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公开(公告)号：US20150267643A1
公开(公告)日：2015-09-24
申请号：US14464649
申请日：2014-08-20
申请人： AIRCELLE
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , Y02T50/671
摘要： A cascade-type thrust reverser for an aircraft turbojet engine includes a front frame, a sliding cowl between a direct jet position and a reverse jet position, a plurality of actuating cylinders interposed between this front frame and this sliding cowl, and a plurality of cascades pivotally mounted on the front frame between the direct and reverse jet positions. In the direct jet position, the cascades are substantially parallel to the axis (A) of the thrust reverser, and in the reverse jet position, the cascades are inclined relative to the axis (A) of the thrust reverser. In particular, the cascade-type thrust reverser includes a single radial layer of cascades.
摘要翻译： 用于飞行器涡轮喷气发动机的级联型推力反向器包括前框架，在直接喷射位置和反向喷射位置之间的滑动罩，插入在该前框架和该滑动罩之间的多个致动缸以及多个级联 在直接和反向喷射位置之间枢转地安装在前框架上。 在直接喷射位置，级联基本上平行于推力反向器的轴线（A），并且在反向喷射位置中，级联相对于推力反向器的轴线（A）倾斜。 特别地，级联型推力反向器包括单个径向的级联层。
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公开(公告)号：US08757319B2
公开(公告)日：2014-06-24
申请号：US13713750
申请日：2012-12-13
申请人： Aircelle
IPC分类号： F01N1/14
CPC分类号： F02K1/34 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C3/13 , F02C7/045 , F02C9/18 , F02K3/077 , F05D2260/96 , Y02T50/672
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20150030445A1
公开(公告)日：2015-01-29
申请号：US13945023
申请日：2013-07-18
申请人： Aircelle
CPC分类号： B64D29/06 , B64D33/02 , B64D2033/0226 , B64D2033/0266 , B64D2033/0273 , B64D2033/0286 , F02C7/042 , F02C7/047 , F02K1/30 , Y02T50/671 , Y10T137/0536
摘要： 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
摘要翻译： 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
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公开(公告)号：US20160040624A1
公开(公告)日：2016-02-11
申请号：US14797587
申请日：2015-07-13
申请人： AIRCELLE
CPC分类号： F02K1/06 , F01D25/24 , F02K1/09 , F02K1/38 , F02K1/46 , F05D2220/323 , Y02T50/671
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US20150030446A1
公开(公告)日：2015-01-29
申请号：US13946316
申请日：2013-07-19
申请人： Aircelle
CPC分类号： B64D29/06 , B64D33/02 , B64D2033/0226 , B64D2033/0266 , B64D2033/0273 , B64D2033/0286 , F02C7/042 , F02C7/047 , F02K1/30 , Y02T50/671 , Y10T137/0536
摘要： The disclosure relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space for the circulation of a main air flow. The nacelle includes a device for modulating the cross-section of the space and has means for injecting an auxiliary flow of a gas by means of an induced ejector effect; suction means for drawing in the injected auxiliary flow; and an internal auxiliary flow return area in one or more walls, the area being configured to allow the circulation of the injected auxiliary flow and the drawn-in auxiliary flow and to bring part of the injected auxiliary flow into contact with the main air flow. The internal return area includes an outer front part forming an area in which the thickness of the internal return area is reduced.
摘要翻译： 本发明涉及一种用于涡轮喷气发动机的机舱，包括形成进气口的上游部分并且限定用于主空气流的循环的空间。 机舱包括用于调节空间横截面的装置，并具有用于通过感应喷射器效应喷射气体的辅助流的装置; 用于吸入注入的辅助流的抽吸装置; 以及在一个或多个壁中的内部辅助流量返回区域，所述区域被配置为允许注入的辅助流和吸入的辅助流的循环，并使部分喷射的辅助流与主空气流接触。 内部返回区域包括外部前部，形成内部返回区域的厚度减小的区域。
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公开(公告)号：US20140360158A1
公开(公告)日：2014-12-11
申请号：US14328967
申请日：2014-07-11
申请人： AIRCELLE
IPC分类号： F02K1/32
CPC分类号： F02K1/32 , F02K1/70 , F05D2260/901 , Y02T50/672
摘要： 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.
摘要翻译： 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。
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公开(公告)号：US08783010B2
公开(公告)日：2014-07-22
申请号：US13662926
申请日：2012-10-29
申请人： Aircelle
CPC分类号： F02K1/60 , B64D33/04 , F02K1/70 , F02K1/763 , Y02T50/671
摘要： 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.
摘要翻译： 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。
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