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    Variable area nozzle for aircraft propulsion system
    2.
    发明授权
    Variable area nozzle for aircraft propulsion system 有权

    公开(公告)号：US12031445B2

    公开(公告)日：2024-07-09

    申请号：US17688419

    申请日：2022-03-07

    申请人： Rohr, Inc.

    发明人： Ann Khidekel

    IPC分类号： F01D17/14 ,  F01D17/24 ,  F02K1/12 ,  F02K1/80 ,  F02K1/11

    CPC分类号： F01D17/141 ,  F01D17/24 ,  F02K1/1207 ,  F02K1/805 ,  F02K1/11 ,  F02K1/12

    摘要： An apparatus is provided for an aircraft propulsion system. This apparatus includes a variable area nozzle apparatus. The variable area nozzle apparatus includes a plurality of panels, a plurality of inter-panel members and an actuation system. The panels are arranged circumferentially about an axial centerline. The panels include a first panel and a second panel. The inter-panel members are arranged circumferentially about the axial centerline. The inter-panel members include a first inter-panel member between and connected to the first panel and the second panel. The first inter-panel member is configured from or otherwise includes an elastomeric material. The actuation system is configured to move the panels and the inter-panel members between a restricted flow arrangement and an unrestricted flow arrangement. The actuation system includes a first linkage and a second linkage. The first linkage is coupled to the first panel. The second linkage is coupled to the second panel.

    AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET
    3.
    发明公开
    AIRCRAFT PROPULSION SYSTEM WITH VARIABLE AREA INLET 审中-公开

    公开(公告)号：US20240092495A1

    公开(公告)日：2024-03-21

    申请号：US18368922

    申请日：2023-09-15

    申请人： Rohr, Inc.

    发明人： Imad D. Ghandour ,  Timothy Gormley

    IPC分类号： B64D33/02 ,  F02C7/042 ,  F02K1/12

    CPC分类号： B64D33/02 ,  F02C7/042 ,  F02K1/12

    摘要： An assembly is provided for an aircraft. This assembly includes a variable area inlet for an aircraft propulsion system. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage and an outer inlet passage. The inlet door is configured to move outward from a closed position to an open position. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends into the inlet structure to the inner inlet passage.

    Plunger Seal Apparatus and Sealing Method
    4.
    发明公开
    Plunger Seal Apparatus and Sealing Method 审中-公开

    公开(公告)号：US20230213003A1

    公开(公告)日：2023-07-06

    申请号：US17567385

    申请日：2022-01-03

    申请人： General Electric Company

    发明人： Anthony Michael Gunasekera ,  Donald M. Corsmeier ,  Bernard J. Renggli ,  Steven Kirgiss

    IPC分类号： F02K1/80 ,  F16J15/34 ,  F02K1/12

    CPC分类号： F02K1/805 ,  F02K1/12 ,  F16J15/3436

    摘要： In some embodiments, apparatuses are provided herein useful to sealing a gap, such as a gap between a gas turbine engine nozzle flap and sidewall. An apparatus for sealing such a gap may be a plunger seal that includes a plunger, a retaining element, a guide pin, and a biasing element. The plunger includes a sealing edge and an actuating edge having at least one recess and an opening formed therein. The biasing element and a portion of the guide pin are nested in the recess. The retaining element anchor the plunger to the retaining element. The retaining element also anchors the plunger seal to the housing When installed in a gap, the housing engages the flap and the plunger engages the sidewall. The biasing element is under compression and urges the guide pin into the actuating edge to urge the plunger toward the sidewall and seal the gap.

    CONTROLLING NOZZLE AREAS OF VARIABLE AREA FAN NOZZLES
    7.
    发明申请
    CONTROLLING NOZZLE AREAS OF VARIABLE AREA FAN NOZZLES 有权
    控制可变区风扇喷嘴的喷嘴区域

    公开(公告)号：US20160281639A1

    公开(公告)日：2016-09-29

    申请号：US14665627

    申请日：2015-03-23

    申请人： The Boeing Company

    发明人： Jason Joseph Jackowski ,  Matthew A. Carpenter ,  Kent Edmund Karnofski

    IPC分类号： F02K1/18 ,  F02K3/02 ,  F02K1/12

    CPC分类号： F02K1/18 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/15 ,  F02K3/025 ,  F05D2270/821 ,  Y02T50/671 ,  Y02T50/677

    摘要： Provided are methods and systems for measuring and controlling nozzle areas of variable area fan nozzles. A control system attached to a nozzle may include a cable having one end connected to a linear displacement measuring device, such as a string potentiometer. The other end of the cable may be connected to a petal. A reference portion of the cable extends across multiple petals of the nozzle and, in some embodiments, substantially parallel to the nozzle circumference. The linear displacement measuring device measures any changes in the length of this reference portion as the petals actuate outwardly or inwardly during operation of the nozzle. The output of the linear displacement measuring device may be used to control actuators that move the petals. In some embodiments, potentiometer's output may be combined with one or more outputs from other sensors, such as a linear variable differential transducer and/or thermocouple.

    摘要翻译： 提供了用于测量和控制可变区域风扇喷嘴的喷嘴区域的方法和系统。 附接到喷嘴的控制系统可以包括具有连接到诸如串电位计的线性位移测量装置的一端的电缆。 电缆的另一端可以连接到花瓣。 电缆的参考部分延伸穿过喷嘴的多个花瓣，并且在一些实施例中基本上平行于喷嘴圆周。 线性位移测量装置在喷嘴操作期间花瓣向外或向内致动时测量该参考部分的长度的任何变化。 线性位移测量装置的输出可用于控制移动花瓣的致动器。 在一些实施例中，电位计的输出可以与来自其他传感器的一个或多个输出组合，例如线性可变差分换能器和/或热电偶。

    HIGH-CYCLE, SHORT RANGE-OF-MOTION LINKAGE APPARATUS FOR GAS TURBINE ENGINE APPLICATIONS
    8.
    发明申请
    HIGH-CYCLE, SHORT RANGE-OF-MOTION LINKAGE APPARATUS FOR GAS TURBINE ENGINE APPLICATIONS 审中-公开
    用于气体涡轮发动机应用的高周期，短距离运动联动装置

    公开(公告)号：US20160258315A1

    公开(公告)日：2016-09-08

    申请号：US15007939

    申请日：2016-01-27

    申请人： Roller Bearing Company of America, Inc.

    发明人： Sean Vintinner ,  Samuel A. Nunn

    IPC分类号： F01D17/14 ,  F02K1/12 ,  F01D17/10 ,  F02K3/02 ,  F01D9/04

    CPC分类号： F01D17/14 ,  F01D9/041 ,  F01D17/105 ,  F01D17/145 ,  F02K1/12 ,  F02K3/02 ,  F05D2220/323 ,  F05D2240/54 ,  F05D2260/50 ,  F16C9/04 ,  F16C11/0614 ,  F16C23/045 ,  F16C33/201 ,  F16C2360/00

    摘要： A high-cycle, short range-of-motion linkage apparatus for actuation of a turbofan engine component includes a pivot member having a head portion and a stem, and an actuator moveable between a first and second position. An actuator first end defines a receiving portion into which the stem is removably secured. An actuator second end defines a coupling member pivotally connected to a turbofan engine structural member and moveable between a first and second position corresponding to the actuator first and second positions. A spherical plain bearing pivotally connects the pivot member head to the turbofan engine component and includes an inner member, an outer member swaged around the inner member and disposed between the inner member and the head of the pivot member, and a liner disposed between the inner and outer members. The outer member defines a range of motion in relation to the inner member up to 90°.

    摘要翻译： 一种用于驱动涡扇风扇发动机部件的高周期，短范围的动作联动装置包括具有头部和杆的枢转构件以及可在第一和第二位置之间移动的致动器。 致动器第一端限定了可拆卸地固定杆的接收部分。 致动器第二端限定枢转地连接到涡轮风扇发动机结构构件并且可以在对应于致动器第一和第二位置的第一和第二位置之间移动的联接构件。 球面滑动轴承将枢转构件头部枢转地连接到涡轮风扇发动机部件，并且包括内部构件，围绕内部构件锻造并且设置在内部构件和枢转构件的头部之间的外部构件，以及设置在内部构件 和外部成员。 外部构件相对于内部构件限定高达90°的运动范围。

    Nacelle for an aircraft bypass turbojet engine
    9.
    发明授权
    Nacelle for an aircraft bypass turbojet engine 有权
    飞机旁路涡轮喷气发动机的机舱

    公开(公告)号：US09279385B2

    公开(公告)日：2016-03-08

    申请号：US14093928

    申请日：2013-12-02

    申请人： AIRCELLE

    发明人： Nicolas Dezeustre ,  Patrick Stella

    IPC分类号： F02K1/12

    CPC分类号： F02K1/12 ,  F02K1/1207 ,  F02K1/1223 ,  F05D2260/52 ,  F05D2300/501 ,  Y02T50/671

    摘要： A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means.

    摘要翻译： 用于飞机旁路涡轮喷气发动机的机舱包括下游，围绕旁路涡轮喷气发动机的一部分的内部静止结构以及围绕内部静止结构的外部结构，其限定了气流循环的环形流动路径。 外部结构包括设置在外部结构的下游端并面向环形流动路径定位的移动翼片。 每个移动挡板可以旋转，以响应于通过气流循环施加在移动挡板上的压力而移动到相对于空转位置增加或减小环形流路横截面高度的位置 通过面对的环形流动路径。 在弹性返回装置的作用下，移动挡板可以从横截面增加或还原位置返回到另一位置。