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1. 发明申请

US20050066664A1 Gas turbine installation 有权
标题翻译：燃气轮机安装
公开(公告)号：US20050066664A1
公开(公告)日：2005-03-31
申请号：US10950531
申请日：2004-09-28
申请人： Takanori Shibata , Shinya Marushima , Nobuaki Kizuka , Hidefumi Araki , Shigeo Hanamiya
发明人： Takanori Shibata , Shinya Marushima , Nobuaki Kizuka , Hidefumi Araki , Shigeo Hanamiya
IPC分类号： F02C7/18 , F02C3/30 , F02C9/28
CPC分类号： F02C7/1435 , F02C7/12 , F02C9/52 , F05D2270/3062
摘要： A gas turbine installation is provided in which turbine cooling air can be humidified with water while suppressing deterioration of the reliability of turbine blades. The gas turbine installation comprises a compressor for compressing air, a combustor for burning compressed air and fuel, a turbine driven by combustion gas, and a humidifier for humidifying the compressed air extracted from an intermediate stage or a discharge section of the compressor. The compressed air humidified by the humidifier is used as turbine cooling air. The humidifier includes a water distributor for adjusting an amount of water added to the compressed air.
摘要翻译：提供了一种燃气轮机装置，其中涡轮冷却空气可以用水加湿，同时抑制涡轮叶片的可靠性的劣化。燃气轮机装置包括用于压缩空气的压缩机，用于燃烧压缩空气和燃料的燃烧器，由燃烧气体驱动的涡轮机和用于加湿从压缩机的中间级或排出部分抽出的压缩空气的加湿器。被加湿器加湿的压缩空气用作涡轮冷却空气。加湿器包括用于调节加到压缩空气中的水量的水分配器。

2. 发明授权

US07444819B2 Gas turbine installation including a compressed air humidifier and method 有权
标题翻译：燃气轮机安装包括压缩空气加湿器和方法
公开(公告)号：US07444819B2
公开(公告)日：2008-11-04
申请号：US10950531
申请日：2004-09-28
申请人： Takanori Shibata , Shinya Marushima , Nobuaki Kizuka , Hidefumi Araki , Shigeo Hanamiya
发明人： Takanori Shibata , Shinya Marushima , Nobuaki Kizuka , Hidefumi Araki , Shigeo Hanamiya
IPC分类号： F02C3/30
CPC分类号： F02C7/1435 , F02C7/12 , F02C9/52 , F05D2270/3062
摘要： A gas turbine installation is provided in which turbine cooling air can be humidified with water while suppressing deterioration of the reliability of turbine blades. The gas turbine installation comprises a compressor for compressing air, a combustor for burning compressed air and fuel, a turbine driven by combustion gas, and a humidifier for humidifying the compressed air extracted from an intermediate stage or a discharge section of the compressor. The compressed air humidified by the humidifier is used as turbine cooling air. The humidifier includes a water distributor for adjusting an amount of water added to the compressed air.
摘要翻译：提供了一种燃气轮机装置，其中涡轮冷却空气可以用水加湿，同时抑制涡轮叶片的可靠性的劣化。燃气轮机装置包括用于压缩空气的压缩机，用于燃烧压缩空气和燃料的燃烧器，由燃烧气体驱动的涡轮机和用于加湿从压缩机的中间级或排出部分抽出的压缩空气的加湿器。被加湿器加湿的压缩空气用作涡轮冷却空气。加湿器包括用于调节加到压缩空气中的水量的水分配器。

3. 发明授权

US07320175B2 Production process of gas turbine 有权
标题翻译：燃气轮机生产工艺
公开(公告)号：US07320175B2
公开(公告)日：2008-01-22
申请号：US10765866
申请日：2004-01-29
申请人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
发明人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
IPC分类号： B21K25/00 , F02C6/00
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/61 , F05D2240/40 , Y02E20/14 , Y02E20/16 , Y02T50/67 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49716
摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
摘要翻译：本发明提供一种可应用于各种循环的燃气轮机的生产方法。燃气轮机的主要部分是基于大致设定的条件而预先设定的，并且可以基于该组设定压缩机的级数和可以提供适合于期望循环的条件的涡轮机的级数主体。每个具有设定级数并且包括在主要部分中的压缩机和涡轮机彼此组合以构造燃气轮机。当压缩机或涡轮机的设定级数在多个期望循环中不同时，具有形成压缩机或涡轮机的大致环形流动通道的内周壁的外周的大致圆盘形构件，被组装到具有较少数量级的循环中，使得在多个期望循环中操作的燃气轮机中的轴承 - 承载距离保持恒定。

4. 发明申请

US20050076502A1 Production process of gas turbine 有权
标题翻译：燃气轮机生产工艺
公开(公告)号：US20050076502A1
公开(公告)日：2005-04-14
申请号：US10765866
申请日：2004-01-29
申请人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
发明人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
IPC分类号： F02C3/04 , F02C3/13 , B23P17/04 , B21K21/16
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/61 , F05D2240/40 , Y02E20/14 , Y02E20/16 , Y02T50/67 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49716
摘要： The invention provides a production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is set in advance based on roughly set conditions, and the number of stages of a compressor and the number of stages of a turbine, which can provide conditions suitable for a desired cycle, are set based on the set principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined with each other to construct the gas turbine. When the set number of stages of the compressor or the turbine differs among a plurality of desired cycles, a substantially disk-shaped member having an outer periphery, which forms an inner peripheral wall of a substantially annular flow passage of the compressor or the turbine, is assembled into the cycle having a smaller number of stages so that the bearing-to-bearing distance is kept constant in the gas turbine operated in the plurality of desired cycles.
摘要翻译：本发明提供一种可应用于各种循环的燃气轮机的生产方法。燃气轮机的主要部分是基于大致设定的条件而预先设定的，并且可以基于该组设定压缩机的级数和可以提供适合于期望循环的条件的涡轮机的级数主体。每个具有设定级数并且包括在主要部分中的压缩机和涡轮机彼此组合以构造燃气轮机。当压缩机或涡轮机的设定级数在多个期望循环中不同时，具有形成压缩机或涡轮机的大致环形的流路的内周壁的外周的大致圆盘状构件，被组装到具有较少数量级的循环中，使得在多个期望循环中操作的燃气轮机中的轴承 - 承载距离保持恒定。

5. 发明授权

US06865893B2 Production process of gas turbine 有权
标题翻译：燃气轮机生产工艺
公开(公告)号：US06865893B2
公开(公告)日：2005-03-15
申请号：US10602686
申请日：2003-06-25
申请人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
发明人： Tomomi Koganezawa , Takanori Shibata , Nobuhiro Seiki , Shinya Marushima , Shinichi Higuchi , Nobuaki Kizuka , Ryou Akiyama , Masami Noda
IPC分类号： F02C3/04 , F02C3/13 , F02C6/00
CPC分类号： F02C3/13 , F02C3/04 , F05D2230/61 , F05D2240/40 , Y02E20/14 , Y02E20/16 , Y02T50/67 , Y10T29/49316 , Y10T29/4932 , Y10T29/49321 , Y10T29/49323 , Y10T29/49716
摘要： A production process of a gas turbine capable of being applied to various cycles. A principal part of a gas turbine is initially set based on roughly set conditions, and the number of stages of the compressor and of the turbine for a desired cycle are set for the principal part. The compressor and the turbine each having the set number of stages and included in the principal part are combined to construct the gas turbine. When the set number of stages of the compressor or the turbine differs for a different desired cycle, a disk-shaped member having an outer periphery, which forms an inner peripheral wall of the annular flow passage of the compressor or the turbine, is assembled into the principal part having a smaller number of stages so that the bearing-to-bearing distance is kept constant.
摘要翻译：能够应用于各种循环的燃气轮机的制造方法。燃气轮机的主要部分基于大致设定的条件初始设定，并且为主要部分设定用于所需循环的压缩机和涡轮机的级数。每个具有设定级数并且包括在主要部分中的压缩机和涡轮机被组合以构造燃气轮机。当压缩机或涡轮机的设定级数对于不同的期望循环不同时，具有形成压缩机或涡轮机的环形流动通道的内周壁的外周的盘形部件被组装成主要部分具有较少的级数，使得承载距离保持恒定。

6. 发明授权

US07909564B2 Gas turbine and gas turbine cooling method 有权
公开(公告)号：US07909564B2
公开(公告)日：2011-03-22
申请号：US12405802
申请日：2009-03-17
申请人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
发明人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
IPC分类号： F04D29/44
CPC分类号： F01D11/025 , F01D5/081 , F01D11/001
摘要： A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

7. 发明授权

US07507069B2 Gas turbine and gas turbine cooling method 有权
标题翻译：燃气轮机和燃气轮机冷却方式
公开(公告)号：US07507069B2
公开(公告)日：2009-03-24
申请号：US11174555
申请日：2005-07-06
申请人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
发明人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
IPC分类号： F04D29/54
CPC分类号： F01D11/025 , F01D5/081 , F01D11/001
摘要： A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.
摘要翻译：燃气轮机包括喷嘴叶片和与喷嘴叶片接合的密封单元，所述涡轮机配备有通过混合和燃烧用于燃烧和燃料的空气而产生的燃烧气体。喷嘴叶片和密封单元设置在气体通道出口侧的向下流动的燃烧气体的通道中。密封单元和喷嘴叶片之间的多个接合部分从燃烧气体的流动方向的上游侧向下游侧连续设置，并且多个接合部中的下游侧具有形成在横跨涡轮旋转轴的方向。可以抑制燃气轮机的热效率的降低。

8. 发明申请

US20060239820A1 Member having internal cooling passage 有权
标题翻译：会员有内部冷却通道
公开(公告)号：US20060239820A1
公开(公告)日：2006-10-26
申请号：US11395310
申请日：2006-04-03
申请人： Nobuaki Kizuka , Yasuhiro Horiuchi , Shinya Marushima , Hidetoshi Kuroki
发明人： Nobuaki Kizuka , Yasuhiro Horiuchi , Shinya Marushima , Hidetoshi Kuroki
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/22141
摘要： Provided is a member having an internal cooling passage 7c formed therein and having opposed partition walls 6b, 6c between which a medium flows to cool a parent material, including a first heat transfer rib 25a which extends from almost the center between the opposed partition walls 6b, 6c to one partition wall 6c and slants in a downstream direction of the medium, and a second heat transfer rib 25b which extends from almost the center between the opposed partition walls 6b, 6c to the other partition wall 6b and slants in the downstream direction of the medium, wherein a slit 70a or 70b which passes through between an upstream side of the cooling passage 7c and a downstream side thereof is formed in the first heat transfer rib 70a or the second heat transfer rib 70b.
摘要翻译：本发明提供一种具有形成在其中的内部冷却通道7c并且具有相对的分隔壁6b，6c的构件，介质在其间流动以冷却母材，其包括第一传热肋25a，第一传热肋25a从相对的分隔壁6b，6c到一个分隔壁6c并沿着介质的下游方向倾斜;以及第二传热肋25b，其从相对的分隔壁6b，6c之间的大致中心延伸到其他分隔壁6b和介质下游方向倾斜，其中在第一传热肋70中形成有在冷却通道7c的上游侧和下游侧之间通过的狭缝70a或70b a或第二传热肋70b。

9. 发明申请

US20060034685A1 Gas turbine and gas turbine cooling method 有权
公开(公告)号：US20060034685A1
公开(公告)日：2006-02-16
申请号：US11174555
申请日：2005-07-06
申请人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
发明人： Nobuaki Kizuka , Shinya Marushima , Masami Noda , Shinichi Higuchi , Yasuhiro Horiuchi
IPC分类号： F01D9/00
CPC分类号： F01D11/025 , F01D5/081 , F01D11/001
摘要： A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

10. 发明授权

US06491495B1 Closed circuit blade-cooled turbine 有权
标题翻译：闭路叶片风机
公开(公告)号：US06491495B1
公开(公告)日：2002-12-10
申请号：US09644058
申请日：2000-08-23
申请人： Shinya Marushima , Shunichi Anzai , Masami Noda , Manabu Matsumoto , Nobuaki Kizuka , Tsuyoshi Takano
发明人： Shinya Marushima , Shunichi Anzai , Masami Noda , Manabu Matsumoto , Nobuaki Kizuka , Tsuyoshi Takano
IPC分类号： F02C718
CPC分类号： F01D5/084 , F01D5/081 , F02C7/18 , F05D2260/205
摘要： In a closed circuit moving blade cooled turbine, holes in the radial direction formed in the outer periphery of a second stage wheel are led to cooling air supply holes to second stage moving blades and to prevent the cooling air from leaking into the junction, the holes in the radial direction and the cooling air supply holes are interconnected and the supply members covering the junction are fit into them. The cooling air after cooling the second stage moving blades is introduced into the collection holes formed in the outer periphery of the spacer via the cooling air collection holes and to prevent the cooling air from leaking into the boundary, the cooling air collection holes and collection holes are interconnected and the collection members covering the boundary are fit into them. To make the sum of minimum sectional areas of the respective paths of the second stage moving blades smaller than the sum of minimum sectional areas of the respective paths of the first stage moving blades, a minimum sectional member is incorporated into the supply member.
摘要翻译：在闭路动叶片冷却涡轮机中，形成在第二级轮的外周上的径向孔被引导到第二级动叶片的冷却空气供给孔，并且防止冷却空气泄漏到接合处，孔在径向方向和冷却空气供应孔相互连接，并且覆盖接合处的供应构件装配到它们中。冷却第二级活动叶片后的冷却空气经由冷却空气收集孔被引入形成在间隔件的外周的收集孔中，并且防止冷却空气泄漏到边界内，冷却空气收集孔和收集孔相互连接并且覆盖边界的收集构件适合它们。为了使第二级动叶片的相应路径的最小截面面积的总和小于第一级动叶片的相应路径的最小截面积的总和，最小截面构件被结合到供应构件中。

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