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1. 发明公开

EP2828490A1 TUYÈRE À SECTION VARIABLE ET NACELLE POUR TURBORÉACTEUR D'AÉRONEF ÉQUIPÉE D'UNE TELLE TUYÈRE 审中-公开
标题翻译：兰斯有变截面和飞机涡轮喷气发动机GONDOLA这样的枪
公开(公告)号：EP2828490A1
公开(公告)日：2015-01-28
申请号：EP13719903.0
申请日：2013-03-19
申请人： Aircelle
发明人： HURLIN, Hervé , MAALIOUNE, Hakim , KERBLER, Olivier
IPC分类号： F01D17/14 , F02K1/08 , F02K1/15
摘要： Variable-section jet pipe (3) for aircraft nacelle (1), of which at least one part (V1, V2, V3; B) is able to move between at least one position of smaller cross section and at least one position of larger cross section, and means for moving said part between said positions, these movement means firstly comprising piezoelectric actuators (P, Pa
1 , P2), and secondly comprising means of controlling these actuators.

2. 发明公开

EP2877732A1 DISPOSITIF D'ENTRAINEMENT DE VOLETS NOTAMMENT POUR TUYÈRE ADAPTATIVE 审中-公开
标题翻译：襟翼控制装置，特别是对于适配喷嘴
公开(公告)号：EP2877732A1
公开(公告)日：2015-06-03
申请号：EP13756587.5
申请日：2013-07-23
申请人： Aircelle
发明人： KERBLER, Olivier , GILO, Olivier , CARUEL, Pierre
IPC分类号： F02K1/12 , F02K1/76
CPC分类号： F02K1/763 , B64D33/04 , F02K1/12 , F02K1/1207 , F02K1/70 , F02K1/76 , F05D2260/50
摘要： The invention relates to a flap-driving device for the nozzle of a turbojet nacelle, said nozzle comprising at least one rotatably movable flap, said device comprising at least one control ring (311) that is rotatably movable along the circumference of said nacelle during the activation of driving means (39, 41), and comprising at least one flap-driving connecting rod (2) connected to said control ring and to a flap, the activation of said means for driving the control ring (311) triggering a movement of said connecting rods (21) in translation. The device according to the invention is characterised in that the means for driving the control ring (311) comprise at least one longitudinal driving cylinder comprising at least one pin (39) connected to at least one lever-forming assembly (41, 71), said assembly being directly or indirectly secured to said ring.

3. 发明公开

EP2819921A1 NACELLE DE TURBOMOTEUR ÉQUIPÉ D'UN ÉCHANGEUR DE CHALEUR 有权转让
标题翻译：有热交换器涡轮发动机GONDOLA
公开(公告)号：EP2819921A1
公开(公告)日：2015-01-07
申请号：EP13708203.8
申请日：2013-02-13
申请人： Aircelle
发明人： CARUEL, Pierre , ZAGANELLI, Franck , GONIDEC, Patrick , KERBLER, Olivier
IPC分类号： B64D33/10 , B64D15/02 , B64D15/04 , B64D15/06 , F02C7/047 , F02C7/12
CPC分类号： F01D25/24 , B64D15/04 , B64D33/02 , B64D33/10 , B64D2033/0233 , F02C7/047 , F02C7/12 , F02K3/06 , F05D2240/14 , F05D2260/213 , Y02T50/676
摘要： The present invention relates to a nacelle (1) of a turbine engine (2) comprising at least one external cowling (3) defining an external aerodynamic surface and at least one internal cowling (4) defining an internal aerodynamic flow surface, these surfaces being connected upstream by a leading edge wall which forms an air inlet lip (6), said turbine engine nacelle comprising at least one heat exchanger (10) associated with at least one flow duct (13) forming at least one recirculation loop through the exchanger and comprising at least one circulation zone (13a) extending at least partially along the external cowling in contact with at least one wall of said external cowling so as to allow exchange of heat by conduction with the air outside the nacelle.

4. 发明公开

EP2817502A1 INVERSEUR DE POUSSÉE À GRILLES PIVOTANTES 审中-公开
标题翻译：与酒吧旋转推力反向器
公开(公告)号：EP2817502A1
公开(公告)日：2014-12-31
申请号：EP13708202.0
申请日：2013-02-13
申请人： Aircelle
发明人： GONIDEC, Patrick , BLIN, Laurent, Albert , KERBLER, Olivier
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , Y02T50/671
摘要： This grid thrust reverser (23) for an aircraft turbojet engine comprises a front frame (1), a sliding cover (3) which slides between a direct jet position and a reverse jet position, a plurality of actuating cylinders (13) interposed between said front frame (1) and said sliding cover (3), and a plurality of grilles (23) mounted pivotably on the front frame (1) between a direct jet position, wherein said grilles (23) are substantially parallel to the axis (A) of the thrust reverser, and a reverse jet position, wherein said grilles are inclined relative to the axis (A) of the thrust reverser, characterised in that it comprises a single radial layer of grilles (23).

5. 发明公开

EP2766259A1 ENSEMBLE ARRIÈRE DE NACELLE POUR TURBORÉACTEUR 审中-公开
标题翻译：发动机的FOR缆车涡轮喷气发动机HEDGE安排
公开(公告)号：EP2766259A1
公开(公告)日：2014-08-20
申请号：EP12767045.3
申请日：2012-09-07
申请人： Aircelle
发明人： HURLIN, Hervé , DEZEUSTRE, Nicolas , KERBLER, Olivier
IPC分类号： B64D29/06 , F02K1/72 , B64D29/08
CPC分类号： F02C7/20 , B64D29/06 , B64D29/08 , F02K1/72
摘要： The invention relates to a rear nacelle assembly for a turbojet engine comprising at least: an internal structure (23), intended to encircle a downstream part of the turbojet engine, wherein said internal structure (23) is rotationally movable between an operative position, in which said internal structure forms the downstream fairing of the turbojet engine and defines an annular jet (7) of cold air with a cowl (31), and a maintenance position, in which said internal structure is separated from the downstream part of the turbojet engine, said thrust reverse cowl (31), concentric with said internal structure (23), said cowl (31) sliding between an open position exposing airflow deflection vanes (32) and a closed position covering said airflow deflection vanes (32), and wherein said cowl is rotationally movable between an operative position in which it defines the annular jet (7) of cold air with said internal structure and a maintenance position in which it is separated from the downstream part of the turbojet engine, a suspension pylon (10) on which said cowl (31) and said internal structure (23) are mounted, the assembly being characterized in that the cowl (31) is mounted on the pylon (10) by a pivot connection sliding about a main axis, and the internal structure (23) is mounted on the pylon (10) by a pivot connection around said main axis.

6. 发明公开

EP2635788A1 DiSPOSITIF D'INVERSION DE POUSSÉE SANS BIELLE DANS LA VEINE 有权
标题翻译：反向推力设备，而无需控制杆电源
公开(公告)号：EP2635788A1
公开(公告)日：2013-09-11
申请号：EP11785745.8
申请日：2011-10-25
申请人： Aircelle
发明人： HURLIN, Hervé , KERBLER, Olivier , DEZEUSTRE, Nicolas , LE BOULICAUT, Loïc
IPC分类号： F02K1/72
CPC分类号： F02K1/72 , F02K1/566 , F02K1/70 , Y02T50/671
摘要： The present invention relates to a jet engine nacelle (1) provided with at least one thrust reverser device which includes a deflection means (41) and at least one cowl (30) translatable in a direction substantially parallel to a longitudinal axis of the nacelle between a closed position, in which said cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means, and an open position, in which said cowl opens a passage into the nacelle and uncovers the deflection means, the thrust reverser device moreover including at least one blocking flap (60) pivotably mounted by at least one end attached to a rear portion of the deflection means, wherein said jet engine nacelle is characterized in that the pivoting end is also translatably connected to the rear portion of the deflection means.

7. 发明公开

EP3030774A1 DISPOSITIF D'INVERSION DE POUSSÉE INTÉGRÉ ET NACELLE DE MOTEUR D'AÉRONEF AINSI ÉQUIPÉE 有权转让
标题翻译： FLUGZEUGTRIEBWERKSGONDEL DAMIT INTEGRIERTE SCHUBUMKEHRRORRICHTUNG
公开(公告)号：EP3030774A1
公开(公告)日：2016-06-15
申请号：EP14759034.3
申请日：2014-08-01
申请人： Aircelle
发明人： GUERIN, Philipe , KERBLER, Olivier , RAMI, Jean-Paul
IPC分类号： F02K1/72 , F02K1/09 , F02K3/06 , F02K1/76
CPC分类号： F02K1/72 , F02K1/09 , F02K1/62 , F02K1/625 , F02K1/70 , F02K1/76 , F02K1/763 , F02K1/766 , F02K3/06
摘要： The thrust reverser device is integrated in an aircraft engine nacelle. Blocking flaps (18) are stored inside a mobile cowl (10, 21) disposed in a downstream section of the nacelle, under deflection cascade assemblies (15) during direct-jet operation of the nacelle. Means are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: -the mobile cowl (10, 21) moves in translation towards the downstream end of the nacelle; -each flap (18) is then deployed in the main airflow path (46).
摘要翻译：本公开提供了集成在飞机机舱中的推力反向装置。在机舱的直接喷射操作期间，阻挡翼片存储在设置在机舱的下游部分中的移动导流罩内，在偏转级联组件下。提供了用于执行从直接喷射操作到反向喷射操作的两个阶段的通道的各种装置：移动整流罩朝向机舱的下游端移动; 然后将每个翼片部署在主空气流动路径中。

8. 发明公开

EP2655191A1 STRUCTURE INTERNE POUR UNE NACELLE D'UN AÉRONEF 审中-公开
标题翻译：一种平面GONDEL内部结构
公开(公告)号：EP2655191A1
公开(公告)日：2013-10-30
申请号：EP11799798.1
申请日：2011-11-30
申请人： Aircelle
发明人： HURLIN, Hervé , KERBLER, Olivier , GILO, Olivier
IPC分类号： B64D33/04 , F02K1/08
CPC分类号： F02C7/20 , F02K1/085 , Y02T50/672
摘要： The invention relates to an inner structure (8) for a nacelle (1) for a aircraft turbofan including a plurality of active (103) and passive (101) movable elements. Each active movable element (103) consists of one or more movable portions (103a, 103b), and each active movable element (103) is configured so as to drive the adjacent passive movable elements (101) such that the inner structure (103) has a nominal first position, a second position in which the active movable elements (103) project beyond by the passive movable elements (101) toward the outside of the inner structure (8), and a third position in which the active movable elements (103) project beyond the passive movable elements (101) toward the inside of the inner structure (8). The invention also relates to a nacelle comprising an outer structure and such an inner structure.

9. 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.

10. 发明授权

EP2870349B1 MÉCANISME D'ACCOUPLEMENT ET DE DÉSACCOUPLEMENT POUR UN DISPOSITIF EMBARQUÉ D'UNE NACELLE DE TURBORÉACTEUR 有权
标题翻译：离合机构FOR A喷射涡轮GONDEL
公开(公告)号：EP2870349B1
公开(公告)日：2016-05-04
申请号：EP13744672.0
申请日：2013-07-02
申请人： Aircelle
发明人： HURLIN, Hervé , GILO, Olivier , KERBLER, Olivier
IPC分类号： F16D11/00 , F02K1/76 , F16D11/10 , F16D11/14
CPC分类号： F02K1/763 , F02K1/766 , F05D2250/41 , F05D2260/4031 , F16D11/10 , F16D11/14 , F16D2011/006

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