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    IMPROVED FAN CASE DRAINAGE SYSTEM
    11.
    发明申请
    IMPROVED FAN CASE DRAINAGE SYSTEM 审中-公开
    改进风扇排水系统

    公开(公告)号：WO2014043493A1

    公开(公告)日：2014-03-20

    申请号：PCT/US2013/059692

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CLARKSON, Steven ,  ROBERTSON, Thomas J.

    IPC: F01D25/24 ,  F02C7/00 ,  F02K3/00

    CPC classification number: F01D25/32 ,  Y02T50/672 ,  Y10T137/8376

    Abstract: A casing for installation in more than one circumferential position, includes a shell into which fluid may drain, a pre-installation bottom dead center of the shell, a first post-installation bottom dead center of the shell wherein the first post-installation bottom dead center of the shell is circumferentially rotated a first number of degrees in a first direction from the pre-installation bottom dead center of the shell. The non-limiting embodiment further discloses a first ramp disposed between the first post-installation bottom dead center of the shell and the pre-installation bottom dead center of the shell for directing fluid from the first post-installation bottom dead center of the shell to the pre-installation bottom dead center of the shell.

    Abstract translation: 一种用于安装在多于一个周向位置的壳体，包括可以排出流体的壳体，壳体的预安装下死点，壳体的第一后安装底部死点，其中第一后安装底部死点 壳体的中心沿壳体的预安装下死点在第一方向上周向旋转第一数量。 非限制性实施例还公开了一种设置在壳体的第一安装后下死点和壳体的预安装下死点之间的第一斜坡，用于将流体从壳体的第一后安装底部死点引导到 壳体的预安装下死点。

    COMBINED FAN CASE ICE LINER AND REAR LINER
    12.
    发明公开
    COMBINED FAN CASE ICE LINER AND REAR LINER 审中-公开
    联合EISISOLIERUNG和后保温风扇罩

    公开(公告)号：EP3049643A2

    公开(公告)日：2016-08-03

    申请号：EP14866210.9

    申请日：2014-09-15

    Applicant: United Technologies Corporation

    Inventor： CLARKSON, Steven

    IPC: F01D25/24

    CPC classification number: F01D25/02 ,  F01D21/14 ,  F01D25/24 ,  F02K1/78 ,  F02K1/82 ,  F05D2220/323 ,  F05D2230/53 ,  F05D2240/11 ,  F05D2240/14 ,  F05D2260/607 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/675

    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
    15.
    发明公开
    FAN CASE ICE LINER FOR TURBOFAN ENGINE 审中-公开
    用于涡轮增压发动机的风扇套内衬

    公开(公告)号：EP3063386A1

    公开(公告)日：2016-09-07

    申请号：EP14858095.4

    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壳体的冰衬里组件。 所公开的冰块衬垫组件包括首尾相连布置的多个弓形板，以形成圆柱形衬垫，该衬垫布置在风扇容纳壳内并位于风扇外围的可磨损条衬里。 因为多个弧形面板以首尾相连的方式布置，所以冰块组件包括多个拼接接头，或者两个弧形面板的两个邻接端之间的接头。 拼接接头用模制的聚合物接头支撑芯增强，该芯比现在采用的高密度铝蜂窝芯材料明显更轻并且更便宜。

    LINERS FOR TURBOMACHINERY CASES
    17.
    发明公开
    LINERS FOR TURBOMACHINERY CASES 审中-公开
    涡轮机械案例的内衬

    公开(公告)号：EP3290658A1

    公开(公告)日：2018-03-07

    申请号：EP17193286.6

    申请日：2015-12-15

    Applicant: United Technologies Corporation

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

    IPC: F01D21/04 ,  F01D25/24 ,  F02K3/06

    CPC classification number: F01D25/24 ,  F01D21/045 ,  F01D25/005 ,  F02K3/06 ,  F05D2230/60 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2300/603 ,  Y02T50/672

    Abstract: A method of making a liner (100; 200) for a turbomachinery case (26) includes overlaying a reinforcing layer (102; 202, 204) and a release layer (104; 206). The method also includes spiral coiling the reinforcing layer and the release layer about an axis (A) of the liner such that a radially inner surface (112) of the release layer radially overlays a radially outer surface (108) of the reinforcing layer.

    Abstract translation: 一种制造用于涡轮机壳体（26）的衬套（100; 200）的方法包括覆盖加强层（102; 202,204）和释放层（104; 206）。 该方法还包括将增强层和释放层绕内衬的轴线（A）螺旋卷绕，使得释放层的径向内表面（112）径向覆盖增强层的径向外表面（108）。

    CORE CASE HEATING FOR GAS TURBINE ENGINES
    18.
    发明公开
    CORE CASE HEATING FOR GAS TURBINE ENGINES 审中-公开
    KERNTRIEBWERKGEHÄUSEHEIZUNGFÜRGASTURBINENMOTOREN

    公开(公告)号：EP3034815A1

    公开(公告)日：2016-06-22

    申请号：EP15200193.9

    申请日：2015-12-15

    Applicant: United Technologies Corporation

    Inventor： CLARKSON, Steven ,  VAN NESS, Daniel L. ,  REMBISH, Paul Thomas

    IPC: F01D25/02 ,  F04D27/02 ,  F02C7/047 ,  F02C7/05

    Abstract: A case for a gas turbine engine includes a core body. The core body defines a longitudinally extending core flow path, a laterally extending bleed air duct coupling the core flow path in fluid communication with the external environment, and a structural member spanning the bleed air duct. A heating element is connected to the core body and is in thermal communication with the structural member.

    Abstract translation: 燃气涡轮发动机的壳体包括芯体。 芯体限定纵向延伸的芯流动路径，连接与外部环境流体连通的芯流动路径的横向延伸的放气管道和横跨排气管道的结构构件。 加热元件连接到芯体并且与结构构件热连通。

    AUXILIARY COMPONENT MOUNTS
    19.
    发明公开
    AUXILIARY COMPONENT MOUNTS 审中-公开
    辅助元件CARRIER

    公开(公告)号：EP2901067A2

    公开(公告)日：2015-08-05

    申请号：EP13856339.0

    申请日：2013-09-13

    Applicant: United Technologies Corporation

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

    IPC: F16M13/00

    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.

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