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    GAS TURBINE AND OPERATING METHOD THEREOF
    1.
    发明申请
    GAS TURBINE AND OPERATING METHOD THEREOF 有权
    燃气轮机及其运行方法

    公开(公告)号：US20110138818A1

    公开(公告)日：2011-06-16

    申请号：US13056064

    申请日：2009-09-24

    申请人： Satoshi Mizukami ,  Tatsuo Ishiguro ,  Junichiro Masada ,  Kazumasa Takata ,  Yuya Fukunaga ,  Hiroki Takahashi ,  Masaki Satoh ,  Yoshiaki Nishimura ,  Norio Oogai ,  Souji Hasegawa ,  Masato Hayashi

    发明人： Satoshi Mizukami ,  Tatsuo Ishiguro ,  Junichiro Masada ,  Kazumasa Takata ,  Yuya Fukunaga ,  Hiroki Takahashi ,  Masaki Satoh ,  Yoshiaki Nishimura ,  Norio Oogai ,  Souji Hasegawa ,  Masato Hayashi

    IPC分类号： F02C7/18 ,  F02C7/26 ,  F02C7/12 ,  F02C6/08

    CPC分类号： F01D11/24 ,  F01D21/00 ,  F01D21/12 ,  F02C7/08 ,  F02C7/12 ,  F02C7/18 ,  F05D2260/205 ,  F05D2260/608

    摘要： Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device (40) connected to a branching channel (42) branching from the discharge side of a compressor (11) and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (11); a temperature-control-medium supply channel (43) that guides compressed air pressurized at the pressuring device (40) to a turbine-cooling-medium channel (50) provided in stationary components of a turbine (13); and a temperature-control-medium return channel (44) that guides the compressed air that has passed through the turbine-cooling-medium channel (50) to the discharge side of the compressor (11) such that the flows are combined, and the pressurizing device (40) is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (50). The pressurizing device (40) is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (13).

    摘要翻译： 提供一种燃气轮机，其能够通过在燃气轮机启动期间ACC系统的快速操作控制来实现燃气轮机的高速启动，提高涡轮机固定部​​件的冷却效率，并且快速地执行回猫所需的操作 在燃气轮机停机期间的预防。 包括连接到从压缩机（11）的排出侧分支的分支通道（42）并且能够独立于压缩机（11）执行用于引入和加压空气的操作的加压装置（40）。 将压缩装置（40）加压的压缩空气引导到设置在涡轮机（13）的静止部件中的涡轮冷却介质通道（50）的温度控制介质供给通路（43）。 以及温度控制介质返回通道（44），其将已经通过所述涡轮冷却介质通道（50）的压缩空气引导到所述压缩机（11）的排出侧，使得所述流合并，并且 加压装置（40）在燃气轮机起动时运转，并且在启动之前准备进行，以通过使涡轮机冷却介质通道（50）中的压缩空气流动来进行升温和冷却。 加压装置（40）在燃气轮机关闭期间运行，以排出剩余在涡轮机（13）中的高温气体。

    Gas turbine and operating method thereof
    2.
    发明授权
    Gas turbine and operating method thereof 有权
    燃气轮机及其运行方法

    公开(公告)号：US09255490B2

    公开(公告)日：2016-02-09

    申请号：US13056064

    申请日：2009-09-24

    申请人： Satoshi Mizukami ,  Tatsuo Ishiguro ,  Junichiro Masada ,  Kazumasa Takata ,  Yuya Fukunaga ,  Hiroki Takahashi ,  Masaki Satoh ,  Yoshiaki Nishimura ,  Norio Oogai ,  Souji Hasegawa ,  Masato Hayashi

    发明人： Satoshi Mizukami ,  Tatsuo Ishiguro ,  Junichiro Masada ,  Kazumasa Takata ,  Yuya Fukunaga ,  Hiroki Takahashi ,  Masaki Satoh ,  Yoshiaki Nishimura ,  Norio Oogai ,  Souji Hasegawa ,  Masato Hayashi

    IPC分类号： F01D11/24 ,  F02C7/18 ,  F01D21/00 ,  F02C7/12

    CPC分类号： F01D11/24 ,  F01D21/00 ,  F01D21/12 ,  F02C7/08 ,  F02C7/12 ,  F02C7/18 ,  F05D2260/205 ,  F05D2260/608

    摘要： Provided is a gas turbine capable of achieving high-speed startup of the gas turbine through quick operation control of an ACC system during startup of the gas turbine, improving the cooling efficiency of turbine stationary components, and quickly carrying out an operation required for cat back prevention during shutdown of the gas turbine. Included are a pressurizing device (40) connected to a branching channel (42) branching from the discharge side of a compressor (11) and capable of carrying out an operation for introducing and pressurizing air independently from the compressor (11); a temperature-control-medium supply channel (43) that guides compressed air pressurized at the pressuring device (40) to a turbine-cooling-medium channel (50) provided in stationary components of a turbine (13); and a temperature-control-medium return channel (44) that guides the compressed air that has passed through the turbine-cooling-medium channel (50) to the discharge side of the compressor (11) such that the flows are combined, and the pressurizing device (40) is operated at startup of the gas turbine and in preparation immediately before startup to carry out temperature-raising and cooling by letting the compressed air flow in the turbine-cooling-medium channel (50). The pressurizing device (40) is operated during shutdown of the gas turbine to exhaust the high-temperature gas remaining in the turbine (13).

    摘要翻译： 提供一种燃气轮机，其能够通过在燃气轮机启动期间ACC系统的快速操作控制来实现燃气轮机的高速启动，提高涡轮机固定部​​件的冷却效率，并且快速地执行回猫所需的操作 在燃气轮机关闭期间的预防。 包括连接到从压缩机（11）的排出侧分支的分支通道（42）并且能够独立于压缩机（11）执行用于引入和加压空气的操作的加压装置（40）。 将压缩装置（40）加压的压缩空气引导到设置在涡轮机（13）的静止部件中的涡轮冷却介质通道（50）的温度控制介质供给通路（43）。 以及温度控制介质返回通道（44），其将已经通过所述涡轮冷却介质通道（50）的压缩空气引导到所述压缩机（11）的排出侧，使得所述流合并，并且 加压装置（40）在燃气轮机起动时运转，并且在启动之前准备进行，以通过使涡轮机冷却介质通道（50）中的压缩空气流动来进行升温和冷却。 加压装置（40）在燃气轮机关闭期间运行，以排出剩余在涡轮机（13）中的高温气体。

    Gas turbine cooled blade
    5.
    发明授权
    Gas turbine cooled blade 有权
    燃气轮机冷却叶片

    公开(公告)号：US06290462B1

    公开(公告)日：2001-09-18

    申请号：US09272559

    申请日：1999-03-19

    申请人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

    发明人： Tatsuo Ishiguro ,  Koji Watanabe ,  Masaaki Matsuura ,  Kenichiro Takeishi ,  Junichiro Masada ,  Yasuoki Tomita ,  Kiyoshi Suenaga

    IPC分类号： F01D1100

    CPC分类号： F01D5/187 ,  F05D2250/185 ,  F05D2260/2212

    摘要： A gas turbine cooled blade is constructed without an increase in the number of parts or time requirements, in which seal air is maintained at a lower temperature with the heat exchange rate being suppressed, and the heat transfer rate of the cooling medium in cooling passage is enhanced. A plurality of cooling passages (A, B, C, D, E) is provided in a blade, and the first row cooling passage (A) is covered at the blade inner and outer peripheries and communicates with the second row cooling passage (B) through communication holes (6) and with the main flow gas path through film cooling holes (7). The second row cooling passage (B) communicates with the blade inner peripheral cavity (10) to form a seal air supply passage. A plurality of ribs (31) are disposed on the inner wall of cooling passage (22) with a predetermined pitch (P). The ribs are arranged alternately and are inclined against cooling medium flow with respective higher first end contacting lower side faces of an immediately upstream rib at a position on both side portions of cooling passage (22). High heat transfer rate areas are formed on both side portions of cooling passage (22), and the average heat transfer rate in cooling passage is enhanced.

    摘要翻译： 在不增加部件或时间要求的情况下构建燃气轮机冷却叶片，其中密封空气在热交换率被抑制下保持在较低温度，并且冷却通道中的冷却介质的传热速率为 增强。 多个冷却通道（A，B，C，D，E）设置在叶片中，第一排冷却通道（A）被覆盖在叶片的内周和外周，并与第二排冷却通道 ）通过连通孔（6）并且主流动气体通道通过膜冷却孔（7）。 第二排冷却通道（B）与叶片内周腔（10）连通，形成密封空气供给通道。 多个肋（31）以预定的间距（P）设置在冷却通道（22）的内壁上。 这些肋交替布置并且相对于冷却介质流倾斜，并且在冷却通道（22）的两侧部分的位置处，相应较高的第一端接触紧紧上游的肋的下侧面。 在冷却通道（22）的两侧形成有高的传热率区域，并且冷却通路的平均传热率提高。

    Gas turbine having cooling-air transfer system
    6.
    发明申请
    Gas turbine having cooling-air transfer system 审中-公开
    具有冷却空气传输系统的燃气轮机

    公开(公告)号：US20070271930A1

    公开(公告)日：2007-11-29

    申请号：US11416454

    申请日：2006-05-03

    申请人： Yoshimasa Takaoka ,  Masato Araki ,  Vincent Laurello ,  Masahito Kataoka ,  Junichiro Masada ,  Koichi Ishizaka ,  Naoki Hagi

    发明人： Yoshimasa Takaoka ,  Masato Araki ,  Vincent Laurello ,  Masahito Kataoka ,  Junichiro Masada ,  Koichi Ishizaka ,  Naoki Hagi

    IPC分类号： F02C7/12

    CPC分类号： F01D5/06 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  Y02T50/676

    摘要： A gas turbine includes a cooling-air transfer system. The cooing-air transfer system extracts part of air discharged from a compressor to a chamber, and transfers the part of air as cooling air to a rotor disk. The cooling-air transfer system includes a plurality of tubular nozzles independently arranged in a circle inside the chamber to surround a rotor, and a seal disk having seal-disk cooling conduits arranged in a circle around the axis of the rotor so as to receive cooling air ejected from the tubular nozzles. The cooling-air transfer system swirls the cooling air ejected from the tubular nozzles.

    摘要翻译： 燃气轮机包括冷却空气输送系统。 冷凝空气输送系统将从压缩机排出的空气的一部分提取到室，并将作为冷却空气的空气的一部分转移到转子盘。 冷却空气传送系统包括多个管状喷嘴，其独立地设置在腔室内的圆周中以围绕转子;以及密封盘，其具有围绕转子轴线布置成圆形的密封盘冷却导管，以便接收冷却 从管状喷嘴排出的空气。 冷却空气传送系统使从管状喷嘴喷出的冷却空气旋转。

    Cooling system of ring segment and gas turbine
    8.
    发明授权
    Cooling system of ring segment and gas turbine 有权
    环段和燃气轮机的冷却系统

    公开(公告)号：US08550778B2

    公开(公告)日：2013-10-08

    申请号：US12763723

    申请日：2010-04-20

    申请人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    发明人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    IPC分类号： F01D5/18

    CPC分类号： F02C7/12 ,  F01D11/24 ,  F05D2240/11

    摘要： In a cooling system of ring segment that cools a ring segment of a gas turbine, the segment body of the ring segment is constituted from a collision plate that has a small hole that blows out cooling air, a cooling space that is enclosed by the collision plate and the main body of the segment body; a first cavity that receives the cooling air from the cooling space; and a first cooling passage, of which one end communicates with the first cavity, and the other end blows out the cooling air from openings that are arranged in the side end portion into combustion gas; the openings of the first cooling passages being arranged so that the arrangement pitch of the openings becomes smaller or the opening area of the openings becomes larger on the upstream in the flow direction of the combustion gas than the openings on the downstream, and are arranged so that the arrangement pitch of the openings becomes larger or the opening area of the openings becomes smaller on the downstream in the flow direction of the combustion gas than the openings on the upstream.

    摘要翻译： 在冷却燃气轮机的环段的环段的冷却系统中，环段的节段主体由具有吹出冷却空气的小孔的碰撞板，被碰撞包围的冷却空间构成 板体和主体的主体; 从冷却空间接收冷却空气的第一腔; 以及第一冷却通路，其一端与第一空腔连通，另一端从布置在侧端部的开口吹出冷却空气为燃烧气体; 第一冷却通道的开口被布置成使得开口的排列间距变得更小，或者在燃烧气体的流动方向上游的开口面积比下游的开口更大，并且被布置成 在燃烧气体的流动方向的下游，开口的排列间距比上游的开口变大，开口的开口面积变小。

    Cooling system of ring segment and gas turbine
    9.
    发明授权
    Cooling system of ring segment and gas turbine 有权
    环段和燃气轮机的冷却系统

    公开(公告)号：US08480353B2

    公开(公告)日：2013-07-09

    申请号：US12913397

    申请日：2010-10-27

    申请人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    发明人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    IPC分类号： F04D29/58

    CPC分类号： F01D25/246 ,  F01D9/04 ,  F01D11/005 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/11 ,  F05D2260/205

    摘要： A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region and a second region having a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages.

    摘要翻译： 一种用于燃气轮机的环段的冷却系统，其包括沿着所述节段主体的主体的轴的轴向设置的第一冷却通道，第二冷却通道，其设置在大致垂直于所述节段主体的方向的一个端部处 第一冷却通道，朝向相邻段体的端部吹送冷却空气;以及第三冷却通道，其将在上游侧部分大致垂直于旋转轴的轴向设置的第一空腔与第一空腔连接， 冷却空间，其被节段主体包围，具有多个小孔的碰撞板。 第一冷却通道包括具有比第一区域冷却通道更小的通道横截面面积的第一区域和第二区域的冷却通道或比第一区域冷却通道更大的排列间距。

    COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE
    10.
    发明申请
    COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE 有权
    环形和气体涡轮冷却系统

    公开(公告)号：US20110182724A1

    公开(公告)日：2011-07-28

    申请号：US12913397

    申请日：2010-10-27

    申请人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    发明人： Hidemichi Koyabu ,  Satoshi Hada ,  Junichiro Masada ,  Keizo Tsukagoshi

    IPC分类号： F01D5/08

    CPC分类号： F01D25/246 ,  F01D9/04 ,  F01D11/005 ,  F01D11/24 ,  F01D25/12 ,  F05D2240/11 ,  F05D2260/205

    摘要： A cooling system of a ring segment for a gas turbine, which includes first cooling passages disposed in an axial direction of the rotating shaft of a main body of the segment body, second cooling passages disposed at one end portion in a direction approximately perpendicular to the first cooling passages, and blowing a cooling air toward the end portion of a neighboring segment body, and third cooling passages connecting a first cavity, which is disposed approximately perpendicular to the axial direction of the rotating shaft at the upstream-end portion, with a cooling space, which is surrounded by the segment body and a collision plate having a plurality of small holes. The first cooling passages include cooling passages of a first region which are disposed adjacent to the end portion on a rear side in a rotation direction, and cooling passages of a second region which are disposed on a farther front side in the rotation direction than the first-region cooling passages and have a smaller passage cross-sectional area than the first-region cooling passages or a greater arrangement pitch than the first-region cooling passages. The first-region cooling passages are disposed adjacent to the second cooling passages of the neighboring segment body.

    摘要翻译： 一种用于燃气轮机的环段的冷却系统，其包括沿着所述节段主体的主体的轴的轴向设置的第一冷却通道，第二冷却通道，其设置在大致垂直于所述节段主体的方向的一个端部处 第一冷却通道，朝向相邻段体的端部吹送冷却空气;以及第三冷却通道，其将在上游侧部分大致垂直于旋转轴的轴向设置的第一空腔与 冷却空间，其被节段主体包围，具有多个小孔的碰撞板。 第一冷却通路包括第一区域的冷却通道，第一区域与沿着旋转方向的后侧的端部相邻设置，并且第二区域的冷却通道设置在比第一区域的旋转方向更远的前侧 并且具有比第一区域冷却通道更小的通道横截面面积或比第一区域冷却通道更大的排列间距。 第一区域冷却通道邻近相邻段体的第二冷却通道设置。