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1. 发明申请

US20110142597A1 TURBINE BLADE STRUCTURE 有权
标题翻译：涡轮叶片结构
公开(公告)号：US20110142597A1
公开(公告)日：2011-06-16
申请号：US12596224
申请日：2009-04-23
申请人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
发明人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
IPC分类号： F01D9/02
CPC分类号： F01D5/16 , F01D5/188 , F05D2260/94 , F05D2260/941
摘要： Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.
摘要翻译：提供一种涡轮叶片结构，其能够抑制在涡轮叶片的制造期间铸造产品的质量变化。一种涡轮叶片结构，其中，空气箔内的空间被分成多个空腔，所述多个空腔由基本上垂直于连接前缘和后缘的中心线设置的肋构件分隔开，分隔构件分隔位于叶片的中心部分的除了叶片前缘侧和叶片后缘侧之外的空腔基本上沿着中心线分成叶片压力侧空腔和叶片吸入侧空腔，其中叶片前缘端部和叶片分隔构件的后缘端部沿着形成在肋构件上的接合槽从一个护罩表面侧插入另一个护罩表面侧。

2. 发明申请

US20100150734A1 TURBINE BLADE 有权
标题翻译：涡轮叶片
公开(公告)号：US20100150734A1
公开(公告)日：2010-06-17
申请号：US12633842
申请日：2009-12-09
申请人： Satoshi Hada , Tomoko Hashimoto , Masanori Yuri , Keizo Tsukagoshi
发明人： Satoshi Hada , Tomoko Hashimoto , Masanori Yuri , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189 , F05D2240/126 , F05D2240/306 , F05D2260/201 , F05D2260/202
摘要： In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.
摘要翻译：在涡轮机叶片中，其中沿着连接前缘和后缘的中心线将叶片分隔成压力侧和吸力侧的片状肋在叶片的大致中央部分中设置，并且其中至少两个空腔设置吸入侧的空腔和压力侧的空腔不相通，用于冷却在吸入侧流入和流出空气的空气的压力调节构件减少流入吸入侧的冷却空气量，相对于压力侧。

3. 发明授权

US08366391B2 Turbine blade structure 有权
标题翻译：涡轮叶片结构
公开(公告)号：US08366391B2
公开(公告)日：2013-02-05
申请号：US12596224
申请日：2009-04-23
申请人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
发明人： Keizo Tsukagoshi , Tomoko Hashimoto , Satoshi Hada
IPC分类号： F01D5/12
CPC分类号： F01D5/16 , F01D5/188 , F05D2260/94 , F05D2260/941
摘要： Provided is a turbine blade structure that is capable of suppressing quality variations of cast products during the manufacturing of turbine blades. A turbine blade structure wherein the space inside an air foil is divided into a plurality of cavities, partitioned by rib members provided substantially perpendicular to the center line connecting a leading edge and a trailing edge, is provided with partition members that partition the inside of the cavities located in the central portion of the blade, excluding the blade leading-edge side and the blade trailing-edge side, into blade pressure side cavities and blade suction side cavities substantially along the center line, wherein blade leading-edge end portions and blade trailing-edge end portions of the partition members are inserted from one shroud surface side to the other shroud surface side along engagement grooves formed on the rib members.
摘要翻译：提供一种涡轮叶片结构，其能够抑制在涡轮叶片的制造期间铸造产品的质量变化。一种涡轮叶片结构，其中，空气箔内的空间被分成多个空腔，所述多个空腔由基本上垂直于连接前缘和后缘的中心线设置的肋构件分隔开，分隔构件分隔位于叶片的中心部分的除了叶片前缘侧和叶片后缘侧之外的空腔基本上沿着中心线分成叶片压力侧空腔和叶片吸入侧空腔，其中叶片前缘端部和叶片分隔构件的后缘端部沿着形成在肋构件上的接合槽从一个护罩表面侧插入另一个护罩表面侧。

4. 发明授权

US08079815B2 Turbine blade 有权
标题翻译：涡轮叶片
公开(公告)号：US08079815B2
公开(公告)日：2011-12-20
申请号：US12633842
申请日：2009-12-09
申请人： Satoshi Hada , Tomoko Hashimoto , Masanori Yuri , Keizo Tsukagoshi
发明人： Satoshi Hada , Tomoko Hashimoto , Masanori Yuri , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189 , F05D2240/126 , F05D2240/306 , F05D2260/201 , F05D2260/202
摘要： In a turbine blade in which a tabular rib partitioning the blade into a pressure side and a suction side is provided in substantially the midsection of the blade along a center line connecting a leading edge and a trailing edge, and at least two cavities of which a cavity at the suction side and a cavity at the pressure side do not communicate with each other are provided, a pressure adjustment member for cooling air flowing into and out of the cavity at the suction side reduces the amount of cooling air flowing into the suction side, relative to the pressure side.
摘要翻译：在涡轮机叶片中，其中沿着连接前缘和后缘的中心线将叶片分隔成压力侧和吸力侧的片状肋在叶片的大致中央部分中设置，并且其中至少两个空腔设置吸入侧的空腔和压力侧的空腔不相通，用于冷却在吸入侧流入和流出空气的空气的压力调节构件减少流入吸入侧的冷却空气量，相对于压力侧。

5. 发明申请

US20110123351A1 TURBINE VANE AND GAS TURBINE 有权
标题翻译：涡轮风扇和气体涡轮
公开(公告)号：US20110123351A1
公开(公告)日：2011-05-26
申请号：US12644633
申请日：2009-12-22
申请人： Satoshi Hada , Keizo Tsukagoshi
发明人： Satoshi Hada , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2240/12 , F05D2260/201 , F05D2260/202 , F05D2260/30
摘要： An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.
摘要翻译：机翼部包括多个冷却室，所述多个冷却室是通过沿着叶片纵向方向延伸的分隔壁将翼型部的内部从前缘侧到后缘侧隔开的空间，并且包括在身体的内壁上的分隔部分; 插入设置在冷却室中并具有多个冲击孔的圆柱体; 以及设置在身体中的胶片孔。插入圆筒包括从前缘侧延伸到后缘侧并且沿叶片纵向方向延伸的分隔部。插入圆筒的内部被分隔成靠近压力表面的压力表面侧插入空间和靠近抽吸表面的吸入表面侧插入空间。

6. 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。

7. 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。

8. 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。

9. 发明授权

US08662844B2 Turbine vane and gas turbine 有权
标题翻译：涡轮叶片和燃气轮机
公开(公告)号：US08662844B2
公开(公告)日：2014-03-04
申请号：US12644633
申请日：2009-12-22
申请人： Satoshi Hada , Keizo Tsukagoshi
发明人： Satoshi Hada , Keizo Tsukagoshi
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2240/12 , F05D2260/201 , F05D2260/202 , F05D2260/30
摘要： An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.
摘要翻译：机翼部包括多个冷却室，所述多个冷却室是通过沿着叶片纵向方向延伸的分隔壁将翼型部的内部从前缘侧到后缘侧隔开的空间，并且包括在身体的内壁上的分隔部分; 插入设置在冷却室中并具有多个冲击孔的圆柱体; 以及设置在身体中的胶片孔。插入圆筒包括从前缘侧延伸到后缘侧并且沿叶片纵向方向延伸的分隔部。插入圆筒的内部被分隔成靠近压力表面的压力表面侧插入空间和靠近抽吸表面的吸入表面侧插入空间。

10. 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。

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