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公开(公告)号：EP3247634B1
公开(公告)日：2019-01-09
申请号：EP16702581.6
申请日：2016-01-21
申请人： Safran Nacelles
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公开(公告)号：EP3732360A1
公开(公告)日：2020-11-04
申请号：EP18842441.0
申请日：2018-12-20
申请人： Safran Nacelles
发明人： GRALL, Loïc , HEAU, Alexis , BREBION, Benjamin , GUILLEMANT, Sébastien, Michel, Thierry , SERISET, Mélody , BOILEAU, Patrick
IPC分类号： F02K1/72
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3.发明公开
公开(公告)号：EP3740666A1
公开(公告)日：2020-11-25
申请号：EP19704358.1
申请日：2019-01-18
申请人： Safran Nacelles
发明人： CARUEL, Pierre , GRALL, Loïc , HEAU, Alexis , KERBLER, Olivier , SERISET, Mélody
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6.发明公开ENSEMBLE ARRIÈRE DE NACELLE POUR TURBORÉACTEUR COMPRENANT UN BERCEAU POUR MÂT DU TYPE CORPS 审中-公开包括身体型MAST摇架的飞机NACELLE后组件
公开(公告)号：EP3247634A1
公开(公告)日：2017-11-29
申请号：EP16702581.6
申请日：2016-01-21
申请人： Safran Nacelles
发明人： BOILEAU, Patrick , KERBLER, Olivier , LEZERAC, Julien , GAUTIER, Armel , GRALL, Loïc , TOUPET, Ludovic
CPC分类号： F02K1/72 , B64D27/16 , B64D29/06 , F01D25/24 , F02C7/20 , F05D2220/323 , F05D2260/50
摘要： The invention relates to a rear nacelle assembly (12) for a turbojet comprising at least one device (10) for thrust reversal by redirecting an air stream circulating from upstream to downstream in a channel of the turbojet, and a pylon designed to connect the nacelle (12) to the structure of the aircraft, the nacelle (12) extending longitudinally from the front to the rear along an axis (A), characterised in that the rear nacelle assembly (12) is equipped with a cradle (34) fixed to the pylon (22) and comprising a first longeron (36a) and a second longeron (36b) extending generally longitudinally either side of the pylon (22), said longerons each carrying means (40a, 40b, 44a, 44b) for guiding, in a sliding manner, a mobile cowling (28) and the grid (32) of the thrust-reversal device (10).
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7.发明公开
公开(公告)号：EP3362667A1
公开(公告)日：2018-08-22
申请号：EP16794703.5
申请日：2016-10-13
申请人： Safran Nacelles
发明人： KERBLER, Olivier , GRALL, Loïc , GLEMAREC, Guillaume , GALASSO, Amadéo , FAUGERAS, José , SERISET, Mélody
CPC分类号： F02K99/00 , F02K1/1261 , F02K3/06 , F05D2220/323 , F05D2240/128 , Y02T50/671
摘要： The present invention relates to a variable cross-section nozzle (13) for an aircraft nacelle (1) having a longitudinal axis (X), the nozzle (13) comprising doors (P) movable between a smaller cross-section position and a larger cross-section position, and movement means (15) for moving each of the doors (P) between said positions, said movement means (5) comprising actuators (16) and control means of said actuators (16), the nozzle (13) being characterised in that each of the doors (P) comprises at least one first (21) and one second (22) guide means for guiding the movement of the doors (P) with respect to a fixed structure (14) of the nozzle (13), the second guide means (22) being located downstream with respect to the first guide means (22), the first and second guide means (21, 22) each being arranged to ensure, at least locally, a substantially curvilinear path.
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公开(公告)号：EP3247635B1
公开(公告)日：2018-05-16
申请号：EP16702757.2
申请日：2016-01-21
申请人： Safran Nacelles
发明人： BOILEAU, Patrick , KERBLER, Olivier , LEZERAC, Julien , GONZALEZ, Aurélien , GRALL, Loïc , TOUPET, Ludovic
CPC分类号： B64D27/18 , B64D27/26 , B64D29/02 , B64D29/06 , B64D2027/266 , B64D2027/268 , F02C7/20 , F02K1/72
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9.发明公开SYSTÈME POUR LA POSE ET LA DÉPOSE D'UN ENSEMBLE PROPULSIF SUR UN MÂT D'UN AÉRONEF 有权用于在飞机的桅杆上安装和拆卸推进式组件的系统
公开(公告)号：EP3247635A1
公开(公告)日：2017-11-29
申请号：EP16702757.2
申请日：2016-01-21
申请人： Safran Nacelles
发明人： BOILEAU, Patrick , KERBLER, Olivier , LEZERAC, Julien , GONZALEZ, Aurélien , GRALL, Loïc , TOUPET, Ludovic
CPC分类号： B64D27/18 , B64D27/26 , B64D29/02 , B64D29/06 , B64D2027/266 , B64D2027/268 , F02C7/20 , F02K1/72
摘要： The invention relates to a system (58) for mounting a propulsion assembly (10) onto a pylon (11) of an aircraft and dismounting same therefrom, said propulsion assembly (10) being of the type comprising a nacelle (12) and a turbojet, the turbojet being joined to the pylon (11) by means of at least one front suspension (24) and a rear suspension (26), characterised in that it comprises a carrier structure (34) which is designed to carry a thrust-reversal device, a front suspension (24) of the turbojet, which carries a front part of the carrier structure (34) and is detachably fixed to a front part of the pylon (11), and a rear suspension (26) of the turbojet, which carries a rear part of the carrier structure (34) and is detachably fixed to a rear part of the pylon (11). Said suspensions (24, 26) can be detached from the pylon (11) in order to dismount the propulsion assembly (10) mounted on the pylon (11).
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公开(公告)号：EP3247632A1
公开(公告)日：2017-11-29
申请号：EP16702579.0
申请日：2016-01-21
申请人： Safran Nacelles
CPC分类号： B64D29/06 , B64D27/16 , B64D33/04 , F02K1/72 , F05D2220/323 , Y02T50/672
摘要： The invention relates to an aircraft turbojet engine nacelle, the nacelle (1) comprising a rear section (4) with no lower fork, the rear section comprising a thrust reversal system, the thrust reversal system comprising a mobile cowl (20), the nacelle being characterized in that it comprises a guide system that translates as one with the mobile cowl (20), said guide system collaborating with at least one slide that is fixed in relation to the nacelle (1), the guide system and the slide being arranged near the position referred to as the 6 o'clock position.
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