专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06769259B2 Gas turbine having a cooling air system and a spray air system 失效
标题翻译：具有冷却空气系统和喷雾空气系统的燃气轮机
公开(公告)号：US06769259B2
公开(公告)日：2004-08-03
申请号：US10347797
申请日：2003-01-22
申请人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
发明人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
IPC分类号： F02C608
CPC分类号： F02C7/18 , F02C3/10 , F02C7/143 , F02C7/185 , F02C7/2365
摘要： A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.
摘要翻译：燃气轮机具有供给用于冷却燃气轮机的高温部分的空气的冷却空气系统和向燃烧器喷射燃料而供给空气的喷射空气系统，并且形成为使得由燃气轮机压缩的高压空气的一部分压缩机用作冷却空气系统和喷雾空气系统的空气，其中热交换器和增压压缩机布置在燃气轮机压缩机的压缩空气出口的下游，并且增压压缩机由由涡轮机轴驱动的压缩机和由涡轮机轴以外的驱动源驱动的压缩机，并且来自增压压缩机的加压空气用作冷却空气系统和喷雾空气系统的空气。

2. 发明申请

US20120275911A1 Gas Turbine Stator Vane 有权
标题翻译：燃气轮机定子叶片
公开(公告)号：US20120275911A1
公开(公告)日：2012-11-01
申请号：US13455612
申请日：2012-04-25
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/143 , F05D2240/10 , F05D2240/80 , F05D2250/184 , F05D2250/711 , F05D2250/712
摘要： A gas turbine stator vane is effective for suppressing a secondary flow in a region sandwiched between a suction surface side and a pressure surface side, as well as for suppressing augmentation of a horseshoe-shaped vortex occurring near a leading edge of the vane. The stator vane includes a vane profile portion having a pressure surface concaved to a chord line of the vane, and a suction surface convexed to the chord line; an outer-circumferential end wall positioned at an outer circumferential side of the vane profile portion; and an inner-circumferential end wall positioned at an inner circumferential side of the vane profile portion. An outer-circumferential end wall inner surface that is an inner-circumferential surface of the outer-circumferential end wall has an inward convexed shape and an outward convexed shape, at the suction surface side of the vane profile portion.
摘要翻译：燃气轮机定子叶片对于抑制夹在吸入面侧和压力面侧的区域中的二次流动以及用于抑制在叶片的前缘附近发生的马蹄形涡流的增大是有效的。定子叶片包括叶片轮廓部分，其具有凹陷到叶片的弦线的压力表面和凸起到弦线的吸力表面; 位于所述叶片轮廓部的外周侧的外周端壁; 以及位于叶片轮廓部的内周侧的内周端壁。作为外周端壁的内周面的外周端壁内表面在叶片型面部的吸附面侧具有向内凸的形状和向外的凸出的形状。

3. 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.

4. 发明授权

US06986256B2 Gas turbine having a cooling air system and a spray air system 失效
公开(公告)号：US06986256B2
公开(公告)日：2006-01-17
申请号：US10768159
申请日：2004-02-02
申请人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
发明人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
IPC分类号： F02C6/08 , F02C7/18
CPC分类号： F02C7/18 , F02C3/10 , F02C7/143 , F02C7/185 , F02C7/2365
摘要： A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.

5. 发明申请

US20050097898A1 Gas turbine unit and its cooling method 审中-公开
标题翻译：燃气轮机组及其冷却方式
公开(公告)号：US20050097898A1
公开(公告)日：2005-05-12
申请号：US10938511
申请日：2004-09-13
申请人： Kazunori Yamanaka , Masami Noda , Shinya Marushima , Satoshi Kondo
发明人： Kazunori Yamanaka , Masami Noda , Shinya Marushima , Satoshi Kondo
IPC分类号： F02C7/12 , F02C7/18
CPC分类号： F02C7/185
摘要： It is the object of the present invention to feed cooling air suitable for cooling the high-temperature part of the gas turbine. The present invention comprises a compressor, a combustor, and a turbine. Further, a turbine-cooling system to feed the gas from the compressor to the turbine is provided, and the turbine-cooling system comprises a heat exchanger to cool the gas compressed by the compressor, and a means for separating liquid from the gas cooled by the heat exchanger. Thus, according to the present invention, it becomes possible to feed cooling air suitable for cooling the high-temperature part of the gas turbine and to achieve higher reliability of the gas turbine unit.
摘要翻译：本发明的目的是提供适于冷却燃气轮机的高温部分的冷却空气。本发明包括压缩机，燃烧器和涡轮机。此外，提供了一种从压缩机将气体供给到涡轮机的涡轮机冷却系统，并且涡轮冷却系统包括用于冷却由压缩机压缩的气体的热交换器，以及用于将气体与由热交换器。因此，根据本发明，能够供给适于冷却燃气轮机的高温部的冷却空气，并且实现燃气轮机组的更高的可靠性。

6. 发明授权

US06393826B1 Gas turbine 失效
标题翻译：燃气轮机
公开(公告)号：US06393826B1
公开(公告)日：2002-05-28
申请号：US09643751
申请日：2000-08-23
申请人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
发明人： Kazunori Yamanaka , Satoshi Kondou , Masami Noda
IPC分类号： F02C608
CPC分类号： F02C7/18 , F02C3/10 , F02C7/143 , F02C7/185 , F02C7/2365
摘要： A gas turbine has a cooling air system supplying air for cooling a high temperature part of the gas turbine and a spray air system supplying air for spraying fuel into a combustor and is formed so that a part of high-pressure air compressed by a gas turbine compressor is used as air of the cooling air system and spray air system, wherein a heat exchanger and a boost compressor are arranged downstream of the outlet of compressed air of the gas turbine compressor, and the boost compressor is composed of a parallel connection of a compressor driven by the turbine shaft and ae compressor driven by a driven source other than the turbine shaft, and pressurized air from the boost compressor is used as air for the cooling air system and the spray air system.
摘要翻译：燃气轮机具有供给用于冷却燃气轮机的高温部分的空气的冷却空气系统和向燃烧器喷射燃料而供给空气的喷射空气系统，并且形成为使得由燃气轮机压缩的高压空气的一部分压缩机用作冷却空气系统和喷雾空气系统的空气，其中热交换器和增压压缩机布置在燃气轮机压缩机的压缩空气出口的下游，并且增压压缩机由由涡轮机轴驱动的压缩机和由涡轮机轴以外的驱动源驱动的压缩机，并且来自增压压缩机的加压空气用作冷却空气系统和喷雾空气系统的空气。

7. 发明授权

US09765628B2 Turbine rotor blade 有权
公开(公告)号：US09765628B2
公开(公告)日：2017-09-19
申请号：US13702557
申请日：2011-12-07
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F01D5/20 , F05D2260/202
摘要： A turbine rotor blade is provided that can reduce a total pressure loss at a blade cross-section on a tip side of the blade and suppress degradation in performance even if cooling air mixes in toward the blade. The rotor blade is mounted to a rotor to form a turbine blade row rotating in a stationary member that includes a platform forming a gas passage through which a mainstream gas flows and an airfoil extending from a gas passage plane in a radial direction vertical to the rotational axis of the rotor, the gas passage plane being a plane of the platform and forming the gas passage. A clearance between the tip-side end face, which is a leading end-side end face of the airfoil, and the stationary member facing the tip-side end face is smaller on the downstream side than on the upstream side.

8. 发明申请

US20150204196A1 Gas Turbine 有权
标题翻译：燃气轮机
公开(公告)号：US20150204196A1
公开(公告)日：2015-07-23
申请号：US14413826
申请日：2012-09-12
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D5/14 , F02C3/04
CPC分类号： F01D5/143 , F01D5/082 , F01D5/145 , F01D5/187 , F01D5/20 , F02C3/04 , F05D2240/301 , F05D2240/55
摘要： The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12d extending from a front edge 12a to a rear edge 12b, a pressure surface 12c opposing the negative pressure surface 12d and extending from the front edge 12a to the rear edge 12b, and a tip surface 13 surrounded by the top end of the negative pressure surface 12d and the top end of the pressure surface 12c, and an end wall section 10 connected to the bottom end of the negative pressure surface 12d and the bottom end of the pressure surface 12c, the rotor blade has a convex shape in positions constituting the negative pressure surface 12d side and the front edge 12a side of the end wall section 10, and the rotor blade has a concave shape in positions constituting the pressure surface 12c side and the front edge 12a side of the end wall section 10.
摘要翻译：本发明的目的在于，即使从转子叶片的端壁部的前端部混入冷却制冷剂，也能够抑制燃气轮机的转子叶片前端附近的二次电流涡流的发展。在包括由从前缘12a延伸到后边缘12b的负压面12d形成的翼形部12的燃气轮机转子叶片4中，与负压面12d相对并从前缘12a延伸到后缘12b和由负压面12d的顶端和压力表面12c的顶端包围的前端表面13以及连接到负压表面12d的底端的端壁部10和压力表面12c的底端，转子叶片在构成负压表面12d侧的位置和端壁部分10的前缘12a侧的位置具有凸形，并且转子叶片在构成压力的位置具有凹形表面12c侧和端壁部10的前缘12a侧。

9. 发明申请

US20090185896A1 GAS TURBINE AND GAS TURBINE COOLING METHOD 有权
标题翻译：气体涡轮机和气体涡轮冷却方法
公开(公告)号：US20090185896A1
公开(公告)日：2009-07-23
申请号：US12366085
申请日：2009-02-05
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： F01D25/12 , F01D9/04
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。

10. 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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式