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1. 发明授权

EP2542470B1 DISPOSITIF DE COMMANDE DE L'ORIENTATION DES PALES DE SOUFFLANTE D'UN TURBOPROPULSEUR PAR CONTREPOIDS 有权转让
标题翻译：桨机构涡扇发动机平衡式来实现的羽毛
公开(公告)号：EP2542470B1
公开(公告)日：2016-08-17
申请号：EP11712605.2
申请日：2011-02-18
申请人： Snecma
发明人： GALLET, François
IPC分类号： B64C11/30 , B64C11/32 , F02K3/04 , F04D29/36 , F01D7/00
CPC分类号： F04D29/323 , B64C11/325 , B64C11/48 , B64D2027/005 , B64D2027/026 , F01D7/00 , F02C6/206 , F05D2220/325 , Y02T50/66 , Y02T50/671 , Y10T74/18784

2. 发明公开

EP2619417A1 DISPOSITIF D'ETANCHEITE A FOURREAU POUR LA TRAVERSEE DE CLOISON PAR UNE BIELLETTE D'UN SYSTEME DE COMMANDE DE L'ORIENTATION DES PALES DE SOUFFLANTE D'UN TURBOPROPULSEUR. 有权转让
标题翻译： DISPOSITIF D'ETANCHEITE A FOURREAU POUR LA TRAVERSEE DE CLOISON PAR UNE BIELLETTE D'UN SYSTEME DE COMMANDE DE L'ORIENTATION DES PALES DE SOUFFLANTE D'UN TURBOPROPULSEUR。
公开(公告)号：EP2619417A1
公开(公告)日：2013-07-31
申请号：EP11773064.8
申请日：2011-09-12
申请人： Snecma
发明人： GALLET, François
IPC分类号： F01D1/26 , F01D7/00 , F01D25/16 , F02C7/06 , F02C7/28 , F02K3/072 , F16J3/04 , F16J15/06 , F16J15/52 , F16J15/56 , F01D25/18
CPC分类号： F02C7/28 , B64C11/308 , B64D2027/005 , F01D7/00 , F01D25/16 , F01D25/183 , F02C7/06 , F02K3/072 , F05D2220/324 , F05D2220/325 , F05D2240/55 , F05D2260/50 , F05D2260/79 , F16J3/047 , F16J15/52 , Y02T50/66 , Y02T50/671
摘要： The invention relates to a sealing device having a sleeve for the passage of a connecting rod of a system for controlling the orientation of the blower blades of a turboprop engine through a partition. The device includes a tube (60) to be attached onto the partition (58) to be sealed, and a frusto-conical sleeve (62) through which the connecting rod (50a) is to pass, wherein the sleeve is axially slidable inside the tube, and the sleeve has, at the larger end thereof, sealing means providing a seal with the tube, and, at the narrower end thereof, sealed-attachment means at a corresponding end of the connecting rod.
摘要翻译：密封装置技术领域本发明涉及一种密封装置，该密封装置具有用于控制涡轮螺旋桨发动机的鼓风机叶片通过隔板的定向的系统的连杆通过的套筒。该装置包括待附接到待密封的隔离物（58）上的管（60）和连接杆（50a）将穿过的截头圆锥形套筒（62），其中套筒可在并且套筒在其较大的端部处具有密封装置，该密封装置为管提供密封，并且在其较窄的端部处在连接杆的对应端部处具有密封附接装置。

3. 发明授权

EP2368030B1 SYSTÈME D'HÉLICES CONTRAROTATIVES ENTRAINÉES PAR UN TRAIN ÉPICYCLOÏDAL OFFRANT UNE RÉPARTITION DE COUPLE ÉQUILIBRÉE ENTRE LES DEUX HÉLICES 有权转让
标题翻译：与保障之间的两个螺旋桨平衡扭矩分配的行星率相对螺旋桨SUB驱动系统
公开(公告)号：EP2368030B1
公开(公告)日：2013-03-13
申请号：EP09774910.5
申请日：2009-12-17
申请人： Snecma
发明人： BALK, Wouter , CHARIER, Gilles, Alain , GALLET, François
IPC分类号： B64C11/48 , F02C7/36 , F02K3/072 , F02C3/067
CPC分类号： F02K3/072 , B64C11/48 , F02C3/067 , F02C7/36 , F05D2260/40311 , F05D2260/96 , Y02T50/66 , Y02T50/671

4. 发明公开

EP2435304A2 DISPOSITIF POUR LA COMMANDE DE L'ORIENTATION DES PALES DE SOUFFLANTE D'UN TURBOPROPULSEUR 有权转让
标题翻译： DEVICE FOR A涡扇发动机球迷的表调整
公开(公告)号：EP2435304A2
公开(公告)日：2012-04-04
申请号：EP10723696.0
申请日：2010-04-19
申请人： Snecma
发明人： BALK, Wouter , CHARIER, Gilles, Alain , GALLET, François
IPC分类号： B64C11/30 , B64C11/34 , F01D7/00 , F02K3/02 , F04D29/36
CPC分类号： B64C11/32 , B64C11/308 , B64C11/48 , B64D2027/005 , B64D2027/026 , F01D7/00 , F02K1/66 , F02K3/02 , Y02T50/66 , Y02T50/671 , Y02T50/673
摘要： The invention relates to a device for controlling the orientation of the blades of a turboprop fan, comprising at least one set (24a) of fan blades (26) of adjustable orientation coupled in rotation to a rotary ring (28a) connected mechanically to a turbine rotor, each blade of the set being coupled, for adjustment of its orientation, to a synchronizer ring (30a). The device also includes a rolling-contact bearing (54a) having an internal cage (56a) which slides on a turbine casing and which is connected to the rod (44) of an actuator (38), and an external cage (52a) that is connected mechanically to the synchronizer ring by means of a plurality of connecting arms (40a) connected to the actuator rod and hinged to the synchronizer ring in such a way that an actuation of the actuator causes a rotational movement of the synchronizer ring about the longitudinal axis.

5. 发明公开

EP2401197A1 DISPOSITIF A HÉLICES CONTRAROTATIVES AYANT UN MOYEN DE CHANGEMENT DE PAS DES HÉLICES 有权转让
标题翻译：随着对片材的手段OPPOSITE螺旋桨设置的推进器
公开(公告)号：EP2401197A1
公开(公告)日：2012-01-04
申请号：EP10706211.9
申请日：2010-02-25
申请人： Snecma
发明人： BALK, Wouter , GALLET, François
IPC分类号： B64C11/30 , B63H3/06 , B63H3/08 , B63H5/10 , B64C11/48 , B64D35/06
CPC分类号： B63H5/10 , B63H3/06 , B63H3/082 , B64C11/306 , B64C11/48 , B64D35/06 , B64D2027/005 , F01D7/00 , F05D2220/324 , Y02T50/66
摘要： The device according to the invention includes a pair of counter-rotating propellers suitable for being modified by an actuator (31) located in a central recess of the shafts. The system for transporting energy to the actuator (31) includes a conduit (34) entering a static casing (5) in the proximity of a planetary gear train (17), as well as control ducts (38) leading to the actuator (31) and passing through the planet carrier (14) of a planetary gear train (17). The junction is provided by a dynamic seal with a manifold. Said path avoids the high-temperature turbine.

6. 发明公开

EP2304191A1 SYSTEME SIMPLIFIE DE COMMANDE DE CALAGE D'UNE PALE D'HELICE D'UN TURBOMOTEUR POUR AERONEF 有权转让
标题翻译：简化的控制系统，用于飞机发动机气动螺丝LEAF调整
公开(公告)号：EP2304191A1
公开(公告)日：2011-04-06
申请号：EP09753872.2
申请日：2009-05-26
申请人： Snecma
发明人： GALLET, François
IPC分类号： F01D7/00 , F04D29/32
CPC分类号： F01D7/00 , F04D29/323 , F04D29/364 , F05D2260/4023 , F05D2260/50 , F05D2260/79 , Y02T50/671 , Y02T50/673
摘要： A system for controlling pitch of a propeller blade of a turboshank engine, including two automatic locking members making it possible, depending on their controlled position, to lock rotation of a blade root in both directions of rotation, or to allow the rotation of the blade root support in either of the two directions.

7. 发明公开

EP2260197A1 SYSTEME D'HELICES CONTRAROTATIVES DISPOSANT D'UN DISPOSITIF DE MISE EN DRAPEAU DES PALES D'HELICES 有权转让
标题翻译：反向旋转的螺旋推进器系统使用设备螺旋桨叶片的空位置
公开(公告)号：EP2260197A1
公开(公告)日：2010-12-15
申请号：EP09723401.7
申请日：2009-03-20
申请人： Snecma
发明人： GALLET, François
IPC分类号： F02K3/072 , B64C11/30 , F02C3/067 , F02C7/36
CPC分类号： F02K3/072 , F02C7/36
摘要： The invention relates to a contra-rotating propeller system (1) for the turbine engine of an aircraft that comprises first and second propellers (6, 8) each including a control system (26, 56) for setting the blades, the latter including rotary actuation means (38, 68) for sliding a member (28, 58) in order to move the blades at an attack angle. According to the invention, the system also includes a declutchable means (72) for connecting in rotation the rotary actuation means (38, 68), wherein the system is designed so that, when said means (72) is clutched, a relative rotation speed is generated between the members (28, 58) and their associated rotary actuation means (38, 68), thereby moving the blades (6a, 6b) into a neutral feathering position.

8. 发明公开

EP2864594A1 SOUFFLANTE A CALAGE VARIABLE PAR ROTATION DIFFERENTIELLE DES DISQUES DE SOUFFLANTE 有权转让
标题翻译： LÜFTERMIT VARIABLER EINSTELLUNG MITTELS差速器旋转DERLÜFTERPLATTEN
公开(公告)号：EP2864594A1
公开(公告)日：2015-04-29
申请号：EP13744617.5
申请日：2013-06-24
申请人： Snecma
发明人： GALLET, François
IPC分类号： F01D7/00 , F04D29/36 , B64C11/06
CPC分类号： F01D9/041 , F01D7/00 , F01D17/12 , F04D29/323 , F05D2220/36 , F05D2260/74 , F05D2260/79 , Y02T50/671 , Y02T50/673
摘要： The invention relates to a compressor rotor for a turbomachine comprising a shaft (12) and at least two disks (10a, 10b) mounted on said shaft in order to hold a single set of vanes (2) that are rotatably mobile about the rotational axis of said shaft, at least one first disk (10a) being mounted in a mobile manner on said shaft in such a way as to be able to generate an angular gap in relation to said second disk (10b) and to trigger a rotation of the vanes (2) about the radial axis of same, at least one of the two disks being shaped in such a way as to receive at least one means for attaching the vanes (11), the connection between said disk and said means enabling a rotation of said means about a radial axis, characterised in that said connection is a ball-jointed connection that is tangentially and axially mobile.
摘要翻译：一种用于涡轮机的压缩机转子，包括轴和安装在轴上的至少两个盘，用于保持围绕轴的旋转轴线可旋转移动的单组叶片，至少一个第一盘以可移动的方式安装在轴能够相对于第二盘产生角度间隙并且触发叶片绕其径向轴的旋转，两个盘中的至少一个被成形为容纳至少一个用于附接叶片的机构，盘和附接机构之间的连接使得附接机构能够围绕径向轴线旋转，并且连接是切向和轴向移动的球接头连接。

9. 发明公开

EP2742229A1 DISPOSITIF D'INVERSION DE POUSSEE POUR TUYERE COMPACTE 有权转让
标题翻译：推力反向器对于紧凑型枪
公开(公告)号：EP2742229A1
公开(公告)日：2014-06-18
申请号：EP12758553.7
申请日：2012-08-08
申请人： Snecma
发明人： GALLET, François
IPC分类号： F02K1/72
CPC分类号： F02K1/70 , F02K1/72
摘要： The present invention relates to a bypass turbojet engine nacelle (10) that forms the fan casing comprising a first, upstream, streamlining element (12) and a second streamlining element (13) that forms the jet pipe, the second element having the ability to move translationally between a position in which it ensures the aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings, a thrust reverser device being housed in the nacelle and comprising flow reverser flaps (17) and cascades of vanes (15) providing radial guidance for the flow. The nacelle is characterized in that the cascades of vanes (15) providing radial guidance for the flow are capable of translational movement along the axis of the nacelle between a position in which they are retracted into the first steamlining element (12) and an active flow-guidance position, the second fan streamlining element (13) being secured to said guide cascades of vanes (15) the reverser flaps (17) being mounted with the ability to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes (15).

10. 发明公开

EP2582959A1 CARTER DE SOUFFLANTE DE TURBOREACTEUR D'AERONEF 审中-公开
标题翻译：风扇罩FOR A平面TURBOJETMOTOR
公开(公告)号：EP2582959A1
公开(公告)日：2013-04-24
申请号：EP11735897.8
申请日：2011-06-16
申请人： Aircelle , Snecma
发明人： BALK, Wouter , GALLET, François , DEZEUSTRE, Nicolas , KERBLER, Olivier
IPC分类号： F02K3/06 , B64D33/02
CPC分类号： F02K3/06 , B64D33/02 , F01D21/045 , F05D2240/14 , F05D2300/433 , F05D2300/603 , Y02T50/672
摘要： Aircraft turbo jet engine fan casing, notable in that it is in the form of a box section (6), the radially interior wall (6a) of which is able to form the internal skin of the cold air flow duct (17) of a nacelle in which said turbo jet engine is intended to be mounted, and the radially exterior wall (6b) of which is able to form the external skin of said nacelle.

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