公开(公告)号：US20150160100A1

公开(公告)日：2015-06-11

申请号：US14611646

申请日：2015-02-02

Applicant: AIRCELLE

Inventor： Hakim MAALIOUNE ,  Rodolphe DENIS ,  Achour DEBIANE

IPC: G01M99/00 ,  G01L5/22

CPC classification number: G01M99/007 ,  G01L5/22 ,  G01M5/0075 ,  G01M13/00

Abstract: A test device for testing an actuating system for a thrust reverser includes a test bench, an input device, controllers and several determination components. The thrust reverser includes actuating cylinders, and the test bench includes a test structure which has counter-thrust cylinders connected to the actuating cylinders to be tested. Input parameters corresponding to external forces could be entered by the input device, and a first determination component determines a digital model of a movable structure of the thrust reverser. In addition, a second determination component determines force to be exerted by the counter-thrust cylinders by using the digital model and the input parameters. A third determination component determines a control set-point applied to the counter-thrust cylinders, and first and second controllers apply control set-points to counter-thrust and actuating cylinders, respectively. A fourth determination component determines at least one dynamic characteristic of each actuating cylinder.

Abstract translation: 用于测试推力反向器的致动系统的测试装置包括测试台，输入装置，控制器和多个确定部件。 推力反向器包括致动气缸，并且测试台包括测试结构，其具有连接到要测试的致动气缸的反推力气缸。 可以由输入装置输入与外力对应的输入参数，第一确定部件确定推力反向器的可移动结构的数字模型。 此外，第二确定部件通过使用数字模型和输入参数来确定由反推力气缸施加的力。 第三确定部件确定施加到反推力缸的控制设定点，并且第一和第二控制器分别将控制设定点施加到反推力和致动缸。 第四确定部件确定每个致动缸的至少一个动态特性。

公开(公告)号：US20140319243A1

公开(公告)日：2014-10-30

申请号：US14173464

申请日：2014-02-05

Applicant: AIRCELLE

Inventor： Pierre CARUEL ,  Peter Segat

IPC: F02K1/56

CPC classification number: F02K1/566 ,  F02K1/09 ,  F02K1/32 ,  F02K1/72 ,  Y02T50/671

Abstract: The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value.

Abstract translation: 推力反向器包括反向罩罩，反向罩罩的下游部分形成喷射喷嘴，从反向罩罩上游固定的梯级叶片，推力反向器挡板和致动器。 推力反向器可以在致动器的作用下在用于以直接喷射模式操作机舱的推力反向器挡板的折叠位置和用于以反向喷射模式操作机舱的展开位置之间平移 。 特别地，致动器的拉伸导致喷嘴的喷嘴部分的变化，只要拉伸低于预定值，并且暴露级联叶片并展开推力反向翼片以便执行反向喷射 模式超出预定值。

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：US20140255178A1

公开(公告)日：2014-09-11

申请号：US14286666

申请日：2014-05-23

Applicant: AIRCELLE

Inventor： Arnaud OUDIN ,  Bertrand Desjoyeaux ,  Nicolas Dezeustre ,  Olivier Kerbler

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D25/28 ,  F04D29/023 ,  F04D29/542 ,  F05C2225/08 ,  F05D2240/12 ,  F05D2300/43 ,  F05D2300/436 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/6034 ,  Y02T50/672

Abstract: A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

Abstract translation: 由复合材料制成的流动矫直叶片包括由三维编织织物棒构成的芯，该芯由纤维覆盖层包围，该芯并且该覆盖物使用热固性树脂固结。

公开(公告)号：US20140234090A1

公开(公告)日：2014-08-21

申请号：US14200365

申请日：2014-03-07

Applicant: AIRCELLE

Inventor： Herve HURLIN ,  Nicolas DEZEUSTRE ,  Olivier KERBLER

IPC: F02C7/20

CPC classification number: F02C7/20 ,  B64D29/06 ,  B64D29/08 ,  F02K1/72

Abstract: A rear nacelle assembly for turbojet engine includes an inner structure surrounding a downstream portion of the turbojet engine. In particular, the inner structure is movable in rotation between an operating position in which it forms a downstream fairing and defines an annular stream of cold air with a thrust reverser cowl, and a maintenance position in which the inner structure moves away from the downstream portion. A suspension pylon is further provided to mount the thrust reverser cowl and the inner structure. The thrust reverser cowl slides between an opening position clearing air flow deviation grids and a closing position recovering the air flow deviation grids. Moreover, the thrust reverser cowl is mounted on the suspension pylon by a pivot connection sliding around a main axis, and the inner structure is mounted on the suspension pylon by a pivot connection around the main axis.

Abstract translation: 用于涡轮喷气发动机的后机舱组件包括围绕涡轮喷气发动机的下游部分的内部结构。 特别地，内部结构可以在其形成下游整流装置的操作位置之间旋转移动并且限定出具有推力反向器整流罩的环形冷空气流，以及内部结构从其下游部分移开的维护位置 。 进一步提供悬挂塔以安装推力反向器罩和内部结构。 推力反向器整流罩在打开位置之间滑动，清除空气流量偏差网格和恢复气流偏差格栅的关闭位置。 此外，推力反向器整流罩通过绕主轴线滑动的枢转连接件安装在悬挂塔上，并且内部结构通过围绕主轴线的枢转连接安装在悬挂塔上。

公开(公告)号：US20140234089A1

公开(公告)日：2014-08-21

申请号：US14133327

申请日：2013-12-18

Applicant: SAGEM DEFENSE SECURITE ,  AIRCELLE

Inventor： Pierre MORADELL-CASELLAS ,  Franck Delnaud

IPC: F16H25/22 ,  F02K1/56

CPC classification number: F16H25/2204 ,  F02K1/56 ,  F02K1/76 ,  F02K1/763 ,  F02K1/766 ,  F16H25/2454 ,  F16H2025/2084 ,  Y02T50/671 ,  Y10T74/18704

Abstract: An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even.

Abstract translation: 用于飞行器发动机推力反向器的致动组件包括：承载主齿轮的驱动轴; 一个滚珠丝杠，其承载与主齿轮啮合的从动齿轮; 螺母，其能够由于滚珠丝杠的旋转而在滚珠丝杠上方平移; 刚性地固定到螺母的延伸管和锁定组件，以在所述反向器的所谓的直接喷射位置阻挡所述驱动轴的旋转。 延伸管在其自由端处包括用于在被致动之前连接到反向器的一部分的构件。 特别地，锁定组件包括固定到驱动轴的支座和可在锁定位置和解锁位置之间移动的开口。 从动和小齿轮之间的减速比（R）是均匀的。

公开(公告)号：US08769926B2

公开(公告)日：2014-07-08

申请号：US13735096

申请日：2013-01-07

Applicant: Aircelle

Inventor： Guy Bernard Vauchel ,  Jean-Philippe Joret

IPC: F02K1/72

CPC classification number: F02K1/62 ,  F02K1/72 ,  F02K1/805

Abstract: A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.

Abstract translation: 提供了一种用于涡轮喷气发动机机舱的推力反向装置，其包括偏转装置和相对于至少一个固定结构可移动的至少一个整流罩，该至少一个整流罩包括至少一个至少部分外围的前框架，并且装备有用于连接到相应的上游部分 。 前框架具有偏转边缘，该偏转边缘具有形成可变形翼片的上游延伸部分，该可变形翼片旨在成为与附接到前框架的对应的上游部分成为空气动力学界面，并且可移动整流罩的一部分被配合成 关闭位置，通过强制撤出可变形翼片与所述上游连接部分相接合。

公开(公告)号：US20140133977A1

公开(公告)日：2014-05-15

申请号：US14161595

申请日：2014-01-22

Applicant: AIRCELLE

Inventor： Romain BILLAULT

IPC: F04D29/40

CPC classification number: F04D29/403 ,  F01D25/243 ,  F02K1/80

Abstract: A device for connecting a front frame of a turbojet engine nacelle to a fan casing includes a locking pin connected to a first assembly flange and a retaining flange that is movably mounted and has at least one opening. In particular, the locking pin has a shank passing through an orifice of a second assembly flange secured to the fan casing. The opening is crossed through by the shank of the locking pin and interacts with an end groove of said locking pin. When the retaining flange is in the unlocking position, the opening has dimensions larger than those of the shank of the locking pin, and when the retaining flange is in the locking position, the opening has dimensions larger than a thickness of the locking pin at its groove but smaller than an overall thickness of the shank of the orifice of the second flange.

Abstract translation: 用于将涡轮喷气发动机机舱的前框架连接到风扇壳体的装置包括连接到第一组装凸缘的锁定销和可移动地安装并具有至少一个开口的保持凸缘。 特别地，锁定销具有穿过固定到风扇壳体的第二组件凸缘的孔的柄。 开口穿过锁定销的柄部并与所述锁定销的端部槽相互作用。 当保持凸缘处于解锁位置时，开口的尺寸大于锁定销的柄的尺寸，并且当保持凸缘处于锁定位置时，开口的尺寸大于其锁定销的厚度 但是小于第二凸缘的孔的柄的整体厚度。

公开(公告)号：US20140131515A1

公开(公告)日：2014-05-15

申请号：US13944187

申请日：2013-07-17

Applicant: AIRCELLE

Inventor： Pierre Caruel

IPC: F02K1/54 ,  B64D33/04

CPC classification number: F02K1/54 ,  B64D33/04 ,  F02K1/72 ,  F02K1/766 ,  Y02T50/671

Abstract: A thrust reverser with grids includes a jet engine pylon, a one piece cowl either directly or indirectly slidably mounted on the jet engine pylon between a direct jet position and a reverse jet position, and a system for locking this cowl on a beam. The system has a single tertiary lock, which is positioned on one side of the jet engine pylon being capable of locking a corresponding upper edge of the cowl. In addition, the tertiary lock includes a locker to lock the cowl, a blocker for blocking the locker, and a position detector in order to detect the position of the locker. The system further includes another detector to detect proper closing of the other upper edge of the cowl.

Abstract translation: 具有网格的推力反向器包括喷气式发动机塔架，直接或间接可滑动地安装在喷气发动机塔架上的直接喷射位置和反向喷射位置之间的一个整流罩，以及用于将该罩盖锁定在梁上的系统。 该系统具有单个三级锁，其位于喷气发动机塔的一侧，能够锁定整流罩的相应上边缘。 此外，三级锁包括用于锁定整流罩的储物柜，用于阻挡储物柜的阻塞器和用于检测储物柜位置的位置检测器。 该系统还包括用于检测整流罩的另一个上边缘的适当关闭的另一检测器。

公开(公告)号：US20140026974A1

公开(公告)日：2014-01-30

申请号：US13953368

申请日：2013-07-29

Applicant: AIRCELLE

Inventor： Bertrand DESJOYEAUX ,  Olivier Hubier

IPC: B29D99/00 ,  F02C7/04

CPC classification number: B29D99/001 ,  B29C70/48 ,  B29C70/84 ,  B29L2031/087 ,  B29L2031/7504 ,  B64D29/00 ,  B64D33/02 ,  F02C7/04 ,  Y10T137/0536

Abstract: A method for manufacturing a nacelle air intake lip including a plurality of components includes the following steps. The first step is positioning, inside a mold, two components within a set of fibrous layers encompassing all or part of the components so that a preform is formed. Next step is performing impregnation of the obtained preform to obtain molding of the nacelle air intake lip.

Abstract translation: 包括多个部件的制造机舱进气口的方法包括以下步骤。 第一步是在模具内部定位一组包含全部或部分组件的纤维层中的两个部件，从而形成预制件。 下一步是对获得的预制件进行浸渍以获得机舱进气口的模制。