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    Method and system for detecting damage to the rotor of an aircraft engine
    2.
    发明申请
    Method and system for detecting damage to the rotor of an aircraft engine 失效
    用于检测飞机发动机转子损坏的方法和系统

    公开(公告)号：US20040060347A1

    公开(公告)日：2004-04-01

    申请号：US10445935

    申请日：2003-05-28

    Applicant: SNECMA MOTEURS ,  SNECMA SERVICES

    Inventor： Patrick Comperat ,  Philippe Even

    IPC: G01M001/00

    CPC classification number: G01H1/006 ,  F01D21/045 ,  F01D25/04 ,  G01M15/12 ,  G01M15/14

    Abstract: The invention relates to detecting damage to the rotor of an aircraft engine that includes means for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method comprises the following steps: reading said acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data; calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; comparing the modulus of said vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of said vector difference exceeds said predetermined threshold value, said steps being performed after said determined flight has been completed.

    Abstract translation: 本发明涉及检测飞机发动机的转子的损坏，其包括用于测量振动和速度的装置，以便获得与转子速度有关的数据，以及在确定的飞行期间转子振动的振幅和相位。 该方法包括以下步骤：读取所述获取的数据; 基于所述获取的数据计算确定的转子速度范围上的平均振动矢量; 计算所述确定的飞行的平均振动矢量与所述转子速度范围的参考飞行的平均振动矢量之间的矢量差; 将所述矢量差的模量与预定阈值进行比较; 以及当所述矢量差的模量超过所述预定阈值时发出警告信号，所述步骤在所述确定的飞行完成之后执行。

    Rotary assembly for a turbomachine
    6.
    发明授权
    Rotary assembly for a turbomachine 有权

    公开(公告)号：US10662795B2

    公开(公告)日：2020-05-26

    申请号：US15024752

    申请日：2014-09-23

    Applicant: Snecma

    Inventor： Mathieu Louis Jean Leduc ,  Pierre-Louis Alexandre Carlos ,  Clement Roussille

    IPC: F01D11/00 ,  F01D5/30 ,  F01D5/12

    Abstract: The invention concerns a rotary assembly for a turbomachine, comprising a disk of which the outer periphery is formed from an alternation of cavities and teeth (12), and blades extending radially from the disk and of which the roots (16) are engaged axially and held radially in the cavities of the disk. According to the invention, the teeth of the disk and the blade roots comprise, at the upstream and/or downstream axial ends of same, axial shoulders (74, 76) disposed circumferentially end-to-end in alternation and together forming a cylindrical surface (78) facing radially towards the inside of the disk.

    Fuel injector for a turbine engine
    7.
    发明授权
    Fuel injector for a turbine engine 有权

    公开(公告)号：US10563586B2

    公开(公告)日：2020-02-18

    申请号：US15026082

    申请日：2014-09-24

    Applicant: Snecma

    Inventor： Christophe Chabaille ,  Sébastien Loval

    IPC: F02C7/22 ,  F23R3/28

    Abstract: A fuel injector (10) such as an injector for an annular combustion chamber of a turbine engine, comprising a downstream head (16) having a central outlet (22) and an annular peripheral outlet (24) surrounding the central outlet (22), and an injector arm (12) upstream of the head (16) comprising coaxial central channel (18) and annular channel (20), characterised in that the central channel (18) is in fluid communication with the peripheral outlet (24) and the annular channel (20) is in fluid communication with the central outlet (22).

    Balanced turbine engine portion and turbine engine
    8.
    发明授权
    Balanced turbine engine portion and turbine engine 有权

    公开(公告)号：US10415424B2

    公开(公告)日：2019-09-17

    申请号：US15037549

    申请日：2014-11-24

    Applicant: SNECMA

    Inventor： Jean-Luc Le Strat ,  Herve Pohier

    IPC: F01D25/04 ,  F01D9/02 ,  F02C7/04 ,  F01D5/02 ,  G01M1/36 ,  F16F15/34

    Abstract: A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.

    Device for fixing two parts together
    9.
    发明授权
    Device for fixing two parts together 有权

    公开(公告)号：US10393158B2

    公开(公告)日：2019-08-27

    申请号：US14896884

    申请日：2014-06-11

    Applicant: SNECMA

    Inventor： Bertrand Boedot

    IPC: F16B5/02 ,  F16B37/12 ,  F16B41/00

    Abstract: The disclosure relates to a fixing device for fixing a first part and a second part together. The fixing device may include a nut non-rigidly coupled to the first part. The first part may have a fixing flange with at least one orifice positioned to accept a threaded shank coupled to the second part. A retainer may be proximate an inner diameter of the at least one orifice positioned to retain the nut within the fixing flange before the nut is screwed onto the threaded shank. The nut may have an externally threaded portion which may couple to the internally threaded portion of the orifice in the flange or of an element attached to the flange and to pass completely through the internally threaded portion until it is housed in a cavity for axially retaining the nut. Therefore, the nut may rotate freely before it is fastened to the threaded shank. The disclosure also relates to a turbomachine that utilizes this device and to an associated fixing method.

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