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    AUTOMATED LAMINATE COMPOSITE SOLID PLY GENERATION
    1.
    发明申请
    AUTOMATED LAMINATE COMPOSITE SOLID PLY GENERATION 审中-公开
    自动化层压复合固体发生

    公开(公告)号：WO2015057391A1

    公开(公告)日：2015-04-23

    申请号：PCT/US2014/058560

    申请日：2014-10-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROACH, James T. ,  HEPWORTH, Ammon ,  CHANG, Hoyt ,  LUCZAK, Blake J.

    IPC: B44C3/02

    CPC classification number: B29C70/386 ,  B29C70/345 ,  B29C70/48 ,  B29D99/0025 ,  B29K2075/00 ,  B29K2105/0872 ,  B29L2031/082 ,  F01D5/282 ,  F01D25/24

    Abstract: A method for creating a laminate design geometry for a composite component according to an exemplary aspect of the present disclosure includes, among other things, defining a spatial volume of a solid defined between a plurality of external surface boundaries, defining an offset boundary spaced by an offset value from one of the plurality of external surface boundaries to define a region in which a ply is to be received, defining a partitioning boundary dividing the region into a ply portion and a resin portion; and repeating the steps of defining an offset boundary and defining a partitioning boundary by defining an offset boundary from any one of the plurality of external surface boundaries and the offset boundary in a previous iteration of defining an offset boundary.

    Abstract translation: 根据本公开的示例性方面，用于创建用于复合部件的层压板设计几何形状的方法包括限定在多个外表面边界之间限定的固体的空间体积，所述实体限定了由 从所述多个外表面边界中的一个边界偏移值来限定其中要接收层的区域，限定将所述区域分成帘布层部分和树脂部分的划分边界; 以及重复以下步骤：定义偏移边界并通过在前一次定义偏移边界的迭代中通过从多个外表面边界和偏移边界中的任一个定义偏移边界来限定分割边界。

    THERMOPLASTIC NOSECONE FOR A TURBINE ENGINE
    3.
    发明申请
    THERMOPLASTIC NOSECONE FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：WO2014120123A3

    公开(公告)日：2014-08-07

    申请号：PCT/US2013/023635

    申请日：2013-01-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROACH, James T.

    IPC: F02C7/20

    Abstract: A nosecone for a turbine engine includes a nosecone body and a nosecone mount. The nosecone body extends along an axis between a tip end and a base end. The nosecone body is configured from or otherwise includes thermoplastic material. The nosecone body includes a shell and an arrangement of ribs, which structurally support at least a portion of the shell. A thickness of the arrangement of ribs is greater than or substantially equal to approximately one half of a thickness of the shell. The nosecone mount is adapted to connect the nosecone body to a component of the turbine engine.

    COMPOSITE AIRFOIL BONDED TO A METALLIC ROOT
    4.
    发明申请
    COMPOSITE AIRFOIL BONDED TO A METALLIC ROOT 审中-公开
    复合材料粘结到金属根

    公开(公告)号：WO2014204573A1

    公开(公告)日：2014-12-24

    申请号：PCT/US2014/034698

    申请日：2014-04-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ROACH, James T. ,  COOK, Grant O., III.

    IPC: F01D5/30 ,  F01D5/14 ,  F04D29/34

    CPC classification number: F04D29/388 ,  B23P15/04 ,  F01D5/147 ,  F01D5/282 ,  F01D5/30 ,  F04D29/322 ,  F04D29/324 ,  F04D29/34 ,  F05D2220/36 ,  F05D2230/232 ,  F05D2240/303

    Abstract: The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an attachment feature (530). The attachment feature (530) may allow the composite body (510) to be attached to a rotor (200). The airfoil (500) may also have a metallic edge (550) which is TLP bonded to the composite body (510) via a co-molded edge (540).

    Abstract translation: 本公开涉及结合到金属根的复合翼型件。 复合体（510）可以形成有金属共模塑细节（520）。 共模塑细节（520）可以是结合到附着特征（530）的瞬态液相（TLP）。 附接特征（530）可以允许复合体（510）附接到转子（200）。 翼型件（500）也可以具有金属边缘（550），其通过共模制边缘（540）与TLP结合到复合体（510）上。

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