公开(公告)号：US20070200351A1

公开(公告)日：2007-08-30

申请号：US11627624

申请日：2007-01-26

申请人： Masakazu Miyagi ,  Tetsuo Sasada ,  Isao Takehara ,  Hidetaro Murata

发明人： Masakazu Miyagi ,  Tetsuo Sasada ,  Isao Takehara ,  Hidetaro Murata

IPC分类号： F01D15/10 ,  H02P9/04

CPC分类号： F01K13/006 ,  F01D15/10 ,  F01K13/00 ,  F05D2220/766

摘要： To provide a plant facility which requires no transmission such as reduction gear and speed up gear, thus increasing the plant efficiency. The plant facility has a turbine which rotates at a frequency higher than the electrical power supply frequency, a generator which is directly connected to the turbine and rotates at the same rotating speed with that of the turbine, and an electrical motor which is directly connected to a load apparatus and driven by electricity at a frequency higher than the electrical power supply frequency generated from the generator. The load apparatus is driven at the same rotating speed with that of the electrical motor.

摘要翻译： 提供不需要传动的工厂设备，例如减速齿轮和加速齿轮，从而提高设备效率。 工厂设备具有以比电源频率高的频率旋转的涡轮机，直接连接到涡轮机并以与涡轮机相同的转速旋转的发电机，以及直接连接到 负载装置，并且以比由发电机产生的电力供给频率高的频率驱动电力。 负载装置以与电动机相同的转速驱动。

公开(公告)号：US06568167B2

公开(公告)日：2003-05-27

申请号：US10244461

申请日：2002-09-17

申请人： Nobuyuki Horii ,  Isao Takehara ,  Hidetaro Murata ,  Motoaki Utamura ,  Takaaki Kuwahara ,  Tetsuo Sasada ,  Fumiyuki Hirose ,  Yasuhiro Katoh

发明人： Nobuyuki Horii ,  Isao Takehara ,  Hidetaro Murata ,  Motoaki Utamura ,  Takaaki Kuwahara ,  Tetsuo Sasada ,  Fumiyuki Hirose ,  Yasuhiro Katoh

IPC分类号： F02C900

CPC分类号： F02C7/1435 ,  Y02E20/16

摘要： A gas turbine comprises a compressor for compressing a gas supplied therein and discharging the compressed gas, a combustor in which the discharged gas from the compressor and a fuel are combusted, a turbine to be driven by a combustion gas from the combustor, and a water injection unit which injects water into the gas to be supplied to the compressor, thereby lowering the temperature of the gas to be introduced into the compressor to a temperature lower than the atmospheric temperature, and causing water droplets having been injected in the gas and within the compressor to be vaporized while flowing down therein, wherein the quantity of water spray injection is controlled while monitoring operational conditions of the gas turbine.

摘要翻译： 燃气轮机包括用于压缩其中供应的气体并排出压缩气体的压缩机，其中来自压缩机和燃料的排放气体燃烧的燃烧器，被来自燃烧器的燃烧气体驱动的涡轮机和水 注入单元，其将水注入到要供应给压缩机的气体中，从而将要引入压缩机的气体的温度降低至低于大气温度的温度，并且使已经注入到气体中的水滴和 压缩机在其中向下流动的同时蒸发，其中在监测燃气轮机的运行状况的同时控制喷水量。

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：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：US20100005808A1

公开(公告)日：2010-01-14

申请号：US12493351

申请日：2009-06-29

申请人： Kenji NANATAKI ,  Nozomi SAITO ,  Hidetaro MURATA

发明人： Kenji NANATAKI ,  Nozomi SAITO ,  Hidetaro MURATA

IPC分类号： F02C9/00 ,  F02C1/00

CPC分类号： F02C9/20 ,  F02C3/10 ,  F02C9/54 ,  F05D2260/85 ,  F05D2260/96 ,  F05D2270/024 ,  F05D2270/101 ,  F05D2270/304

摘要： A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively usable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

摘要翻译： 具有包括压缩机7，燃烧器8和高压汽轮机9的气体发生器2的双轴燃气轮机1构成为能够选择性地用于控制第一控制模式和第二控制模式 气体发生器。 此外，在第一控制模式中，压缩机中的IGV角度根据气体发生器的校正轴转速被控制，在第二控制模式中，控制IGV角度以保持恒定的气体发生器轴旋转 速度。 此外，第一控制模式用于在固定或较低负载条件下启动，停止和操作涡轮机，并且第二控制模式在除了施加第一控制模式的操作状态之外使用。

公开(公告)号：US06779332B2

公开(公告)日：2004-08-24

申请号：US10704842

申请日：2003-11-12

申请人： Nobuyuki Horii ,  Isao Takehara ,  Hidetaro Murata ,  Motoaki Utamura ,  Takaaki Kuwahara ,  Tetsuo Sasada ,  Fumiyuki Hirose ,  Yasuhiro Katoh

发明人： Nobuyuki Horii ,  Isao Takehara ,  Hidetaro Murata ,  Motoaki Utamura ,  Takaaki Kuwahara ,  Tetsuo Sasada ,  Fumiyuki Hirose ,  Yasuhiro Katoh

IPC分类号： F02G300

CPC分类号： F02C7/1435 ,  Y02E20/16

摘要： A gas turbine comprises a compressor for compressing a gas supplied therein and discharging the compressed gas, a combustor in which the discharged gas from the compressor and a fuel are combusted, a turbine to be driven by a combustion gas from the combustor, and a water injection unit which injects water into the gas to be supplied to the compressor, thereby lowering the temperature of the gas to be introduced into the compressor to a temperature lower than the atmospheric temperature, and causing water droplets having been injected in the gas and within the compressor to be vaporized while flowing down therein, wherein the quantity of water spray injection is controlled while monitoring operational conditions of the gas turbine.

摘要翻译： 燃气轮机包括用于压缩其中供应的气体并排出压缩气体的压缩机，其中来自压缩机和燃料的排放气体燃烧的燃烧器，被来自燃烧器的燃烧气体驱动的涡轮机和水 注入单元，其将水注入到要供应给压缩机的气体中，从而将要引入压缩机的气体的温度降低至低于大气温度的温度，并且使已经注入到气体中的水滴和 压缩机在其中向下流动的同时蒸发，其中在监测燃气轮机的运行状况的同时控制喷水量。

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。

公开(公告)号：US20130084162A1

公开(公告)日：2013-04-04

申请号：US13604729

申请日：2012-09-06

申请人： Atsushi SANO ,  Hidetoshi Kuroki ,  Hironori Tsukidate ,  Hidetaro Murata ,  Hayato Maekawa

发明人： Atsushi SANO ,  Hidetoshi Kuroki ,  Hironori Tsukidate ,  Hidetaro Murata ,  Hayato Maekawa

IPC分类号： F01D25/14

CPC分类号： F01D11/24 ,  F05D2260/201

摘要： A gas turbine is provided that can suppress an increase in the supplied amount of cooling air in clearance adjustment through casing cooling.The gas turbine 101 includes a turbine casing 19 enclosing a turbine shaft 105, the turbine casing 19 including a cooling air header 21 and a cooling passage 24; and an exhaust diffuser 113 connected to the exhaust side of the casing 19, the exhaust diffuser 113 including an exhaust diffuser cooling passage 26. A plate 22 formed with a plurality of impingement cooling holes 28 is installed inside the cooling air header, and a route is formed which allows cooling air introduced from the impingement cooling holes to flow from the casing cooling passage to the diffuser cooling passage.

摘要翻译： 提供一种能够通过套管冷却来抑制间隙调整中的冷却空气的供给量的增加的燃气轮机。 燃气轮机101包括包围涡轮机轴105的涡轮壳体19，涡轮壳体19包括冷却空气集管21和冷却通道24; 以及连接到壳体19的排气侧的排气扩散器113，排气扩散器113包括排气扩散器冷却通道26.形成有多个冲击冷却孔28的板22安装在冷却空气集管内， 被形成为允许从冲击冷却孔引入的冷却空气从壳体冷却通道流向扩散器冷却通道。

公开(公告)号：US20130064670A1

公开(公告)日：2013-03-14

申请号：US13601426

申请日：2012-08-31

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： F01D5/00 ,  F01D5/30 ,  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。 叶片在与翼型件部分的任何表面位置垂直的方向上的外壳内具有±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：US20110126547A1

公开(公告)日：2011-06-02

申请号：US12980120

申请日：2010-12-28

申请人： Kenji NANATAKI ,  Nozomi SAITO ,  Hidetaro MURATA

发明人： Kenji NANATAKI ,  Nozomi SAITO ,  Hidetaro MURATA

IPC分类号： F02C9/00

CPC分类号： F02C9/20 ,  F02C3/10 ,  F02C9/54 ,  F05D2260/85 ,  F05D2260/96 ,  F05D2270/024 ,  F05D2270/101 ,  F05D2270/304

摘要： A twin-shaft gas turbine 1, which has a gas generator 2 including a compressor 7, a combustor 8, and a high-pressure turbine 9, is configured to make a first control mode and a second control mode selectively useable for control of the gas generator. In addition, in the first control mode, an IGV angle in the compressor is controlled in accordance with a corrected shaft rotation speed of the gas generator, and in the second control mode, the IGV angle is controlled to maintain a constant gas generator shaft rotation speed. Furthermore, the first control mode is used to start, to stop, and to operate the turbine under fixed or lower load conditions, and that the second control mode is used under operational states other than those to which the first control mode is applied.

摘要翻译： 具有包括压缩机7，燃烧器8和高压汽轮机9的气体发生器2的双轴燃气轮机1被构造成能够选择性地用于控制第一控制模式和第二控制模式 气体发生器。 此外，在第一控制模式中，压缩机中的IGV角度根据气体发生器的校正轴转速被控制，在第二控制模式中，控制IGV角度以保持恒定的气体发生器轴旋转 速度。 此外，第一控制模式用于在固定或较低负载条件下启动，停止和操作涡轮机，并且第二控制模式在除了施加第一控制模式的操作状态之外使用。