公开(公告)号：US08277192B2

公开(公告)日：2012-10-02

申请号：US12018521

申请日：2008-01-23

申请人： Nobuaki Kizuka ,  Hidetaro Murata ,  Hidetoshi Kuroki ,  Kenji Nanataki

发明人： Nobuaki Kizuka ,  Hidetaro Murata ,  Hidetoshi Kuroki ,  Kenji Nanataki

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F05D2220/3212 ,  F05D2240/301 ,  F05D2250/74 ,  Y02T50/673

摘要： An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+−.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.

摘要翻译： 叶片轮廓形成为使得叶片横截面的叶片间横截面与出口喉部宽度的叶片间通道宽度以无量纲方式表示的通道宽度比从叶片入口朝向叶片出口基本单调地减小。 叶片在与翼型轮廓部分的任何表面位置垂直的方向上的外壳中具有在±2.0mm范围内的叶片翼型件形状。 机翼轮廓部分具有以笛卡尔坐标表示的参考翼型轮廓，其中Z是表示来自翼型轮廓部分的根部的截面高度的距离。 在各部分Z处由X和Y表示的轮廓在叶片高度方向上彼此平滑地连接以形成翼型轮廓部分的完整形状。

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.

公开(公告)号：US20100180604A1

公开(公告)日：2010-07-22

申请号：US12687228

申请日：2010-01-14

申请人： Ryo KAWAI ,  Hidetaro MURATA ,  Takeo SAITO ,  Nobuaki KIZUKA ,  Kenji NANATAKI

发明人： Ryo KAWAI ,  Hidetaro MURATA ,  Takeo SAITO ,  Nobuaki KIZUKA ,  Kenji NANATAKI

IPC分类号： F02C7/26 ,  F02C7/22

CPC分类号： F23R3/34 ,  F02C7/26 ,  F02C9/34 ,  F23N5/184 ,  F23N2037/02 ,  F23N2037/04 ,  F23N2041/20

摘要： A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

摘要翻译： 双轴燃气轮机能够启动预混燃烧而不熄灭火焰。 双轴燃气轮机包括燃烧器和气体发生器控制器。 燃烧器具有预混合燃烧器，该预混燃烧器包括要单独进行预混合燃烧的燃烧区域。 气体发生器控制器控制燃烧器。 在燃烧器中开始预混燃烧的方法中，气体发生器控制器基于燃料空气比选择要进行预混合燃烧的燃烧区域中的至少一个，并且开始预混燃烧 所选择的燃烧区域或分别在所选择的燃烧区域中。 此外，随着燃料 - 空气比的增加，控制器增加了进行预混合燃烧的所选择的区域的数量。

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。

公开(公告)号：US20110167833A1

公开(公告)日：2011-07-14

申请号：US13069022

申请日：2011-03-22

申请人： Ryo KAWAI ,  Hidetaro MURATA ,  Takeo SAITO ,  Nobuaki KIZUKA ,  Kenji NANATAKI

发明人： Ryo KAWAI ,  Hidetaro MURATA ,  Takeo SAITO ,  Nobuaki KIZUKA ,  Kenji NANATAKI

IPC分类号： F02C9/26

CPC分类号： F23R3/34 ,  F02C7/26 ,  F02C9/34 ,  F23N5/184 ,  F23N2037/02 ,  F23N2037/04 ,  F23N2041/20

摘要： A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

摘要翻译： 双轴燃气轮机能够启动预混燃烧而不熄灭火焰。 双轴燃气轮机包括燃烧器和气体发生器控制器。 燃烧器具有预混合燃烧器，该预混燃烧器包括要单独进行预混合燃烧的燃烧区域。 气体发生器控制器控制燃烧器。 在燃烧器中开始预混燃烧的方法中，气体发生器控制器基于燃料空气比选择要进行预混合燃烧的燃烧区域中的至少一个，并且开始预混燃烧 所选择的燃烧区域或分别在所选择的燃烧区域中。 此外，随着燃料 - 空气比的增加，控制器增加了进行预混合燃烧的所选择的区域的数量。

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。

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。

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.

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。

公开(公告)号：US08499541B2

公开(公告)日：2013-08-06

申请号：US13069022

申请日：2011-03-22

申请人： Ryo Kawai ,  Hidetaro Murata ,  Takeo Saito ,  Nobuaki Kizuka ,  Kenji Nanataki

发明人： Ryo Kawai ,  Hidetaro Murata ,  Takeo Saito ,  Nobuaki Kizuka ,  Kenji Nanataki

IPC分类号： F02C9/26

CPC分类号： F23R3/34 ,  F02C7/26 ,  F02C9/34 ,  F23N5/184 ,  F23N2037/02 ,  F23N2037/04 ,  F23N2041/20

摘要： A two-shaft gas turbine is capable of starting premixed combustion without extinguishing a flame. The two-shaft gas turbine includes a combustor and a gas generator controller. The combustor has a premix burner that includes combustion regions in which premixed combustion is to be carried out individually. The gas generator controller controls the combustor. In a method for starting the premixed combustion in the combustor, the gas generator controller selects at least one of the combustion regions in which the premixed combustion is to be carried out, on the basis of a fuel-air ratio, and starts premix combustion in the selected combustion region or separately in each of the selected combustion regions. Further, as the fuel-air ratio is increased, the controller increases the number of the selected region in which the premixed combustion is carried out.

摘要翻译： 双轴燃气轮机能够启动预混燃烧而不熄灭火焰。 双轴燃气轮机包括燃烧器和气体发生器控制器。 燃烧器具有预混合燃烧器，该预混燃烧器包括要单独进行预混合燃烧的燃烧区域。 气体发生器控制器控制燃烧器。 在燃烧器中开始预混燃烧的方法中，气体发生器控制器基于燃料空气比选择要进行预混合燃烧的燃烧区域中的至少一个，并且开始预混燃烧 所选择的燃烧区域或分别在所选择的燃烧区域中。 此外，随着燃料 - 空气比的增加，控制器增加了进行预混合燃烧的所选择的区域的数量。