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    Methods and Assemblies for Attaching Airfoils Within a Flow Path
    11.
    发明申请
    Methods and Assemblies for Attaching Airfoils Within a Flow Path 有权

    公开(公告)号：US20220213798A1

    公开(公告)日：2022-07-07

    申请号：US17706761

    申请日：2022-03-29

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

    IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

    Methods and Assemblies for Attaching Airfoils Within a Flow Path
    12.
    发明申请
    Methods and Assemblies for Attaching Airfoils Within a Flow Path 审中-公开

    公开(公告)号：US20200025002A1

    公开(公告)日：2020-01-23

    申请号：US16377398

    申请日：2019-04-08

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Donald Brett Desander ,  Edward Charles Vickers

    IPC: F01D9/04 ,  F04D29/54 ,  F01D11/00 ,  F01D9/02

    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.

    System for cooling a turbine shroud
    13.
    发明授权
    System for cooling a turbine shroud 有权

    公开(公告)号：US10422244B2

    公开(公告)日：2019-09-24

    申请号：US14658313

    申请日：2015-03-16

    Applicant: General Electric Company

    Inventor： Jason David Shapiro

    IPC: F01D25/12 ,  F01D11/08 ,  F01D11/12 ,  F01D11/24 ,  F01D9/04

    Abstract: In one aspect the present subject matter is directed to a system for cooling a turbine shroud. The system includes a cooling medium source that provides a cooling medium, and a turbine shroud support assembly that includes a shroud support ring. A shroud seal is coupled to the turbine shroud support assembly. The shroud seal includes a back side surface and an inner surface. A pin extends at least partially through the shroud support ring towards the back side surface. The pin includes a flow passage having an inlet that is in fluid communication with the cooling medium source and an aperture that is disposed downstream from the inlet. The aperture is oriented to direct a flow of the cooling medium out of the flow passage in a flow direction that is non-perpendicular to the back side surface of the shroud seal.

    CMC shroud support system of a gas turbine
    14.
    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
    15.
    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.

    Continuous ring composite turbine shroud
    17.
    发明授权
    Continuous ring composite turbine shroud 有权
    连续环复合涡轮机罩

    公开(公告)号：US09518474B2

    公开(公告)日：2016-12-13

    申请号：US14220434

    申请日：2014-03-20

    Applicant: General Electric Company

    Inventor： Jason David Shapiro ,  Jared Peter Buhler ,  Brian Kenneth Corsetti

    IPC: F01D11/00 ,  F01D11/08 ,  F01D9/04 ,  F01D11/18 ,  F01D25/24

    CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/18 ,  F01D25/246 ,  F05D2300/603

    Abstract: A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.

    Abstract translation: 由支撑组件支撑的复合环形护罩，所述支撑组件包括至少一个环并且至少部分地设置在所述环内。 护罩偏压抵靠环的内凸缘并与其密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环的径向孔。

    METHOD AND SYSTEM FOR A CERAMIC MATRIX COMPOSITE SHROUD HANGER ASSEMBLY
    18.
    发明申请
    METHOD AND SYSTEM FOR A CERAMIC MATRIX COMPOSITE SHROUD HANGER ASSEMBLY 有权
    一种陶瓷基复合材料的组装方法与系统

    公开(公告)号：US20160251982A1

    公开(公告)日：2016-09-01

    申请号：US14634060

    申请日：2015-02-27

    Applicant: General Electric Company

    Inventor： Jason David Shapiro

    IPC: F01D25/26 ,  F01D25/24 ,  F01D9/04

    CPC classification number: F01D11/08 ,  F01D25/246 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2260/15 ,  F05D2260/941 ,  F05D2300/6033 ,  Y02T50/672

    Abstract: A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.

    Abstract translation: 提供了一种用于燃气涡轮发动机的护罩和衣架组件以及将负载从陶瓷基体复合材料（CMC）护罩传送到CMC护罩悬挂器组件的方法。 护罩和衣架组件包括由具有第一热膨胀系数的第一材料形成的护罩悬挂器组件，护罩悬挂器组件具有前悬挂部分和独立的后悬挂部分，以及由具有第二系数的第二材料形成的护罩 的热膨胀的前后悬挂部分构造成联接在一起以跨过护罩的向前径向延伸的壁。

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