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    COMBINED FAN CASE ICE LINER AND REAR LINER
    1.
    发明申请
    COMBINED FAN CASE ICE LINER AND REAR LINER 审中-公开

    公开(公告)号：WO2015080787A3

    公开(公告)日：2015-06-04

    申请号：PCT/US2014/055593

    申请日：2014-09-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CLARKSON, Steven

    IPC: F01D25/24

    Abstract: A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. The ice liner section may comprise fiberglass and the rear liner section comprises fiberglass, such that the combined liner comprises a single piece. The combined liner may comprise a plurality of segments in the range of one segment to nine segments. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile that is less than the first cross-sectional profile. The combined liner may comprise an uninterrupted aerodynamic surface.

    FAN CASE ICE LINER FOR TURBOFAN ENGINE
    3.
    发明申请
    FAN CASE ICE LINER FOR TURBOFAN ENGINE 审中-公开
    风箱发动机风箱冰垫

    公开(公告)号：WO2015065526A1

    公开(公告)日：2015-05-07

    申请号：PCT/US2014/039360

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROBERTSON, Thomas, J., Jr. ,  CLARKSON, Steven

    IPC: F02C7/05 ,  F02C7/045 ,  B29C39/02 ,  B29C39/26 ,  B29C43/02 ,  B29C70/06

    CPC classification number: F04D29/522 ,  F01D25/02 ,  F02C7/047 ,  F02C7/05 ,  F04D29/023 ,  F05D2220/32 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603

    Abstract: An ice liner assembly for a fan containment case for a turbofan gas turbine engine is disclosed. The disclosed ice liner assembly includes a plurality of arcuate panels arranged end to end to form a cylindrical liner that is disposed within the fan containment case and aft of the fan and abradable strip liner that circumscribes the fan. Because the plurality of arcuate panels are arranged end to end fashion, the ice liner assembly includes a plurality of splice joints, or a joint between two abutting ends of two arcuate panels. The splice joints are reinforced with molded polymeric splice support cores that are substantially lighter and less expensive than currently employed high density aluminum honeycomb core materials.

    Abstract translation: 公开了一种用于涡轮风扇燃气涡轮发动机的风扇容纳箱的冰套组件。 所公开的冰盖组件包括多个弧形面板，其端对端布置以形成圆柱形衬套，该圆柱形衬套设置在风扇容纳壳体内，风扇后部和可磨损的带状衬套限定风扇。 由于多个弧形面板以端对端的方式布置，所以冰套组件包括多个接合接头，或两个弧形面板的两个邻接端之间的接头。 接头接头用模制的聚合物接头支撑芯加强，其与当前使用的高密度铝蜂窝芯材料相比更轻且更便宜。

    FAN CASE BALLISTIC LINER AND METHOD OF MANUFACTURING SAME
    4.
    发明申请
    FAN CASE BALLISTIC LINER AND METHOD OF MANUFACTURING SAME 审中-公开
    风扇式弹簧衬板及其制造方法

    公开(公告)号：WO2014039198A1

    公开(公告)日：2014-03-13

    申请号：PCT/US2013/053893

    申请日：2013-08-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CLARKSON, Steven

    IPC: B21D51/18 ,  B21D41/02 ,  B21D39/08

    CPC classification number: F01D21/045 ,  B29C53/562 ,  B29C63/34 ,  F01D25/24 ,  F02C7/045 ,  F02C7/057 ,  F02K1/827 ,  Y02T50/672

    Abstract: A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap.

    Abstract translation: 制造具有衬垫的风扇壳体的方法包括以下步骤：提供具有切割和第一直径的圆形横截面的预成型件，使预成型件弯曲以将第一直径减小到第二直径，并将预成型件粘合到 风扇外壳的内表面。 燃气轮机的风扇壳体具有内表面的风扇壳体。 预制件粘附到内表面并具有提供间隙的切口。

    AUXILIARY COMPONENT MOUNTS
    7.
    发明申请
    AUXILIARY COMPONENT MOUNTS 审中-公开
    辅助组件安装

    公开(公告)号：WO2014081500A2

    公开(公告)日：2014-05-30

    申请号：PCT/US2013/059746

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROBERTSON, Thomas, J. ,  CLARKSON, Steven ,  COSTA, Mark, W.

    IPC: F02C7/20

    CPC classification number: F02C7/32 ,  F01D21/045 ,  F02C7/20 ,  F05D2220/32 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2260/311

    Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

    Abstract translation: 公开了一种用于将部件安装到燃气轮机的安装座。 安装件可以包括附接到部件的中心部分和围绕中心部分并延伸到燃气涡轮发动机的凸缘，凸缘包括以预定负载断裂的可熔区域。 还公开了一种保护安装在燃气涡轮发动机上的部件的方法。 该方法可以包括将安装件附接到燃气涡轮发动机的壳体，该安装件包括以预定负载断裂的可熔区域。 该方法还可以包括将部件附接到安装件。 该方法还可以包括当安装座经受预定负载时的易熔区域断裂，将部件从燃气涡轮发动机的壳体上拆下。

    LAYERED ICE LINER
    8.
    发明申请
    LAYERED ICE LINER 审中-公开
    分层冰垫

    公开(公告)号：WO2015094764A1

    公开(公告)日：2015-06-25

    申请号：PCT/US2014/069073

    申请日：2014-12-08

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CLARKSON, Steven ,  BERGETHON, Richard B.

    IPC: F02C7/05

    CPC classification number: F04D29/526 ,  F01D21/045 ,  F02C7/045 ,  F02C7/05 ,  F02K3/06 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

    Abstract: A liner assembly for lining of a gas turbine engine includes a honeycomb core having at least two axially adjacent segments, including a forward segment and an aft segment. An impact resistant layer is disposed against and radially inward of the honeycomb forward segment. A radially interior layer, defining a relatively substantially uninterrupted flowpath over at least a portion of the impact resistant layer and the aft segment, extends against and radially interior of both the impact resistant layer and the honeycomb aft segment.

    Abstract translation: 一种用于燃气涡轮发动机衬套的衬套组件包括具有至少两个轴向相邻段的蜂窝芯，包括前段和后段。 抗冲击层抵靠蜂窝状前段的径向内侧设置。 在耐冲击层和后段的至少一部分上限定相对基本上不间断的流动路径的径向内部层向抗冲击层和蜂窝状后段两侧延伸并径向向内延伸。

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