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    BENCH AFT SUB-ASSEMBLY FOR TURBINE EXHAUST CASE FAIRING
    1.
    发明申请
    BENCH AFT SUB-ASSEMBLY FOR TURBINE EXHAUST CASE FAIRING 审中-公开
    用于涡轮机排气箱的BENCH AFT组件

    公开(公告)号：WO2014197037A2

    公开(公告)日：2014-12-11

    申请号：PCT/US2014/023065

    申请日：2014-03-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CONWAY, Chuong ,  LILES, Jason David ,  SCOTT, Jonathan Ariel

    IPC: F01D9/04 ,  F01D25/28 ,  F01D25/30 ,  F02C7/20

    CPC classification number: F02C7/20 ,  F01D25/162 ,  F01D25/246 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/232 ,  F05D2230/50 ,  F05D2240/90

    Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.

    Abstract translation: 用于涡轮机框架的整流罩子组件88包括内环50，外环48和多个支柱。 内环由多个内部段82形成。外环由多个外部段80形成。多个支撑壳84,86连接内部环48和外部环50.在另一个实施例中， 整流罩子组件包括连接多个内部部分82和多个支柱86的内部带45，以形成外部狭槽，以及连接多个外部部分80和多个支柱86的外部带44 形成内槽。 组装整流罩46的方法包括将上述整流罩子组件38插入涡轮机框架42的后端，在涡轮机架42的前端将多个前支柱84插入外槽和内槽中 并且将前支撑杆84连接到整流罩子组件88。

    FLOW METERING ANTI-ROTATION OUTER DIAMETER (OD) HEX NUT
    2.
    发明申请
    FLOW METERING ANTI-ROTATION OUTER DIAMETER (OD) HEX NUT 审中-公开
    流量测量反转外径（外径）十六进制

    公开(公告)号：WO2014008128A1

    公开(公告)日：2014-01-09

    申请号：PCT/US2013/048603

    申请日：2013-06-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCOTT, Jonathan Ariel

    IPC: F02C7/00 ,  F02C7/32 ,  F02C9/00

    CPC classification number: F01D9/065 ,  F01D25/12 ,  F05D2260/31 ,  F16B39/02 ,  Y02T50/675

    Abstract: An outer diameter (OD) hex nut secures a hollow cooling rod to an outer case of an engine. The OD hex nut includes a flange portion and a hollow tube portion. The flange portion includes a central aperture for receiving cooling airflow and a plurality of vernier holes located circumferentially around the flange portion. The hollow tube portion extends from the flange portion and is in fluid communication with the central aperture to receive cooling airflow for distribution to the hollow cooling rod.

    Abstract translation: 外径（OD）六角螺母将中空的冷却杆固定到发动机的外壳上。 OD六角螺母包括凸缘部分和中空管部分。 凸缘部分包括用于接收冷却气流的中心孔和围绕凸缘部分周向定位的多个游标孔。 中空管部分从凸缘部分延伸并与中心孔流体连通以接收冷却气流，以分配到中空冷却杆。

    SCUPPER CHANNELLING IN GAS TURBINE MODULES
    4.
    发明申请
    SCUPPER CHANNELLING IN GAS TURBINE MODULES 审中-公开
    气体涡轮机模块中的辅助通道

    公开(公告)号：WO2014105577A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/076179

    申请日：2013-12-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCOTT, Jonathan Ariel ,  HAWKE, Larry B.

    IPC: F02C7/20 ,  F02C7/06 ,  F01D25/16 ,  F02C7/12

    CPC classification number: F01D25/125 ,  F01D9/065 ,  F01D25/162 ,  F01D25/24 ,  F01D25/30 ,  F02C7/12 ,  F02C7/20 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/675

    Abstract: A gas turbine module comprises a frame, a bearing support ring, a service line, and a scupper channel system. A service line is disposed through a radial passage of the frame and a service line port of the bearing support ring. The scupper line is disposed radially through a radial passage of the frame and is open to the scupper drain port. The scupper channel system is formed into a radially inner surface of the bearing support ring, and includes a collection portion in fluid communication with the scupper drain port.

    Abstract translation: 一种燃气轮机模块，包括框架，轴承支撑环，服务线和排水通道系统。 服务线通过框架的径向通道和轴承支撑环的服务线端口布置。 排屑管径向设置在框架的径向通道中，并且通向排水口。 排水通道系统形成为轴承支承环的径向内表面，并且包括与排屑口流体连通的收集部分。

    COOLING APPARATUS FOR A MID-TURBINE FRAME
    5.
    发明申请
    COOLING APPARATUS FOR A MID-TURBINE FRAME 审中-公开
    中型涡轮机的冷却装置

    公开(公告)号：WO2014008129A1

    公开(公告)日：2014-01-09

    申请号：PCT/US2013/048606

    申请日：2013-06-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SCOTT, Jonathan Ariel

    IPC: F02C7/00 ,  F02C7/12 ,  F02C7/32 ,  F02C9/00

    CPC classification number: F02C7/18 ,  F01D9/065 ,  F05D2220/3213 ,  F05D2230/64 ,  F05D2250/311 ,  F05D2260/20 ,  Y02T50/675 ,  Y02T50/676

    Abstract: A cooling apparatus bifurcates and regulates cooling airflow provided to a mid-turbine frame. A flow metering tube includes a top portion and a tube portion, wherein the top portion includes a first central aperture that directs a first cooling airflow into the tube portion and a first plurality of apertures located circumferentially around the central aperture that directs a second cooling airflow to a portion outside the tube portion. A metering plate is located on the top portion of the flow metering tube, wherein the metering plate includes a second central aperture aligned with the central aperture of the flow metering tube and a second plurality of apertures located circumferentially around the central aperture, wherein a size of the second central aperture meters the first cooling airflow and a size and number of the second plurality of apertures meters the second cooling airflow.

    Abstract translation: 冷却装置使提供给中间涡轮机框架的冷却气流分叉并调节。 流量计量管包括顶部部分和管部分，其中顶部包括将第一冷却气流引导到管部分中的第一中心孔和围绕中心孔周向定位的第一多个孔，其引导第二冷却气流 到管部分外部的部分。 计量盘位于流量计量管的顶部，其中计量板包括与流量计量管的中心孔对准的第二中心孔和围绕中心孔周向定位的第二多个孔，其中尺寸 第二中心孔的第一冷却气流计量第二冷却气流，第二多个孔的尺寸和数量对第二冷却气流进行测量。

    TURBINE FRAME ASSEMBLY AND METHOD OF DESIGNING TURBINE FRAME ASSEMBLY
    7.
    发明申请
    TURBINE FRAME ASSEMBLY AND METHOD OF DESIGNING TURBINE FRAME ASSEMBLY 审中-公开
    涡轮机框架组件和设计涡轮机框架组件的方法

    公开(公告)号：WO2014105425A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/074278

    申请日：2013-12-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： YEAGER, William ,  SCOTT, Jonathan Ariel

    IPC: F02C7/24 ,  F01D25/26 ,  F01D25/24

    CPC classification number: F01D25/162 ,  F01D25/145 ,  F01D25/26 ,  F01D25/30 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2240/15 ,  F05D2260/231 ,  F05D2300/171 ,  F05D2300/175 ,  Y10T29/49321

    Abstract: A structural case assembly comprises a frame, fairing and heat shield. The frame is fabricated from a material having a temperature limit below an operating point of a gas turbine engine, and comprises an outer ring, an inner ring and a plurality of struts extending therebetween to define a flow path. The fairing is fabricated from a material having a temperature limit above the operating point of the gas turbine engine, and comprises a ring-strut-ring structure that lines the flow path. The heat shield is disposed between the frame and the fairing to inhibit radiant heat transfer therebetween. The heat shield may block all line-of-sight between the fairing and the frame. The frame may be produced from CA-6NM alloy. A method for designing a turbine case structure includes selecting a frame material having a temperature limit below the operating point of an engine.

    Abstract translation: 结构壳体组件包括框架，整流罩和隔热罩。 框架由具有低于燃气涡轮发动机工作点的温度限制的材料制成，并且包括外环，内环和在其之间延伸的多个支柱，以限定流路。 整流罩由温度极限高于燃气涡轮发动机的工作点的材料制成，并且包括使流道流动的环形支柱结构。 隔热罩设置在框架和整流罩之间，以防止它们之间的辐射热传递。 隔热罩可能会阻塞整流罩和框架之间的所有视线。 框架可以由CA-6NM合金制成。 一种用于设计涡轮机壳结构的方法包括选择温度极限低于发动机工作点的框架材料。

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