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    VARIABLE-GEOMETRY CONVERGENT-DIVERGENT EXHAUST NOZZLE
    1.
    发明公开
    VARIABLE-GEOMETRY CONVERGENT-DIVERGENT EXHAUST NOZZLE 审中-公开

    公开(公告)号：US20240191672A1

    公开(公告)日：2024-06-13

    申请号：US18234148

    申请日：2023-08-15

    申请人： ROLLS-ROYCE plc

    发明人： Jack F. COLEBROOKE

    IPC分类号： F02K1/12

    CPC分类号： F02K1/1207

    摘要： A variable-geometry convergent-divergent exhaust nozzle includes: a duct to receive exhaust from a combustor; and first and second flap assemblies each including proximal and distal flaps. The first and second proximal flaps are rotatably coupled to the exhaust duct and include entry surfaces that in part define a nozzle passageway to convey the exhaust to an exterior of the engine. The first and second distal flaps are rotatably coupled to the first and second proximal flaps. The first distal flap includes converging and diverging surfaces angled with respect to each other. The second distal flap includes converging and diverging surfaces angled with respect to each other. The converging surfaces define at least in part a convergent portion of the nozzle passageway. The first and second diverging surfaces define at least in part a divergent portion of the nozzle passageway.

    JET VECTORING APPARATUS
    2.
    发明公开
    JET VECTORING APPARATUS 审中-公开

    公开(公告)号：US20240052799A1

    公开(公告)日：2024-02-15

    申请号：US18260396

    申请日：2021-12-01

    申请人： The Secretary of State for Defence

    发明人： Peter Geoffrey Martin

    IPC分类号： F02K1/12 ,  F02K1/09

    CPC分类号： F02K1/1207 ,  F02K1/09

    摘要： A jet vectoring apparatus has a nozzle (1) which comprises a throat aperture (8) and an exit aperture (9), the apparatus also having a post exit surface (10). Variation of at least one of the throat aperture (8), exit aperture (9) and post exit surface causes a pressure differential upon the post exit surface which permits the direction of propulsive jet flow (3) (also known as jet thrust) to be varied relative to the longitudinal axis (2) of the apparatus.

    Thrust reverse variable area fan nozzle
    3.
    发明授权
    Thrust reverse variable area fan nozzle 有权

    公开(公告)号：US10001080B2

    公开(公告)日：2018-06-19

    申请号：US14462682

    申请日：2014-08-19

    申请人： The Boeing Company

    发明人： David F. Cerra ,  Robert H. Willie

    IPC分类号： F02K1/72 ,  F02K1/12 ,  F02K3/02 ,  F02K1/76 ,  F02K1/70 ,  F02K1/11

    CPC分类号： F02K1/72 ,  F02K1/11 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/70 ,  F02K1/763 ,  F02K3/025 ,  F05D2260/50

    摘要： A thrust reverse variable area nozzle system for a nacelle of an aircraft engine system may include a reverse thrust opening disposed in the nacelle, and a thrust reverser door pivotally movable relative to the nacelle for selectively covering the reverse thrust opening, wherein the thrust reverser door is pivotally movable between a first position for completely covering the reverse thrust opening, a second position for partially uncovering a forward portion of the reverse thrust opening and discharging a bypass airflow through the forward portion of the reverse thrust opening in a forward direction, and a third position for partially uncovering an aft portion of the reverse thrust opening and discharging the bypass airflow through the aft portion of the reverse thrust opening in an aft direction.

    Pivoting ring petal actuation for variable area fan nozzle
    5.
    发明授权
    Pivoting ring petal actuation for variable area fan nozzle 有权

    公开(公告)号：US09650991B2

    公开(公告)日：2017-05-16

    申请号：US13928407

    申请日：2013-06-27

    申请人： The Boeing Company

    发明人： Christopher T. Jasklowski

    IPC分类号： F02K1/18 ,  F02K1/12 ,  F02K1/72

    CPC分类号： F02K1/18 ,  F02K1/1207 ,  F02K1/72 ,  F05D2250/11 ,  F05D2260/56

    摘要： A variable area fan nozzle comprising an array of rigid petals and a petal actuation system comprising left and right assemblies, each assembly comprising: a multiplicity of tracks attached to or integrally formed with respective petals; a curved pivoting ring segment; an actuator coupled to the ring segment; and a multiplicity of sets of cam followers spaced along the ring segment and aligned with respective tracks. Each ring segment is pivotable between first and second angular positions depending on how the state of the actuator changes. As one ring segment pivots in one direction, one set of cam followers exert inward forces on the tracks to deflect petals inward; as that ring segment pivots in the other direction, another set of cam followers exert outward forces on the tracks to deflect petals outward.

    ACTIVELY CONTROLLED COOLING AIR EXHAUST DOOR ON AN AIRCRAFT ENGINE NACELLE
    8.
    发明申请
    ACTIVELY CONTROLLED COOLING AIR EXHAUST DOOR ON AN AIRCRAFT ENGINE NACELLE 审中-公开
    飞机控制冷却空气排气门在飞机发动机上

    公开(公告)号：US20160047274A1

    公开(公告)日：2016-02-18

    申请号：US14462106

    申请日：2014-08-18

    申请人： Rohr, Inc.

    发明人： Kevin Woolworth ,  Michael S. Pretty ,  Daniel J. Shetzer ,  Martin Channell ,  Thomas Holt

    IPC分类号： F01D25/24

    CPC分类号： F01D25/24 ,  F01D25/14 ,  F02C6/08 ,  F02C7/18 ,  F02C9/18 ,  F02K1/06 ,  F02K1/10 ,  F02K1/1207 ,  F02K1/30 ,  F02K1/32 ,  F02K1/34 ,  F02K1/70 ,  F02K1/72 ,  F02K1/76 ,  F02K1/763 ,  F02K1/766 ,  F02K1/805 ,  Y02T50/675

    摘要： An assembly is provided for a turbofan engine. This turbofan engine assembly includes a cowling, a door and an actuation mechanism configured to actuate movement of the door in response to receiving a control signal. The cowling is configured to form a compartment at least partially around a case of the turbofan engine. The cowling includes an exhaust port that is fluidly coupled with the compartment. The door is configured to at least partially open and close the exhaust port. This variable exhaust port may be opened in case increased airflow is needed through the compartment, such as when increased cooling airflow is needed through an environmental air precooler that cools compressed air for the aircraft cabin and the precooler exhausts its cooling air into the compartment.

    摘要翻译： 为涡扇发动机提供组件。 该涡轮风扇发动机组件包括整流罩，门和致动机构，其构造成响应于接收控制信号致动门的运动。 整流罩配置成至少部分地围绕涡轮风扇发动机的壳体形成隔间。 整流罩包括与隔室流体耦合的排气口。 门构造成至少部分地打开和关闭排气口。 例如当需要通过冷却用于飞行器机舱的压缩空气的预冷器的环境空气预冷器来增加冷却气流时，可以打开该可变排气口以防止需要增加气流，并且预冷器将其冷却空气排出到隔间内。

    Pivoting Ring Petal Actuation for Variable Area Fan Nozzle
    9.
    发明申请
    Pivoting Ring Petal Actuation for Variable Area Fan Nozzle 有权
    可变区域风扇喷嘴的旋转环花瓣致动

    公开(公告)号：US20150000305A1

    公开(公告)日：2015-01-01

    申请号：US13928407

    申请日：2013-06-27

    申请人： The Boeing Company

    发明人： Christopher T. Jasklowski

    IPC分类号： F02C7/00

    CPC分类号： F02K1/18 ,  F02K1/1207 ,  F02K1/72 ,  F05D2250/11 ,  F05D2260/56

    摘要： A variable area fan nozzle comprising an array of rigid petals and a petal actuation system comprising left and right assemblies, each assembly comprising: a multiplicity of tracks attached to or integrally formed with respective petals; a curved pivoting ring segment; an actuator coupled to the ring segment; and a multiplicity of sets of cam followers spaced along the ring segment and aligned with respective tracks. Each ring segment is pivotable between first and second angular positions depending on how the state of the actuator changes. As one ring segment pivots in one direction, one set of cam followers exert inward forces on the tracks to deflect petals inward; as that ring segment pivots in the other direction, another set of cam followers exert outward forces on the tracks to deflect petals outward.

    摘要翻译： 一种可变区域风扇喷嘴，包括刚性花瓣阵列和包括左组件和右组件的花瓣致动系统，每个组件包括：多个轨道，其连接到或与其相应的花瓣一体形成; 弯曲的枢转环段; 耦合到所述环段的致动器; 以及沿着环形部分间隔开并与相应的轨道对准的多组凸轮从动件。 根据致动器的状态如何变化，每个环段可在第一和第二角位置之间枢转。 当一个环段在一个方向上枢转时，一组凸轮从动件在轨道上施加向内的力以使花瓣向内偏转; 当该环段沿另一方向枢转时，另一组凸轮从动件在轨道上施加向外的力以使花瓣向外偏转。

    GAS TURBINE EXHAUST NOISE REDUCTION
    10.
    发明申请
    GAS TURBINE EXHAUST NOISE REDUCTION 有权
    气体涡轮排气噪声减少

    公开(公告)号：US20140284395A1

    公开(公告)日：2014-09-25

    申请号：US13746006

    申请日：2013-01-21

    申请人： LOCKHEED MARTIN CORPORATION

    发明人： Anthony Richard Pilon

    IPC分类号： F02K1/12

    CPC分类号： F02K1/1207 ,  F02K1/008 ,  F02K1/1215 ,  F02K1/15 ,  F02K1/46

    摘要： A gas turbine jet noise reduction apparatus including a variable geometry gas turbine engine nozzle comprising a circumferentially distributed array of nozzle flap panels supported for alternate collective splaying and gathering motion, with the collective splaying motion of the flap panels being from a narrow position defining a minimum cross-sectional area at a nozzle exit plane, to a wide position defining a maximum cross-sectional area at the nozzle exit plane. A plurality of nozzle seal panels is supported in a circumferentially distributed array within the array of nozzle flap panels. A seal panel actuator is operatively engageable with the seal panels to deflect the seal panels radially inward into respective deployed positions to reduce jet noise by increasing exhaust stream mixing with ambient air.

    摘要翻译： 一种燃气轮机喷气式噪声降低装置，包括可变几何形状的燃气涡轮发动机喷嘴，其包括支撑用于交替的集体展开和收集运动的喷嘴挡板的周向分布的阵列，其中所述挡板的所述集体张开运动来自限定最小值 在喷嘴出口平面处的横截面面积，限定在喷嘴出口平面处的最大横截面面积的宽位置。 多个喷嘴密封面板被支撑在喷嘴挡片阵列内的周向分布的阵列中。 密封面板致动器可操作地与密封面板接合，以将密封面板径向向内偏转到相应的展开位置，以通过增加与环境空气的排气流混合来减少喷射噪声。