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公开(公告)号：US07645119B2
公开(公告)日：2010-01-12
申请号：US11892375
申请日：2007-08-22
IPC分类号： F01D9/02
摘要： An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.
摘要翻译： 一种轴流涡轮机，其具有由涡轮喷嘴构成的台架和沿轴向流动方向配置的涡轮机转子叶片。 涡轮喷嘴的喷嘴叶片的两端部由隔膜内圈和隔膜外圈支撑，形成从上游侧到下游侧的直径扩大的流路。 在这种轴流式涡轮机中，由隔膜内圈和隔膜外圈支撑的喷嘴的端部处的后缘作为曲率弯曲到出口侧，并且后缘之间的中间部分形成为直的。
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公开(公告)号：US20090110550A1
公开(公告)日：2009-04-30
申请号：US12243642
申请日：2008-10-01
IPC分类号： F01D1/02
CPC分类号： F01D1/02 , F01D5/145 , F01D9/02 , F01D11/10 , Y10S415/914
摘要： An axial flow turbine stage structure has: an annular diaphragm inner ring; an annular diaphragm outer ring arranged radially outside and coaxially with the diaphragm inner ring and separated from the diaphragm inner ring by an annular flow path interposed between them; stationary blades arranged peripherally at intervals in the annular flow path and rigidly secured to the diaphragm inner ring and the diaphragm outer ring; and moving blades rigidly secured to the outer periphery of a rotatable rotor and arranged peripherally at intervals respectively at axially downstream sides of the stationary blades. Through holes are formed in the diaphragm outer ring so as to allow axial upstream side and axially downstream side of the stationary blades to communicate with each other.
摘要翻译： 轴流涡轮机级结构具有：环形隔膜内圈; 环形隔膜外环，其设置在隔膜内环的径向外侧并与隔膜内圈同轴，并通过插入其间的环形流路与隔膜内圈分离; 固定叶片在环形流动路径中间隔设置并刚性地固定到隔膜内环和隔膜外圈; 以及刚性地固定到可旋转转子的外周并且周向地间隔地设置在固定叶片的轴向下游侧的移动叶片。 在隔膜外圈中形成通孔，以使固定叶片的轴向上游侧和轴向下游侧彼此连通。
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公开(公告)号：US07300247B2
公开(公告)日：2007-11-27
申请号：US11392956
申请日：2006-03-30
IPC分类号： F01D9/02
摘要： An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.
摘要翻译： 一种轴流涡轮机，其具有由涡轮喷嘴构成的台架和沿轴向流动方向配置的涡轮机转子叶片。 涡轮喷嘴的喷嘴叶片的两端部由隔膜内圈和隔膜外圈支撑，形成从上游侧到下游侧的直径扩大的流路。 在这种轴流式涡轮机中，由隔膜内圈和隔膜外圈支撑的喷嘴的端部处的后缘作为曲率弯曲到出口侧，并且后缘之间的中间部分形成为直的。
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公开(公告)号：US08147180B2
公开(公告)日：2012-04-03
申请号：US12243642
申请日：2008-10-01
IPC分类号： F01D11/00
CPC分类号： F01D1/02 , F01D5/145 , F01D9/02 , F01D11/10 , Y10S415/914
摘要： An axial flow turbine stage structure has: an annular diaphragm inner ring; an annular diaphragm outer ring arranged radially outside and coaxially with the diaphragm inner ring and separated from the diaphragm inner ring by an annular flow path interposed between them; stationary blades arranged peripherally at intervals in the annular flow path and rigidly secured to the diaphragm inner ring and the diaphragm outer ring; and moving blades rigidly secured to the outer periphery of a rotatable rotor and arranged peripherally at intervals respectively at axially downstream sides of the stationary blades. Through holes are formed in the diaphragm outer ring so as to allow axial upstream side and axially downstream side of the stationary blades to communicate with each other.
摘要翻译： 轴流涡轮机级结构具有：环形隔膜内圈; 环形隔膜外环，其设置在隔膜内环的径向外侧并与隔膜内圈同轴，并通过插入其间的环形流路与隔膜内圈分离; 固定叶片在环形流动路径中间隔设置并刚性地固定到隔膜内环和隔膜外圈; 以及刚性地固定到可旋转转子的外周并且周向地间隔地设置在固定叶片的轴向下游侧的移动叶片。 在隔膜外圈中形成通孔，以使固定叶片的轴向上游侧和轴向下游侧彼此连通。
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公开(公告)号：US20080199310A1
公开(公告)日：2008-08-21
申请号：US11892375
申请日：2007-08-22
IPC分类号： F01D9/02
摘要： An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.
摘要翻译： 一种轴流涡轮机，其具有由涡轮喷嘴构成的台架和沿轴向流动方向配置的涡轮机转子叶片。 涡轮喷嘴的喷嘴叶片的两端部由隔膜内圈和隔膜外圈支撑，形成从上游侧到下游侧的直径扩大的流路。 在这种轴流式涡轮机中，由隔膜内圈和隔膜外圈支撑的喷嘴的端部处的后缘作为曲率弯曲到出口侧，并且后缘之间的中间部分形成为直的。
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公开(公告)号：US20070086891A1
公开(公告)日：2007-04-19
申请号：US11392956
申请日：2006-03-30
IPC分类号： F01D9/00
摘要： An axial flow turbine provided with a stage composed of a turbine nozzle and a turbine rotor blade arranged in an axial flow direction. Both end portions of a nozzle blade of the turbine nozzle are supported by a diaphragm inner ring and a diaphragm outer ring, and a flow passage is formed to have its diameter expanded from an upstream stage to a downstream stage. In such axial flow turbine, trailing edges at ends of the nozzle blade supported by the diaphragm inner ring and the diaphragm outer ring are curved as a curvature to an outlet side, and an intermediate portion between the trailing edges is formed to be straight.
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公开(公告)号：US08753087B2
公开(公告)日：2014-06-17
申请号：US12979004
申请日：2010-12-27
申请人： Naoki Shibukawa , Yoriharu Murata , Akihiro Onoda , Daisuke Nomura , Tomohiro Tejima , Osamu Furuya , Kenichi Imai
发明人： Naoki Shibukawa , Yoriharu Murata , Akihiro Onoda , Daisuke Nomura , Tomohiro Tejima , Osamu Furuya , Kenichi Imai
IPC分类号： F01D5/22
CPC分类号： F01D1/04 , F01D5/22 , F05D2220/31 , F05D2220/3215 , F05D2260/96
摘要： A turbine rotor assembly 10 comprises a turbine rotor and a plurality of moving blades 20 implanted in a circumferential direction of the rotor. A flow passage is formed between each of the moving blades 20 and a circumferentially adjacent moving blade 20. Each of the moving blades 20 comprises a suction side connecting member 22 protruded on a blade suction surface 21 and a pressure side connecting member 24 protruded on a blade pressure surface 23, wherein the suction side connecting member 22 of each of the moving blades 20 is configured to be connected with the pressure side connecting member 24 of the circumferentially adjacent moving blade 20 to form an intermediate connecting member 30 between the moving blade 20 and the circumferentially adjacent moving blade 20 during a rotation of the turbine rotor. A downstream side end edge 32 of the intermediate connecting member 30 is positioned at an upstream side of a throat S of the flow passage.
摘要翻译： 涡轮转子组件10包括涡轮转子和沿转子的圆周方向注入的多个活动叶片20。 在每个活动叶片20和周向相邻的活动叶片20之间形成有流动通道。每个活动叶片20包括突出在叶片吸入表面21上的吸力侧连接构件22和在叶片吸入表面21上突出的压力侧连接构件24。 叶片压力表面23，其中每个动叶片20的吸力侧连接构件22构造成与周向相邻的活动叶片20的压力侧连接构件24连接，以在动叶片20之间形成中间连接构件30 以及在涡轮机转子的旋转期间周向相邻的移动叶片20。 中间连接构件30的下游侧端缘32位于流路的喉部S的上游侧。
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公开(公告)号：US20110158810A1
公开(公告)日：2011-06-30
申请号：US12979004
申请日：2010-12-27
申请人： Naoki Shibukawa , Yoriharu Murata , Akihiro Onoda , Daisuke Nomura , Tomohiro Tejima , Osamu Furuya , Kenichi Imai
发明人： Naoki Shibukawa , Yoriharu Murata , Akihiro Onoda , Daisuke Nomura , Tomohiro Tejima , Osamu Furuya , Kenichi Imai
IPC分类号： F01D5/22
CPC分类号： F01D1/04 , F01D5/22 , F05D2220/31 , F05D2220/3215 , F05D2260/96
摘要： A turbine rotor assembly 10 comprises a turbine rotor and a plurality of moving blades 20 implanted in a circumferential direction of the rotor. A flow passage is formed between each of the moving blades 20 and a circumferentially adjacent moving blade 20. Each of the moving blades 20 comprises a suction side connecting member 22 protruded on a blade suction surface 21 and a pressure side connecting member 24 protruded on a blade pressure surface 23, wherein the suction side connecting member 22 of each of the moving blades 20 is configured to be connected with the pressure side connecting member 24 of the circumferentially adjacent moving blade 20 to form an intermediate connecting member 30 between the moving blade 20 and the circumferentially adjacent moving blade 20 during a rotation of the turbine rotor. A downstream side end edge 32 of the intermediate connecting member 30 is positioned at an upstream side of a throat S of the flow passage.
摘要翻译： 涡轮转子组件10包括涡轮转子和沿转子的圆周方向注入的多个活动叶片20。 在每个活动叶片20和周向相邻的活动叶片20之间形成有流动通道。每个活动叶片20包括突出在叶片吸入表面21上的吸力侧连接构件22和在叶片吸入表面21上突出的压力侧连接构件24。 叶片压力表面23，其中每个动叶片20的吸力侧连接构件22构造成与周向相邻的活动叶片20的压力侧连接构件24连接，以在动叶片20之间形成中间连接构件30 以及在涡轮机转子的旋转期间周向相邻的移动叶片20。 中间连接构件30的下游侧端缘32位于流路的喉部S的上游侧。
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公开(公告)号：US20120067045A1
公开(公告)日：2012-03-22
申请号：US13231287
申请日：2011-09-13
申请人： Hiroyuki KAWAGISHI , Akihiro Onoda , Tomohiro Tejima , Tomohiko Tsukuda , Asako Inomata , Naoki Shibukawa
发明人： Hiroyuki KAWAGISHI , Akihiro Onoda , Tomohiro Tejima , Tomohiko Tsukuda , Asako Inomata , Naoki Shibukawa
CPC分类号： F01K13/00
摘要： In one embodiment, a calculation method of moisture loss in a steam turbine calculates first a wetness fraction at the inlet and outlet of each of stationary blade cascades and rotor blade cascades. Subsequently, the moisture loss is classified into (1) supersaturation loss, (2) condensation loss, (3) acceleration loss, (4) braking loss, (5) capture loss and (6) pumping loss, and a loss for calculation of the moisture loss is selected from the above losses (1) to (6) according to the wetness fraction of steam at the inlet and outlet of each blade cascade. An amount of each selected loss is calculated, and an amount of moisture loss at each blade cascade is calculated.
摘要翻译： 在一个实施例中，蒸汽涡轮机中的水分流失的计算方法首先计算每个固定叶片级联和转子叶片级联的入口和出口处的湿度分数。 随后，水分损失分为（1）过饱和损失，（2）冷凝损失，（3）加速损失，（4）制动损失，（5）捕获损失和（6）泵送损失，计算损失 根据在每个叶片级联的入口和出口处的蒸汽的湿度分数，从上述损失（1）至（6）中选择水分损失。 计算每个选定损失的量，并计算每个叶片级联处的水分损失量。
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公开(公告)号：US08695345B2
公开(公告)日：2014-04-15
申请号：US13231287
申请日：2011-09-13
申请人： Hiroyuki Kawagishi , Akihiro Onoda , Tomohiro Tejima , Tomohiko Tsukuda , Asako Inomata , Naoki Shibukawa
发明人： Hiroyuki Kawagishi , Akihiro Onoda , Tomohiro Tejima , Tomohiko Tsukuda , Asako Inomata , Naoki Shibukawa
IPC分类号： F01K13/02
CPC分类号： F01K13/00
摘要： In one embodiment, a calculation method of moisture loss in a steam turbine calculates first a wetness fraction at the inlet and outlet of each of stationary blade cascades and rotor blade cascades. Subsequently, the moisture loss is classified into (1) supersaturation loss, (2) condensation loss, (3) acceleration loss, (4) braking loss, (5) capture loss and (6) pumping loss, and a loss for calculation of the moisture loss is selected from the above losses (1) to (6) according to the wetness fraction of steam at the inlet and outlet of each blade cascade. An amount of each selected loss is calculated, and an amount of moisture loss at each blade cascade is calculated.
摘要翻译： 在一个实施例中，蒸汽涡轮机中的水分流失的计算方法首先计算每个固定叶片级联和转子叶片级联的入口和出口处的湿度分数。 随后，水分损失分为（1）过饱和损失，（2）冷凝损失，（3）加速损失，（4）制动损失，（5）捕获损失和（6）泵送损失，计算损失 根据在每个叶片级联的入口和出口处的蒸汽的湿度分数，从上述损失（1）至（6）中选择水分损失。 计算每个选定损失的量，并计算每个叶片级联处的水分损失量。
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