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    Turbine stage
    3.
    发明授权
    Turbine stage 有权
    涡轮舞台

    公开(公告)号：US08734100B2

    公开(公告)日：2014-05-27

    申请号：US13169411

    申请日：2011-06-27

    申请人： Fabrice Marcel Noel Garin ,  Alain Dominique Gendraud ,  Thierry Lequitte ,  Sebastien Jean Laurent Prestel

    发明人： Fabrice Marcel Noel Garin ,  Alain Dominique Gendraud ,  Thierry Lequitte ,  Sebastien Jean Laurent Prestel

    IPC分类号： F01D9/00

    CPC分类号： F01D25/246 ,  F01D11/12 ,  Y02T50/671

    摘要： A turbine stage for a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by an outer casing, and a sectorized nozzle fastened to the casing downstream from the wheel, each ring sector having a downstream end that is held bearing radially outwards against a cylindrical rail of the casing by means of the nozzle, the casing rail including an annular row of through radial notches reducing the areas for heat exchange by conduction both between the casing and the ring sectors and between the casing and the nozzle.

    摘要翻译： 用于涡轮机的涡轮级，该级包括安装在由外壳承载的扇形环内的转子轮，以及固定到车轮下游的壳体的扇形喷嘴，每个环形部分具有径向向外保持的下游端 通过喷嘴抵靠壳体的圆柱形轨道，壳体轨道包括环形排的通过径向槽口，通过壳体和环形部分之间以及壳体和喷嘴之间的导电来减少用于热交换的区域。

    Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design
    6.
    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） 。

    TURBINE RING ASSEMBLY
    8.
    发明申请
    TURBINE RING ASSEMBLY 有权
    涡轮环组件

    公开(公告)号：US20120027572A1

    公开(公告)日：2012-02-02

    申请号：US13255436

    申请日：2010-03-01

    申请人： Franck Roger Denis Denece ,  Alain Dominique Gendraud ,  Georges Habarou ,  Hubert Illand ,  Damien Bonneau

    发明人： Franck Roger Denis Denece ,  Alain Dominique Gendraud ,  Georges Habarou ,  Hubert Illand ,  Damien Bonneau

    IPC分类号： F01D25/24

    CPC分类号： F01D25/246 ,  D03D25/005 ,  F01D9/04 ,  F01D11/08 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2260/30 ,  F05D2300/21 ,  F05D2300/603 ,  Y02T50/67 ,  Y02T50/672

    摘要： A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

    摘要翻译： 涡轮环组件包括环支撑结构和多个环形部分，每个环形部分包括单片陶瓷基体复合材料。 每个环形部分包括形成环形基部的第一部分，其中限定了涡轮机环的内侧面的内侧面和外表面，两个突出部形成部分从该外侧面延伸，该突出部形成部分包括接合在环形支撑结构中的壳体中的端部。 环形部分呈现出基本上形状的部分，并且突片的端部由环形支撑结构保持而没有径向间隙。 翼片可以在子午线部分具有不小于平均宽度的三倍的自由长度。

    HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE
    9.
    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。

    Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it
    10.
    发明授权
    Unit for locking ring sectors on a turbomachine casing, comprising radial passages for gripping it 有权
    用于在涡轮机壳体上锁定环形部分的单元，包括用于夹紧的径向通道

    公开(公告)号：US08721277B2

    公开(公告)日：2014-05-13

    申请号：US12990913

    申请日：2009-05-14

    申请人： Alain Dominique Gendraud

    发明人： Alain Dominique Gendraud

    IPC分类号： F01D9/04 ,  F01D25/28

    CPC分类号： F01D25/246 ,  F05D2230/60 ,  F05D2230/70 ,  F16B2/245 ,  Y02T50/672

    摘要： A unit locking a ring sector attachment device onto an aircraft turbomachine casing, the unit including two clamping arms connected to each other at their aft ends by a connecting arm extending approximately parallel to the general direction between the two clamping arms. The unit also includes a passage enabling gripping of the unit on each side of a fictitious median plane orthogonal to the circumferential direction, each passage being formed in the connecting arm, extending along a direction line approximately parallel to the direction between the arms.

    摘要翻译： 单元将环形部分附接装置锁定到飞行器涡轮机壳体上，该单元包括两个夹持臂，它们的后端通过大致平行于两个夹紧臂之间的大致方向延伸的连接臂连接。 该单元还包括能够在垂直于圆周方向的虚拟中间平面的每侧上夹持单元的通道，每个通道形成在连接臂中，沿着大致平行于臂之间的方向的方向线延伸。