公开(公告)号：US12104557B2

公开(公告)日：2024-10-01

申请号：US17126109

申请日：2020-12-18

Applicant: Airbus Operations (S.A.S.)

Inventor： Wolfgang Brochard ,  Florent Mercat ,  Bastian Sabathier

IPC: F02K1/82 ,  F02K1/04

CPC classification number: F02K1/827 ,  F02K1/04 ,  F05D2260/963

Abstract: An output cone of an aircraft propulsive assembly extending in a general direction called longitudinal direction and including a front part and a rear part. The longitudinal assembly of the front part and rear part forms an acoustic treatment system with at least two degrees of freedom. Such a system allows for the treatment of several frequency ranges or of one wide frequency range by the treatment of several overlapping ranges.

公开(公告)号：US20200164997A1

公开(公告)日：2020-05-28

申请号：US16682252

申请日：2019-11-13

Applicant: Airbus Operations S.A.S.

Inventor： Wolfgang Brochard ,  Laurent Cazeaux ,  Claire Maffre

IPC: B64D33/02 ,  G10K11/172 ,  G10K11/168

Abstract: An acoustic absorption structure includes: at least one acoustic element which has at least one cavity delimited by at least one enclosure comprising at least one first drainage orifice passing through the enclosure, and a rotational indexing system making it possible to position the acoustic element so that at least one first drainage orifice is positioned in proximity to or at a lowest point of the cavity. An aircraft propulsion assembly including such an acoustic absorption structure is also described.

公开(公告)号：US09889942B2

公开(公告)日：2018-02-13

申请号：US15015841

申请日：2016-02-04

Applicant: AIRBUS OPERATIONS (S.A.S.)

Inventor： Olivier Pautis ,  Wolfgang Brochard

IPC: B64D27/12 ,  B64C3/18 ,  B64D27/26 ,  B64F5/10

CPC classification number: B64D27/12 ,  B64C3/187 ,  B64D27/26 ,  B64F5/10

Abstract: In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.

公开(公告)号：US20150175272A1

公开(公告)日：2015-06-25

申请号：US14573447

申请日：2014-12-17

Applicant: Airbus Operations (S.A.S.)

Inventor： Wolfgang Brochard ,  Sébastien Alby ,  David Ewens

IPC: B64D45/00 ,  B64D27/26

CPC classification number: B64D45/00 ,  A62C2/065 ,  A62C3/08 ,  B64D27/26 ,  B64D2045/009 ,  F02C7/20 ,  F02C7/25 ,  F05D2300/702 ,  Y02T50/672

Abstract: The disclosure herein relates to a structural element for an aircraft comprising a portion of an attachment pylon primary structure. According to the disclosure herein, the attachment pylon primary structure portion is at least partially covered by a protective assembly comprising a layer forming a firewall and a thermally insulating layer, thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion.

Abstract translation: 本文的公开内容涉及用于飞行器的结构元件，其包括附接塔一级结构的一部分。 根据本文的公开内容，附接塔主结构部分至少部分地被包括形成防火墙的层和绝热层的保护组件覆盖，隔热层位于形成防火墙的层与附接塔一级结构之间 一部分。