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    SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A TURBOMACHINE
    2.
    发明申请
    SYSTEM AND METHOD FOR REDUCING COMBUSTION DYNAMICS IN A TURBOMACHINE 审中-公开
    用于减少涡轮机燃烧动力学的系统和方法

    公开(公告)号：US20130133331A1

    公开(公告)日：2013-05-30

    申请号：US13751301

    申请日：2013-01-28

    申请人： Kapil Kumar Singh ,  Vasanth Srinivasa Kothnur ,  Fei Han

    发明人： Kapil Kumar Singh ,  Vasanth Srinivasa Kothnur ,  Fei Han

    IPC分类号： F23R3/28

    CPC分类号： F23R3/286 ,  F23R3/00 ,  F23R2900/00013

    摘要： A turbomachine includes a combustion chamber, and at least one pre-mixer mounted to the combustion chamber. The at least one pre-mixer includes a main body having a first end portion that extends to a second end portion. The first end portion is configured to receive an amount of fuel and an amount of air and the second end portion defines an exit plane from which a fuel-air mixture discharges into the combustion chamber. The turbomachine also includes a combustion dynamics reduction system operatively coupled to the at least one pre-mixer. The combustion dynamics reduction system includes at least one of a boundary layer perturbation mechanism and an acoustic wave introduction system which disrupt a flow pattern of the fuel-air mixture within the at least one pre-mixer.

    摘要翻译： 涡轮机包括燃烧室，以及安装在燃烧室上的至少一个预混合器。 所述至少一个预混合器包括具有延伸到第二端部的第一端部的主体。 第一端部构造成接收一定量的燃料和一定量的空气，并且第二端部限定了燃料 - 空气混合物从该出口平面排出到燃烧室中。 涡轮机还包括可操作地耦合到至少一个预混合器的燃烧动力学降低系统。 燃烧动力学降低系统包括边界层扰动机构和声波引入系统中的至少一个，其破坏在至少一个预混合器内的燃料 - 空气混合物的流动模式。

    FUEL SYSTEM ACOUSTIC FEATURE TO MITIGATE COMBUSTION DYNAMICS FOR MULTI-NOZZLE DRY LOW Nox COMBUSTION SYSTEM AND METHOD
    5.
    发明申请
    FUEL SYSTEM ACOUSTIC FEATURE TO MITIGATE COMBUSTION DYNAMICS FOR MULTI-NOZZLE DRY LOW Nox COMBUSTION SYSTEM AND METHOD 有权
    燃油系统声学特性，用于减轻多喷嘴干燥低NOx燃烧系统和方法的燃烧动力学

    公开(公告)号：US20110162370A1

    公开(公告)日：2011-07-07

    申请号：US12651600

    申请日：2010-01-04

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

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

    IPC分类号： F02C7/22 ,  B23P11/00

    CPC分类号： F02C7/228 ,  F02C7/22 ,  F05D2240/128 ,  F05D2270/082 ,  F23R3/28 ,  F23R2900/00014 ,  Y10T29/49826

    摘要： A dry low NOx (DLN) fuel nozzle of a fuel system is provided and includes one or more downstream orifices formed to define a first fluid path along which fluid is directed to flow, an upstream orifice, located upstream from the one or more downstream orifices, formed to define a second fluid path along which the fluid is directed to flow and connecting passages disposed to fluidly couple the first and second fluid paths of the downstream and upstream orifices, respectively, to one another. At least one of a radial size and an axial location of the upstream orifice is set to cooperatively detune an acoustic impedance of the fuel system.

    摘要翻译： 提供燃料系统的干式低NOx（DLN）燃料喷嘴，并且包括一个或多个下游孔，其形成为限定流体被引导流动的第一流体路径，位于一个或多个下游孔的上游的上游孔 ，其被形成为限定流体被引导流过的第二流体路径和设置成将下游和上游孔口的第一和第二流体路径分别彼此流体耦合的连接通道。 上游孔的径向尺寸和轴向位置中的至少一个被设定为协调地使燃料系统的声阻抗失谐。

    Fuel system acoustic feature to mitigate combustion dynamics for multi-nozzle dry low NOx combustion system and method
    6.
    发明授权
    Fuel system acoustic feature to mitigate combustion dynamics for multi-nozzle dry low NOx combustion system and method 有权
    燃料系统声学特征，以减轻多喷嘴干燥低NOx燃烧系统和方法的燃烧动力学

    公开(公告)号：US08322140B2

    公开(公告)日：2012-12-04

    申请号：US12651600

    申请日：2010-01-04

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

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

    IPC分类号： F02C1/00

    CPC分类号： F02C7/228 ,  F02C7/22 ,  F05D2240/128 ,  F05D2270/082 ,  F23R3/28 ,  F23R2900/00014 ,  Y10T29/49826

    摘要： A dry low NOx (DLN) fuel nozzle of a fuel system is provided and includes one or more downstream orifices formed to define a first fluid path along which fluid is directed to flow, an upstream orifice, located upstream from the one or more downstream orifices, formed to define a second fluid path along which the fluid is directed to flow and connecting passages disposed to fluidly couple the first and second fluid paths of the downstream and upstream orifices, respectively, to one another. At least one of a radial size and an axial location of the upstream orifice is set to cooperatively detune an acoustic impedance of the fuel system.

    摘要翻译： 提供燃料系统的干式低NOx（DLN）燃料喷嘴，并且包括一个或多个下游孔，其形成为限定流体被引导流动的第一流体路径，位于一个或多个下游孔的上游的上游孔 ，其被形成为限定流体被引导流过的第二流体路径和设置成将下游和上游孔口的第一和第二流体路径分别彼此流体耦合的连接通道。 上游孔的径向尺寸和轴向位置中的至少一个被设定为协调地使燃料系统的声阻抗失谐。

    TURBOMACHINE FUEL NOZZLE
    7.
    发明申请
    TURBOMACHINE FUEL NOZZLE 审中-公开
    涡轮燃料喷嘴

    公开(公告)号：US20110289929A1

    公开(公告)日：2011-12-01

    申请号：US12789820

    申请日：2010-05-28

    申请人： Abdul Rafey Khan ,  Kapil Kumar Singh

    发明人： Abdul Rafey Khan ,  Kapil Kumar Singh

    IPC分类号： F02C9/26 ,  F02C7/22

    CPC分类号： F23D11/24 ,  F23D11/38 ,  F23D2900/14482 ,  F23R3/28

    摘要： A turbomachine includes a compressor, a turbine operatively coupled to the compressor, and a combustor fluidly linking the compressor and the turbine. The combustor includes at least one fuel nozzle. The at least one fuel nozzle includes a flow passage including a body having first end that extends to a second end through at least one flow channel having a flow area. A fuel inlet is provided at the first end of the body. The fuel inlet is configured to receive at least one fuel. A fuel outlet is provided at the second end of the body. A control flow passage is fluidly connected to the body between the first and second ends. The control flow passage is configured and disposed to deliver a control flow into the fuel nozzle. The control flow establishes a selectively variable effective flow area of the flow passage.

    摘要翻译： 涡轮机包括压缩机，可操作地联接到压缩机的涡轮机和流体连接压缩机和涡轮机的燃烧器。 燃烧器包括至少一个燃料喷嘴。 所述至少一个燃料喷嘴包括流动通道，该流动通道包括主体，该主体具有通过具有流动区域的至少一个流动通道延伸到第二端的第一端。 燃料入口设置在主体的第一端。 燃料入口构造成容纳至少一种燃料。 燃料出口设置在主体的第二端。 控制流动通道在第一和第二端之间流体地连接到主体。 控制流路被构造和设置成将控制流输送到燃料喷嘴中。 控制流程建立了流路的选择性变化的有效流动面积。

    RESONATOR ASSEMBLY FOR MITIGATING DYNAMICS IN GAS TURBINES
    9.
    发明申请
    RESONATOR ASSEMBLY FOR MITIGATING DYNAMICS IN GAS TURBINES 有权
    用于减轻气体涡轮动力学的共振器装置

    公开(公告)号：US20100313568A1

    公开(公告)日：2010-12-16

    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： F02C7/24

    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。