NEAR FLOW PATH SEAL FOR A TURBOMACHINE
    1.
    发明申请
    NEAR FLOW PATH SEAL FOR A TURBOMACHINE 审中-公开
    涡轮机附近的流路密封

    公开(公告)号:US20130186103A1

    公开(公告)日:2013-07-25

    申请号:US13354625

    申请日:2012-01-20

    IPC分类号: F02C7/28 F16J15/44

    摘要: A near flow path seal for a turbomachine includes a support member having a first end portion that extends to a second end portion through an intermediate portion, and an arm member extending from the first end portion of the support member. The arm member includes a first end that extends to a second end, a first surface extending between the first and second ends, and a second, opposing surface extending between the first and second ends. The second surface includes a plurality of surface features that extend from about the first end toward the second end.

    摘要翻译: 用于涡轮机的近流路密封件包括支撑构件,该支撑构件具有通过中间部分延伸到第二端部的第一端部和从支撑构件的第一端部延伸的臂构件。 臂构件包括延伸到第二端的第一端,在第一和第二端之间延伸的第一表面和在第一和第二端之间延伸的第二相对表面。 第二表面包括从大约第一端向第二端延伸的多个表面特征。

    IMPINGEMENT PLATE FOR TURBOMACHINE COMPONENTS AND COMPONENTS EQUIPPED THEREWITH
    2.
    发明申请
    IMPINGEMENT PLATE FOR TURBOMACHINE COMPONENTS AND COMPONENTS EQUIPPED THEREWITH 失效
    用于涡轮机组件和组件的冲击板

    公开(公告)号:US20120177478A1

    公开(公告)日:2012-07-12

    申请号:US12985498

    申请日:2011-01-06

    IPC分类号: F01D25/12

    摘要: An impingement plate adapted to reduce thermally-induced strains and stresses that may damage the plate or its attachment to a second component. The plate includes an interior region having cooling holes, a peripheral wall surrounding the interior region and projecting out of the plane of the interior region, a peripheral flange surrounding the peripheral wall and lying in a plane spaced apart from the plane of the interior region, and one or more through-thickness rib. One such rib may be disposed in the interior region, project away from and out of the plane of the interior region, and linearly extend across the interior region. Alternatively or in addition, one such rib may be disposed between the peripheral wall and flange and project out of the plane of the flange.

    摘要翻译: 适于减少可能损坏板或其附接到第二部件的热诱导应变和应力的冲击板。 所述板包括具有冷却孔的内部区域,围绕所述内部区域并突出到所述内部区域的平面外围的周边壁;围绕所述周边壁并位于与所述内部区域的平面间隔开的平面中的周边凸缘, 和一个或多个贯穿厚度的肋。 一个这样的肋可以设置在内部区域中,远离和离开内部区域的平面,并且线性延伸穿过内部区域。 或者或另外,一个这样的肋可以设置在周壁和凸缘之间并突出到凸缘的平面之外。

    NOZZLE FOR TURBINE SYSTEM
    3.
    发明申请
    NOZZLE FOR TURBINE SYSTEM 审中-公开
    涡轮系统喷嘴

    公开(公告)号:US20140023517A1

    公开(公告)日:2014-01-23

    申请号:US13555417

    申请日:2012-07-23

    IPC分类号: F01D5/18

    摘要: A nozzle for a turbine system is disclosed. The nozzle includes an airfoil, an inner sidewall, and an outer sidewall. The airfoil includes exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge. The airfoil further defines a tip and a root. The inner sidewall is connected to the airfoil at the tip. The outer sidewall is connected to the airfoil at the root. The inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile.

    摘要翻译: 公开了一种用于涡轮机系统的喷嘴。 喷嘴包括翼型件,内侧壁和外侧壁。 翼型件包括限定压力侧的外表面和在前缘和后缘之间延伸的吸力侧。 翼型件还限定了尖端和根部。 内侧壁在尖端连接到翼型。 外侧壁与根部的翼型连接。 内侧壁和外侧壁均包括限定压力侧斜面,吸力侧斜面,前缘面和后缘面的周缘。 内侧壁压侧侧斜面,内侧壁吸力侧斜面,外侧壁压侧侧斜面或外侧壁吸力侧斜面中的至少一方具有大致曲线的轮廓。

    Torsion seal
    4.
    发明授权
    Torsion seal 有权
    扭转密封

    公开(公告)号:US08544852B2

    公开(公告)日:2013-10-01

    申请号:US13152585

    申请日:2011-06-03

    申请人: Sheo Narain Giri

    发明人: Sheo Narain Giri

    IPC分类号: F16J15/02

    摘要: A torsion seal is provided and includes a first section, a second section and a torsion section connected at opposite end portions thereof to the first and second sections and having a central portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.

    摘要翻译: 提供扭转密封件,并且包括第一部分,第二部分和扭转部分,该部分在其相对端部处连接到第一和第二部分,并且具有在相对端部之间延伸的中心部分,以吸收容器的不同热生长, 第一和第二部分联接。

    SEAL FOR TURBOMACHINE SEGMENTS
    5.
    发明申请
    SEAL FOR TURBOMACHINE SEGMENTS 审中-公开
    密封用于涡轮机部分

    公开(公告)号:US20130028713A1

    公开(公告)日:2013-01-31

    申请号:US13190431

    申请日:2011-07-25

    IPC分类号: F01D11/00 F02C7/12 F01D25/26

    CPC分类号: F16J15/0887 F16J15/064

    摘要: In one embodiment, a system includes a seal having a first sealing end portion, a second sealing end portion, and an intermediate portion between the first and second sealing end portions, wherein the seal has at least one metering hole configured to control a leakage flow across the seal.

    摘要翻译: 在一个实施例中,系统包括具有第一密封端部分,第二密封端部分以及第一和第二密封端部之间的中间部分的密封件,其中密封件具有至少一个计量孔,该计量孔构造成控制泄漏流动 穿过印章。

    System for axial retention of rotating segments of a turbine
    7.
    发明授权
    System for axial retention of rotating segments of a turbine 有权
    用于涡轮机旋转段轴向保持的系统

    公开(公告)号:US09051845B2

    公开(公告)日:2015-06-09

    申请号:US13344421

    申请日:2012-01-05

    IPC分类号: F01D5/32 F01D5/30

    摘要: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

    摘要翻译: 涡轮机系统包括涡轮机,其包括包括旋转轴线的转子,第一旋转段,具有在第一安装位置中联接到转子的第一轴向安装件的第一配合轴向安装件,以及构造成插入到第一安装位置的第一销 在转子的第一槽和第一旋转段中的第一配合槽中的插入位置。 第一插入位置中的第一销被构造成阻止第一配合轴向安装件相对于第一轴向安装件的轴向运动。 涡轮机还包括第二旋转段,其具有在第二安装位置中联接到转子的第二轴向安装件的第二配合轴向安装件。 在第二安装位置的第二旋转部分构造成阻止第一销的移除。

    Impingement plate for turbomachine components and components equipped therewith
    8.
    发明授权
    Impingement plate for turbomachine components and components equipped therewith 失效
    用于装配有涡轮机组件和部件的冲击板

    公开(公告)号:US08714911B2

    公开(公告)日:2014-05-06

    申请号:US12985498

    申请日:2011-01-06

    IPC分类号: F01D25/12

    摘要: An impingement plate adapted to reduce thermally-induced strains and stresses that may damage the plate or its attachment to a second component. The plate includes an interior region having cooling holes, a peripheral wall surrounding the interior region and projecting out of the plane of the interior region, a peripheral flange surrounding the peripheral wall and lying in a plane spaced apart from the plane of the interior region, and one or more through-thickness rib. One such rib may be disposed in the interior region, project away from and out of the plane of the interior region, and linearly extend across the interior region. Alternatively or in addition, one such rib may be disposed between the peripheral wall and flange and project out of the plane of the flange.

    摘要翻译: 适于减少可能损坏板或其附接到第二部件的热诱导应变和应力的冲击板。 所述板包括具有冷却孔的内部区域,围绕所述内部区域并突出到所述内部区域的平面外围的周边壁;围绕所述周边壁并位于与所述内部区域的平面间隔开的平面中的周边凸缘, 和一个或多个贯穿厚度的肋。 一个这样的肋可以设置在内部区域中,远离和离开内部区域的平面,并且线性延伸穿过内部区域。 或者或另外,一个这样的肋可以设置在周壁和凸缘之间并突出到凸缘的平面之外。

    Cooling hole exits for a turbine bucket tip shroud
    9.
    发明授权
    Cooling hole exits for a turbine bucket tip shroud 有权
    涡轮机铲斗顶盖的冷却孔出口

    公开(公告)号:US08511990B2

    公开(公告)日:2013-08-20

    申请号:US12490429

    申请日:2009-06-24

    申请人: Sheo Narain Giri

    发明人: Sheo Narain Giri

    IPC分类号: F01D5/18

    摘要: A turbine bucket for a gas turbine engine is described herein. The turbine bucket may include an airfoil, a tip shroud positioned on a tip of the airfoil, and a number of cooling holes extending through the airfoil and the tip shroud. One or more of the cooling holes may include a length of narrowing diameter about the tip shroud and a length of expanding diameter about a surface of the tip shroud.

    摘要翻译: 这里描述了用于燃气涡轮发动机的涡轮机桶。 涡轮机桶可以包括翼型件,位于翼型件的尖端上的尖端护罩,以及延伸穿过翼型件和尖端护罩的多个冷却孔。 一个或多个冷却孔可以包括围绕尖端护罩的变窄直径的长度和围绕尖端护罩的表面的扩展直径的长度。

    HINGE SEAL
    10.
    发明申请
    HINGE SEAL 审中-公开
    铰链密封

    公开(公告)号:US20120306169A1

    公开(公告)日:2012-12-06

    申请号:US13152604

    申请日:2011-06-03

    申请人: Sheo Narain Giri

    发明人: Sheo Narain Giri

    IPC分类号: F01D11/00 F16J15/02

    摘要: A hinge seal is provided and includes a first section, a second section and a hinge section connected at opposite end portions thereof to the first and second sections and having a central piano hinge portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.

    摘要翻译: 提供铰链密封件,其包括第一部分,第二部分和铰链部分,铰链部分在其相对端部处连接到第一和第二部分,并且具有在相对端部之间延伸的中央钢琴铰链部分,以吸收容器的不同热生长 第一和第二部分耦合到其上。