SEAL IN COMBUSTOR NOZZLE OF GAS TURBINE ENGINE
    25.
    发明申请
    SEAL IN COMBUSTOR NOZZLE OF GAS TURBINE ENGINE 审中-公开
    密封在燃气涡轮发动机的燃烧器喷嘴

    公开(公告)号:US20160033134A1

    公开(公告)日:2016-02-04

    申请号:US14449339

    申请日:2014-08-01

    CPC classification number: F23R3/286 F23R2900/00012

    Abstract: A nozzle for use in a combustor of a combustion turbine engine, the nozzle including: radial sections defined by sidewalls; a gap formed between opposing sidewalls of adjacent ones of the radial sections; a groove formed on each of the sidewalls that define the gap, the grooves positioned correspondingly so to together form a pocket; and a seal having a zigzagging profile disposed within the pocket. The pocket may intercept the gap over a seal length, and the seal may extend longitudinally within the pocket such that the zigzagging profile intersects the gap over the seal length.

    Abstract translation: 一种用于燃气涡轮发动机的燃烧器的喷嘴,所述喷嘴包括:由侧壁限定的径向部分; 在相邻的径向部分的相对的侧壁之间形成的间隙; 形成在限定所述间隙的每个侧壁上的凹槽,所述凹槽对应地一起形成一个口袋; 以及密封件,其具有设置在口袋内的锯齿状轮廓。 口袋可以拦截密封长度上的间隙,并且密封件可以在口袋内纵向延伸,使得锯齿形轮廓与密封长度上的间隙相交。

    SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS
    26.
    发明申请
    SYSTEM AND METHOD FOR REDUCING MODAL COUPLING OF COMBUSTION DYNAMICS 有权
    用于减少燃烧动力学模态耦合的系统和方法

    公开(公告)号:US20150219337A1

    公开(公告)日:2015-08-06

    申请号:US14170738

    申请日:2014-02-03

    Abstract: A system and method for reducing modal coupling of combustion dynamics generally include multiple combustors, and each combustor includes multiple fuel nozzle groups for mixing fuel with a compressed working fluid prior to combustion. A fuel circuit is in fluid communication with each fuel nozzle, and orifice plates in the fuel circuit upstream from the fuel nozzles control the fuel split between the fuel nozzles in each combustor and/or between different combustors to produce a frequency difference between combustors.

    Abstract translation: 用于减少燃烧动态的模态耦合的系统和方法通常包括多个燃烧器,并且每个燃烧器包括用于在燃烧之前将燃料与压缩的工作流体混合的多个燃料喷嘴组。 燃料回路与每个燃料喷嘴流体连通,并且来自燃料喷嘴上游的燃料回路中的孔板控制每个燃烧器中的燃料喷嘴之间和/或不同燃烧器之间的燃料分配,以产生燃烧器之间的频率差。

    Fuel oxygen reduction unit with plasma reactor

    公开(公告)号:US10914274B1

    公开(公告)日:2021-02-09

    申请号:US16567657

    申请日:2019-09-11

    Abstract: A fuel oxygen reduction unit for an aeronautical engine is provided. The fuel oxygen reduction unit includes a stripping gas line that provides a stripping gas flow and a plasma reactor in fluid communication with the stripping gas line. The plasma reactor includes a plasma reactor gas inlet that receives the stripping gas flow from the stripping gas line and a plasma reactor gas outlet that provides the stripping gas flow back to the stripping gas line, the plasma reactor configured to reduce a free oxygen content of the stripping gas flow such that an outlet free oxygen content of the stripping gas flow that exits the plasma reactor gas outlet is lower than an inlet free oxygen content of the stripping gas flow that enters the plasma reactor gas inlet.

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