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    Moveable exhaust plug liner
    1.
    发明授权
    Moveable exhaust plug liner 有权

    公开(公告)号：US10570852B2

    公开(公告)日：2020-02-25

    申请号：US15711229

    申请日：2017-09-21

    Applicant: United Technologies Corporation

    Inventor： Andre L. Bent ,  Steven H. Zysman ,  Nigel David Sawyers-Abbott

    IPC: F02K1/06 ,  F02K1/08 ,  F02K1/56 ,  F02C9/18 ,  F02K1/32

    Abstract: An exhaust section of a gas turbine engine includes an exhaust plug defining a plurality of exhaust plug apertures circumferentially spaced from each other. Also included is an exhaust nozzle radially offset from the exhaust plug defining an exhaust pathway between the exhaust plug and the exhaust nozzle. Further included is an exhaust plug liner having a non-uniform outer surface axially aligned with the exhaust plug apertures. The exhaust plug liner is rotatable relative to the exhaust plug between a first position and a second position to selectively change a cross-sectional area of the exhaust pathway during thrust reversal operation to reduce an amount of reverse thrust necessary.

    Link arm drag reducing device
    5.
    发明授权
    Link arm drag reducing device 有权

    公开(公告)号：US09670877B2

    公开(公告)日：2017-06-06

    申请号：US14320829

    申请日：2014-07-01

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  Matthew Exner

    IPC: F02K1/76 ,  F02K1/72

    CPC classification number: F02K1/763 ,  F02K1/72 ,  Y02T50/672

    Abstract: A flowpath channel has a blade pivotally connected along a longitudinal axis thereof, at opposing top and bottom ends thereof, to respective top and bottom portions of the flowpath channel. The chord axis of the blade, between leading and trailing edges thereof, is capable of pivoting parallel to and skewed from the flowpath. The top end of the blade and an attachment structure secured to the flowpath channel each include a race. A bearing is disposed therebetween, and the blade is rotatable about the longitudinal axis.

    GAS TURBINE ENGINE AND THRUST REVERSER ASSEMBLY THEREFORE
    6.
    发明申请
    GAS TURBINE ENGINE AND THRUST REVERSER ASSEMBLY THEREFORE 审中-公开
    气体涡轮发动机和逆变器组装

    公开(公告)号：US20160169157A1

    公开(公告)日：2016-06-16

    申请号：US14970214

    申请日：2015-12-15

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  James Power

    IPC: F02K1/72

    CPC classification number: F02K1/72 ,  F02K1/763 ,  F05D2260/56 ,  Y02T50/672

    Abstract: The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct by means of a camming surface, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.

    Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机的推力反向器。 当平移的整流罩从燃气涡轮发动机的机舱翻转后方时，在后方向上也平移了级联，并且通过凸轮表面将联接到级联的阻挡门转动到风扇管道中，从而将空气 风扇管通过级联。 在收起位置中，级联和阻塞门均位于机舱的径向内壁和/或平移罩的径向外侧。

    GAS TURBINE ENGINE AND THRUST REVERSER ASSEMBLY THEREFORE
    7.
    发明申请
    GAS TURBINE ENGINE AND THRUST REVERSER ASSEMBLY THEREFORE 审中-公开
    气体涡轮发动机和逆变器组装

    公开(公告)号：US20160153399A1

    公开(公告)日：2016-06-02

    申请号：US14955919

    申请日：2015-12-01

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  James Power

    IPC: F02K1/72

    CPC classification number: F02K1/72 ,  Y02T50/672

    Abstract: The present disclosure relates generally to a thrust reverser for a gas turbine engine. As a translating cowl is translated aft from the nacelle of the gas turbine engine, a cascade is also translated in the aft direction and a blocker door coupled to the cascade is pivoted into a fan duct, thereby diverting air in the fan duct through the cascade. In the stowed position, both the cascade and the blocker door are disposed radially outward of a radially inner wall of the nacelle and/or the translating cowl.

    Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机的推力反向器。 当平移的整流罩从燃气涡轮发动机的机舱翻转后方时，在后方向上也平移了级联，并且连接到级联的阻塞门枢转到风扇管道中，从而通过级联转向风扇管道中的空气 。 在收起位置中，级联和阻塞门均位于机舱的径向内壁和/或平移罩的径向外侧。

    Fluid additive system
    8.
    发明授权
    Fluid additive system 有权

    公开(公告)号：US11448128B2

    公开(公告)日：2022-09-20

    申请号：US16785853

    申请日：2020-02-10

    Applicant: United Technologies Corporation

    Inventor： Nigel David Sawyers-Abbott ,  Kenneth N. Baker

    IPC: F02C7/06 ,  F01D25/20

    Abstract: A lubrication system for a gas turbine engine includes a primary fluid tank to receive a primary fluid, at least one secondary fluid tank to receive at least one fluid additive, and a mixer. The mixer has at least a first inlet in fluid communication with the primary fluid tank and a second inlet in fluid communication with the at least one secondary fluid tank. The mixer has at least one outlet that delivers a mixture of the primary fluid and the at least one fluid additive to a gas turbine engine component.

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