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    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：US20160258445A1

    公开(公告)日：2016-09-08

    申请号：US15032161

    申请日：2014-05-23

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas J. Robertson, JR. ,  Steven Clarkson

    IPC: F04D29/52 ,  F01D25/02 ,  F04D29/02

    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

    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，其基本上比当前使用的更轻且更便宜

    CORE DRAINAGE SYSTEMS FOR FAN CASE ASSEMBLIES
    4.
    发明申请
    CORE DRAINAGE SYSTEMS FOR FAN CASE ASSEMBLIES 有权
    风扇组件的核心排水系统

    公开(公告)号：US20150159508A1

    公开(公告)日：2015-06-11

    申请号：US14560334

    申请日：2014-12-04

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Robertson, JR. ,  Steven Clarkson

    IPC: F01D25/00 ,  F01D25/24

    CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/32 ,  F05D2260/602 ,  Y02T50/671

    Abstract: A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side.

    Abstract translation: 用于风扇容纳的芯部包括中间芯段和用于通过中间芯段确定的用于流体通道的增压室。 中间芯段具有轴向入口侧，与轴向入口侧相对的轴向出口侧，径向内侧和与径向内侧相对的径向外侧。 径向外侧构造成可操作地连接到圆柱形外壳，并且径向内侧构造成可操作地连接到至少一个弓形面板以形成衬套组件。 气室在靠近径向外侧延伸穿过中间芯段，用于在轴向入口侧和轴向出口侧之间流体通过。

    AUXILIARY COMPONENT MOUNTS
    7.
    发明申请
    AUXILIARY COMPONENT MOUNTS 有权
    辅助组件安装

    公开(公告)号：US20160177840A1

    公开(公告)日：2016-06-23

    申请号：US14410487

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas J. Robertson ,  Steven Clarkson ,  Mark W. Costa

    IPC: F02C7/32 ,  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。

    Instrumentation Boss For Fan Containment Case
    9.
    发明申请
    Instrumentation Boss For Fan Containment Case 有权
    风扇防护箱仪表板

    公开(公告)号：US20160010503A1

    公开(公告)日：2016-01-14

    申请号：US14613755

    申请日：2015-02-04

    Applicant: United Technologies Corporation

    Inventor： Thomas J. Robertson, JR. ,  Mark W. Costa ,  Steven Clarkson

    IPC: F01D25/28 ,  G01D11/30 ,  F01D25/24

    CPC classification number: F01D25/28 ,  F01D25/24 ,  F05D2230/60 ,  F05D2240/90 ,  F05D2300/121 ,  F05D2300/603 ,  G01D11/30 ,  Y02T50/672

    Abstract: A method for installing a mounting hole through a wall of a fan case of a gas turbine engine is disclosed. The method may comprise: 1) installing a pilot hole through the wall of the fan case at an angle perpendicular to an outer surface of the wall, 2) inserting a boss through the pilot hole, 3) bonding the boss to the wall of the fan case, and 4) installing the mounting hole through the boss at an off-axis angle with respect to the angle perpendicular to the outer surface of the wall.

    Abstract translation: 公开了一种通过燃气涡轮发动机的风扇壳体的壁安装安装孔的方法。 该方法可以包括：1）以垂直于壁的外表面的角度，通过风扇壳体的壁安装导向孔，2）将凸台穿过导向孔，3）将凸台粘合到 风扇壳体，以及4）相对于垂直于壁的外表面的角度以离轴角度安装安装孔。

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