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    Aircraft turbine engine with reduction gear
    2.
    发明授权
    Aircraft turbine engine with reduction gear 有权

    公开(公告)号：US11085329B2

    公开(公告)日：2021-08-10

    申请号：US16580823

    申请日：2019-09-24

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Julien Fabien Patrick Becoulet ,  Xavier Jean Yves Alain Agneray ,  Michel Gilbert Roland Brault

    IPC分类号： F01D25/18 ,  F01D25/16

    摘要： A turbine engine includes a fan. The fan includes a first shaft driven in rotation via a reduction gear, the first shaft being guided in rotation with respect to a support of a fixed structure via an upstream bearing and a downstream bearing, the downstream bearing guiding in rotation the first shaft with respect to a downstream branch of the support, the first shaft and the support together defining an enclosure. The reduction gear includes a ring gear fixed to the structure via a shell. The turbine engine also includes a lubricator composed of at least one pipe for conveying a liquid lubricant, wherein the pipe is located in the enclosure, the pipe passing through an orifice made in the shell and an opening made in the downstream branch.

    Device for deicing a separator nose of an aviation turbine engine
    5.
    发明授权
    Device for deicing a separator nose of an aviation turbine engine 有权

    公开(公告)号：US10138755B2

    公开(公告)日：2018-11-27

    申请号：US14783263

    申请日：2014-04-11

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Benoit Jean Henri Gomanne ,  Michel Gilbert Roland Brault

    IPC分类号： F01D25/02 ,  F01D25/24 ,  F02C7/047

    摘要： A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.

    DYNAMIC SEAL BEWTEEN TWO ROTORS OF AN AIRCRAFT TURBINE ENGINE
    9.
    发明申请
    DYNAMIC SEAL BEWTEEN TWO ROTORS OF AN AIRCRAFT TURBINE ENGINE 有权

    公开(公告)号：US20210071546A1

    公开(公告)日：2021-03-11

    申请号：US16956162

    申请日：2018-12-13

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Michel Gilbert Roland Brault ,  Julien Fabien Patrick Becoulet ,  Romain Guillaume Cuvillier ,  Arnaud Nicolas Negri

    IPC分类号： F01D25/18 ,  F02C7/28

    摘要： An aircraft turbomachine has a longitudinal axis A and includes a reduction gear, at least one turbine shaft, an upstream end of which is connected to an input shaft of a reduction gear, a fan, one shaft of which is connected to an output shaft of the reduction gear, and dynamic sealing means between said reduction gear input shaft and the fan shaft. The sealing means includes an annular cowling, the axial cross-section of which is substantially U-shaped An outer annular leg of the annular cowling is fastened to the fan shaft, and an inner annular leg supports at least one annular sealing joint that cooperates with the reduction gear input shaft. The cowling is elastically deformable in the radial direction in relation to the axis A.