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：US20150113944A1

公开(公告)日：2015-04-30

申请号：US14226180

申请日：2014-03-26

Applicant: AIRCELLE

Inventor： Sébastien PASCAL ,  Laurent Albert BLIN

IPC: F02K1/68 ,  B64D33/04

CPC classification number: F02K1/68 ,  B64D33/04 ,  F02K1/70 ,  Y02T50/671

Abstract: A door for a door-type thrust reverser is able to move between a direct jet mode of a nacelle and a reverse jet mode. The door includes an inner wall being integrated into a flow path of an air flow generated by a turbojet engine, an outer wall, at least one side wall connecting the inner wall to the outer wall of the door, and a deflector to deflect the air flow. In particular, the deflector includes a cavity of the door which is shaped to convey a fraction of the air flow from one air inlet rigidly secured to the inner wall of the door to one air outlet rigidly secured to the side wall of the door, so as to redirect, during operation of the nacelle in the reverse jet mode, a part of the air flow upstream from the inner wall of the door.

Abstract translation: 门式推力反向器的门能够在机舱的直接喷射模式和反向喷射模式之间移动。 门包括内壁，该内壁整合到由涡轮喷气发动机产生的空气流的流动路径中，外壁，连接内壁和门的外壁的至少一个侧壁以及偏转空气 流。 特别地，偏转器包括门的空腔，其形状适于将一小部分空气流从刚性地固定到门的内壁的一个空气入口传送到刚性地固定到门的侧壁的一个空气出口，因此 为了在反向喷射模式下在机舱的操作期间重定向一部分空气流从门的内壁上游。

公开(公告)号：US20130056554A1

公开(公告)日：2013-03-07

申请号：US13662926

申请日：2012-10-29

Applicant: AIRCELLE

Inventor： Denis GUILLOIS ,  Laurent Albert BLIN ,  Löic CHAPELAIN

IPC: B63H11/10

CPC classification number: F02K1/60 ,  B64D33/04 ,  F02K1/70 ,  F02K1/763 ,  Y02T50/671

Abstract: A thrust reverser with doors having at least one stationary structure is provided, on which at least one door is mounted pivoting between a closed position in which the door closes the reverser and makes up an outer cowling part, and an open position in which the door opens a passage in the stationary structure and can at least partially block a flow of air generated by a turbojet engine so as to reorient the door. The stationary structure includes at least two sets of cascade vanes that can be covered by the door when in the closed position.

Abstract translation: 提供具有至少一个固定结构的门的推力反向器，其上安装有至少一个门，枢转在关闭位置之间，门关闭反向器并构成外整流罩部分，以及打开位置，其中门 打开固定结构中的通道并且可以至少部分地阻挡由涡轮喷气发动机产生的空气流，以便重新定向门。 固定结构包括至少两组级联叶片，当组合叶片处于关闭位置时可以被门覆盖。