公开(公告)号：US20130062434A1

公开(公告)日：2013-03-14

申请号：US13656948

申请日：2012-10-22

Applicant: Aircelle

Inventor： Guy Bernard VAUCHEL ,  Peter SEGAT

IPC: F02K1/62 ,  F16C7/02

CPC classification number: F02K1/62 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F02K1/763 ,  F16C7/02 ,  Y02T50/672 ,  Y10T74/2158

Abstract: An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring.

Abstract translation: 提供了一种布置，其包括在涡轮喷气发动机机舱的内部固定结构上的推力反向器翼片连杆。 连杆通过作为弹簧的弹性装置连接到内部固定结构。

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：US20140154064A1

公开(公告)日：2014-06-05

申请号：US14176236

申请日：2014-02-10

Applicant: AIRCELLE

Inventor： Xavier BOUTEILLER ,  Patrick BOILEAU ,  Peter SEGAT

IPC: F02K1/56

CPC classification number: F02K1/566 ,  F02K1/72 ,  Y02T50/672

Abstract: A thrust reverser device of a nacelle includes a thrust reversal cowl which moves alternately from a closed position to an open position in which the thrust reversal cowl opens a path within the nacelle and uncovers a flow deflector, and a rear frame supporting deflecting cascades. The flow deflector includes first deflecting cascades distributed over a circumference of the thrust reversal cowl and arranged so that a diverted flow passes, at least in part, through the first deflecting cascades, when the thrust reverser device is in reverse jet. In particular, the rear frame has an extension structure provided with second deflecting cascades which redirect a portion of the diverted flow when the thrust reverser device is in reverse jet.

Abstract translation: 机舱的推力反向装置包括推力反转罩，其从关闭位置交替地移动到打开位置，在该位置推力反转罩在机舱内打开路径并且露出导流板，以及支撑偏转级联的后框架。 导流器包括分布在推力反向罩的圆周上的第一偏转级联，并且布置成使得当推力反向装置处于反向喷射时，转向流至少部分地穿过第一偏转级联。 特别地，后框架具有延伸结构，该延伸结构设置有第二偏转级联，当推力反向装置处于反向喷射状态时，该第二偏转级联重新定向一部分转向流。

公开(公告)号：US20160222917A1

公开(公告)日：2016-08-04

申请号：US15093805

申请日：2016-04-08

Applicant: AIRCELLE

Inventor： Peter SEGAT ,  Sarah TISSOT ,  Xavier BOUTEILLER

IPC: F02K1/76 ,  B64D33/04 ,  F02K1/72

CPC classification number: F02K1/763 ,  B64D33/04 ,  F02K1/09 ,  F02K1/1261 ,  F02K1/72 ,  F02K1/766 ,  F05D2220/323 ,  F05D2240/128 ,  F05D2240/129

Abstract: The present disclosure concerns a nacelle for an aircraft engine, which includes a thrust reverser cowling that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling opens a passage in the nacelle and uncovers a deflection device, and at least one actuator for moving the cowling. The nozzle section of the cowling delimits at least one opening that is combined with a leakage door, the leakage door being movably mounted on the cowling between a closed position in which the door engages with the associated opening to counteract the flow of air through said opening, and an open escape position in which the door is retracted to allow a portion of the air flow to flow through said opening.

Abstract translation: 本公开涉及一种用于飞行器发动机的机舱，其包括可滑动地安装在直接喷射位置和反向喷射位置之间的推力反向器整流罩，在该反向喷射位置中，整流罩打开机舱中的通道并露出偏转装置，并且在 至少一个用于移动整流罩的致动器。 整流罩的喷嘴部分限定了与泄漏门组合的至少一个开口，泄漏门​​可移动地安装在整流罩上，在关闭位置之间，门与相关联的开口啮合以抵消空气流过所述开口 以及敞开的逃逸位置，其中门缩回以允许空气流的一部分流过所述开口。

公开(公告)号：US20150097056A1

公开(公告)日：2015-04-09

申请号：US14566995

申请日：2014-12-11

Applicant: AIRCELLE

Inventor： Pierre CARUEL ,  Peter SEGAT

IPC: F02K1/72 ,  F02K1/76 ,  F02K1/09

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，级联叶片在缩回位置和活动位置之间移动，并且容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。