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公开(公告)号：US09410485B2
公开(公告)日：2016-08-09
申请号：US14272884
申请日：2014-05-08
Applicant: AIRCELLE
Inventor： Franck Laurant , Francois Bellet , Jean-Philippe Joret
IPC: B32B3/24 , B64D33/02 , B64D29/00 , B64C7/02 , B64C1/00 , F02C7/20 , B64D33/08 , F02C7/04 , F01D25/24 , B29L31/00 , B29L31/30 , B32B3/26 , F02C6/08
CPC classification number: F02C7/20 , B29L2031/3076 , B29L2031/7504 , B32B3/266 , B32B2250/03 , B32B2250/40 , B32B2605/18 , B64C7/02 , B64D29/00 , B64D33/08 , B64D2241/00 , F01D25/24 , F02C6/08 , F02C7/04 , F05D2240/14 , F05D2270/09 , F05D2300/603 , Y02T50/672 , Y10T428/24182 , Y10T428/24281 , Y10T428/24322 , Y10T428/24612
Abstract: A composite panel includes an inner skin and an outer skin and has an opening for receiving a sampling scoop, which forms a channel and the sampling opening of which is in communication with the outer skin. In particular, the outer skin is shaped such that, at the opening, same forms at least a portion of a flow surface of the sampling scoop.
Abstract translation: 复合面板包括内皮和外皮，并且具有用于接收采样勺的开口，其形成通道，并且其采样开口与外皮连通。 特别地，外皮成形为使得在开口处相同形成采样勺的流动表面的至少一部分。
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公开(公告)号：US20160016669A1
公开(公告)日：2016-01-21
申请号：US14633269
申请日：2015-02-27
Applicant: AIRCELLE
Inventor： Xavier CAZUC , Jean-Philippe Joret
CPC classification number: B64D29/06 , F01D25/28 , F02K1/70 , F02K1/72 , F05D2300/603 , Y02T50/672
Abstract: The present disclosure relates to a front frame for an aircraft nacelle comprising a turbojet mounted on a suspension strut, said nacelle comprising a thrust reverser including an actuator designed to open a thrust reversal cowling. The front frame comprises a tubular torsion box, a first straight attachment edge intended to attach the box to a turbojet casing and a second straight attachment edge intended to attach the box to air flow diversion means. The front frame is arranged to transmit tensile and compressive loads between the turbojet casing and the air flow diversion means and torsion loads absorbed by the suspension strut. The front frame is characterized in that the tubular torsion box has a semi-elliptical or elliptical cross-section.
Abstract translation: 本公开涉及一种用于飞机机舱的前架，其包括安装在悬架支柱上的涡轮喷气发动机，所述机舱包括推力反向器，其包括设计成打开推力反向罩的致动器。 前框架包括管状扭转箱，用于将箱子附接到涡轮喷气发动机壳体的第一直线附接边缘和用于将箱体附接到空气流引导装置的第二直线附接边缘。 前框架布置成在涡轮喷气发动机壳体和空气流动分流装置之间传递拉伸和压缩载荷以及由悬架支柱吸收的扭转载荷。 前框架的特征在于，管状扭转箱具有半椭圆形或椭圆形的横截面。
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公开(公告)号：US09938897B2
公开(公告)日：2018-04-10
申请号：US14496518
申请日：2014-09-25
Applicant: Aircelle
Inventor： Jean-Philippe Joret , André Baillard
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.
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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
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.
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公开(公告)号：US09670878B2
公开(公告)日：2017-06-06
申请号：US14322601
申请日：2014-07-02
Applicant: AIRCELLE
Inventor： Xavier Cazuc , Jean-Philippe Joret
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.
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Patent Agency Ranking
6.发明授权Control device for a turbojet engine thrust reverser, blocking the reverser 有权用于涡轮喷气发动机推力反向器的控制装置，阻挡反向器公开(公告)号：US09593644B2
公开(公告)日：2017-03-14
申请号：US14975326
申请日：2015-12-18
Applicant: AIRCELLE
Inventor： Jean-Philippe Joret , Pascal Soulier , Vincent Taddei
Abstract: A control device for a thrust reverser of a turbojet engine nacelle, which includes movable portions actuated by actuators, includes: a first blocking control acting on a motor-actuated system; and a second blocking control acting, mechanically, on the movable portions. The second blocking control may inhibit, when activated, a deployment of the movable portions. The control device further includes a device inhibiting disengagement of the first blocking control when a mechanical control is activated.
Abstract translation: 用于涡轮喷气发动机机舱的推力反向器的控制装置，其包括由致动器致动的可动部分，包括：作用在电动机致动系统上的第一阻塞控制; 以及机械地作用在可动部分上的第二阻挡控制。 第二阻塞控制可以在被激活时抑制可移动部分的展开。 控制装置还包括当机械控制被激活时禁止第一阻塞控制分离的装置。
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公开(公告)号：US08769926B2
公开(公告)日：2014-07-08
申请号：US13735096
申请日：2013-01-07
Applicant: Aircelle
Inventor： Guy Bernard Vauchel , Jean-Philippe Joret
IPC: F02K1/72
Abstract: A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.
Abstract translation: 提供了一种用于涡轮喷气发动机机舱的推力反向装置，其包括偏转装置和相对于至少一个固定结构可移动的至少一个整流罩，该至少一个整流罩包括至少一个至少部分外围的前框架，并且装备有用于连接到相应的上游部分 。 前框架具有偏转边缘，该偏转边缘具有形成可变形翼片的上游延伸部分，该可变形翼片旨在成为与附接到前框架的对应的上游部分成为空气动力学界面，并且可移动整流罩的一部分被配合成 关闭位置，通过强制撤出可变形翼片与所述上游连接部分相接合。
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公开(公告)号：US20130126638A1
公开(公告)日：2013-05-23
申请号：US13735096
申请日：2013-01-07
Applicant: AIRCELLE
Inventor： Guy Bernard VAUCHEL , Jean-Philippe Joret
IPC: F02K1/62
Abstract: A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap.
Abstract translation: 提供了一种用于涡轮喷气发动机机舱的推力反向装置，其包括偏转装置和相对于至少一个固定结构可移动的至少一个整流罩，该至少一个整流罩包括至少一个至少部分外围的前框架，并且装备有用于连接到相应的上游部分 。 前框架具有偏转边缘，该偏转边缘具有形成可变形翼片的上游延伸部分，该可变形翼片旨在成为与附接到前框架的对应的上游部分成为空气动力学界面，并且可移动整流罩的一部分被配合成 关闭位置，通过强制撤出可变形翼片与所述上游连接部分相接合。
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公开(公告)号：US09834313B2
公开(公告)日：2017-12-05
申请号：US14633269
申请日：2015-02-27
Applicant: AIRCELLE
Inventor： Xavier Cazuc , Jean-Philippe Joret
CPC classification number: B64D29/06 , F01D25/28 , F02K1/70 , F02K1/72 , F05D2300/603 , Y02T50/672
Abstract: The present disclosure relates to a front frame for an aircraft nacelle comprising a turbojet mounted on a suspension strut, said nacelle comprising a thrust reverser including an actuator designed to open a thrust reversal cowling. The front frame comprises a tubular torsion box, a first straight attachment edge intended to attach the box to a turbojet casing and a second straight attachment edge intended to attach the box to air flow diversion means. The front frame is arranged to transmit tensile and compressive loads between the turbojet casing and the air flow diversion means and torsion loads absorbed by the suspension strut. The front frame is characterized in that the tubular torsion box has a semi-elliptical or elliptical cross-section.
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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。
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