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    RING SECTOR OF TURBOMACHINE TURBINE
    2.
    发明申请
    RING SECTOR OF TURBOMACHINE TURBINE 有权
    涡轮涡轮机的环形部分

    公开(公告)号：US20110188993A1

    公开(公告)日：2011-08-04

    申请号：US13018789

    申请日：2011-02-01

    申请人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    发明人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    IPC分类号： F01D9/04

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/24 ,  F05D2250/26 ,  F05D2260/201 ,  Y02T50/676

    摘要： A turbine ring sector comprising: a wall presenting an inside face and an outside face, the inside face defining an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage, said multiply-perforated metal sheet having a bottom; wherein the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap; and wherein the variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value, said minimum value defining the minimum of the gap, and then increases from the minimum value to a second maximum value.

    摘要翻译： 一种涡轮环形部分，包括：呈现内表面和外表面的壁，所述内表面限定气体流过的轴向定向气流通道; 以及位于与所述气流通道相对的所述壁侧的多孔金属片，所述多孔金属片具有底部; 其中所述壁的外表面和所述多孔金属片的底部之间的间隔限定了间隙; 并且其中在其整个轴向范围上的所述间隙的值的变化从第一最大值朝向最小值减小，所述最小值定义所述间隙的最小值，然后从所述最小值增加到第二最大值。

    Ring sector of turbomachine turbine
    3.
    发明授权
    Ring sector of turbomachine turbine 有权
    涡轮机轮环

    公开(公告)号：US08684665B2

    公开(公告)日：2014-04-01

    申请号：US13018789

    申请日：2011-02-01

    申请人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    发明人： Jean-Luc Bacha ,  Emmanuel Berche ,  Didier Jeannel

    IPC分类号： F01D5/14

    CPC分类号： F01D11/24 ,  F05D2240/11 ,  F05D2250/14 ,  F05D2250/16 ,  F05D2250/24 ,  F05D2250/26 ,  F05D2260/201 ,  Y02T50/676

    摘要： A turbine ring sector comprising a wall presenting an inside face and an outside face, in which the inside face defines an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage is disclosed. The multiply-perforated metal sheet has a bottom, and the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap. The variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value and then increases from the minimum value to a second maximum value.

    摘要翻译： 一种涡轮机环形部分，包括呈现内表面和外表面的壁，其中所述内侧面限定气体流过的轴向取向的气流通道; 并且公开了位于与气流通道相对的壁的侧面上的多孔金属片。 多孔金属片具有底部，壁的外表面和多孔金属片的底部之间的空间限定了间隙。 在其整个轴向范围上的间隙值的变化从第一最大值朝向最小值减小，然后从最小值增加到第二最大值。

    TURBINE STAGE IN A TURBINE ENGINE
    4.
    发明申请
    TURBINE STAGE IN A TURBINE ENGINE 审中-公开
    涡轮发动机中的涡轮级

    公开(公告)号：US20120237342A1

    公开(公告)日：2012-09-20

    申请号：US13511266

    申请日：2010-12-14

    申请人： Emmanuel Berche ,  Vincent Philippot

    发明人： Emmanuel Berche ,  Vincent Philippot

    IPC分类号： F01D11/00

    CPC分类号： F01D11/08 ,  F01D11/005 ,  F01D25/246 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/10 ,  F05D2300/603 ,  Y02T50/672

    摘要： A turbine stage for a turbine engine includes a bladed wheel rotatable inside a sectorized ring of composite material carried by a casing. Each ring sector has a downstream circumferential rim held to bear radially against an annular tab that is engaged radially in an annular groove of the downstream circumferential rim of the ring with axial clearance, when cold, that is designed to be reduced to zero in operation when hot, and to enable the annular tab of the casing to be clamped axially in leaktight manner in the annular groove of the ring sector.

    摘要翻译： 用于涡轮发动机的涡轮级包括在由壳体承载的复合材料的扇形环内可旋转的叶片轮。 每个环形部分具有保持径向地抵靠环形突片的下游圆周边缘，该环形突出部径向地接合在环的下游圆周边缘的环形槽中，当冷时，轴向间隙被设计成在操作时被减小到零， 并且使得壳体的环形突片能够以密封的方式被轴向夹紧在环形部分的环形槽中。

    TURBINE WHEEL FOR A TURBINE ENGINE
    7.
    发明申请
    TURBINE WHEEL FOR A TURBINE ENGINE 有权
    涡轮发动机涡轮轮

    公开(公告)号：US20120269650A1

    公开(公告)日：2012-10-25

    申请号：US13448830

    申请日：2012-04-17

    申请人： Emmanuel Berche ,  Jean-Luc Bacha ,  Tangi Brusq

    发明人： Emmanuel Berche ,  Jean-Luc Bacha ,  Tangi Brusq

    IPC分类号： F01D5/18 ,  F01D5/02

    CPC分类号： F01D5/082 ,  F01D5/26 ,  F01D11/008 ,  F05B2240/33 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2214 ,  F05D2260/22141 ,  F05D2260/36 ,  Y02T50/676 ,  Y10S416/50

    摘要： A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.

    摘要翻译： 一种用于涡轮发动机的涡轮机叶轮，其包括承载叶片的盘，每个叶片具有承载翼型并通过根部连接的平台，以及容纳在所述柄间空间中的密封和阻尼片，所述平台包括在其径向上的突起 为了限定径向间隙并且在片材和平台之间产生至少一个空间，并且片材包括用于将空气供给到每个空间的孔，所述片材在操作中径向承载在其上。

    SEGMENTED TURBINE RING FOR A TURBOMACHINE, AND TURBOMACHINE FITTED WITH SUCH A RING
    8.
    发明申请
    SEGMENTED TURBINE RING FOR A TURBOMACHINE, AND TURBOMACHINE FITTED WITH SUCH A RING 审中-公开
    用于涡轮机的SEGMENTED涡轮环和用这种环的TURBOMACHINE

    公开(公告)号：US20120141257A1

    公开(公告)日：2012-06-07

    申请号：US13311094

    申请日：2011-12-05

    申请人： Emmanuel Berche ,  Jean-Luc Bacha ,  Didier Fabre ,  Jean-Pierre Mareix

    发明人： Emmanuel Berche ,  Jean-Luc Bacha ,  Didier Fabre ,  Jean-Pierre Mareix

    IPC分类号： F04D29/58

    CPC分类号： F01D11/005 ,  F05D2240/11 ,  F05D2240/57

    摘要： The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises: a plurality of segments assembled by means of sealed connection involving sealing strips, provided in the mutually-facing radial faces of said segments the internal lateral faces of which delimit the flow path along which the hot gaseous flow travels; and through-orifices, formed in said segments, to carry external fresh air towards their radial and internal faces. Advantageously, one, the lower one, of the sealing strips of the means of connection is designed to lie close to the lateral internal faces of said segments and to run parallel to them, passing through a cooling chamber formed in the radial faces of the segments and into which said orifices open.

    摘要翻译： 分段环具有通过其的涡轮机的气态热流，并且包括：多个段，其通过密封连接组装，所述密封连接包括密封条，设置在所述段的相互面对的径向面中，其内侧面限定 热气流沿其流动的流路; 以及形成在所述段中的通孔，以将外部新鲜空气向其径向和内表面携带。 有利地，连接装置的密封条中的一个密封条的一个被设计成靠近所述段的侧向内表面并平行于它们延伸，通过形成在段的径向面中的冷却室 并且所述孔打开。