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1. 发明授权

US09109461B2 Axial flow compressor, gas turbine system having the axial flow compressor and method of modifying the axial flow compressor 有权
标题翻译：轴流压缩机，具有轴流压缩机的燃气轮机系统和轴流式压缩机的改进方法
公开(公告)号：US09109461B2
公开(公告)日：2015-08-18
申请号：US13197947
申请日：2011-08-04
申请人： Yasuo Takahashi , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
发明人： Yasuo Takahashi , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
IPC分类号： F01D5/14 , F01D25/00 , F04D29/54
CPC分类号： F01D25/00 , F01D5/142 , F04D29/544 , F05D2230/50 , F05D2240/10
摘要： There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
摘要翻译：提供了一种轴流式压缩机，其由于燃气轮机的部分负载操作而提高了轴流式压缩机的最后一级定子叶片上的叶片负载的增加的可靠性。环形流路由安装有多个转子叶片的转子和安装有多个定子叶片的壳体形成，其中两个或更多个定子叶片设置在最后一个转子叶片的下游，转子叶片是设置在转子叶片在环形流路的流动方向上的最下游侧，设置在最上游侧的第一定子叶片上的叶片负荷设定为小于设置在第一定子叶片下游的第二定子叶片的叶片负载量行。

2. 发明申请

US20120070267A1 Axial Flow Compressor, Gas Turbine System Having the Axial Flow Compressor and Method of Modifying the Axial Flow Compressor 有权
标题翻译：轴流式压缩机，具有轴流式压缩机的燃气轮机系统及轴流压缩机修改方法
公开(公告)号：US20120070267A1
公开(公告)日：2012-03-22
申请号：US13197947
申请日：2011-08-04
申请人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
发明人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama , Ichiro Miyoshi
IPC分类号： F04D19/02 , F04D29/32 , F02C3/04 , F01D9/02
CPC分类号： F01D25/00 , F01D5/142 , F04D29/544 , F05D2230/50 , F05D2240/10
摘要： There is provided an axial flow compressor that improves reliability on an increase in a blade loading on a last-stage stator vane of the axial flow compressor due to a partial load operation of a gas turbine. An annular flow passage is formed by a rotor having multiple rotor blades fitted thereto and a casing having multiple stator vanes fitted thereto, two or more of the stator vanes are disposed downstream of a last-stage rotor blade that is the rotor blade disposed. at the most downstream side in a flow direction of the annular flow passage, a blade loading on a first stator vane disposed at the most upstream side is set to be smaller than a blade loading of a second stator vane disposed downstream of the first stator vane by one row.
摘要翻译：提供了一种轴流式压缩机，其由于燃气轮机的部分负载操作而提高了轴流式压缩机的最后一级定子叶片上的叶片负载的增加的可靠性。由安装有多个转子叶片的转子和安装有多个定子叶片的壳体形成环形流动通道，其中两个或更多个定子叶片设置在设置转子叶片的最后一个转子叶片的下游。在环形流路的流动方向的最下游侧，设置在最上游侧的第一定子叶片上的叶片的载荷被设定为小于设置在第一定子叶片下游的第二定子叶片的叶片负荷一行

3. 发明申请

US20120163965A1 Axial Compressor 审中-公开
标题翻译：轴压缩机
公开(公告)号：US20120163965A1
公开(公告)日：2012-06-28
申请号：US13336644
申请日：2011-12-23
申请人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama
发明人： Yasuo TAKAHASHI , Chihiro Myoren , Ryou Akiyama
IPC分类号： F01D9/04 , B23P6/00 , B23P15/00
CPC分类号： F04D29/544 , Y10T29/49238 , Y10T29/49245
摘要： When a gas turbine is operated with inlet guide vanes (IGVs) closed during part load operation or the like, the degradation of aerodynamic performance and of reliability may potentially occur since the load on rear stage side vanes of a compressor increases. An object of the present invention is to suppress the degradation of the aerodynamic performance and of reliability of an axial compressor.The axial compressor includes a rotor; a plurality of rotor blade rows installed on the rotor; a casing located outside of the rotor blade rows; a plurality of stator vane rows installed on the casing; and exit guide vanes installed on the downstream side of a final stage stator vane row among the stator vane rows. An incidence angle of a flow toward the final stage stator vane row is equal to or below a limit line of an incidence operating range.
摘要翻译：当在部分加载操作等期间在入口导向叶片（IGV）关闭的情况下操作燃气轮机时，由于压缩机的后级侧叶片上的负载增加，潜在的空气动力性能和可靠性的降低可能会发生。本发明的目的是抑制轴向压缩机的空气动力性能的劣化和可靠性的降低。轴向压缩机包括转子; 安装在转子上的多个转子叶片排; 壳体，位于转子叶片排的外侧; 安装在所述壳体上的多个定子叶片排; 以及安装在定子叶片排中的末级定子叶片排的下游侧的出口导向叶片。朝向末级定子叶片排的流的入射角等于或低于入射操作范围的极限线。

4. 发明申请

US20100293963A1 Two-Shaft Gas Turbine 审中-公开
标题翻译：双轴燃气轮机
公开(公告)号：US20100293963A1
公开(公告)日：2010-11-25
申请号：US12780002
申请日：2010-05-14
申请人： Chihiro Myoren , Ryou Akiyama
发明人： Chihiro Myoren , Ryou Akiyama
IPC分类号： F02C3/10 , F01D1/02
CPC分类号： F02C3/10 , F01D5/142 , F05D2220/321
摘要： On a two-shaft gas turbine, on at least one of an inner peripheral side or an outer peripheral side of a main flow passage, an outlet of a high-pressure turbine is lower than an inlet of a low-pressure turbine, an outer periphery of a flow channel that connects the outlet of the high-pressure turbine and the inlet of the low-pressure turbine includes a first casing shroud that is supported by a casing and located on an outer peripheral side of a final-stage rotor vane of the high-pressure turbine, and an initial-stage stator vane of the low-pressure turbine, and a connection position of the first casing shroud and the initial-stage stator vane of the low-pressure turbine is closer to the inlet of the initial-stage stator vane of the low-pressure turbine than the outlet of the final-stage rotor vane of the high-pressure turbine.
摘要翻译：在双轴燃气轮机上，在主流路的内周侧或外周侧的至少一方，高压涡轮机的出口低于低压涡轮机的入口，外侧连接高压涡轮机的出口和低压涡轮机的入口的流路的周边包括第一壳体护罩，其由壳体支撑并位于最终级转子叶片的外周侧高压涡轮机和低压涡轮机的初级定子叶片，并且低压涡轮机的第一壳体护罩和初级定子叶片的连接位置更接近初始状态的入口低压涡轮机的台阶定子叶片比高压涡轮机的末级转子叶片的出口。

5. 发明授权

US09303656B2 Axial compressor 有权
标题翻译：轴流压缩机
公开(公告)号：US09303656B2
公开(公告)日：2016-04-05
申请号：US13272635
申请日：2011-10-13
申请人： Yasuo Takahashi , Chihiro Myoren
发明人： Yasuo Takahashi , Chihiro Myoren
IPC分类号： F04D29/32 , F04D29/54
CPC分类号： F04D29/324 , F04D29/542 , F04D29/544 , F05B2240/123 , F05B2240/301 , Y10T29/49316
摘要： An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
摘要翻译：轴向压缩机包括附接到限定环形流动路径的壳体的内表面的多个定子叶片和附接到限定环形流动路径的旋转转子的多个转子叶片。在定子叶片的压力表面和定子叶片的吸力表面之间限定流动路径，叶片彼此周向相邻，或在转子叶片的压力表面和转子叶片的吸力表面之间，叶片彼此周向相邻。流路形成为在轴向弦长的50％的上游侧设置流路宽度最小的喉部。

6. 发明授权

US09279329B2 Transonic blade 有权
标题翻译：跨音速刀片
公开(公告)号：US09279329B2
公开(公告)日：2016-03-08
申请号：US13879084
申请日：2010-10-18
申请人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
发明人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
IPC分类号： F04D29/38 , F01D5/14 , F04D21/00 , F04D29/32
CPC分类号： F01D5/147 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F05D2210/30 , F05D2240/301 , F05D2240/302 , Y02T50/673
摘要： The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
摘要翻译：本发明提供一种跨音速刀片，其同时实现设计点的减震和在轴流式旋转机器中以跨音速或更高的流场工作的叶片的失速余量的改善。刀片的每个翼展位置处的横截面表面平行于将前缘与刀片的后缘连接的交错线移动。堆垛线向工作流体的上游侧移动。堆叠线将叶片横截面的各重心位置从翼面方向位置的连接到旋转机械的旋转轴或外周侧壳体的轮毂横截面的顶端横截面位于最远离轮毂横截面的翼展方向的位置上。

7. 发明申请

US20130259668A1 Transonic Blade 有权
标题翻译：跨音速刀片
公开(公告)号：US20130259668A1
公开(公告)日：2013-10-03
申请号：US13879084
申请日：2010-10-18
申请人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
发明人： Chihiro Myoren , Yasuo Takahashi , Shinya Marushima
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/141 , F04D21/00 , F04D29/324 , F04D29/384 , F05D2210/30 , F05D2240/301 , F05D2240/302 , Y02T50/673
摘要： The present invention provides a transonic blade that concurrently achieves reduction in shock loss at a design point and improvement in stall margin in blades operating in a flow field of transonic speed or higher in an axial-flow rotating machine. A cross-sectional surface at each of spanwise positions of the blade is shifted parallel to a stagger line connecting a leading edge with a trailing edge of the blade. A stacking line is shifted toward an upstream side of working fluid. The stacking line connects together respective gravity center positions of blade cross-sectional surfaces at spanwise positions in a range from a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine to a tip cross-sectional surface lying at a position most remote from the hub cross-sectional surface in a spanwise direction.
摘要翻译：本发明提供一种跨音速刀片，其同时实现设计点的减震和在轴流式旋转机器中以超音速或更高速度流动的叶片中的失速余量的改善。刀片的每个翼展位置处的横截面表面平行于将前缘与刀片的后缘连接的交错线移动。堆垛线向工作流体的上游侧移动。堆叠线将叶片横截面的各重心位置从翼面方向位置的连接到旋转机械的旋转轴或外周侧壳体的轮毂横截面的顶端横截面位于最远离轮毂横截面的翼展方向的位置上。

8. 发明授权

US08425185B2 Transonic blade 有权
标题翻译：跨音速刀片
公开(公告)号：US08425185B2
公开(公告)日：2013-04-23
申请号：US12707493
申请日：2010-02-17
申请人： Chihiro Myoren , Yasuo Takahashi
发明人： Chihiro Myoren , Yasuo Takahashi
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , Y02T50/673
摘要： A transonic blade is provided that operates in a flow field where flow has a transonic speed or higher in an axial-flow rotating machine and that concurrently achieves a reduction in shock loss and in the local stress of the blade. The transonic blade includes a hub cross-sectional surface joined to a rotating shaft or an outer circumferential side casing of a rotating machine; a tip cross-sectional surface located furthest from the hub cross-sectional surface in a spanwise direction which is a vertical direction of the rotating shaft; a leading edge located on an upstream side; and a trailing edge located on a downstream side. At least a part of a passing working fluid flow has a transonic speed or higher. A portion of a stacking line which is a line connecting together respective gravity centers of cross-sectional surfaces located from the hub cross-sectional surface to the tip cross-sectional surface is located on a downstream side of a stacking center in a flow direction of a working fluid main flow.
摘要翻译：提供了一种跨音速叶片，其操作在流场中，其中流动在轴流旋转机器中具有跨音速或更高速度，并且同时实现减震和叶片的局部应力。所述超音速叶片包括与旋转机械的旋转轴或外周侧壳体连接的轮毂横截面; 在所述旋转轴的垂直方向的翼展方向上离所述轮毂横截面最远的前端横截面; 位于上游侧的前缘; 以及位于下游侧的后缘。通过的工作流体流的至少一部分具有跨音速或更高速度。作为从轮毂截面面到前端截面的相互重叠的横截面重心连接的线的一部分，位于堆叠中心的流动方向的下游侧工作流体主流。

9. 发明申请

US20120093637A1 Axial Compressor 有权
标题翻译：轴压缩机
公开(公告)号：US20120093637A1
公开(公告)日：2012-04-19
申请号：US13272635
申请日：2011-10-13
申请人： Yasuo TAKAHASHI , Chihiro Myoren
发明人： Yasuo TAKAHASHI , Chihiro Myoren
IPC分类号： F04D19/00 , B21D53/78 , F04D29/54
CPC分类号： F04D29/324 , F04D29/542 , F04D29/544 , F05B2240/123 , F05B2240/301 , Y10T29/49316
摘要： An axial compressor includes a plurality of stator vanes attached to an inner surface of a casing defining an annular flow path and a plurality of rotor blades attached to a rotating rotor defining the annular flow path. A flow path is defined between a pressure surface of a stator vane and a suction surface of a stator vane, the vanes being circumferentially adjacent to each other, or between a pressure surface of a rotor blade and a suction surface of a rotor blade, the blades being circumferentially adjacent to each other. The flow path is formed so that a throat portion at which a flow path width is minimized is provided on the upstream side of 50% of an axial chord length.
摘要翻译：轴向压缩机包括附接到限定环形流动路径的壳体的内表面的多个定子叶片和附接到限定环形流动路径的旋转转子的多个转子叶片。在定子叶片的压力表面和定子叶片的吸力表面之间限定流动路径，叶片彼此周向相邻，或在转子叶片的压力表面和转子叶片的吸力表面之间，叶片彼此周向相邻。流路形成为在轴向弦长的50％的上游侧设置流路宽度最小的喉部。

10. 发明授权

US09217368B2 Gas turbine, exhaust diffuser, and method of modifying gas turbine plant 有权
标题翻译：燃气轮机，排气扩散器，以及改变燃气轮机设备的方法
公开(公告)号：US09217368B2
公开(公告)日：2015-12-22
申请号：US12981992
申请日：2010-12-30
申请人： Chihiro Myoren , Ryo Akiyama , Shinya Marushima
发明人： Chihiro Myoren , Ryo Akiyama , Shinya Marushima
IPC分类号： F01D25/30 , F01D1/02 , F02C6/18 , F02C3/10 , F22B1/18
CPC分类号： F02C6/18 , F01D1/02 , F01D25/30 , F02C3/10 , F05D2220/72 , F05D2240/12 , F22B1/1815 , Y02E20/16 , Y10T29/4932
摘要： A method of modifying a gas turbine plant which is provided with a one-shaft gas turbine having a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a one-shaft turbine driven by the combustion gas generated by the combustor and supported by a rotational axis common to the compressor, and an electric generator for generating electric power by driving force of the one-shaft turbine, wherein: the one-shaft turbine is replaced with a two-shaft gas turbine including a compressor for compressing air, a combustor for generating a combustion gas from the air compressed by the compressor and a fuel, and a high-pressure turbine driven by the combustion gas generated by the combustor and supported by a first rotational axis common to the compressor, and a low-pressure turbine driven by the combustion gas used to drive the high-pressure turbine and supported by a second rotational axis, which is different from the axis for the high-pressure turbine.
摘要翻译：一种修改燃气轮机设备的方法，该燃气轮机设备设置有具有用于压缩空气的压缩机的单轴燃气轮机，用于从由压缩机压缩的空气和燃料产生燃烧气体的燃烧器，以及单轴涡轮驱动由燃烧器产生的燃烧气体由压缩机共用的旋转轴线支撑，以及用于通过单轴涡轮机的驱动力产生电力的发电机，其中：单轴涡轮机被二轴换向，轴式燃气轮机，包括用于压缩空气的压缩机，用于从由压缩机压缩的空气产生燃烧气体的燃烧器和燃料，以及由燃烧器产生的燃烧气体驱动并由第一旋转轴线支撑的高压涡轮机以及由用于驱动高压涡轮机并由第二旋转轴线支撑的燃烧气体驱动的低压涡轮机，该低压涡轮机不同于轴为高压汽轮机。

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