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    TURBINE STAGE FOR A TURBINE ENGINE
    3.
    发明申请
    TURBINE STAGE FOR A TURBINE ENGINE 有权
    涡轮发动机的涡轮级

    公开(公告)号：US20150118035A1

    公开(公告)日：2015-04-30

    申请号：US14394355

    申请日：2013-04-17

    Applicant: SNECMA

    Inventor： Alain Dominique Gendraud ,  Alberto Martin-Matos ,  Vincent Millier ,  Sebastien Jean Laurent Prestel

    IPC: F01D25/24 ,  F01D9/04

    CPC classification number: F01D25/246 ,  F01D9/04 ,  F01D9/041 ,  F01D9/042 ,  F01D11/005 ,  F05D2230/60 ,  F05D2240/10 ,  F05D2240/128 ,  F05D2240/91

    Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.

    Abstract translation: 一种用于涡轮发动机的涡轮级，该级包括一个喷嘴和一个安装在由壳体承载的扇形环内的轮。 喷嘴连接到壳体并且通过承受环形裂环而轴向保持在下游。 每个环形扇区在其上游端包括C形截面的构件，其接合在壳体轨道上并且径向保持开口环。 每个环形扇形体的C形构件的径向内壁在整个轴向尺寸上在开口环的内部延伸，并且其上游端部接合在喷嘴的至少一个凹部中。

    UNLOCKABLE DEVICE FOR AXIALLY ARRESTING A SEALING RING WITH WHICH AN AIRCRAFT TURBOMACHINE MODULE ROTOR WHEEL MAKES CONTACT
    5.
    发明申请
    UNLOCKABLE DEVICE FOR AXIALLY ARRESTING A SEALING RING WITH WHICH AN AIRCRAFT TURBOMACHINE MODULE ROTOR WHEEL MAKES CONTACT 有权
    用于轴向旋转密封圈的解锁装置与飞机涡轮机模块转子轮联系

    公开(公告)号：US20140341722A1

    公开(公告)日：2014-11-20

    申请号：US14361954

    申请日：2012-12-04

    Applicant: SNECMA

    Inventor： Olivier Belmonte ,  Sebastien Jean Laurent Prestel

    IPC: F02C7/20 ,  F02C7/28 ,  F01D11/12

    CPC classification number: F02C7/20 ,  F01D11/122 ,  F01D25/246 ,  F01D25/28 ,  F02C7/28 ,  F05D2230/644 ,  F05D2240/11 ,  F05D2240/14 ,  F05D2250/312 ,  F05D2250/35 ,  F05D2250/70 ,  F05D2260/30

    Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.

    Abstract translation: 一种用于轴向阻止由可磨损材料制成的密封环的装置，其与飞行器涡轮机模块转子的周边接触，所述装置具有第一参考中心轴线，并且包括：支撑件，其包括支撑开口，所述支撑开口限定以 第二轴距轴线一定距离; 以及轴向停止部分，其包括以与轴线相距一定距离的第三轴线设置的抽取通道，并且围绕其周边限定互补的圆形轨道，与轨道配合以允许部件围绕轴线在轴向停止位置 用于密封环，以及通过提取通道提取环的位置。

    LABYRINTH SEAL FOR GAS TURBINE ENGINE TURBINE
    6.
    发明申请
    LABYRINTH SEAL FOR GAS TURBINE ENGINE TURBINE 有权
    燃油涡轮发动机油漆的乳胶密封

    公开(公告)号：US20140105732A1

    公开(公告)日：2014-04-17

    申请号：US14134405

    申请日：2013-12-19

    Applicant: SNECMA

    Inventor： Florent Pierre Antoine LUNEAU ,  Alain Dominique Gendraud ,  Patrick Joseph Marie Girard ,  Sebastien Jean Laurent Prestel

    IPC: F01D11/12

    CPC classification number: F01D11/122 ,  F01D11/001 ,  F05D2250/283

    Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮机，包括至少一个涡轮机定子和一个涡轮机转子，所述涡轮机定子包括至少一个内部环形平台，所述内部平台包括限定所述涡轮机定子和所述涡轮机转子之间的至少一个空腔的径向壁， 其中所述涡轮转子包括至少一个细长元件，所述至少一个细长元件基本上轴向地定位并且在所述空腔中限定密封挡板，并且所述涡轮机定子包括由可磨损材料制成的至少一个元件，所述可磨损材料设计成与所述涡轮转子的所述细长元件接合， 形成迷宫密封。

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