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    TURBINE ENGINE, TURBINE ENGINE ROTOR, AND CONNECTION SYSTEM
    1.
    发明专利
    TURBINE ENGINE, TURBINE ENGINE ROTOR, AND CONNECTION SYSTEM 审中-公开

    公开(公告)号：JP2006348931A

    公开(公告)日：2006-12-28

    申请号：JP2005338031

    申请日：2005-11-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W

    IPC: F01D5/06 ,  F01D5/08 ,  F01D11/00

    Abstract: PROBLEM TO BE SOLVED: To increase efficiency by compensating for a reduction in the cross section of the flow passage of a compressor. SOLUTION: A turbine engine comprises a rotor stack 32 having vane stages 38A to I and blade disks 34A to I. The disks support the blade stages 36A to I. Spacers 62A to H connect the adjacent disks 34A to I in pairs to each other to transmit a compressive force. Recessed parts of the spacers 62B to H compensate for a reduction in the cross section of the flow passage. The spacers 62 exclude loss heat transfer during air recirculation by cavities between the outer disks. Joints 66C to H on the radial inner side of the spacers 62C to H comprise a first annular structural part extending from the forward disks to the rear and a second annular structural part extending from the backward disks to the front, and transmit torque. An anti-vortex tube 100 between the disks 34G and 34H is fitted to a joint 66G, leads air stream on the radial inner side to a spacer 67G, maintains a specified disk temperature characteristic, and controls a thermo/mechanical stress. COPYRIGHT: (C)2007,JPO&INPIT

    INTEGRALLY BLADED ROTOR WITH SLOTTED OUTER RIM
    2.
    发明申请
    INTEGRALLY BLADED ROTOR WITH SLOTTED OUTER RIM 审中-公开
    整体磨削的转子带有凹槽外缘

    公开(公告)号：WO2014074185A2

    公开(公告)日：2014-05-15

    申请号：PCT/US2013053752

    申请日：2013-08-06

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  NORRIS JAMES W

    CPC classification number: F01D5/34 ,  F01D11/006 ,  Y02T50/671 ,  Y02T50/673

    Abstract: An integrally bladed rotor has an outer rim with a plurality of blades extending radially outwardly of the outer rim. A plurality of channels are formed radially inwardly of the outer rim. A discontinuity formed at a radially outer surface of the outer rim includes a first thin slot at a radially outer face of the outer rim with an enlarged seal holding area. A second thin slot is positioned radially inwardly of the seal holding. The first and second thin slots are thinner circumferentially than the enlarged seal holding area. A seal is inserted into the seal holding area. The seal does not extend into the first and second thin slots, nor into the channels.

    Abstract translation: 整体叶片式转子具有外缘，该外缘具有多个从外缘沿径向向外延伸的叶片。 多个通道形成在外缘的径向内侧。 在外轮缘的径向外表面处形成的不连续处包括在外轮缘的径向外表面处的第一细槽以及增大的密封保持区域。 第二细槽位于密封保持件的径向内侧。 第一和第二细槽在圆周上比扩大的密封保持区域更薄。 密封件插入密封件保持区域。 密封不会延伸到第一和第二细槽中，也不会延伸到通道中。

    DIFFUSER ASPIRATION FOR A TIP TURBINE ENGINE
    3.
    发明申请
    DIFFUSER ASPIRATION FOR A TIP TURBINE ENGINE 审中-公开
    用于提升涡轮发动机的增压器吸气

    公开(公告)号：WO2006059980A3

    公开(公告)日：2006-09-08

    申请号：PCT/US2004039996

    申请日：2004-12-01

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

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

    IPC: F02C3/073 ,  F01D5/30 ,  F02C3/08

    CPC classification number: F01D5/326 ,  F02C3/073 ,  F02C3/08

    Abstract: A fan-turbine rotor assembly includes a diffuser section (114) which turns and diffuses the airflow from a radial core airflow passage (80) toward an axial airflow direction. Diffuser flow passages communicate with the diffuser passages (144) at a location which reduces separation of the airflow as the airflow is turned from the radial core airflow passage (80) toward an axial airflow direction through airflow aspiration at the potentially turbulent locations.

    Abstract translation: 风扇 - 涡轮转子组件包括扩散器部分（114），其将来自径向芯气流通道（80）的气流朝向轴向气流方向扩散。 扩散器流动通道在一个位置处与扩散通道（144）连通，当气流从径向核心气流通道（80）通过在潜在湍流位置处的气流抽吸朝向轴向气流方向转动时，气流的分离减小。

    ANNULAR TURBINE RING ROTOR
    4.
    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。

    REINFORCEMENT RINGS FOR A DIFFUSER SECTION OF A TIP TURBINE ENGINE FAN ROTOR ASSEMBLY
    6.
    发明申请
    REINFORCEMENT RINGS FOR A DIFFUSER SECTION OF A TIP TURBINE ENGINE FAN ROTOR ASSEMBLY 审中-公开
    用于提升涡轮发动机风扇转子总成的增压器部分的加固环

    公开(公告)号：WO2007015916A3

    公开(公告)日：2007-04-05

    申请号：PCT/US2006028122

    申请日：2006-07-20

    Applicant: UNITED TECHNOLOGIES CORP ,  NORRIS JAMES W ,  NORDEEN CRAIG A ,  ROBERGE GARY ,  MERRY BRIAN

    Inventor： NORRIS JAMES W ,  NORDEEN CRAIG A ,  ROBERGE GARY ,  MERRY BRIAN

    IPC: F02K3/068 ,  F01D5/30 ,  F02C3/073 ,  F04D25/04

    CPC classification number: F04D29/541 ,  F01D5/022 ,  F02C3/073 ,  F02K3/068 ,  F05D2300/702 ,  Y02T50/672

    Abstract: A fan-turbine rotor assembly (24) includes a diffuser (114) mountable to the outer periphery of a multitude of hollow fan blade sections (72) to provide structural support to the outer tips of the fan blade sections and to turn and diffuse the airflow from the radial core airflow passage toward an axial airflow direction. The diffuser includes a fan blade tip shroud inner portion (136) which forms a planar ring about the multiple of fan blade sections. Diffuser support rings (115a, 115b) are mounted to the fan blade tip shroud to further share the radial load applied to the fan blade sections by the blade mounted diffuser and annular turbine (32).

    Abstract translation: 风扇涡轮机转子组件（24）包括可安装到多个中空风扇叶片部分（72）的外周的扩散器（114），以向风扇叶片部分的外部尖端提供结构支撑，并且使 从径向芯气流通道朝向轴向气流方向的气流。 扩散器包括风扇叶片尖端护罩内部部分（136），其围绕多个风扇叶片部分形成平面环。 扩散器支撑环（115a，115b）安装到风扇叶片尖端护罩，以进一步共享由叶片安装的扩散器和环形涡轮机（32）施加到风扇叶片部分的径向载荷。

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