Turbine combustor endcover assembly
    1.
    发明授权
    Turbine combustor endcover assembly 有权
    涡轮燃烧器内盖组件

    公开(公告)号:US07134287B2

    公开(公告)日:2006-11-14

    申请号:US10615776

    申请日:2003-07-10

    IPC分类号: F02C7/20

    CPC分类号: F23R3/60

    摘要: The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face of the endcover. Seal cover/endcover annular seals are disposed in registering axial cavities to seal against fluid leakage externally of the endcover assembly. Generally C-shaped and W-shaped seals are disposed in the cavities between the stepped shoulders of the insert and aperture to seal against leakage through the internal face of the endcover. The seals maintain sealing engagement during assembly and thermal distortion during turbine usage.

    摘要翻译: 用于燃烧器的封盖组件包括具有开口的端盖,通过端盖的内表面设置在阶梯式孔开口中的插入件,延伸穿过插入件和孔的燃料盒以及在封盖的外表面上的密封盖。 密封盖/端盖环形密封件设置成对准轴向空腔以密封外罩组件的流体泄漏。 通常,C形和W形密封件设置在插入件的阶梯状肩部和孔之间的空腔中,以防止通过内罩的内表面泄漏。 涡轮机使用期间,密封件在组装和热变形期间保持密封接合。

    SWIRL ANGLE OF SECONDARY FUEL NOZZLE FOR TURBOMACHINE COMBUSTOR
    3.
    发明申请
    SWIRL ANGLE OF SECONDARY FUEL NOZZLE FOR TURBOMACHINE COMBUSTOR 审中-公开
    涡轮燃烧器二次燃油喷嘴的SWIRL角

    公开(公告)号:US20100058767A1

    公开(公告)日:2010-03-11

    申请号:US12205503

    申请日:2008-09-05

    IPC分类号: F02C1/00

    摘要: A combustor includes a primary combustion chamber and a secondary combustion chamber, one or more primary nozzles disposed in the primary combustion chamber and providing fuel to the primary combustion chamber, a centerbody assembly, a venturi disposed downstream of the centerbody assembly, and a secondary fuel nozzle housed within the centerbody assembly and extending towards the venturi and providing fuel to the secondary combustion chamber. The secondary fuel nozzle includes a fuel passage and an air passage, and a swirler positioned around the fuel passage and having one or more vanes projecting radially within the air passage, each vane having a trailing edge arranged at a swirl angle relative to a longitudinal axis of the secondary fuel nozzle, the swirl angle is greater than 45°.

    摘要翻译: 燃烧器包括主燃烧室和二次燃烧室,设置在主燃烧室中的一个或多个主喷嘴并向主燃烧室提供燃料,中心体组件,设置在中心体组件下游的文丘里管和辅助燃料 喷嘴容纳在中心体组件内并且朝向文丘里管延伸并向第二燃烧室提供燃料。 二次燃料喷嘴包括燃料通道和空气通道,以及旋转器,其位于燃料通道周围并且具有一个或多个径向地在空气通道内突出的叶片,每个叶片具有相对于纵向轴线以旋转角度布置的后缘 的二次燃料喷嘴,旋转角度大于45°。