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1. 发明申请

US20100047065A1 BLADE STRUCTURE OF GAS TURBINE 有权
标题翻译：气体涡轮叶片结构
公开(公告)号：US20100047065A1
公开(公告)日：2010-02-25
申请号：US12518445
申请日：2007-05-10
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
IPC分类号： F01D9/04 , F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/20 , F01D9/041 , F05D2240/121 , F05D2240/303
摘要： To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section 28 of a stationary blade 21 is bent in the rotational direction of a rotor. Thus, even if combustion gas leaks from a tip clearance between an end wall of a casing and a tip portion of a rotor blade, and a stagnation line 35 near a tip portion 22 is situated in the side of a back surface 24, because a section located radially outward of the border section 28 is bent in the rotational direction of the rotor, the stagnation line 35 is also situated toward the rotational direction of the rotor. Therefore, the stagnation lines 35 formed at various heights in the heightwise direction of the stationary blade 21 are generally aligned in the rotational direction of the rotor. Thus, fluctuation of pressure distribution in the heightwise direction of the stationary blade 21, of the combustion gas flowing into the stationary blade 21 can be reduced. As a result, secondary flow loss can be reduced and turbine efficiency can be improved.
摘要翻译：为了减少二次流动损失和提高涡轮机效率，位于固定叶片21的边界部分28的径向外侧的部分沿转子的旋转方向弯曲。因此，即使燃烧气体从壳体的端壁和转子叶片的前端部之间的顶端间隙泄漏，并且在顶端部22附近的停滞线35位于后表面24的侧面，因为位于边界部分28的径向外侧的部分沿转子的旋转方向弯曲，停滞线35也朝向转子的旋转方向。因此，在静止叶片21的高度方向上形成在各高度处的停滞线35大致在转子的旋转方向上对齐。因此，可以减少流入固定叶片21的燃烧气体的静止叶片21的高度方向的压力分布的波动。结果，能够降低二次流动损失，提高涡轮效率。

2. 发明授权

US09732674B2 Flow path structure and gas turbine exhaust diffuser 有权
公开(公告)号：US09732674B2
公开(公告)日：2017-08-15
申请号：US13991796
申请日：2010-12-24
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
IPC分类号： F02C7/00 , F01D25/30 , F01D5/14 , F01D25/16
CPC分类号： F02C7/00 , F01D5/143 , F01D25/162 , F01D25/30 , F05D2250/712
摘要： A flow path structure includes a wall surface in which a flow path is formed, a structure configured to extend in a direction intersecting a main stream direction of a fluid flowing through the flow path from the wall surface, and a concave section forming region formed throughout a range including the structure in the main stream direction and having a concave section formed in the wall surface. As the structure occupies a partial range of the flow path in the flow path cross section intersecting the main stream, a cross-sectional area of the flow path is varied in accordance with positional variation in the main stream direction.

3. 发明申请

US20050172607A1 Exhaust diffuser for axial-flow turbine 审中-公开
标题翻译：轴流式涡轮排气扩散器
公开(公告)号：US20050172607A1
公开(公告)日：2005-08-11
申请号：US11052199
申请日：2005-02-08
申请人： Koichi Ishizaka , Masanori Yuri , Susumu Wakazono , Ronald Takahashi
发明人： Koichi Ishizaka , Masanori Yuri , Susumu Wakazono , Ronald Takahashi
IPC分类号： F01D5/14 , F01D25/30 , F02K1/00
CPC分类号： F01D5/142 , F01D25/30
摘要： An axial-flow turbine has an exhaust diffuser including a hub-side tube and a tip-side tube. In the exhaust diffuser, front struts and rear struts are placed to cross a flow of working fluid. A wake generated behind the front strut diverts from the rear strut and passes through a gap between a pair of the rear struts. Otherwise, a wake generated behind the front strut hits against the front face of the rear strut. The front struts are equal to or multiple of the rear struts in number.
摘要翻译：轴流涡轮机具有包括轮毂侧管和前端侧管的排气扩散器。在排气扩散器中，前支柱和后支柱被放置成穿过工作流体流。在前支柱后面产生的尾流从后支柱转移并穿过一对后支柱之间的间隙。否则，前支柱后面产生的尾迹撞击后支柱的前表面。前支柱等于或多个后支柱的数量。

4. 发明申请

US20140053572A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20140053572A1
公开(公告)日：2014-02-27
申请号：US13977172
申请日：2012-01-31
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono , Koichi Ishizaka , Yukinori Machida
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono , Koichi Ishizaka , Yukinori Machida
IPC分类号： F02C9/18
CPC分类号： F02C9/18 , F01D25/305 , F02C6/08 , F02C7/06 , F02C7/20 , F02C7/268 , F02C9/52 , F05D2220/32 , F05D2250/12 , F05D2260/606 , F05D2270/101
摘要： A gas turbine provided with an air bleeder tube (1) that, during startup, bleeds a portion of the compressed air of a compressor from the compressor and discharged the bled air into a cylindrical exhaust duct (20), wherein the air bleeder tube (1) is disposed at a portion that does not obstruct the flow of the main flow of combustion gas.
摘要翻译：一种设置有排气管（1）的燃气轮机，其在启动期间将来自压缩机的压缩机的一部分压缩空气排出，并将排出的空气排出到圆柱形排气管道（20）中，其中排气管 1）设置在不妨碍主燃烧气体流动的部分。

5. 发明申请

US20130259670A1 FLOW PATH STRUCTURE AND GAS TURBINE EXHAUST DIFFUSER 有权
标题翻译：流路结构和气体涡轮排气歧管
公开(公告)号：US20130259670A1
公开(公告)日：2013-10-03
申请号：US13991796
申请日：2010-12-24
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
IPC分类号： F02C7/00
CPC分类号： F02C7/00 , F01D5/143 , F01D25/162 , F01D25/30 , F05D2250/712
摘要： A flow path structure includes a wall surface in which a flow path is formed, a structure configured to extend in a direction intersecting a main stream direction of a fluid flowing through the flow path from the wall surface, and a concave section forming region formed throughout a range including the structure in the main stream direction and having a concave section formed in the wall surface. As the structure occupies a partial range of the flow path in the flow path cross section intersecting the main stream, a cross-sectional area of the flow path is varied in accordance with positional variation in the main stream direction.
摘要翻译：流路结构包括其中形成有流路的壁面，构造成沿着与从壁面流过流路的流体的主流方向相交的方向延伸的结构，以及整体形成的凹部形成区域包括在主流方向上的结构并且在壁表面中形成有凹部的范围。由于结构占据与主流相交的流路横截面中的流路的局部范围，所以流路的横截面积根据主流方向的位置变化而变化。

6. 发明申请

US20070025847A1 Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：US20070025847A1
公开(公告)日：2007-02-01
申请号：US11196388
申请日：2005-08-04
申请人： Susumu Wakazono , Kouichi Ishizaka , Masanori Yuri , Ronald Takahashi
发明人： Susumu Wakazono , Kouichi Ishizaka , Masanori Yuri , Ronald Takahashi
IPC分类号： F03B11/02
CPC分类号： F01D25/162
摘要： An outer shape of a section in the longitudinal direction at a leading edge of the strut is an aerofoil whose thickness is gradually increased along a flow direction of the combustion gas to prevent reduction of turbine efficiency caused by a shock wave generated at the strut of the exhaust diffuser.
摘要翻译：在支柱的前缘处的纵向截面的外形是其沿着燃烧气体的流动方向的厚度逐渐增加的机翼，以防止由于在支柱的支柱处产生的冲击波而引起的涡轮效率降低排气扩散器。

7. 发明申请

US20130224034A1 BLADE BODY AND ROTARY MACHINE 审中-公开
标题翻译：叶片机和旋转机
公开(公告)号：US20130224034A1
公开(公告)日：2013-08-29
申请号：US13881582
申请日：2010-12-27
申请人： Yasuro Sakamoto , Eisaku Ito , Hitoshi Kitagawa , Susumu Wakazono
发明人： Yasuro Sakamoto , Eisaku Ito , Hitoshi Kitagawa , Susumu Wakazono
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2240/304 , Y02T50/673
摘要： The blade body of the present invention is provided with a main body which has a dorsal face and a ventral face and also provided with a trailing edge portion which connects the dorsal face to the ventral face with a continuous curved face. The curved face of the trailing edge portion is gradually decreased in curvature radius from one of the dorsal face and the ventral face toward the rear end portion which is positioned most downstream in a direction at which a fluid flows, decreased to the greatest extent in curvature radius at the rear end portion, thereafter, gradually increased in curvature radius from the rear end portion toward the other of the dorsal face and the ventral face and arrives at the other of the dorsal face and the ventral face.
摘要翻译：本发明的刀体设置有具有背面和腹面的主体，并且还具有将背面与腹面连续地连接的后缘部的后缘部。后边缘部分的曲面从曲面半径逐渐减小，从背面和腹面之一到后端部，其位于流体流动方向最下游的最下方，曲率最大程度地减小后端部的半径，此后，从后端部朝向背面和腹面的另一侧逐渐增加曲率半径，并到达背面和腹面的另一侧。

8. 发明授权

US08317466B2 Blade structure of gas turbine 有权
标题翻译：燃气轮机叶片结构
公开(公告)号：US08317466B2
公开(公告)日：2012-11-27
申请号：US12518445
申请日：2007-05-10
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono
IPC分类号： F01D5/12
CPC分类号： F01D5/145 , F01D5/143 , F01D5/20 , F01D9/041 , F05D2240/121 , F05D2240/303
摘要： To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section 28 of a stationary blade 21 is bent in the rotational direction of a rotor. Thus, even if combustion gas leaks from a tip clearance between an end wall of a casing and a tip portion of a rotor blade, and a stagnation line 35 near a tip portion 22 is situated in the side of a back surface 24, because a section located radially outward of the border section 28 is bent in the rotational direction of the rotor, the stagnation line 35 is also situated toward the rotational direction of the rotor. Therefore, the stagnation lines 35 formed at various heights in the heightwise direction of the stationary blade 21 are generally aligned in the rotational direction of the rotor. Thus, fluctuation of pressure distribution in the heightwise direction of the stationary blade 21, of the combustion gas flowing into the stationary blade 21 can be reduced. As a result, secondary flow loss can be reduced and turbine efficiency can be improved.
摘要翻译：为了减少二次流动损失和提高涡轮机效率，位于固定叶片21的边界部分28的径向外侧的部分沿转子的旋转方向弯曲。因此，即使燃烧气体从壳体的端壁和转子叶片的前端部之间的顶端间隙泄漏，并且在顶端部22附近的停滞线35位于后表面24的侧面，因为位于边界部分28的径向外侧的部分沿转子的旋转方向弯曲，停滞线35也朝向转子的旋转方向。因此，在静止叶片21的高度方向上形成在各高度处的停滞线35大致在转子的旋转方向上对齐。因此，可以减少流入固定叶片21的燃烧气体的静止叶片21的高度方向的压力分布的波动。结果，能够降低二次流动损失，提高涡轮效率。

9. 发明申请

US20100284818A1 TURBINE BLADE CASCADE ENDWALL 审中-公开
标题翻译：涡轮叶片CASCADE ENDWALL
公开(公告)号：US20100284818A1
公开(公告)日：2010-11-11
申请号：US12812115
申请日：2008-09-25
申请人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono , Takashi Hiyama
发明人： Yasuro Sakamoto , Eisaku Ito , Susumu Wakazono , Takashi Hiyama
IPC分类号： F01D5/14
CPC分类号： F01D9/041 , F01D5/141 , F01D5/143 , F01D5/145 , F05D2250/70 , F05D2250/711
摘要： Provided is a turbine blade cascade endwall that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, therefore being capable of achieving enhanced turbine performance. A convex portion (11) that is gently swollen as a whole, that has an apex (P1) at a position of 0 to 20% pitch in a position of 5 to 25% Cax, that gently slopes from this apex (P1) toward a downstream side and a suction side surface of an adjacently disposed turbine stationary blade (B1) or turbine moving blade, and that slopes slightly steeply from the apex (P1) toward an upstream side is provided between one turbine stationary blade (B1) or turbine moving blade and another turbine stationary blade (B1) or turbine moving blade disposed adjacent to one turbine stationary blade (B1) or turbine moving blade.
摘要翻译：提供了一种涡轮叶栅级联端壁，其能够减少横流，并且能够减少与横流相关联地发生的二次流损失，因此能够实现增强的涡轮性能。一个整体轻轻肿胀的凸部（11），其顶点（P1）位于从该顶点（P1）缓缓倾斜的5至25％Cax位置处的0至20％间距的位置，朝向相邻设置的涡轮固定叶片（B1）或涡轮机动叶片的下游侧和吸力侧表面，并且从顶点（P1）向上游侧稍微倾斜地倾斜设置在一个涡轮静叶片（B1）或涡轮移动叶片和邻近一个涡轮固定叶片（B1）或涡轮机动叶片设置的另一涡轮机静叶片（B1）或涡轮机动叶片。

10. 发明授权

US07410343B2 Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：US07410343B2
公开(公告)日：2008-08-12
申请号：US11196388
申请日：2005-08-04
申请人： Susumu Wakazono , Kouichi Ishizaka , Masanori Yuri , Ronald Takahashi
发明人： Susumu Wakazono , Kouichi Ishizaka , Masanori Yuri , Ronald Takahashi
IPC分类号： F04D29/04
CPC分类号： F01D25/162
摘要： An outer shape of a section in the longitudinal direction at a leading edge of the strut is an aerofoil whose thickness is gradually increased along a flow direction of the combustion gas to prevent reduction of turbine efficiency caused by a shock wave generated at the strut of the exhaust diffuser.
摘要翻译：在支柱的前缘处的纵向截面的外形是其沿着燃烧气体的流动方向的厚度逐渐增加的机翼，以防止由于在支柱的支柱处产生的冲击波而引起的涡轮效率降低排气扩散器。

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