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.