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1. 发明公开

EP2961974A1 DISPOSITIF D'INVERSION DE POUSSEE 审中-公开
公开(公告)号：EP2961974A1
公开(公告)日：2016-01-06
申请号：EP14711834.3
申请日：2014-03-03
申请人： Aircelle
发明人： BOILEAU, Patrick , SEGAT, Peter , CARUEL, Pierre , TISSOT, Sarah
IPC分类号： F02K1/09 , F02K1/72
CPC分类号： F02K1/72 , F02K1/09 , F02K1/827 , F05D2240/129 , F05D2240/90 , F05D2250/34
摘要： The subject of the present invention is a thrust reverser device for an aircraft turbojet engine comprising: - a mobile cowl, translating cascades of vanes 1, connected to the mobile cowl able to be moved between a direct-jet position in which they are retracted inside a fan casing, on the one hand, and on the other hand an indirect-jet position in which they are deployed out of said fan casing, - a strut 2, - a front suspension means 4 of said turbojet engine, notable in that the translating cascades of vanes 1 have a sliding connection with the strut 2 via at least one spacer piece 3 connected to the strut 2 downstream of the front suspension 4.
摘要翻译：本发明的主题是一种用于飞机涡轮喷气发动机的推力反向器装置，其包括： - 移动罩，其将连接到移动罩的叶片的叶栅1平移，所述移动罩能够在直接喷射位置和直接喷射位置之间移动，一方面是风扇壳体，另一方面是间接喷射位置，其中它们从所述风扇壳体中展开， - 支柱2， - 所述涡轮喷气发动机的前悬架装置4，其特征在于，平移叶片1的叶栅通过连接到前悬架4下游的支柱2的至少一个间隔件3与支柱2具有滑动连接。

2. 发明公开

EP2791006A1 Structure d'entrée d'air pour nacelle de turboréacteur 有权转让
标题翻译： LUFTEINLASSSTRUKTURFÜREINE TURBOSTRAHL-MOTORENGONDEL
公开(公告)号：EP2791006A1
公开(公告)日：2014-10-22
申请号：EP12810370.2
申请日：2012-12-07
申请人： Aircelle
发明人： DEZEUSTRE, Nicolas , CARUEL, Pierre , GONIDEC, Patrick , BOILEAU, Patrick
IPC分类号： B64D33/02 , F02C7/045
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286
摘要： The present invention relates to an air intake structure (2) for a turbojet engine nacelle comprising a substantially annular main structure having an internal wall (12) and an external wall (11) and an air intake lip structure (13) connecting said external and internal walls upstream, a first acoustic attenuation structure having a holed acoustic skin (16), a cellular core (17) and a solid rear skin (18) with which said internal panel is equipped, and a second acoustic attenuation structure (121) having a similar architecture fitted to part of the air intake lip substantially near a junction with the internal wall, characterized in that the rear skin of the first acoustic structure is aligned with that (182) of the second acoustic structure, said rear skin also being structural.
摘要翻译：用于涡轮喷气发动机机舱的进气结构包括具有连接外壁和内壁上游的内壁，外壁和进气口结构的基本上环形的主结构。进气结构还包括第一声学衰减结构，该第一声衰减结构具有带孔的声学皮肤，多孔芯和固定的后壁，内壁配有该第一声衰减结构，以及具有类似结构的第二声衰减结构，进气口基本上在与内壁的接合处附近。第一声衰减结构的后表皮与第二声衰减结构的后表皮对准，两个后皮都是结构的。

3. 发明公开

EP3016861A1 DISPOSITIF D'ASSISTANCE POUR LA MAN UVRE D'UN CAPOT ET NACELLE DE TURBORÉACTEUR AINSI ÉQUIPÉE 有权转让
标题翻译： DEVICE FOR支机动盖子和涡轮喷气引擎，GONDEL
公开(公告)号：EP3016861A1
公开(公告)日：2016-05-11
申请号：EP14747693.1
申请日：2014-07-01
申请人： Aircelle
发明人： BOILEAU, Patrick , BLONDEAU, Samuel
IPC分类号： B64D29/08 , B64D29/06
CPC分类号： B64D29/06 , B64D29/08 , E05D7/00 , E05F3/18 , E05F3/20 , F01D25/24 , F05D2220/323
摘要： The present invention concerns a device for assisting in the manoeuvring of a cover of a nacelle of a turbojet engine or similar. The assistance device comprises a joint collinear with an existing joint or hinge for a fitting of the cover (1, 2), the joint of the device being rigidly secured to an angled part (13-15) of which one end bears on the fitting (35, 38) of the cover (1, 2) and of which one point is hinged to a compression spring (17, 27) in order to apply assistance momentum to the fitting of the cover when the cover (1, 2) is raised. Application to nacelles of turbojet engines or similar.

4. 发明授权

EP2791006B1 STRUCTURE D'ENTRÉE D'AIR POUR NACELLE DE TURBORÉACTEUR 有权转让
标题翻译：进气口结构FOR涡轮喷气发动机GONDEL
公开(公告)号：EP2791006B1
公开(公告)日：2017-01-11
申请号：EP12810370.2
申请日：2012-12-07
申请人： Aircelle
发明人： DEZEUSTRE, Nicolas , CARUEL, Pierre , GONIDEC, Patrick , BOILEAU, Patrick
IPC分类号： B64D33/02 , F02C7/045
CPC分类号： F02C7/045 , B64D33/02 , B64D2033/0206 , B64D2033/0286

5. 发明公开

EP2739840A1 NACELLE DE TURBORÉACTEUR À TUYÈRE VARIABLE 有权
标题翻译：带有可调喷嘴TL-ENGINE GONDOLA
公开(公告)号：EP2739840A1
公开(公告)日：2014-06-11
申请号：EP12743476.9
申请日：2012-06-29
申请人： Aircelle
发明人： CARUEL, Pierre , GONIDEC, Patrick , BOILEAU, Patrick
IPC分类号： F02K1/06 , F02K1/12 , F02K1/30 , F02K1/72
CPC分类号： F02K1/763 , F02K1/06 , F02K1/12 , F02K1/30 , F02K1/625 , F02K1/72 , F02K1/766 , Y02T50/671
摘要： The invention relates to a turbojet engine nacelle, including: a thrust reverser device (3), and a system for actuating said device, which includes at least one mobile cowl (30) that is translatably mounted so as to be capable of passing from a closed position, in which the cowl ensures the aerodynamic continuity of the nacelle, to an open position, in which the cowl opens a passage in the nacelle for diverted flow; and at least one gas-exhaust nozzle section (5) extending said cowl and comprising at least one nozzle flap (50) movably mounted between a closed position and at least one open position in which said nozzle flap opens a passage (51) for discharge toward the outside of the nozzle. Said nacelle is characterized in that said nozzle flap is pivotably mounted onto the mobile cowl, and the actuation system includes an actuation means capable of actuating the translation of the mobile cowl and the pivoting of the nozzle flap among three positions. The present invention can be used in the field of turbojet engines.

6. 发明公开

EP2931607A1 ENSEMBLE PROPULSIF POUR AÉRONEF 有权转让
标题翻译：驱动单元一种平面
公开(公告)号：EP2931607A1
公开(公告)日：2015-10-21
申请号：EP13820811.1
申请日：2013-12-12
申请人： Aircelle , Snecma Société Anonyme
发明人： BOILEAU, Patrick , CARUEL, Pierre , ANCUTA, Carmen , BEUTIN, Bruno
IPC分类号： B64D29/08
摘要： The invention relates to a propulsion unit (1) for an aircraft, including: a turbofan (7); a nacelle (2) surrounding the turbofan (7), including an inner structure (17) surrounding a downstream compartment of the turbofan (7), consisting of two annular half-portions (19a, 19b); and means (27, 29) for moving said half-portions, which include a rail/guide unit and are shaped such as to move the half-portion (19a, 19b) between a working position and a maintenance position. The propulsion unit according to the invention is characterised in that the rail/guide unit (27) is shaped such as to space the half-portion (19a, 19b) radially relative to a longitudinal axis of the nacelle, during a translation movement of the half-portion (19a, 19b) and in that the moving means include at least one connecting rod (29) which is connected to the half-portion (19a, 19b) and to the turbofan (7) and which is shaped such as to rotate the half-portion about said rail (37).

7. 发明公开

EP2742228A1 DISPOSITIF D'INVERSION DE POUSSÉE 审中-公开
标题翻译：推力反向器
公开(公告)号：EP2742228A1
公开(公告)日：2014-06-18
申请号：EP12744048.5
申请日：2012-07-05
申请人： Aircelle
发明人： BOUTEILLER, Xavier , BOILEAU, Patrick , SEGAT, Peter
IPC分类号： F02K1/72
CPC分类号： F02K1/566 , F02K1/72 , Y02T50/672
摘要： The invention relates to a thrust reverser device (100) for a nacelle, including at least: a translatable thrust reverser cowl (30) capable of alternately passing from a closed position, in which the cowl ensures the aerodynamic continuity of the nacelle and covers a flow-diverting means (40, 80), to an open position, in which the cowl opens a passage in the nacelle and uncovers the flow-diverting means (40, 80); a means (40) for diverting the flow through the passage, including a plurality of first cascades (40) distributed over the circumference of the cowl (30) and arranged such that at least a portion of the diverted flow passes through said cascades; and a rear frame (70) supporting a downstream end of at least one cascade (40), the thrust reverser device being characterized in that the rear frame (70) includes at least one extending structure (80) having second cascades (81) that redirect a portion of the diverted flow when the jet of the device is reversed, said structure (80) extending the first cascades (40).

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