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：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：US20140217234A1

公开(公告)日：2014-08-07

申请号：US14245843

申请日：2014-04-04

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE

IPC: B64D27/10

CPC classification number: B64D27/10 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268

Abstract: An aircraft propulsion assembly includes a turbojet engine, a support providing a transfer of force torque to an aircraft from a suspension assembly, and the suspension assembly interposed between the support and the turbojet engine. The suspension assembly includes a device for absorbing thrust forces, an upstream suspension fasteners mounted on a fan housing and an intermediate housing of the turbojet engine. In particular, the suspension assemble further includes a main upstream suspension fastener to absorb a moment (Mx) along an axis (X) of the turbojet engine and forces (Fy and Fz) in a plane perpendicular to the axis (X), and a pair of additional upstream suspension fasteners separate from the main upstream suspension fastener to absorb a moment (Mz) along an axis (Z) and a moment (My) along an axis (Y) and forces (Fx) along the axis (X).

Abstract translation: 飞行器推进组件包括涡轮喷气发动机，提供从悬架组件向飞行器传递力矩的支架以及插入支撑件和涡轮喷气发动机之间的悬架组件。 悬架组件包括用于吸收推力的装置，安装在风扇壳体上的上游悬挂紧固件和涡轮喷气发动机的中间壳体。 特别地，悬架组装还包括主上游悬挂紧固件，以沿着涡轮喷气发动机的轴线（X）吸收力矩（Mx），并且在垂直于轴线（X）的平面中的力（Fy和Fz），以及 一对附加的上游悬挂紧固件与主上游悬挂紧固件分离，以沿着轴线（Z）和沿着轴线（Y）的力矩（I）和沿轴线（X）的力（Fx）吸收力矩（Mz）。

公开(公告)号：US20140217233A1

公开(公告)日：2014-08-07

申请号：US14245798

申请日：2014-04-04

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE

IPC: B64D27/10

CPC classification number: B64D27/10 ,  B64D27/26 ,  B64D2027/266 ,  B64D2027/268

Abstract: An aircraft propulsion assembly includes a support providing a transfer of a force torque to an aircraft from a suspension assembly which is interposed between the support and a turbojet engine. The suspension assembly is mounted on an intermediate housing, a main housing or a fan housing, and on the support. In particular, the suspension assembly includes following suspension fasteners: —a first suspension fastener having a device for absorbing thrust forces and forces “Fz” along an axis “Z”, —a second suspension fastener to absorb, with the first suspension fastener, a moment “Mx” around an axis “X” and forces “Fy” along an axis “Y”, —a third suspension fastener to absorb, with the first suspension fastener, a moment “My” along the axis “Y” and forces “Fx” along an axis “X”. A moment “Mz” along the axis “Z” is absorbed by one of the suspension fasteners.

Abstract translation: 一种飞行器推进组件包括支撑件，其提供从设置在支撑件和涡轮喷气发动机之间的悬架组件向飞行器传递力矩。 悬挂组件安装在中间壳体，主壳体或风扇壳体上以及支撑件上。 特别地，悬架组件包括以下悬挂紧固件： - 第一悬挂紧固件，其具有用于吸收推力并沿轴线“Z”施加“Fz”的装置， - 第二悬挂紧固件，用于吸收第一悬挂紧固件 力矩“Mx”，并沿“Y”轴强制“Fy”，第三悬挂紧固件用第一悬挂紧固件吸收沿“Y”轴的力矩“My”并强制“ Fx“。 沿着轴线“Z”的“Mz”被其中一个悬挂紧固件吸收。

公开(公告)号：US20140130889A1

公开(公告)日：2014-05-15

申请号：US14093903

申请日：2013-12-02

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE

IPC: F02C7/04

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0286 ,  Y10T137/0536

Abstract: The present disclosure relates to an air inlet structure for a turbojet engine nacelle. The air inlet structure has a stationary internal wall to be attached to one element of a mid-section of the nacelle, and a longitudinal external wall extended by an air inlet lip connected to the stationary internal wall. In particular, one portion forming the air inlet lip is provided with depressurizing openings for a part of the air inlet lip.

Abstract translation: 本发明涉及涡轮喷气发动机机舱的进气结构。 空气入口结构具有固定的内壁，其被附接到机舱的中间部分的一个元件，以及由连接到固定内壁的进气口延伸的纵向外壁。 特别地，形成空气入口唇缘的一个部分设置有用于空气入口唇缘的一部分的减压开口。

公开(公告)号：US20140061332A1

公开(公告)日：2014-03-06

申请号：US14048206

申请日：2013-10-08

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE ,  Olivier Kerbler ,  Herve Hurlin ,  Pierre Moradell-Casellas

IPC: F02K1/76

CPC classification number: F02K1/763 ,  F02K1/625 ,  F02K1/64 ,  F02K1/72 ,  F05D2250/34 ,  Y02T50/672

Abstract: An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway.

Abstract translation: 一种组件包括悬挂塔和推力反向器，其具有用于偏转流动的叶片和能够通过致动器在打开位置和关闭位置之间移动的整流罩。 推力反向器还包括能够在滑道中滑动的轨道。 特别地，致动器与相应的导轨成一直线设置。 致动器可以是致动器，其具有连接到环形螺钉或适于拉动对应的轨道或相应的滑道上的致动器的旋转螺母。

公开(公告)号：US20130121814A1

公开(公告)日：2013-05-16

申请号：US13731150

申请日：2012-12-31

Applicant: Aircelle ,  Snecma

Inventor： Hervé HURLIN ,  Nicolas DEZEUSTRE ,  Olivier KERBLER ,  François GALLET ,  Bertrand DESJOYEAUX

IPC: F01D25/24

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D29/08

Abstract: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Abstract translation: 提供了一种用于涡轮喷气发动机的机舱，其包括涡轮喷气发动机上游的进气口，旨在围绕涡轮喷气发动机及其壳体的风扇的中间部分和下游部分。 中间部分由能够确保机舱的外部空气动力学连续性的至少一个航空结构制成，并且航空结构刚性地结合，以便能够被分离到至少一个周围的固定结构。

公开(公告)号：US20140301837A1

公开(公告)日：2014-10-09

申请号：US14310184

申请日：2014-06-20

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE ,  Xavier HERT ,  Luc QUERNET

IPC: F02K1/56

CPC classification number: F02K1/566 ,  F02K1/60 ,  F02K1/605 ,  F02K1/62 ,  F02K1/70 ,  F02K1/763 ,  F05D2260/50 ,  F05D2260/52 ,  Y02T50/671

Abstract: A door for a door-type thrust reverser is pivotally mounted on a stationary structure of a thrust reverser. The door includes an inner surface integrated to a flow path of an air flow generated by a turbojet engine, an outer surface providing an outer aerodynamic continuity of a nacelle equipped with the thrust reverser, a spoiler to deflect the air flow disposed at an upstream end of the door, and an actuator actuating the spoiler. The spoiler is movably mounted, in rotation around a rotation axis substantially perpendicular to a front frame of the door, between a retracted and a deployed position. In particular, the actuator includes a first rod connected to the spoiler, a second rod connected to the first rod and the front frame, and a third rod connected to the first and second rods as well as to the spoiler.

Abstract translation: 门式推力反向器的门枢转地安装在推力反向器的固定结构上。 门包括与涡轮喷气发动机产生的空气流的流动路径相整合的内表面，提供装备有推力反向器的机舱的外部空气动力学连续性的外表面，用于使设置在上游端的气流偏转的扰流板 的门，以及致动扰流板的致动器。 扰流器围绕基本上垂直于门的前框架的旋转轴线在缩回和展开位置之间可旋转地安装。 特别地，致动器包括连接到扰流板的第一杆，连接到第一杆和前框架的第二杆以及连接到第一杆和第二杆以及扰流器的第三杆。

公开(公告)号：US20140174251A1

公开(公告)日：2014-06-26

申请号：US14171024

申请日：2014-02-03

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE

IPC: F16C7/02

CPC classification number: F16C7/02 ,  F16B7/182 ,  Y10T74/2142

Abstract: A tubular connecting rod includes a hollow body including at least one end provided with an opening and a connecting rod head arranged to be fitted through the opening. The connecting rod head includes at least one shoulder arranged to position the connecting rod head relative to the opening of the hollow body in a predetermined locked position. In particular, the end of the hollow body is provided with at least one slot.

Abstract translation: 管状连杆包括中空体，该中空体包括设置有开口的至少一端和设置成穿过该开口的连杆头。 连杆头包括至少一个肩部，其布置成将连杆头相对于中空体的开口定位在预定的锁定位置。 特别地，中空体的端部设置有至少一个狭槽。

公开(公告)号：US20140086738A1

公开(公告)日：2014-03-27

申请号：US14093928

申请日：2013-12-02

Applicant: AIRCELLE

Inventor： Nicolas DEZEUSTRE ,  Patrick STELLA

IPC: F02K1/12

CPC classification number: F02K1/12 ,  F02K1/1207 ,  F02K1/1223 ,  F05D2260/52 ,  F05D2300/501 ,  Y02T50/671

Abstract: A nacelle for an aircraft bypass turbojet engine includes downstream, an internal stationary structure surrounding part of the bypass turbojet engine, and an external structure surrounding the internal stationary structure, defining an annular flow path along which an air flow circulates. The external structure includes a mobile flap disposed at the downstream end of the external structure and positioned facing the annular flow path. Each mobile flap can rotate such as to move into a position that increases or reduces the height of the cross-section of the annular flow path in relation to an idle position, in response to the pressure exerted on the mobile flap by the air flow circulating through the facing annular flow path. The mobile flap can return from the cross-section-increasing or -reducing position to another position under the effect of an elastic return means.

Abstract translation: 用于飞机旁路涡轮喷气发动机的机舱包括下游，围绕旁路涡轮喷气发动机的一部分的内部静止结构以及围绕内部静止结构的外部结构，其限定了气流循环的环形流动路径。 外部结构包括设置在外部结构的下游端并面向环形流动路径定位的移动翼片。 每个移动挡板可以旋转，以响应于通过气流循环施加在移动挡板上的压力而移动到相对于空转位置增加或减小环形流路横截面高度的位置 通过面对的环形流动路径。 在弹性返回装置的作用下，移动挡板可以从横截面增加或还原位置返回到另一位置。