公开(公告)号：US20170361939A1

公开(公告)日：2017-12-21

申请号：US15626698

申请日：2017-06-19

Applicant: Airbus Operations SAS

Inventor： Camil NEGULESCU ,  Jean-Michel ROGERO ,  Renaud FAURE

IPC: B64D27/14 ,  F02C7/04 ,  B64C1/16 ,  B64C5/02 ,  B64D33/02 ,  B64C1/00 ,  B64C21/02

CPC classification number: B64D27/14 ,  B64C1/16 ,  B64C5/02 ,  B64C21/02 ,  B64C39/04 ,  B64C2001/0045 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  B64D2033/0226 ,  F02C7/04 ,  Y02T50/44

Abstract: In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines.