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    3D CMC MATERIAL HAVING A THERMAL PROTECTION LAYER
    2.
    发明申请
    3D CMC MATERIAL HAVING A THERMAL PROTECTION LAYER 审中-公开

    公开(公告)号：WO2019194860A2

    公开(公告)日：2019-10-10

    申请号：PCT/US2018/051276

    申请日：2018-09-17

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： MORRISON, Jay A. ,  BRUNELLI, Marco Claudio Pio ,  MERRILL, Gary B.

    Abstract: A component (10) is disclosed having an outer surface (22) of a ceramic matrix composite material (12), wherein the outer surface (22) is part of a thermal protective layer (24) that is 10-50% of a total 3D CMC thickness. The component further includes an inner surface (23) of the ceramic matrix composite material (12). Reinforcing fibers (20) extend throughout the ceramic matrix composite material (12), wherein the reinforcing fibers (20) extend unitarily or interconnectedly from the outer surface (22) to the inner surface (23).

    A DUCTING ARRANGEMENT FOR DIRECTING COMBUSTION GAS
    5.
    发明申请
    A DUCTING ARRANGEMENT FOR DIRECTING COMBUSTION GAS 审中-公开
    用于指导燃烧气体的排水装置

    公开(公告)号：WO2017023330A1

    公开(公告)日：2017-02-09

    申请号：PCT/US2015/043974

    申请日：2015-08-06

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： MORRISON, Jay A. ,  CHARRON, Richard C. ,  KUMAR, Manish ,  MONTGOMERY, Matthew D.

    IPC: F01D9/02

    CPC classification number: F01D9/023 ,  F05D2250/38

    Abstract: A ducting arrangement (10), including: an annular duct (38) having a plurality of discrete IEPs (18) secured together to form the annular duct that defines an annular chamber (14) configured to deliver an annular flow of combustion gases directly onto turbine blades without a turning vane, wherein the annular duct defines a chamber mid-annulus (98); an IEP intermediate portion (34) for each IEP, each IEP intermediate portion defining a respective intermediate flow path (48) in fluid communication with the annular chamber and defining an intermediate flow path axis (192); and a cone (16) for each IEP intermediate portion, each cone defining a cone flow path (46), the cone flow path defining a cone flow path axis (190). When viewed from upstream toward downstream along a longitudinal axis (134) of the gas turbine engine each cone flow path axis intersects a respective intermediate flow path axis (192).

    Abstract translation: 一种管道装置（10），包括：环形管道（38），其具有固定在一起以形成环形管道的多个离散IEP（18），该环形管道限定环形室（14），其被配置成将环形气流直接传递到 不具有转动叶片的涡轮机叶片，其中所述环形管道限定腔室中间环（98）; 每个IEP中间部分限定与环形室流体连通并且限定中间流路轴线（192）的相应的中间流路（48）; 以及用于每个IEP中间部分的锥体（16），每个锥体限定锥形流动路径（46），锥形流动路径限定锥形流动路径轴线（190）。 当从燃气涡轮发动机的纵向轴线（134）的上游向下游观察时，每个锥形流路轴线与相应的中间流路轴线（192）相交。

    TURBINE AIRFOIL COMPRISING A CORE SUPPORT STRUCTURE AND A HEAT RESISTANT OUTER SHELL
    8.
    发明申请
    TURBINE AIRFOIL COMPRISING A CORE SUPPORT STRUCTURE AND A HEAT RESISTANT OUTER SHELL 审中-公开
    包含核心支撑结构和耐热外壳的涡轮机叶片

    公开(公告)号：WO2017105380A1

    公开(公告)日：2017-06-22

    申请号：PCT/US2015/065424

    申请日：2015-12-14

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： DYER, Zachary D ,  JAMES, Allister William ,  SHINDE, Sachin R. ,  MORRISON, Jay A.

    IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/06

    CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D9/065 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2260/37 ,  F05D2300/175 ,  F05D2300/6033

    Abstract: An airfoil (30) for a turbine (10), wherein the airfoil (30) includes leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The airfoil (30) includes a core support structure (34) having first (46) and second (54) support sections that include first (50) and second (56) air inlets, respectively. The airfoil (30) also includes at least one first air channel (62) that extends from the first air inlet (50) and through the first support section (46) to an associated air exit hole (60). In addition, the airfoil (30) includes at least one truss (58) connected between the first (46) and second (54) support sections and at least one second air channel (66) that extends from the second air inlet (56) and through the second support section (54), truss (58) and first support section (46) to an associated air exit hole (60). Further, the airfoil (30) includes a high heat resistant outer shell (32), wherein a portion (48) of the core support structure (30) is located within the outer shell (32). The outer shell may include first and second high heat resistant members.

    Abstract translation: 一种用于涡轮机（10）的翼型件（30），其中所述翼型件（30）包括前缘（36​​）和后缘（38）边缘以及高（40）和低（42）压力表面。 翼型件（30）包括具有分别包括第一（50）和第二（56）进气口的第一支架部分（46）和第二支架部分（54）的芯支撑结构（34）。 翼型件30还包括至少一个第一空气通道62，该第一空气通道62从第一空气入口50并通过第一支撑部分46延伸到相关的空气出口孔60。 此外，翼型件30包括连接在第一支撑部分46和第二支撑部分54之间的至少一个桁架58以及从第二空气入口56延伸的至少一个第二空气通道66， 并通过第二支撑部分（54），桁架（58）和第一支撑部分（46）到达相关的空气出口孔（60）。 此外，翼型件（30）包括高耐热外壳（32），其中芯支撑结构（30）的一部分（48）位于外壳（32）内。 外壳可以包括第一和第二高耐热构件。

    REINFORCED CERAMIC MATRIX COMPOSITE COMPONENTS
    10.
    发明申请
    REINFORCED CERAMIC MATRIX COMPOSITE COMPONENTS 审中-公开

    公开(公告)号：WO2020112076A1

    公开(公告)日：2020-06-04

    申请号：PCT/US2018/062445

    申请日：2018-11-26

    Applicant: SIEMENS AKTIENGESELLSCHAFT ,  SIEMENS ENERGY, INC.

    Inventor： MORRISON, Jay A.

    IPC: F01D5/28

    Abstract: There is provided a reinforced ceramic matrix composite component (30) and a method (100) for making the same, the components (30) having an airfoil (32) having fiber material (62) hosted with a ceramic matrix (63), the fiber material (62) woven in successive layers about spanwise extending reinforcement members (55) to define the airfoil (32).

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