利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

49 条记录 (耗时 0.042 秒)

    Combustor
    1.
    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
    3.
    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
    5.
    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 combustor
    6.
    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 with fuel and air swirler
    8.
    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。

    Three-dimensional swirler in a gas turbine combustor
    9.
    发明授权
    Three-dimensional swirler in a gas turbine combustor 有权
    燃气轮机燃烧器中的三维旋流器

    公开(公告)号：US06502399B2

    公开(公告)日：2003-01-07

    申请号：US09794134

    申请日：2001-02-28

    申请人： Shigemi Mandai ,  Masataka Ohta ,  Mitsuru Inada ,  Shinji Akamatsu

    发明人： Shigemi Mandai ,  Masataka Ohta ,  Mitsuru Inada ,  Shinji Akamatsu

    IPC分类号： F23R314

    CPC分类号： F23R3/14

    摘要： A pre-mixture forming swirler in a gas turbine pre-mixed flame type low NOx combustor is improved so as to accelerate mixing of fuel and air and to prevent the occurrence of flame stagnation and burning of components. In particular, a three-dimensional swirler is constructed such that each swirler vane is twisted from a hub side thereof to a tip side so that a fitting angle of the tip side relative to a center axis of a fuel nozzle is larger than an angle of the hub side. Thereby, while the angle of the hub side is set smaller so that flame stagnation and burning of components resulted therefrom may be prevented from occurring, the angle of the tip side may be selected so that the shearing flow necessary for appropriate mixing of fuel and air is obtained. Thus, favorable pre-mixing is achieved, life deterioration due to burning, etc., is prevented and combustion efficiency is enhanced.

    摘要翻译： 在燃气轮机预混合火焰型低NOx燃烧器中形成旋流器的预混合物得到改善，以加速燃料和空气的混合，并防止部件火焰停滞和燃烧。 特别地，三维旋流器被构造成使得每个旋流器叶片从其轮毂侧扭转到尖端侧，使得尖端侧相对于燃料喷嘴的中心轴线的配合角度大于 集线器侧。 由此，在将轮毂侧的角度设定得较小的同时，能够防止由此引起的部件产生火焰停滞和燃烧的情况下，可以选择前端侧的角度，使得适当地混合燃料和空气所需的剪切流 获得。 因此，可以实现良好的预混合，防止燃烧等引起的寿命劣化，提高燃烧效率。