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：US08757319B2

公开(公告)日：2014-06-24

申请号：US13713750

申请日：2012-12-13

Applicant: Aircelle

Inventor： Xavier Bouteiller ,  Laurent Albert Blin

IPC: F01N1/14

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：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：US20160040624A1

公开(公告)日：2016-02-11

申请号：US14797587

申请日：2015-07-13

Applicant: AIRCELLE

Inventor： Xavier Bouteiller ,  Patrick Gonidec ,  Laurent Albert Blin

IPC: F02K1/06 ,  F01D25/24

CPC classification number: F02K1/06 ,  F01D25/24 ,  F02K1/09 ,  F02K1/38 ,  F02K1/46 ,  F05D2220/323 ,  Y02T50/671

Abstract: A nacelle jet pipe is equipped with a device for regulating the pressure of a flow of air leaving the jet pipe. The device includes an annular element surrounding the downstream end of the jet pipe, and an adjuster to adjust the position of part of the annular element in relation to the downstream end of the jet pipe. In particular, the annular element forms, with the downstream end of the jet pipe, a constricted zone the widest part of which is situated upstream of the narrowest part and the profile of which can be varied according to the position of the annular element.

Abstract translation: 机舱喷射管配备有用于调节离开喷射管的空气流的压力的装置。 该装置包括围绕喷射管的下游端的环形元件和调节器，用于相对于喷射管的下游端调节环形元件的一部分的位置。 特别地，环形元件与喷射管的下游端形成收缩区，其最宽的部分位于最窄部分的上游，并且其轮廓可以根据环形元件的位置而变化。

公开(公告)号：US20140360158A1

公开(公告)日：2014-12-11

申请号：US14328967

申请日：2014-07-11

Applicant: AIRCELLE

Inventor： Patrick Gonidec ,  Laurent Albert Blin ,  Xavier Bouteiller ,  LoÏc Chapelain

IPC: F02K1/32

CPC classification number: F02K1/32 ,  F02K1/70 ,  F05D2260/901 ,  Y02T50/672

Abstract: A thrust reverser for aircraft turbojet engine nacelle includes at least one upstream door and a downstream door. The upstream and downstream doors move in concert between a direct jet position and a reverse jet position. In the direct jet position, two doors are closed, and in the reverse jet position the two doors are open and able to deflect a part of a cold air flow circulating inside the nacelle. The thrust reverser further includes a curved downstream edge of the upstream door to make adapted a part of cold air flow circulating between an upper camber of the upstream door and a lower camber of the downstream door.

Abstract translation: 用于飞行器涡轮喷气发动机机舱的推力反向器包括至少一个上游门和下游门。 上游和下游门在直接喷射位置和反向喷射位置之间协调运动。 在直接喷射位置，两个门关闭，并且在反向喷射位置，两个门是敞开的，并且能够使在机舱内循环的一部分冷气流偏转。 推力反向器还包括上游门的弯曲的下游边缘，以使适应的一部分冷气流在上游门的上弯道和下游门的下弧面之间循环。