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    Seal ring
    11.
    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.

    Coolant flow redirection component
    12.
    发明授权
    Coolant flow redirection component 有权

    公开(公告)号：US10822953B2

    公开(公告)日：2020-11-03

    申请号：US15800544

    申请日：2017-11-01

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Elizabeth F. Vinson

    IPC: F01D5/08

    Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore, and is static relative to the shaft. Each rotor is axially adjacent at least one other rotor and a gap is defined between each rotor and an adjacent rotor. A cooling passage for a cooling flow is defined between the shaft and the rotors, and a cooling flow redirection component is disposed at the gap and is operable to redirect the cooling flow in the cooling passage into the gap.

    Retaining ring end gap features
    13.
    发明授权
    Retaining ring end gap features 有权

    公开(公告)号：US10392966B2

    公开(公告)日：2019-08-27

    申请号：US15274306

    申请日：2016-09-23

    Applicant: United Technologies Corporation

    Inventor： Joseph T. Caprario ,  Noah Wadsworth ,  Mark E. Marler ,  James P. Allore ,  Elizabeth F. Vinson

    IPC: F01D25/04 ,  F01D5/30 ,  F01D5/32 ,  F01D9/02

    Abstract: A gas turbine engine and a retaining ring are disclosed. The gas turbine engine includes a rotating disc assembly, including a rotating disc, a cover plate, and a retaining ring disposed between the rotating disc and the cover plate, wherein the retaining ring axially retains the rotating disc and the cover plate, the retaining ring including a rotating disc face to interface with the rotating disc; a cover plate face to interface with the cover plate; and an end gap portion defining an end gap, wherein at least one of the rotating disc face, the cover plate face, and the end gap portion includes a stress reducing feature.

    SEAL SUPPORT STRUCTURE
    15.
    发明申请
    SEAL SUPPORT STRUCTURE 审中-公开
    密封支撑结构

    公开(公告)号：US20160115804A1

    公开(公告)日：2016-04-28

    申请号：US14921503

    申请日：2015-10-23

    Applicant: United Technologies Corporation

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

    IPC: F01D11/00 ,  F16J15/16

    Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

    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密封支撑结构包括构造成保持圆周密封件的密封支撑件和被构造用于将密封支撑结构安装到燃气涡轮发动机支架的发动机支撑件。 发动机支撑件包括至少一个通道，其构造成提供密封支撑结构的径向移动和密封支撑件的周向保持。 另一个实施例涉及一种包括周向密封和密封支撑结构的密封系统，该结构被配置为提供径向运动。

    COOLANT FLOW REDIRECTION COMPONENT
    17.
    发明申请
    COOLANT FLOW REDIRECTION COMPONENT 审中-公开
    冷却流程重定向组件

    公开(公告)号：US20160069193A1

    公开(公告)日：2016-03-10

    申请号：US14841265

    申请日：2015-08-31

    Applicant: United Technologies Corporation

    Inventor： Michael G. McCaffrey ,  Elizabeth F. Vinson

    IPC: F01D5/18 ,  F02C3/04

    CPC classification number: F01D5/187 ,  F01D5/082 ,  F02C3/04 ,  F04D29/053 ,  F04D29/321 ,  F04D29/584 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/201 ,  Y02T50/676

    Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor and mechanically connected to the compressor section via a shaft. Multiple rotors are disposed in one of the compressor section and the turbine section. Each of the rotors includes a rotor disk portion having a radially inward bore, and is static relative to the shaft. Each rotor is axially adjacent at least one other rotor and a gap is defined between each rotor and an adjacent rotor. A cooling passage for a cooling flow is defined between the shaft and the rotors, and a cooling flow redirection component is disposed at the gap and is operable to redirect the cooling flow in the cooling passage into the gap.

    Abstract translation: 燃气涡轮发动机包括压缩机部分，流体连接到压缩机部分的燃烧器和流体连接到燃烧器并经由轴机械连接到压缩机部分的涡轮部分。 多个转子设置在压缩机部分和涡轮部分之一中。 每个转子包括具有径向向内的孔的转子盘部分，并且相对于轴是静态的。 每个转子轴向相邻至少一个其他转子，并且在每个转子和相邻转子之间限定间隙。 用于冷却流的冷却通道限定在轴和转子之间，并且冷却流重定向部件设置在间隙处，并且可操作以将冷却通道中的冷却流重定向到间隙中。

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