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公开(公告)号：US11313251B2
公开(公告)日：2022-04-26
申请号：US16985413
申请日：2020-08-05
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Julien Sentier , Clément Breton
Abstract: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.
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公开(公告)号：US20210237890A1
公开(公告)日：2021-08-05
申请号：US17091604
申请日：2020-11-06
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Jacques Lalane , Arnaud Bourhis , Florent Mercat
IPC: B64D33/02 , B64D29/00 , G10K11/162
Abstract: An acoustic panel for an aircraft nacelle includes, from a central axis of the nacelle to the exterior thereof, a resistive skin perforated with sound-absorbing micro-perforations, a first attenuation stage, a septum perforated with holes, a second attenuation stage, and a back skin configured to provide the mechanical strength of the acoustic panel. The septum is a planar wall having a thickness greater than that of the resistive skin, preferably greater than 4 mm. Such a panel is configured to attenuate several frequency ranges one of which being a low-frequency range, while optimizing the weight, the cost and the air intake functions. The thickness of the septum, the dimensions of the holes in the septum, the OAR of the septum and the height of the second attenuation stage are adjusted to match the mean attenuated low frequency to the vibration frequency of the aircraft engine.
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23.发明授权公开(公告)号：US11027817B2
公开(公告)日：2021-06-08
申请号：US15961295
申请日：2018-04-24
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Jacques Lalane , Maud Lavieille
IPC: B64C1/40 , G10K11/168 , G10K11/172 , F02C7/045 , B64D33/02 , B32B3/26
Abstract: An acoustic treatment panel including a porous acoustically resistive structure which includes at least one external layer which is in contact with the external environment and which has through holes, internal strips including several openings which communicate with the inside of the cells of the panel and connecting canals, interposed between the external layer and the internal strips, which ensure that the floor-section openings communicate with at least one through hole of the external layer.
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公开(公告)号：US10676203B2
公开(公告)日：2020-06-09
申请号：US15834605
申请日：2017-12-07
Applicant: Airbus Operations S.A.S. , AIRBUS SAS
Inventor： Alain Porte , Patrick Oberle , Gregory Albet
Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment.
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Patent Agency Ranking
公开(公告)号：US20200070949A1
公开(公告)日：2020-03-05
申请号：US16555144
申请日：2019-08-29
Applicant: Airbus Operations S.A.S.
Inventor： Alain Porte , Jacques Lalane
Abstract: A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.
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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：US20180304987A1
公开(公告)日：2018-10-25
申请号：US15961316
申请日：2018-04-24
Applicant: Airbus Operations (S.A.S.)
Inventor： Alain Porte , Jacques Lalane , Maud Lavieille
IPC: B64C1/40 , G10K11/168 , G10K11/172
CPC classification number: B64C1/40 , B32B3/266 , B32B2307/102 , B32B2605/18 , B64D33/02 , B64D2033/0206 , F02C7/045 , F05D2260/963 , G10K11/168 , G10K11/172
Abstract: An acoustic treatment panel in which each cell includes a plurality of conduits which extend from the porous acoustically resistive structure to the reflective layer of the acoustic treatment panel, each conduit including at least one opening set away from the porous acoustically resistive structure and configured to cause the inside and the outside of the conduit to communicate.
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公开(公告)号：US20180170568A1
公开(公告)日：2018-06-21
申请号：US15834605
申请日：2017-12-07
Applicant: Airbus Operations S.A.S. , AIRBUS SAS
Inventor： Alain Porte , Patrick Oberle , Gregory Albet
Abstract: An air input structure includes an air input lip and a front reinforcement frame placed inside the air input lip. The front part of the air input lip has a plurality of segments distributed angularly along the leading edge of the air input lip, two adjacent segments being separated by an intermediate part having an excess thickness. Each segment has four edges, each having an excess thickness relative to the rest of the segment. Thus, the air input lip has a lighter structure.
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29.发明申请Panel for the acoustic treatment comprising hot air ducts and at least one annular channel 有权用于声学处理的面板包括热风管道和至少一个环形通道公开(公告)号：US20130224000A1
公开(公告)日：2013-08-29
申请号：US13573802
申请日：2012-10-03
Applicant: AIRBUS OPERATIONS (S.A.S.)
Inventor： Alain Porte , Frédéric Chelin , Grégory Albet
IPC: F01D25/24
CPC classification number: F01D25/24 , B64D15/04 , B64D33/02 , B64D2033/0206 , B64D2033/0233 , F02C7/045 , F02C7/24 , F05D2260/96 , Y02T50/672
Abstract: An aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip an annular channel wherein hot air circulates, as well as a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure, and a reflective layer, as well as ducts for channeling hot air with each one inlet communicating with the annular channel and one outlet communicating with the inner conduit, wherein the panel for acoustic treatment comprises, upstream from the ducts, an annular channel which extends over at least a portion of the nacelle circumference, at least one conduit providing communication between said annular channel and the upstream annular channel, and a plurality of ducts that open into said downstream annular channel, the panel for acoustic treatment being connected to the front frame in regard to the annular channel.
Abstract translation: 飞机机舱包括由形成进气口的内部管道延伸的唇缘，与所述唇缘限定热空气循环的环形通道的前框架，以及用于声学处理的面板，从外部向外包括声阻层， 至少一个蜂窝结构和反射层，以及用于引导热空气的管道，每个入口与环形通道连通，一个出口与内部导管连通，其中用于声学处理的面板包括在管道上游， 在所述机舱周边的至少一部分上延伸的环形通道，在所述环形通道和所述上游环形通道之间提供连通的至少一个导管以及通向所述下游环形通道的多个管道，用于声学处理的所述面板为 相对于环形通道连接到前框架。
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