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    GAS TURBINE ENGINE MOUNTING RING
    1.
    发明申请
    GAS TURBINE ENGINE MOUNTING RING 有权
    气体涡轮发动机安装环

    公开(公告)号：US20140165533A1

    公开(公告)日：2014-06-19

    申请号：US13717898

    申请日：2012-12-18

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Andreas ELEFTHERIOU ,  Denis LECLAIR ,  David DENIS ,  David MENHEERE ,  Paul AITCHISON

    IPC: F02K3/04

    CPC classification number: F01D25/162 ,  F02K3/06 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/4932

    Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.

    Abstract translation: 一种用于飞行器发动机的壳体包括外圈和限定其间的气流通道的内毂，所述外圈具有限定轴向的轴线; 多个支柱，其布置成周向阵列并且从所述内毂径向延伸到所述外环以将所述内毂安装到所述外环; 其中所述外环由双层皮肤限定，所述双层皮肤包括与所述金属板的环形内表面同心地围绕并径向间隔开的轴向延伸的环形外皮，所述外表皮和内表皮大体上彼此平行， 端环和环形后端环，其与外表面和内表面相邻地焊接或钎焊，所述外表面和内表面邻近表皮的前后边缘以在其间限定环形空腔，并且所述外环还包括多个周向间隔开的轴向延伸的肋， 外皮和内皮加固双面皮。

    MISTUNED COMPRESSOR ROTOR WITH HUB SCOOPS
    2.
    发明申请
    MISTUNED COMPRESSOR ROTOR WITH HUB SCOOPS 审中-公开

    公开(公告)号：US20190085868A1

    公开(公告)日：2019-03-21

    申请号：US15706311

    申请日：2017-09-15

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Karan ANAND ,  Farid ABRARI ,  Ernest ADIQUE ,  Paul AITCHISON ,  Daniel FUDGE ,  Kari HEIKURINEN ,  Paul STONE ,  Tibor URAC ,  Thomas VEITCH

    IPC: F04D29/66 ,  F04D29/32

    Abstract: A compressor rotor for a gas turbine engine includes a hub disposed about an axis of rotation and an outer surface forming a radially inner gaspath boundary, the outer surface defining a nominal hub diameter. A circumferential array of blades extends radially outwardly from the hub. A first inter-blade passage is defined between a first set of adjacent blades and has a first throat area. A second inter-blade passage is defined between a second set of adjacent blades and has a second throat area that is smaller than the first throat area. At least one scoop is disposed in the second inter-blade passage, the scoop defining a cavity extending radially into the outer surface of the hub relative to the nominal hub diameter.

    VANE FOR GAS TURBINE ENGINE
    4.
    发明申请
    VANE FOR GAS TURBINE ENGINE 有权

    公开(公告)号：US20210156272A1

    公开(公告)日：2021-05-27

    申请号：US16692178

    申请日：2019-11-22

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Tammy YAM ,  Tibor URAC ,  Paul AITCHISON

    IPC: F01D9/04 ,  F01D11/00

    Abstract: A vane configured to be disposed in a gas path defined in part by an inner surface of a case of a gas turbine engine is provided. The vane comprises a vane body configured to extend through an aperture in the case and a vane head disposed at an end of the vane body. The vane head has an abutting surface configured to contact an outer surface of the case when the vane body extends through the aperture, and a groove configured to receive a sealing member. The groove opens to the abutting surface and is outwardly open relative to an inner region surrounded by the groove. The groove has an inner seating surface that hinders movement of the sealing member toward the abutting surface and can facilitate installation of the vane in the engine.

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