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    High-pressure turbine of a turbomachine
    2.
    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
    3.
    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。

    HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE
    6.
    发明申请
    HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE 有权
    涡轮发动机用高压涡轮机，相关导向部件和飞机发动机

    公开(公告)号：US20110229314A1

    公开(公告)日：2011-09-22

    申请号：US13059350

    申请日：2009-08-24

    申请人： Mathieu Dakowski ,  Alain Dominique Gendraud

    发明人： Mathieu Dakowski ,  Alain Dominique Gendraud

    IPC分类号： F01D9/00

    CPC分类号： F02C3/045 ,  F01D9/042 ,  F01D25/246 ,  F05D2250/41 ,  F05D2270/114 ,  Y02T50/671

    摘要： An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.

    摘要翻译： 一种涡轮机涡轮机的导叶组件的组装，由一组固定的流动稳定叶片形成。 导向叶片组件的外边缘轴向地轴承在涡轮机的外壳的一条线上，并且导向叶片组件的内边缘与涡轮机的内壳线的轴向滑动连接，轴向滑动连接 允许内边缘沿着马达轴线自由，其中轴向止动通过叶片的外边缘的轴向轴承来实现。

    High-pressure turbine for turbomachine, associated guide vane sector and aircraft engine
    7.
    发明授权
    High-pressure turbine for turbomachine, associated guide vane sector and aircraft engine 有权
    用于涡轮机的高压涡轮机，相关导向叶片部件和飞机发动机

    公开(公告)号：US08858169B2

    公开(公告)日：2014-10-14

    申请号：US13059350

    申请日：2009-08-24

    申请人： Mathieu Dakowski ,  Alain Dominique Gendraud

    发明人： Mathieu Dakowski ,  Alain Dominique Gendraud

    IPC分类号： F01D1/02 ,  F01D25/24

    CPC分类号： F02C3/045 ,  F01D9/042 ,  F01D25/246 ,  F05D2250/41 ,  F05D2270/114 ,  Y02T50/671

    摘要： An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.

    摘要翻译： 一种涡轮机涡轮机的导叶组件的组装，由一组固定的流动稳定叶片形成。 导向叶片组件的外边缘轴向地轴承在涡轮机的外壳的一条线上，并且导向叶片组件的内边缘与涡轮机的内壳线的轴向滑动连接，轴向滑动连接 允许内边缘沿着马达轴线自由，其中轴向止动通过叶片的外边缘的轴向轴承来实现。

    Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design
    8.
    发明授权
    Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design 有权
    用于飞机涡轮机的低压涡轮机，包括具有改进设计的分段喷嘴

    公开(公告)号：US08979489B2

    公开(公告)日：2015-03-17

    申请号：US13300981

    申请日：2011-11-21

    申请人： Jean-Claude Christian Taillant ,  Alain Dominique Gendraud

    发明人： Jean-Claude Christian Taillant ,  Alain Dominique Gendraud

    IPC分类号： F01D25/24 ,  F01D9/04 ,  F01D11/00 ,  F01D25/12

    CPC分类号： F01D9/042 ,  F01D11/005 ,  F01D25/12 ,  Y02T50/675

    摘要： The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).

    摘要翻译： 本发明涉及一种涡轮机的低压涡轮（1），其包括属于上游级（20B）的喷嘴（62）和属于下游级（20C）的喷嘴（162），所述喷嘴（62）形成段 （62a），其具有外部结构（66），所述外部结构（66）包括：径向地支撑在固定到所述壳体上的钩（79）上的突片（76），在所述壳体中的径向（87） 限定环形上游冷却空气循环空腔（91）;接触表面（84），其从所述突片（85）向下游方向延伸并且在内侧衬有可磨损元件（86），所述接触表面包括 位于所述喷嘴（162）上并且径向地支承在所述壳体的止动件（93）上的下游端（92），所述接触表面（84）限定与腔（91）连通的环形下游冷却空气循环腔（94） 。