公开(公告)号：US20170096238A1

公开(公告)日：2017-04-06

申请号：US15280130

申请日：2016-09-29

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  Jean Michel Rogero

IPC: B64D45/00 ,  B64D29/02 ,  F01D19/00 ,  B64D27/18 ,  F01D25/24 ,  F02K3/06

CPC classification number: B64D45/00 ,  B64C7/02 ,  B64D27/18 ,  B64D29/02 ,  B64D2045/009 ,  F01D19/00 ,  F01D25/24 ,  F02C7/25 ,  F02K3/06 ,  F05D2220/323 ,  F05D2250/36 ,  F05D2250/71 ,  Y02T50/671

Abstract: A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.

公开(公告)号：US10017267B2

公开(公告)日：2018-07-10

申请号：US15231898

申请日：2016-08-09

Applicant: Airbus Operations (SAS)

Inventor： Olivier Pautis ,  Jean Michel Rogero

IPC: B64D27/26 ,  B64D27/12 ,  F01D25/28 ,  F02C7/20

CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D2027/264 ,  F01D25/28 ,  F02C7/20 ,  F05D2240/90 ,  Y02T50/44 ,  Y02T50/671

Abstract: An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.

公开(公告)号：US20170043878A1

公开(公告)日：2017-02-16

申请号：US15231898

申请日：2016-08-09

Applicant: Airbus Operations (SAS)

Inventor： Olivier Pautis ,  Jean Michel Rogero

IPC: B64D27/26 ,  B64D27/12

CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D2027/264 ,  F01D25/28 ,  F02C7/20 ,  F05D2240/90 ,  Y02T50/44 ,  Y02T50/671

Abstract: An engine assembly for an aircraft rigid structure comprising a mounting pylon comprising a central box and a box extension connected to a reducing gear case of the turboreactor. The box extension includes two parts bearing the front engine attachments, these pieces each comprising a structure forming a reinforcing rib of the central box, as well as two parts of horseshoe shape surrounding the reducing gear case.

Abstract translation: 一种用于飞机刚性结构的发动机组件，包括安装塔，其包括中央箱和连接到涡轮反应器的减速齿轮箱的箱延伸。 箱体延伸部分包括两个支承前部发动机附件的部件，这些部件各自包括形成中央箱的加强肋的结构，以及围绕减速齿轮箱的马蹄形的两个部分。