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    High-pressure turbine of a turbomachine
    3.
    发明授权
    High-pressure turbine of a turbomachine 有权
    涡轮机的高压涡轮机

    公开(公告)号：US08133018B2

    公开(公告)日：2012-03-13

    申请号：US12038604

    申请日：2008-02-27

    申请人： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

    发明人： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

    IPC分类号： F01D9/00

    CPC分类号： F01D25/246 ,  F01D9/042

    摘要： A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

    摘要翻译： 涡轮机的高压涡轮机，包括至少一个上游引导叶片元件和叶轮，其安装成在附接到从外壳悬挂的环形支撑件的环形部分内旋转，所述上游引导叶片元件包括在其上 径向内端，用于附接到内壳体的机构，并且在其径向外端处具有用于轴向地按压在涡轮机的固定元件上的机构，所述机构与所述环形支撑件独立于所述环形支撑件悬挂， 。

    HIGH-PRESSURE TURBINE OF A TURBOMACHINE
    4.
    发明申请
    HIGH-PRESSURE TURBINE OF A TURBOMACHINE 有权
    涡轮机的高压涡轮机

    公开(公告)号：US20080267768A1

    公开(公告)日：2008-10-30

    申请号：US12038604

    申请日：2008-02-27

    申请人： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

    发明人： Mathieu Dakowski ,  Claire Dorin ,  Alain Dominique Gendraud ,  Vincent Philippot

    IPC分类号： F01D5/02

    CPC分类号： F01D25/246 ,  F01D9/042

    摘要： High-pressure turbine of a turbomachine A high-pressure turbine (10) of a turbomachine, comprising at least one upstream guide vane element (16) and an impeller (18) mounted so as to rotate inside ring sectors (20) attached to an annular support (24) which is suspended from an outer casing (22), the upstream guide vane element comprising, at its radially inner end, means of attachment to an inner casing and, at its radially outer end, means (102, 104) for pressing axially on a fixed element (90) of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

    摘要翻译： 涡轮机的高压涡轮机涡轮机的高压涡轮机（10），包括至少一个上游引导叶片元件（16）和叶轮（18），所述至少一个上游引导叶片元件（16）和叶轮（18）安装成在环形部分（20）内旋转， 环形支撑件（24），其从外壳（22）悬挂，所述上游引导叶片元件在其径向内端包括附接到内壳的装置，并且在其径向外端处包括装置（102,104） 用于轴向地压在涡轮机的固定元件（90）上，所述固定元件（90）独立于环形支撑件从外壳悬挂以附接环形部分。

    Turbomachine turbine ring sector
    6.
    发明授权
    Turbomachine turbine ring sector 有权
    涡轮机水轮机领域

    公开(公告)号：US08348602B2

    公开(公告)日：2013-01-08

    申请号：US11926908

    申请日：2007-10-29

    申请人： Erwan Daniel Botrel ,  Claire Dorin

    发明人： Erwan Daniel Botrel ,  Claire Dorin

    IPC分类号： F01D25/14

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  F05D2250/191 ,  F05D2250/70 ,  F05D2260/201 ,  Y02T50/676

    摘要： A turbine ring sector is disclosed. The turbine ring sector includes a wall bounding an aerodynamic flowpath in which gases flow from the upstream region toward the downstream region, and a multiperforated plate, situated on the opposite side of the aerodynamic flowpath with respect to the wall. The multiperforated plate includes a bottom and side walls. The distance between the wall of the ring sector and the bottom of the multiperforated plate defines a gap which is progressive in an axial direction, from the upstream region toward the downstream region. The value of the gap situated at the upstream region is below the value of the gap situated at the downstream region.

    摘要翻译： 公开了涡轮机环形部分。 涡轮机环段包括界定气体流动路径的壁，气流从上游区域流向下游区域，多孔穿孔板位于空气动力学流路相对于壁的相反侧。 多孔板包括底壁和侧壁。 环形部分的壁与多孔板的底部之间的距离限定了从上游区域向下游区域在轴向方向上渐进的间隙。 位于上游区域的间隙的值低于位于下游区域的间隙的值。

    TURBOMACHINE TURBINE RING SECTOR
    7.
    发明申请
    TURBOMACHINE TURBINE RING SECTOR 有权
    涡轮涡轮环系

    公开(公告)号：US20080101923A1

    公开(公告)日：2008-05-01

    申请号：US11926908

    申请日：2007-10-29

    申请人： Erwan Daniel BOTREL ,  Claire Dorin

    发明人： Erwan Daniel BOTREL ,  Claire Dorin

    IPC分类号： F03B11/00

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  F05D2250/191 ,  F05D2250/70 ,  F05D2260/201 ,  Y02T50/676

    摘要： The present invention concerns the field of turbomachines, in particular the cooling of the ring sectors (1) of a turbine (8) of a turbomachine (9).It more specifically concerns a turbine ring sector (1) comprising: a wall (11) bounding an aerodynamic flowpath (5) in which gases flow from the upstream region (52) toward the downstream region (53), and a multiperforated plate (2), situated on the opposite side of the aerodynamic flowpath (5) with respect to the wall (11), said multiperforated plate (2) comprising a bottom (21, 121, 221, 321) and side walls (22, 23), the distance between the wall (11) of the ring sector (1) and the bottom (21, 121, 221, 321) of the multiperforated plate (2) defining a gap (7) which is progressive in an axial direction, from the upstream region (52) toward the downstream region (53). According to the invention, the value of the gap situated at the upstream region (52) is below the value of the gap situated at the downstream region (53).

    摘要翻译： 本发明涉及涡轮机领域，特别是涡轮机（9）的涡轮机（8）的环形部分（1）的冷却。 更具体地涉及涡轮机环形部分（1），包括：界定气体流动路径（5）的壁（11），气流从上游区域（52）流向下游区域（53），多孔板（2） ），其位于空气动力学流路（5）相对于壁（11）的相反侧，所述多孔板（2）包括底部（21,121,221,321）和侧壁（22,23）， 环形扇区（1）的壁（11）与多孔板（2）的底部（21,121,221,321）之间的距离限定了从轴向方向延伸的间隙（7） 上游区域（52）朝向下游区域（53）。 根据本发明，位于上游区域（52）处的间隙的值低于位于下游区域（53）处的间隙的值。