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1. 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.

2. 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.

3. 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.

4. 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。

5. 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。

6. 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。

7. 发明授权

US06568192B2 Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades 有权
标题翻译：燃气轮机，燃气轮机装置和燃气轮机动叶片的制冷剂收集方法
公开(公告)号：US06568192B2
公开(公告)日：2003-05-27
申请号：US10138429
申请日：2002-05-06
申请人： Ryou Akiyama , Shinya Marushima , Manabu Matsumoto , Tsuyoshi Takano
发明人： Ryou Akiyama , Shinya Marushima , Manabu Matsumoto , Tsuyoshi Takano
IPC分类号： F02C716
CPC分类号： F02C7/12 , F01D5/081 , F01D5/187 , F05D2260/205
摘要： A turbine rotor includes a plurality of moving blades having cooling paths through which a refrigerant flows inside, a plurality of wheels having the moving blades mounted in the outer periphery thereof and at least one spacer member installed between the wheels. The spacer member has a plurality of flow paths through which a refrigerant flows after cooling the moving blades. The plurality of flow paths have flow paths interconnecting to the cooling paths in the moving blades on a first wheel adjacent the spacer member and interconnecting to a space formed on a side wall surface with which a second wheel adjacent the spacer member and the spacer member are in contact.
摘要翻译：涡轮转子包括具有制冷剂流过其中的冷却通道的多个活动叶片，具有安装在其外周中的移动叶片的多个车轮和安装在车轮之间的至少一个间隔件。间隔件具有多个流动路径，制冷剂在冷却动叶片之后流过该流路。所述多个流路具有与所述间隔件相邻的第一轮上的所述活动叶片中的冷却路径相互连接的流路，并且与形成在侧壁表面上的空间相互连接，与所述间隔件相邻的第二轮接触。

8. 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。

9. 发明授权

US06405538B1 Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades 有权
标题翻译：燃气轮机，燃气轮机装置和燃气轮机动叶片的制冷剂收集方法
公开(公告)号：US06405538B1
公开(公告)日：2002-06-18
申请号：US09644770
申请日：2000-08-24
申请人： Ryou Akiyama , Shinya Marushima , Manabu Matsumoto , Tsuyoshi Takano
发明人： Ryou Akiyama , Shinya Marushima , Manabu Matsumoto , Tsuyoshi Takano
IPC分类号： F02C716
CPC分类号： F02C7/12 , F01D5/081 , F01D5/187 , F05D2260/205
摘要： A gas turbine having a structure for collecting a refrigerant after cooling the moving blades, has a plurality of wheels having a plurality of moving blades including cooling paths in the outer periphery and a plurality of spacer members alternately arranged on the rotating axis. A plurality of flow paths through which a refrigerant flows after cooling the moving blades are provided in the spacer members. First flow paths interconnect the moving blades arranged on the wheels on the upstream side of gas flow to the downstream side of gas flow of the spacer members, and second flow paths interconnect the moving blades arranged on the wheels on the downstream side of gas flow to the upstream side of gas flow of the spacer members. The flow paths may be provided with bent parts in the neighborhood of the center of the space members in the axial direction or may be in a linear shape.
摘要翻译：具有用于在冷却动叶片之后收集制冷剂的结构的燃气轮机具有多个车轮，所述多个车轮具有包括外周部的冷却路径的多个动叶片和交替配置在旋转轴上的多个间隔件。在间隔件中设置有多个冷却流动叶片后制冷剂流过的流路。第一流动路径将布置在气流上游侧的轮上的动叶片与间隔件的气流的下游侧相互连接，第二流路将布置在气流下游侧的轮上的动叶相互连接间隔件的气流的上游侧。流动路径可以在轴向方向上在空间构件的中心附近设置弯曲部分，或者可以是直线形状。

10. 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.

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