公开(公告)号：US11208193B2

公开(公告)日：2021-12-28

申请号：US16201035

申请日：2018-11-27

Applicant: AIRBUS OPERATIONS SAS

Inventor： Florian Ravise ,  Wolfgang Brochard

IPC: B64C1/40 ,  F02C7/045 ,  G10K11/168

Abstract: An acoustic panel (1) includes a plate (2) made of an acoustic absorbing material (3), as well as a resistive skin (4) and a backing skin (6) arranged respectively on both sides of the plate (2), the acoustic panel (1) including acoustic elements (8) able to carry out an acoustic absorption, each of them being arranged in a housing (7) provided in the plate (2) with an opening (9) in front of the resistive skin (4). The combination of the plate (2) and the acoustic elements (8) allows to combine the sound attenuation properties of these two types of elements and to increase the frequency range of sounds that can be attenuated by the acoustic panel (1), without increasing the dimension.

公开(公告)号：US09238510B2

公开(公告)日：2016-01-19

申请号：US14140512

申请日：2013-12-25

Applicant: Airbus Operations (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: B64C27/26 ,  B64D27/26 ,  B64D27/00

CPC classification number: B64D27/26 ,  B64D27/00 ,  B64D2027/266

Abstract: A boomerang link for aircraft engine mounts, including a first orifice and a second orifice both designed to connect the boomerang link to an aircraft pylon, and a third orifice designed to connect the boomerang link to an aircraft engine. The third orifice is offset relative to a plane passing simultaneously through an axis of the first orifice and through an axis of the second orifice. When the boomerang link is seen in section in any plane orthogonal to the axes, a straight line segment extending from the axis of the second orifice to an axis of the third orifice crosses a region external to the boomerang link. This conformation confers on the boomerang link a flexibility enabling it to filter transverse vibrations between an engine and an aircraft pylon.

Abstract translation: 用于飞行器发动机支架的回旋式离合器连接件，包括设计成将回旋臂连杆连接到飞机塔架的第一孔口和第二孔口以及用于将飞旋镖杆连接到飞机发动机的第三孔。 第三孔相对于同时穿过第一孔的轴线并穿过第二孔的轴线的平面偏移。 当在与轴正交的任何平面中的截面中看到飞旋镖连杆时，从第二孔的轴线延伸到第三孔的轴线的直线段穿过回旋形连杆的外部区域。 这种构想赋予了回旋镖连杆的灵活性，使其能够过滤发动机和飞机塔架之间的横向振动。

公开(公告)号：US20140064950A1

公开(公告)日：2014-03-06

申请号：US14016296

申请日：2013-09-03

Applicant: AIRBUS OPERATIONS (SAS)

Inventor： Wolfgang Brochard ,  Romain Terral

IPC: F01D25/24

CPC classification number: F01D25/24 ,  B64D27/20 ,  B64D27/26 ,  B64D29/06 ,  Y02T50/44

Abstract: A propulsion unit for an aircraft, comprising one turbine engine and a mounting device for a turbine engine designed to be added laterally on an aircraft structure and comprising a rigid mounting structure. The rigid mounting structure supports at least one arch which is concave towards the longitudinal axis of the propulsion unit and which has a distal end at an angular distance of between 45 and 120 degrees from a vertical plane passing through the axis, on the other side of the structure, and supporting a distal connecting element connecting the turbine engine to the arch.

Abstract translation: 一种用于飞机的推进单元，包括一个涡轮发动机和用于涡轮发动机的安装装置，该涡轮发动机设计成横向地添加在飞行器结构上并且包括刚性安装结构。 刚性安装结构支撑至少一个拱形件，该拱形件朝向推进单元的纵向轴线是凹形的，并且具有与通过轴线的垂直平面成45度到120度之间的角距离的远端，在另一侧 并且支撑将涡轮发动机连接到拱顶的远端连接元件。