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    DEVICE FOR LOCKING A ROOT OF A ROTOR BLADE
    4.
    发明申请
    DEVICE FOR LOCKING A ROOT OF A ROTOR BLADE 有权
    用于锁定转子叶片的装置

    公开(公告)号：US20130136605A1

    公开(公告)日：2013-05-30

    申请号：US13816083

    申请日：2011-08-08

    申请人： Jacques Rene Bart ,  Antoine Jean-Philippe Beaujard

    发明人： Jacques Rene Bart ,  Antoine Jean-Philippe Beaujard

    IPC分类号： F01D5/32 ,  F02C7/08

    CPC分类号： F01D5/326 ,  F01D5/3084 ,  F01D5/323

    摘要： A device for locking a root of a rotor blade in a groove in a rotor disk of a turbomachine including: a circular ring sector configured to be mounted, transversely to the axis of the turbomachine, in a groove in the rotor disk; at least one locking wedge, which is rigidly secured and perpendicular to the ring sector, and extends parallel to the axis of the ring sector so as to hold the root of the blade radially in the groove; and at least one locking tooth extending from the ring sector radially with respect to the axis of the ring sector, so as to prevent the root of the blade from moving axially in the groove.

    摘要翻译： 一种用于将转子叶片的根部锁定在涡轮机的转子盘中的槽中的装置，包括：圆形环形部分，其被构造成横向于涡轮机的轴线安装在转子盘的凹槽中; 至少一个锁定楔，其刚性地固定并垂直于所述环形部分，并且平行于所述环形部分的轴线延伸，以将所述刀片的根部径向地保持在所述凹槽中; 以及至少一个从所述环形部分相对于所述环形部分的轴线径向延伸的锁定齿，以防止所述刀片的根部在所述凹槽中轴向移动。

    TURBOMACHINE BLADE OR VANE HAVING COMPLEMENTARY ASYMMETRICAL GEOMETRY
    8.
    发明申请
    TURBOMACHINE BLADE OR VANE HAVING COMPLEMENTARY ASYMMETRICAL GEOMETRY 有权
    涡轮叶片或具有补充不对称几何的叶片

    公开(公告)号：US20130101429A1

    公开(公告)日：2013-04-25

    申请号：US13607131

    申请日：2012-09-07

    申请人： Clément Roussille ,  Julien Mateo ,  Antoine Jean-Philippe Beaujard ,  Elric Georges André Fremont

    发明人： Clément Roussille ,  Julien Mateo ,  Antoine Jean-Philippe Beaujard ,  Elric Georges André Fremont

    IPC分类号： F01D5/14

    CPC分类号： F01D5/147 ,  B29C70/00 ,  D03D25/005 ,  F01D5/225 ,  F01D5/282 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

    摘要： A turbomachine blade is made of composite material. The blade includes a first portion constituting at least an airfoil exhibiting two faces each connecting a leading edge to a trailing edge, the first portion forming a single part with at least one second portion present only on one of the faces of the airfoil. The second portion constitutes a portion of at least one of the following elements: a flowpath delimiting outer portion of an inner platform, an inner portion of an inner platform, a flowpath delimiting inner portion of an outer platform, and an outer portion of an outer platform. Portions of fiber reinforcements corresponding to the first and the second portions of the blade are at least partially mutually imbricated. Yarns of the first portion of the fiber reinforcement penetrate into the second portion of the fiber reinforcement.

    摘要翻译： 涡轮机叶片由复合材料制成。 叶片包括构成至少一个翼面的第一部分，其具有两个面，每个翼面将前缘连接到后缘，第一部分形成具有至少一个第二部分的第一部分，其仅存在于翼型的一个面上。 第二部分构成以下元件中的至少一个的一部分：限定内平台的外部部分的流路，内平台的内部部分，外平台的限定内部部分的流路和外平台的外部部分 平台。 对应于叶片的第一和第二部分的纤维增强部分至少部分地相互嵌入。 纤维增强材料的第一部分的纱线进入纤维增强件的第二部分。

    CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT
    9.
    发明申请
    CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT 有权
    CMC涡轮喷嘴适用于通过径向接触支撑金属涡轮机内壳

    公开(公告)号：US20120251314A1

    公开(公告)日：2012-10-04

    申请号：US13435910

    申请日：2012-03-30

    申请人： Antoine Jean-Philippe BEAUJARD ,  Gilles Alain Charier ,  Jean Pierre Mareix ,  Didier Fabre

    发明人： Antoine Jean-Philippe BEAUJARD ,  Gilles Alain Charier ,  Jean Pierre Mareix ,  Didier Fabre

    IPC分类号： F01D9/04

    CPC分类号： F01D5/282 ,  F01D9/065 ,  F01D25/246 ,  F05D2300/603 ,  Y02T50/672

    摘要： Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending radially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

    摘要翻译： 复合材料涡轮喷嘴刀片包括适于使冷却流体流过其并在护罩（11）和根部（12）之间延伸的翼型件（10），所述护罩成形为连接到一个或多个涡轮机壳体（6） ，7），并且所述根部被成形为提供与涡轮机内部壳体（5）的连接处，其中其根部（12）以松散的质地产生并且包括外部上游侧松动纹理凸耳（122）和 外部下游侧松动的纹理凸耳（124），两个外侧凸耳的端部相对于涡轮机的旋转轴线径向延伸，以形成用于支撑和定心所述内部壳体的装置。

    CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT
    10.
    发明申请
    CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY AN AXIAL CONTACT 有权
    CMC涡轮喷嘴适用于通过轴向接触支持金属涡轮内部壳体

    公开(公告)号：US20120251309A1

    公开(公告)日：2012-10-04

    申请号：US13435754

    申请日：2012-03-30

    申请人： Antoine Jean-Philippe Beaujard ,  Didier Fabre ,  Jean Pierre Mareix

    发明人： Antoine Jean-Philippe Beaujard ,  Didier Fabre ,  Jean Pierre Mareix

    IPC分类号： F01D9/04 ,  F02C7/18

    CPC分类号： F01D5/282 ,  F01D9/065 ,  F01D25/246 ,  F05D2300/603 ,  Y02T50/672

    摘要： Composite material turbine nozzle blade including an airfoil (10) adapted to have a cooling fluid flow through it and extending between a shroud (11) and a root (12), said shroud being shaped to be attached to one or more turbine casings (6, 7) of a turbomachine and said root being shaped to provide a junction with a turbine internal casing (5), wherein its root (12) is produced with a loosened texture and includes an external upstream side loosened texture lug (122) and an external downstream side loosened texture lug (124), the ends of the two external side lugs extending axially relative to the rotation axis of the turbomachine to form means for supporting and centering said internal casing.

    摘要翻译： 复合材料涡轮喷嘴刀片包括适于使冷却流体流过其并在护罩（11）和根部（12）之间延伸的翼型件（10），所述护罩成形为连接到一个或多个涡轮机壳体（6） ，7），并且所述根部被成形为提供与涡轮机内部壳体（5）的连接处，其中其根部（12）以松散的质地产生并且包括外部上游侧松动纹理凸耳（122）和 外部下游侧松动的纹理凸耳（124），两个外侧凸耳的端部相对于涡轮机的旋转轴线轴向延伸，以形成用于支撑和对中所述内部壳体的装置。