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21 条记录 (耗时 0.045 秒)

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

    公开(公告)号：US08857189B2

    公开(公告)日：2014-10-14

    申请号：US13495499

    申请日：2012-06-13

    申请人： Keisuke Matsuyama ,  Takanori Ito ,  Tei Yamato ,  Koji Maeta ,  Sosuke Nakamura

    发明人： Keisuke Matsuyama ,  Takanori Ito ,  Tei Yamato ,  Koji Maeta ,  Sosuke Nakamura

    IPC分类号： F02C7/24 ,  F02C1/00 ,  F23R3/28

    CPC分类号： F23R3/28 ,  F23R2900/00014

    摘要： In a gas-turbine combustion burner which is provided, at a distal end thereof, with a fuel spraying hole that sprays fuel into a combustion region formed inside a combustion cylinder of a gas-turbine combustor and in which a fuel flow path that guides the fuel, which is supplied from a fuel source, to the fuel spraying hole is formed in the interior thereof, the impedance of a fuel supply system that guides the fuel from the fuel source to the fuel spraying hole is set so that propagation of pressure fluctuations from the combustion region to the fuel supply system becomes an allowable level or less.

    摘要翻译： 在一种燃气轮机燃烧器中，在燃气轮机燃烧器的远端设置有燃料喷射孔，该燃料喷射孔将燃料喷射到形成在燃气轮机燃烧器的燃烧气缸内部的燃烧区域中， 在其内部形成从燃料源供给到燃料喷射孔的燃料，将燃料从燃料源引导到燃料喷射孔的燃料供给系统的阻抗被设定为使压力波动的传播 从燃烧区域到燃料供给系统成为允许水平以下。

    Combustor and gas turbine having the same
    6.
    发明授权
    Combustor and gas turbine having the same 有权
    燃气轮机和燃气轮机相同

    公开(公告)号：US08490744B2

    公开(公告)日：2013-07-23

    申请号：US13121874

    申请日：2009-10-15

    申请人： Sosuke Nakamura ,  Taiki Kinoshita ,  Masaki Ono ,  Keisuke Matsuyama ,  Kenta Taniguchi

    发明人： Sosuke Nakamura ,  Taiki Kinoshita ,  Masaki Ono ,  Keisuke Matsuyama ,  Kenta Taniguchi

    IPC分类号： F02K1/00

    CPC分类号： F23R3/005 ,  F01D9/023 ,  F01D25/04 ,  F23M20/005 ,  F23R3/06 ,  F23R3/46 ,  F23R2900/00014

    摘要： An object is to provide a combustor that requires a small mounting space for an acoustic damper, that can achieve size reduction, and that can improve the ease of maintenance. A combustor (5) of the present invention includes a combustion cylinder (19) that defines a combustion area (23) therein and an acoustic damper (31) that has a damper cover having an acoustic-damper resonance space communicating with the combustion area (23). The damper cover is provided along the combustion cylinder (19) so as to extend in a direction intersecting an axial direction (L) of the combustion cylinder (19).

    摘要翻译： 目的是提供一种需要用于声阻尼器的小的安装空间的燃烧器，其可以实现尺寸减小，并且可以提高维护的便利性。 本发明的燃烧器（5）包括在其中限定燃烧区域（23）的燃烧气缸（19）和具有阻尼器盖的声阻尼器（31），所述阻尼器罩具有与燃烧区域连通的声阻尼器谐振空间 23）。 阻尼器盖沿着燃烧筒（19）设置成沿与燃烧气缸（19）的轴向（L）相交的方向延伸。

    GAS TURBINE
    7.
    发明申请
    GAS TURBINE 审中-公开
    燃气轮机

    公开(公告)号：US20100313567A1

    公开(公告)日：2010-12-16

    申请号：US12866419

    申请日：2008-11-20

    申请人： Sosuke Nakamura ,  Keisuke Matsuyama ,  Takashi Hiyama ,  Yasuro Sakamoto ,  Kaoru Sakata

    发明人： Sosuke Nakamura ,  Keisuke Matsuyama ,  Takashi Hiyama ,  Yasuro Sakamoto ,  Kaoru Sakata

    IPC分类号： F02C3/00

    CPC分类号： F01D9/023 ,  F01D5/142 ,  F01D9/041 ,  F05D2210/30 ,  F05D2210/40 ,  F05D2220/3212

    摘要： In a gas turbine that generates rotational power by supplying fuel to compressed air compressed by a compressor and burning the fuel in a combustor and supplying resultant combustion gas to a turbine, a circumferential distance starting from a leading edge of a turbine first stage nozzle toward a trailing edge side of the first stage nozzle and ending at center of transition pieces of such combustors that are adjacent in a circumferential direction is set relative to a circumferential pitch of such first stage nozzles within a range of 0.05≦S/P≦0.15, and an axial distance between a leading edge of the first stage nozzle and a transition piece rear end of the combustor is set relative to the circumferential pitch of the first stage nozzles within a range of 0.00≦L/P≦0.13. By improving the relative position of a transition piece of the combustor and the first stage nozzle, both suppression of inner pressure fluctuations of the combustor and enhancement in aerodynamic efficiency can be achieved.

    摘要翻译： 在燃气轮机中，通过向由压缩机压缩的压缩空气供给燃料并燃烧燃烧器中的燃料并将合成的燃烧气体供给到涡轮机而产生旋转动力，从涡轮机第一级喷嘴的前缘朝向 第一级喷嘴的后缘侧并且在这样的燃烧器的周向相邻的过渡件的中心处终止，相对于这种第一级喷嘴的周向间距设定在0.05＆lt; NlE; S / P＆nlE; 0.15的范围内， 并且在第一级喷嘴的前缘与燃烧器的过渡件后端之间的轴向距离相对于第一级喷嘴的周向间距设定在0.00＆amp; llE; L / P＆nlE; 0.13的范围内。 通过改善燃烧器和第一级喷嘴的过渡件的相对位置，可以实现燃烧器的内部压力波动的抑制和空气动力学效率的提高。

    Gas turbine having a combustion oscillation suppressing device
    8.
    发明授权
    Gas turbine having a combustion oscillation suppressing device 有权
    具有燃烧振动抑制装置的燃气轮机

    公开(公告)号：US08904794B2

    公开(公告)日：2014-12-09

    申请号：US12671046

    申请日：2008-10-17

    申请人： Keisuke Matsuyama ,  Kotaro Miyauchi

    发明人： Keisuke Matsuyama ,  Kotaro Miyauchi

    IPC分类号： F02C7/24 ,  F01D9/02 ,  F23R3/00

    CPC分类号： F02C7/24 ,  F01D9/023 ,  F05D2260/96 ,  F05D2260/963 ,  F23M20/005 ,  F23R3/00 ,  F23R2900/00014

    摘要： A gas turbine including a combustion oscillation suppressing device disposed to a transition piece of a combustor to define a gas space S, and having a plurality of vent holes through which a gas space L and the inside of the transition piece communicate. The combustion oscillation suppressing device is formed of a first member and a second member which define the gas space, the second member having the plurality of vent holes, and a portion of a transition piece wall includes the second member. A distance from the second member to the first member in the radial direction of the transition piece is a height of the gas space, and when the height of the gas space varies along an axial direction of the transition piece, an opening ratio σp of each of the plurality of vent holes is adjusted depending on the height of the gas space.

    摘要翻译： 一种燃气轮机，包括设置在燃烧器的过渡件上以限定气体空间S的燃烧振荡抑制装置，并且具有多个通气孔，气体空间L和过渡件的内部通过该通气孔连通。 燃烧振动抑制装置由限定气体空间的第一构件和第二构件形成，具有多个通气孔的第二构件和过渡件壁的一部分包括第二构件。 在过渡件的径向方向上从第二构件到第一构件的距离是气体空间的高度，并且当气体空间的高度沿着过渡件的轴向方向变化时，开口率＆sgr 根据气体空间的高度来调节多个通气孔中的每一个。

    GAS TURBINE
    10.
    发明申请
    GAS TURBINE 有权
    燃气轮机

    公开(公告)号：US20100186411A1

    公开(公告)日：2010-07-29

    申请号：US12671046

    申请日：2008-10-17

    申请人： Keisuke Matsuyama ,  Kotaro Miyauchi

    发明人： Keisuke Matsuyama ,  Kotaro Miyauchi

    IPC分类号： F02C7/24

    CPC分类号： F02C7/24 ,  F01D9/023 ,  F05D2260/96 ,  F05D2260/963 ,  F23M20/005 ,  F23R3/00 ,  F23R2900/00014

    摘要： An object of the present invention is to provide a gas turbine that improves appearance of a combustion oscillation suppressing device disposed to a transition piece of a combustor. To achieve the object, a combustion oscillation suppressing device 34 is disposed to a transition piece 32 of a combustor to define a gas space S, and has a plurality of vent holes 343 through which a gas space L and the inside of the transition piece 32 communicate with each other. The combustion oscillation suppressing device 34 has: a first member 341 that has a substantially U-shaped cross-section formed by press-working, and is disposed on the outer circumference of the transition piece 32 with a substantially U-shaped cross-section opening thereof facing the transition piece 32; and a second member 342 that defines the gas space S between the first member 341 and the second member 342 by blocking the substantially U-shaped cross-section opening of the first member 341, and has the vent holes 343. In a radial-direction cross section of the transition piece 32, when the outer diameter of the transition piece 32 varies along an axial direction of the transition piece 32, distances d1 and d2 from the axis L of the transition piece 32 to each bent portion of the first member 341 having a substantially U-shaped cross-section are set to be substantially equal.

    摘要翻译： 本发明的目的在于提供一种能够改善设置在燃烧器的过渡件上的燃烧振动抑制装置的外观的燃气轮机。 为了实现该目的，燃烧振动抑制装置34设置在燃烧器的过渡件32上以形成气体空间S，并且具有多个通气孔343，气体空间L和过渡件32的内部 相互沟通。 燃烧振动抑制装置34具有：第一构件341，其具有通过加压加工形成的大致U字形的截面，并且设置在过渡件32的外周上，具有大致U形的横截面开口 面向过渡件32; 以及第二构件342，其通过阻挡第一构件341的大致U形的横截面开口限定第一构件341和第二构件342之间的气体空间S，并且具有通气孔343。 当过渡件32的外径沿着过渡件32的轴向方向变化时，过渡件32的横截面为从过渡件32的轴线L到第一件341的每个弯曲部分的距离d1和d2 具有基本上U形的横截面被设定为基本相等。