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    PLATFORM SEAL
    2.
    发明申请
    PLATFORM SEAL 有权

    公开(公告)号：US20210140335A1

    公开(公告)日：2021-05-13

    申请号：US16677262

    申请日：2019-11-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bryan H. Farrar ,  Howard J. Liles

    IPC: F01D11/00 ,  F01D9/04 ,  F01D25/12

    Abstract: A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

    Platform seal
    4.
    发明授权
    Platform seal 有权

    公开(公告)号：US11187096B2

    公开(公告)日：2021-11-30

    申请号：US16677262

    申请日：2019-11-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Bryan H. Farrar ,  Howard J. Liles

    IPC: F01D9/04 ,  F01D11/00 ,  F01D25/12

    Abstract: A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

    CMC VANE MATE FACE FLANGE
    6.
    发明申请
    CMC VANE MATE FACE FLANGE 有权

    公开(公告)号：US20210102469A1

    公开(公告)日：2021-04-08

    申请号：US16592884

    申请日：2019-10-04

    Applicant: United Technologies Corporation

    Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan H. Farrar ,  Cheng Gao

    IPC: F01D5/28

    Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.

    CMC vane mate face flange
    8.
    发明授权
    CMC vane mate face flange 有权

    公开(公告)号：US11466577B2

    公开(公告)日：2022-10-11

    申请号：US16592884

    申请日：2019-10-04

    Applicant: United Technologies Corporation

    Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan H. Farrar ,  Cheng Gao

    IPC: F01D9/04 ,  F01D5/28

    Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.

    Vane retention feature
    9.
    发明授权
    Vane retention feature 有权

    公开(公告)号：US11268393B2

    公开(公告)日：2022-03-08

    申请号：US16689529

    申请日：2019-11-20

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Howard J. Liles ,  Bryan P. Dube ,  Bryan H. Farrar

    IPC: F01D9/04

    Abstract: An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.

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