利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

10 条记录 (耗时 0.012 秒)

    LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN
    3.
    发明申请
    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：US20120134788A1

    公开(公告)日：2012-05-31

    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： F04D29/58

    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） 。

    Low pressure turbine for an aircraft turbomachine, comprising a segmented nozzle with an improved design
    4.
    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） 。

    Cooled turbine guide vane
    5.
    发明授权
    Cooled turbine guide vane 失效
    冷却涡轮导叶

    公开(公告)号：US5772398A

    公开(公告)日：1998-06-30

    申请号：US774636

    申请日：1996-12-30

    申请人： Isabelle Marie-Agnes Noiret ,  Jean-Claude Christian Taillant

    发明人： Isabelle Marie-Agnes Noiret ,  Jean-Claude Christian Taillant

    IPC分类号： F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F02C7/18 ,  F04D29/38

    CPC分类号： F01D5/189 ,  F05D2240/81 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    摘要： A cooled turbine guide vane comprises a hollow aerodynamic portion between inner and outer platforms. The interior of the aerodynamic portion is partitioned into a leading edge duct and a main cavity in which a perforated tubular member is disposed, being spaced from the intrados and extrados side walls of the vane by longitudinal ribs. The tubular member is divided by a partition into two cavities on the intrados and extrados sides of the partition. A first cooling circuit is constituted by the leading edge duct and the intrados cavity of the tubular member, and a second cooling circuit is constituted by the extrados cavity and a cooling system for the inner platform, both circuits being supplied with air by the same source from the outer platform. Cooling air from each circuit passes through the perforations of the tubular member to impinge on the inside face of the respective side wall of the vane and is then guided towards the trailing edge where it escapes through slits in the trailing edge.

    摘要翻译： 冷却的涡轮引导叶片包括在内平台和外平台之间的中空空气动力部分。 空气动力部分的内部被分隔成前缘管道和主空腔，其中设置多孔管状构件，其通过纵向肋与叶片的内侧和外侧侧壁间隔开。 管状构件由分隔件分隔成分隔件的内侧和外侧两个空腔。 第一冷却回路由管状部件的前缘管道和内部空腔构成，第二冷却回路由外部空腔和内部平台的冷却系统构成，两个回路由相同的源供给空气 从外部平台。 来自每个电路的冷却空气通过管状构件的穿孔以撞击在叶片的相应侧壁的内表面上，然后被引导到后缘，在该后缘通过后缘中的狭缝逸出。

    Sectored, one-piece nozzle of a turbine engine turbine stator
    8.
    发明授权
    Sectored, one-piece nozzle of a turbine engine turbine stator 失效
    涡轮发动机涡轮定子的一体式喷嘴

    公开(公告)号：US5752804A

    公开(公告)日：1998-05-19

    申请号：US562598

    申请日：1995-11-24

    申请人： Josette Benoist ,  Jerome Emmanuel Rene Jolu ,  Paul Martyez ,  Jean-Claude Christian Taillant

    发明人： Josette Benoist ,  Jerome Emmanuel Rene Jolu ,  Paul Martyez ,  Jean-Claude Christian Taillant

    IPC分类号： F01D25/24 ,  F04D29/44

    CPC分类号： F01D25/246 ,  F05D2230/642 ,  Y02T50/671

    摘要： A nozzle of a turbine stator of a turbine engine, wherein at least two of the vanes are fixed to each inner platform and to opposite each outer platform, and a maintaining unit is configured to maintain each sector with respect to a case of the turbine stator and to connect sectors together and has a rotational maintaining element, a radial maintaining element and an axial maintaining element. The radial maintaining element is flexible so as to permit a radial expansion of each sector and is constituted by an elastic joint fixed to the case so as to surround the sectors.

    摘要翻译： 涡轮发动机的涡轮机定子的喷嘴，其中至少两个叶片固定到每个内平台并且与每个外平台相对，并且保持单元构造成相对于涡轮机定子的壳体来维持每个扇区 并且将扇区连接在一起并具有旋转保持元件，径向保持元件和轴向保持元件。 径向保持元件是柔性的，以便允许每个扇区的径向膨胀，并且由固定到壳体上的弹性接头构成以围绕扇形部分。

    Unsectored, one piece distributor of a turbojet turbine stator
    10.
    发明授权
    Unsectored, one piece distributor of a turbojet turbine stator 失效
    涡轮喷气发动机定子的单件分配器

    公开(公告)号：US5645398A

    公开(公告)日：1997-07-08

    申请号：US562597

    申请日：1995-11-24

    申请人： Josette Benoist ,  Paul Martyez ,  Jean-Claude Christian Taillant

    发明人： Josette Benoist ,  Paul Martyez ,  Jean-Claude Christian Taillant

    IPC分类号： F01D9/04 ,  F01D25/24 ,  F01D25/26

    CPC分类号： F01D9/042 ,  F01D25/246 ,  F05D2230/642 ,  Y02T50/673

    摘要： While remaining in one piece and unsectored, a nozzle permits a slight radial expansion of an assembly. The nozzle is formed by an inner platform mounted in a sliding manner with respect to a stator and an outer platform mounted in a free manner with respect to the case of the stator. Rods are fitted in a pivoting manner so as to radially guide and axially block upper parts of vanes, which are mounted in a sliding manner in the inner platform. The assembly is advantageously completed by gaskets. The nozzle can be used in high pressure turbines of turbojets.

    摘要翻译： 虽然保持在一个单件中并且未被接合，但是喷嘴允许组件略微径向膨胀。 喷嘴由相对于定子滑动安装的内平台和相对于定子的壳体以自由方式安装的外平台形成。 杆以枢转的方式安装，以便径向地引导和轴向地阻挡叶片的上部，其以滑动方式安装在内平台中。 该组件有利地由垫圈完成。 喷嘴可用于涡轮喷气发动机的高压涡轮机。