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    Combustor of gas turbine with concentric swirler vanes
    1.
    发明授权
    Combustor of gas turbine with concentric swirler vanes 有权
    燃气轮机与同心旋流叶片的燃烧器

    公开(公告)号：US07669421B2

    公开(公告)日：2010-03-02

    申请号：US11334744

    申请日：2006-01-19

    申请人： Keijiro Saitoh ,  Masataka Ohta ,  Satoshi Tanimura ,  Shigemi Mandai

    发明人： Keijiro Saitoh ,  Masataka Ohta ,  Satoshi Tanimura ,  Shigemi Mandai

    IPC分类号： F02C3/00

    CPC分类号： F23R3/14 ,  F23C2900/07001 ,  Y02E20/344 ,  Y02T50/675

    摘要： A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.

    摘要翻译： 提供了具有连接在一起的内管和过渡管的燃气轮机燃烧器。 燃烧器包括内部旋流器和外部旋流器。 内部旋流器由相对于内管的中心轴线同心设置的圆筒形向内旋流器环以及设置在向内旋流器环的外周表面上的多个向内旋流叶片组成。 外部旋流器由设置在向内旋流叶片的外周侧并相对于向内旋流器环同心的圆柱形向外旋流器环组成，并且设置在外旋流器环的外周表面上的多个向外旋流叶片 。 内部旋流器和外部旋流器设置在内管内。

    Premixing nozzle, combustor, and gas turbine
    2.
    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 。

    Combustor
    5.
    发明授权
    Combustor 有权
    燃烧器

    公开(公告)号：US6068467A

    公开(公告)日：2000-05-30

    申请号：US244031

    申请日：1999-02-04

    申请人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Satoshi Tanimura ,  Kotaro Miyauchi ,  Mitsuru Inada ,  Shinji Akamatsu ,  Hideki Haruta

    发明人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Satoshi Tanimura ,  Kotaro Miyauchi ,  Mitsuru Inada ,  Shinji Akamatsu ,  Hideki Haruta

    IPC分类号： F23D14/02 ,  F23D23/00 ,  F23C5/00

    CPC分类号： F23D23/00 ,  F23D14/02 ,  F23D2206/10 ,  F23D2209/10 ,  F23D2900/14021

    摘要： A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.

    摘要翻译： 燃烧器具有引导喷嘴02，其设置在内筒01的中心部分处，内筒01在其端部处开放到燃烧室018中，并且包括围绕其外圆周布置的多个主喷嘴03。 沿着用于点燃从主喷嘴03喷射的燃料F的火焰保持锥体014的外圆周，设置椭圆形截面形状的椭圆形延伸管016，其从主喷嘴03的前面延伸，以在轴向上具有开口 火焰保持锥体014的开口的位置。结果，热预混火焰013不流回到主喷嘴03的开口的周缘的主旋流器区域015，使得燃料F和 可以改善空气流A，减少Nox排放，同时消除基板04和主喷嘴03的燃烧。

    Combustor containing fuel nozzle
    6.
    发明授权
    Combustor containing fuel nozzle 有权
    含燃料喷嘴的燃烧器

    公开(公告)号：US06931854B2

    公开(公告)日：2005-08-23

    申请号：US10287507

    申请日：2002-11-05

    申请人： Keijirou Saitoh ,  Takashi Kawano ,  Hidemi Niinai ,  Yutaka Kawata ,  Shigemi Mandai ,  Kuniaki Aoyama

    发明人： Keijirou Saitoh ,  Takashi Kawano ,  Hidemi Niinai ,  Yutaka Kawata ,  Shigemi Mandai ,  Kuniaki Aoyama

    IPC分类号： F23D14/02 ,  F23D14/58 ,  F23R3/28 ,  F02C1/00 ,  F02G3/00

    CPC分类号： F23R3/286 ,  F23D2210/00 ,  F23D2900/14004 ,  F23R2900/00014

    摘要： There is provided a combustor comprising a fuel nozzle which is comprised of a rodlike body which has a fuel passage and which is located in an air passage; a plurality of hollow members which are connected to the fuel passage and which extend in radial directions from the rodlike body into the air passage; at least one injection port formed in each hollow member to inject a fuel from the fuel passage into the air passage; and a projection which extends from a farmost inner wall of each hollow member that is most distant from an axis of the rodlike body to the injection port that is most distant from the axis. A hole for leaking fuel that is connected to an air passage may be formed in a farmost inner wall of the hollow member that is more distant from an axis of a rodlike body than the injection port that is most distant from the axis, or may be formed to be adjacent to all the injection ports on an upstream or downstream side in the direction of the airflow. Thus, a vortex does not occur in the hollow column.

    摘要翻译： 提供了一种燃烧器，其包括燃料喷嘴，该燃料喷嘴由具有燃料通道并且位于空气通道中的杆状体构成; 多个中空构件，其连接到燃料通道并且在径向方向上从杆状体延伸到空气通道中; 形成在每个中空构件中的至少一个喷射口，用于将来自燃料通道的燃料喷射到空气通道中; 以及从最远离杆状体的轴线到最远离轴线的喷射口的每个中空构件的农田内壁延伸的突起。 连接到空气通道的用于泄漏燃料的孔可以形成在中空构件的农田内壁中，该中空构件的远离轴线的轴线比距离轴线最远的喷射口更远离杆状体的轴线，或者可以是 形成为与气流方向上游侧或下游侧的所有喷射口相邻。 因此，在中空塔中不会发生涡流。

    Cooling structure of a combustor tail tube
    8.
    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。

    Gas turbine fuel injector with unequal fuel distribution
    9.
    发明授权
    Gas turbine fuel injector with unequal fuel distribution 有权
    具有不均等燃料分配的燃气轮机燃油喷射器

    公开(公告)号：US06460339B2

    公开(公告)日：2002-10-08

    申请号：US09828138

    申请日：2001-04-09

    申请人： Koichi Nishida ,  Katsunori Tanaka ,  Shigemi Mandai ,  Yutaka Kawata ,  Masataka Ohta

    发明人： Koichi Nishida ,  Katsunori Tanaka ,  Shigemi Mandai ,  Yutaka Kawata ,  Masataka Ohta

    IPC分类号： F02G300

    CPC分类号： F23R3/343 ,  F23R3/286

    摘要： A gas turbine combustor improves the fuel distribution from a main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor. The gas turbine combustor is a multi-nozzle type premixing combustor with a nozzle outer tube (7) for forming and injecting a premixed gas of main fuel and combustion air divided and disposed in plural sections around a cone (4) for forming a diffusion flame by reaction between pilot fuel and combustion air disposed in a center of a section of a combustor inner tube (1). Nozzle holes (5a) of a main fuel nozzle (5) are formed in three positions at equal intervals on the nozzle main body wall, and one of them is disposed at the outer periphery of the combustor inner tube (1) on a diametral line linking between the center of the combustor inner tube (1) and the center of the main fuel nozzle (5), whereby the fuel distribution to the outer periphery is decreased.

    摘要翻译： 燃气轮机燃烧器改善来自主燃料喷嘴的燃料分布，抑制内部压力的波动和内管金属温度升高，提高燃烧器的燃烧稳定性和耐久性。 燃气轮机燃烧器是具有喷嘴外管（7）的喷嘴外管（7）的多喷嘴型预混合燃烧器，用于形成并喷射主燃料和燃烧空气的预混合气体，燃烧空气以形成扩散火焰的锥体（4）为中心分成多个部分 通过引燃燃料与设置在燃烧器内管（1）的一部分的中心的燃烧空气之间的反应。 主燃料喷嘴（5）的喷嘴孔（5a）以等间隔在喷嘴主体壁上形成三个位置，其中一个位于燃烧器内管（1）的外径上， 在燃烧器内管（1）的中心与主燃料喷嘴（5）的中心之间连接，从而减少了向外周的燃料分配。