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    INNER DIAMETER SCALLOP CASE FLANGE FOR A CASE OF A GAS TURBINE ENGINE
    2.
    发明公开
    INNER DIAMETER SCALLOP CASE FLANGE FOR A CASE OF A GAS TURBINE ENGINE 审中-公开
    EINGEHÄUSEINES GASTURBINENMOTORS INNENDURCHMESSER-MUSCHELGEHÄUSEFLANSCH

    公开(公告)号：EP3103972A1

    公开(公告)日：2016-12-14

    申请号：EP16174009.7

    申请日：2016-06-10

    Applicant: United Technologies Corporation

    Inventor： CHOW, Wai Tuck ,  IVANOV, Oleg ,  PRIHAR, Ron I.

    IPC: F01D25/24

    Abstract: A case (70) for a gas turbine engine incudes a radial flange (82) with a partial scallop (180) along an inner diameter (190) of the radial flange (82). A case assembly for a gas turbine engine incudes a first case (70) with an a first radial flange (82) with a partial scallop (180) along an inner diameter (190) of the first radial flange (82). The partial scallop (80) is adjacent to a first aperture (122) through the first radial flange (82). The assembly also includes a second case (68) with an a second radial flange (80) with a second aperture (120) through the second radial flange (80) the second radial flange (80) mountable to the first radial flange (82) at an interface (130) such that the second aperture (120) is axially aligned with the first aperture (122). The second case (68) also includes a seal lip (142) that extends from the second case (68) and interfaces with said first case (70) at a longitudinal interface (144).

    Abstract translation: 用于燃气涡轮发动机的壳体（70）沿着径向凸缘（82）的内径（190）包含具有部分扇形齿（180）的径向凸缘（82）。 用于燃气涡轮发动机的壳体组件包括具有沿着第一径向凸缘（82）的内径（190）的具有部分扇形齿（180）的第一径向凸缘（82）的第一壳体（70）。 部分扇贝（80）通过第一径向凸缘（82）与第一孔（122）相邻。 组件还包括具有第二径向凸缘（80）的第二壳体（68），第二径向凸缘（80）具有穿过第二径向凸缘（80）的第二孔径（120），可安装到第一径向凸缘（82）的第二径向凸缘（80） 在接口（130）处使得第二孔（120）与第一孔（122）轴向对准。 第二壳体（68）还包括从第二壳体（68）延伸并且在纵向界面（144）处与所述第一壳体（70）接合的密封唇缘（142）。

    CASING FLANGE COUPLING ASSEMBLY AND CORRESPONDING METHOD OF REDISTRIBUTING A FLANGE LOAD
    5.
    发明公开
    CASING FLANGE COUPLING ASSEMBLY AND CORRESPONDING METHOD OF REDISTRIBUTING A FLANGE LOAD 审中-公开
    法兰法兰连接组件及法兰重新加载的对应方法

    公开(公告)号：EP3170994A1

    公开(公告)日：2017-05-24

    申请号：EP16200352.9

    申请日：2016-11-23

    Applicant: United Technologies Corporation

    Inventor： CHOW, Wai Tuck ,  PRIHAR, Ron I.

    IPC: F01D25/24

    Abstract: A bushing (60) including a body portion (62) including a cylinder portion (66) having a bore (64) there through configured to receive a bolt (24); a flange portion (74) orthogonal and integral to the cylinder portion (66), the flange portion (74) configured to abut a load bearing surface (38) of a flange (18); a lip portion (80) orthogonal to and integral to the flange portion (74) proximate the cylinder portion (66), wherein the lip portion (80) redistributes a flange load.

    Abstract translation: 1。一种衬套（60），包括：主体部分（62），该主体部分包括圆柱部分（66），该圆柱部分具有构造成接收螺栓（24）的穿孔（64）; 与所述缸体部分正交且整体形成的凸缘部分，所述凸缘部分构造成邻接凸缘的承载表面; 与所述凸缘部分（74）正交并与所述凸缘部分（74）接近的所述圆筒部分（66）整体形成的唇部分（80），其中所述唇部分（80）重新分配凸缘负载。

    PROCESS FOR REPAIRING TURBINE ENGINE COMPONENTS
    6.
    发明公开
    PROCESS FOR REPAIRING TURBINE ENGINE COMPONENTS 审中-公开

    公开(公告)号：EP3611337A2

    公开(公告)日：2020-02-19

    申请号：EP19190609.8

    申请日：2019-08-07

    Applicant: United Technologies Corporation

    Inventor： MORRIS, Robert, J. ,  OWEN, William D. ,  MONTGOMERY, Stuart K. ,  PRIHAR, Ron I.

    IPC: F01D5/00 ,  F01D5/14 ,  B23P6/00

    Abstract: A process for repairing an aircraft engine component includes receiving a plurality of component measurements of a damaged component, comparing the plurality of component measurements of the damaged component to a finite element model of an ideal component, generating a finite element model of the damaged component based at least partially on the comparison, determining a corrective material removal operation based at least in part on the finite element model of the damaged component, and removing material from the damaged component according to the corrective material removal operation, thereby creating a repaired component.

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