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    Combustor
    1.
    发明授权
    Combustor 有权
    燃烧器

    公开(公告)号：US06267583B1

    公开(公告)日：2001-07-31

    申请号：US09289606

    申请日：1999-04-12

    申请人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Eiji Akita

    发明人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Eiji Akita

    IPC分类号： F23D1484

    CPC分类号： F23D23/00 ,  F23D2206/10 ,  F23M20/005

    摘要： A combustor includes a pilot fuel nozzle and a plurality of main premixing nozzles arranged therearound for forming a premixture of air and fuel supplied from a main fuel nozzle, and is improved so as not to cause vibratory combustion. Pilot fuel nozzle unit 104 comprises a plurality of pilot fuel nozzles 103. A plurality of main premixing nozzles 102 are disposed on a coaxial circumference of the pilot fuel nozzle unit 104. The pilot fuel nozzles 103 are arranged irregularly in a circumferential direction of the pilot fuel nozzle unit 104, so as to form portion 105 where there is no pilot fuel nozzle 103. Premature in the main premixing nozzles 102 positioned corresponding to the pilot fuel nozzle 103 burns with comparatively short flames. Premature in the main premixing nozzles 102 positioned corresponding to the portion 105 of no pilot fuel nozzle 103 burns with long flames because of flames spreading from adjacent main fuel nozzles. Thus, by differences in flame length, heat generation rate distribution is dispersed.

    摘要翻译： 燃烧器包括导向燃料喷嘴和布置在其周围的多个主预混合喷嘴，用于形成从主燃料喷嘴供应的空气和燃料的预混合物，并且被改进以便不引起振动燃烧。 先导燃料喷嘴单元104包括多个先导燃料喷嘴103.多个主要预混合喷嘴102设置在引燃燃料喷嘴单元104的同轴圆周上。引燃燃料喷嘴103沿飞行员的周向不规则地排列 燃料喷嘴单元104，以便形成不存在先导燃料喷嘴103的部分105.在对应于引燃燃料喷嘴103定位的主预混合喷嘴102中，过早地燃烧较短的火焰。 由于相邻的主燃料喷嘴的火焰蔓延，在与主燃料喷嘴103的部分105对应定位的主预混合喷嘴102中过早地燃烧着较长的火焰。 因此，通过火焰长度的差异，分散发热率分布。

    Combustor
    2.
    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。

    Gas turbine combustor
    4.
    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。

    Gas turbine combustor
    6.
    发明授权
    Gas turbine combustor 失效
    燃气轮机燃烧器

    公开(公告)号：US06209326B1

    公开(公告)日：2001-04-03

    申请号：US09244030

    申请日：1999-02-04

    申请人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Tatsuo Ishiguro ,  Mitsuru Inada ,  Hideki Haruta

    发明人： Shigemi Mandai ,  Koichi Nishida ,  Masataka Ota ,  Tatsuo Ishiguro ,  Mitsuru Inada ,  Hideki Haruta

    IPC分类号： F02C100

    CPC分类号： F23R3/286 ,  F23C7/004 ,  F23D14/02 ,  F23D2205/00 ,  F23D2206/10 ,  F23D2900/14021

    摘要： To prepare a more homogeneous premixture than that of the device of the prior art thereby to suppress an NOx emission and to lower a fuel feed pressure. A gas turbine combustor comprising: an outer cylinder 106 having main swirlers 101 therein and adapted to be fed with air; and an annular fuel feed manifold 110 disposed at the outer circumference of the outer cylinder 106 on the upstream or downstream side of the main swirlers 101 and having a plurality of nozzle ports 111 communicating with the inside of the outer cylinder 106, so that a fuel is injected from the outer circumference to the center of the air flowing in the outer cylinder 106.

    摘要翻译： 为了制备比现有技术的装置更均匀的预混合物，从而抑制NOx排放并降低燃料供给压力.1。一种燃气轮机燃烧器，包括：外筒106，其中具有主旋流器101，并适于供给 空气; 以及环形燃料供给歧管110，其设置在主旋流器101的上游侧或下游侧的外筒106的外周，并具有与外筒106的内部连通的多个喷嘴口111， 从外圆周喷射到在外筒106中流动的空气的中心。

    Gas turbine system and combined plant comprising the same
    7.
    发明授权
    Gas turbine system and combined plant comprising the same 有权
    燃气轮机系统及其组合设备

    公开(公告)号：US06389796B1

    公开(公告)日：2002-05-21

    申请号：US09666188

    申请日：2000-09-21

    申请人： Shigemi Mandai ,  Hidetaka Mori ,  Hideaki Sugishita ,  Eiji Akita

    发明人： Shigemi Mandai ,  Hidetaka Mori ,  Hideaki Sugishita ,  Eiji Akita

    IPC分类号： F02C330

    CPC分类号： F01K23/10 ,  F01K21/047 ,  Y02E20/16

    摘要： A gas turbine system and a combined plant including the gas turbine system provides a higher effect in realizing a high plant efficiency and reduction of NOx generation. The gas turbine system includes a compressor (1) for compressing combustion air, a combustor (2) for burning fuel with the combustion air, and a gas turbine (3) driven by high temperature gas generated at the combustor (2). A portion of the exhaust gas discharged from the gas turbine (3) is recirculated back into the combustor (2). A combined plant can also include the gas turbine system.

    摘要翻译： 燃气轮机系统和包括燃气轮机系统的组合设备在实现高设备效率和减少NOx产生方面提供更高的效果。 燃气轮机系统包括用于压缩燃烧空气的压缩机（1），用于燃烧燃烧空气的燃料的燃烧器（2）和由燃烧器（2）产生的高温气体驱动的燃气轮机（3）。 从燃气轮机（3）排出的废气的一部分再循环回到燃烧器（2）中。 组合式工厂还可以包括燃气轮机系统。

    Gas turbine and gas turbine combustor
    8.
    发明授权
    Gas turbine and gas turbine combustor 有权
    燃气轮机和燃气轮机燃烧器

    公开(公告)号：US06634175B1

    公开(公告)日：2003-10-21

    申请号：US09762598

    申请日：2001-02-09

    申请人： Yutaka Kawata ,  Shigemi Mandai ,  Yoshiaki Tsukuda ,  Eiji Akita ,  Hisato Arimura

    发明人： Yutaka Kawata ,  Shigemi Mandai ,  Yoshiaki Tsukuda ,  Eiji Akita ,  Hisato Arimura

    IPC分类号： F23R310

    CPC分类号： F23R3/04

    摘要： A gas turbine combustor has homogenous air inflow by elimination of turbulence from the air, reducing combustion instability. A combustor 3 has, at its center, a pilot nozzle 8 and eight main nozzles 7 around the pilot nozzle 8. The air flows in around the individual nozzles 7 and 8 to the leading end of the combustor 3 so that it is used for combustion. An annular flow ring 20, having a semicirculat section, is disposed at the upstream end portion of a combustion cylinder 10, and a porous plate 50 and a surrounding rib 51 are disposed downstream of the flow ring 20. The air inflow is smoothly turned at first by the flow ring 20 and then straightened by the porous plate 50 so that the air flows without any disturbance around the individual nozzles 7 and 8 to the leading end, thereby reducing combustion instability.

    摘要翻译： 燃气轮机燃烧器通过消除来自空气的紊流而具有均匀的空气流入，从而降低燃烧不稳定性。 燃烧器3在其中心处具有引导喷嘴8和围绕引燃喷嘴8的八个主喷嘴7.空气在单独的喷嘴7和8周围流到燃烧器3的前端，使其用于燃烧 。 具有半圆形部分的环形流动环20设置在燃烧气缸10的上游端部，并且多孔板50和周围肋51设置在流动环20的下游。空气流入平滑地转向 首先通过流动环20，然后由多孔板50拉直，使得空气在各个喷嘴7和8周围没有任何干扰地流到前端，从而减少燃烧不稳定性。

    Gas turbine combustor
    9.
    发明授权
    Gas turbine combustor 失效
    燃气轮机燃烧器

    公开(公告)号：US6158223A

    公开(公告)日：2000-12-12

    申请号：US140011

    申请日：1998-08-26

    申请人： Shigemi Mandai ,  Masataka Ota ,  Satoshi Tanimura ,  Hideki Haruta

    发明人： Shigemi Mandai ,  Masataka Ota ,  Satoshi Tanimura ,  Hideki Haruta

    IPC分类号： F23R3/10 ,  F23D23/00 ,  F23R3/02 ,  F23R3/14 ,  F23R3/20 ,  F23R3/28 ,  F23R3/32 ,  F23R3/54

    CPC分类号： F23R3/286 ,  F23D23/00 ,  F23R3/02 ,  F23R3/54

    摘要： In gas turbine combustor in which combustion air flows on outer periphery of cylinder body and turns to enter the cylinder body while being mixed with fuel in main burner to form pre-mixture, there is provided upstream of the main burner 101 in the combustor 103 a rectifier 106 or 108 for rectifying the combustion air so as to make flow velocity of the combustion air uniform, thereby shortcomings in the prior art of concentration non-uniformity of the pre-mixture of main fuel and combustion air, high concentration of NO.sub.x generated from the main burner 101 in combustion, etc. are eliminated and larger combustion range to maintain stable combustion is attained.

    摘要翻译： 在燃气轮机燃烧器中，燃烧空气在气缸本体的外周上流动，并与主燃烧器中的燃料混合而进入气缸本体以形成预混合物，在燃烧器103a中的主燃烧器101的上游 用于整流燃烧空气的整流器106或108，以使燃烧空气的流速均匀，从而在主燃料和燃烧空气的预混合物的浓度不均匀性的现有技术中存在缺点，由 燃烧时的主燃烧器101等被消除，燃烧范围更大，能够保持稳定的燃烧。

    Gas turbine combustor
    10.
    发明授权
    Gas turbine combustor 有权
    燃气轮机燃烧器

    公开(公告)号：US6105372A

    公开(公告)日：2000-08-22

    申请号：US145499

    申请日：1998-09-02

    申请人： Shigemi Mandai ,  Masataka Ota ,  Katsunori Tanaka ,  Shinji Akamatsu

    发明人： Shigemi Mandai ,  Masataka Ota ,  Katsunori Tanaka ,  Shinji Akamatsu

    IPC分类号： F02C7/18 ,  F23R3/10 ,  F23R3/42 ,  F02C1/00

    CPC分类号： F23R3/10 ,  F05B2260/202

    摘要： A gas turbine combustor having a combustion chamber (10) with a steam-cooled peripheral wall (2) has an air hole (1) for injecting dilution air therethrough bored in the peripheral wall (2) on an upstream side of the combustion chamber (10). The air is thereby supplied through the air hole (1) into the vicinity of an inner surface of the peripheral wall (2) to form a film flow of air, and an increase of the fuel concentration there is suppressed. The dilution air is preferably supplied from a gas turbine compressor (6).

    摘要翻译： 具有具有蒸汽冷却周边壁（2）的燃烧室（10）的燃气轮机燃烧器具有用于在燃烧室的上游侧的周壁（2）中喷射稀释空气的空气孔（1） 10）。 因此，空气通过空气孔（1）供给到周壁（2）的内表面附近，形成空气的膜流，抑制了燃料浓度的增加。 稀释空气优选地从燃气涡轮压缩机（6）供给。