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    AUFGEHÄNGTE WASSERKRAFTANLAGE
    3.
    发明公开
    AUFGEHÄNGTE WASSERKRAFTANLAGE 审中-公开
    暂停水电厂

    公开(公告)号：EP3029312A1

    公开(公告)日：2016-06-08

    申请号：EP14460096.2

    申请日：2014-12-02

    申请人： Drozdowski, Feliks Leonard

    发明人： Drozdowski, Feliks Leonard

    IPC分类号： F03B17/06

    CPC分类号： F03B17/063 ,  F05B2240/123 ,  F05B2240/13 ,  F05B2240/911 ,  Y02E10/28

    摘要： Gegenstand der Erfindung ist ein aufgehängtes Wasserkraftwerk über fließendem Wasser, welches unter eine Brücke gehängt ist, aufweisend eine Wasserkammer (1) , welche sich langsam nach oben verengt, und wobei das Wasserrad mit einem Stromgenerator verbunden ist. Das Wasserrad (3) befindet sich über dem Wasserstand des fließenden Wassers. Vor dem Wasserrad ist eine Düse (2) für eine Einspritzung wie bei einer Pelton-Turbine. Hinter dem Wasserrad ist eine Flosse (4) die Wasserleere verursacht.

    摘要翻译： 本发明是一种悬浮在自来水电厂水，这是一个桥下悬挂，包括一个水腔室（1），其慢慢向上变窄，并且其中所述水轮连接到一个电流发生器。 水轮（3）位于流动的水的水位的上方。 水车前是用于注射作为冲击式水轮机的喷嘴（2）。 水车后面的翅片（4）使所述的水空白。

    Airfoil design method for an axial compressor and axial compressor
    4.
    发明授权
    Airfoil design method for an axial compressor and axial compressor 有权
    轴流式压缩机和轴流式压缩机的翼型设计方法

    公开(公告)号：EP2441964B1

    公开(公告)日：2017-07-12

    申请号：EP11185095.4

    申请日：2011-10-13

    申请人： Mitsubishi Hitachi Power Systems, Ltd.

    发明人： Takahashi, Yasuo ,  Myoren, Chihiro

    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： A high performance airfoil of a compressor is provided that can achieve a reduction in secondary loss and in cross flow and ensuring of reliability. An axial compressor includes a plurality of stator vanes 5 attached to an inner surface of a casing 3 defining an annular flow path and a plurality of rotor blades 4 attached to a rotating rotor 2 defining the annular flow path. A flow path is defined between a pressure surface 22 of a stator vane 5 and a suction surface 21 of a stator vane 5, the vanes being circumferentially adjacent to each other, or between a pressure surface 22 of a rotor blade 4 and a suction surface 23 of a rotor blade 4, 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 and an axial flow path width distribution extending from the leading edges 23 to trailing edges 24 of the vanes or the blades defining the flow path therebetween has an inflection point on the downstream side of the throat portion.

    摘要翻译： 提供一种压缩机的高性能翼型，其可以实现二次损失和横向流动的降低并确保可靠性。 轴流式压缩机包括多个定子叶片5，多个定子叶片5连接到限定环形流动路径的壳体3的内表面，多个转子叶片4连接到限定环形流动路径的旋转转子2。 流动路径被限定在定子叶片5的压力表面22与定子叶片5的吸力表面21之间，所述叶片在周向上彼此相邻，或者在转子叶片4的压力表面22与吸力表面之间 转子叶片4的叶片23,23彼此在周向上相邻。 流路形成为，在从前缘23到后缘24的轴向弦长和轴向流路宽度分布的50％的上​​游侧设置流路宽度最小的喉部， 限定其间的流动路径的叶片或叶片在喉部的下游侧具有拐点。

    Axial compressor
    6.
    发明公开
    Axial compressor 有权
    Axialverdichter

    公开(公告)号：EP2441964A3

    公开(公告)日：2014-09-03

    申请号：EP11185095.4

    申请日：2011-10-13

    申请人： Mitsubishi Hitachi Power Systems, Ltd.

    发明人： Takahashi, Yasuo ,  Myoren, Chihiro

    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： A high performance airfoil of a compressor is provided that can achieve a reduction in secondary loss and in cross flow and ensuring of reliability.
    An axial compressor includes a plurality of stator vanes 5 attached to an inner surface of a casing 3 defining an annular flow path and a plurality of rotor blades 4 attached to a rotating rotor 2 defining the annular flow path. A flow path is defined between a pressure surface 22 of a stator vane 5 and a suction surface 21 of a stator vane 5, the vanes being circumferentially adjacent to each other, or between a pressure surface 22 of a rotor blade 4 and a suction surface 23 of a rotor blade 4, 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 and an axial flow path width distribution extending from the leading edges 23 to trailing edges 24 of the vanes or the blades defining the flow path therebetween has an inflection point on the downstream side of the throat portion.

    摘要翻译： 提供了一种压缩机的高性能翼型件，其可以实现二次损失和交叉流动的减小并确保可靠性。 轴向压缩机包括多个定子叶片5，其附接到壳体3的限定环形流路的内表面，以及多个转子叶片4，其连接到限定环形流动路径的旋转转子2。 在定子叶片5的压力表面22和定子叶片5的吸力表面21之间，叶片彼此周向相邻或在转子叶片4的压力表面22和吸力表面 23是转子叶片4，叶片周向地相邻。 流路形成为使得在流路宽度最小的喉部设置在轴向弦长的50％的上​​游侧和从前缘23延伸到后缘24的轴向流路宽度分布 限定其间的流路的叶片或叶片之间具有在喉部的下游侧的拐点。

    SHROUDED FLUID TURBINE WITH BOUNDARY LAYER ENERGISING ELEMENTS
    8.
    发明公开
    SHROUDED FLUID TURBINE WITH BOUNDARY LAYER ENERGISING ELEMENTS 审中-公开
    与界面元素THRILLS液体涂覆TURBINE

    公开(公告)号：EP2836700A1

    公开(公告)日：2015-02-18

    申请号：EP13718019.6

    申请日：2013-04-10

    申请人： Ogin, Inc.

    发明人： RUBAK, Rune ,  WESTERGAARD, Carsten, H. ,  HJORT, Søren

    IPC分类号： F03D1/04

    CPC分类号： F01D1/04 ,  F03D1/04 ,  F05B2240/122 ,  F05B2240/123 ,  F05B2240/1231 ,  F05B2240/124 ,  F05B2240/133 ,  F05B2250/182 ,  Y02E10/72

    摘要： The present disclosure relates to fluid turbines having a turbine shroud assembly formed with mixing elements (e.g., both inwardly and outwardly curving elements) having airfoil cross sections. These airfoils form ringed airfoil shapes that provide a means of controlling the flow of fluid over the rotor assembly or over portions of the rotor assembly. The fluid dynamic performance of the ringed airfoils directly affects the performance of the turbine rotor assembly. The mass and surface area of the shrouds result in load forces on support structures. By delaying or eliminating the separation of the boundary layer over the ringed airfoils, boundary layer energizing members (e.g., vortex generators, flow control ports) on the ringed airfoils increase the power output of the fluid turbine system and allow for relatively shorter chord-length airfoil cross sections and therefore reduced mass and surface area of the shroud assemblies.