公开(公告)号：US20180216574A1

公开(公告)日：2018-08-02

申请号：US15883260

申请日：2018-01-30

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Eric HARAMBURU ,  Patrick OBERLE ,  Nicolas JOLIVET

IPC: F02K1/76 ,  F02K1/72

CPC classification number: F02K1/763 ,  B64D29/06 ,  F02K1/70 ,  F02K1/72

Abstract: A nacelle comprising a fixed cowl and a movable cowl movable in translation, a window delimited by the fixed cowl and the movable cowl, a reverser flap movable in rotation and a drive mechanism coordinating the movements of the reverser flap with those of the movable cowl. The drive mechanism comprises two bearings fixed to the nacelle, for each bearing, a lever arm with one end movable in rotation on the bearing and one end articulated on the reverser flap, for each lever arm, a rail comprising a straight portion and a curved portion, for each lever arm, a rod with one end articulated on the lever arm, and for each rail, a slider that is movable in translation on the rail and is articulated to one end of the rod.

公开(公告)号：US20180106216A1

公开(公告)日：2018-04-19

申请号：US15785012

申请日：2017-10-16

Applicant: Airbus Operations SAS ,  Airbus SAS

Inventor： Nicolas JOLIVET ,  Franck OUNDJIAN ,  Frédéric PIARD ,  Vincent BILLEROT ,  Benoit LETAY ,  Patrick OBERLE ,  Thomas SAUVALLE ,  Thierry SURPLY ,  Alain PORTE

IPC: F02K1/62 ,  F02K1/76

CPC classification number: F02K1/62 ,  B64D29/02 ,  F02K1/72 ,  F02K1/763 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2250/313 ,  F05D2260/53

Abstract: A nacelle for a ducted fan turbojet engine comprising an engine. The nacelle comprises a fixed cowl, an upstream wall bounding off, with the engine, a working section for a secondary flow, a movable cowl with an interior wall and an exterior wall, and movable in translation between a closing position where the exterior wall adjoins the fixed cowl and the interior wall prolongs the upstream wall, and an opening position where the exterior wall is distant from the fixed cowl so as to open a window and the interior wall is distant from the upstream wall, an inverter flap between the interior wall and the exterior wall mounted to be free in rotation about an axis of rotation situated on the interior wall and a drive mechanism for moving the movable cowl.

公开(公告)号：US20190242329A1

公开(公告)日：2019-08-08

申请号：US16253035

申请日：2019-01-21

Applicant: Airbus SAS

Inventor： Patrick OBERLE

IPC: F02K1/56 ,  F02K1/60 ,  F02K1/76 ,  B64D29/06

CPC classification number: F02K1/72 ,  F02K1/09 ,  F02K1/763 ,  F05D2260/50

Abstract: A nacelle for a dual-flow turbojet engine comprises a structure, a fixed cowl, a cowl translationally mobile on the structure, a window open between a secondary jet and the outside of the nacelle, and delimited by the fixed and mobile cowls, an outer thrust-reversing door rotationally mobile and a driving mechanism. The driving mechanism comprises a single power cylinder arranged at the level of a median plane and having a first end mounted articulated on the structure, a shaft with the second end of the power cylinder mounted articulated on the shaft, a first yoke joint secured to the outer thrust-reversing door and free to rotate on the shaft, and a second yoke joint secured to the mobile cowl, and where each of the two flanks of the second yoke joint has a groove in each of which the shaft is mounted to slide parallel to the median plane.