公开(公告)号：US20150167586A1

公开(公告)日：2015-06-18

申请号：US14630837

申请日：2015-02-25

Applicant: AIRCELLE

Inventor： Fabrice PROVOST

IPC: F02K1/80

CPC classification number: F02K1/80 ,  F01D25/243 ,  F02K1/54 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2260/37

Abstract: The present disclosure relates to a holding assembly to hold a front frame of a thrust reverser to a turbojet engine casing. The assembly includes at least one connecting flange connecting the front frame to the turbojet engine casing, and also a system for locking the connecting flange. The system includes an actuating handle pivotally mounted on one of two facing ends of the connecting flange, and a connecting rod interposed between the other end of the two facing ends and a portion of the actuating handle. The system locks together the two facing ends, and the actuating handle includes a support provided with a groove and a screw for adjusting a free length of the groove. Furthermore, the connecting rod has, at its one end, an axis pivoting and sliding in the groove.

Abstract translation: 本公开涉及一种用于将推力反向器的前框架保持到涡轮喷气发动机壳体的保持组件。 该组件包括至少一个将前框架连接到涡轮喷气发动机壳体的连接凸缘，以及用于锁定连接凸缘的系统。 该系统包括枢转地安装在连接凸缘的两个相对端的一个上的致动柄，以及插入在两个相对端的另一端和致动手柄的一部分之间的连杆。 系统将两个相对的端部锁定在一起，并且致动手柄包括设置有凹槽的支撑件和用于调节槽的自由长度的螺钉。 此外，连杆在其一端具有在凹槽中枢转和滑动的轴。

公开(公告)号：US09051899B2

公开(公告)日：2015-06-09

申请号：US14177494

申请日：2014-02-11

Applicant: AIRCELLE

Inventor： Helene Malot ,  Philippe Bienvenu

IPC: G10K11/172 ,  F02K1/82 ,  F02K1/04 ,  F02K1/44 ,  F02K1/80

CPC classification number: F02K1/827 ,  F02K1/04 ,  F02K1/44 ,  F02K1/80 ,  F05D2230/232 ,  F05D2250/283 ,  F05D2260/30 ,  Y02T50/671

Abstract: An exhaust cone for an aircraft turbojet engine includes a front part which has a front end and a rear end. The front end is equipped with a front connecting flange connecting to an outlet of a turbojet engine and the rear end is equipped with a rear connecting flange connecting to a rear part of the exhaust cone. In particular, the front part is further equipped with a sound attenuation structure including an outer skin, and the outer skin overlaps the front connecting flange and the rear connecting flange.

Abstract translation: 用于飞机涡轮喷气发动机的排气锥体包括具有前端和后端的前部。 前端配备有连接到涡轮喷气发动机的出口的前连接凸缘，并且后端配备有连接到排气锥的后部的后连接凸缘。 特别地，前部还配备有包括外皮的声音衰减结构，并且外表皮与前连接凸缘和后连接凸缘重叠。

公开(公告)号：US20150083823A1

公开(公告)日：2015-03-26

申请号：US14558833

申请日：2014-12-03

Applicant: AIRCELLE

Inventor： Hervé HURLIN ,  Olivier GILO ,  Olivier KERBLER

IPC: F02K1/76 ,  F16D11/14

CPC classification number: F02K1/763 ,  F02K1/766 ,  F05D2250/41 ,  F05D2260/4031 ,  F16D11/10 ,  F16D11/14 ,  F16D2011/006

Abstract: A mechanism for coupling and uncoupling a motor inlet shaft and an outlet shaft, in particular, the inlet shaft is mounted in rotation on a front frame, and the outlet shaft is mounted in rotation on a rear frame. The outlet shaft rotates an outlet pinion, and the rear frame is slidably mounted to translate between a forward compact position and a backward deployed position. The mechanism includes a coupler, and first and second lockers to couple or uncouple the inlet and outlet shafts according to the translation of the rear frame between the forward compact position and the backward deployed position. The first locker locks in rotation the inlet shaft on the front frame, the second locker locks the outlet shaft on the rear frame. In particular, the second locker automatically locks the inlet and outlet shafts in rotation respectively, according to the displacement of the rear frame.

Abstract translation: 用于将电动机入口轴和出口轴，特别是入口轴联接和分离的机构旋转安装在前框架上，并且出口轴旋转安装在后框架上。 出口轴使出口小齿轮旋转，并且后框架可滑动地安装以在前部紧凑位置和向后展开位置之间平移。 该机构包括联接器，以及第一和第二储物柜，用于根据在前紧凑位置和向后展开位置之间的后框架的平移来连接或分离入口和出口轴。 第一个储物柜锁定前框架上的入口轴，第二个储物柜将出口轴锁定在后框架上。 特别地，第二储物柜根据后框架的位移自动将入口和出口轴锁定在旋转中。

公开(公告)号：US20150030445A1

公开(公告)日：2015-01-29

申请号：US13945023

申请日：2013-07-18

Applicant: Aircelle

Inventor： Patrick GONIDEC ,  Laurent Albert Blin

IPC: B64D29/06 ,  B64D33/02

CPC classification number: B64D29/06 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/0266 ,  B64D2033/0273 ,  B64D2033/0286 ,  F02C7/042 ,  F02C7/047 ,  F02K1/30 ,  Y02T50/671 ,  Y10T137/0536

Abstract: A nacelle for a turbojet engine has a longitudinal axis and a rear section including an annular vein formed by a wall of a fixed internal structure and a wall of an external structure. The nacelle includes a device for modulating the cross-section of a space formed by the annular vein. The device includes an injector to inject an auxiliary flow of a gas so as to vary the orientation or speed of the auxiliary flow, a suction orifice for drawing in part of the injected auxiliary flow, and an internal auxiliary flow return area in one or more walls. In particular, the internal return area allows the circulation of part of the injected auxiliary flow and the drawn-in auxiliary flow

Abstract translation: 用于涡轮喷气发动机的机舱具有纵向轴线和后部分，其包括由固定内部结构的壁和外部结构的壁形成的环形静脉。 机舱包括用于调制由环形静脉形成的空间的横截面的装置。 该装置包括喷射器以喷射气体的辅助流，以改变辅助流的取向或速度，用于抽吸部分注入的辅助流的吸入孔以及一个或多个内部辅助流回流区域 墙壁 特别地，内部返回区域允许部分注入的辅助流和引入的辅助流的循环

公开(公告)号：US08939713B2

公开(公告)日：2015-01-27

申请号：US13681219

申请日：2012-11-19

Applicant: Aircelle

Inventor： Céline Blin ,  Guillaume Strub ,  Vincent Peyron

IPC: F01D5/00 ,  F04D29/66 ,  F01D25/24 ,  B64D29/00 ,  B64D33/02

CPC classification number: F01D25/24 ,  B64D29/00 ,  B64D33/02

Abstract: An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.

Abstract translation: 提供了一种用于飞机机舱的空气动力学元件，其包括固定护罩和相对于护罩可轴向移动的进气口。 空气动力学元件是柔性的并且具有大致圆柱形的总体形状并且限定附接到机舱的进气口的内壁的上游部分和径向抵靠护罩的内表面的下游部分。 元件的下游部分包括朝向空气动力学元件的外侧突出的环形凸缘和在其自由端的方向上朝向空气动力学元件的外侧倾斜的端部叶片。

公开(公告)号：US20150007896A1

公开(公告)日：2015-01-08

申请号：US14496518

申请日：2014-09-25

Applicant: AIRCELLE

Inventor： Jean-Philippe JORET ,  André BAILLARD

IPC: F02C7/045 ,  B64D33/02 ,  B64D29/00

CPC classification number: F02C7/045 ,  B64D29/00 ,  B64D29/06 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/20 ,  F05D2230/64 ,  Y10T137/0536

Abstract: An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.

Abstract translation: 用于涡轮喷气发动机机舱的进气结构包括附接到风扇壳体的内板和能够在机舱的纵向方向上的平移运动的外板。 外部面板包括能够在内部面板和外部面板之间提供接合部的空气入口唇缘的一部分，并且至少在接合端的区域中配备每个空气入口唇部和内部面板， 具有声衰减结构。 特别地，当外部面板处于关闭位置时，连接端中的至少一个配备有径向缓冲器，该径向缓冲器能够与另一接合端所示的相应的接合凸缘接触。

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：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：US20140341744A1

公开(公告)日：2014-11-20

申请号：US14322601

申请日：2014-07-02

Applicant: AIRCELLE

Inventor： Xavier CAZUC ,  Jean-Philippe JORET

IPC: F02K1/82

CPC classification number: F02K1/827 ,  F01D9/041 ,  F05D2260/96 ,  F05D2260/963 ,  Y02T50/672 ,  Y02T50/673

Abstract: A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure.

Abstract translation: 用于涡轮喷气发动机的蜂窝声学结构包括封闭壁。 闭合的壁包括具有声学透明区域和声反射区域的至少两个面。 封闭的墙壁上填充有多个单元，并且声反射区域设置在闭合的壁内，使得空中声音振动的声路径穿过声透明区域，穿透在单元内并在声反射区域上反射。 特别地，一些单元中的声学路径具有大于蜂窝声学结构的厚度的一半的深度。

公开(公告)号：US08876018B2

公开(公告)日：2014-11-04

申请号：US13656948

申请日：2012-10-22

Applicant: Aircelle

Inventor： Guy Bernard Vauchel ,  Peter Segat

IPC: B63H11/00 ,  B64D33/04 ,  F02K1/00 ,  F02K3/02 ,  F02K1/62 ,  F16C7/02 ,  F02K1/72 ,  B64D29/06 ,  F02K1/76

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。