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    GAS TURBINE POWER PLANT WITH NON-HOMOGENEOUS INPUT GAS
    1.
    发明申请
    GAS TURBINE POWER PLANT WITH NON-HOMOGENEOUS INPUT GAS 有权
    具有非均匀输入气体的气体涡轮发电厂

    公开(公告)号：US20150007576A1

    公开(公告)日：2015-01-08

    申请号：US14492222

    申请日：2014-09-22

    Applicant: ALSTOM Technology Ltd

    Inventor： Felix GUETHE ,  Madhavan Narasimhan Poyyapakkam ,  Frank Graf ,  Bruno Schuermans ,  Eribert Benz

    IPC: F02C3/34 ,  F02C3/13 ,  F23R3/28 ,  F23R3/04

    CPC classification number: F02C3/34 ,  F02C3/13 ,  F02C7/08 ,  F23C9/00 ,  F23C2202/30 ,  F23R3/04 ,  F23R3/26 ,  F23R3/286

    Abstract: The invention relates to a method for operating a gas turbine which includes a compressor with annular inlet area, at least two burners, a combustion chamber and a turbine. According to the method, at least one first partial intake flow, consisting of oxygen-reduced gas which has an oxygen concentration which is lower than the average oxygen concentration of the compressor intake flow, and at least one second partial intake flow, consisting of fresh air, are fed to the compressor in an alternating manner in the circumferential direction of the inlet area. In addition, the invention relates to a gas turbine power plant with a gas turbine, the compressor inlet of which includes at least one first segment and at least one second segment which are arranged in an alternating manner around a compressor inlet in the circumferential direction, wherein a feed for an oxygen-reduced gas is connected to the first segment and a fresh air feed is connected to the second segment of the compressor inlet.

    Abstract translation: 本发明涉及一种用于操作燃气轮机的方法，其包括具有环形入口区域的压缩机，至少两个燃烧器，燃烧室和涡轮机。 根据该方法，至少一个第一部分进气流由氧气浓度低于压缩机进气流量的平均氧气浓度的氧还原气体组成，至少一个第二部分进气流由新鲜的 空气在入口区域的圆周方向上交替地供给到压缩机。 此外，本发明涉及一种具有燃气轮机的燃气轮机发电厂，其压缩机入口包括至少一个第一段和至少一个第二段，所述至少一个第一段和第二段以周向方式围绕压缩机入口交替布置， 其中用于氧还原气体的进料连接到第一段，并且新鲜空气进料连接到压缩机入口的第二段。

    Damper arrangement for reducing combustion-chamber pulsation
    2.
    发明授权
    Damper arrangement for reducing combustion-chamber pulsation 有权

    公开(公告)号：US10718520B2

    公开(公告)日：2020-07-21

    申请号：US14061954

    申请日：2013-10-24

    Applicant: ALSTOM Technology Ltd

    Inventor： Mirko Ruben Bothien ,  Jaan Hellat ,  Bruno Schuermans

    IPC: F23R3/06 ,  F23R3/34 ,  F23M20/00 ,  F02C6/02 ,  F23R3/00

    Abstract: The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.

    Gas turbine damper with inner neck extending into separate cavities
    3.
    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.

    COMBUSTION CHAMBER SEAL SEGMENTS EQUIPPED WIHT DAMPING DEVICES
    9.
    发明申请
    COMBUSTION CHAMBER SEAL SEGMENTS EQUIPPED WIHT DAMPING DEVICES 审中-公开
    燃烧室密封部件装备有阻尼装置

    公开(公告)号：US20150075168A1

    公开(公告)日：2015-03-19

    申请号：US14498136

    申请日：2014-09-26

    Applicant: ALSTOM Technology Ltd.

    Inventor： Jeffrey DE JONGE ,  Andreas Huber ,  Bruno Schuermans ,  Urs Benz

    IPC: F02C7/24 ,  B23P19/04

    CPC classification number: F02C7/24 ,  B23P19/04 ,  F23M20/005 ,  F23R3/002 ,  F23R2900/00012 ,  F23R2900/00014 ,  Y10T29/49323

    Abstract: A strip seal arrangement for turbine components employs acoustic damping. A sealing plate having a front face adjacent a combustion chamber and a back face facing away from a combustion chamber configured to have one or more holes of a predefined cross-sectional area. Containers having predefined volumes are attached to the back face of the sealing plate such that the one or more holes are in fluidic communication with the one or more containers thereby creating at least one acoustic damper. The side edges of the sealing plate fit into a slots of burner front panels, creating a seal between the panels.

    Abstract translation: 涡轮机部件的带状密封装置采用声阻尼。 密封板，其具有邻近燃烧室的前表面和背离燃烧室的背面，该燃烧室被配置为具有预定横截面积的一个或多个孔。 具有预定体积的容器附接到密封板的背面，使得一个或多个孔与一个或多个容器流体连通，从而形成至少一个声阻尼器。 密封板的侧边缘装配到燃烧器前面板的槽中，在面板之间形成密封。

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