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    TEC MOUNT REDUNDANT FASTENING
    32.
    发明公开
    TEC MOUNT REDUNDANT FASTENING 审中-公开
    冗余固定泰格支持

    公开(公告)号：EP2841339A4

    公开(公告)日：2015-12-16

    申请号：EP13781678

    申请日：2013-02-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  ALVANOS IOANNIS

    IPC: B64D27/26 ,  F02C7/20

    CPC classification number: F02C7/20 ,  B64D27/26 ,  B64D2027/264

    Abstract: A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link.

    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM
    34.
    发明公开
    HIGH PRESSURE TURBINE COOLANT SUPPLY SYSTEM 审中-公开
    冷却液供给系统高压涡轮

    公开(公告)号：EP2855884A4

    公开(公告)日：2016-05-11

    申请号：EP13797827

    申请日：2013-05-15

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MOSLEY JOHN H ,  ALVANOS IOANNIS ,  STRIPINIS PHILIP S ,  FREIBERG DOUGLAS PAUL ,  PINERO HECTOR M ,  O'CONNOR JOHN J ,  PIETROBON JON

    IPC: F02C7/12 ,  F01D5/08 ,  F01D25/08 ,  F01D25/12

    CPC classification number: F01D5/082 ,  F01D25/12

    Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

    GAS TURBINE ENGINE COOLING SYSTEM
    35.
    发明公开
    GAS TURBINE ENGINE COOLING SYSTEM 审中-公开
    冷却系统的燃气涡轮发动机

    公开(公告)号：EP2820253A4

    公开(公告)日：2015-12-30

    申请号：EP13754366

    申请日：2013-02-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SUCIU GABRIEL L ,  ALVANOS IOANNIS

    IPC: F01D9/02 ,  F01D5/08 ,  F01D25/08 ,  F02C6/08 ,  F02C7/08 ,  F02C7/12

    CPC classification number: F02C6/08 ,  F01D5/08 ,  F02C7/08

    Abstract: A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.

    CANTILEVER STATOR WITH VORTEX INITIATION FEATURE
    37.
    发明公开
    CANTILEVER STATOR WITH VORTEX INITIATION FEATURE 审中-公开
    FREITRAGENDER STATOR MIT WIRBELERZEUGUNGSFUNKTION

    公开(公告)号：EP2971547A4

    公开(公告)日：2016-12-07

    申请号：EP13880304

    申请日：2013-11-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS

    IPC: F01D5/20 ,  F01D5/12 ,  F01D9/02 ,  F04D29/68

    CPC classification number: F01D11/001 ,  F01D5/02 ,  F01D9/041 ,  F01D11/02 ,  F01D25/24 ,  F02C3/06 ,  F02C3/14 ,  F04D29/164 ,  F04D29/321 ,  F04D29/329 ,  F04D29/685 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2250/294 ,  F05D2250/61

    Abstract: An axial flow compressor is disclosed with a plurality of rotors. Each rotor includes a disk having an outer rim. Each outer rim is coupled to a radially outwardly extending rotor blade. The case is coupled to a plurality of radially inwardly extending stator vanes, i.e. cantilever-type stator vanes. Each stator vane is disposed between two rotor blades and extends towards one of the outer rims and terminates at a tip disposed in close proximity to one of the outer rims. At least one of the outer rims includes a serrated outer surface that faces the tip of a stator vane which results in a vortex flow causing air that would normally leak through the clearance between the stator vane and the outer rim to engage the stator vane to a greater degree thereby increasing the efficiency of the compressor.

    Abstract translation: 公开了具有多个转子的轴流式压缩机。 每个转子包括具有外缘的盘。 每个外轮缘联接到径向向外延伸的转子叶片。 壳体联接到多个径向向内延伸的定子叶片，即悬臂式定子叶片。 每个定子叶片设置在两个转子叶片之间并且延伸到外轮缘中的一个并且终止于靠近其中一个外轮缘设置的尖端。 外缘中的至少一个包括面向定子叶片尖端的锯齿状外表面，其导致涡流，导致空气通常通过定子叶片和外轮缘之间的间隙泄漏，以将定子叶片接合到 从而提高压缩机的效率。

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