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28 条记录 (耗时 0.033 秒)

    Fuel nozzle, gas turbine combustor with the same, and gas turbine with the same
    21.
    发明授权
    Fuel nozzle, gas turbine combustor with the same, and gas turbine with the same 有权
    燃油喷嘴，燃气轮机与燃气轮机相同，与燃气轮机相同

    公开(公告)号：US09062885B2

    公开(公告)日：2015-06-23

    申请号：US13216966

    申请日：2011-08-24

    申请人： Eiji Takami ,  Katsunori Tanaka ,  Koichi Nishida ,  Shinji Akamatsu ,  Hideki Haruta ,  Tomo Kawakami ,  Kei Inoue

    发明人： Eiji Takami ,  Katsunori Tanaka ,  Koichi Nishida ,  Shinji Akamatsu ,  Hideki Haruta ,  Tomo Kawakami ,  Kei Inoue

    IPC分类号： F23R3/28 ,  B05B15/00 ,  F23R3/14 ,  F23R3/36

    CPC分类号： F23R3/14 ,  F23R3/28 ,  F23R3/283 ,  F23R3/36 ,  F23R2900/03044

    摘要： A fuel nozzle for a gas turbine combustor includes: an internal cylinder; a burner cylinder concentrically provided on the outer circumference of the internal cylinder in the vicinity of its distal end to surround the distal end portion of the internal cylinder; an air passage provided between the burner cylinder and the internal cylinder for delivering combustion air; a space provided at an axial center of the internal cylinder and extending in the axial direction of the internal cylinder; a plurality of inner passages provided at approximately equal intervals in the circumferential direction of the internal cylinder for injecting fluid through its distal end portion; and at least one communication portion provided on the upstream side of the distal end portion of the internal cylinder and extending from the outer wall of the internal cylinder toward the inner side in the radial direction to communicate with the space.

    摘要翻译： 一种用于燃气轮机燃烧器的燃料喷嘴，包括：内筒; 燃烧器筒同心地设置在内圆筒的远端附近的外周上，以包围内筒的前端部; 设置在燃烧器筒和内筒之间用于输送燃烧空气的空气通道; 设置在所述内筒的轴心且在所述内筒的轴向延伸的空间; 多个内通道，其在所述内筒的圆周方向上以相等的间隔设置，用于通过其前端部分喷射流体; 以及至少一个连通部，其设置在所述内筒的前端部的上游侧，并且从所述内筒的外壁向径向内侧延伸，与所述空间连通。

    Gas turbine combustor having multiple independently operable burners and staging method thereof
    24.
    发明授权
    Gas turbine combustor having multiple independently operable burners and staging method thereof 有权
    具有多个可独立操作的燃烧器的燃气轮机燃烧器及其分级方法

    公开(公告)号：US07797942B2

    公开(公告)日：2010-09-21

    申请号：US11266202

    申请日：2005-11-04

    申请人： Toshihiko Saitoh ,  Masataka Ohta ,  Shinji Akamatsu ,  Masakazu Nose

    发明人： Toshihiko Saitoh ,  Masataka Ohta ,  Shinji Akamatsu ,  Masakazu Nose

    IPC分类号： F02C1/00 ,  F02G3/00

    CPC分类号： F23R3/343 ,  F23R3/286

    摘要： In a combustor of a gas turbine which has a pilot nozzle being installed to the center of the axis of a combustor basket and a plurality of main nozzles being installed to the vicinity of the pilot nozzle and provided with a premixing tool on the outer circumference thereof, wherein, fuel being injected as air-fuel pre-mixture from the main nozzle into the interior of a transition piece forming a combustion chamber downstream of the combustor basket is ignited by diffusion flame being generated by the pilot nozzle in the transition piece so as to generate a premixed flame in the transition piece, wherein combustion is performed by a part of the plurality of main nozzles from start-up until a predetermined load rate and then performed by adding the remaining portion of the plurality of main nozzles when the predetermined load rate is exceeded.

    摘要翻译： 在燃气轮机的燃烧器中，具有安装在燃烧器筐的轴心的中心的先导喷嘴，并且多个主喷嘴安装在导向喷嘴附近，并且在其外周上设置有预混合工具 其特征在于，从所述主喷嘴向所述燃烧器筐下游形成燃烧室的过渡部件的内部喷射的燃料被喷射，所述扩散火焰由所述过渡部件中的先导喷嘴产生， 以在过渡件中产生预混合的火焰，其中燃料由多个主喷嘴的一部分从起动直到预定的负载率进行，然后通过在预定的负载下加入多个主喷嘴的剩余部分 率超过。

    Gas turbine combustor with fuel and air swirler
    26.
    发明授权
    Gas turbine combustor with fuel and air swirler 有权
    燃气涡轮燃烧器与燃料和空气旋流器

    公开(公告)号：US06301900B1

    公开(公告)日：2001-10-16

    申请号：US09554447

    申请日：2000-07-06

    申请人： Shigemi Mandai ,  Masataka Ohta ,  Hideki Haruta ,  Koichi Nishida ,  Shinji Akamatsu ,  Masahiro Kamogawa

    发明人： Shigemi Mandai ,  Masataka Ohta ,  Hideki Haruta ,  Koichi Nishida ,  Shinji Akamatsu ,  Masahiro Kamogawa

    IPC分类号： F23R314

    CPC分类号： F23D11/38 ,  F23D11/107 ,  F23D2900/00016 ,  F23R3/28

    摘要： A nozzle cap (10) is disposed downstream of a nozzle body (1) of a combustor for a gas turbine, an inner surface part (12) of which is of a conical shape diverging downstream to define a fuel-jet guide (17) for guiding fuel jet ejected from one or more nozzle holes (3) provided at the center of a downstream end surface of the nozzle body. Fuel ejected from the one or more nozzle holes smoothly runs along the fuel-jet guide without remaining there to join with a swirl stream (S) in a swirl path (9), and to burn without generating smoke. Air introduced into a first auxiliary air path (6) defined between the nozzle body and a partition (5) at a position upstream thereof passes through a second auxiliary air path (16) defined between a downstream end surface (2) of the nozzle body (1) and an upstream end surface (13) of the nozzle cap and reaches an entrance (19) of the fuel-jet guide. The air then flows along the fuel-jet guide to cool the nozzle cap and prevent the fuel ejected from the one or more nozzle holes from sticking to the nozzle cap.

    摘要翻译： 喷嘴盖（10）设置在用于燃气轮机的燃烧器的喷嘴主体（1）的下游，其内表面部分（12）具有向下游扩散的锥形形状，以限定燃料喷射引导件（17） 用于引导从设置在喷嘴体的下游端面的中心的一个或多个喷嘴孔（3）喷出的燃料喷射。 从一个或多个喷嘴孔喷出的燃料沿燃料喷射导向装置平滑地延伸，而不残留在漩涡路径（9）中的旋流（S），并且燃烧而不产生烟雾。 被引入第一辅助空气通道（6）中的空气通道（6），其限定在喷嘴主体和分隔件（5）之间的位于其上游的位置处，通过限定在喷嘴体的下游端面（2）之间的第二辅助空气通道 （1）和喷嘴盖的上游端表面（13）到达燃料喷射引导件的入口（19）。 然后空气沿着燃料喷射引导件流动以冷却喷嘴帽，并且防止从一个或多个喷嘴孔喷出的燃料粘附到喷嘴帽。

    Gas turbine combustor
    27.
    发明授权
    Gas turbine combustor 有权
    燃气轮机燃烧器

    公开(公告)号：US06282886B1

    公开(公告)日：2001-09-04

    申请号：US09437146

    申请日：1999-11-10

    申请人： Yoshichika Sato ,  Yoji Kochi ,  Koichi Akagi ,  Kazuya Kobayashi ,  Koichi Nishida ,  Shinji Akamatsu ,  Hideki Haruta ,  Kotaro Miyauchi ,  Rintaro Chikami ,  Shigemi Mandai ,  Masataka Ota

    发明人： Yoshichika Sato ,  Yoji Kochi ,  Koichi Akagi ,  Kazuya Kobayashi ,  Koichi Nishida ,  Shinji Akamatsu ,  Hideki Haruta ,  Kotaro Miyauchi ,  Rintaro Chikami ,  Shigemi Mandai ,  Masataka Ota

    IPC分类号： F02C300

    CPC分类号： F23L7/00 ,  F23C9/00 ,  F23D2900/00008 ,  F23L2900/07002 ,  F23R3/005 ,  F23R3/14 ,  F23R3/343 ,  F23R3/60

    摘要： In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

    摘要翻译： 在燃烧器20的内管28的中心部分，引导燃料喷嘴22和引导锥体33布置，并且主燃料喷嘴21和主旋流器32在其周围。 进气部（X-1）设有用于使进气均匀的整流管11。 在进气部分（X-2）中，在内管28的周向壁上设有适当数量的气孔。在主旋流器部分（X-3）和先导锥体部分（X-4）中， 使用主旋流器32，并且分别采用对先导式旋流器33的热应力影响较小的优化焊接结构。 尾管冷却部（X-5）具有对热应力影响较小的冷却结构，均匀地冷却尾管24的凸缘部71。 通过部分（X-1）至（X-5）的改进，燃烧器20中获得较高温度的障碍物被溶解并且燃烧器性能提高。