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    Cooling air bleed device in a turbomachine
    1.
    发明授权
    Cooling air bleed device in a turbomachine 有权
    在涡轮机中冷却排气装置

    公开(公告)号：US08448448B2

    公开(公告)日：2013-05-28

    申请号：US12490962

    申请日：2009-06-24

    Applicant: Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

    Inventor： Stephane Pierre Guillaume Blanchard ,  Mathieu Dakowski ,  Thomas Daris ,  Romain Nicolas Lunel

    IPC: F02C6/04

    CPC classification number: F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18 ,  F02K1/822 ,  Y02T50/675 ,  Y10T137/7891

    Abstract: An air bleed device for cooling components in a turbine engine, including an annular conduit having a substantially rectangular cross-section formed in a housing and having a radially internal wall swept by an airflow is disclosed. The device includes an air inlet orifice, and a flap valve for controlling the airflow entering through the orifice, formed by a plate borne by a maneuvering member mobile in translation parallel to the axis of the orifice between a position in which the plate closes off the orifice and a position in which the plate opens the orifice.

    Abstract translation: 一种用于在涡轮发动机中冷却部件的排气装置，包括形成在壳体中并且具有被气流扫掠的径向内壁的具有基本矩形横截面的环形导管。 该装置包括空气入口孔和用于控制通过孔口进入的气流的瓣阀，由通过平行于孔的轴线平移移动的操纵构件所承载的板形成，该板在其中板关闭的位置 孔和板打开孔口的位置。

    Turbine stator for aircraft turbine engine including a vibration damping device
    2.
    发明授权
    Turbine stator for aircraft turbine engine including a vibration damping device 有权
    用于飞机涡轮发动机的涡轮定子，包括减振装置

    公开(公告)号：US08133010B2

    公开(公告)日：2012-03-13

    申请号：US12247462

    申请日：2008-10-08

    Applicant: Mathieu Dakowski ,  Sandrine Gandelot ,  Eric Jacques Lefebvre

    Inventor： Mathieu Dakowski ,  Sandrine Gandelot ,  Eric Jacques Lefebvre

    IPC: F04D29/66

    CPC classification number: F01D5/081 ,  F01D5/26 ,  F01D11/001 ,  F05D2260/6022 ,  F05D2260/96 ,  Y02T50/676

    Abstract: A turbine stator for an aircraft turbine engine is disclosed. The turbine stator includes a stator wall supporting a high pressure air injector fixed on the downstream side, and an annular abradable element support. The lower radial end of the element support is fixed to the high pressure air injector and the upper radial end of the element support is fixed to the stator wall, such that they jointly delimit a cavity under pressure. The turbine stator also includes at least one vibration damping device located in the cavity under pressure. The vibration damping device is in contact with each of the two elements taken among the stator wall and the annular support.

    Abstract translation: 公开了一种用于飞机涡轮发动机的涡轮机定子。 涡轮定子包括支撑固定在下游侧的高压空气喷射器的定子壁和环形可磨损元件支撑件。 元件支撑件的下部径向端部固定到高压空气喷射器，并且元件支撑件的上部径向端部固定到定子壁上，使得它们在压力下共同限定空腔。 涡轮定子还包括在压力下位于空腔中的至少一个减振装置。 减震装置与定子壁和环形支架中的两个元件中的每一个接触。

    VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE
    3.
    发明申请
    VENTILATION OF A HIGH-PRESSURE TURBINE IN A TURBOMACHINE 有权
    涡轮机中的高压涡轮通风

    公开(公告)号：US20110280735A1

    公开(公告)日：2011-11-17

    申请号：US13125154

    申请日：2009-10-16

    Applicant: Mathieu Dakowski ,  Fabrice Garin ,  Delphine Roussin-Leroux ,  Wilfried Schweblen

    Inventor： Mathieu Dakowski ,  Fabrice Garin ,  Delphine Roussin-Leroux ,  Wilfried Schweblen

    IPC: F02C7/18

    CPC classification number: F01D5/082 ,  F01D5/087 ,  F02C7/18 ,  F05D2260/205 ,  Y02T50/671 ,  Y02T50/676

    Abstract: A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.

    Abstract translation: 一种涡轮机高压涡轮，包括具有上游和下游环形凸缘的转子盘，所述转子盘分开径向内部的环形空腔，其中盘的轮毂从两个径向外部的环形空腔延伸，其中一个在盘的上游并且接收通风空气 流动，另一个在盘的下游，盘的上游凸缘包括连接到上游永恒腔的机构和用于使盘的毂通风的内腔。

    HIGH-PRESSURE TURBINE FOR TURBOMACHINE, ASSOCIATED GUIDE VANE SECTOR AND AIRCRAFT ENGINE
    4.
    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

    Applicant: Mathieu Dakowski ,  Alain Dominique Gendraud

    Inventor： Mathieu Dakowski ,  Alain Dominique Gendraud

    IPC: F01D9/00

    CPC classification number: F02C3/045 ,  F01D9/042 ,  F01D25/246 ,  F05D2250/41 ,  F05D2270/114 ,  Y02T50/671

    Abstract: 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.

    Abstract translation: 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。

    Variable-section turbomachine nozzle
    5.
    发明授权
    Variable-section turbomachine nozzle 有权
    可变截面涡轮机喷嘴

    公开(公告)号：US07520135B2

    公开(公告)日：2009-04-21

    申请号：US11248330

    申请日：2005-10-13

    Applicant: Mathieu Dakowski ,  Guy Lapergue ,  Romain Lunel ,  Guillaume Sevi

    Inventor： Mathieu Dakowski ,  Guy Lapergue ,  Romain Lunel ,  Guillaume Sevi

    IPC: F02K1/12

    CPC classification number: F02K1/1207

    Abstract: A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control levers comprising both controlled levers that are actuated directly by actuators, and follower levers that are actuated by the controlled levers via transmission links. When the nozzle is at rest, the flaps associated with the follower levers present a radial offset relative to the flaps associated with the controlled levers.

    Abstract translation: 可变截面涡轮机喷嘴包括多个移动翼片，以及包括各自与相应的活动翼片相关联的控制杆的移动翼片控制系统，所述控制杆包括由致动器直接致动的受控杆和致动器的从动杆 通过控制杆通过传输链路。 当喷嘴处于静止状态时，与从动杆相关联的翼片相对于与受控杆相关的翼片呈现径向偏移。

    COOLING AIR BLEED DEVICE IN A TURBOMACHINE
    10.
    发明申请
    COOLING AIR BLEED DEVICE IN A TURBOMACHINE 有权
    在涡轮机中冷却空气装置

    公开(公告)号：US20090320498A1

    公开(公告)日：2009-12-31

    申请号：US12490962

    申请日：2009-06-24

    Applicant: Stephane Pierre Guillaume BLANCHARD ,  Mathieu DAKOWSKI ,  Thomas DARIS ,  Romain Nicolas LUNEL

    Inventor： Stephane Pierre Guillaume BLANCHARD ,  Mathieu DAKOWSKI ,  Thomas DARIS ,  Romain Nicolas LUNEL

    IPC: F02C7/18 ,  F01D25/12

    CPC classification number: F01D9/06 ,  F01D25/12 ,  F02C6/08 ,  F02C7/18 ,  F02K1/822 ,  Y02T50/675 ,  Y10T137/7891

    Abstract: Air bleed device for cooling components in a turbine engine, including an annular conduit (18) having a substantially rectangular cross-section formed in a housing (12) and having a radially internal wall (22) swept by an airflow (24), and which comprises at least one air inlet orifice (20), a flap valve (40) for controlling the airflow entering through the orifice (20), formed by a plate (44) borne by a maneuvering member (50) mobile in translation parallel to the axis (21) of the orifice (20) between a position in which the plate (44) closes off said orifice and a position in which the plate (44) opens said orifice.

    Abstract translation: 用于在涡轮发动机中冷却部件的排气装置，包括形成在壳体（12）中并且具有由气流（24）扫过的径向内壁（22）的基本矩形横截面的环形导管18，以及 其包括至少一个空气入口孔口（20），用于控制通过所述孔口（20）进入的空气的瓣阀（40），所述阀门由平板运动的机动构件（50）承载的平板（44）形成， 所述孔口（20）的轴线（21）在所述板（44）关闭所述孔口的位置与所述板（44）打开所述孔口的位置之间。

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