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    Multifrequency absorption acoustic panel for an aircraft nacelle
    1.
    发明授权
    Multifrequency absorption acoustic panel for an aircraft nacelle 有权

    公开(公告)号：US11745887B2

    公开(公告)日：2023-09-05

    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 ,  G10K11/172 ,  G10K11/168

    CPC classification number: B64D33/02 ,  G10K11/168 ,  G10K11/172 ,  B64D2033/0206

    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.

    Assembly comprising two juxtaposed acoustic panels in which the panels comprise a resistive face which extends as far as an end wall
    3.
    发明授权
    Assembly comprising two juxtaposed acoustic panels in which the panels comprise a resistive face which extends as far as an end wall 有权

    公开(公告)号：US11066994B2

    公开(公告)日：2021-07-20

    申请号：US16586075

    申请日：2019-09-27

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

    Inventor： Alain Porte ,  Jacques Lalane ,  François Pons

    IPC: F02C7/045 ,  B64D33/02 ,  G10K11/16

    Abstract: An assembly including two juxtaposed acoustic panels. Resistive faces of the acoustic panels are in the continuation of one another. A first resistive face extends as far as the first end wall of a first panel. The first end wall is in contact with a second end wall of a second panel in the region of the first resistive face and of the second resistive face. A connecting piece is interposed between the first end wall and the second end wall over a part of the length thereof so that the connecting piece does not extend as far as the first and second resistive faces. That makes it possible to form an acoustic cladding that is continuous, exhibiting no non-acoustic zone or reduced-acoustic zone at the junction between the acoustic panels of which it is formed. A nacelle of an aircraft propulsion unit is one application.

    Air intake structure of an aircraft nacelle
    5.
    发明授权
    Air intake structure of an aircraft nacelle 有权

    公开(公告)号：US11427343B2

    公开(公告)日：2022-08-30

    申请号：US16560344

    申请日：2019-09-04

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

    Inventor： Alain Porte ,  Jacques Lalane ,  Florent Mercat

    IPC: B64D33/02 ,  B64D15/12 ,  B64D15/04 ,  F02C7/045 ,  F02C7/047 ,  B64D29/00

    Abstract: An air intake structure for an aircraft nacelle is disclosed. The air intake structure delimits a channel and includes a lip having a U-shaped cross section oriented towards the rear, a first sound-absorbing panel fixed behind the lip and delimiting the channel, and a second sound-absorbing panel fixed behind the first sound-absorbing panel and delimiting the channel. Each sound-absorbing panel includes a cellular core which is fixed between an inner skin pierced with holes and oriented towards the channel, and an outer skin oriented in the opposite direction, where the inner skin of the first sound-absorbing panel has a thickness greater than the thickness of the inner skin of the second sound-absorbing panel, and where each of the inner skins includes a heat source which is embedded in the mass of the inner skin.

    Sound attenuation panel for aircraft having a combination of acoustic attenuation properties
    6.
    发明授权
    Sound attenuation panel for aircraft having a combination of acoustic attenuation properties 有权

    公开(公告)号：US11459950B2

    公开(公告)日：2022-10-04

    申请号：US16379205

    申请日：2019-04-09

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

    Inventor： Alain Porte ,  Jacques Lalane ,  Arnulfo Carazo Mendez

    IPC: F02C7/045 ,  B64D33/02

    Abstract: Sound attenuation panel for aircraft having a combination of acoustic attenuation properties. The acoustic panel includes an acoustic structure having a cellular structure and a resistive skin and a backing skin, the acoustic panel also including at least one auxiliary acoustic device with cavities that is configured to produce additional acoustic absorption, the auxiliary acoustic device with cavities being attached to the acoustic structure and including adjacent chambers or cavities separated by shared walls, each of the chambers or cavities having perforations and being adapted to produce acoustic absorption. The combination of the acoustic structure and the auxiliary acoustic device with cavities enables combination of the acoustic absorption properties of these two types of element and an increased range of frequencies of the noise that can be attenuated by the acoustic panel without increasing its overall size.

    MULTIFREQUENCY ABSORPTION ACOUSTIC PANEL FOR AN AIRCRAFT NACELLE
    9.
    发明申请
    MULTIFREQUENCY ABSORPTION ACOUSTIC PANEL FOR AN AIRCRAFT NACELLE 有权

    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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