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    CMC shroud support system of a gas turbine
    2.
    发明授权
    CMC shroud support system of a gas turbine 有权

    公开(公告)号：US10378387B2

    公开(公告)日：2019-08-13

    申请号：US14891806

    申请日：2014-04-23

    Applicant: General Electric Company

    Inventor： Jonathan David Baldiga ,  Jason David Shapiro

    IPC: F01D25/28 ,  F01D11/08 ,  F01D11/12 ,  F01D25/24

    Abstract: A shroud support system with load spreading comprises a shroud hanger having a first wall and a second wall spaced apart in an axial direction by a retainer support wall, a ceramic matrix composite shroud segment disposed in the shroud hanger between the first and second walls and the retainer support wall, a retainer having circumferentially spaced first and second bolt holes, the retainer passing through the shroud, first and second bolts passing through the shroud hanger and engaging the first and second bolt holes of the retainer.

    Integral segmented CMC shroud hanger and retainer system
    4.
    发明授权
    Integral segmented CMC shroud hanger and retainer system 有权

    公开(公告)号：US10087784B2

    公开(公告)日：2018-10-02

    申请号：US14770411

    申请日：2014-02-21

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Jonathan David Baldiga

    IPC: F01D25/24 ,  F01D25/00

    Abstract: A shroud hanger with integral retainer assembly comprises a ceramic matrix composite shroud hanger a first wall and a second wall, the hanger having a support wall extending between the first and second walls, the support wall having a shoulder near circumferential ends, a retainer depending from the support wall having a first lower leg and a second lower leg extending in the circumferential direction, a first shroud supported by the first lower leg and a second shroud supported by the second lower leg.

    Compound angle accelerator
    6.
    发明授权
    Compound angle accelerator 有权

    公开(公告)号：US11859550B2

    公开(公告)日：2024-01-02

    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

    CPC classification number: F02C7/18 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2260/201

    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.

    Unitary flow path structure
    9.
    发明授权
    Unitary flow path structure 有权

    公开(公告)号：US10393381B2

    公开(公告)日：2019-08-27

    申请号：US15417399

    申请日：2017-01-27

    Applicant: General Electric Company

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

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

    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.

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