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    BIELLE COUDEE EQUIPEE D'AU MOINS UN MOYEN D'AUTO-ALIGNEMENT
    2.
    发明公开
    BIELLE COUDEE EQUIPEE D'AU MOINS UN MOYEN D'AUTO-ALIGNEMENT 有权
    与至少一个自对准指配备BENT VERBINDUNGSSTANGE

    公开(公告)号：EP2411686A1

    公开(公告)日：2012-02-01

    申请号：EP10715310.8

    申请日：2010-03-09

    申请人： Aircelle

    发明人： VAUCHEL, Guy, Bernard ,  SEGAT, Peter ,  BAILLARD, André ,  BOURET, Georges, Alain

    IPC分类号： F16C7/06 ,  F16C7/04 ,  F02K1/12 ,  F02K1/70 ,  F02K1/72

    CPC分类号： F16C7/04 ,  F02K1/1261 ,  F02K1/70 ,  F02K1/72 ,  F16C7/06 ,  Y10T74/2142

    摘要： The invention relates to a bent connecting rod (31) for linking a first assembly to a second assembly which are movable relative to each other and through which a flow in the space defined thereby passes. The rod has at least one first and one second pivot point (35, 38) that are designed so as to enable the pivotal movement of the connecting rod (31) relative to said first and second assemblies, respectively, the bent connecting rod (31) being suitably positionable such that the bend (40) is located upstream from said flow relative to said second pivot point (38), said second pivot point (38) being suitably built into the second movable assembly, characterized in that the bent connecting rod (31) includes at least two portions (33, 37) linked together by at least one self-aligning means (39a, 39b).

    FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH SLIDING ACTUATION SYSTEM
    5.
    发明公开
    FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH SLIDING ACTUATION SYSTEM 有权
    随着对GONDOLA燃气涡轮发动机变截面带滑控制系统NOZZLE旁路通道

    公开(公告)号：EP2074312A1

    公开(公告)日：2009-07-01

    申请号：EP06850518.9

    申请日：2006-10-12

    申请人： United Technologies Corporation

    发明人： GUKEISEN, Robert L.

    IPC分类号： F02K1/12 ,  F02K3/06

    CPC分类号： F02K1/1261 ,  F02K1/12 ,  F02K1/1253 ,  F02K3/06 ,  F02K3/075 ,  F05D2260/50

    摘要： A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area.

    摘要翻译： 风扇可变面积喷嘴（FVAN）包括翼板组件而变化的风扇喷嘴出口面积。 的致动器系统驱动的滑动驱动环相对于安装到风扇机舱滑块轨道的多个通过襟翼联接以调节襟翼组件的每个翼片到变桨翼片组件绕圆周执行线以改变所述环形设计风扇喷嘴的直径 风扇机舱和核心机舱之间的出口区域。 该FVAN可以被分离成其由所述致动器系统，以提供一个低轮廓的阻力不对称风扇喷嘴出口面积的相关联的致动器的unabhängig每个可调整驱动环的扇区的倍数。

    Variable area nozzle in a gas turbine engine
    6.
    发明公开
    Variable area nozzle in a gas turbine engine 有权
    DüsemitveränderlichemQuerschnitt in einem Gasturbinenmotor

    公开(公告)号：EP1900909A2

    公开(公告)日：2008-03-19

    申请号：EP07253222.9

    申请日：2007-08-16

    申请人： Rolls-Royce plc

    发明人： Lace, Brian Richard

    IPC分类号： F01D17/16

    CPC分类号： F01D17/162 ,  F02K1/1261 ,  F02K3/04

    摘要： A gas turbine engine 10 comprises a fan 13, a bypass duct 22 having a nozzle 23, through which fluid B from the fan 13 flows, and a variable area nozzle device 34 located in the nozzle 23. The variable area nozzle device 34 comprises an arcuate fairing 36 having one end 44 in slidable cooperation with the bypass duct 22. In a deployed position the area of the nozzle is reduced from that when stowed thereby improving engine operability and efficiency.

    摘要翻译： 燃气涡轮发动机10包括风扇13，具有喷嘴23的旁通管道22，来自风扇13的流体B流过该喷嘴23，以及位于喷嘴23中的可变区域喷嘴装置34.可变区域喷嘴装置34包括： 弧形整流罩36具有与旁通管道22可滑动配合的一端44.在展开位置，喷嘴的区域与收起的区域相比减小，从而提高发动机的可操作性和效率。

    INVERSEUR DE POUSSÉE POUR NACELLE DE TURBORÉACTEUR D'AÉRONEF
    8.
    发明公开
    INVERSEUR DE POUSSÉE POUR NACELLE DE TURBORÉACTEUR D'AÉRONEF 有权
    SCHUBUMKEHRERFÜRGONDEL EINES FLUGZEUGTURBOFANS

    公开(公告)号：EP3155252A2

    公开(公告)日：2017-04-19

    申请号：EP15733812.0

    申请日：2015-06-05

    申请人： Safran Nacelles

    发明人： GONIDEC, Patrick ,  KERBLER, Olivier ,  HUE, Corentin ,  BOILEAU, Patrick

    IPC分类号： F02K1/12

    CPC分类号： F02K1/72 ,  F02K1/1261 ,  F02K1/763 ,  Y02T50/671

    摘要： The invention relates to a thrust reverser (18) for a nacelle (10) of an aircraft turbofan including at least one movable thrust reverser cover (20), a means for locking the cover (20), a variable-exhaust output nozzle (22) which is arranged forming a downstream extension of said cover (20) and which is movable, and at least one actuator (24) which includes an actuator rod (28) suitable for moving the variable nozzle (22) and the movable cover (20), characterised in that the reverser (18) is provided with a resilient coupler (30) comprising a body (32) which is rigidly connected to the thrust reverser cover (20), resilient return means (48) and abutments which are supported by the body (32) of the coupler (30) and which engage with the actuating rod (28) of the actuator (24) such as to resiliently return the nozzle (22) into the neutral position thereof, said return means (48) being calibrated such that, when the cover (20) is unlocked, the return means (48) oppose the relative movement of the actuating rod (28) relative to the cover (20), such as to enable the movement of the assembly consisting of the cover (20) and the nozzle (22), and when the cover (20) is locked, the actuator (24) drives the actuating rod (28) against the return means (48), such as to enable the movement of the nozzle (22).

    摘要翻译： 本发明涉及一种用于飞机涡扇风机的机舱（10）的推力反向器（18），其包括至少一个可移动推力反向器盖（20），用于锁定盖（20）的装置，可变排气输出喷嘴（22） ），其布置成形成所述盖（20）的下游延伸部并且可移动;以及至少一个致动器（24），其包括适于移动可变喷嘴（22）和可动盖（20）的致动器杆（28） ），其特征在于，所述反向器（18）设置有弹性联接器（30），弹性联接器（30）包括刚性地连接到推力反向器盖（20）的主体（32），弹性返回装置（48） 联接器（30）的主体（32）并且与致动器（24）的致动杆（28）接合，以便将喷嘴（22）弹性地返回到其中立位置，所述返回装置（48）是 被校准为使得当盖（20）被解锁时，返回装置（48）与相对移动器相对 致动杆（28）相对于盖（20）的移动，使得能够使由盖（20）和喷嘴（22）组成的组件移动，并且当盖（20）被锁定时， 致动器（24）将致动杆（28）驱动抵靠返回装置（48），以使喷嘴（22）能够移动。

    NACELLE DE TURBORÉACTEUR À DOUBLE FLUX
    10.
    发明公开
    NACELLE DE TURBORÉACTEUR À DOUBLE FLUX 审中-公开
    旁通燃气涡轮GONDEL

    公开(公告)号：EP2268910A2

    公开(公告)日：2011-01-05

    申请号：EP09742294.3

    申请日：2009-04-09

    申请人： Aircelle

    发明人： VAUCHEL, Guy Bernard

    IPC分类号： F02K1/12 ,  F02K1/72

    CPC分类号： F02K1/1261 ,  F02K1/72 ,  F05D2260/50

    摘要： The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl (6) mounted such that it can move in translation in a direction substantially parallel to a longitudinal axis of the nacelle and able to move alternately from a closed position in which it ensures the aerodynamic continuity of the nacelle and covers deflection means (70) and an open position in which it opens a passage in the nacelle and uncovers the deflection means, the said moving cowl also being extended by at least one nozzle section (7) mounted at a downstream end of the said moving cowl, characterized in that the nozzle section comprises at least one panel (10) mounted such that it can rotate about at least one pivot about an axis substantially perpendicular to a longitudinal axis of the nacelle, the said panel further being connected to a fixed fairing structure (2) of the turbojet engine by at least one link rod (11) mounted such that it can rotate about anchor points on the panel of the nozzle section and on the fixed structure, respectively.