公开(公告)号：US20170321633A1

公开(公告)日：2017-11-09

申请号：US15654030

申请日：2017-07-19

Applicant: SAFRAN NACELLES

Inventor： Patrick BOILEAU ,  Olivier KERBLER ,  Julien LEZERAC ,  Armel GAUTIER ,  Loïc GRALL ,  Ludovic TOUPET

IPC: F02K1/72 ,  F01D25/24 ,  B64D27/16 ,  F02C7/20 ,  B64D29/06

CPC classification number: F02K1/72 ,  B64D27/16 ,  B64D27/26 ,  B64D29/06 ,  B64D2027/264 ,  F01D25/24 ,  F02C7/20 ,  F05D2220/323 ,  F05D2260/50

Abstract: The present disclosure provides a nacelle rear assembly for turbojet engine including at least one thrust reverser device to redirect air flow circulating from upstream to downstream in a flow path of the turbojet engine and a mast to link the nacelle to a structure of the aircraft. In one form, the nacelle extends longitudinally from forth to back along an axis and includes a cradle fastened on the mast. In one form, the cradle includes a first longeron and a second longeron extending longitudinally on either side of the mast. The first and second longeron each include a sliding guide device for sliding of a movable cowl and of a cascade of the thrust reverser device.

公开(公告)号：US20170313432A1

公开(公告)日：2017-11-02

申请号：US15653971

申请日：2017-07-19

Applicant: SAFRAN NACELLES

Inventor： Patrick BOILEAU ,  Olivier KERBLER ,  Julien LEZERAC ,  Aurélien GONZALEZ ,  Loïc GRALL ,  Ludovic TOUPET

IPC: B64D27/18 ,  B64D29/02 ,  B64D29/06 ,  B64D27/26

CPC classification number: B64D27/18 ,  B64D27/26 ,  B64D29/02 ,  B64D29/06 ,  B64D2027/266 ,  B64D2027/268 ,  F02C7/20 ,  F02K1/72

Abstract: The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon.