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    FLOW STRAIGHTENER UNIT COMPRISING A CENTRING AND ATTACHMENT PLATE
    1.
    发明申请
    FLOW STRAIGHTENER UNIT COMPRISING A CENTRING AND ATTACHMENT PLATE 有权

    公开(公告)号：US20210396143A1

    公开(公告)日：2021-12-23

    申请号：US17292122

    申请日：2019-11-08

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Alexandre Bernard Marie BOISSON ,  Kaelig Merwen ORIEUX

    IPC: F01D9/04 ,  F01D5/28

    Abstract: The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).

    IMPROVED TURBMACHINE FAN DISC
    3.
    发明申请
    IMPROVED TURBMACHINE FAN DISC 有权

    公开(公告)号：US20210189893A1

    公开(公告)日：2021-06-24

    申请号：US17057550

    申请日：2019-05-20

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Thomas Alain DE GAILLARD ,  Alexandre Bernard Marie BOISSON ,  Rémi Roland Robert MERCIER ,  Alexis Thomas CHABOUD

    IPC: F01D5/30 ,  F04D29/32

    Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of axial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.

    TURBINE ENGINE INCLUDING A HEAT EXCHANGER FORMED IN A PLATFORM
    5.
    发明申请
    TURBINE ENGINE INCLUDING A HEAT EXCHANGER FORMED IN A PLATFORM 审中-公开

    公开(公告)号：US20200284160A1

    公开(公告)日：2020-09-10

    申请号：US16809637

    申请日：2020-03-05

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Cedric ZACCARDI ,  Alexandre Bernard Marie BOISSON ,  Christophe Marcel Lucien PERDRIGEON ,  Catherine PIKOVSKY

    IPC: F01D25/12

    Abstract: The invention proposes a turbine engine (10) of an aircraft including a primary air flow duct (16) and a secondary air flow duct (20) which is located around the primary duct (16), the secondary duct (20) including a stator (52) including a plurality of blades distributed around a main axis (A) of the turbine engine (10) and which includes inter-blade platforms (80) each one of which is located between the radially internal ends (56) or between the radially external ends (58) of two adjacent blades (54), each platform (80) including a wall (82) partially delimiting the secondary duct (20), and including a fluid circuit (40), which includes a heat exchanger (44) formed by at least one of the platforms (80), characterised in that the platform (80) includes a line (84) that has an inlet port (90) of the fluid and a fluid outlet port (92), and in that the fluid circuit (40) includes a distributor (104) associated with each port (90, 92) of said at least one platform (80) with the rest of the fluid circuit (40) and of which each distributor is axially offset with respect to said platform (80) along the main axis (A) in one direction or the other.

    COMPOSITE OUTLET GUIDE VANE WITH METAL FASTENER FOR A TURBOMACHINE
    6.
    发明申请
    COMPOSITE OUTLET GUIDE VANE WITH METAL FASTENER FOR A TURBOMACHINE 审中-公开

    公开(公告)号：US20200025001A1

    公开(公告)日：2020-01-23

    申请号：US16512931

    申请日：2019-07-16

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Alexandre Bernard Marie BOISSON ,  Larry Sylvio Laborieux ,  Kaëlig Merwen Orieux

    IPC: F01D9/04 ,  F01D25/06

    Abstract: The invention describes an outlet guide vane (1) for a fan (2) of a turbomachine, comprising: a blade (10) made of composite material and having a radial inner end (101), a first metal fastener portion (11) fastened to the radial inner end (101), at least a first platform (13) extending transversely with respect to the blade (10) in the vicinity of its radial inner end (101), the first metal fastener portion (11) being configured to be mounted on and fastened to an upstream flange (62) and to a downstream flange (63) of a hub (6), the first platform (13) being monolithic with the first metal fastener portion (11) or with the blade (10). The invention also relates to a rectifier wheel (3) and to a turbomachine comprising such an outlet guide vane (1).

    PREFORM AND ONE-PIECE VANE FOR TURBOMACHINE
    10.
    发明申请
    PREFORM AND ONE-PIECE VANE FOR TURBOMACHINE 审中-公开

    公开(公告)号：US20190381696A1

    公开(公告)日：2019-12-19

    申请号：US16489791

    申请日：2018-02-19

    Applicant: SAFRAN AIRCRAFT ENGINES

    Inventor： Jérémy GUIVARC'H ,  Alexandre Bernard Marie BOISSON ,  Thomas Alain DE GAILLARD ,  Gilles Pierre-Marie NOTARIANNI

    IPC: B29B11/16 ,  B29C70/22

    Abstract: A fiber preform for a turbine engine blade, the preform comprising a main fiber structure (40) obtained by a single piece of three-dimensional weaving, said main first structure (40) comprising a first longitudinal segment (41) suitable for forming a blade root, a second longitudinal segment (42) extending the first longitudinal segment (41) and suitable for forming an airfoil portion (22), and a first transverse segment (51) extending transversely from the junction (49) between the first and second longitudinal segments (41, 42) and suitable for forming a first tongue for a first platform, wherein the first transverse segment (51) extends axially over a length that is less than 30%, preferably less than 15%, of the length of the junction (49) between the first and second longitudinal segments (41, 42).

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