公开(公告)号：US08845295B2

公开(公告)日：2014-09-30

申请号：US12018556

申请日：2008-01-23

申请人： Yutaka Yamashita ,  Shigeki Senoo ,  Eiji Saito ,  Takeshi Kudo ,  Tateki Nakamura

发明人： Yutaka Yamashita ,  Shigeki Senoo ,  Eiji Saito ,  Takeshi Kudo ,  Tateki Nakamura

IPC分类号： F01D5/14 ,  F01D5/22

CPC分类号： F01D5/141 ,  F01D5/22

摘要： A turbine bucket for a steam turbine low-pressure final stage has an exhaust area exceeding 9.6 m2 and 13.8 m2 in steam-turbine final-stage buckets for a rated speed 3600 rpm and 300 rpm machines, respectively. The turbine bucket is made of martensite steel. A blade portion of the turbine bucket has a suction surface 7 and a pressure surface 8 which are each formed, at a turbine blade root, of three areas consisting of a steam inlet side area 12 with curvature, a steam outlet side area 13 with curvature and an approximately straightly formed area located between the two areas.

摘要翻译： 用于汽轮机低压最终级的涡轮机桶分别具有超过9.6m 2的排气面积和13.8m 2的蒸汽涡轮机末级斗，额定转速为3600rpm和300rpm。 涡轮桶由马氏体钢制成。 涡轮机叶片的叶片部分具有抽吸表面7和压力表面8，它们在涡轮叶片根部处形成有由具有曲率的蒸汽入口侧区域12组成的三个区域，具有曲率的蒸汽出口侧区域13 以及位于两个区域之间的大致直立的区域。

公开(公告)号：US20080206065A1

公开(公告)日：2008-08-28

申请号：US12018556

申请日：2008-01-23

申请人： Yutaka Yamashita ,  Shigeki Senoo ,  Eiji Saito ,  Takeshi Kudo ,  Tateki Nakamura

发明人： Yutaka Yamashita ,  Shigeki Senoo ,  Eiji Saito ,  Takeshi Kudo ,  Tateki Nakamura

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/22

摘要： A turbine bucket is provided that can make centrifugal stress acting on a blade or dovetail not greater than a limit value of a material and that is provided with a shape of a blade root that can ensure a steam passage even if the blade is increased in length in order to increase an exhaust area.The turbine bucket is for a steam turbine low-pressure final stage and has an exhaust area exceeding 9.6 m2 (13.8 m2) in steam-turbine final-stage buckets for a rated speed 3600 rpm (3000 rpm) machine. The turbine bucket is made of martensite steel. A blade portion of the turbine bucket has a suction surface 7 and a pressure surface 8 which are each formed, at a turbine blade root, of three areas consisting of a steam inlet side area 12 with curvature, a steam outlet side area 13 with curvature and an approximately straightly formed area put between the two areas. An airfoil of the turbine bucket root is formed such that the relationship between a blade pitch t and a turbine-axial width BW of the blade portion is BW/t≧5.

摘要翻译： 提供一种涡轮机桶，其可以使作用在叶片或燕尾榫上的离心应力不大于材料的极限值，并且设置有叶片形状，即使叶片长度增加也能确保蒸汽通道 以增加排气区域。 涡轮机桶用于汽轮机低压终级，并且在蒸汽涡轮机最终级桶中具有超过9.6m 2（13.8m 2以上）的排气面积，用于 额定转速3600 rpm（3000 rpm）机。 涡轮桶由马氏体钢制成。 涡轮机叶片的叶片部分具有抽吸表面7和压力表面8，它们在涡轮叶片根部处形成有由具有曲率的蒸汽入口侧区域12组成的三个区域，具有曲率的蒸汽出口侧区域13 以及放置在两个区域之间的大致直立的区域。 涡轮叶根的叶片形成为叶片间距t与叶片部分的涡轮轴向宽度BW之间的关系为BW / t> = 5。

公开(公告)号：US20120076646A1

公开(公告)日：2012-03-29

申请号：US13231860

申请日：2011-09-13

申请人： Hideki Ono ,  Kenichi Murata ,  Shigeki Senoo

发明人： Hideki Ono ,  Kenichi Murata ,  Shigeki Senoo

IPC分类号： F01D9/02 ,  F04D21/00 ,  F01D1/02

CPC分类号： F01D5/141 ,  F05D2220/31 ,  F05D2240/121 ,  F05D2240/122 ,  F05D2250/711 ,  F05D2250/713

摘要： Suppressing profile loss of a moving blade due to radial flow without an increase in the length of a shaft of a turbine is disclosed. The degree of reaction on an inner circumferential side is set to an appropriate degree, reducing profile loss due to supersonic inflow, and improving turbine efficiency. A steam turbine stator vane has a trailing edge with a curved line when the stator vane is viewed from a downstream side in the axial direction. The curved line has an inflection point located on an outer circumferential side with respect to the center of the stator vane in the height direction of the stator vane. An inner circumferential portion of the curved line is located on the inner circumferential side with respect to the inflection point. An outer circumferential portion of the curved line is located on the outer circumferential side with respect to the inflection point.

摘要翻译： 公开了由于径向流动而不增加涡轮轴的长度而增加动叶片的轮廓损失。 将内周侧的反应度设定在适当的程度，减少由于超音速流入造成的轮廓损失，提高涡轮效率。 当从轴向的下游侧观察定子叶片时，汽轮机定子叶片具有带有曲线的后缘。 曲线具有相对于定子叶片的中心在定子叶片的高度方向上的外周侧上的拐点。 曲线的内周部相对于拐点位于内周侧。 曲线的外周部相对于拐点位于外周侧。

公开(公告)号：US07547187B2

公开(公告)日：2009-06-16

申请号：US11350025

申请日：2006-02-09

申请人： Shigeki Senoo ,  Tetsuaki Kimura

发明人： Shigeki Senoo ,  Tetsuaki Kimura

IPC分类号： F01D9/00

CPC分类号： F01D5/143 ,  F05D2250/322 ,  Y10S416/02

摘要： An axial turbine includes a plurality of stages, each of the plurality of stages having stationary blades adjacent to each other along the turbine circumferential direction and corresponding moving blades adjacent to each other along the circumferential direction, each of the moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, so as to be opposed to the corresponding stationary blade. In this axial turbine, each of the stationary blades is formed so that the intersection line between the outer periphery of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer periphery of the stationary blade and that is parallel to the central axis of the turbine.

摘要翻译： 轴向涡轮机包括多个级，多个级中的每一级具有沿着涡轮机圆周方向彼此相邻的固定叶片和沿圆周方向彼此相邻的对应的活动叶片，每个动叶片位于 沿着工作流体的流动方向相应的一个固定叶片，以便与相应的固定叶片相对。 在该轴向涡轮机中，每个固定叶片被形成为使得构成具有比前一级中的动叶片更长的移动叶片的台阶的静止叶片的外周与包含涡轮机的中心轴的平面之间的交线， 具有至少包括固定叶片的出口外周边并且平行于涡轮机的中心轴线的流路恒定直径部分。

公开(公告)号：US07429161B2

公开(公告)日：2008-09-30

申请号：US11392738

申请日：2006-03-30

申请人： Shigeki Senoo ,  Tetsuaki Kimura

发明人： Shigeki Senoo ,  Tetsuaki Kimura

IPC分类号： F01D1/02

CPC分类号： F01D5/143 ,  F05D2250/322 ,  Y10S416/02

摘要： An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.

摘要翻译： 轴向涡轮机包括多个级，每个级包括沿着涡轮机圆周方向排列成一排的多个静止叶片和与固定叶片平行的多个活动叶片，每个动叶片设置在相应的叶片的下游 在工作流体的流动方向上的相应固定叶片中的一个，以便与相应的固定叶片相对。 这里，每个固定叶片形成为使得构成具有比前一级的动叶片长的动叶片的台阶的静止叶片的外周部分和包含涡轮机的中心轴线的平面之间的交线线具有 流路恒定直径部分，其包括至少固定叶片的出口外周部分并且平行于涡轮机中心轴线。

公开(公告)号：US08425181B2

公开(公告)日：2013-04-23

申请号：US12706073

申请日：2010-02-16

申请人： Shigeki Senoo

发明人： Shigeki Senoo

IPC分类号： F01B25/00

CPC分类号： F01D9/041 ,  F01D5/143 ,  F01D5/145 ,  F01D25/32 ,  F05D2220/31

摘要： The axial-flow turbine includes an extraction chamber 15 disposed on the outer circumference of a turbine blade chamber 12 and an extraction opening 16. An outer diaphragm 8 forming the downstream-side wall surface of the extraction chamber 15 is provided with a projection 21 formed more radially inwardly than the downstream-side edge on the outer circumference of an adjacent bucket 2 on the upstream side of the extraction opening 16 to form the downstream-side wall surface of the extraction opening 16. The projection 21 forms an upstream-side wall surface 18 of the outer diaphragm 8 for leading a part of the working fluid to the extraction chamber 15, and an inner wall surface 19 of the outer diaphragm 8 for leading the remaining working fluid to a bucket 11 on the downstream side of the extraction opening 16.

摘要翻译： 轴流涡轮机包括设置在涡轮叶片室12的外周的抽出室15和抽出口16.构成提取室15的下游侧壁面的外隔膜8设置有形成的突起21 比在抽出口16的上游侧的相邻的铲斗2的外周上的下游侧边缘更径向向内，以形成提取开口16的下游侧壁表面。突起21形成上游侧壁 用于将一部分工作流体引导到提取室15的外隔膜8的表面18和外隔膜8的内壁表面19，用于将剩余的工作流体引导到提取开口的下游侧的桶11 16。

公开(公告)号：US07901179B2

公开(公告)日：2011-03-08

申请号：US12236116

申请日：2008-09-23

申请人： Shigeki Senoo ,  Tetsuaki Kimura

发明人： Shigeki Senoo ,  Tetsuaki Kimura

IPC分类号： F01D1/02

CPC分类号： F01D5/143 ,  F05D2250/322 ,  Y10S416/02

摘要： An axial turbine includes a plurality of stages each comprising a plurality of stationary blades arranged in a row along the turbine circumferential direction and a plurality of moving blades in a row parallel to the stationary blades, each of the moving blade being disposed downstream of a respective one of the corresponding stationary blade in a flow direction of a working fluid so as to be opposed to the corresponding stationary blade. Herein, each of the stationary blades is formed so that the intersection line between the outer peripheral portion of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer peripheral portion of the stationary blade and that is parallel to the turbine central axis.

摘要翻译： 轴向涡轮机包括多个级，每个级包括沿着涡轮机圆周方向排列成一排的多个静止叶片和与固定叶片平行的多个活动叶片，每个动叶片设置在相应的叶片的下游 在工作流体的流动方向上的相应固定叶片中的一个，以便与相应的固定叶片相对。 这里，每个固定叶片形成为使得构成具有比前一级的动叶片长的动叶片的台阶的静止叶片的外周部分和包含涡轮机的中心轴线的平面之间的交线线具有 流路恒定直径部分，其包括至少固定叶片的出口外周部分并且平行于涡轮机中心轴线。

公开(公告)号：US20060222490A1

公开(公告)日：2006-10-05

申请号：US11350025

申请日：2006-02-09

申请人： Shigeki Senoo ,  Tetsuaki Kimura

发明人： Shigeki Senoo ,  Tetsuaki Kimura

IPC分类号： F01D9/00

CPC分类号： F01D5/143 ,  F05D2250/322 ,  Y10S416/02

摘要： An axial turbine includes a plurality of stages, each of the plurality of stages having stationary blades adjacent to each other along the turbine circumferential direction and corresponding moving blades adjacent to each other along the circumferential direction, each of the moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, so as to be opposed to the corresponding stationary blade. In this axial turbine, each of the stationary blades is formed so that the intersection line between the outer periphery of the stationary blade constituting a stage having moving blades longer than moving blades in a preceding stage and a plane containing the central axis of the turbine, has a flow path constant diameter portion that includes at least an outlet outer periphery of the stationary blade and that is parallel to the central axis of the turbine.

公开(公告)号：US09051839B2

公开(公告)日：2015-06-09

申请号：US13536105

申请日：2012-06-28

申请人： Shigeki Senoo

发明人： Shigeki Senoo

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/145 ,  F01D9/04 ,  F05D2240/302 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/305 ,  F05D2240/306

摘要： A supersonic turbine moving blade in which increased circumferential speed due to increased blade length and average diameter reduces shock wave loss in its inflow area. It has at least one of the following features: pressure surface curvature is nonnegative from the leading to trailing edge end; negative pressure surface curvature is positive upstream and negative downstream; dimensionless pressure surface curvature (inter-blade pitch divided by curvature radius) is larger than 0.0 and smaller than 0.1 in the 30%-to-60% portion of the length along the pressure surface; the leading edge part is formed by continuous curvature curves and the distance between ½ point of the blade maximum thickness and leading edge end exceeds ½ of the maximum thickness; the exit angle is larger than a theoretical outflow angle; and the maximum thickness point is nearer to the trailing edge than to the leading edge.

摘要翻译： 超音速涡轮机动叶片由于叶片长度和平均直径的增加而增加了圆周速度，从而减小了流入区域的冲击波损耗。 它具有以下特征中的至少一个：压力表面曲率从前缘到后缘端是非负的; 负压面曲率为上游和下游正负极; 在压力表面的长度的30％至60％部分中，无量纲压力表面曲率（叶片间间距除以曲率半径）大于0.0且小于0.1; 前缘部分由连续的曲率曲线形成，叶片最大厚度和前缘端的1/2点之间的距离超过最大厚度的1/2; 出射角大于理论流出角; 并且最大厚度点比前缘更接近后缘。

公开(公告)号：US08308421B2

公开(公告)日：2012-11-13

申请号：US13014997

申请日：2011-01-27

申请人： Shigeki Senoo ,  Tetsuaki Kimura

发明人： Shigeki Senoo ,  Tetsuaki Kimura

IPC分类号： F01D1/02

CPC分类号： F01D5/143 ,  F05D2250/322 ,  Y10S416/02

摘要： A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

摘要翻译： 一种操作轴流涡轮机的方法，具有包括固定叶片和活动叶片的台架，每个固定叶片的出口的径向高度高于其入口的径向高度，每个活动叶片位于相应的一个 所述静叶片沿着工作流体的流动方向移动，所述动叶片被构造成使得动叶片前端圆周速度马赫数超过1.0，所述方法包括限制流过外周部分的工作流体的径向速度分量 静止叶片从固定叶片入口到固定叶片出口，其中通过固定叶片的工作流体基本上平行于涡轮机的中心轴线从固定叶片出口流动到动叶片入口。