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    STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES
    42.
    发明申请
    STACKED ANNULAR COMPONENTS FOR TURBINE ENGINES 审中-公开
    用于涡轮发动机的堆叠式环形构件

    公开(公告)号：WO2006110125A3

    公开(公告)日：2007-02-22

    申请号：PCT/US2004040206

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  ROBERGE GARY D ,  MERRY BRIAN

    Inventor： SUCIU GABRIEL L ,  ROBERGE GARY D ,  MERRY BRIAN

    IPC: F01D5/34 ,  F01D5/02 ,  F01D5/06 ,  F02C3/073 ,  F02K3/068

    CPC classification number: F02K3/068 ,  F01D5/025 ,  F01D5/34 ,  F02C3/067 ,  F02C3/073 ,  Y02T50/671 ,  Y10T29/49321

    Abstract: Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially thereform. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

    Abstract translation: 作为示例，关于具有多个环形压缩机转子翼型组件（120）的轴向压缩机来描述改进的环形部件和用于将环形部件组装到涡轮发动机中的改进方法。 每个压缩机转子翼型组件包括环形转子部分（122），从其轴向延伸的间隔部分（124）和沿径向延伸的多个翼型件（52）。 多个翼型件可以与环形部分一体地形成。 压缩机转子翼型件组件依次堆叠在中心连接件（134）或外圆环上。 一个压缩机转子翼型组件（120a）的间隔部分邻接邻近的压缩机转子翼型组件（120b）的环形转子部分，以将它们彼此保持在中心连接的外圆环上。 通过依次堆叠压缩机转子叶片组件然后保持它们，可以消除典型的分体式壳体，凸缘和转子螺栓。

    ANNULAR TURBINE RING ROTOR
    43.
    发明申请
    ANNULAR TURBINE RING ROTOR 审中-公开
    环形涡轮机转子

    公开(公告)号：WO2006059997A3

    公开(公告)日：2006-11-16

    申请号：PCT/US2004040125

    申请日：2004-12-01

    Applicant: UNITED TECHNOLOGIES CORP ,  SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  MERRY BRIAN

    IPC: F01D5/30 ,  F01D11/02

    CPC classification number: F01D11/02 ,  F01D5/30

    Abstract: A fan-turbine rotor assembly (24) includes one or more turbine ring rotors (32). Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring (114) includes axial installation and radial locking of each turbine ring rotor.

    Abstract translation: 风扇 - 涡轮转子组件（24）包括一个或多个涡轮环转子（32）。 每个涡轮机环形转子都被铸造为一个整体的环形环。 通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏被最小化，这提高了发动机效率。 涡轮环转子到扩散器环（114）的组装包括每个涡轮环转子的轴向安装和径向锁定。

    GEARED TURBOFAN WITH A GEARBOX AFT OF A FAN DRIVE TURBINE
    45.
    发明申请
    GEARED TURBOFAN WITH A GEARBOX AFT OF A FAN DRIVE TURBINE 审中-公开
    具有风扇驱动轮的齿轮箱的齿轮涡轮机

    公开(公告)号：WO2015138030A2

    公开(公告)日：2015-09-17

    申请号：PCT/US2014071037

    申请日：2014-12-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SCHWARZ FREDERICK M ,  SUCIU GABRIEL L

    IPC: F02C3/107

    CPC classification number: F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/4031

    Abstract: A gas turbine engine according to an example of the present disclosure includes a drive turbine configured to drive a fan section, a speed change mechanism connected to the drive turbine and located aft of the drive turbine and aft of the fan. An output of the speed change mechanism connects to the fan.

    Abstract translation: 根据本公开的示例的燃气涡轮发动机包括构造成驱动风扇部分的驱动涡轮机，连接到驱动涡轮机并位于驱动涡轮机的后部并且位于风扇后部的变速机构。 变速机构的输出与风扇连接。

    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS
    48.
    发明申请
    LOW PROFILE COMPRESSOR BLEED AIR-OIL COOLERS 审中-公开

    公开(公告)号：WO2014081493A3

    公开(公告)日：2014-07-17

    申请号：PCT/US2013057080

    申请日：2013-08-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SNAPE NATHAN ,  SUCIU GABRIEL L ,  PICKFORD SIMON ,  PENDA ALLAN R

    IPC: F02C7/141

    CPC classification number: F02C6/08 ,  F02C7/14 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/675

    Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE
    50.
    发明申请
    COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 审中-公开
    带齿轮系统的逆转低压涡轮机安装在涡轮机排气箱

    公开(公告)号：WO2013176709A3

    公开(公告)日：2014-03-13

    申请号：PCT/US2013026287

    申请日：2013-02-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MERRY BRIAN D ,  SUCIU GABRIEL L

    IPC: F02C3/067 ,  F01D25/24 ,  F02K3/072

    CPC classification number: F01D15/12 ,  F01D1/24 ,  F01D25/162 ,  F01D25/30 ,  F02C3/107 ,  F02C7/32 ,  F02K3/072 ,  Y02T50/671

    Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

    Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴。 外转子直接驱动轴并且包括一组外部叶片。 内转子具有与外组叶片交替散布的内组叶片。 内转子构造成围绕与外转子的旋转轴线相反的方向旋转。 齿轮系统将内转子连接到轴，并且构造成以比外部组叶片更快的速度旋转内组叶片。

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