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    Axial swirler for a gas turbine burner
    2.
    发明授权
    Axial swirler for a gas turbine burner 有权
    用于燃气轮机燃烧器的轴向旋流器

    公开(公告)号：US09518740B2

    公开(公告)日：2016-12-13

    申请号：US13937482

    申请日：2013-07-09

    Applicant: ALSTOM Technology Ltd

    Inventor： Fernando Biagioli ,  Naresh Aluri ,  Madhavan Narasimhan Poyyapakkam ,  Jan Cerny

    IPC: F23R3/14 ,  F23R3/28 ,  F23C7/00

    CPC classification number: F23R3/14 ,  F23C7/004 ,  F23R3/286

    Abstract: An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius.

    Abstract translation: 用于燃气涡轮燃烧器的轴向旋流器包括具有围绕旋流器轴线周向分布的多个旋流器叶片的叶片环。 每个旋流器叶片包括后缘。 为了实现径向方向上的出口流速分布和/或燃料当量比的受控分布。 后缘是不连续的，后缘具有预定半径的不连续性。

    METHOD FOR PREMIXING AIR WITH A GASEOUS FUEL AND BURNER ARRANGEMENT FOR CONDUCTING SAID METHOD
    3.
    发明申请
    METHOD FOR PREMIXING AIR WITH A GASEOUS FUEL AND BURNER ARRANGEMENT FOR CONDUCTING SAID METHOD 有权
    用气体燃料预热空气的方法和燃烧器装置用于导电方法

    公开(公告)号：US20150300646A1

    公开(公告)日：2015-10-22

    申请号：US14685945

    申请日：2015-04-14

    Applicant: ALSTOM Technology Ltd

    Inventor： Fernando BIAGIOLI ,  Madhavan Narasimhan Poyyapakkam

    IPC: F23R3/14 ,  F23R3/28

    CPC classification number: F23R3/14 ,  F23C7/004 ,  F23C2900/07001 ,  F23D2900/14021 ,  F23D2900/14701 ,  F23R3/286

    Abstract: A method for premixing air with a gaseous fuel for being burned in a combustion chamber includes: guiding the air in an air stream along a burner axis through a coaxial air tube into a combustion chamber arranged at an end of said air tube; and impressing a swirl on the air stream by passing it through a first swirl device concentrically arranged within the air tube and comprising a plurality of radially oriented first blades. The method further includes: injecting gaseous fuel into the air stream at the first swirl device; and mixing said air in said air stream with the injected gaseous fuel in a first mixing zone arranged just after said first swirl device

    Abstract translation: 用于将空气与用于在燃烧室中燃烧的气体燃料预混合的方法包括：沿着燃烧器轴线的空气流中的空气通过同轴空气管引导到布置在所述空气管的端部的燃烧室中; 并且通过使其通过同心地布置在所述空气管内并包括多个径向取向的第一叶片的第一旋流装置来在所述空气流上施加漩涡。 该方法还包括：在第一涡流装置处将气体燃料喷射到空气流中; 以及将所述空气流中的空气与喷射的气体燃料混合在刚刚在所述第一涡流装置之后布置的第一混合区域中

    GAS TURBINE POWER PLANT WITH NON-HOMOGENEOUS INPUT GAS
    4.
    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。

    Axial swirler
    6.
    发明授权
    Axial swirler 有权
    轴流旋流器

    公开(公告)号：US09557061B2

    公开(公告)日：2017-01-31

    申请号：US14072170

    申请日：2013-11-05

    Applicant: ALSTOM Technology Ltd

    Inventor： Fernando Biagioli ,  Madhavan Narasimhan Poyyapakkam ,  Riccardo Cenni ,  Khawar Syed

    IPC: F23R3/14 ,  F23R3/28 ,  F23C7/00 ,  F23R3/36

    CPC classification number: F23R3/14 ,  F23C7/004 ,  F23D2900/14021 ,  F23R3/286 ,  F23R3/36

    Abstract: An axial swirler, in particular for premixing of oxidizer and fuel in gas turbines, includes a series of swirl vanes with a streamline cross-section. Each swirl vane has a leading edge, a trailing edge, and a suction side and a pressure side extending each between the leading and trailing edges. The swirl vanes are arranged around a swirler axis, wherein the leading edges extend essentially in radial direction. Flow slots are formed between the suction side of each swirl vane and the pressure side of its nearest neighboring swirl vane. Furthermore, at least one swirl vane has a discharge flow angle between a tangent to its camber line at its trailing edge and the swirler axis that is monotonically increasing with increasing radial distance from the swirler axis. The invention also relates to a burner with such a swirler and a method of operating the burner.

    Abstract translation: 特别是用于燃气轮机中氧化剂和燃料的预混合的轴向旋流器包括一系列具有流线横截面的旋流叶片。 每个旋流叶片具有前缘，后缘以及每个在前缘和后缘之间延伸的吸力侧和压力侧。 涡旋叶片围绕旋流器轴线布置，其中前缘基本上沿径向延伸。 流动槽形成在每个涡流叶片的吸力侧和其最近的相邻旋流叶片的压力侧之间。 此外，至少一个旋流叶片具有在其后缘处的其弯曲线的切线与旋流器轴线之间的排出流动角度，该旋流器轴线随着距旋流器轴线的径向距离的增加而单调增加。 本发明还涉及具有这种旋流器的燃烧器和操作燃烧器的方法。

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