公开(公告)号：US20130112497A1

公开(公告)日：2013-05-09

申请号：US13713750

申请日：2012-12-13

Applicant: AIRCELLE

Inventor： Xavier BOUTEILLER ,  Laurent Albert BLIN

IPC: F02K1/34

CPC classification number: F02K1/34 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C3/13 ,  F02C7/045 ,  F02C9/18 ,  F02K3/077 ,  F05D2260/96 ,  Y02T50/672

Abstract: A turbojet engine nacelle includes at least one nacelle element having a wall delimiting a main flow channel. The flow channel has a variable flow passage section. The cross-sectional area of at least one first area of the channel is greater than that of at least one second area of the channel. The turbojet engine nacelle further includes at least one secondary flow conduit establishing a fluidic connection between the first area and the second area of the channel and is arranged parallel to the channel. The wall of the nacelle element is at least partly covered by an acoustic damping panel extending in said areas of the channel. The conduit passes through the acoustic damping panel in order to establish the secondary flow via the acoustic damping panel. The present invention can be used in the avionics field.

Abstract translation: 涡轮喷气发动机机舱包括至少一个具有限定主流动通道的壁的机舱元件。 流动通道具有可变流路部分。 通道的至少一个第一区域的横截面面积大于通道的至少一个第二区域的横截面面积。 涡轮喷气发动机机舱还包括至少一个次级流动管道，其在通道的第一区域和第二区域之间建立流体连接并且平行于通道布置。 机舱元件的壁至少部分地被在通道的所述区域中延伸的声阻尼板覆盖。 管道通过声阻尼板，以便通过声阻尼板建立二次流。 本发明可用于航空电子领域。

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：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。