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    ACOUSTIC LINER AND GAS TURBINE ENGINE WITH SUCH ACOUSTIC LINER
    16.
    发明公开
    ACOUSTIC LINER AND GAS TURBINE ENGINE WITH SUCH ACOUSTIC LINER 审中-公开

    公开(公告)号：EP3799030A1

    公开(公告)日：2021-03-31

    申请号：EP19199792.3

    申请日：2019-09-26

    申请人： Rolls-Royce Deutschland Ltd & Co KG ,  ITP Next Generation Turbines S.L.

    发明人： RICHTER, Christoph ,  SERRANO GONZALEZ, Adolfo

    IPC分类号： G10K11/172 ,  F01D25/04 ,  F02C7/045 ,  F02K1/82

    摘要： The invention regards an acoustic liner (4) which comprises: a facing sheet (5) that comprises holes (50), the facing sheet (5) having a porosity and a facing sheet thickness (d), a backing sheet (8), and a plurality of cells (7) arranged between the facing sheet (5) and the backing sheet (8), the cells (7) having a cell depth (L 1 ) and each cell defining a cavity. A plurality of internal necks (6) are provided that extend from the inner side (52) of the facing sheet (5) towards the backing sheet (8), each internal neck (6) being located around a hole (50) of the facing sheet (5), thereby extending the longitudinal length (L 2 ) of the hole (50). The invention further regards a gas turbine engine with such acoustic liner (4).

    TRANSITION DUCT FOR A GAS TURBINE ENGINE
    17.
    发明公开
    TRANSITION DUCT FOR A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3783200A1

    公开(公告)日：2021-02-24

    申请号：EP20194230.7

    申请日：2014-12-11

    申请人： Siemens Energy Global GmbH & Co. KG

    发明人： Bartley, Robert H. ,  Bascones, Miguel ,  Evins, Joseph L. ,  Hase, Matthias ,  Kumar, Manish ,  Sayavong, Khamhou ,  Weaver, Adam J. ,  Williams, Lashanda N.

    IPC分类号： F01D9/02 ,  F01D25/04 ,  F23R3/60

    摘要： A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.

    FACE SEAL WITH DAMPER
    20.
    发明公开
    FACE SEAL WITH DAMPER 审中-公开

    公开(公告)号：EP3693555A1

    公开(公告)日：2020-08-12

    申请号：EP20155676.8

    申请日：2020-02-05

    申请人： United Technologies Corporation

    发明人： WALKER, Brady

    IPC分类号： F01D11/00 ,  F16J15/34 ,  F01D25/04

    摘要： A gas turbine engine component includes a static component, a seal body (68) associated with the static component, the seal body (68) having an end surface (70) configured to face a rotating seal seat (62), and a damper (102) positioned radially outward of the seal body (68). The damper (102) includes a contact (116) that engages the seal body (68) to dampen radial movement of the seal body (68) while accommodating axial movement of the seal body (68).