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公开(公告)号：US20160362167A1
公开(公告)日：2016-12-15
申请号：US15182672
申请日：2016-06-15
Applicant: Airbus Operations S.L. , Airbus Operations S.A.S.
Inventor： Javier Toral Vazquez , Esteban Martino Gonzalez , Diego Folch Cortes , Pablo Goya Abaurrea , Vasilis Votsios , Michel Fouinnetau , Sylvain Roumegas , Wolfgang Brochard
Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.
Abstract translation: 飞机后部机身内部有一个内部屏蔽罩，它具有由安装在其两侧的两个发动机构成的推进系统。 内部防护罩位于后机身内部的合适位置，用于覆盖可能影响对方发动机的关键元件的故障事件中与其中一个发动机分离的碎片的可能轨迹。 内部屏蔽件包括属于飞行器子系统的流体容器的集合体，特别是饮用水和废水子系统，具有足够的流体，用于提供停止碎片所需的能量吸收能力。 还公开了具有内部屏蔽的飞机。
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公开(公告)号：US20200002016A1
公开(公告)日：2020-01-02
申请号：US16440214
申请日：2019-06-13
Applicant: Airbus Operations S.A.S.
Inventor： Clément Breton , Julien Sentier , Frédéric Vinches , Alain Porte , Wolfgang Brochard
Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.
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公开(公告)号：US10464683B2
公开(公告)日：2019-11-05
申请号：US15458567
申请日：2017-03-14
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Wolfgang Brochard
Abstract: To reduce flexural deformations of an engine, an engine assembly comprises a device for attaching the engine onto a structure of an aircraft, the attachment device including a primary structure, an attachment device for attaching the engine onto the primary structure of the attachment pylon, and a nacelle including thrust reversal cowls, each equipped with an inner structure arranged around a case portion of the engine. The assembly includes flexible devices for transmitting forces, arranged between the case portion and the inner structures of the cowls, each device including an elastically deformable device configured so that in the closed position of the cowl, with the engine at a standstill, it adopts a partial elastic deformation state allowing the device to apply a prestress force on the case portion.
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公开(公告)号：US11511875B2
公开(公告)日：2022-11-29
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 , G10K11/168 , G10K11/172 , B32B3/30
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.
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公开(公告)号：US20210215122A1
公开(公告)日：2021-07-15
申请号：US17126109
申请日：2020-12-18
Applicant: Airbus Operations (S.A.S.)
Inventor： Wolfgang Brochard , Florent Mercat , Bastian Sabathier
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.
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Patent Agency Ranking
公开(公告)号：US10246196B2
公开(公告)日：2019-04-02
申请号：US15285211
申请日：2016-10-04
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Olivier Pautis , Wolfgang Brochard
Abstract: In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly.
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公开(公告)号：US11746705B2
公开(公告)日：2023-09-05
申请号：US16682271
申请日：2019-11-13
Applicant: Airbus Operations S.A.S.
Inventor： Wolfgang Brochard , Laurent Cazeaux , Claire Maffre
IPC: F02C7/24 , B64D29/00 , G10K11/168
CPC classification number: F02C7/24 , B64D29/00 , G10K11/168 , F05D2260/96
Abstract: A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.
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公开(公告)号：US11679889B2
公开(公告)日：2023-06-20
申请号：US16440214
申请日：2019-06-13
Applicant: Airbus Operations S.A.S.
Inventor： Clément Breton , Julien Sentier , Frédéric Vinches , Alain Porte , Wolfgang Brochard
CPC classification number: B64D29/06 , B64C7/02 , F01D25/243 , F05D2260/30
Abstract: A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.
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9.发明申请公开(公告)号：US20200165975A1
公开(公告)日：2020-05-28
申请号：US16682271
申请日：2019-11-13
Applicant: Airbus Operations S.A.S.
Inventor： Wolfgang Brochard , Laurent Cazeaux , Claire Maffre
IPC: F02C7/24 , B64D29/00 , G10K11/168
Abstract: A method for manufacturing an acoustic element of a sound absorption structure including at least one cylindrical, conical or truncated conical chamber obtained from a flat preform shaped and then assembled in order to obtain the cylindrical, conical or truncated conical shape of the chamber. This manufacturing method makes it possible to obtain an acoustic element that has thin walls and is made from a material suited to its environment. An acoustic element obtained using the manufacturing method, a sound absorption structure comprising at least one such acoustic element and an aircraft powerplant comprising at least one such structure are also described.
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公开(公告)号：US09868545B2
公开(公告)日：2018-01-16
申请号：US14573447
申请日：2014-12-17
Applicant: Airbus Operations (S.A.S.)
Inventor： Wolfgang Brochard , Sébastien Alby , David Ewens
CPC classification number: B64D45/00 , A62C2/065 , A62C3/08 , B64D27/26 , B64D2045/009 , F02C7/20 , F02C7/25 , F05D2300/702 , Y02T50/672
Abstract: A protective assembly and structural element for an aircraft comprising a portion of an attachment pylon primary structure is provided. 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, the thermally insulating layer being located between the layer forming a firewall and the attachment pylon primary structure portion. The protective assembly is attached to the pylon primary structure by fasteners axially arranged in pairs, one of each pair extending through the protective assembly and the other of each pair extending through the pylon primary structure.
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