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26 条记录 (耗时 0.02 秒)

    BLADE BODY AND ROTARY MACHINE
    1.
    发明申请
    BLADE BODY AND ROTARY MACHINE 审中-公开
    叶片机和旋转机

    公开(公告)号：US20130224034A1

    公开(公告)日：2013-08-29

    申请号：US13881582

    申请日：2010-12-27

    申请人： Yasuro Sakamoto ,  Eisaku Ito ,  Hitoshi Kitagawa ,  Susumu Wakazono

    发明人： Yasuro Sakamoto ,  Eisaku Ito ,  Hitoshi Kitagawa ,  Susumu Wakazono

    IPC分类号： F01D5/14

    CPC分类号： F01D5/141 ,  F05D2240/304 ,  Y02T50/673

    摘要： The blade body of the present invention is provided with a main body which has a dorsal face and a ventral face and also provided with a trailing edge portion which connects the dorsal face to the ventral face with a continuous curved face. The curved face of the trailing edge portion is gradually decreased in curvature radius from one of the dorsal face and the ventral face toward the rear end portion which is positioned most downstream in a direction at which a fluid flows, decreased to the greatest extent in curvature radius at the rear end portion, thereafter, gradually increased in curvature radius from the rear end portion toward the other of the dorsal face and the ventral face and arrives at the other of the dorsal face and the ventral face.

    摘要翻译： 本发明的刀体设置有具有背面和腹面的主体，并且还具有将背面与腹面连续地连接的后缘部的后缘部。 后边缘部分的曲面从曲面半径逐渐减小，从背面和腹面之一到后端部，其位于流体流动方向最下游的最下方，曲率最大程度地减小 后端部的半径，此后，从后端部朝向背面和腹面的另一侧逐渐增加曲率半径，并到达背面和腹面的另一侧。

    BLADE STRUCTURE OF GAS TURBINE
    2.
    发明申请
    BLADE STRUCTURE OF GAS TURBINE 有权
    气体涡轮叶片结构

    公开(公告)号：US20100047065A1

    公开(公告)日：2010-02-25

    申请号：US12518445

    申请日：2007-05-10

    申请人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    发明人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    IPC分类号： F01D9/04 ,  F01D5/14

    CPC分类号： F01D5/145 ,  F01D5/143 ,  F01D5/20 ,  F01D9/041 ,  F05D2240/121 ,  F05D2240/303

    摘要： To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section 28 of a stationary blade 21 is bent in the rotational direction of a rotor. Thus, even if combustion gas leaks from a tip clearance between an end wall of a casing and a tip portion of a rotor blade, and a stagnation line 35 near a tip portion 22 is situated in the side of a back surface 24, because a section located radially outward of the border section 28 is bent in the rotational direction of the rotor, the stagnation line 35 is also situated toward the rotational direction of the rotor. Therefore, the stagnation lines 35 formed at various heights in the heightwise direction of the stationary blade 21 are generally aligned in the rotational direction of the rotor. Thus, fluctuation of pressure distribution in the heightwise direction of the stationary blade 21, of the combustion gas flowing into the stationary blade 21 can be reduced. As a result, secondary flow loss can be reduced and turbine efficiency can be improved.

    摘要翻译： 为了减少二次流动损失和提高涡轮机效率，位于固定叶片21的边界部分28的径向外侧的部分沿转子的旋转方向弯曲。 因此，即使燃烧气体从壳体的端壁和转子叶片的前端部之间的顶端间隙泄漏，并且在顶端部22附近的停滞线35位于后表面24的侧面，因为 位于边界部分28的径向外侧的部分沿转子的旋转方向弯曲，停滞线35也朝向转子的旋转方向。 因此，在静止叶片21的高度方向上形成在各高度处的停滞线35大致在转子的旋转方向上对齐。 因此，可以减少流入固定叶片21的燃烧气体的静止叶片21的高度方向的压力分布的波动。 结果，能够降低二次流动损失，提高涡轮效率。

    FLOW PATH STRUCTURE AND GAS TURBINE EXHAUST DIFFUSER
    5.
    发明申请
    FLOW PATH STRUCTURE AND GAS TURBINE EXHAUST DIFFUSER 有权
    流路结构和气体涡轮排气歧管

    公开(公告)号：US20130259670A1

    公开(公告)日：2013-10-03

    申请号：US13991796

    申请日：2010-12-24

    申请人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    发明人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    IPC分类号： F02C7/00

    CPC分类号： F02C7/00 ,  F01D5/143 ,  F01D25/162 ,  F01D25/30 ,  F05D2250/712

    摘要： A flow path structure includes a wall surface in which a flow path is formed, a structure configured to extend in a direction intersecting a main stream direction of a fluid flowing through the flow path from the wall surface, and a concave section forming region formed throughout a range including the structure in the main stream direction and having a concave section formed in the wall surface. As the structure occupies a partial range of the flow path in the flow path cross section intersecting the main stream, a cross-sectional area of the flow path is varied in accordance with positional variation in the main stream direction.

    摘要翻译： 流路结构包括其中形成有流路的壁面，构造成沿着与从壁面流过流路的流体的主流方向相交的方向延伸的结构，以及整体形成的凹部形成区域 包括在主流方向上的结构并且在壁表面中形成有凹部的范围。 由于结构占据与主流相交的流路横截面中的流路的局部范围，所以流路的横截面积根据主流方向的位置变化而变化。

    Blade structure of gas turbine
    7.
    发明授权
    Blade structure of gas turbine 有权
    燃气轮机叶片结构

    公开(公告)号：US08317466B2

    公开(公告)日：2012-11-27

    申请号：US12518445

    申请日：2007-05-10

    申请人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    发明人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono

    IPC分类号： F01D5/12

    CPC分类号： F01D5/145 ,  F01D5/143 ,  F01D5/20 ,  F01D9/041 ,  F05D2240/121 ,  F05D2240/303

    摘要： To reduce secondary flow loss and to improved turbine efficiency, a section located radially outward of a border section 28 of a stationary blade 21 is bent in the rotational direction of a rotor. Thus, even if combustion gas leaks from a tip clearance between an end wall of a casing and a tip portion of a rotor blade, and a stagnation line 35 near a tip portion 22 is situated in the side of a back surface 24, because a section located radially outward of the border section 28 is bent in the rotational direction of the rotor, the stagnation line 35 is also situated toward the rotational direction of the rotor. Therefore, the stagnation lines 35 formed at various heights in the heightwise direction of the stationary blade 21 are generally aligned in the rotational direction of the rotor. Thus, fluctuation of pressure distribution in the heightwise direction of the stationary blade 21, of the combustion gas flowing into the stationary blade 21 can be reduced. As a result, secondary flow loss can be reduced and turbine efficiency can be improved.

    摘要翻译： 为了减少二次流动损失和提高涡轮机效率，位于固定叶片21的边界部分28的径向外侧的部分沿转子的旋转方向弯曲。 因此，即使燃烧气体从壳体的端壁和转子叶片的前端部之间的顶端间隙泄漏，并且在顶端部22附近的停滞线35位于后表面24的侧面，因为 位于边界部分28的径向外侧的部分沿转子的旋转方向弯曲，停滞线35也朝向转子的旋转方向。 因此，在静止叶片21的高度方向上形成在各高度处的停滞线35大致在转子的旋转方向上对齐。 因此，可以减少流入固定叶片21的燃烧气体的静止叶片21的高度方向的压力分布的波动。 结果，能够降低二次流动损失，提高涡轮效率。

    TURBINE BLADE CASCADE ENDWALL
    8.
    发明申请
    TURBINE BLADE CASCADE ENDWALL 审中-公开
    涡轮叶片CASCADE ENDWALL

    公开(公告)号：US20100284818A1

    公开(公告)日：2010-11-11

    申请号：US12812115

    申请日：2008-09-25

    申请人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono ,  Takashi Hiyama

    发明人： Yasuro Sakamoto ,  Eisaku Ito ,  Susumu Wakazono ,  Takashi Hiyama

    IPC分类号： F01D5/14

    CPC分类号： F01D9/041 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F05D2250/70 ,  F05D2250/711

    摘要： Provided is a turbine blade cascade endwall that is capable of reducing crossflow and is capable of reducing secondary-flow loss that occurs in association with the crossflow, therefore being capable of achieving enhanced turbine performance. A convex portion (11) that is gently swollen as a whole, that has an apex (P1) at a position of 0 to 20% pitch in a position of 5 to 25% Cax, that gently slopes from this apex (P1) toward a downstream side and a suction side surface of an adjacently disposed turbine stationary blade (B1) or turbine moving blade, and that slopes slightly steeply from the apex (P1) toward an upstream side is provided between one turbine stationary blade (B1) or turbine moving blade and another turbine stationary blade (B1) or turbine moving blade disposed adjacent to one turbine stationary blade (B1) or turbine moving blade.

    摘要翻译： 提供了一种涡轮叶栅级联端壁，其能够减少横流，并且能够减少与横流相关联地发生的二次流损失，因此能够实现增强的涡轮性能。 一个整体轻轻肿胀的凸部（11），其顶点（P1）位于从该顶点（P1）缓缓倾斜的5至25％Cax位置处的0至20％间距的位置，朝向 相邻设置的涡轮固定叶片（B1）或涡轮机动叶片的下游侧和吸力侧表面，并且从顶点（P1）向上游侧稍微倾斜地倾斜设置在一个涡轮静叶片（B1）或涡轮 移动叶片和邻近一个涡轮固定叶片（B1）或涡轮机动叶片设置的另一涡轮机静叶片（B1）或涡轮机动叶片。

    GAS TURBINE
    9.
    发明申请
    GAS TURBINE 有权
    燃气轮机

    公开(公告)号：US20140041395A1

    公开(公告)日：2014-02-13

    申请号：US14008513

    申请日：2012-03-23

    申请人： Hitoshi Kitagawa ,  Yasuro Sakamoto ,  Eisaku Ito

    发明人： Hitoshi Kitagawa ,  Yasuro Sakamoto ,  Eisaku Ito

    IPC分类号： F01D5/14

    CPC分类号： F01D5/14 ,  F01D5/141 ,  F01D5/142 ,  F01D5/145

    摘要： A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.

    摘要翻译： 燃气轮机通过在燃烧器中供给燃料来燃烧在压缩机中被压缩的空气，以便通过将产生的燃烧气体供给到涡轮来获得旋转动力。 涡轮机包括涡轮叶片元件和涡轮叶片元件，其涡轮在叶片元件和涡轮叶片元件之间交替定位，所述涡轮叶片元件和涡轮叶片元件沿着燃烧气体在具有圆柱形状的涡轮机气缸中流动的方向交替定位;以及烟道气体扩散器， 圆筒。 涡轮机叶片元件包括沿圆周方向等间隔设置的多个涡轮机叶片。 涡轮机叶片在纵向端部侧上具有比纵向中间部分侧的喉部宽度大的喉部宽度。 这有效地恢复烟气的压力。 这提高了涡轮机的效率，从而可以提高性能。

    Gas turbine with improved blade and vane and flue gas diffuser
    10.
    发明授权
    Gas turbine with improved blade and vane and flue gas diffuser 有权

    公开(公告)号：US09719354B2

    公开(公告)日：2017-08-01

    申请号：US14008513

    申请日：2012-03-23

    申请人： Hitoshi Kitagawa ,  Yasuro Sakamoto ,  Eisaku Ito

    发明人： Hitoshi Kitagawa ,  Yasuro Sakamoto ,  Eisaku Ito

    IPC分类号： F01D5/14

    CPC分类号： F01D5/14 ,  F01D5/141 ,  F01D5/142 ,  F01D5/145

    摘要： A gas turbine burns the air compressed in a compressor with supplying fuel in a combustor so as to obtain rotary power by supplying the generated combustion gas to a turbine. The turbine includes turbine vane elements and turbine blade elements that are alternately positioned in a direction in which the combustion gas fluidizes in a turbine cylinder having a cylindrical shape, and a flue gas diffuser having a cylindrical shape and connected to a rear portion of the turbine cylinder. The turbine blade element includes a plurality of turbine blades positioned at equal intervals in the circumference direction. The turbine blades have a throat width on a longitudinal end side made larger than a throat width on a longitudinally intermediate portion side. This efficiently restores the pressure of the flue gas. This improves the efficiency of the turbine so that the performance can be improved.