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48 条记录 (耗时 0.028 秒)

    Combustor casing for combustion dynamics mitigation
    3.
    发明授权
    Combustor casing for combustion dynamics mitigation 有权
    用于燃烧动力学减轻的燃烧器套管

    公开(公告)号：US09447970B2

    公开(公告)日：2016-09-20

    申请号：US13067153

    申请日：2011-05-12

    申请人： Kwanwoo Kim ,  Dheeraj Sharma ,  Sven Bethke ,  Yongqiang Fu

    发明人： Kwanwoo Kim ,  Dheeraj Sharma ,  Sven Bethke ,  Yongqiang Fu

    IPC分类号： F23M5/00 ,  F02C7/24 ,  F23R3/00

    CPC分类号： F23R3/002 ,  F23R2900/00014

    摘要： A dampener or resonator is provided within a combustor casing to mitigate combustion dynamics. The combustor casing head end volume is reduced by the resonator to mitigate combustion dynamics. The resonator is formed by a ring shaped plate that carries a continuous inwardly protruding wall or segmented inwardly protruding wall portions. The resonator can be a stand alone part that is inserted into the combustor casing or it can be integrally formed with the combustor casing.

    摘要翻译： 在燃烧器壳体内设置阻尼器或谐振器以减轻燃烧动态。 通过谐振器减小燃烧器壳体头端部体积以减轻燃烧动力学。 谐振器由环形板形成，该环形板承载着连续的向内突出的壁或分段的向内突出的壁部分。 谐振器可以是插入到燃烧器壳体中的独立部件，或者可以与燃烧器壳体一体形成。

    Resonator assembly for mitigating dynamics in gas turbines
    5.
    发明授权
    Resonator assembly for mitigating dynamics in gas turbines 有权
    用于减轻燃气轮机动力学的谐振器组件

    公开(公告)号：US08408004B2

    公开(公告)日：2013-04-02

    申请号：US12485505

    申请日：2009-06-16

    申请人： Lewis Berkley Davis, Jr. ,  Fei Han ,  Shiva Srinivasan ,  Kapil Kumar Singh ,  Kwanwoo Kim ,  Venkateswarlu Narra

    发明人： Lewis Berkley Davis, Jr. ,  Fei Han ,  Shiva Srinivasan ,  Kapil Kumar Singh ,  Kwanwoo Kim ,  Venkateswarlu Narra

    IPC分类号： F02C3/00 ,  F23R3/46

    CPC分类号： F23R3/002 ,  F23M20/005 ,  F23R2900/00013 ,  F23R2900/00014

    摘要： A combustor for a gas turbine engine and related method is provided in which a plurality of combustor cans are selectively adapted with corresponding resonators. The resonators may, for example, be attached to every can in the consecutive arrangement of combustor cans, every other can, every third can or the like, and may be tuned to the same or first, second, third, etc. frequencies of operation. Such selective tuning is configured to suppress one or more of out-of-phase and in-phase dynamic interaction of streams discharged from adjacent combustor cans by changing the frequencies of pressure oscillation instabilities across the arrangement of consecutive cans.

    摘要翻译： 提供了一种用于燃气涡轮发动机的燃烧器和相关方法，其中多个燃烧器罐选择性地适应于相应的谐振器。 例如，谐振器可以在燃烧器罐的连续布置中，每隔一个可以，每隔三分之一或者类似地连接到每个罐，并且可以调谐到相同或第一，第二，第三等操作频率 。 这种选择性调谐被配置为通过改变跨连续罐排列的压力振荡不稳定性的频率来抑制从相邻燃烧器罐排出的流的异相和同相动态相互作用中的一个或多个。

    System and method for controlling combustion dynamics
    6.
    发明授权
    System and method for controlling combustion dynamics 有权
    控制燃烧动力学的系统和方法

    公开(公告)号：US08381530B2

    公开(公告)日：2013-02-26

    申请号：US12431095

    申请日：2009-04-28

    申请人： Kapil Kumar Singh ,  Fei Han ,  Shiva Srinivasan ,  Kwanwoo Kim

    发明人： Kapil Kumar Singh ,  Fei Han ,  Shiva Srinivasan ,  Kwanwoo Kim

    IPC分类号： F02C7/22

    CPC分类号： F23D14/48 ,  F02C7/222 ,  F02C9/28 ,  F05D2260/964 ,  F23D2900/14482 ,  F23N5/24 ,  F23R2900/00013

    摘要： A tunable fluid flow control system for controlling combustion dynamics in a combustor is disclosed. The control system includes a fuel supply path having an inlet portion, a first diverted portion, a second diverted portion, and an exit portion. A first diverted portion has a first length and a first diameter. A second diverted portion has a second length and a second diameter and spaced apart from the first diverted portion. The first and second diverted portions converge at a merging location. The exit portion is coupled to the merging location of the first and second diverted portions. At least one flow regulation device is coupled to the inlet portion and configured to divert fuel flow to the first and second diverted portions alternately to generate fuel flow perturbations at the merging location.

    摘要翻译： 公开了一种用于控制燃烧器中的燃烧动力学的可调流体流量控制系统。 控制系统包括具有入口部分，第一转向部分，第二转向部分和出口部分的燃料供给路径。 第一转向部分具有第一长度和第一直径。 第二转向部分具有第二长度和第二直径并且与第一转向部分间隔开。 第一和第二转向部分在合并位置收敛。 出口部分耦合到第一和第二转向部分的合并位置。 至少一个流量调节装置联接到入口部分并被配置成交替地将燃料流转移到第一和第二转向部分以在合并位置产生燃料流动扰动。

    Combustor with Fuel Staggering for Flame Holding Mitigation
    7.
    发明申请
    Combustor with Fuel Staggering for Flame Holding Mitigation 有权
    燃料燃烧器火焰控制减轻

    公开(公告)号：US20120167544A1

    公开(公告)日：2012-07-05

    申请号：US12983342

    申请日：2011-01-03

    申请人： David Kaylor Toronto ,  Kwanwoo Kim ,  Abdul Rafey Khan ,  Luis Flamand

    发明人： David Kaylor Toronto ,  Kwanwoo Kim ,  Abdul Rafey Khan ,  Luis Flamand

    IPC分类号： F02C3/30

    CPC分类号： F23R3/286 ,  F23D2900/14004 ,  F23D2900/14021 ,  F23R3/16 ,  F23R3/34 ,  F23R3/346 ,  F23R2900/03045

    摘要： The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.

    摘要翻译： 本申请提供了一种燃烧器。 燃烧器可包括其中具有空气流的气流通道。 流动障碍物可以位于空气流动路径内并且在其下游引起尾流或再循环区域。 多个燃料喷射器可以位于流动障碍物的下游。 燃料喷射器可将燃料流注入空气流动路径，使得尾气或再循环区域中的燃料和空气流不超过可燃性极限。

    SYSTEM AND METHOD FOR SUPPRESSING COMBUSTION INSTABILITY IN A TURBOMACHINE
    9.
    发明申请
    SYSTEM AND METHOD FOR SUPPRESSING COMBUSTION INSTABILITY IN A TURBOMACHINE 审中-公开
    用于抑制涡轮机燃烧不稳定性的系统和方法

    公开(公告)号：US20100192578A1

    公开(公告)日：2010-08-05

    申请号：US12363018

    申请日：2009-01-30

    申请人： Kapil Kumar Singh ,  Fei Han ,  Keith Robert McManus ,  Shivakumar Srinivasan ,  Kwanwoo Kim

    发明人： Kapil Kumar Singh ,  Fei Han ,  Keith Robert McManus ,  Shivakumar Srinivasan ,  Kwanwoo Kim

    IPC分类号： F02C1/00

    CPC分类号： F23R3/10 ,  F23R2900/00014

    摘要： A system for suppressing combustion instability in a turbomachine includes at least one combustion chamber operatively connected to the turbomachine, and at least one pre-mixer mounted to the at least one combustion chamber. The at least one pre-mixer is configured to receive an amount of fuel and an amount of air that is combined and discharged into the at least one combustion chamber. In addition, the turbomachine includes a combustion instability suppression system operatively associated with the at least one pre-mixer. The combustion instability suppression system is configured to create a combustion asymmetry. The combustion asymmetry facilitates combustion instability suppression in the turbomachine.

    摘要翻译： 用于抑制涡轮机中的燃烧不稳定性的系统包括至少一个可操作地连接到涡轮机的燃烧室，以及安装在至少一个燃烧室上的至少一个预混合器。 所述至少一个预混合器被配置为接收一定量的燃料和一定量的空气，所述空气被组合并排放到所述至少一个燃烧室中。 此外，涡轮机包括与至少一个预混合器可操作地相关联的燃烧不稳定性抑制系统。 燃烧不稳定性抑制系统被配置成产生燃烧不对称性。 燃烧不对称促进涡轮机中的燃烧不稳定性抑制。

    Premixer fuel nozzle for gas turbine engine
    10.
    发明授权
    Premixer fuel nozzle for gas turbine engine 有权
    燃气涡轮发动机预混合燃料喷嘴

    公开(公告)号：US09046262B2

    公开(公告)日：2015-06-02

    申请号：US13170133

    申请日：2011-06-27

    申请人： Kwanwoo Kim ,  Nishant Govindbhai Parsania ,  Ajay Pratap Singh

    发明人： Kwanwoo Kim ,  Nishant Govindbhai Parsania ,  Ajay Pratap Singh

    IPC分类号： F02C7/22 ,  F23R3/14 ,  F23C7/00 ,  F23R3/28

    CPC分类号： F23C7/004 ,  F23C2900/07001 ,  F23R3/286

    摘要： In an embodiment, a system includes a turbine fuel nozzle having a hub with an axis, a shroud surrounding the hub along the axis, an air flow path between the hub and the shroud, and a fuel flow path. The turbine fuel nozzle also includes a swirl vane extending between the hub and the shroud in a radial direction relative to the axis. The swirl vane includes a fuel inlet coupled to the fuel flow path, a fuel chamber extending from the fuel inlet, and a plurality of fuel outlets extending from the fuel chamber to the air flow path. The plurality of fuel outlets is positioned at an axial distance of at least approximately ⅔ of an axial length of the fuel chamber downstream from an upstream point along an upstream edge of the fuel chamber.

    摘要翻译： 在一个实施例中，系统包括涡轮燃料喷嘴，其具有带有轴的轮毂，围绕轴线的轮毂的护罩，轮毂和护罩之间的空气流动路径以及燃料流动路径。 涡轮燃料喷嘴还包括在毂和护罩之间沿相对于轴线的径向方向延伸的旋流叶片。 涡旋叶片包括联接到燃料流动路径的燃料入口，从燃料入口延伸的燃料室和从燃料室延伸到空气流动路径的多个燃料出口。 多个燃料出口被定位在燃料室的沿着燃料室的上游边缘的上游点下游的燃料室的轴向长度的至少近似⅔的轴向距离处。