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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. 发明授权

US4267220A Dust-controlling mat having good flame-proofness 失效
标题翻译：防尘垫具有良好的防火性能
公开(公告)号：US4267220A
公开(公告)日：1981-05-12
申请号：US110531
申请日：1980-01-08
申请人： Akira Yagi , Ichiro Miyoshi , Nobusue Nogami
发明人： Akira Yagi , Ichiro Miyoshi , Nobusue Nogami
IPC分类号： D01F6/48 , D01F6/50 , D06M14/02 , D06N7/00 , B32B3/02
CPC分类号： D06N7/0042 , D06M7/00 , D06M2200/40 , Y10S428/921 , Y10T428/23986 , Y10T428/23993
摘要： Disclosed is a dust-controlling mat comprising tufted pile yarns containing fibers composed of a grafting product or polymer blend of polyvinyl alcohol and polyvinyl chloride and a dust adsorbing agent retained in the tufted pile yarns in an amount of 1 to 40% by weight based on the tufted piled yarns. This dust-controlling mat has an excellent dust-controlling property and a highly improved flame-proofing property in combination.
摘要翻译：公开了一种防尘垫，其包括簇绒绒毛纱，其含有由聚乙烯醇和聚氯乙烯的接枝产物或聚合物共混物组成的纤维和保留在簇绒绒毛纱中的粉尘吸附剂，其量为1至40重量％，基于簇绒的纱线。该防尘垫具有优异的防尘性能和高度改进的防火性能。

4. 发明授权

US09765628B2 Turbine rotor blade 有权
公开(公告)号：US09765628B2
公开(公告)日：2017-09-19
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 , F01D5/20
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.

5. 发明申请

US20150204196A1 Gas Turbine 有权
标题翻译：燃气轮机
公开(公告)号：US20150204196A1
公开(公告)日：2015-07-23
申请号：US14413826
申请日：2012-09-12
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D5/14 , F02C3/04
CPC分类号： F01D5/143 , F01D5/082 , F01D5/145 , F01D5/187 , F01D5/20 , F02C3/04 , F05D2240/301 , F05D2240/55
摘要： The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12d extending from a front edge 12a to a rear edge 12b, a pressure surface 12c opposing the negative pressure surface 12d and extending from the front edge 12a to the rear edge 12b, and a tip surface 13 surrounded by the top end of the negative pressure surface 12d and the top end of the pressure surface 12c, and an end wall section 10 connected to the bottom end of the negative pressure surface 12d and the bottom end of the pressure surface 12c, the rotor blade has a convex shape in positions constituting the negative pressure surface 12d side and the front edge 12a side of the end wall section 10, and the rotor blade has a concave shape in positions constituting the pressure surface 12c side and the front edge 12a side of the end wall section 10.
摘要翻译：本发明的目的在于，即使从转子叶片的端壁部的前端部混入冷却制冷剂，也能够抑制燃气轮机的转子叶片前端附近的二次电流涡流的发展。在包括由从前缘12a延伸到后边缘12b的负压面12d形成的翼形部12的燃气轮机转子叶片4中，与负压面12d相对并从前缘12a延伸到后缘12b和由负压面12d的顶端和压力表面12c的顶端包围的前端表面13以及连接到负压表面12d的底端的端壁部10和压力表面12c的底端，转子叶片在构成负压表面12d侧的位置和端壁部分10的前缘12a侧的位置具有凸形，并且转子叶片在构成压力的位置具有凹形表面12c侧和端壁部10的前缘12a侧。

6. 发明申请

US20120275911A1 Gas Turbine Stator Vane 有权
标题翻译：燃气轮机定子叶片
公开(公告)号：US20120275911A1
公开(公告)日：2012-11-01
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
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。

7. 发明授权

US07452709B2 Method of screening prion disease infection factor 失效
标题翻译：筛选朊病毒感染因子的方法
公开(公告)号：US07452709B2
公开(公告)日：2008-11-18
申请号：US10470848
申请日：2002-01-31
申请人： Tetsuyuki Kitamoto , Ichiro Miyoshi , Shirou Mohri
发明人： Tetsuyuki Kitamoto , Ichiro Miyoshi , Shirou Mohri
IPC分类号： C12N7/00 , C12N15/82
CPC分类号： C07K14/47 , A01K2217/05 , A01K2217/075 , G01N33/6896 , G01N2333/4709 , G01N2500/00 , G01N2800/2828
摘要： Early detection of infectious agents of human prion diseases such as CJD by using an animal model, etc. is needed in order to rapidly determine prion infections in pharmaceuticals such as blood products, foods, or cosmetics. This invention provides a screening method for infectious agents of human or non-human prion diseases in samples, which employs, as an indication, the deposition of the aberrant prion protein in the follicular dendritic cell (FDC) of a non-human animal.
摘要翻译：需要通过使用动物模型等早期检测人类朊病毒疾病如CJD的感染因子，以便迅速确定药品如血液制品，食品或化妆品中的朊病毒感染。本发明提供了一种用于样品中人或非人朊病毒疾病感染性试剂的筛选方法，该方法将异常朊病毒蛋白沉积在非人动物的滤泡树突状细胞（FDC）中。

8. 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。

9. 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。

10. 发明授权

US10012087B2 Gas turbine including a contoured end wall section of a rotor blade 有权
公开(公告)号：US10012087B2
公开(公告)日：2018-07-03
申请号：US14413826
申请日：2012-09-12
申请人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
发明人： Ichiro Miyoshi , Shinichi Higuchi , Masami Noda
IPC分类号： F01D5/14 , F02C3/04 , F01D5/08 , F01D5/18 , F01D5/20
CPC分类号： F01D5/143 , F01D5/082 , F01D5/145 , F01D5/187 , F01D5/20 , F02C3/04 , F05D2240/301 , F05D2240/55
摘要： The object of the invention is to suppress development of a secondary current whirl in the vicinity of a rotor blade front edge of a gas turbine even when a cooling refrigerant is mixed in from the front edge of an end wall section of the rotor blade. In a gas turbine rotor blade 4 including a wing shape section 12 formed of a negative pressure surface 12d extending from a front edge 12a to a rear edge 12b, a pressure surface 12c opposing the negative pressure surface 12d and extending from the front edge 12a to the rear edge 12b, and a tip surface 13 surrounded by the top end of the negative pressure surface 12d and the top end of the pressure surface 12c, and an end wall section 10 connected to the bottom end of the negative pressure surface 12d and the bottom end of the pressure surface 12c, the rotor blade has a convex shape in positions constituting the negative pressure surface 12d side and the front edge 12a side of the end wall section 10, and the rotor blade has a concave shape in positions constituting the pressure surface 12c side and the front edge 12a side of the end wall section 10.

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