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：US20160039528A1

公开(公告)日：2016-02-11

申请号：US14885422

申请日：2015-10-16

Applicant: AIRCELLE

Inventor： Pierre CARUEL

IPC: B64D29/06 ,  F01D25/24 ,  B64D33/02

CPC classification number: B64D29/06 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0273 ,  F01D25/24 ,  F02C3/04 ,  F02C7/04 ,  F02K1/64 ,  F02K3/06 ,  F05D2220/323 ,  F05D2220/327 ,  F05D2260/96 ,  Y02T50/672

Abstract: A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange

Abstract translation: 用于飞行器涡轮喷气发动机的机舱包括：基本上圆柱形的内部封套，基本上圆柱形的外部封套，下游分隔壁和固定到圆柱形内部封套的上游分隔壁和设置在上游分隔壁前方的前唇缘。 圆柱形内封套包括上游部分，其包括通过附接凸缘连接到包括风扇壳体的下游部分的声罩。 特别地，前唇通过在上游和下游隔壁之间呈现下游边缘而延伸并设置在上游分隔壁上方，以便固定到圆柱形外壳的同源边缘，以便安排对 附件法兰

公开(公告)号：US20150354500A1

公开(公告)日：2015-12-10

申请号：US14830258

申请日：2015-08-19

Applicant: AIRCELLE

Inventor： Pierre CARUEL

IPC: F02K1/76

CPC classification number: F02K1/763 ,  F05D2260/403 ,  F05D2260/84

Abstract: The present disclosure provides an actuator for an aircraft turbojet engine nacelle, which is interposed between a stationary front part of the nacelle and a moveable rear part of the nacelle. The actuator includes a main actuating arm, and a secondary actuating arm which axially extends from a rear section suitable for being connected on the moveable rear part of the nacelle, to a front section secured to a main nut screwed on a worm drive, in particular, the secondary actuating arm being designed for overcoming a breakdown of the main actuating arm.

Abstract translation: 本公开提供了一种用于飞行器涡轮喷气发动机机舱的致动器，其被插入在机舱的固定前部和机舱的可移动的后部之间。 致动器包括主致动臂和辅助致动臂，其从适于连接在机舱的可移动后部上的后部轴向延伸到固定到拧在蜗杆传动装置上的主螺母的前部，特别是 ，辅助致动臂被设计成克服主致动臂的击穿。

公开(公告)号：US20130228635A1

公开(公告)日：2013-09-05

申请号：US13663652

申请日：2012-10-30

Applicant: AIRCELLE

Inventor： Pierre CARUEL

IPC: F02K1/72

CPC classification number: F02K1/72 ,  F02K1/09

Abstract: A bypass turbojet engine nacelle equipped with a thrust reverser device is provided that includes a cowl with translational mobility and a diversion means supported by a front frame upstream of the cowl. A variable-geometry jet pipe nozzle is mounted at a downstream end of the cowl and is translatable in a direction substantially parallel to a longitudinal axis of the nacelle towards at least one position that causes a variation in its cross-section. At least part of the front frame, the diversion means, and the jet pipe nozzle form an assembly having translational mobility in a direction substantially parallel to a longitudinal axis of the nacelle in a downstream direction of the nacelle towards a position that causes a variation in the cross-section of the jet pipe nozzle, the cowl being in the closed position during that movement of said assembly.

Abstract translation: 提供了一种配备有推力反向装置的旁通涡轮喷气发动机机舱，其包括具有平移运动性的整流罩和由整流罩上游的前框架支撑的分流装置。 可变几何喷射管喷嘴安装在整流罩的下游端，并且可在基本上平行于机舱的纵向轴线的方向上朝向导致其横截面变化的至少一个位置平移。 前框架，分流装置和喷射管喷嘴的至少一部分在机舱的下游方向上形成在基本上平行于机舱的纵向轴线的方向上的平移运动的组件朝向导致机舱的变化的位置 喷射管喷嘴的横截面，整流罩在所述组件的运动期间处于关闭位置。

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：US20150377132A1

公开(公告)日：2015-12-31

申请号：US14846129

申请日：2015-09-04

Applicant: AIRCELLE

Inventor： Pierre CARUEL

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

CPC classification number: F02C7/14 ,  B64D33/02 ,  B64D2033/0233 ,  F01D25/12 ,  F01D25/24 ,  F05D2220/323 ,  F05D2260/213 ,  Y02T50/675

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.

Abstract translation: 本公开提供一种飞机机舱，包括：具有上游进气口的外部空气动力壁; 内部空气动力学壁，连接两个外部和内部空气动力学外观的进气口; 前壁，布置在进气口的下游并连接两个外部和内部空气动力学表面; 以及用于循环用于冷却第二流体的第一流体的网络。 该网络包括两个空气/油型热交换器，一个空气/空气型热交换器，用于从机舱外部收集空气的空气勺，用于收集冷空气的孔和用于排放空气的出口孔。

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：US20130243589A1

公开(公告)日：2013-09-19

申请号：US13894647

申请日：2013-05-15

Applicant: AIRCELLE

Inventor： Pierre CARUEL

IPC: F02C7/20

CPC classification number: F02C7/20 ,  B64D29/06 ,  B64D33/04 ,  F01D21/045 ,  F02K1/766

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.

Abstract translation: 涡轮喷气发动机机舱包括固定结构，其具有涡轮喷气发动机的风扇壳体和安装在风扇壳体下游并直接或间接支撑叶栅叶片的前框架。 前框架能够与覆盖流动分流装置的关闭位置和暴露该流动分流装置的打开位置之间滑动的推力反向器整流罩协作。 发动机舱的至少一个加强结构在风扇壳体和前框架之间传递负载。 加强结构沿着机舱的纵向轴线延伸，并且在前框架和推力反向器整流罩之间支撑第三防线和/或抑制装置。

公开(公告)号：US20160257418A1

公开(公告)日：2016-09-08

申请号：US15153172

申请日：2016-05-12

Applicant: AIRCELLE

Inventor： Pierre CARUEL

IPC: B64D33/02 ,  B64D15/04

CPC classification number: B64D33/02 ,  B64D15/04 ,  B64D2033/0206 ,  B64D2033/0233 ,  B64D2033/0286

Abstract: A de-icing device is provided that includes a piccolo tube integrated with a front bulkhead for limiting an inner volume of a perforated front lip. The piccolo tube is in contact with a noise reduction cellular structure provided with perforations and hot air circulation channels delivered by the piccolo tube, the de-icing hot air being diffused through the perforations and channels of the cellular structure, on the perforations facing the front lip.

Abstract translation: 提供了一种除冰装置，其包括与前舱壁一体的短路管，用于限制穿孔前唇的内部容积。 短裤管与降噪细胞结构接触，该结构设有由短裤管输送的穿孔和热空气循环通道，除冰热空气通过穿孔和细胞结构的通道扩散到面向前部的穿孔上 唇。