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    Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section
    3.
    发明授权
    Gas turbine combustor having bypass and annular gas passage for reducing uneven temperature distribution in combustor tail cross section 有权
    具有旁路和环形气体通道的燃气轮机燃烧器，用于减少燃烧器尾部截面中不均匀的温度分布

    公开(公告)号：US06860098B2

    公开(公告)日：2005-03-01

    申请号：US10098146

    申请日：2002-03-15

    申请人： Kiyoshi Suenaga ,  Shigemi Mandai ,  Katsunori Tanaka

    发明人： Kiyoshi Suenaga ,  Shigemi Mandai ,  Katsunori Tanaka

    IPC分类号： F02C7/18 ,  F23R3/04 ,  F23R3/06 ,  F23R3/26 ,  F23R3/42 ,  F02C9/00

    CPC分类号： F23R3/045 ,  F23R2900/00014

    摘要： There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.

    摘要翻译： 提供燃烧燃料的燃烧器，包括连接到燃烧器的一侧以将空气供入燃烧器的旁路通道; 以及环形通道，设置在燃烧器周围并连接到旁通通道，其中通过旁通通道供应的空气在圆周方向上通过环形通道，并且通过一个开口均匀地供应到燃烧器的周向， 燃烧器和环形通道。 因此，能够将通过旁通路的压缩空气均匀地供给到燃烧器的尾部，能够减少燃烧器尾部的截面的温度分布的不均匀。

    Gas turbine combustor
    5.
    发明授权
    Gas turbine combustor 有权
    燃气轮机燃烧器

    公开(公告)号：US06837051B2

    公开(公告)日：2005-01-04

    申请号：US10671472

    申请日：2003-09-29

    申请人： Shigemi Mandai ,  Kiyoshi Suenaga ,  Kuniaki Aoyama ,  Kazufumi Ikeda ,  Katsunori Tanaka

    发明人： Shigemi Mandai ,  Kiyoshi Suenaga ,  Kuniaki Aoyama ,  Kazufumi Ikeda ,  Katsunori Tanaka

    IPC分类号： F02C7/18 ,  F23M99/00 ,  F23R3/00 ,  F23R3/06 ,  F23R3/10 ,  F23R3/30 ,  F02C7/24

    CPC分类号： F23R3/06 ,  F23D2211/00 ,  F23M20/005 ,  F23R3/005 ,  F23R2900/00001 ,  F23R2900/00014

    摘要： A gas turbine combustor includes a side wall, for defining a combustion volume, having upstream and downstream ends, a pilot nozzle, disposed adjacent the upstream end of the side wall, for discharging a pilot fuel to form a diffusion flame in the combustion volume, and a plurality of main nozzles, provided around the pilot nozzles, for discharging a fuel-air mixture to form premixed flames in the combustion volume. Film air is supplied into the combustion volume downstream of the main nozzles along the inner surface of the side wall to reduce the fuel-air ratio in a region adjacent the inner surface of the side wall and to restrain a combustion-driven oscillation in the combustion volume.

    摘要翻译： 燃气轮机燃烧器包括用于限定具有上游和下游端的燃烧体积的侧壁，邻近侧壁的上游端设置的先导喷嘴，用于排放引燃燃料以在燃烧体积中形成扩散火焰， 以及设置在先导喷嘴周围的多个主喷嘴，用于排出燃料 - 空气混合物以在燃烧体积中形成预混合火焰。 薄膜空气沿着侧壁的内表面供应到主喷嘴下游的燃烧体积中，以减小邻近侧壁内表面的区域中的燃料空气比，并且抑制燃烧驱动的燃烧驱动 卷。

    Premixing nozzle, combustor, and gas turbine
    7.
    发明授权
    Premixing nozzle, combustor, and gas turbine 有权
    预喷嘴，燃烧器和燃气轮机

    公开(公告)号：US07360363B2

    公开(公告)日：2008-04-22

    申请号：US10415649

    申请日：2002-07-05

    申请人： Shigemi Mandai ,  Keijirou Saitoh ,  Katsunori Tanaka ,  Wataru Akizuki

    发明人： Shigemi Mandai ,  Keijirou Saitoh ,  Katsunori Tanaka ,  Wataru Akizuki

    IPC分类号： F23R3/14

    CPC分类号： F23R3/14 ,  F23C2900/07001 ,  F23R3/286 ,  F23R3/343

    摘要： A premixing nozzle includes swirler blades for agitating combustion air inside a nozzle body. Each one end of the swirler blades is fitted to the nozzle body, and the other end is connected to a hub, respectively. The tip portion of a fuel nozzle shaft is conical, and a part of the tip portion is arranged inside the hub. A combustion gas flows into the hub from a space between the tip portion of the fuel nozzle shaft and the upstream end of the hub, passes through between the tip portion and the inner peripheral surface of the hub, and flows toward the downstream of the hub.

    摘要翻译： 预混合喷嘴包括用于搅拌喷嘴体内的燃烧空气的旋流器叶片。 旋流器叶片的每一端安装到喷嘴体上，另一端分别连接到轮毂。 燃料喷嘴轴的前端部是锥形的，顶端部的一部分配置在轮毂内。 燃烧气体从燃料喷嘴轴的前端部和轮毂的上游端部之间的空间流入轮毂，在轮毂的前端部和内周面之间通过，并且向毂的下游侧流动 。

    Cooling structure of a combustor tail tube
    10.
    发明授权
    Cooling structure of a combustor tail tube 有权
    燃烧器尾管的冷却结构

    公开(公告)号：US06553766B2

    公开(公告)日：2003-04-29

    申请号：US09832937

    申请日：2001-04-12

    申请人： Takehiko Shimizu ,  Satoshi Hada ,  Kouichi Akagi ,  Katsunori Tanaka ,  Ryotaro Magoshi ,  Mitsuo Hasegawa ,  Shigemi Mandai ,  Mitsuru Kondo

    发明人： Takehiko Shimizu ,  Satoshi Hada ,  Kouichi Akagi ,  Katsunori Tanaka ,  Ryotaro Magoshi ,  Mitsuo Hasegawa ,  Shigemi Mandai ,  Mitsuru Kondo

    IPC分类号： F23R306

    CPC分类号： F23M5/08 ,  F01D9/023 ,  F02C7/16 ,  F05D2260/2322 ,  F23R3/002

    摘要： A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets (5) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets (5) is varied depending on the metal temperature of parts of the tail tube (4). For example, the passage sectional area of the cooling jackets (5) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets (5) formed at the casing side wall.

    摘要翻译： 燃烧器尾管的冷却结构能够通过减少热应力和防止热变形来避免尾管中的裂纹的形成，延长使用寿命。 多个冷却套（5）沿着尾管壁的整个圆周在燃气轮机燃烧器的尾管的纵向方向上延伸。 冷却套（5）的通道截面积根据尾管（4）的部件的金属温度而变化。 例如，形成在转子侧壁的冷却套（5）和相邻尾管的相对侧壁的通道截面积大于形成在壳体侧的冷却套（5）的通道截面面积 壁。