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1. 发明授权

US08469659B2 Turbine blade cascade endwall 有权
标题翻译：涡轮叶栅级联端壁
公开(公告)号：US08469659B2
公开(公告)日：2013-06-25
申请号：US12670962
申请日：2008-09-25
申请人： Yasuro Sakamoto , Eisaku Ito , Hiroyuki Otomo
发明人： Yasuro Sakamoto , Eisaku Ito , Hiroyuki Otomo
IPC分类号： F04D29/44
CPC分类号： F01D9/041 , F01D5/143 , F01D11/08 , F05D2250/71
摘要： Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade.
摘要翻译：提供了一种涡轮叶栅级联端壁，其能够抑制在涡轮机定子叶片的吸力表面上产生的涡流，并且能够减少由于该涡流引起的二次流动损失。设置在以环状布置的多个涡轮机定子叶片的末端侧的涡轮叶片级联端壁设置有减压部件，该减压部件减轻在涡轮机的吸力面处在叶片高度方向上产生的压力梯度定子叶片由于间隙泄漏流动而泄漏，所述间隙泄漏在位于涡轮机定子叶片的上游侧的涡轮转子叶片的末端与面对该涡轮机转子叶片的顶端的前端壁之间的间隙。

2. 发明申请

US20100196154A1 TURBINE BLADE CASCADE ENDWALL 有权
标题翻译：涡轮叶片CASCADE ENDWALL
公开(公告)号：US20100196154A1
公开(公告)日：2010-08-05
申请号：US12670962
申请日：2008-09-25
申请人： Yasuro Sakamoto , Eisaku Ito , Hiroyuki Otomo
发明人： Yasuro Sakamoto , Eisaku Ito , Hiroyuki Otomo
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/143 , F01D11/08 , F05D2250/71
摘要： Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade.
摘要翻译：提供了一种涡轮叶栅级联端壁，其能够抑制在涡轮机定子叶片的吸力表面上产生的涡流，并且能够减少由于该涡流引起的二次流动损失。设置在以环状布置的多个涡轮机定子叶片的末端侧的涡轮叶片级联端壁设置有减压部件，该减压部件减轻在涡轮机的吸力面处在叶片高度方向上产生的压力梯度定子叶片由于间隙泄漏流动而泄漏，所述间隙泄漏在位于涡轮机定子叶片的上游侧的涡轮转子叶片的末端与面对该涡轮机转子叶片的顶端的前端壁之间的间隙。

3. 发明授权

US09091170B2 One-stage stator vane cooling structure and gas turbine 有权
标题翻译：一级定子叶片冷却结构和燃气轮机
公开(公告)号：US09091170B2
公开(公告)日：2015-07-28
申请号：US13000874
申请日：2009-12-24
申请人： Yasuro Sakamoto , Eisaku Ito
发明人： Yasuro Sakamoto , Eisaku Ito
IPC分类号： F02C7/12 , F01D9/04 , F01D5/18 , F01D9/02 , F02C7/18
CPC分类号： F01D9/041 , F01D5/186 , F01D9/023 , F02C7/18 , F05D2260/202
摘要： A one-stage stator vane cooling structure consisting of: a plurality of linking members that are provided between a plurality of combustors disposed in the circumferential direction of a gas turbine; and cooling holes that are provided in each of the one-stage stator vanes to discharge a cooling gas from the inside to the outside of the one-stage stator vanes in order to cool the one-stage stator vanes on the periphery of the stagnation line of the combustion gas flowing in from the plurality of combustors; in which the cooling holes are formed at positions that are determined according to the relative positions of the one-stage stator vanes and the linking members disposed near the one-stage stator vanes.
摘要翻译：一级定子叶片冷却结构，包括：多个连接构件，其设置在沿燃气轮机的圆周方向设置的多个燃烧器之间; 以及设置在每个一级定子叶片中以将冷却气体从一级定子叶片的内部排出到外部的冷却孔，以便冷却停滞线周边上的一级定子叶片的从多个燃烧器流入的燃烧气体; 其中冷却孔形成在根据设置在一级定子叶片附近的一级定子叶片和连接构件的相对位置确定的位置处。

4. 发明申请

US20140041395A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20140041395A1
公开(公告)日：2014-02-13
申请号：US14008513
申请日：2012-03-23
申请人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
发明人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/141 , F01D5/142 , F01D5/145
摘要： A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.
摘要翻译：燃气轮机通过在燃烧器中供给燃料来燃烧在压缩机中被压缩的空气，以便通过将产生的燃烧气体供给到涡轮来获得旋转动力。涡轮机包括涡轮叶片元件和涡轮叶片元件，其涡轮在叶片元件和涡轮叶片元件之间交替定位，所述涡轮叶片元件和涡轮叶片元件沿着燃烧气体在具有圆柱形状的涡轮机气缸中流动的方向交替定位;以及烟道气体扩散器，圆筒。涡轮机叶片元件包括沿圆周方向等间隔设置的多个涡轮机叶片。涡轮机叶片在纵向端部侧上具有比纵向中间部分侧的喉部宽度大的喉部宽度。这有效地恢复烟气的压力。这提高了涡轮机的效率，从而可以提高性能。

5. 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。

6. 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.

7. 发明申请

US20140056690A1 GAS TURBINE 有权
标题翻译：燃气轮机
公开(公告)号：US20140056690A1
公开(公告)日：2014-02-27
申请号：US14008496
申请日：2012-03-06
申请人： Yasuro Sakamoto , Eisaku Ito
发明人： Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D9/04
CPC分类号： F01D9/045 , F01D5/143 , F01D11/08
摘要： A gas turbine includes a turbine blade, a turbine vane, a ring segment circumferentially surrounding the turbine blade, an outer shroud circumferentially surrounding the turbine vane, and a combustion gas flow-path provided in the ring segment and the outer shroud. The outer shroud is positioned on an upstream side of the ring segment in a gas flow direction of the combustion gas. Seal gas, of which temperature is lower than that of the combustion gas, is fed between the ring segment- and the outer shroud into the combustion gas flow-path. The outer shroud has a guide surface that is provided on an inner circumference thereof on a downstream side of the gas flow direction. The guide surface is formed such that a flow passage area of the combustion gas flow-path is gradually increased.
摘要翻译：燃气轮机包括涡轮机叶片，涡轮叶片，周向围绕涡轮机叶片的环形分段，周向围绕涡轮叶片的外部护罩以及设置在环形部分和外部护罩中的燃烧气体流动路径。外护罩位于燃烧气体的气流方向上的环段的上游侧。温度低于燃烧气体的密封气体在环形部分和外部护罩之间供给到燃烧气体流动路径中。外护罩具有在气体流动方向的下游侧设置在其内周的引导面。引导表面形成为使得燃烧气体流路的流路面积逐渐增加。

8. 发明授权

US09719354B2 Gas turbine with improved blade and vane and flue gas diffuser 有权
公开(公告)号：US09719354B2
公开(公告)日：2017-08-01
申请号：US14008513
申请日：2012-03-23
申请人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
发明人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/141 , F01D5/142 , F01D5/145
摘要： A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.

9. 发明授权

US09689272B2 Gas turbine and outer shroud 有权
公开(公告)号：US09689272B2
公开(公告)日：2017-06-27
申请号：US14008496
申请日：2012-03-06
申请人： Yasuro Sakamoto , Eisaku Ito
发明人： Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D9/04 , F01D5/14 , F01D11/08
CPC分类号： F01D9/045 , F01D5/143 , F01D11/08
摘要： A gas turbine includes a turbine blade, a turbine vane, a ring segment circumferentially surrounding the turbine blade, an outer shroud circumferentially surrounding the turbine vane, and a combustion gas flow-path provided in the ring segment and the outer shroud. The outer shroud is positioned on an upstream side of the ring segment in a gas flow direction of the combustion gas. Seal gas, of which temperature is lower than that of the combustion gas, is fed between the ring segment- and the outer shroud into the combustion gas flow-path. The outer shroud has a guide surface that is provided on an inner circumference thereof on a downstream side of the gas flow direction. The guide surface is formed such that a flow passage area of the combustion gas flow-path is gradually increased.

10. 发明授权

US09395085B2 Communicating structure between adjacent combustors and turbine portion and gas turbine 有权
标题翻译：相邻燃烧器与涡轮机部分和燃气轮机之间的通信结构
公开(公告)号：US09395085B2
公开(公告)日：2016-07-19
申请号：US13500009
申请日：2010-05-14
申请人： Rosic Budmir , Yasuro Sakamoto , Sumiu Uchida , Eisaku Ito , Tsuyoshi Kitamura , Satoshi Hada , Sosuke Nakamura
发明人： Rosic Budmir , Yasuro Sakamoto , Sumiu Uchida , Eisaku Ito , Tsuyoshi Kitamura , Satoshi Hada , Sosuke Nakamura
IPC分类号： F01D9/02 , F23R3/60 , F01D9/06 , F23R3/34
CPC分类号： F23R3/60 , F01D9/023 , F01D9/065 , F23R3/346
摘要： In a communicating structure between combustors that generates combustion gas inside pipe pieces and a turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of turbine stator vanes and turbine rotor blades, at least some of the first-stage turbine stator vanes closest to the combustor among the turbine stator vanes are disposed downstream of sidewalls of one pipe piece and another pipe piece that are adjacent to each other, and the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the sidewalls of the pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the one pipe piece and an internal surface of the sidewall of the other pipe piece.
摘要翻译：在通过使燃烧气体依次通过由涡轮机定子叶片和涡轮机转子叶片形成的涡轮级而产生旋转驱动力的燃烧器之间的通气结构中产生燃烧气体的至少一部分的第一在涡轮定子叶片中最接近燃烧器的台阶涡轮机定子叶片设置在彼此相邻的一个管件和另一个管件的侧壁的下游，并且距离设置在下游的第一级涡轮机定子叶片的前缘的距离所述管件的侧壁的靠近所述涡轮部的所述侧壁的端部的距离等于或小于所述一个管件的侧壁的内表面与所述另一个管件的侧壁的内表面之间的间隔。

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