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1. 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。

2. 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。

3. 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。

4. 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。

5. 发明申请

US20110044805A1 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：US20110044805A1
公开(公告)日：2011-02-24
申请号：US12861339
申请日：2010-08-23
申请人： Hidemichi Koyabu , Satoshi Hada
发明人： Hidemichi Koyabu , Satoshi Hada
IPC分类号： F01D25/08
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F05D2240/81 , F05D2260/201
摘要： A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
摘要翻译：环段的冷却系统设有：具有多个小孔的碰撞板; 由所述碰撞板和所述节段主体的主体包围的冷却空间; 在燃烧气体的流动方向上，分段主体的上游端部与旋转轴的轴向垂直地配置的第一空腔; 第一冷却通道，其从所述冷却空间与所述第一空腔连通; 以及第二冷却通道，其在所述燃烧气体的流动方向上从所述第一空腔与所述段主体的下游端部中的燃烧气体d气体空间连通。

6. 发明授权

US08777559B2 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：US08777559B2
公开(公告)日：2014-07-15
申请号：US12861339
申请日：2010-08-23
申请人： Hidemichi Koyabu , Satoshi Hada
发明人： Hidemichi Koyabu , Satoshi Hada
IPC分类号： F01D25/08
CPC分类号： F01D25/12 , F01D11/08 , F01D11/24 , F05D2240/81 , F05D2260/201
摘要： A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
摘要翻译：环段的冷却系统设有：具有多个小孔的碰撞板; 由所述碰撞板和所述节段主体的主体包围的冷却空间; 在燃烧气体的流动方向上，分段主体的上游端部与旋转轴的轴向垂直地配置的第一空腔; 第一冷却通道，其从所述冷却空间与所述第一空腔连通; 以及第二冷却通道，其在所述燃烧气体的流动方向上从所述第一空腔与所述段主体的下游端部中的燃烧气体d气体空间连通。

7. 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.

8. 发明授权

US06887039B2 Stationary blade in gas turbine and gas turbine comprising the same 有权
标题翻译：包括燃气轮机和燃气轮机的固定叶片
公开(公告)号：US06887039B2
公开(公告)日：2005-05-03
申请号：US10191448
申请日：2002-07-10
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： F01D9/02 , F01D11/02 , F02C7/28 , F01D11/00
CPC分类号： F01D11/02 , F02C7/28
摘要： A stationary blade of a gas turbine, which can reduce thermal stress produced at a portion in the vicinity of a rear edge of an inner shroud of the stationary blade. The stationary blade is positioned adjacent to at least one of moving-blade disks in an axial direction of the gas turbine. A concave portion is provided in the inner shroud in a manner such that the concave portion is formed in the vicinity of a rear edge of the inner shroud and on an inner-peripheral face of the inner shroud, where cooling air passes along the inner-peripheral face which faces a rotation shaft of the moving-blade disks; and a protruding portion which protrudes towards the rotation shaft is formed at the rear edge of the inner shroud.
摘要翻译：燃气轮机的固定叶片，其可以降低在固定叶片的内护罩的后边缘附近的部分产生的热应力。固定叶片沿着燃气轮机的轴向方向定位成与活动叶片盘中的至少一个相邻。在内护罩中设置有凹部，使得凹部形成在内护罩的后缘附近和内护罩的内周面附近，在内罩的内周面上，面向移动刀片盘的旋转轴的周边面; 并且在内护罩的后边缘处形成有朝向旋转轴突出的突出部。

9. 发明申请

US20100223925A1 SOLAR THERMAL RECEIVER AND SOLAR THERMAL POWER GENERATION FACILITY 审中-公开
标题翻译：太阳能热水器和太阳能发电设备
公开(公告)号：US20100223925A1
公开(公告)日：2010-09-09
申请号：US12708158
申请日：2010-02-18
申请人： Junichiro Masada , Satoshi Hada , Takayoshi Iijima
发明人： Junichiro Masada , Satoshi Hada , Takayoshi Iijima
IPC分类号： F03G6/00 , F24J2/48
CPC分类号： F24S20/20 , F24S10/75 , F24S70/20 , F24S2010/751 , F24S2080/011 , F28F19/02 , Y02E10/41 , Y02E10/44 , Y02E10/46
摘要： A solar thermal receiver capable of improving the power generation efficiency in solar thermal power generation, reducing the production cost, and enhancing the thermal shock resistance and a solar thermal power generation facility using the solar thermal receiver are provided. The solar thermal receiver that receives solar radiation to heat fluid includes a heat-receiving section that is made of metal and that constitutes a flow path in which at least the fluid flows; and a coating layer that is disposed on at least a surface of an area of the heat-receiving section irradiated with the sunlight, that absorbs energy of the sunlight, and that has heat resistance.
摘要翻译：提供了能够提高太阳能发电的发电效率，降低生产成本，提高耐热冲击性的太阳能热接收器以及使用太阳能热接收器的太阳能发电设备。将太阳辐射接收到热流体的太阳能热接收器包括由金属制成并构成至少流体流动的流动路径的受热部分; 以及设置在受太阳光照射的受热部的区域的至少一个表面上的吸收太阳光的能量并具有耐热性的涂层。

10. 发明授权

US06742991B2 Turbine blade and gas turbine 有权
标题翻译：涡轮叶片和燃气轮机
公开(公告)号：US06742991B2
公开(公告)日：2004-06-01
申请号：US10192676
申请日：2002-07-11
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： F01D518
CPC分类号： F01D5/188 , F01D5/186 , F01D5/189 , F05D2250/70 , F05D2260/202
摘要： A turbine blade applicable to a gas turbine has a turbine blade body having film cooling holes, the interior space of which is partitioned into two cavities by a rib. Hollow inserts each having impingement holes are respectively arranged in the cavities to form cooling spaces therebetween. Communication is ensured between the cavities by bypass hole and slits, so that the impingement cooling is interrupted with respect to the prescribed side having a good heat transmission in the turbine blade body. A partition wall is further arranged between the rib and the insert arranged in the trailing-edge side, thus providing a separation between the cooling spaces respectively arranged in the rear side and front side. Thus, it is possible to noticeably reduce the amount of cooling air in the turbine blade body; and it is possible to reduce temperature differences entirely over the turbine blade body as small as possible.
摘要翻译：适用于燃气轮机的涡轮叶片具有涡轮叶片体，其具有膜冷却孔，其内部空间通过肋分隔成两个空腔。各个具有冲击孔的中空插入件分别设置在空腔中，以在它们之间形成冷却空间。通过旁通孔和狭缝确保空腔之间的通信，使得冲击冷却相对于在涡轮叶片体中具有良好的热传递的规定侧被中断。分隔壁还布置在布置在后缘侧的肋和插入件之间，从而在分别布置在后侧和前侧的冷却空间之间分开。因此，可以显着地减少涡轮叶片体内的冷却空气量; 并且可以尽可能小地将涡轮叶片体上的温差完全降低。

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