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    Methods and Features for Positioning a Flow Path Inner Boundary Within a Flow Path Assembly
    11.
    发明申请
    Methods and Features for Positioning a Flow Path Inner Boundary Within a Flow Path Assembly 审中-公开

    公开(公告)号：US20190226349A1

    公开(公告)日：2019-07-25

    申请号：US16371362

    申请日：2019-04-01

    Applicant: General Electric Company

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

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

    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.

    COMPOUND ANGLE ACCELERATOR
    13.
    发明申请
    COMPOUND ANGLE ACCELERATOR 有权

    公开(公告)号：US20220316397A1

    公开(公告)日：2022-10-06

    申请号：US17219988

    申请日：2021-04-01

    Applicant: General Electric Company

    Inventor： James Daniel Longhurst ,  Antonio C. Gominho ,  Jordan Paule Tesorero ,  Jonathan David Baldiga ,  Orin J. Hall

    IPC: F02C7/18 ,  F01D25/12

    Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.

    Methods and features for positioning a flow path inner boundary within a flow path assembly
    14.
    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：US11384651B2

    公开(公告)日：2022-07-12

    申请号：US16371362

    申请日：2019-04-01

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Brandon ALIanson 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.

    Unitary flow path structure
    15.
    发明授权
    Unitary flow path structure 有权

    公开(公告)号：US11143402B2

    公开(公告)日：2021-10-12

    申请号：US16398439

    申请日：2019-04-30

    Applicant: General Electric Company

    Inventor： Mark Eugene Noe ,  Shawn Michael Pearson ,  Joshua Tyler Mook ,  Brandon ALlanson Reynolds ,  Jonathan David Baldiga

    IPC: F23R3/00 ,  F01D5/06 ,  F01D5/22 ,  F01D9/04 ,  F01D9/02 ,  F01D25/24 ,  F02C3/14 ,  F02C7/22

    Abstract: Gas turbine engines, as well as outer walls and flow path assemblies of gas turbine engines, are provided. For example, an outer wall of a flow path comprises a combustor portion extending through a combustion section, and a turbine portion extending through at least a first turbine stage of a turbine section. The combustor and turbine portions are integrally formed as a single unitary structure that defines an outer boundary of the flow path. As another example, a flow path assembly comprises a combustor dome positioned a forward end of a combustor; an outer wall extending from the combustor dome through at least a first turbine stage; and an inner wall extending from the combustor dome through at least a combustion section. The combustor dome extends radially from the outer wall to the inner wall and is integrally formed with the outer and inner walls as a single unitary structure.

    COMPLIANT SEAL COMPONENT AND ASSOCIATED METHOD
    17.
    发明申请
    COMPLIANT SEAL COMPONENT AND ASSOCIATED METHOD 审中-公开

    公开(公告)号：US20190338668A1

    公开(公告)日：2019-11-07

    申请号：US16513033

    申请日：2019-07-16

    Applicant: General Electric Company

    Inventor： Victor Hugo Silva Correia ,  Jonathan David Baldiga

    IPC: F01D25/12 ,  F01D11/00

    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.

    Flow path assembly with pin supported nozzle airfoils
    18.
    发明授权
    Flow path assembly with pin supported nozzle airfoils 有权

    公开(公告)号：US10370990B2

    公开(公告)日：2019-08-06

    申请号：US15440320

    申请日：2017-02-23

    Applicant: General Electric Company

    Inventor： Brandon ALlanson Reynolds ,  Jonathan David Baldiga

    IPC: F01D9/04 ,  F23R3/00 ,  F01D25/00 ,  F01D25/24 ,  F23R3/10 ,  F23R3/60 ,  F01D9/02

    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall and an outer wall defining an opening therethrough, as well as a nozzle airfoil having an inner end radially opposite an outer end that is positioned within the opening defined in the outer wall such that the outer end projects radially outwardly from the outer wall. The flow path assembly also comprises a pin and a first support member. The pin extends from the first support member to the outer end of the nozzle airfoil to support the nozzle airfoil. In some embodiments, the outer end of the nozzle airfoil defines a flange configured to receive the pin and a radial stop configured to press against a radially outward external support, and the pin is configured to transfer a load on the nozzle airfoil to an external structure.

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