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    Shroud hanger assembly
    21.
    发明授权
    Shroud hanger assembly 有权

    公开(公告)号：US10400619B2

    公开(公告)日：2019-09-03

    申请号：US15318114

    申请日：2015-05-05

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Jonathan David Baldiga

    IPC: F01D11/08 ,  F01D25/24 ,  F01D11/12

    Abstract: A shroud hanger assembly or shroud assembly is provided for a gas turbine engine wherein a hanger includes a radially depending and axially extending arm. The arm or retainer engages a pocket formed in a shroud so as to retain the shroud in a desired position relative to the hanger. An aft retaining structure is provided on the hanger and provides a seat for a seal structure which biases the retainer so that the arm of the hanger maintains engagement in the shroud pocket. A baffle may be utilized at the hanger to cool at least some portion of the shroud.

    Compliant seal component and associated method
    22.
    发明授权
    Compliant seal component and associated method 有权

    公开(公告)号：US10392967B2

    公开(公告)日：2019-08-27

    申请号：US15810448

    申请日：2017-11-13

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Victor Hugo Silva Correia ,  Jonathan David Baldiga

    IPC: F01D11/00 ,  F01D25/12 ,  F16J15/02

    Abstract: A compliant seal component, a turbomachine including such compliant seal component, and an associated method for cooling the compliant seal component disposed in the turbomachine are disclosed. The compliant seal component includes a convoluted portion and a plurality of end portions spaced apart from each other. The plurality of end portions is joined to the convoluted portion. An end portion of the plurality of end portions includes a first section and a second section, the second section defining a plenum. The end portion further includes a plurality of inlet holes and a plurality of outlet holes. The plurality of inlet holes is configured to direct a portion of a cooling fluid to the plenum. The portion of the cooling fluid in the plenum is configured to cool the end portion. The plurality of outlet holes is configured to discharge the portion of the cooling fluid from the plenum.

    Methods and features for positioning a flow path inner boundary within a flow path assembly
    24.
    发明授权
    Methods and features for positioning a flow path inner boundary within a flow path assembly 有权

    公开(公告)号：US10247019B2

    公开(公告)日：2019-04-02

    申请号：US15440235

    申请日：2017-02-23

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Brandon ALlanson Reynolds ,  Jonathan David Baldiga

    IPC: F01D9/04 ,  F02C3/14 ,  F01D9/02 ,  F01D11/02

    Abstract: Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.

    ANNULAR SHROUD ASSEMBLY
    30.
    发明申请
    ANNULAR SHROUD ASSEMBLY 有权

    公开(公告)号：US20220307383A1

    公开(公告)日：2022-09-29

    申请号：US17215539

    申请日：2021-03-29

    Applicant: General Electric Company

    Inventor： Michael Elia Hayek ,  Tyler Frederick Hooper ,  Megan Lynn Williams ,  Jonathan David Baldiga

    IPC: F01D11/02 ,  F01D9/04

    Abstract: A shroud assembly including a shroud support and an annular shroud is provided. The shroud assembly includes one or more pins for securing the annular shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. A gas turbine engine having a compressor section, a combustion section, a turbine section and a shroud assembly is also provided. The shroud assembly includes one or more pins for securing the continuous shroud to the shroud support. The pins having a block capable of translating radially to allowing the shroud to expand and contract in the radial direction. Methods for assembling a shroud assembly structure in a gas turbine engine are also provided.

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