公开(公告)号：US20140245716A1

公开(公告)日：2014-09-04

申请号：US14273778

申请日：2014-05-09

Applicant: AIRCELLE

Inventor： Patrick GONIDEC

IPC: F02K1/76

CPC classification number: F02K1/763 ,  F02K1/70 ,  F02K1/766 ,  F05D2260/30 ,  Y02T50/672

Abstract: A thrust reverser for a turbojet aircraft engine nacelle includes a pair of twin doors including an upstream door and a downstream door which is connected to the upstream door by a connecting rod. The thrust reverse also includes an actuating cylinder for operating the upstream door between a direct jet position in which the two doors are closed and a reversed jet position in which the two doors are open and deflects a portion of a cold air stream flowing inside the nacelle. A locking system of the thrust reverser locks the upstream and downstream doors relative to one another by the operation of the actuating cylinder alone.

Abstract translation: 用于涡轮喷气飞机发动机机舱的推力反向器包括一对双门，包括上游门和下游门，其通过连接杆连接到上游门。 推力反向还包括用于在两个门关闭的直接喷射位置和两个门打开的反向喷射位置之间操作上游门的致动缸，并且偏转在机舱内流动的冷气流的一部分 。 推力反向器的锁定系统通过单独的致动缸的操作将上游门和下游门相对于彼此锁定。

公开(公告)号：US20160115902A1

公开(公告)日：2016-04-28

申请号：US14987302

申请日：2016-01-04

Applicant: AIRCELLE

Inventor： Olivier KERBLER ,  Olivier GILO ,  Patrick GONIDEC

IPC: F02K1/12

CPC classification number: F02K1/1261 ,  B64C15/02 ,  B64D29/06 ,  B64D33/04 ,  F02K1/12 ,  F02K1/1207 ,  F02K1/1253 ,  F02K1/763

Abstract: The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

Abstract translation: 本公开提供了一种涡轮喷气发动机机舱，其具有包括整流罩的下游部分，该整流罩以构成喷嘴的铰接折片结束。 特别地，铰链翼片铰接并可平移地铰接到整流罩。

公开(公告)号：US20150030445A1

公开(公告)日：2015-01-29

申请号：US13945023

申请日：2013-07-18

Applicant: Aircelle

Inventor： Patrick GONIDEC ,  Laurent Albert Blin

IPC: B64D29/06 ,  B64D33/02

CPC classification number: B64D29/06 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0266 ,  B64D2033/0273 ,  B64D2033/0286 ,  F02C7/042 ,  F02C7/047 ,  F02K1/30 ,  Y02T50/671 ,  Y10T137/0536

Abstract: A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls. In particular, the internal return area allows the circulation of part of the injected auxiliary flow and the drawn-in auxiliary flow

Abstract translation: 用于涡轮喷气发动机的机舱具有纵向轴线和后部分，其包括由固定内部结构的壁和外部结构的壁形成的环形静脉。 机舱包括用于调制由环形静脉形成的空间的横截面的装置。 该装置包括喷射器以喷射气体的辅助流，以改变辅助流的取向或速度，用于抽吸部分注入的辅助流的吸入孔以及一个或多个内部辅助流回流区域 墙壁 特别地，内部返回区域允许部分注入的辅助流和引入的辅助流的循环

公开(公告)号：US20140369812A1

公开(公告)日：2014-12-18

申请号：US14471323

申请日：2014-08-28

Applicant: AIRCELLE

Inventor： Pierre CARUEL ,  Franck ZAGANELLI ,  Patrick GONIDEC ,  Olivier KERBLER

IPC: F01D25/24

CPC classification number: F01D25/24 ,  B64D15/04 ,  B64D33/02 ,  B64D33/10 ,  B64D2033/0233 ,  F02C7/047 ,  F02C7/12 ,  F02K3/06 ,  F05D2240/14 ,  F05D2260/213 ,  Y02T50/676

Abstract: A nacelle of a turbine engine includes an external cowling, an internal cowling, and a heat exchanger associated with at least one circulation duct for a fluid. In particular, the circulation duct forms a recirculation loop through the heat exchanger, and the recirculation loop includes at least one circulation area extending at least partially along the external cowling in contact with a wall of the external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

Abstract translation: 涡轮发动机的机舱包括外部整流罩，内部整流罩和与用于流体的至少一个循环管道相关联的热交换器。 特别地，循环管道形成通过热交换器的再循环回路，并且再循环回路包括至少部分沿着外部整流罩延伸的至少一个循环区域，该外部整流罩与外部整流罩的壁接触，以便允许通过 与机舱外的空气导通。

公开(公告)号：US20150267643A1

公开(公告)日：2015-09-24

申请号：US14464649

申请日：2014-08-20

Applicant: AIRCELLE

Inventor： Patrick GONIDEC ,  Laurent Albert Blin ,  Olivier Kerbler

IPC: F02K1/72

CPC classification number: F02K1/72 ,  Y02T50/671

Abstract: A cascade-type thrust reverser for an aircraft turbojet engine includes a front frame, a sliding cowl between a direct jet position and a reverse jet position, a plurality of actuating cylinders interposed between this front frame and this sliding cowl, and a plurality of cascades pivotally mounted on the front frame between the direct and reverse jet positions. In the direct jet position, the cascades are substantially parallel to the axis (A) of the thrust reverser, and in the reverse jet position, the cascades are inclined relative to the axis (A) of the thrust reverser. In particular, the cascade-type thrust reverser includes a single radial layer of cascades.

Abstract translation: 用于飞行器涡轮喷气发动机的级联型推力反向器包括前框架，在直接喷射位置和反向喷射位置之间的滑动罩，插入在该前框架和该滑动罩之间的多个致动缸以及多个级联 在直接和反向喷射位置之间枢转地安装在前框架上。 在直接喷射位置，级联基本上平行于推力反向器的轴线（A），并且在反向喷射位置中，级联相对于推力反向器的轴线（A）倾斜。 特别地，级联型推力反向器包括单个径向的级联层。

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：US20140225380A1

公开(公告)日：2014-08-14

申请号：US14187770

申请日：2014-02-24

Applicant: AIRCELLE

Inventor： Patrick GONIDEC

IPC: E05C19/12

CPC classification number: E05C19/12 ,  B64D29/06 ,  E05B41/00 ,  E05C1/006 ,  Y10T292/0936

Abstract: A locking device includes a locking pair having a bolt to engage with a retainer and a detection linkage. The bolt is movably mounted against a spring which tends to return the bolt to a position spaced apart from the retainer. The detection linkage is also movably mounted between an unlocked position where the detection linkage allows unlocking of the bolt and the retainer. In particular, a portion of the bolt then engages with the detection linkage by means of a detecting part of the detection linkage to block a possible return of the detection linkage towards a locked position where the detection linkage engages with the portion of the bolt so as to oppose to unlocking of the bolt. The detecting part irreversibly drives the detection linkage to its unlocked position even when one locking pair is unlocked.

Abstract translation: 锁定装置包括具有螺栓以与保持器和检测连杆相接合的锁定对。 螺栓可移动地抵靠弹簧安装，该弹簧倾向于将螺栓返回到与保持器间隔开的位置。 检测联动装置还可移动地安装在解锁位置之间，其中检测联动装置允许释放螺栓和保持器。 特别地，螺栓的一部分然后借助于检测联动装置的检测部分与检测联动装置接合，以阻止检测联动装置朝向锁定位置的可能返回，其中检测联动装置与螺栓的该部分接合，以便 反对解锁螺栓。 即使当一个锁定对被解锁时，检测部件也不可逆地将检测连杆驱动到其解锁位置。

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。