C2900/07022 ,  F23D14/62 ,  F23R3/002 ,  F23R3/32 ,  F23R3/54 ,  F23R2900/00013

    Abstract: A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle.

    Abstract translation: 用于减少燃烧器中的燃烧动力学的系统包括具有从下游表面轴向分离的上游表面的端盖，并且管束从上游表面延伸穿过下游表面。 管束内的分隔器限定了一个沿轴向延伸穿过下游表面的稀释剂通道，与分隔器流体连通的稀释剂供应器提供稀释剂流向稀释剂通道。 一种用于减少燃烧动力学的方法，包括使燃料通过管束流动，使稀释剂流过管束内的稀释剂通道，其中稀释剂通道轴向延伸通过端盖的至少一部分进入燃烧室，以及 在管束与至少一个其它相邻管束之间的燃烧室中形成稀释剂阻挡层。

    COMBUSTION ARRANGEMENT AND TURBINE COMPRISING A DAMPING FACILITY
    16.
    发明申请
    COMBUSTION ARRANGEMENT AND TURBINE COMPRISING A DAMPING FACILITY 有权
    燃烧装置和包括阻尼装置的涡轮机

    公开(公告)号：US20140196468A1

    公开(公告)日：2014-07-17

    申请号：US14237870

    申请日：2012-07-24

    Applicant: Ghenadie Bulat

    Inventor： Ghenadie Bulat

    IPC: F23R3/26 ,  F02C7/24 ,  F23R3/54

    CPC classification number: F23R3/26 ,  F02C7/24 ,  F23R3/54 ,  F23R2900/00013

    Abstract: A combustion arrangement for a turbine is provided including: a casing; a combustion chamber within the casing, an inner casing volume may be defined as a volume inside the casing but outside the combustion chamber; a partitioning wall partitioning the inner casing volume into first and second volume portions, the partitioning wall may have at least one aperture to allow fluid communication between the first and second volume portions; and a valve may be arranged at the casing to allow an outgoing fluid flow from the inner casing volume to an outside of the casing depending on a valve operating position. The combustion chamber has a combustion entry port for supplying an oxidant into the combustion chamber, where the combustion entry port may be in fluid communication with the first volume portion. The arrangement may be adapted to adjust the valve operating position for damping an oscillation of the arrangement.

    Abstract translation: 提供一种用于涡轮机的燃烧装置，包括：壳体; 在壳体内的燃烧室，内壳容积可以被定义为壳体内部但在燃烧室外部的体积; 分隔壁将内部壳体体积分成第一和第二体积部分，分隔壁可以具有至少一个孔，以允许第一和第二体积部分之间的流体连通; 并且阀可以布置在壳体处，以允许输出流体根据阀操作位置从内壳体积流到壳体的外部。 燃烧室具有燃烧入口，用于向燃烧室供应氧化剂，其中燃烧入口与第一容积部分流体连通。 该装置可以适于调整阀操作位置以阻尼该装置的振荡。

    ACTIVE CONTROL FUEL NOZZLE SYSTEM
    17.
    发明申请
    ACTIVE CONTROL FUEL NOZZLE SYSTEM 审中-公开
    主动控制燃油喷嘴系统

    公开(公告)号：US20140165576A1

    公开(公告)日：2014-06-19

    申请号：US13714113

    申请日：2012-12-13

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Wei CHEN ,  Keith McManus ,  John Lipinski ,  Carolyn Antoniono

    IPC: F02C9/26

    CPC classification number: F02C9/26 ,  F23R3/28 ,  F23R2900/00013 ,  F23R2900/03281

    Abstract: It is desirable for a gas turbine system to operate in a wide range operating conditions. However, under certain conditions there exist dynamic boundaries that limit a combustor from reaching its designated condition. Perturbation devices formed of electromagnetic plates can be incorporated into fuel nozzles of the combustor to influence the dynamics so that the range of operating conditions can be widened. The perturbation devices vibrate according to the perturbation signals provided from a dynamics controller. The vibration characteristics of the perturbation devices can be controlled by controlling the attributes of the perturbation signals. The vibrations influence the dynamics of fluid—fuel, oxidant, or both—flowing past the perturbation devices within the fuel nozzles.

    Abstract translation: 期望燃气轮机系统在宽范围的操作条件下操作。 然而，在某些条件下，存在限制燃烧器达到其指定条件的动态边界。 由电磁板形成的扰动装置可以并入燃烧器的燃料喷嘴中，以影响动力学，从而能够扩大工作条件的范围。 扰动装置根据从动力学控制器提供的扰动信号而振动。 可以通过控制扰动信号的属性来控制扰动装置的振动特性。 振动影响流体 - 燃料，氧化剂或两者流过燃料喷嘴内的扰动装置的动力学。

    Active combustion control for turbine engine
    18.
    发明授权
    Active combustion control for turbine engine 有权
    涡轮发动机主动燃烧控制

    公开(公告)号：US08650880B1

    公开(公告)日：2014-02-18

    申请号：US12705905

    申请日：2010-02-15

    Applicant: Harvey B. Jansen ,  Matthew C. Caspermeyer

    Inventor： Harvey B. Jansen ,  Matthew C. Caspermeyer

    IPC: F02C7/24

    CPC classification number: F02C9/263 ,  F02C7/232 ,  F23R3/28 ,  F23R2900/00013

    Abstract: An active combustion control device provides modulated fuel flow to the combustor of a turbine engine to mitigate combustion instability. The device includes a valve unit and an electronic valve driver controlling translation and rotation components in the valve unit that drive a metering member having a modulating end. The axial position and rotation of the end geometries relative to static flow ports inside the valve unit modulate the fuel flowing from the valve unit to the combustor atomizer. The amplitude and frequency of the modulated fuel flow match that of the instable combustor fuel flow and the phase is offset by 180 degrees so that the resultant fuel flow is at or near a stable state.

    Abstract translation: 主动燃烧控制装置向涡轮发动机的燃烧器提供调节的燃料流，以减轻燃烧不稳定性。 该装置包括阀单元和电子阀驱动器，其控制阀单元中的平移和旋转部件，其驱动具有调制端的计量构件。 端部几何形状相对于阀单元内的静态流动端口的轴向位置和旋转调节从阀单元流向燃烧器雾化器的燃料。 调制燃料流的振幅和频率与不稳定的燃烧器燃料流量的幅度和频率相匹配，相位偏移了180度，使得所得到的燃料流量处于或接近稳定状态。

    Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
    19.
    发明授权
    Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities 有权
    燃气轮机发动机燃烧器采用周边声学还原使用火焰温度不均匀性

    公开(公告)号：US08631656B2

    公开(公告)日：2014-01-21

    申请号：US12059256

    申请日：2008-03-31

    Applicant: Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

    Inventor： Allen Michael Danis ,  Mark Anthony Mueller ,  Timothy James Held ,  Steven Marakovits

    IPC: F23R3/34 ,  F02C7/236

    CPC classification number: F23R3/50 ,  F23R2900/00013 ,  F23R2900/00014

    Abstract: A gas turbine engine combustor includes an annulus with one or more circular rows of burners and a means for providing a number of equiangular spaced apart flame temperature nonuniformities around the annulus during engine operation. The number of the flame temperature nonuniformities being equal to a circumferential acoustic mode to be attenuated in the combustor (i.e three, five, or seven). Fuel lines and/or water lines in supply communication with the burners and metering orifices in a portion of the fuel lines and/or the water lines may be used to produce the flame temperature nonuniformities. The annulus of the burners may have an equal number of equiangular spaced apart first and second arcuate segments of the burners and a means for operating the burners in the first segments and operating the burners in the second segments at different first and second flame temperatures respectively.

    Abstract translation: 燃气涡轮发动机燃烧器包括具有一个或多个圆形排燃烧器的环形空间，以及用于在发动机运行期间在环空周围提供多个等角间隔开的火焰温度不均匀性的装置。 火焰温度不均匀性的数量等于在燃烧器中被衰减的周向声学模式（即三个，五个或七个）。 可以使用与燃料管线和/或水管线的一部分中的燃烧器和计量孔供应连通的燃料管线和/或水管线来产生火焰温度不均匀性。 燃烧器的环带可以具有相等数量的燃烧器的等角度间隔开的第一和第二弧形段，以及用于在第一段中操作燃烧器并分别在不同的第一和第二火焰温度下操作第二段中的燃烧器的装置。

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