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1. 发明申请

US20090320438A1 TWO-SHAFT GAS TURBINE 有权
标题翻译：双轴瓦斯涡轮
公开(公告)号：US20090320438A1
公开(公告)日：2009-12-31
申请号：US12466818
申请日：2009-05-15
申请人： Tomomi KOGANEZAWA , Shinichi Higuchi , Yasuo Takahashi , Ryo Akiyama , Shinya Marushima
发明人： Tomomi KOGANEZAWA , Shinichi Higuchi , Yasuo Takahashi , Ryo Akiyama , Shinya Marushima
IPC分类号： F02G3/00
CPC分类号： F02C6/18 , F02C3/10 , F02C3/305 , F02C9/16 , Y02E20/14 , Y02E20/16
摘要： Provided is a two-shaft gas turbine with improved reliability that improves output power and efficiency and is stably operated by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system in which the flow rate of fluid flowing into a combustor is increased compared with a simple cycle gas turbine.A portion of working fluid driving the high-pressure turbine is allowed to flow not into the high-pressure turbine but into a low-pressure turbine.
摘要翻译：提供了一种具有改进的可靠性的双轴燃气轮机，其提高输出功率和效率，并且通过在压缩机的驱动力与高压涡轮机的输出功率之间的平衡来稳定地操作，在双轴燃气轮机被应用于与简单循环燃气轮机相比流入燃烧器的流体的流量增加的系统。驱动高压涡轮机的工作流体的一部分被允许不流入高压涡轮机，而是流入低压涡轮机。

2. 发明授权

US08613186B2 Two-shaft gas turbine 有权
标题翻译：双轴燃气轮机
公开(公告)号：US08613186B2
公开(公告)日：2013-12-24
申请号：US12466818
申请日：2009-05-15
申请人： Tomomi Koganezawa , Shinichi Higuchi , Yasuo Takahashi , Ryo Akiyama , Shinya Marushima
发明人： Tomomi Koganezawa , Shinichi Higuchi , Yasuo Takahashi , Ryo Akiyama , Shinya Marushima
IPC分类号： F02C6/00 , F02G1/00 , F02G3/00
CPC分类号： F02C6/18 , F02C3/10 , F02C3/305 , F02C9/16 , Y02E20/14 , Y02E20/16
摘要： Provided in one embodiment is a two-shaft gas turbine that exhibits improved reliability, output power, and efficiency. The turbine operates stably by establishing a balance between the driving force of a compressor and the output power of a high-pressure turbine in the case where the two-shaft gas turbine is applied to a system, in which the flow rate of a fluid flowing into a combustor is higher than a simple cycle gas turbine. A portion of the fluid driving the high-pressure turbine is allowed to flow not into the high-pressure turbine but into a low-pressure turbine.
摘要翻译：在一个实施例中提供的是具有提高的可靠性，输出功率和效率的双轴燃气轮机。在将双轴燃气轮机应用到系统的情况下，通过在压缩机的驱动力和高压涡轮机的输出功率之间建立平衡来使涡轮运行平稳，其中流体流动的流量燃烧器高于简单循环燃气轮机。驱动高压涡轮机的流体的一部分被允许不流入高压涡轮机，而是流入低压涡轮机。

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

US06648600B2 Turbine rotor 有权
公开(公告)号：US06648600B2
公开(公告)日：2003-11-18
申请号：US10136313
申请日：2002-05-02
申请人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
发明人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
IPC分类号： F01D518
CPC分类号： F01D5/084 , F01D5/08 , Y10T29/49318
摘要： A turbine rotor can fix the heat resisting pipes provided in divided form per the disk member with simple structure for preventing wearing and damaging. The turbine rotor includes a coolant flow path formed through a plurality of disc shaped members respectively stacked across stacking planes in axial direction, a heat resisting pipe divided into a plurality of fractions adapted to be inserted into a portion of the coolant flow path defined in each disc shaped member, spot facing recesses each formed at opening portion of coolant flow path at the same side of the disc shaped member coaxially with the coolant flow path and having greater inner diameter than the opening portion, and ring shaped projecting portions formed at respective end portions of the fractions of the heat resisting pipe and engageable with respective spot facing recesses.

7. 发明申请

US20120060509A1 Inner Bleed Structure of 2-Shaft Gas Turbine and a Method to Determine the Stagger Angle of Last Stage Stator of Compressor for 2-Shaft Gas Turbine 审中-公开
标题翻译： 2轴燃气轮机内部排气结构及确定2轴燃气轮机压缩机末级定子交错角的方法
公开(公告)号：US20120060509A1
公开(公告)日：2012-03-15
申请号：US13198751
申请日：2011-08-05
申请人： Chihiro MYOREN , Ryou Akiyama , Shinya Marushima , Yasuo Takahashi , Shinichi Higuchi
发明人： Chihiro MYOREN , Ryou Akiyama , Shinya Marushima , Yasuo Takahashi , Shinichi Higuchi
IPC分类号： F02C6/04 , G01M15/14
CPC分类号： F04D29/321 , F01D5/085
摘要： An inner bleed structure of the 2-shaft gas turbine includes a slit for leading part of compressed air to a cavity is formed between a wall surface of a rotor wheel of the compressor equipped with a last stage rotor of the compressor which is connected to a first rotating shaft and end of an inner casing, and a bleed hole for leading part of compressed air after flowing down the last stage of the compressor to a cavity formed in the inner side of the inner casing at the downstream side of the last stage of the compressor.
摘要翻译： 2轴燃气轮机的内排气结构包括用于将压缩空气的一部分引导到空腔的狭缝形成在配备有压缩机的最后级转子的压缩机的转子轮的壁表面之间，压缩机的最后级转子连接到第一旋转轴和内壳的端部，以及用于在压缩机的最后阶段向下流动的压缩空气的前端部分之后的下游侧的形成在内壳的内侧的空腔的排气孔压缩机。

8. 发明授权

US06994516B2 Turbine rotor 有权
公开(公告)号：US06994516B2
公开(公告)日：2006-02-07
申请号：US10824469
申请日：2004-04-15
申请人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
发明人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
IPC分类号： F01D5/00
CPC分类号： F01D5/084 , F01D5/08 , Y10T29/49318
摘要： A turbine rotor can fix the heat resisting pipes provided in divided form per the disk member with simple structure for preventing wearing and damaging. The turbine rotor includes a coolant flow path formed through a plurality of disc shaped members respectively stacked across stacking planes in axial direction, a heat resisting pipe divided into a plurality of fractions adapted to be inserted into a portion of the coolant flow path defined in each disc shaped member, spot facing recesses each formed at opening portion of coolant flow path at the same side of the disc shaped member coaxially with the coolant flow path and having greater inner diameter than the opening portion, and ring shaped projecting portions formed at respective end portions of the fractions of the heat resisting pipe and engageable with respective spot facing recesses.

9. 发明授权

US06746204B2 Turbine rotor 有权
公开(公告)号：US06746204B2
公开(公告)日：2004-06-08
申请号：US10352898
申请日：2003-01-29
申请人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
发明人： Yasuo Takahashi , Shinya Marushima , Shinichi Higuchi , Tsuyoshi Takano
IPC分类号： F03D0000
CPC分类号： F01D5/084 , F01D5/08 , Y10T29/49318
摘要： A turbine rotor can fix the heat resisting pipes provided in divided form per the disk member with simple structure for preventing wearing and damaging. The turbine rotor includes a coolant flow path formed through a plurality of disc shaped members respectively stacked across stacking planes in axial direction, a heat resisting pipe divided into a plurality of fractions adapted to be inserted into a portion of the coolant flow path defined in each disc shaped member, spot facing recesses each formed at opening portion of coolant flow path at the same side of the disc shaped member coaxially with the coolant flow path and having greater inner diameter than the opening portion, and ring shaped projecting portions formed at respective end portions of the fractions of the heat resisting pipe and engageable with respective spot facing recesses.

10. 发明授权

US09217368B2 Gas turbine, exhaust diffuser, and method of modifying gas turbine plant 有权
标题翻译：燃气轮机，排气扩散器，以及改变燃气轮机设备的方法
公开(公告)号：US09217368B2
公开(公告)日：2015-12-22
申请号：US12981992
申请日：2010-12-30
申请人： Chihiro Myoren , Ryo Akiyama , Shinya Marushima
发明人： Chihiro Myoren , Ryo Akiyama , Shinya Marushima
IPC分类号： F01D25/30 , F01D1/02 , F02C6/18 , F02C3/10 , F22B1/18
CPC分类号： F02C6/18 , F01D1/02 , F01D25/30 , F02C3/10 , F05D2220/72 , F05D2240/12 , F22B1/1815 , Y02E20/16 , Y10T29/4932
摘要： A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressure turbine.
摘要翻译：一种修改燃气轮机设备的方法，该燃气轮机设备设置有具有用于压缩空气的压缩机的单轴燃气轮机，用于从由压缩机压缩的空气和燃料产生燃烧气体的燃烧器，以及单轴涡轮驱动由燃烧器产生的燃烧气体由压缩机共用的旋转轴线支撑，以及用于通过单轴涡轮机的驱动力产生电力的发电机，其中：单轴涡轮机被二轴换向，轴式燃气轮机，包括用于压缩空气的压缩机，用于从由压缩机压缩的空气产生燃烧气体的燃烧器和燃料，以及由燃烧器产生的燃烧气体驱动并由第一旋转轴线支撑的高压涡轮机以及由用于驱动高压涡轮机并由第二旋转轴线支撑的燃烧气体驱动的低压涡轮机，该低压涡轮机不同于轴为高压汽轮机。

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