利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

30 条记录 (耗时 0.054 秒)

    Coolant recovery type gas turbine
    3.
    发明授权
    Coolant recovery type gas turbine 有权
    冷却液回收式燃气轮机

    公开(公告)号：US06393829B2

    公开(公告)日：2002-05-28

    申请号：US09308981

    申请日：1999-05-28

    申请人： Shinya Marushima ,  Manabu Matsumoto ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Takashi Machida ,  Masaru Sekihara

    发明人： Shinya Marushima ,  Manabu Matsumoto ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Takashi Machida ,  Masaru Sekihara

    IPC分类号： F02C300

    CPC分类号： F02C7/18 ,  F01D25/12 ,  F05D2260/205 ,  F05D2260/2322

    摘要： A gas turbine has a rotor shaft which includes a plurality of discs, each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion and having spaces arranged between the discs. The respective discs and spacers are arranged in the axial direction. Gap portions are formed between the rotor axis side regions of the discs facing the spacers and adjacent spacers. Contact surfaces contacting each other on both rotor peripheral side regions of the discs facing the spaces and adjacent spacers are formed. A first flow path for supplying a coolant into the moving blades and a second flow path for recovering the coolant heated by the moving blades from the moving blade are provided. A third flow path for introducing fluid into the gap portions is formed in the discs with the third flow path being independent from the first and second flow paths.

    摘要翻译： 燃气轮机具有转子轴，该转子轴包括多个盘，每个盘具有由燃烧气体驱动的多个活动叶片，环形地布置在周边部分上，并且在盘之间具有间隔。 相应的盘和间隔件沿轴向布置。 间隙部分形成在面向间隔物和相邻间隔物的盘的转子轴线侧区域之间。 形成面对空间和相邻间隔物的圆盘的两个转子周边区域彼此接触的接触表面。 提供了用于将冷却剂供应到动叶片中的第一流动路径和用于从动叶片回收由移动叶片加热的冷却剂的第二流路。 用于将流体引入间隙部分的第三流动路径形成在盘中，其中第三流动路径独立于第一和第二流动路径。

    Coolant recovery type gas turbine
    4.
    发明授权
    Coolant recovery type gas turbine 失效
    冷却液回收式燃气轮机

    公开(公告)号：US06735957B2

    公开(公告)日：2004-05-18

    申请号：US10403124

    申请日：2003-04-01

    申请人： Shinya Marushima ,  Manabu Matsumoto ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Takashi Machida ,  Masaru Sekihara

    发明人： Shinya Marushima ,  Manabu Matsumoto ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Takashi Machida ,  Masaru Sekihara

    IPC分类号： F02G712

    CPC分类号： F02C7/18 ,  F01D25/12 ,  F05D2260/205 ,  F05D2260/2322

    摘要： An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

    摘要翻译： 目的是通过抑制作用在燃气轮机的转子上的热应力和热变形来提高燃气轮机的操作可靠性。 燃气轮机具有转子轴，转子轴沿轴向方向依次布置有多个盘，每个盘具有环形地设置在周边部分上的多个燃烧气体驱动的移动叶片和布置在盘之间的间隔件，其特征在于 在转子轴中心部分侧的面对间隔件的盘和相邻的间隔件之间形成间隙部分，形成两个接触表面，这两个接触表面在转子周边侧的两个区域上接触， 上述圆盘面对间隔件和相邻的间隔件，并且提供了将流体引导到上述间隙部分的第三流动路径。

    Gas turbine and gas turbine blade
    8.
    发明授权
    Gas turbine and gas turbine blade 失效
    燃气轮机和燃气轮机叶片

    公开(公告)号：US5393198A

    公开(公告)日：1995-02-28

    申请号：US120474

    申请日：1993-09-14

    申请人： Masami Noda ,  Takashi Ikeguchi ,  Shunichi Anzai ,  Kazuhiko Kawaike ,  Isao Takehara

    发明人： Masami Noda ,  Takashi Ikeguchi ,  Shunichi Anzai ,  Kazuhiko Kawaike ,  Isao Takehara

    IPC分类号： F01D5/18 ,  F01D9/02

    CPC分类号： F01D5/187 ,  F05D2260/2212

    摘要： A blade for a gas turbine has a leading edge portion which has an arc-shaped cross-section, and a maximum thickness portion of the blade is located within this arc. With this blade configuration, an abrupt acceleration of hot gas at the leading edge portion of the blade is restrained, so that the velocity of the hot gas at the blade surface can be made low. Therefore, the heat transfer coefficient from the hot gas to the blade wall is lowered, so that the amount of cooling air required to be passed through the interior of the blade can be reduced.

    摘要翻译： 用于燃气轮机的叶片具有具有弧形横截面的前缘部分，并且叶片的最大厚度部分位于该弧形内。 利用该叶片构造，能够抑制叶片的前端部的热气的突然加速，能够使叶片表面的热气的速度变低。 因此，从热气体到叶片壁的传热系数降低，从而可以减少要通过叶片内部的冷却空气量。

    Turbine blade
    9.
    发明授权
    Turbine blade 失效
    涡轮叶片

    公开(公告)号：US5100293A

    公开(公告)日：1992-03-31

    申请号：US573798

    申请日：1990-08-28

    申请人： Shunichi Anzai ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Masami Noda ,  Tetsuo Sasada ,  Isao Takehara ,  Haruo Urushidani

    发明人： Shunichi Anzai ,  Kazuhiko Kawaike ,  Takashi Ikeguchi ,  Masami Noda ,  Tetsuo Sasada ,  Isao Takehara ,  Haruo Urushidani

    IPC分类号： F01D5/18

    CPC分类号： F01D5/189 ,  F01D5/186 ,  F05D2260/201

    摘要： A cooling structure for a turbine blade. Comprising a hollow-structured main body and a cooling medium discharging device located in the inner cavity of the hollow-structured main body and formed to discharge a cooling medium from the surface thereof, so that the cooling medium discharged from the cooling medium discharging device impinges against the inner surface of the main body to remove the heat from the same. The turbine blade further includes a projection formed on the inner surface of the leading edge of the main body, extending along the spanwise direction of the blade, and the cooling medium discharging device is formed to allow at least part of the cooling medium to directly impinge against proximal portions of the projection. With this arrangement, a turbine blade is provided which allows a small amount of cooling air to cool the turbine blade and its leading edge in particular with great effectiveness.

    Gas turbine with turbine blade cooling
    10.
    发明授权
    Gas turbine with turbine blade cooling 有权
    带涡轮叶片的燃气轮机冷却

    公开(公告)号：US06185924B1

    公开(公告)日：2001-02-13

    申请号：US09173171

    申请日：1998-10-15

    申请人： Manabu Matsumoto ,  Shinya Marushima ,  Takashi Ikeguchi ,  Kazuhiko Kawaike

    发明人： Manabu Matsumoto ,  Shinya Marushima ,  Takashi Ikeguchi ,  Kazuhiko Kawaike

    IPC分类号： F04D2958

    CPC分类号： F02C7/18 ,  F01D5/082 ,  F01D5/085 ,  F01D25/12 ,  F01D25/14 ,  F05D2260/205 ,  F05D2260/232

    摘要： A high efficiency coolant collection type gas turbine is obtained by forming coolant supply and collection flow paths for moving blades in a more outer peripheral side of a gas turbine rotor than a hub, supplying the coolant supplied from a shaft end into the moving blades through the supply flow path, collecting the coolant after cooling into a combustion chamber side, supplying air extracted from a compressor to cool moving blades of a downstream side stage or a rotor outer wall through slits formed from a turbine rotor central portion to the hub, reducing rotor thermal stress and a pressure loss of the coolant flow paths and cooling a high stage side of a compressor rotor.

    摘要翻译： 通过形成用于在燃气轮机转子的外周侧的移动叶片的冷却剂供给和收集流动路径，而不是轮毂，获得高效的冷却剂收集式燃气轮机，将从轴端供应的冷却剂通过 供给流路，冷却到燃烧室侧后收集冷却剂，供给从压缩机抽出的空气，通过从涡轮转子中心部向轮毂形成的狭缝，将下游侧或转子外壁的活动叶片冷却，还原转子 热应力和冷却剂流动路径的压力损失并且冷却压缩机转子的高段侧。