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    Thermal mechanical dimple array for a combustor wall assembly
    1.
    发明授权
    Thermal mechanical dimple array for a combustor wall assembly 有权

    公开(公告)号：US10281152B2

    公开(公告)日：2019-05-07

    申请号：US15105409

    申请日：2014-12-19

    Applicant: United Technologies Corporation

    Inventor： Hoyt Y. Chang

    IPC: F02G3/00 ,  F23R3/00 ,  F23R3/50

    Abstract: A thermal mechanical dimple array for combustor liners of gas turbine engines are located at known hot spots along liner to reduce stress and minimize cracking. Such arrays have indentations in the liners at the hot spots that act to thermal mechanically flex the liner at the hot spot away from the heat source and distribute stresses such that cracking of the liner is reduced and durability is improved.

    THERMAL MECHANICAL DIMPLE ARRAY FOR A COMBUSTOR WALL ASSEMBLY
    2.
    发明申请
    THERMAL MECHANICAL DIMPLE ARRAY FOR A COMBUSTOR WALL ASSEMBLY 审中-公开
    用于燃气壁组件的热机械二维阵列

    公开(公告)号：US20160320060A1

    公开(公告)日：2016-11-03

    申请号：US15105409

    申请日：2014-12-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Hoyt Y. Chang

    IPC: F23R3/00 ,  F23R3/50

    CPC classification number: F23R3/002 ,  F23R3/007 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03041 ,  F23R2900/03044 ,  Y02T50/675

    Abstract: A thermal mechanical dimple array for combustor liners of gas turbine engines are located at known hot spots along liner to reduce stress and minimize cracking. Such arrays have indentations in the liners at the hot spots that act to thermal mechanically flex the liner at the hot spot away from the heat source and distribute stresses such that cracking of the liner is reduced and durability is improved.

    Abstract translation: 用于燃气涡轮发动机的燃烧器衬套的热机械凹坑阵列位于沿着衬套的已知热点处以减少应力并使开裂最小化。 这种阵列在热点处的衬垫上具有凹陷，其作用为在离热源的热点处热衬套的热机械挠曲，并且分布应力，使得衬垫的开裂减小并且耐久性得到改善。

    COMBUSTOR LINER
    4.
    发明申请
    COMBUSTOR LINER 审中-公开

    公开(公告)号：US20160215980A1

    公开(公告)日：2016-07-28

    申请号：US14917379

    申请日：2014-08-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Hoyt Y. Chang

    IPC: F23R3/00 ,  F23R3/06

    CPC classification number: F23R3/007 ,  F02C7/24 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03044 ,  Y02T50/672 ,  Y02T50/675

    Abstract: A combustor includes a liner and a support. The liner includes first and second spaced apart liner walls defining a combustion chamber therebetween, and an end wall joining the first and second liner walls at a forward end. The support is configured to resiliently support the liner and includes first and second spaced apart support walls having first and second retainers configured to capture aft ends of the first and second liner walls. A gas turbine engine and a method of assembling a combustor are also disclosed.

    Abstract translation: 燃烧器包括衬套和支撑件。 衬套包括在其间限定燃烧室的第一和第二间隔开的衬套壁，以及在前端连接第一和第二衬套壁的端壁。 支撑件被构造成弹性地支撑衬套并且包括第一和第二间隔开的支撑壁，其具有构造成捕获第一和第二衬套壁的后端的第一和第二保持器。 还公开了一种燃气涡轮发动机和组装燃烧器的方法。

    Combustor panel having material transition region
    7.
    发明授权
    Combustor panel having material transition region 有权

    公开(公告)号：US10451280B2

    公开(公告)日：2019-10-22

    申请号：US14623379

    申请日：2015-02-16

    Applicant: United Technologies Corporation

    Inventor： Hoyt Y. Chang

    IPC: F23R3/00 ,  F23R3/60 ,  B29C64/00 ,  B33Y80/00 ,  B33Y10/00 ,  B33Y50/00 ,  B29L31/00

    Abstract: A combustor thermal shield is provided. The combustor thermal shield may have a combustor panel that may protect a surface of a combustor from heat and/or flame. The combustor thermal shield may be mounted to the combustor by an attachment stud formed as a unitary body with the combustor panel. The combustor panel and the attachment stud may be made of different materials. A transition region may be disposed between the attachment stud and the combustor thermal shield and formed as a unitary body with the combustor panel and the attachment stud. The transition region may be made of a mixture of the different materials. The mixture may vary according to a gradient as a function of proximity to the combustor panel and the attachment stud.

    AUTOMATED LAMINATE COMPOSITE SOLID PLY GENERATION
    10.
    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：US20160250812A1

    公开(公告)日：2016-09-01

    申请号：US15028557

    申请日：2014-10-01

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James T. Roach ,  Ammon Hepworth ,  Hoyt Y. Chang ,  Blake J. Luczak

    IPC: B29C70/38 ,  B29D99/00 ,  B29C70/34

    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。

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