公开(公告)号：US20150030446A1

公开(公告)日：2015-01-29

申请号：US13946316

申请日：2013-07-19

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: 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.

Abstract translation: 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。

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。

公开(公告)号：US08833055B2

公开(公告)日：2014-09-16

申请号：US13801813

申请日：2013-03-13

Applicant: Aircelle

Inventor： Patrick Gonidec ,  Philippe Avenel ,  Pierre Moradell-Casallas

IPC: F02K1/09 ,  F02K1/76 ,  F02K1/72

CPC classification number: F02K1/766 ,  F02K1/09 ,  F02K1/72 ,  Y02T50/671

Abstract: A locking/unlocking device for a thrust reverser with sliding cover and adaptive nozzle is provided that includes a fixed pin secured to a fixed structure of the reverser, a first sleeve secured to the sliding cover and able to accommodate the pin, a second sleeve slidably mounted on the first sleeve, a third sleeve secured to the adaptive nozzle and slidably mounted on the second sleeve, first locking means able to lock the first sleeve with respect to the pin, second locking means able to lock the second sleeve with respect to the first sleeve, and third locking means able to lock the third sleeve with respect to the second sleeve.

Abstract translation: 提供一种用于具有滑动盖和自适应喷嘴的​​推力反向器的锁定/解锁装置，其包括固定到反向器的固定结构的固定销，固定到滑动盖并能够容纳销的第一套筒，可滑动地 安装在第一套筒上，第三套筒固定到自适应喷嘴并可滑动地安装在第二套筒上，第一锁定装置能够相对于销锁定第一套筒，第二锁定装置能够相对于第二套筒锁定第二套筒 第一套筒和第三锁定装置能够相对于第二套筒锁定第三套筒。

公开(公告)号：US10294822B2

公开(公告)日：2019-05-21

申请号：US14471323

申请日：2014-08-28

Applicant: AIRCELLE

Inventor： Pierre Caruel ,  Franck Zaganelli ,  Patrick Gonidec ,  Olivier Kerbler

IPC: F01D25/24 ,  B64D15/04 ,  B64D33/10 ,  F02C7/047 ,  F02C7/12 ,  F02K3/06 ,  B64D33/02

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.

公开(公告)号：US10125721B2

公开(公告)日：2018-11-13

申请号：US14987302

申请日：2016-01-04

Applicant: AIRCELLE

Inventor： Olivier Kerbler ,  Olivier Gilo ,  Patrick Gonidec

IPC: F02K1/12 ,  B64D29/06 ,  B64D33/04 ,  B64C15/02 ,  F02K1/76

Abstract: The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl.

公开(公告)号：US09334831B2

公开(公告)日：2016-05-10

申请号：US13917905

申请日：2013-06-14

Applicant: AIRCELLE

Inventor： Patrick Gonidec ,  Alexandre Bellanger

IPC: B64D29/06 ,  B64D33/02 ,  F02K1/76 ,  F02K1/70 ,  F02K1/72 ,  F01D25/24

CPC classification number: F02K1/766 ,  B64D29/06 ,  F01D25/24 ,  F02K1/70 ,  F02K1/72 ,  Y02T50/671

Abstract: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Abstract translation: 用于飞机旁路涡扇发动机的机舱包括气流进入的上游部分，围绕涡扇风扇的风扇的中间部分和具有内部结构的下游部分和限定空气流动的流动管道的外部结构。 外部结构包括可移动地安装在内部固定结构上的一个整流罩。 机舱也有一个顶部，接受一个挂架安装飞机的翼。 机舱还包括安装在机舱的一侧上的内部结构上的一个第一面板和安装在机舱的另一侧上的一个第二面板。 第一个面板与机翼的一部分发生物理干扰。 第二个面板在推力反向时增加了从机舱的另一侧移除的空气。

公开(公告)号：US20130280052A1

公开(公告)日：2013-10-24

申请号：US13917905

申请日：2013-06-14

Applicant: AIRCELLE

Inventor： Patrick Gonidec ,  Alexandre Bellager

IPC: F01D25/24

CPC classification number: F02K1/766 ,  B64D29/06 ,  F01D25/24 ,  F02K1/70 ,  F02K1/72 ,  Y02T50/671

Abstract: A nacelle for an aircraft bypass turbofan engine includes an upstream section via which an airflow enters, a middle section surrounding the fan of the turbofan and a downstream section having an inner structure and an outer structure delimiting a flow duct in which the air flows. The outer structure includes one cowling movably mounted on the inner fixed structure. The nacelle also has a top to accept a pylon for attaching a wing of the aircraft. The nacelle further includes one first panel mounted on the inner structure on one side of the nacelle and one second panel mounted on the other side of the nacelle. The first panel undergoes a physical interference with a part of the wing. The second panel increases the air removed from this other side of the nacelle during thrust reversal.

Abstract translation: 用于飞机旁路涡扇发动机的机舱包括气流进入的上游部分，围绕涡扇风扇的风扇的中间部分和具有内部结构的下游部分和限定空气流动的流动管道的外部结构。 外部结构包括可移动地安装在内部固定结构上的一个整流罩。 机舱也有一个顶部，接受一个挂架安装飞机的翼。 机舱还包括安装在机舱的一侧上的内部结构上的一个第一面板和安装在机舱的另一侧上的一个第二面板。 第一个面板与机翼的一部分发生物理干扰。 第二个面板在推力反向时增加了从机舱的另一侧移除的空气。