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    Airfoil assembly with spacer and tie-spar
    11.
    发明授权
    Airfoil assembly with spacer and tie-spar 有权

    公开(公告)号：US10107117B2

    公开(公告)日：2018-10-23

    申请号：US14838412

    申请日：2015-08-28

    Applicant: United Technologies Corporation

    Inventor： Jesse M. Carr ,  Bryan P. Dube

    IPC: F01D9/04 ,  F01D5/28 ,  F01D25/24

    Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.

    RIM SEAL FOR GAS TURBINE ENGINE
    13.
    发明申请
    RIM SEAL FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20180058236A1

    公开(公告)日：2018-03-01

    申请号：US15244203

    申请日：2016-08-23

    Applicant: United Technologies Corporation

    Inventor： Anton G. Banks ,  Christopher Corcoran ,  Bryan P. Dube

    IPC: F01D11/00 ,  F02C3/04 ,  F01D5/02 ,  F01D5/30 ,  F04D29/32 ,  F04D29/08

    Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.

    CLAMPED VANE ARC SEGMENT HAVING LOAD-TRANSMITTING FEATURES
    15.
    发明申请
    CLAMPED VANE ARC SEGMENT HAVING LOAD-TRANSMITTING FEATURES 审中-公开
    具有负载传输功能的夹紧风扇部分

    公开(公告)号：US20160084096A1

    公开(公告)日：2016-03-24

    申请号：US14838407

    申请日：2015-08-28

    Applicant: United Technologies Corporation

    Inventor： Jesse M. Carr ,  Bryan P. Dube

    IPC: F01D9/04 ,  F02C3/04 ,  F01D25/28

    CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D25/246 ,  F01D25/28 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/80 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil.

    Abstract translation: 叶片弧段包括径向内部和外部平台以及机械夹紧在平台之间的机翼。 翼型件具有在径向内部和外部整流平台之间径向延伸的翼型部分。 至少一个整流罩平台包括前侧和后侧，周向侧面和气体通道侧和相对的径向侧。 径向侧包括多个突起，其具有基本上垂直于翼型件的径向切向和轴向载荷传递方向的面定向的面，使得这些面分别主要承受径向，切向和轴向载荷传递 机翼。

    Thermal gradient reducing device for gas turbine engine component
    19.
    发明授权
    Thermal gradient reducing device for gas turbine engine component 有权

    公开(公告)号：US11078844B2

    公开(公告)日：2021-08-03

    申请号：US16197835

    申请日：2018-11-21

    Applicant: United Technologies Corporation

    Inventor： Adam P. Generale ,  Bryan P. Dube

    IPC: F02C7/18 ,  F01D25/00

    Abstract: An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.

    VANE WITH COLLAR
    20.
    发明申请
    VANE WITH COLLAR 有权

    公开(公告)号：US20210156270A1

    公开(公告)日：2021-05-27

    申请号：US16690959

    申请日：2019-11-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Alyson T. Burdette ,  Bryan P. Dube ,  Rutva A. Patel ,  Nicholas Broulidakis

    IPC: F01D9/02

    Abstract: An airfoil piece includes at least one inner ceramic matrix composite ply which defines an internal cavity of an airfoil section and first and second collar projections. At least one inner ceramic matrix composite ply is continuous through the airfoil section and first and second collar projections, first and second platforms at the first and second ends of the airfoil section. The first and second collar projections extend radially past the first and second platforms, respectively. A vane for a gas turbine engine and a method of assembling a vane are also disclosed.

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