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11. 发明授权

US09845689B2 Turbine exhaust structure and gas turbine 有权
公开(公告)号：US09845689B2
公开(公告)日：2017-12-19
申请号：US14008434
申请日：2012-03-22
申请人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
发明人： Hitoshi Kitagawa , Yasuro Sakamoto , Eisaku Ito
IPC分类号： F01D9/02 , F01D25/30 , F02C7/00
CPC分类号： F01D9/02 , F01D25/30 , F02C7/00 , F05D2250/52 , F05D2260/213
摘要： In a turbine exhaust structure and a gas turbine, a turbine casing (26) formed in an annular shape to constitute a combustion gas passage A is provided. An exhaust diffuser (31) formed in an annular shape to constitute a flue gas passage (B) is connected to the turbine casing (26) to constitute a configuration. By providing a pressure loss body (61) in the exhaust diffuser (31), efficient pressure recovery can be carried out, which improves turbine efficiency, thereby enabling improvement of the performance.

12. 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.

13. 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。

14. 发明申请

US20120247125A1 COMMUNICATING STRUCTURE BETWEEN COMBUSTOR AND TURBINE PORTION AND GAS TURBINE 有权
标题翻译：燃油机与涡轮机和气体涡轮机之间的通讯结构
公开(公告)号：US20120247125A1
公开(公告)日：2012-10-04
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： F02C7/00 , F02C3/04
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。

15. 发明申请

US20110116937A1 ONE-STAGE STATOR VANE COOLING STRUCTURE AND GAS TURBINE 有权
标题翻译：一级定子风扇冷却结构和气体涡轮
公开(公告)号：US20110116937A1
公开(公告)日：2011-05-19
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： F01D5/18
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。

16. 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。

17. 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。

18. 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.

19. 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。

20. 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。

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