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21. 发明授权

US06530229B2 Gas turbine having a cooling air system and a spray air system 失效
公开(公告)号：US06530229B2
公开(公告)日：2003-03-11
申请号：US10107400
申请日：2002-03-28
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.

22. 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。

23. 发明授权

US5393198A Gas turbine and gas turbine blade 失效
标题翻译：燃气轮机和燃气轮机叶片
公开(公告)号：US5393198A
公开(公告)日：1995-02-28
申请号：US120474
申请日：1993-09-14
申请人： Masami Noda , Takashi Ikeguchi , Shunichi Anzai , Kazuhiko Kawaike , Isao Takehara
发明人： Masami Noda , Takashi Ikeguchi , Shunichi Anzai , Kazuhiko Kawaike , Isao Takehara
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A blade for a gas turbine has a leading edge portion which has an arc-shaped cross-section, and a maximum thickness portion of the blade is located within this arc. With this blade configuration, an abrupt acceleration of hot gas at the leading edge portion of the blade is restrained, so that the velocity of the hot gas at the blade surface can be made low. Therefore, the heat transfer coefficient from the hot gas to the blade wall is lowered, so that the amount of cooling air required to be passed through the interior of the blade can be reduced.
摘要翻译：用于燃气轮机的叶片具有具有弧形横截面的前缘部分，并且叶片的最大厚度部分位于该弧形内。利用该叶片构造，能够抑制叶片的前端部的热气的突然加速，能够使叶片表面的热气的速度变低。因此，从热气体到叶片壁的传热系数降低，从而可以减少要通过叶片内部的冷却空气量。

24. 发明授权

US5100293A Turbine blade 失效
标题翻译：涡轮叶片
公开(公告)号：US5100293A
公开(公告)日：1992-03-31
申请号：US573798
申请日：1990-08-28
申请人： Shunichi Anzai , Kazuhiko Kawaike , Takashi Ikeguchi , Masami Noda , Tetsuo Sasada , Isao Takehara , Haruo Urushidani
发明人： Shunichi Anzai , Kazuhiko Kawaike , Takashi Ikeguchi , Masami Noda , Tetsuo Sasada , Isao Takehara , Haruo Urushidani
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F01D5/186 , F05D2260/201
摘要： A cooling structure for a turbine blade. Comprising a hollow-structured main body and a cooling medium discharging device located in the inner cavity of the hollow-structured main body and formed to discharge a cooling medium from the surface thereof, so that the cooling medium discharged from the cooling medium discharging device impinges against the inner surface of the main body to remove the heat from the same. The turbine blade further includes a projection formed on the inner surface of the leading edge of the main body, extending along the spanwise direction of the blade, and the cooling medium discharging device is formed to allow at least part of the cooling medium to directly impinge against proximal portions of the projection. With this arrangement, a turbine blade is provided which allows a small amount of cooling air to cool the turbine blade and its leading edge in particular with great effectiveness.

25. 发明授权

US09334745B2 Gas turbine stator vane 有权
标题翻译：燃气轮机定子叶片
公开(公告)号：US09334745B2
公开(公告)日：2016-05-10
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 , F01D5/14
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。

26. 发明申请

US20140294557A1 Turbine Rotor Blade 有权
标题翻译：涡轮转子叶片
公开(公告)号：US20140294557A1
公开(公告)日：2014-10-02
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
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.
摘要翻译：提供了一种涡轮转子叶片，其可以降低叶片的叶片横截面处的总压力损失，并且即使冷却空气朝向叶片混合也能够降低性能的劣化。转子叶片安装到转子上以形成在固定构件中旋转的涡轮叶片排，该固定构件包括形成主流气体流过的气体通道的平台和从气体通道平面沿垂直于旋转的径向延伸的翼型转子的轴线，气体通道平面是平台的平面并形成气体通道。作为翼型的前端侧端面的前端侧端面与面向前端侧端面的固定构件之间的间隙在下游侧比在上游侧小。

27. 发明授权

US07950897B2 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：US07950897B2
公开(公告)日：2011-05-31
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： F04D27/00
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.
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。

28. 发明申请

US20090196738A1 GAS TURBINE AND GAS TURBINE COOLING METHOD 有权
公开(公告)号：US20090196738A1
公开(公告)日：2009-08-06
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： F01D5/14 , F01D5/02 , F01D5/30
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.

29. 发明授权

US07373773B2 Gas turbine installation, cooling air supplying method and method of modifying a gas turbine installation 有权
标题翻译：燃气轮机安装，冷却空气供应方法和修改燃气轮机装置的方法
公开(公告)号：US07373773B2
公开(公告)日：2008-05-20
申请号：US10916396
申请日：2004-08-12
申请人： Masami Noda
发明人： Masami Noda
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F01D5/081 , F01D25/12 , F01D25/14 , Y02T50/676
摘要： The invention provides a gas turbine installation, a cooling air supplying method, a method of modifying a gas turbine installation, which can reduce the amount of compressed air extracted for cooling of an exhaust plenum and which can increase energy efficiency. The gas turbine installation comprises an exhaust plenum comprising an exhaust casing connected to the downstream side of a turbine and made up of an outer casing and an inner casing, and an exhaust diffuser made up of an outer diffuser and an inner diffuser, which are disposed between the outer casing and the inner casing; a first cooling system for introducing, from the outer peripheral side of the outer diffuser, cooling air for cooling the exhaust plenum; and a second cooling system for introducing, from the inner peripheral side of the inner diffuser, cooling air for cooling the exhaust plenum.
摘要翻译：本发明提供了一种燃气轮机装置，冷却空气供给方法，改进燃气轮机装置的方法，该方法可以减少抽出用于冷却排气室的压缩空气的量并且可以提高能量效率。燃气轮机装置包括排气室，该排气室包括连接到涡轮的下游侧并由外壳和内壳构成的排气罩，以及由外扩散器和内扩散器构成的排气扩散器，在外壳和内壳之间; 第一冷却系统，用于从外扩散器的外周侧引入用于冷却排气室的冷却空气; 以及第二冷却系统，用于从内扩散器的内周侧引入用于冷却排气室的冷却空气。

30. 发明授权

US07029236B2 Closed circuit blade-cooled turbine 有权
标题翻译：闭路叶片风机
公开(公告)号：US07029236B2
公开(公告)日：2006-04-18
申请号：US10793771
申请日：2004-03-08
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： F01D5/08
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. The holes in the radial direction and the cooling air supply holes are interconnected and supply members covering the connections are installed. The cooling air after cooling the second stage moving blades is introduced into collection holes formed in the outer periphery of the spacer via the cooling air collection holes. The cooling air collection holes and collection holes are interconnected and collection members covering the connection are installed. 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 thee respective path of the first stage moving blades, a minimum sectional member is incorporated into the supply member.
摘要翻译：在闭路动叶片冷却式涡轮机中，形成在第二级轮的外周的径向的孔被引导到第二级动叶片的冷却空气供给孔。径向孔和冷却空气供应孔互相连接，并且安装覆盖连接的供应构件。冷却第二级活动叶片后的冷却空气通过冷却空气收集孔被引入形成在间隔件外周的收集孔中。连接冷却空气收集孔和收集孔，并安装覆盖连接的收集构件。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之和，将最小截面构件并入供应构件。

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