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    PIVOT THRUST REVERSER WITH MULTI-POINT ACTUATION
    31.
    发明申请
    PIVOT THRUST REVERSER WITH MULTI-POINT ACTUATION 有权
    PIVOT扭矩反转器具有多点执行

    公开(公告)号：US20150008268A1

    公开(公告)日：2015-01-08

    申请号：US14184376

    申请日：2014-02-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02K1/62 ,  B64D29/00

    CPC classification number: F02K1/763 ,  B23P19/04 ,  B64D29/00 ,  B64D33/04 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/64 ,  F02K1/72 ,  F05D2260/50 ,  Y10T29/49229

    Abstract: One embodiment includes a pivot thrust reverser with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

    Abstract translation: 一个实施例包括枢转推力反向器，其具有带有上连杆的第一枢转门和下连杆以及与第一枢转门隔开的第二枢转门，具有上连杆和下连杆。 第一致动器位于附接位置的第一侧以驱动第一枢轴门。 第二致动器位于附接位置的第二侧以驱动第二枢转门。 第三致动器基本上位于与附接位置径向相对的位置，以驱动第一枢转门和第二枢转门。 第一枢转门构造成通过第一致动器和第三致动器由收起位置枢转到展开位置。 第二枢转门构造成通过第二致动器和第三致动器由收起位置枢转到展开位置。

    Multi core geared gas turbine engine
    35.
    发明授权
    Multi core geared gas turbine engine 有权

    公开(公告)号：US11255263B2

    公开(公告)日：2022-02-22

    申请号：US16733504

    申请日：2020-01-03

    Applicant: United Technologies Corporation

    Inventor： Marc J. Muldoon ,  Joseph B. Staubach ,  Jesse M. Chandler ,  Neil Terwilliger ,  Gabriel L. Suciu

    IPC: F02C7/36 ,  F02C6/20

    Abstract: An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

    Ceramic liner for a turbine exhaust case
    37.
    发明授权
    Ceramic liner for a turbine exhaust case 有权

    公开(公告)号：US10801411B2

    公开(公告)日：2020-10-13

    申请号：US14917396

    申请日：2014-08-19

    Applicant: United Technologies Corporation

    Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

    IPC: F02C7/20 ,  F02K1/82 ,  F01D25/28 ,  F01D25/26

    Abstract: A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positions. A ceramic-based liner is located at an aft portion of the core engine. The ceramic-based component mechanically interfaces with the movable portion of the nacelle when the nacelle is in the fully closed position. A turbine section and a method of accommodating thermally-induced dimensional change of engine components are also disclosed.

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