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1. 发明授权

US09551224B2 Turbine and method for manufacturing turbine 有权
标题翻译：涡轮机及其制造方法
公开(公告)号：US09551224B2
公开(公告)日：2017-01-24
申请号：US13818016
申请日：2011-10-28
申请人： Tomoyuki Onishi , Yuichiro Waki , Shoki Yamashita , Takaaki Matsuo , Asaharu Matsuo
发明人： Tomoyuki Onishi , Yuichiro Waki , Shoki Yamashita , Takaaki Matsuo , Asaharu Matsuo
IPC分类号： F04D29/54 , F01D5/12 , F01D9/04 , F01D11/00 , F01D5/30
CPC分类号： F01D5/12 , F01D5/3069 , F01D9/042 , F01D11/001 , F01D11/003
摘要： The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction.
摘要翻译：涡轮机包括：可旋转地支撑的轴体; 多个涡轮叶片构件; 覆盖所述轴体和所述涡轮叶片排的壳体; 外圈构件，其设置在所述壳体的内周上，并且具有内周部，所述内周部具有在周向上连续的具有不平坦形状的截面; 多个涡轮叶片构件，每个涡轮叶片构件具有装配到外圈构件的内周部分中的罩和从护罩延伸到径向内侧的涡轮叶片主体; 以及板构件，其连接所述多个涡轮叶片构件中的至少一些，并且在所述轴向方向上覆盖所述护罩的一侧，从而密封形成在所述周向上彼此相邻的所述护罩之间的护罩间隙。

2. 发明申请

US20130149125A1 TURBINE AND METHOD FOR MANUFACTURING TURBINE 有权
标题翻译：用于制造涡轮的涡轮机和方法
公开(公告)号：US20130149125A1
公开(公告)日：2013-06-13
申请号：US13818016
申请日：2011-10-28
申请人： Tomoyuki Onishi , Yuichiro Waki , Shoki Yamashita , Takaaki Matsuo , Asaharu Matsuo
发明人： Tomoyuki Onishi , Yuichiro Waki , Shoki Yamashita , Takaaki Matsuo , Asaharu Matsuo
IPC分类号： F01D5/12
CPC分类号： F01D5/12 , F01D5/3069 , F01D9/042 , F01D11/001 , F01D11/003
摘要： The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction.
摘要翻译：涡轮机包括：可旋转地支撑的轴体; 多个涡轮叶片构件; 覆盖所述轴体和所述涡轮叶片排的壳体; 外圈构件，其设置在所述壳体的内周上，并且具有内周部，所述内周部具有在周向上连续的具有不平坦形状的截面; 多个涡轮叶片构件，每个涡轮叶片构件具有装配到外圈构件的内周部分中的罩和从护罩延伸到径向内侧的涡轮叶片主体; 以及板构件，其连接所述多个涡轮叶片构件中的至少一些，并且在所述轴向方向上覆盖所述护罩的一侧，从而密封形成在所述周向上彼此相邻的所述护罩之间的护罩间隙。

3. 发明授权

US09353640B2 Turbine 有权
标题翻译：涡轮
公开(公告)号：US09353640B2
公开(公告)日：2016-05-31
申请号：US13995542
申请日：2011-12-22
申请人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D11/08 , F01D11/04 , F01D11/10 , F01D5/22
CPC分类号： F01D11/04 , F01D5/225 , F01D11/10 , F05D2250/294
摘要： A turbine includes a blade, a structure installed at a tip section side of the blade via a gap and configured to relatively rotate with respect to the blade, a step section formed at the tip section of the blade, having at least one step surface, and protruding toward a portion opposite to the tip section of the structure, a seal fin formed at the portion opposite to the tip section of the structure, extending toward the step section, and configured to form a micro gap between the step section and the seal fin, and a cutout section formed at the step surface to be connected to an upper surface of the step section. The cutout section guides a separation vortex separated from a main stream of a fluid passing through the gap toward the seal fin on the upper surface of the step section.
摘要翻译：涡轮机包括叶片，通过间隙安装在叶片的尖端部侧的结构，其构造成相对于叶片相对旋转;台阶部，形成在叶片的尖端部分，具有至少一个台阶表面，并且向与所述结构的前端部相反的部分突出，形成在与所述结构的前端部相反的部分处的所述密封翅片朝向所述台阶部延伸，并且构造成在所述台阶部与所述密封件之间形成微缝隙翅片和形成在台阶表面处以与台阶部分的上表面连接的切口部分。切口部分引导从步进部分的上表面上的通过间隙的流体的主流与密封翅片分离的分离涡流。

4. 发明授权

US09593587B2 Turbine seal fin leakage flow rate control 有权
标题翻译：涡轮密封翅片泄漏流量控制
公开(公告)号：US09593587B2
公开(公告)日：2017-03-14
申请号：US13580078
申请日：2011-01-27
申请人： Kazuyuki Matsumoto , Yoshihiro Kuwamura , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Kazuyuki Matsumoto , Yoshihiro Kuwamura , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D11/00 , F01D11/08 , F16J15/447 , F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F01D11/08 , F05D2220/31 , F05D2240/127 , F05D2240/55 , F16J15/447
摘要： Provided is a turbine in which seal fins (15) are provided to a hub shroud (41) to protrude toward a bottom surface (33a) of an annular groove (33), small gaps (H) are formed between the tip ends of the seal fins and the bottom surface of the annular groove, and assuming that the axial distance between a first seal fin (15a) disposed on the front edge side of the hub shroud among the seal fins and a front edge (41a) of the hub shroud is (L) and the axial distance between the front edge of the hub shroud and an inside surface (33b) of the annular groove is (Bu), the first seal fin is disposed to satisfy L/Bu
摘要翻译：本发明提供一种涡轮机，其中，密封翅片（15）设置在轮毂护罩（41）上，朝向环状槽（33）的底面（33a）突出，在密封翅片和环形槽的底面，并且假设设置在密封翅片之间的轮毂罩的前边缘侧的第一密封翅片（15a）与轮毂罩的前边缘（41a）之间的轴向距离是（L），轮毂罩的前缘与环状槽的内侧面（33b）之间的轴向距离为（Bu），第一密封翅片设置为满足L / Bu <0.3。

5. 发明申请

US20130094945A1 SEAL STRUCTURE, TURBINE MACHINE HAVING THE SAME, AND POWER GENERATING PLANT EQUIPPED WITH THE SAME 审中-公开
标题翻译：密封结构，具有该密封结构的涡轮机，以及配备其的发电厂
公开(公告)号：US20130094945A1
公开(公告)日：2013-04-18
申请号：US13637207
申请日：2011-05-23
申请人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D5/143 , F01D5/225 , F01D11/005 , F01D11/02
摘要： A seal structure includes shrouds that are provided at tips of a plurality of blades on which a main flow of fluid impinges and that come into contact with adjacent shrouds to form a cylindrical shape; a sealing part connected to a structure body facing the shrouds; and a space that is defined by downstream sides of the shrouds, a downstream side of the sealing part, and a wall on a downstream side of the structure body, and that communicates with the main flow of fluid that has impinged on the blades. An end of the wall on the downstream side of the structure body is formed so as to be disposed a predetermined distance away from a shroud extension and away from a sealing-part extension and so as to be located on the opposite side of the shroud extension with respect to the sealing-part extension.
摘要翻译：密封结构包括设置在多个叶片的尖端处的护罩，主流体流入其上并与相邻护罩接触以形成圆柱形; 连接到面向所述护罩的结构体的密封部分; 以及由所述护罩的下游侧，所述密封部的下游侧以及所述结构体的下游侧的壁形成的与所述叶片的冲击主流相连通的空间。该结构体的下游侧的壁的一端形成为远离护罩延伸部远离密封部分延伸部预定距离并且位于护罩延伸部的相对侧上相对于密封部分延伸。

6. 发明申请

US20120321449A1 TURBINE 有权
标题翻译：涡轮
公开(公告)号：US20120321449A1
公开(公告)日：2012-12-20
申请号：US13580078
申请日：2011-01-27
申请人： Kazuyuki Matsumoto , Yoshihiro Kuwamura , Hiroharu yama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Kazuyuki Matsumoto , Yoshihiro Kuwamura , Hiroharu yama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D11/08
CPC分类号： F01D11/001 , F01D11/02 , F01D11/08 , F05D2220/31 , F05D2240/127 , F05D2240/55 , F16J15/447
摘要： Provided is a turbine in which seal fins (15) are provided to a hub shroud (41) to protrude toward a bottom surface (33a) of an annular groove (33), small gaps (H) are formed between the tip ends of the seal fins and the bottom surface of the annular groove, and assuming that the axial distance between a first seal fin (15a) disposed on the front edge side of the hub shroud among the seal fins and a front edge (41a) of the hub shroud is (L) and the axial distance between the front edge of the hub shroud and an inside surface (33b) of the annular groove is (Bu), the first seal fin is disposed to satisfy L/Bu
摘要翻译：本发明提供一种涡轮机，其中，密封翅片（15）设置在轮毂护罩（41）上，朝向环状槽（33）的底面（33a）突出，在密封翅片和环形槽的底面，并且假设设置在密封翅片之间的轮毂罩的前边缘侧的第一密封翅片（15a）与轮毂罩的前边缘（41a）之间的轴向距离是（L），轮毂罩的前缘与环状槽的内侧面（33b）之间的轴向距离为（Bu），第一密封翅片设置为满足L / Bu <0.3。

7. 发明授权

US09388701B2 Turbine 有权
标题翻译：涡轮
公开(公告)号：US09388701B2
公开(公告)日：2016-07-12
申请号：US13519403
申请日：2011-01-31
申请人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D5/22 , F01D11/02 , F01D11/08 , F16J15/447
CPC分类号： F01D5/225 , F01D11/02 , F01D11/08 , F05D2240/55 , F16J15/4472
摘要： A turbine (1) of the present invention comprises that at one part of a tip part (51) of the blade (50) and an area (11a) of the structure (11) corresponding to the tip part (51) of the blade, a stepped part (52) is formed, a seal fin (15) is provided at the another part of the tip part (51) of the blade and the area (11 a) of the structure (11), a cavity (C) is formed between the tip part (51) of the blade and the area (11a) of the structure (11) and between the seal fin (15) and a partition wall (54, 15). The seal fin (15) comprises a fin main body part (16), and a space restriction part (17). Thus, the present invention provides a high performance turbine in which the leakage flow rate is reduced.
摘要翻译：本发明的涡轮机（1）包括在叶片（50）的尖端部分（51）的一部分和与叶片（50）的尖端部分（51）相对应的结构（11）的区域（11a）形成有阶梯部（52），在叶片的前端部（51）的另一部分和结构（11）的区域（11a）上设置有密封翅片（15），空腔）形成在叶片的末端部分（51）和结构（11）的区域（11a）之间并且在密封翅片（15）和分隔壁（54,15）之间。密封翅片（15）包括翅片主体部分（16）和空间限制部分（17）。因此，本发明提供了一种泄漏流量降低的高性能涡轮机。

8. 发明申请

US20120288360A1 TURBINE 有权
标题翻译：涡轮
公开(公告)号：US20120288360A1
公开(公告)日：2012-11-15
申请号：US13519403
申请日：2011-01-31
申请人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
发明人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Asaharu Matsuo
IPC分类号： F01D11/08
CPC分类号： F01D5/225 , F01D11/02 , F01D11/08 , F05D2240/55 , F16J15/4472
摘要： A turbine (1) of the present invention comprises that at one part of a tip part (51) of the blade (50) and an area (11a) of the structure (11) corresponding to the tip part (51) of the blade, a stepped part (52) is formed, a seal fin (15) is provided at the another part of the tip part (51) of the blade and the area (11a) of the structure (11), a cavity (C) is formed between the tip part (51) of the blade and the area (11a) of the structure (11) and between the seal fin (15) and a partition wall (54, 15). The seal fin (15) comprises a fin main body part (16), and a space restriction part (17). Thus, the present invention provides a high performance turbine in which the leakage flow rate is reduced.
摘要翻译：本发明的涡轮机（1）包括在叶片（50）的尖端部分（51）的一部分和与叶片（50）的尖端部分（51）相对应的结构（11）的区域（11a）形成台阶部（52），在叶片的前端部（51）的另一部分和结构（11）的区域（11a）上设置有密封翅片（15），空腔（C）形成在叶片的末端部分（51）和结构（11）的区域（11a）之间以及密封翅片（15）和分隔壁（54,15）之间。密封翅片（15）包括翅片主体部分（16）和空间限制部分（17）。因此，本发明提供了一种泄漏流量降低的高性能涡轮机。

9. 发明授权

US5984637A Cooling medium path structure for gas turbine blade 失效
标题翻译：燃气轮机叶片的冷却介质路径结构
公开(公告)号：US5984637A
公开(公告)日：1999-11-16
申请号：US27201
申请日：1998-02-20
申请人： Asaharu Matsuo
发明人： Asaharu Matsuo
IPC分类号： F01D5/08 , F01D5/30 , F01D11/00 , F02C7/18
CPC分类号： F01D5/087 , F01D11/006 , F01D5/081 , F05D2260/205
摘要： A cooling medium path structure for cooling a gas turbine blade. The structure includes a disk-side cooling medium path, a blade-side cooling medium path formed at the root portion of the blade and a delivery block disposed between the two cooling medium paths so as to establish communication therebetween. The delivery block is provided with an elastic engaging section which comes into elastic and line-contact with the disk-side cooling medium path and the blade-side cooling medium path. Thus, the sealing property of the contact portions of the structure is secured so as to allow a cooling medium to be supplied without leaking from the cooling medium paths. The heat of the cooling medium, generated as a result of cooling the high-temperature portion of the gas turbine, can be recovered so as to make the best use of the heated medium.
摘要翻译：一种用于冷却燃气轮机叶片的冷却介质路径结构。该结构包括盘侧冷却介质路径，形成在叶片根部的叶片侧冷却介质路径和设置在两个冷却介质路径之间的输送块，以在它们之间建立连通。输送块设置有与盘侧冷却介质路径和叶片侧冷却介质路径弹性和线接触的弹性接合部。因此，确保了结构的接触部分的密封性能，以允许供应冷却介质而不会从冷却介质路径泄漏。可以回收由于冷却燃气轮机的高温部分而产生的冷却介质的热量，以充分利用被加热的介质。

10. 发明授权

US09726027B2 Turbine 有权
公开(公告)号：US09726027B2
公开(公告)日：2017-08-08
申请号：US13817893
申请日：2011-09-08
申请人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Masaaki Matsuura , Asaharu Matsuo
发明人： Yoshihiro Kuwamura , Kazuyuki Matsumoto , Hiroharu Oyama , Yoshinori Tanaka , Masaaki Matsuura , Asaharu Matsuo
IPC分类号： F01D5/20 , F01D9/00 , F01D11/08 , F01D5/22
CPC分类号： F01D9/00 , F01D5/225 , F01D11/001 , F01D11/02 , F01D11/08 , F05D2220/31 , F16J15/4472
摘要： A turbine includes: a blade body having a blade provided at one of a rotor rotatably supported and a stator provided around the rotor and extending in a radial direction and a shroud extending in a circumferential direction at a tip portion in the radial direction of the blade; and an accommodating concave body provided at another one of the rotor and the stator, extending in the circumferential direction, accommodating the shroud with a gap interposed therebetween, and relatively rotating with respect to the blade body, wherein a leakage flow leaked from a main flow flowing along the blade flows into the gap; and wherein the shroud is provided with a guide curved surface formed between a peripheral surface facing the accommodating concave body and a trailing edge end portion formed closer to a main flow side in a downstream side of the leakage flow than the peripheral surface.

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