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    INNER DIAMETER SCALLOP CASE FLANGE FOR A CASE OF A GAS TURBINE ENGINE
    2.
    发明申请
    INNER DIAMETER SCALLOP CASE FLANGE FOR A CASE OF A GAS TURBINE ENGINE 有权
    用于气体涡轮发动机的内径直径的SCALLOP壳法兰

    公开(公告)号：US20160363004A1

    公开(公告)日：2016-12-15

    申请号：US14735299

    申请日：2015-06-10

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Wai Tuck Chow ,  Oleg Ivanov ,  Ron I. Prihar

    IPC: F01D25/24 ,  F01D25/14

    CPC classification number: F01D25/243 ,  F01D25/145 ,  F01D25/24 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/15 ,  F05D2250/611

    Abstract: A case for a gas turbine engine incudes a radial flange with a partial scallop along an inner diameter of the radial flange. A case assembly for a gas turbine engine incudes a first case with an a first radial flange with a partial scallop along an inner diameter of the first radial flange, the partial scallop adjacent to a first aperture thorough the first radial flange and a second case with an a second radial flange with a second aperture thorough the second radial flange the second radial flange mountable to the first radial flange at an interface such that the second aperture is axially aligned with the first aperture and a seal lip that extends from the second case interfaces with said first case at a longitudinal interface

    Abstract translation: 用于燃气涡轮发动机的壳体沿着径向凸缘的内径包含具有部分扇贝的径向凸缘。 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的内径的部分扇形的第一径向凸缘的第一壳体，与通过第一径向凸缘的第一孔相邻的部分扇形带和第二壳体， 第二径向凸缘，其具有穿过所述第二径向凸缘的第二孔，所述第二径向凸缘可在界面处安装到所述第一径向凸缘，使得所述第二孔与所述第一孔轴向对准;以及密封唇，所述密封唇从所述第二壳体界面 所述第一壳体在纵向界面处

    FAN CASE BUSHING
    3.
    发明申请
    FAN CASE BUSHING 审中-公开

    公开(公告)号：US20190309764A1

    公开(公告)日：2019-10-10

    申请号：US16449815

    申请日：2019-06-24

    Applicant: United Technologies Corporation

    Inventor： Wai Tuck Chow ,  Ron I. Prihar

    IPC: F04D29/056 ,  F01D25/24 ,  F04D29/52 ,  F04D29/64 ,  F04D19/00

    Abstract: A bushing including a body portion including a cylinder portion having a bore there through configured to receive a bolt; a flange portion orthogonal and integral to the cylinder portion, the flange portion configured to abut a load bearing surface of a flange; a lip portion orthogonal to and integral to the flange portion proximate the cylinder portion, wherein the lip portion redistributes a flange load.

    Process for repairing turbine engine components
    5.
    发明授权
    Process for repairing turbine engine components 有权

    公开(公告)号：US11434764B2

    公开(公告)日：2022-09-06

    申请号：US16520951

    申请日：2019-07-24

    Applicant: United Technologies Corporation

    Inventor： Robert J. Morris ,  William D. Owen ,  Stuart K. Montgomery ,  Ron I. Prihar

    IPC: F01D5/00 ,  F01D5/02

    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.

    Fan case bushing
    6.
    发明授权
    Fan case bushing 有权

    公开(公告)号：US10352328B2

    公开(公告)日：2019-07-16

    申请号：US14948432

    申请日：2015-11-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Wai Tuck Chow ,  Ron I. Prihar

    IPC: F16D1/033 ,  F04D29/056 ,  F04D19/00 ,  F04D29/52 ,  F04D29/64 ,  F01D25/24

    Abstract: A bushing including a body portion including a cylinder portion having a bore there through configured to receive a bolt; a flange portion orthogonal and integral to the cylinder portion, the flange portion configured to abut a load bearing surface of a flange; a lip portion orthogonal to and integral to the flange portion proximate the cylinder portion, wherein the lip portion redistributes a flange load.

    BRACKET DOUBLER
    9.
    发明申请
    BRACKET DOUBLER 有权
    支架双打

    公开(公告)号：US20160215697A1

    公开(公告)日：2016-07-28

    申请号：US14527175

    申请日：2014-10-29

    Applicant: United Technologies Corporation

    Inventor： Derek W. Anderson ,  Ron I. Prihar ,  William Bogue

    IPC: F02C7/20 ,  F16M13/02 ,  F16L3/02

    CPC classification number: F02C7/20 ,  F02C7/32 ,  F16L3/223 ,  F16L3/237 ,  F16L55/035 ,  F16L57/00

    Abstract: A bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A doubler is mechanically fastened adjacent to the separation. Another bracket assembly for a gas turbine engine includes a bracket base with a separation between a first bended feature and a second bended feature. A cushioned tube support is welded to the bracket base. A doubler is mechanically fastened adjacent to the separation. A method of assembling a bracket assembly for a gas turbine engine includes mechanically fastening a doubler to a bracket base adjacent to a separation between a first bended feature and a second bended feature.

    Abstract translation: 用于燃气涡轮发动机的支架组件包括具有第一弯曲特征和第二弯曲特征之间的间隔的托架基座。 倍增器在分离附近机械固定。 用于燃气涡轮发动机的另一个支架组件包括具有第一弯曲特征和第二弯曲特征之间的间隔的托架基座。 缓冲管支撑件焊接到支架底座。 倍增器在分离附近机械固定。 组装用于燃气涡轮发动机的支架组件的方法包括将倍频器机械地紧固到与第一弯曲特征和第二弯曲特征之间的间隔相邻的支架基座。

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