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    Gas turbine damper with inner neck extending into separate cavities
    1.
    发明授权
    Gas turbine damper with inner neck extending into separate cavities 有权

    公开(公告)号：US09897314B2

    公开(公告)日：2018-02-20

    申请号：US14279767

    申请日：2014-05-16

    Applicant: ALSTOM Technology Ltd

    Inventor： Mirko Ruben Bothien ,  Nicolas Noiray ,  Bruno Schuermans

    IPC: F23R3/00 ,  F23M20/00

    CPC classification number: F23M20/005 ,  F23R3/002 ,  F23R2900/00014

    Abstract: The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.

    Combustor transition
    4.
    发明授权
    Combustor transition 有权
    燃烧器过渡

    公开(公告)号：US09482106B2

    公开(公告)日：2016-11-01

    申请号：US14062091

    申请日：2013-10-24

    Applicant: ALSTOM Technology Ltd

    Inventor： Michael Düsing ,  Mirko Ruben Bothien

    IPC: F01D9/02 ,  F02C7/12 ,  F23R3/00

    CPC classification number: F01D9/023 ,  F02C7/12 ,  F05D2250/52 ,  F23R3/002 ,  Y10T29/49229

    Abstract: A combustor transition can be adapted to guide combustion gases in a hot gas flow path extending between a combustor and a first stage of a turbine in a gas turbine. The combustor transition includes a duct having an upstream end adapted for connection to the combustor and a downstream end adapted for connection to a first stage of the turbine. The downstream end comprises an outer wall, an inner wall, a first side wall and a second side wall. At least one side wall has a side wall extension, which can extend in a downstream direction beyond the outlet. A gas turbine can be retrofitted with such a combustor transition and a gas turbine with such a combustor transition can also undergo a borescope inspection.

    Abstract translation: 燃烧器过渡可以适于引导在燃气轮机中在燃烧器和涡轮机的第一级之间延伸的热气流路径中的燃烧气体。 燃烧器转变包括具有适于连接到燃烧器的上游端的管道和适于连接到涡轮机的第一级的下游端。 下游端包括外壁，内壁，第一侧壁和第二侧壁。 至少一个侧壁具有侧壁延伸部，其可以在下游方向上延伸超过出口。 燃气轮机可以用这样的燃烧器过渡进行改装，并且具有这样的燃烧器过渡的燃气轮机也可以进行孔镜检查。

    DAMPER FOR GAS TURBINE
    5.
    发明申请
    DAMPER FOR GAS TURBINE 审中-公开
    燃气轮机阻尼器

    公开(公告)号：US20150113992A1

    公开(公告)日：2015-04-30

    申请号：US14523040

    申请日：2014-10-24

    Applicant: ALSTOM Technology Ltd

    Inventor： Devis Tonon ,  Mirko Ruben Bothien ,  Franklin Marie Genin ,  Douglas Anthony Pennell

    IPC: F02C7/24

    CPC classification number: F02C7/24 ,  F05D2260/963 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00014

    Abstract: The invention relates to a damper for reducing the pulsations in a chamber of a gas turbine. The damper includes a resonator cavity and a neck in flow communication with the resonator cavity and the chamber. The neck includes a mouth to communicate with the chamber. The air flow inside the chamber flows across the mouth of the neck. The neck is so configured that the longitudinal axis of its mouth is angled 0-90° relative to the direction of the air flow inside the chamber. The damper of this invention may effectively alleviate the detrimental effect of the grazing flow and thus it enables the placement of the damper also at locations where strong grazing flows are present.

    Abstract translation: 本发明涉及一种用于减少燃气轮机室内的脉动的阻尼器。 阻尼器包括谐振器腔和与谐振器腔和腔室流动连通的颈部。 颈部包括与腔室通信的嘴。 室内的气流流过颈部的口。 颈部被配置成使得其嘴部的纵向轴线相对于腔室内的气流的方向成角度0-90°。 本发明的阻尼器可以有效地减轻放牧流的有害影响，从而能够将阻尼器放置在存在强放牧流动的地方。

    SENSOR MOUNTING ATTACHMENT
    6.
    发明申请
    SENSOR MOUNTING ATTACHMENT 有权
    传感器安装附件

    公开(公告)号：US20140346313A1

    公开(公告)日：2014-11-27

    申请号：US14273840

    申请日：2014-05-09

    Applicant: ALSTOM Technology Ltd.

    Inventor： Mirko Ruben Bothien ,  Stephen W. Jorgensen

    IPC: F16F9/32 ,  F16M13/02

    CPC classification number: F16F9/32 ,  F16M13/02 ,  G01L23/26

    Abstract: A mountable attachment for positioning a sensor in an environment, like a combustion chamber of a gas turbine is disclosed. The mountable attachment includes a mounting member having a hollow elongated configuration for incorporating the sensor therewithin. The attachment further includes at least one primary resilient member disposed within the mounting member in a coordinating manner with the sensor for applying an axially outward force on the mounting member to prevent thereto from loosening from a counterpart , and providing a mounting torque for mounting the sensor at a target position within the environment . The attachment may also include additional resilient member, such as a secondary resilient member, which may in combination with the primary resilient members attain a resulting mounting force to prevent the mounting member from loosening from the counterpart.

    Abstract translation: 公开了一种用于将传感器定位在诸如燃气轮机的燃烧室的环境中的可安装附件。 可安装附件包括具有中空细长结构的安装构件，用于将传感器并入其中。 所述附件还包括至少一个主弹性构件，其以与所述传感器协调的方式配置在所述安装构件内，用于在所述安装构件上施加轴向向外的力，以防止所述主弹性构件从所述安装构件松动，并提供用于安装所述传感器的安装扭矩 在环境中的目标位置。 附件还可以包括附加的弹性构件，例如次级弹性构件，其可以与主弹性构件组合获得最终的安装力，以防止安装构件从配件松动。

    DAMPING DEVICE FOR A GAS TURBINE COMBUSTOR
    10.
    发明申请
    DAMPING DEVICE FOR A GAS TURBINE COMBUSTOR 有权
    一种气体涡轮搅拌机的阻尼装置

    公开(公告)号：US20140150435A1

    公开(公告)日：2014-06-05

    申请号：US14088527

    申请日：2013-11-25

    Applicant: ALSTOM Technology Ltd

    Inventor： Thomas Michael MAURER ,  Urs Benz ,  Mirko Ruben Bothien

    IPC: F23R3/42

    CPC classification number: F23R3/42 ,  F05D2260/963 ,  F23M20/005 ,  F23R3/00 ,  F23R3/002 ,  F23R2900/00014

    Abstract: The invention relates to a damping device for a gas turbine combustor with significantly reduced cooling air mass flow requirements. The damping device includes a wall with a first inner wall and a second outer wall, arranged in a distance to each other. The inner wall is subjected to high temperatures on a side with a hot gas flow. A plurality of cooling channels extend essentially parallel between the first inner wall and the second outer wall, and at least one damping volume bordered by cooling channels. Furthermore, the damping device includes a first passage for supplying a cooling medium from a cooling channel into the damping volume and a second passage for connecting the damping volume to the combustion chamber. An end plate, fixed to the inner wall, separates the damping volume from the combustion chamber.

    Abstract translation: 本发明涉及一种用于燃气轮机燃烧器的阻尼装置，其具有显着降低的冷却空气质量流量要求。 阻尼装置包括具有彼此间隔设置的第一内壁和第二外壁的壁。 内壁在热气流的一侧经受高温。 多个冷却通道基本上平行于第一内壁和第二外壁之间延伸，以及至少一个由冷却通道界定的阻尼体积。 此外，阻尼装置包括用于将冷却介质从冷却通道供应到阻尼容积中的第一通道和用于将阻尼体积连接到燃烧室的第二通道。 固定在内壁上的端板将阻尼体积与燃烧室分开。

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