公开(公告)号：US20170298870A1

公开(公告)日：2017-10-19

申请号：US15290115

申请日：2016-10-11

Applicant: AIRCELLE

Inventor： Patrick BOILEAU ,  Olivier KERBLER

IPC: F02K1/60 ,  F02K1/76

CPC classification number: F02K1/766 ,  F02K1/09 ,  F02K1/72 ,  F02K1/763 ,  F02K1/80

Abstract: A thrust reverser of a turbofan pod is provided that includes movable cowlings that retract relative to stationary front structure to reveal stationary or movable thrust reverser cascades, as well as a secondary variable nozzle section connected to the movable cowlings by guiding means enabling movement controlled by actuators engaged with the front structure to apply an axial thrust. The actuators are directly connected to the secondary nozzle, and in that the thrust reverser comprises latches connected to the movable cowlings, having two positions providing, alternately, latching onto the front structure or latching onto the control of the secondary nozzle.

公开(公告)号：US20140291066A1

公开(公告)日：2014-10-02

申请号：US14304555

申请日：2014-06-13

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE ,  Pierre CARUEL ,  Patrick GONIDEC ,  Patrick BOILEAU

IPC: F02C7/045

CPC classification number: F02C7/045 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286

Abstract: An air intake structure for a turbojet engine nacelle includes a substantially annular main structure having an internal wall, an external wall and an air intake lip structure connecting the external and internal walls upstream. The air intake structure also includes a first acoustic attenuation structure which has a holed acoustic skin, a cellular core and a solid rear skin with which the internal wall is equipped, and a second acoustic attenuation structure having a similar architecture fitted to a part of the air intake lip substantially near a junction with the internal wall. The rear skin of the first acoustic attenuation structure is aligned with the rear skin of the second acoustic attenuation structure, both of rear skins being structural.

Abstract translation: 用于涡轮喷气发动机机舱的进气结构包括具有连接外壁和内壁上游的内壁，外壁和进气口结构的基本上环形的主结构。 进气结构还包括第一声衰减结构，该第一声衰减结构具有孔声学皮肤，多孔芯和固定的后壁，内壁装有该第一声衰减结构，以及具有类似结构的第二声衰减结构， 进气口基本上在与内壁的接合处附近。 第一声​​衰减结构的后表皮与第二声衰减结构的后表皮对准，两个后表皮都是结构的。

公开(公告)号：US20160101871A1

公开(公告)日：2016-04-14

申请号：US14974352

申请日：2015-12-18

Applicant: AIRCELLE

Inventor： Patrick BOILEAU ,  Samuel BLONDEAU

IPC: B64D29/06 ,  F01D25/24 ,  E05F3/18 ,  E05D7/00 ,  E05F3/20

CPC classification number: B64D29/06 ,  B64D29/08 ,  E05D7/00 ,  E05F3/18 ,  E05F3/20 ,  F01D25/24 ,  F05D2220/323

Abstract: An assistance device is provided to maneuver of a cover of a nacelle of a turbojet engine. The assistance device includes a joint collinear with an existing joint or hinge for a fitting of the cover, and the joint of the device is rigidly secured to an angled part of which one end bears on the fitting of the cover and of which one point is hinged to a compression spring in order to apply assistance momentum to the fitting of the cover when the cover is raised.

Abstract translation: 提供辅助装置以操纵涡轮喷气发动机的机舱的盖。 辅助装置包括与现有的用于接合盖的接头或铰链共同的接头，并且该装置的接头刚性地固定到其一端承载在盖的配件上的成角度的部分，并且其中一点是 铰链到压缩弹簧，以便当盖被升起时将辅助动量施加到盖的装配。

公开(公告)号：US20150367946A1

公开(公告)日：2015-12-24

申请号：US14716969

申请日：2015-05-20

Applicant: AIRCELLE ,  SNECMA

Inventor： Patrick BOILEAU ,  Pierre Caruel ,  Carmen Ancuta ,  Bruno Beutin

IPC: B64D27/16 ,  B64D29/00

CPC classification number: B64D27/16 ,  B64D29/00 ,  B64D29/08 ,  F02K1/78 ,  F02K3/06 ,  F05D2230/72

Abstract: The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.

Abstract translation: 本公开涉及一种用于飞行器的推进单元，其包括围绕涡轮喷气发动机的机舱。 机舱具有围绕涡轮喷气发动机的下游隔室的内部结构，并且内部结构包括两个环形半部分。 推进单元还包括轨道/引导单元并且使工作位置和维护位置之间的环形半部分移动。 特别地，轨道/引导单元在环形半部分的平移运动期间相对于机舱的纵向轴线径向地移动环形半部分。 机舱设置有连接到环形半部分和涡轮喷气发动机的连杆，使得连杆有助于围绕轨道旋转环形半部。

公开(公告)号：US20170016412A1

公开(公告)日：2017-01-19

申请号：US15281569

申请日：2016-09-30

Applicant: AIRCELLE

Inventor： Patrick BOILEAU ,  Olivier KERBLER

IPC: F02K1/62 ,  F01D25/24 ,  F02K1/76

CPC classification number: F02K1/625 ,  F01D25/24 ,  F02K1/72 ,  F02K1/763 ,  F05D2220/32 ,  F05D2250/34 ,  F05D2250/90

Abstract: A thrust reverser of a bypass turbojet engine nacelle is disclosed, which includes movable cowls that move backwards with respect to a fixed front structure to uncover thrust reverser cascades and a variable secondary nozzle connected to the movable cowls by guide means allowing an axial sliding of the system which controls the movement of this variable secondary nozzle, wherein it includes cylinders bearing on the front structure for controlling reversal means of the displacement direction connected to the movable cowls, which move the variable secondary nozzle backwards when these cylinders output a forward stroke, as well as blocking devices which connect the secondary nozzle to the movable cowls when this nozzle is deployed.

Abstract translation: 公开了旁路涡轮喷气发动机机舱的推力反向器，其包括相对于固定前部结构向后移动的可动罩，以揭开推力反向器级联，以及通过引导装置连接到可动罩的可变次级喷嘴，允许轴向滑动 系统，其控制该可变二次喷嘴的运动，其中它包括在前结构上支撑的气缸，用于控制连接到可动罩的位移方向的反转装置，当这些气缸输出向前冲程时向后移动可变二次喷嘴，如 以及当该喷嘴被部署时将二次喷嘴连接到可动罩的阻挡装置。

公开(公告)号：US20160025039A1

公开(公告)日：2016-01-28

申请号：US14841407

申请日：2015-08-31

Applicant: AIRCELLE

Inventor： Patrick BOILEAU ,  Peter SEGAT ,  Pierre CARUEL ,  Sarah TISSOT

IPC: F02K1/72 ,  F02K1/82

CPC classification number: F02K1/72 ,  F02K1/09 ,  F02K1/827 ,  F05D2240/129 ,  F05D2240/90 ,  F05D2250/34

Abstract: A thrust reverser device for an aircraft turbojet engine includes: a movable cowl, translating cascades connected to the movable cowl, a mast; and a front suspension to suspend the turbojet engine. The cascades translates between a direct jet position where the cascades are retracted in a fan casing, and an indirect jet position where the cascades are brought out of the fan casing. In particular, the cascades have a sliding connection with the mast by means of at least one spacer connected to the mast downstream of the front suspension.

Abstract translation: 一种用于飞机涡轮喷气发动机的推力反向装置，包括：可移动整流罩，平移与可移动整流罩连接的级联，桅杆; 以及悬挂涡轮喷气发动机的前悬架。 级联在级联收缩在风扇壳体中的直接喷射位置和级联从风扇壳体离开的间接射流位置之间转换。 特别地，级联通过至少一个连接到前悬架下游的桅杆的间隔件与桅杆滑动连接。

公开(公告)号：US20150354499A1

公开(公告)日：2015-12-10

申请号：US14173484

申请日：2014-02-05

Applicant: AIRCELLE

Inventor： Pierre CARUEL ,  Patrick GONIDEC ,  Patrick BOILEAU

IPC: F02K1/76 ,  F02K1/62

CPC classification number: F02K1/763 ,  F02K1/06 ,  F02K1/12 ,  F02K1/30 ,  F02K1/625 ,  F02K1/72 ,  F02K1/766 ,  Y02T50/671

Abstract: A turbojet engine nacelle has a thrust reverser device and an actuating system for said thrust reverser device, and the thrust reverser device includes a moving cowl mounted translatably alternating between a closed position and an open position, and a jet nozzle section for gases that extends the moving cowl. In particular, the jet nozzle section includes a nozzle flap mounted movable between a closed position and an open position in which the nozzle flap opens a leakage passage toward the outside of the nozzle section. The actuating system has an actuator shared with the moving cowl and the nozzle flap to activate the translational movement of the moving cowl and to pivot the nozzle flap between three following positions: an idle position, an open position of the nozzle flap and an open position of the moving cowl.

Abstract translation: 涡轮喷气发动机发动机舱具有推力反向装置和用于所述推力反向装置的致动系统，并且推力反向装置包括可在可关闭位置和打开位置之间平移地交替安装的移动整流罩，以及用于气体的喷嘴部分， 移动整流罩 特别地，喷嘴部分包括安装在关闭位置和打开位置之间的喷嘴盖，喷嘴盖打开朝向喷嘴部分外部的泄漏通道。 致动系统具有与移动整流罩和喷嘴挡板共享的致动器，以启动移动整流罩的平移运动并使喷嘴阀瓣在三个以下位置之间枢转：空转位置，喷嘴挡板的打开位置和打开位置 的移动整流罩。

公开(公告)号：US20140154064A1

公开(公告)日：2014-06-05

申请号：US14176236

申请日：2014-02-10

Applicant: AIRCELLE

Inventor： Xavier BOUTEILLER ,  Patrick BOILEAU ,  Peter SEGAT

IPC: F02K1/56

CPC classification number: F02K1/566 ,  F02K1/72 ,  Y02T50/672

Abstract: A thrust reverser device of a nacelle includes a thrust reversal cowl which moves alternately from a closed position to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers a flow deflector, and a rear frame supporting deflecting cascades. The flow deflector includes first deflecting cascades distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through the first deflecting cascades, when the thrust reverser device is in reverse jet. In particular, the rear frame has an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet.

Abstract translation: 机舱的推力反向装置包括推力反转罩，其从关闭位置交替地移动到打开位置，在该位置推力反转罩在机舱内打开路径并且露出导流板，以及支撑偏转级联的后框架。 导流器包括分布在推力反向罩的圆周上的第一偏转级联，并且布置成使得当推力反向装置处于反向喷射时，转向流至少部分地穿过第一偏转级联。 特别地，后框架具有延伸结构，该延伸结构设置有第二偏转级联，当推力反向装置处于反向喷射状态时，该第二偏转级联重新定向一部分转向流。