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    SELF-SEALING APPARATUS THAT ADJUSTS A THROAT AREA OF A NOZZLE
    3.
    发明申请
    SELF-SEALING APPARATUS THAT ADJUSTS A THROAT AREA OF A NOZZLE 审中-公开
    自密封装置调节喷嘴的一个区域

    公开(公告)号：US20150315999A1

    公开(公告)日：2015-11-05

    申请号：US14796556

    申请日：2015-07-10

    Applicant: The Boeing Company

    Inventor： Eric L. Werner

    IPC: F02K1/10 ,  F02K1/15

    CPC classification number: F02K1/10 ,  F02K1/12 ,  F02K1/15

    Abstract: A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.

    Abstract translation: 飞机发动机中的流量控制面板二维，会聚/扩散喷嘴调节喷嘴的喉部区域，并且被配置为自密封，从而需要更少的部件并且提供喷嘴的喉部区域的更简化的结构。

    BLADDER TYPE VARIABLE AREA FAN NOZZLE
    5.
    发明申请
    BLADDER TYPE VARIABLE AREA FAN NOZZLE 有权
    叶片类型可变区域风扇喷嘴

    公开(公告)号：US20100139240A1

    公开(公告)日：2010-06-10

    申请号：US12440623

    申请日：2006-10-12

    Applicant: Glenn Levasseur

    Inventor： Glenn Levasseur

    IPC: F02K1/08 ,  F02K1/10 ,  F02K1/12

    CPC classification number: F02K1/10 ,  F02K1/085 ,  F02K1/1207 ,  F02K1/645

    Abstract: A variable fan nozzle for use in a gas turbine engine includes a nozzle section, such as an inflatable bladder, associated with a fan bypass passage for conveying a bypass airflow. The nozzle section has an internal fluid pressure that is selectively variable to influence the bypass airflow.

    Abstract translation: 用于燃气涡轮发动机的可变风扇喷嘴包括与用于传送旁路气流的风扇旁路通道相关联的喷嘴部分，例如可膨胀气囊。 喷嘴部分具有可选择地变化以影响旁路气流的内部流体压力。

    Jet engine provided with a thrust reverser
    6.
    发明授权
    Jet engine provided with a thrust reverser 失效
    喷气发动机配有推力反向器

    公开(公告)号：US5310117A

    公开(公告)日：1994-05-10

    申请号：US13964

    申请日：1993-02-05

    Applicant: Etienne Fage ,  Jean-Pierre Lair

    Inventor： Etienne Fage ,  Jean-Pierre Lair

    IPC: F02K1/11 ,  F02K1/60 ,  F02K1/10 ,  F02K1/12

    CPC classification number: F02K1/60 ,  F02K1/11 ,  Y02T50/671

    Abstract: A jet engine for an aircraft has a thrust reverser including one or more doors which define at least a part of the throat of the engine's nozzle. The engine further includes a latch mechanism for retaining the doors in a stowed position. The doors may be deployed for reversal of engine thrust, but are also capable while stowed of being pivoted in a limited way to change the cross-section area of the throat of the nozzle.

    Abstract translation: 用于飞机的喷气发动机具有推力反向器，其包括限定发动机喷嘴的喉部的至少一部分的一个或多个门。 发动机还包括用于将门保持在收起位置的闩锁机构。 门可以部署用于反转发动机推力，而且还能够以有限的方式枢转以改变喷嘴的喉部的横截面积。

    Flexible aft cowls for aircraft
    8.
    发明授权
    Flexible aft cowls for aircraft 有权

    公开(公告)号：US11492998B2

    公开(公告)日：2022-11-08

    申请号：US16721157

    申请日：2019-12-19

    Applicant: The Boeing Company

    Inventor： Luke D. Torjesen

    IPC: F02K1/10 ,  B64D33/04 ,  F02K1/82 ,  F01D25/30 ,  F02K3/06

    Abstract: Flexible aft cowls are disclosed. In some examples, an aircraft engine having a flexible aft cowl is disclosed. In some examples, the aircraft engine comprises an aft cowl having a flexible portion defining a throat area adjacent an engine core nozzle of the aircraft engine. In some examples, the flexible portion to move radially between a first radial position in response to pressure within a nacelle not exceeding a pressure threshold and a second radial position in response to pressure within the nacelle exceeding the pressure threshold. In some examples, the throat area defined by the flexible portion is greater when the flexible portion is in the second radial position than when the flexible portion is in the first radial position.

    System for actuating an exhaust cowl
    9.
    发明授权
    System for actuating an exhaust cowl 有权

    公开(公告)号：US10371089B2

    公开(公告)日：2019-08-06

    申请号：US14600824

    申请日：2015-01-20

    Applicant: United Technologies Corporation

    Inventor： Donald W. Peters ,  James P. Bangerter

    IPC: F02K1/06 ,  F02C3/10 ,  F01D25/24 ,  F16H21/04 ,  F16H21/54 ,  F02K1/09 ,  F02K1/15 ,  F02K1/12 ,  F02K1/10

    Abstract: In various embodiments, a cowl actuation system may comprise a cowl, an actuator, a bell crank, and a guide arm. The cowl may be configured to modulate at least a portion of the exhaust flow of a gas turbine engine. The bell crank may have a first end and a second end. The first end may be operatively coupled to the actuator. The second end may be operatively coupled to the cowl. The bell crank may be configured to pivot about a first point located between the first end and the second end. The first point may also be located along a diameter. The guide arm may have a third end and a fourth end. The third end may be mounted to a second point. The fourth end may be operatively coupled to the cowl. The second point may be located along the diameter.

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