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公开(公告)号：US09163838B2
公开(公告)日：2015-10-20
申请号：US13395763
申请日：2010-11-08
Applicant: Satoshi Takiguchi , Shinji Akamatsu , Kenji Sato , Naoki Abe
Inventor： Satoshi Takiguchi , Shinji Akamatsu , Kenji Sato , Naoki Abe
CPC classification number: F23R3/14 , F23C2900/07001 , F23D2900/00003 , F23D2900/00008 , F23D2900/14004 , F23D2900/14701 , F23R3/286 , F23R3/36
Abstract: Provided is a gas turbine combustion burner capable of uniformly ejecting fuel from ejection holes for reduced NOx emissions of gas turbine combustors. The gas turbine combustion burner includes a plurality of swirling vanes (20) for ejecting fuel from fuel ejection holes (23, 24) into air or a mixture of air and fuel flowing from an upstream side while applying a swirling force to form a swirling mixed airflow and a nozzle (21) having the swirling vanes (20) arranged radially on an outer circumferential surface thereof and having a first fuel passage (26), through which the fuel is guided to the fuel ejection holes (23, 24), provided therein, a cavity (25) communicating with the fuel ejection holes (23, 24) is provided in each swirling vane (20), and at least two second fuel passages (27) are provided between the cavity (25) and the first fuel passage (26) along an axial direction.
Abstract translation: 提供一种燃气轮机燃烧器，其能够从用于减少燃气轮机燃烧器的NOx排放的喷射孔均匀地排出燃料。 燃气轮机燃烧器包括多个旋转叶片（20），用于将燃料从燃料喷射孔（23,24）喷射到空气中或从上游侧流出的空气和燃料的混合物，同时施加旋转力以形成旋转混合 气流和具有涡旋叶片（20）的喷嘴（21），径向布置在其外圆周表面上并且具有第一燃料通道（26），燃料被引导到燃料喷射孔（23,24），所述第一燃料通道 在每个回旋叶片（20）中设置有与燃料喷射孔（23,24）连通的空腔（25），并且至少两个第二燃料通道（27）设置在空腔（25）和第一燃料 通道（26）。
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2.发明申请公开(公告)号：US20100116645A1
公开(公告)日：2010-05-13
申请号：US12593250
申请日：2007-03-27
Applicant: Yoichi Sato , Shigeru Horigome , Satoshi Takiguchi , Yasutake Takamatsu , Katsunori Takahashi
Inventor： Yoichi Sato , Shigeru Horigome , Satoshi Takiguchi , Yasutake Takamatsu , Katsunori Takahashi
IPC: C23C14/40
CPC classification number: G11B5/8404
Abstract: A surface processing method of processing a surface of a substrate includes disposing the substrate in a vacuum chamber, processing by applying a high-frequency voltage to the substrate and by sputtering the surface of the substrate, measuring a cathode drop potential generated at the substrate in the processing and obtaining a time integration value of the cathode drop potential, and determining whether or not a processed state of the surface of the substrate is good based on the time integration value obtained in the measuring.
Abstract translation: 处理基板表面的表面处理方法包括将基板设置在真空室中，通过向基板施加高频电压，通过溅射基板的表面进行处理，测定基板上产生的阴极液滴电位 处理并获得阴极滴下电位的时间积分值，并且基于在测量中获得的时间积分值来确定衬底的表面的处理状态是否良好。
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公开(公告)号：US08826666B2
公开(公告)日：2014-09-09
申请号：US13882655
申请日：2012-03-30
Applicant: Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
Inventor： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
CPC classification number: F23R3/28 , F23C2900/07021 , F23D14/24 , F23D2900/00014 , F23D2900/00016 , F23R3/14 , F23R3/283 , F23R3/343
Abstract: A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.
Abstract translation: 引燃喷嘴，燃气轮机燃烧器和燃气轮机设置有具有燃料通道的喷嘴主体，以预定间隔布置在喷嘴主体的前端部外周部分的外侧的盖环，以形成 内部空气通道并且能够朝向喷嘴主体的前侧喷射空气;多个喷嘴头，其包括燃料喷嘴，喷嘴以周向方向以预定间隔安装到盖环的前端部，以便连通 并且能够从内部空气通道向喷射空气的外部喷射燃料;以及旋转力施加单元，其通过内部空气通道喷射的空气施加旋转力。
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公开(公告)号：US20140041389A1
公开(公告)日：2014-02-13
申请号：US13882655
申请日：2012-03-30
Applicant: Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
Inventor： Shuhei Kajimura , Keijiro Saito , Satoshi Takiguchi , Mitsuhiro Nakao , Koichi Nishida , Shinji Akamatsu , Sosuke Nakamura , Masaki Mitani
IPC: F23R3/28
CPC classification number: F23R3/28 , F23C2900/07021 , F23D14/24 , F23D2900/00014 , F23D2900/00016 , F23R3/14 , F23R3/283 , F23R3/343
Abstract: A pilot nozzle, a gas turbine combustor and a gas turbine are provided with a nozzle main body having a fuel passage, a cover ring arranged at an outside of a front end-outer peripheral portion of the nozzle main body at a predetermined interval to form an inner air passage and capable of injecting air toward a front side of the nozzle main body, a plurality of nozzle tips that includes a fuel injection nozzle attached to a front end portion of the cover ring at a predetermined interval in a circumferential direction to communicate with the fuel passage and is able to inject fuel toward an outside of injection air from the inner air passage, and a swirling force application unit that applies a swirling force to air injected through the inner air passage.
Abstract translation: 引燃喷嘴，燃气轮机燃烧器和燃气轮机设置有具有燃料通道的喷嘴主体，以预定间隔布置在喷嘴主体的前端部外周部分的外侧的盖环，以形成 内部空气通道并且能够朝向喷嘴主体的前侧喷射空气;多个喷嘴头，其包括燃料喷嘴，喷嘴以周向方向以预定间隔安装到盖环的前端部，以便连通 并且能够从内部空气通道向喷射空气的外部喷射燃料;以及旋转力施加单元，其通过内部空气通道喷射的空气施加旋转力。
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公开(公告)号：US20140013762A1
公开(公告)日：2014-01-16
申请号：US14007253
申请日：2012-03-14
Applicant: Satoshi Takiguchi , Keijiro Saito , Teruhiro Matsumoto , Kenji Sato , Hidenobu Tamai , Shigemi Mandai
Inventor： Satoshi Takiguchi , Keijiro Saito , Teruhiro Matsumoto , Kenji Sato , Hidenobu Tamai , Shigemi Mandai
CPC classification number: F02C7/18 , F01D9/023 , F01D25/14 , F23R3/002 , F23R3/286 , F23R3/42 , F23R2900/00012
Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).
Abstract translation: 根据本发明的燃烧器（10）包括：燃烧器筐（14），其中压缩空气和燃料彼此混合并且混合物燃烧; 一个过渡件（17），其中燃烧器筐（14）的顶端部分间插入间隙（C）; 弹簧夹（19），其密封所述燃烧器筐（14）和所述过渡件（17）之间的间隙; 设置在所述间隙（C）的开口部（Ck）上的节流部（21），所述开口部（Ck）向所述燃烧器筐（14）的前端侧的所述过渡件（17）开口， 所述开口部（Ck）与所述基端侧相比较; 和用于冷却节流部（21）的冷却装置（22）。
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Patent Agency Ranking
公开(公告)号：US20130139511A1
公开(公告)日：2013-06-06
申请号：US13817384
申请日：2012-02-28
Applicant: Satoshi Sometani , Satoshi Takiguchi , Shigemi Mandai
Inventor： Satoshi Sometani , Satoshi Takiguchi , Shigemi Mandai
IPC: F02C7/00
Abstract: A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).
Abstract translation: 燃气轮机燃烧器包括：外筒（31）; 设置在所述外筒（31）内部以在所述外筒（31）和所述内筒（32）之间形成空气通道（30）的内筒（32） 沿着燃烧器轴线（S）的方向设置在所述内筒（32）的中心部分的先导喷嘴（35）; 多个主喷嘴（36），其围绕所述先导喷嘴（35）设置在所述内筒（32）的内周面上，以围绕所述先导喷嘴（35），所述多个主喷嘴（36）将燃料与燃烧空气 引入空气通道（30）并将燃料喷射到内筒（32）中; 以及在空气通道（30）内部跨越圆周方向设置的顶帽喷嘴（41），以在到达多个主喷嘴（36）之前将燃料与燃烧空气混合。
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公开(公告)号：US08065880B2
公开(公告)日：2011-11-29
申请号：US11655059
申请日：2007-01-19
Applicant: Koichi Ishizaka , Yutaka Kawata , Satoshi Takiguchi , Satoshi Tanimura
Inventor： Koichi Ishizaka , Yutaka Kawata , Satoshi Takiguchi , Satoshi Tanimura
IPC: F02C1/00
Abstract: A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has a fuel nozzle, a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle, and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle. The swirler vanes gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vanes.
Abstract translation: 用于燃气轮机的预混合燃烧器可以有效地预混合燃料和空气以产生具有均匀浓度的燃料气体，同时通过使燃料气体的流量基本上均匀地可靠地实现防止闪回。 用于燃气轮机的预混合燃烧器具有燃料喷嘴，燃烧器筒体，其布置成围绕燃料喷嘴并且在其与燃料喷嘴之间形成空气通道，以及沿燃料喷嘴的轴向布置的旋流叶片 在燃料喷嘴的外周面周向的多个位置。 旋流器叶片从上游侧到下游侧逐渐弯曲，以使从空气通道中流动的空气从上游侧向下游侧旋转。 在旋流叶片的内周侧的后缘部设置切口部。
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公开(公告)号：US20100263381A1
公开(公告)日：2010-10-21
申请号：US11655059
申请日：2007-01-19
Applicant: Koichi Ishizaka , Yutaka Kawata , Satoshi Takiguchi , Satoshi Tanimura
Inventor： Koichi Ishizaka , Yutaka Kawata , Satoshi Takiguchi , Satoshi Tanimura
IPC: F02C7/22
Abstract: A premixed combustion burner for a gas turbine is provided that can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has: a fuel nozzle; a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle; and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle and that gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vane.
Abstract translation: 提供了一种用于燃气轮机的预混合燃烧器，其能够有效地预混合燃料和空气以产生具有均匀浓度的燃料气体，同时通过使燃料气体的流量基本上均匀地可靠地实现防止闪回。 用于燃气轮机的预混合燃烧器具有：燃料喷嘴; 燃烧器筒，其布置成围绕燃料喷嘴并在其与燃料喷嘴之间形成空气通道; 旋流器叶片，其沿着燃料喷嘴的轴向设置在燃料喷嘴的外周面的圆周方向上的多个位置，并且从上游侧向下游侧逐渐弯曲，以旋转内侧的空气 空气通道从上游侧到下游侧。 在旋流叶片的内周侧的后缘部设置切口部。
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公开(公告)号：US09957893B2
公开(公告)日：2018-05-01
申请号：US14007253
申请日：2012-03-14
Applicant: Satoshi Takiguchi , Keijiro Saito , Teruhiro Matsumoto , Kenji Sato , Hidenobu Tamai , Shigemi Mandai
Inventor： Satoshi Takiguchi , Keijiro Saito , Teruhiro Matsumoto , Kenji Sato , Hidenobu Tamai , Shigemi Mandai
CPC classification number: F02C7/18 , F01D9/023 , F01D25/14 , F23R3/002 , F23R3/286 , F23R3/42 , F23R2900/00012
Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).
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公开(公告)号：US09719419B2
公开(公告)日：2017-08-01
申请号：US13817384
申请日：2012-02-28
Applicant: Satoshi Sometani , Satoshi Takiguchi , Shigemi Mandai
Inventor： Satoshi Sometani , Satoshi Takiguchi , Shigemi Mandai
Abstract: A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).
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