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    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY, BLADE FOR ROTOR ASSEMBLY AND INTER-STAGE CAVITY SEAL
    1.
    发明专利
    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY, BLADE FOR ROTOR ASSEMBLY AND INTER-STAGE CAVITY SEAL 审中-公开

    公开(公告)号：JP2006342797A

    公开(公告)日：2006-12-21

    申请号：JP2006154370

    申请日：2006-06-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA ,  VIRTUE JOHN P JR ,  HILL JAMES D ,  PINERO HECTOR M ,  JOHNSON ERIKA

    IPC: F01D11/02 ,  F02C7/28

    Abstract: PROBLEM TO BE SOLVED: To provide a seal assembly for restricting leaking-out of cooling air in constant. SOLUTION: An inside cavity 50 is positioned between a vane support part 52 and a rotary assembly 54 on the inside in the radial direction of an annular duct 30. The cooling air 40 is introduced into the cavity 50 by a duct 70, and cools a blade 58 by flowing in a conduit 72. The cavity 50 is separated from the duct 30 by a seal 80, and air pressure is properly maintained over the whole engine conditions. A segment-like ring 86 extends by crossing the cavity 50 from a divided rim area 110, and a runner 170 is aligned with land 84. One complete segment-like ring 86 is formed by aligning a plurality of adjacent ring segments 164 and 166 in a state of inserting the blade 58 into a disc. Leaking-out restriction is improved by extending the runner 170 outside or inside in the radial direction from the ring 86 by inclining to a shaft 11. COPYRIGHT: (C)2007,JPO&INPIT

    SEGMENTED SEAL FOR GAS TURBINE ENGINE
    3.
    发明申请
    SEGMENTED SEAL FOR GAS TURBINE ENGINE 审中-公开
    燃气轮机发动机的分段密封件

    公开(公告)号：WO2015119687A2

    公开(公告)日：2015-08-13

    申请号：PCT/US2014064956

    申请日：2014-11-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HILL JAMES D ,  SUCIU GABRIEL L ,  MERRY BRIAN D ,  ALVANOS IOANNIS

    IPC: F02C7/28 ,  F01D11/00

    CPC classification number: F01D11/005 ,  F01D5/06 ,  F01D5/081 ,  F01D9/041 ,  F01D11/001 ,  F05D2220/32 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2260/30 ,  Y02T50/676

    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.

    Abstract translation: 本公开的一个示例性实施例涉及燃气涡轮发动机。 发动机包括第一转子盘，第二转子盘和周向分段的密封件。 分段式密封件接合第一转子盘和第二转子盘。 分段式密封件还包括接触第一盘的前表面，接触第二盘的后表面以及径向外表面。 此外，（1）后表面和（2）前表面和径向外表面中的一个包括穿孔以允许流体流过分段密封件的内部。

    INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE
    10.
    发明公开
    INLET MANIFOLD FOR MULTI-TUBE PULSE DETONATION ENGINE 审中-公开

    公开(公告)号：EP3092397A4

    公开(公告)日：2017-10-11

    申请号：EP14885222

    申请日：2014-12-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HILL JAMES D ,  CUOZZO MICHAEL J

    IPC: F02K7/067 ,  F02C5/02

    CPC classification number: F02C5/02 ,  F02C5/10 ,  F23R7/00

    Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.

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