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1. 发明申请

US20120014832A1 Ni-BASED SINGLE CRYSTAL SUPERALLOY 有权
标题翻译：镍基单晶超级合金
公开(公告)号：US20120014832A1
公开(公告)日：2012-01-19
申请号：US13144748
申请日：2010-01-15
申请人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Tøiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
发明人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Tøiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
IPC分类号： C22C19/05
CPC分类号： F01D5/28 , C22C19/057 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52 , F05D2300/607 , Y02T50/671
摘要： The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.
摘要翻译：这里公开的Ni系单晶合金为单晶，其化学组成为：Co：8〜12％，Cr：5〜7.5％，Mo：0.2〜1.2％，W：5〜 7％，Al：5〜6.5％，Ta：8〜12％。 Hf：0.01〜0.2％，Re：2〜4％，Si：0.005〜0.1％，余量由Ni和不可避免的杂质构成。

2. 发明授权

US08900512B2 Ni-based single crystal superalloy 有权
标题翻译：镍基单晶超合金
公开(公告)号：US08900512B2
公开(公告)日：2014-12-02
申请号：US13144748
申请日：2010-01-15
申请人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
发明人： Hiroshi Harada , Tadaharu Yokokawa , Yutaka Koizumi , Toshiharu Kobayashi , Masao Sakamoto , Kyoko Kawagishi , Ikuo Okada , Hidataka Oguma , Taiji Torigoe , Masaki Taneike , Eisaku Ito , Junichiro Masada , Keizo Tsukagoshi , Hidemichi Koyabu
IPC分类号： C22C19/05 , F01D5/28 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52
CPC分类号： F01D5/28 , C22C19/057 , C22F1/00 , C22F1/02 , C22F1/10 , C30B11/00 , C30B29/52 , F05D2300/607 , Y02T50/671
摘要： The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.
摘要翻译：这里公开的Ni系单晶合金为单晶，其化学组成为：Co：8〜12％，Cr：5〜7.5％，Mo：0.2〜1.2％，W：5〜 7％，Al：5〜6.5％，Ta：8〜12％。 Hf：0.01〜0.2％，Re：2〜4％，Si：0.005〜0.1％，余量由Ni和不可避免的杂质构成。

3. 发明授权

US08550778B2 Cooling system of ring segment and gas turbine 有权
标题翻译：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。

4. 发明授权

US08480353B2 Cooling system of ring segment and gas turbine 有权
标题翻译：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。

5. 发明申请

US20110182724A1 COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE 有权
标题翻译：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。

6. 发明申请

US20110255989A1 Cooling system of ring segment and gas turbine 有权
标题翻译：环段和燃气轮机的冷却系统
公开(公告)号：US20110255989A1
公开(公告)日：2011-10-20
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。

7. 发明申请

US20110138818A1 GAS TURBINE AND OPERATING METHOD THEREOF 有权
标题翻译：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。

8. 发明申请

US20130098063A1 COOLNG STRUCTURE FOR RECOVERY-TYPE AIR-COOLED GAS TURBINE COMBUSTOR 有权
标题翻译：回收式空气冷却气涡轮机的冷却结构
公开(公告)号：US20130098063A1
公开(公告)日：2013-04-25
申请号：US13806523
申请日：2011-08-10
申请人： Satoshi Mizukami , Tatsuo Ishiguro , Junichiro Masada , Kazumasa Takata , Shunsuke Torii , Yuya Fukunaga , Tetsu Konishi , Yoshiaki Nishimura , Yoshiaki Igarashi , Shinya Ishikawa
发明人： Satoshi Mizukami , Tatsuo Ishiguro , Junichiro Masada , Kazumasa Takata , Shunsuke Torii , Yuya Fukunaga , Tetsu Konishi , Yoshiaki Nishimura , Yoshiaki Igarashi , Shinya Ishikawa
IPC分类号： F02C7/18 , F23R3/06 , F02C7/08
CPC分类号： F02C7/18 , F01D9/023 , F02C7/08 , F02C7/24 , F05D2260/202 , F23R3/005 , F23R3/06 , F23R3/44 , F23R2900/00014
摘要： In a cooling structure for a recovery-type air-cooled gas turbine combustor having a recovery-type air-cooling structure that bleeds, upstream of the combustor, and pressurizes compressed air supplied from a compressor, that uses the bled and pressurized air to cool a wall, and that recovers and reuses the bled and pressurized air as combustion air for burning fuel in the combustor together with a main flow of the compressed air, wall cooling in which cooling air is supplied to cooling air passages formed in the wall of the combustor to perform cooling involves a downstream wall region, closer to a turbine, that is cooled using the bled and pressurized air as the cooling air and an upstream wall region, closer to a burner, that is cooled using, as the cooling air, bled compressed air bled from a main flow of the compressed air through a housing inner space.
摘要翻译：在用于具有回收式空气冷却结构的回收式空气冷却燃气轮机燃烧器的冷却结构中，所述回收型空气冷却结构在燃烧器的上游出来并对从压缩机供给的压缩空气进行加压，所述回收式空气冷却结构使用过滤和加压空气来冷却一个墙壁，并且回收和再利用排放和加压的空气作为用于燃烧燃烧器中的燃料的燃烧空气以及压缩空气的主流，壁冷却，其中冷却空气被供应到冷却空气通道用于进行冷却的燃烧器包括更靠近涡轮机的下游壁区域，其使用作为冷却空气的排放和加压空气以及更靠近燃烧器的上游壁区域冷却，所述上游壁区域作为冷却空气被流出压缩空气从压缩空气的主流流过壳体内部空间。

9. 发明申请

US20070271930A1 Gas turbine having cooling-air transfer system 审中-公开
标题翻译：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。

10. 发明授权

US06761529B2 Cooling structure of stationary blade, and gas turbine 有权
公开(公告)号：US06761529B2
公开(公告)日：2004-07-13
申请号：US10202654
申请日：2002-07-25
申请人： Friedrich Soechting , Satoshi Hada , Masamitsu Kuwabara , Junichiro Masada , Yasuoki Tomita
发明人： Friedrich Soechting , Satoshi Hada , Masamitsu Kuwabara , Junichiro Masada , Yasuoki Tomita
IPC分类号： F01D906
CPC分类号： F01D5/187 , F01D9/041 , F05D2240/81 , F05D2260/201
摘要： A collision plate having plural small holes is provided at an interval from a bottom surface of an inner shroud to form a chamber and guides cooling air from the small holes into the chamber. A leading edge flow path is provided at a leading edge side along a width direction and introduces the cooling air. A side flow path is provided along both sides of the inner shroud and guides the cooling air to a trailing edge side. A header is formed along the width direction near the trailing edge and guides the cooling air from the side flow path. Plural trailing edge flow paths are formed at the trailing edge side at intervals along a width direction, in which one end of each flow path is connected to the header and the other end is open at the trailing edge, and the cooling air in the header is ejected from the trailing edge.

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