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    FASTENER COVER FOR FLANGED JOINT
    22.
    发明申请
    FASTENER COVER FOR FLANGED JOINT 有权

    公开(公告)号：US20220333503A1

    公开(公告)日：2022-10-20

    申请号：US17694956

    申请日：2022-03-15

    Applicant: GE Avio S.r.l.

    Inventor： Roberto Maddaleno ,  Andrea Depalma ,  Antonio Giuseppe D'Ettole ,  Matteo Renato Usseglio ,  Christian Campanale

    IPC: F01D25/24 ,  F01D25/30

    Abstract: A fastener cover for a flanged joint including first and second annular flanges extending about an axis, comprising: an annular, axially-extending, inboard wall; an annular, axially-extending outboard wall positioned radially outboard of the inboard wall; and a first radial wall interconnecting the inboard and outboard walls, wherein, collectively, the inboard and outboard walls and the first radial wall define a cavity for receiving a portion of a fastener; at least one fastener pocket including sidewalls extending axially away from the first radial wall and defining a tubular shape, which is closed off opposite the first radial wall by a floor plate having a clearance hole passing therethrough for accepting a shank of the fastener; and wherein the cover includes a balance weight receptacle for accepting at least one balance weight.

    Gas turbine engine with hollow rotor in fluid communication with a balance piston cavity
    23.
    发明授权
    Gas turbine engine with hollow rotor in fluid communication with a balance piston cavity 有权

    公开(公告)号：US11473439B1

    公开(公告)日：2022-10-18

    申请号：US17448621

    申请日：2021-09-23

    Applicant: General Electric Company ,  GE Avio S.r.l.

    Inventor： Luca Giacobone ,  Matteo Renato Usseglio ,  Andrea Depalma ,  Roberto Maddaleno ,  Darek Tomasz Zatorski

    IPC: F01D9/06 ,  F01D11/10 ,  F16J15/00 ,  F01D11/00 ,  F01D11/02

    Abstract: A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.

    GAS TURBINE ENGINE NOZZLES
    24.
    发明申请
    GAS TURBINE ENGINE NOZZLES 有权

    公开(公告)号：US20220290571A1

    公开(公告)日：2022-09-15

    申请号：US17393743

    申请日：2021-08-04

    Applicant: GE Avio S.r.l. ,  Avio Polska Sp. z o.o.

    Inventor： Matteo Renato Usseglio ,  Enrico Ganzitti ,  Gianfranco Brandino ,  Rafal Robak ,  Tomasz Mucha

    IPC: F01D9/02

    Abstract: A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.

    Seal for a turbine engine
    26.
    发明授权
    Seal for a turbine engine 有权

    公开(公告)号：US10954807B2

    公开(公告)日：2021-03-23

    申请号：US15997421

    申请日：2018-06-04

    Applicant: GE Avio S.r.l.

    Inventor： Matteo Renato Usseglio ,  Enrico Ganzitti

    IPC: F01D11/00 ,  F01D11/08 ,  F16J15/32 ,  F01D9/04 ,  F01D25/24

    Abstract: An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.

    Gas turbine engine including a rotating blade assembly
    28.
    发明授权
    Gas turbine engine including a rotating blade assembly 有权

    公开(公告)号：US12146422B2

    公开(公告)日：2024-11-19

    申请号：US17888539

    申请日：2022-08-16

    Applicant: GE Avio S.r.l

    Inventor： Roberto Maddaleno ,  Matteo Renato Usseglio

    IPC: F01D5/30 ,  F01D5/22

    Abstract: A rotating blade assembly for a turbine engine having a drive shaft, the rotating blade assembly comprising a disc, at least one blade assembly, and a retainer. The disc being operably coupled to the drive shaft and including a seat having at least a portion of a first through hole. The at least one blade assembly having an upper platform, a lower platform, a dovetail extending from the lower platform, and a blade extending between the upper platform and the lower platform. The retainer assembly securing the disc to the at least one blade assembly and comprising a hollow tubular element, a pin, and a fastener.

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