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    BLADE OUTER AIR SEAL MOUNT
    42.
    发明申请
    BLADE OUTER AIR SEAL MOUNT 审中-公开
    叶片外部密封装置

    公开(公告)号：US20160333716A1

    公开(公告)日：2016-11-17

    申请号：US15112657

    申请日：2015-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey

    IPC: F01D11/12 ,  F04D29/16 ,  F04D29/32 ,  F02C3/04 ,  F01D5/02

    Abstract: The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade outer air seal section causing it to move away from its nominal position.

    Abstract translation: 本公开总体上涉及叶片外部空气密封部分安装件，其包括弹性弹簧元件，该弹性弹簧元件用于当叶片外部空气密封部分施加到叶片外部空气密封部分上的不均匀的力使其移动时，向叶片外部空气密封部分提供重新定心力 从其名义上的位置。

    CIRCUMFERENTIAL SEAL WITH SEAL DAMPENING ELEMENTS
    45.
    发明申请
    CIRCUMFERENTIAL SEAL WITH SEAL DAMPENING ELEMENTS 有权
    具有密封防潮元件的圆形密封

    公开(公告)号：US20160108750A1

    公开(公告)日：2016-04-21

    申请号：US14882672

    申请日：2015-10-14

    Applicant: United Technologies Corporation

    Inventor： Ross Wilson ,  Michael G. McCaffrey

    IPC: F01D11/02 ,  F16J15/44 ,  F01D11/00 ,  F16J15/16

    CPC classification number: F01D11/025 ,  F01D11/00 ,  F01D11/001 ,  F01D11/003 ,  F01D11/02 ,  F01D25/04 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/16 ,  F16J15/445

    Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a circumferential seal for a gas turbine engine includes a first beam, a second beam, a seal shoe and at least one feature between the first beam and second beam configured to retain a beam spacer, wherein the at least one feature is configured to dampen at least one of beam and shoe vibration of the circumferential seal. Another embodiment is directed to a circumferential seal including a beam spacer.

    Abstract translation: 本公开涉及燃气轮机发动机的密封系统。 在一个实施例中，用于燃气涡轮发动机的周向密封件包括第一梁，第二梁，密封靴以及被配置成保持梁间隔件的第一梁和第二梁之间的至少一个特征，其中至少一个特征是 被配置成阻尼所述周向密封件的梁和鞋的振动中的至少一个。 另一实施例涉及包括梁间隔件的周向密封。

    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE
    46.
    发明申请
    VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE 审中-公开
    用于涡轮发动机的可变区域风扇装置

    公开(公告)号：US20150361822A1

    公开(公告)日：2015-12-17

    申请号：US14762302

    申请日：2013-01-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  Raymond Surace ,  Tracy A. Propheter-Hinckley

    IPC: F01D17/16

    CPC classification number: F01D17/162 ,  F01D5/145 ,  F01D5/187

    Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

    Abstract translation: 用于涡轮发动机的可调节定子叶片包括轴，凸缘和绕可变叶片轴线枢转的定子叶片体。 定子叶片体在第一端和第二端之间轴向延伸。 定子叶片主体包括翼型件，空腔和位于第一端的主体表面。 空腔从体表面的入口轴向延伸到翼型中。 轴从第一端沿着可变叶片轴线延伸。 凸缘围绕入口和轴周向延伸，并且从定子叶片体径向延伸。

    Seal ring
    48.
    发明授权
    Seal ring 有权

    公开(公告)号：US11287045B2

    公开(公告)日：2022-03-29

    申请号：US16243632

    申请日：2019-01-09

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael G. McCaffrey ,  John R. Farris ,  Theodore W. Hall ,  John J. Korzendorfer ,  Elizabeth F. Vinson ,  Jeffrey Michael Jacques ,  John E. Paul ,  Ross Wilson ,  Edwin Otero ,  Alan W. Stoner

    IPC: F16J15/44 ,  F01D11/02

    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

    Balanced composite root region for a blade of a gas turbine engine
    49.
    发明授权
    Balanced composite root region for a blade of a gas turbine engine 有权

    公开(公告)号：US11280202B2

    公开(公告)日：2022-03-22

    申请号：US16841126

    申请日：2020-04-06

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey

    IPC: F01D5/30 ,  F01D5/28 ,  F01D5/14

    Abstract: A rotor blade for a gas turbine engine including an inner ply layer group includes a flared region and an airfoil region, a neck region between the flared region and the airfoil region; and a platform shell that comprises a platform shell root region, a platform shell platform region, and a platform shell neck region between the platform shell root region and the platform shell platform region, the platform shell root region sheathes the flared region, and the platform shell neck region flares outwardly away from the neck region to intersect the platform shell platform region at a platform shell neck region perimeter around an airfoil opening perimeter.

    Disk supported damper for a gas turbine engine
    50.
    发明授权
    Disk supported damper for a gas turbine engine 有权

    公开(公告)号：US11193376B2

    公开(公告)日：2021-12-07

    申请号：US16785999

    申请日：2020-02-10

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey

    IPC: F01D5/10

    Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis; and a damper pivot support that extends from a rim of the rotor disk, the damper pivot support comprising an aperture that defines a pivot axis parallel to the axis. A method to dampen a rotor blade of a gas turbine engine, includes independently pivoting a first damper and a second damper of a damper assembly about the pivot axis to respectively contact a first blade and a second blade in response to centrifugal force below a platform of the respective first blade and second blade.

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