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    Assembly for a turbine engine
    3.
    发明授权
    Assembly for a turbine engine 有权

    公开(公告)号：US11885268B2

    公开(公告)日：2024-01-30

    申请号：US17758731

    申请日：2021-01-06

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Philippe Gérard Edmond Joly ,  Jean-Marc Claude Perrollaz ,  Laurent Jablonski

    IPC分类号： F01D15/12 ,  F02C7/36

    CPC分类号： F02C7/36

    摘要： An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.

    Turbomachine assembly having a damper
    4.
    发明授权
    Turbomachine assembly having a damper 有权

    公开(公告)号：US11808170B2

    公开(公告)日：2023-11-07

    申请号：US17614812

    申请日：2020-05-27

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Philippe Gérard Edmond Joly ,  Romain Nicolas Lagarde ,  Jean-Marc Claude Perrollaz ,  Laurent Jablonski ,  François Jean Comin ,  Edouard Antoine Dominique Marie De Jaeghere ,  Charles Jean-Pierre Douguet

    IPC分类号： F01D5/26 ,  F01D5/10 ,  F04D29/66

    CPC分类号： F01D5/26 ,  F01D5/10 ,  F04D29/668 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2250/71 ,  F05D2260/96

    摘要： The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against the second rotor (140), and *being configured to apply a second centrifugal force (C2) on the second rotor (140), and o a linking part (20): *connecting the first bearing part (21) to the second bearing part (22), and being thinned relative to the first bearing part (21) and the second bearing part (22), and o a flyweight (3) which is fixedly mounted on the damper (2).

    BLISK COMPRISING A HUB HAVING A RECESSED FACE ON WHICH A FILLING MEMBER IS MOUNTED
    6.
    发明申请
    BLISK COMPRISING A HUB HAVING A RECESSED FACE ON WHICH A FILLING MEMBER IS MOUNTED 审中-公开

    公开(公告)号：US20180087389A1

    公开(公告)日：2018-03-29

    申请号：US15554936

    申请日：2016-03-01

    申请人： Safran Aircraft Engines

    发明人： Philippe Gérard Edmond Joly ,  François Jean Comin ,  Laurent Jablonski ,  Damien Merlot ,  Jean-Marc Claude Perrollaz

    IPC分类号： F01D5/34

    CPC分类号： F01D5/34 ,  F05D2220/36

    摘要： A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

    Damping device
    8.
    发明授权
    Damping device 有权

    公开(公告)号：US11536157B2

    公开(公告)日：2022-12-27

    申请号：US16955518

    申请日：2018-12-18

    申请人： SAFRAN AIRCRAFT ENGINES

    发明人： Philippe Gérard Edmond Joly ,  François Jean Comin ,  Charles Jean-Pierre Douguet ,  Laurent Jablonski ,  Romain Nicolas LaGarde ,  Jean-Marc Claude Perrollaz

    IPC分类号： F01D25/04

    摘要： The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.

    Vane with spoiler
    10.
    发明授权
    Vane with spoiler 有权

    公开(公告)号：US10598033B2

    公开(公告)日：2020-03-24

    申请号：US15509063

    申请日：2015-09-03

    申请人： Safran Aircraft Engines

    发明人： Laurent Jablonski ,  Pierre-Guillaume Bardin ,  Philippe Gérard Edmond Joly

    IPC分类号： F01D9/04 ,  F01D5/32 ,  F01D21/04 ,  F01D5/14 ,  F01D5/30

    摘要： Relates to a vane for a turbomachine. The vane (12′) has a blade (13′) and a root (18′) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450′) of the root is connected to a radially internal end (430′) of the leading edge (431′) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.