公开(公告)号：US10605196B2

公开(公告)日：2020-03-31

申请号：US15286955

申请日：2016-10-06

Applicant: AIRCELLE

Inventor： Pierre Caruel ,  Thiery Le Docte

IPC: F02K1/60 ,  F02K1/82 ,  F02K1/70 ,  F02K1/76

Abstract: A door-type thrust reverser device for a turbojet engine nacelle is provided that includes a fixed structure, a mobile structure mobile with respect to said fixed structure, and at least one door mounted with the ability to pivot via pivots between a retracted position corresponding to the nacelle operating in direct-jet mode, and a deployed position corresponding to the nacelle operating in reverser-jet mode. The thrust reverser device includes a device for bleeding off some of a secondary or bypass airflow, which device is able to bleed off part of the secondary airflow from a duct through which the secondary airflow circulates and for conveying said bled-off airflow toward at least one pivot of the door, so as to cool areas on and/or around the door pivots.

公开(公告)号：US10087842B2

公开(公告)日：2018-10-02

申请号：US13894647

申请日：2013-05-15

Applicant: AIRCELLE

Inventor： Pierre Caruel

IPC: F02C7/20 ,  B64D29/06 ,  B64D33/04 ,  F01D21/04 ,  F02K1/76

Abstract: A turbojet engine nacelle includes a fixed structure, which has a fan casing of the turbojet engine and a front frame mounted downstream of the fan casing and directly or indirectly supporting cascade vanes. The front frame is able to collaborate with a thrust reverser cowling sliding between a closed position covering the flow-diverting means and an open position exposing this flow-diverting means. At least one reinforcing structure of the engine nacelle transmits load between the fan casing and the front frame. The reinforcing structure extends along the longitudinal axis of the nacelle and supports a third line of defense and/or an inhibiting device between the front frame and the thrust reverser cowling.

公开(公告)号：US09562595B2

公开(公告)日：2017-02-07

申请号：US14166524

申请日：2014-01-28

Applicant: AIRCELLE

Inventor： Pierre Caruel ,  Pierre Moradell-Casellas

IPC: F02K1/62 ,  F16H25/12 ,  F02K1/72 ,  F02K1/76 ,  F16H25/20

CPC classification number: F16H25/12 ,  F02K1/625 ,  F02K1/72 ,  F02K1/763 ,  F16H25/20 ,  F16H2025/2059 ,  F16H2025/2075 ,  Y02T50/671 ,  Y10T74/18576

Abstract: The present disclosure relates to a double-acting linear actuator for moving an inner part and an outer part of a cowl relative to a fixed frame. The linear actuator includes a first tubular body housing a first drive shaft and a second tubular body housing a second drive shaft. In particular, the first and second tubular bodies are mounted in series by the second drive shaft which is mounted on the first tubular body. The second drive shaft translates the second tubular body relative to the first tubular body when a lock of the first tubular body is in a locked position, and the first drive shaft translates both the first tubular and second tubular bodies when the lock is in an unlocked position.

Abstract translation: 本发明涉及一种用于使整流罩的内部部分和外部部分相对于固定框架移动的双作用线性致动器。 线性致动器包括容纳第一驱动轴的第一管状体和容纳第二驱动轴的第二管状体。 特别地，第一和第二管状体通过安装在第一管状体上的第二驱动轴串联安装。 当第一管状体的锁定处于锁定位置时，第二驱动轴相对于第一管状体转动第二管状体，并且当锁处于解锁状态时，第一驱动轴平移第一管状体和第二管状体 位置。

公开(公告)号：US20140369829A1

公开(公告)日：2014-12-18

申请号：US14471307

申请日：2014-08-28

Applicant: AIRCELLE

Inventor： Jean-Philippe Joret ,  Xavier Bouteiller ,  Xavier Cazuc ,  Pierre Caruel

IPC: F01D25/24

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2250/14

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

Abstract translation: 机舱包括设置有推力反向器和前框架的外部结构，可移动的整流罩和覆盖涡轮喷气发动机的下游部分的内部结构。 外部结构和内部结构限定了气流的流动。 特别地，安装在可移动整流罩的减小的横截面区域上的推力反向器的前框架和引导级联的连接位于相对于前框架和引导件的连接处的轴线偏移的轴线的中心 安装在可动罩的周边的其余部分上的级联居中。

公开(公告)号：US10087841B2

公开(公告)日：2018-10-02

申请号：US14846129

申请日：2015-09-04

Applicant: AIRCELLE

Inventor： Pierre Caruel

IPC: F02C7/14 ,  F01D25/24 ,  F01D25/12 ,  B64D33/02

Abstract: The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air.

公开(公告)号：US09777598B2

公开(公告)日：2017-10-03

申请号：US14471307

申请日：2014-08-28

Applicant: AIRCELLE

Inventor： Jean-Philippe Joret ,  Xavier Bouteiller ,  Xavier Cazuc ,  Pierre Caruel

IPC: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2250/14

Abstract: A nacelle includes an outer structure provided with a thrust reverser and a front frame, a movable cowl, and an inner structure covering a downstream section of a turbojet engine. The outer structure and the inner structure define a flow stream of an air flow. In particular, the connection of the front frame and diversion cascade of the thrust reverser which is mounted on a reduced transverse section area of the movable cowl is centered on an axis offset relative to an axis on which the connection of the front frame and the diversion cascade mounted on the remainder of the periphery of the movable cowl is centered.

公开(公告)号：US09453478B2

公开(公告)日：2016-09-27

申请号：US14566995

申请日：2014-12-11

Applicant: AIRCELLE

Inventor： Pierre Caruel ,  Peter Segat

IPC: F02K1/72 ,  F02K1/76 ,  F02K1/09 ,  F02K1/64

CPC classification number: F02K1/72 ,  F02K1/09 ,  F02K1/763 ,  F02K1/766 ,  Y02T50/671

Abstract: A thrust reverser for a turbojet engine nacelle includes a movable cowl, cascade vanes and a portion forming a movable variable nozzle. The cowl translates between a closing position and a maintenance position which is located beyond a thrust reversal position. In the maintenance position, the cowl opens a passage within the nacelle and allows access the inside of the nacelle. The variable nozzle is translated by an actuator between reduced ejection section and increased section positions. In particular, the cascade vanes move between retracted and active positions and are housed in an envelope formed by a fan casing and an outer cowl in the retracted position. In the active position, the cascade vanes are displaced downstream by an actuator through a passage open by the movable cowl in the nacelle. The actuator of the cascade vanes is dissociable from the actuator driving the variable nozzle.

Abstract translation: 用于涡轮喷气发动机机舱的推力反向器包括可移动整流罩，级联叶片和形成可移动可变喷嘴的部分。 整流罩在关闭位置和位于推力反转位置之外的维护位置之间平移。 在维护位置，整流罩在机舱内打开通道，并允许进入机舱内部。 可变喷嘴由致动器在减少的喷射部分和增加的部分位置之间平移。 特别地，级联叶片在收缩位置和活动位置之间移动并且被收纳在由风扇壳体和处于缩回位置的外整流罩形成的封套中。 在主动位置，级联叶片由致动器向下游移动，通过机舱中的可移动整流罩打开的通道。 级联叶片的致动器可从驱动可变喷嘴的致动器解离。

公开(公告)号：US09410500B2

公开(公告)日：2016-08-09

申请号：US14173464

申请日：2014-02-05

Applicant: AIRCELLE

Inventor： Pierre Caruel ,  Peter Segat

IPC: F02K1/72 ,  F02K1/56 ,  F02K1/32 ,  F02K1/09

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：US09366201B2

公开(公告)日：2016-06-14

申请号：US14263290

申请日：2014-04-28

Applicant: AIRCELLE

Inventor： Pierre Caruel

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2230/80 ,  Y02T50/671

Abstract: A thrust reverser for a nacelle of a turbojet engine includes deflecting cascades and an external cowl which translates from a closure position to an opening position by a set of control cylinders being attached by their ends to the external cowl. The deflecting cascades are supported by a front frame and a rear frame respectively and are enclosed in an envelope formed by a fan carter and by a fan cowl. The thrust reverser further includes a lock which is able to connect or disconnect the deflecting cascades to the external cowl. When the lock is unlocked, the set of control cylinders translate the external cowl alone in downstream direction while in the lock position, the control cylinders translates the external cowl and the deflecting cascades together in downstream direction.

Abstract translation: 用于涡轮喷气发动机的机舱的推力反向器包括偏转级联和外部整流罩，其通过其端部附接到外部整流罩的一组控制气缸从闭合位置转换到打开位置。 偏转级联由前框架和后框架分别支撑并封闭在由风扇卡盘和风扇罩组成的信封中。 推力反向器还包括能够将偏转级联连接或断开到外部整流罩的锁。 当锁解锁时，一组控制缸在处于锁定位置时在下游方向上单独平移外部整流罩，控制缸在下游方向将外部整流罩和偏转级联平移在一起。

公开(公告)号：US09151225B2

公开(公告)日：2015-10-06

申请号：US14304555

申请日：2014-06-13

Applicant: AIRCELLE

Inventor： Nicolas Dezeustre ,  Pierre Caruel ,  Patrick Gonidec ,  Patrick Boileau

IPC: F02C7/045 ,  B64D33/02

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，两个后皮都是结构的。