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    Synchronized air modulating system
    5.
    发明授权
    Synchronized air modulating system 有权

    公开(公告)号：US11492977B2

    公开(公告)日：2022-11-08

    申请号：US16431955

    申请日：2019-06-05

    Applicant: United Technologies Corporation

    Inventor： Nicholas W. Kantany ,  Edward Boucher ,  Kristine Marie Carnavos ,  Robert Russell Mayer ,  Donald W. Peters

    IPC: F02C7/28 ,  F02C9/20 ,  F02K3/075 ,  F02K3/115

    Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

    SYNCHRONIZED AIR MODULATING SYSTEM
    7.
    发明申请
    SYNCHRONIZED AIR MODULATING SYSTEM 审中-公开

    公开(公告)号：US20190323435A1

    公开(公告)日：2019-10-24

    申请号：US16431955

    申请日：2019-06-05

    Applicant: United Technologies Corporation

    Inventor： Nicholas W. Kantany ,  Edward Boucher ,  Kristine Marie Carnavos ,  Robert Russell Mayer ,  Donald W. Peters

    IPC: F02C7/28 ,  F02K3/075 ,  F02K3/115 ,  F02C9/20

    Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

    SYNCHRONIZED AIR MODULATING SYSTEM
    9.
    发明申请
    SYNCHRONIZED AIR MODULATING SYSTEM 审中-公开
    同步空气调节系统

    公开(公告)号：US20160097327A1

    公开(公告)日：2016-04-07

    申请号：US14812926

    申请日：2015-07-29

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Nicholas W. Kantany ,  Edward Boucher ,  Kristine Marie Carnavos ,  Robert Russell Mayer ,  Donald W. Peters

    IPC: F02C7/28 ,  F02C9/20

    CPC classification number: F02C7/28 ,  F02C9/20 ,  F02K3/075 ,  F02K3/115

    Abstract: A system for modulating air flow in a gas turbine engine is provided. The system may include a seal wall comprising an opening, a seal door configured to slideably engage the seal wall, and an actuator configured to move the seal door over the opening. In various embodiments, the system may include a surface forward of the seal door. The seal door may be configured to seal a passage through the surface and the opening of the seal wall. A track may be disposed under the seal door. The track may comprise cobalt. Rollers may be coupled to the seal door with the rollers on the track. The seal door may comprise a nickel-chromium alloy. A sync ring may be coupled to the seal door. The actuator may be coupled through the sync ring to the seal door.

    Abstract translation: 提供一种用于调节燃气涡轮发动机中的气流的系统。 系统可以包括密封壁，密封壁包括开口，被配置为可滑动地接合密封壁的密封门以及构造成将密封门移动到开口上方的致动器。 在各种实施例中，系统可以包括密封门前面的表面。 密封门可以被构造成密封通过密封壁的表面和开口的通道。 轨道可以设置在密封门下方。 轨道可以包括钴。 辊子可以与轨道上的辊连接到密封门。 密封门可以包括镍 - 铬合金。 同步环可以联接到密封门。 致动器可以通过同步环耦合到密封门。

    GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT
    10.
    发明申请
    GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT 审中-公开
    气体涡轮发动机中型涡轮机支架轴承支持

    公开(公告)号：US20150337732A1

    公开(公告)日：2015-11-26

    申请号：US14818392

    申请日：2015-08-05

    Applicant: United Technologies Corporation

    Inventor： Robert Russell Mayer ,  George J. Kramer ,  Paul W. Palmer

    IPC: F02C7/06 ,  F02C7/36 ,  F02C7/20 ,  F02C3/045

    Abstract: A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1.

    Abstract translation: 燃气涡轮发动机包括与风扇流体连接的风扇和压缩机部。 压缩机包括高压压缩机和低压压缩机。 燃烧器流体地连接到压缩机部分。 涡轮部分流体地连接到燃烧器。 涡轮部分包括经由第一轴联接到高压压缩机的高压涡轮机。 低压涡轮机经由第二轴联接到低压压缩机。 齿轮架构在第二轴和风扇之间互连。 燃气涡轮发动机是具有大于六（6）的旁路比的高旁路齿轮飞机发动机。 低压涡轮机具有大于5的压力比，并且齿轮架构包括大于2.5:1的齿轮减速比。

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