EP1355294A1 - Schallwiderstandsfähige Mehrkomponentenschicht für eine schalldämpfende Platte und Platte unter Verwendung einer solchen Schicht - Google Patents

Schallwiderstandsfähige Mehrkomponentenschicht für eine schalldämpfende Platte und Platte unter Verwendung einer solchen Schicht Download PDF

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Publication number
EP1355294A1
EP1355294A1 EP03362003A EP03362003A EP1355294A1 EP 1355294 A1 EP1355294 A1 EP 1355294A1 EP 03362003 A EP03362003 A EP 03362003A EP 03362003 A EP03362003 A EP 03362003A EP 1355294 A1 EP1355294 A1 EP 1355294A1
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EP
European Patent Office
Prior art keywords
component
structural component
layer
layer according
fibers
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Granted
Application number
EP03362003A
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English (en)
French (fr)
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EP1355294B1 (de
Inventor
Robert André
Michel Buge
Alain Porte
Eric Rambaud
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Airbus Operations SAS
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Airbus Operations SAS
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Publication of EP1355294A1 publication Critical patent/EP1355294A1/de
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    • G—PHYSICS
    • G10—MUSICAL INSTRUMENTS; ACOUSTICS
    • G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
    • G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
    • G10K11/172—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects

Definitions

  • the present invention relates to an acoustically resistive layer consisting of a plurality of superimposed and linked components and intended for constitute one of the elements of an acoustic attenuation panel, including a panel intended to be mounted in the walls of nacelles aircraft turbojets.
  • this type of panel incorporates an alveolar core, such that a honeycomb structure flanked, incident sound wave side, of a acoustic damping layer and, on the opposite side, a reflector back.
  • the acoustic damping layer is a porous structure with a role dissipative, that is to say, partially transforming the acoustic energy of the sound wave passing through it in heat.
  • This porous structure may be, for example, a metal fabric or a carbon fiber fabric whose weaving makes it possible to fulfill its function dissipating.
  • acoustic panels in front for example in the case of panels equipping nacelles of turbojet engines, also have structural properties sufficient to, in particular, receive and transfer aerodynamic efforts, inertial and those related to the maintenance of the nacelle, to the structural nacelle / engine links, it is necessary to confer on the acoustic damping layer of structural properties.
  • the present invention aims to improve these types of layer acoustic damping by optimizing their resistance to efforts requiring panels equipped with such resistive layers, both axially and radially, the forces generated by the aerodynamic flow, the engine thrust and during thrust reversal.
  • the fibers of the first structural component consist of wicks or slicks unidirectional for example carbon or glass pre-impregnated with a thermoplastic resin, in particular a resin of the family of polyetheretherketones (PEEK) or the family of polyetherimides (PEI).
  • a thermoplastic resin in particular a resin of the family of polyetheretherketones (PEEK) or the family of polyetherimides (PEI).
  • the fibers of the second structural component can also be consisting of unidirectional wicks or layers of carbon or glass, pre-impregnated with a thermoplastic or thermosetting resin.
  • the fibers of the first structural component consist of a fabric for example carbon or glass, pre-impregnated with a PEI type resin, the weft or chain of said fabric being oriented in said direction of flow aerodynamic.
  • the fibers of the second structural component can also be made of a carbon or glass fabric, weft or warp threads said fabric being oriented orthogonally to said direction of flow aerodynamic.
  • the first and second structural components have non-circular openings each having their largest dimension respectively parallel to the direction of the flow aerodynamically and orthogonally to the latter, said openings being preferably rectangular.
  • an intermediate component is interposed between the dissipative component and the second component structure, said intermediate component having a surface area open and being formed of at least one layer of fibers per example of carbon or glass bonded by a resin preferably thermoplastic material, said fibers being oriented in the direction of aerodynamic flow.
  • the intermediate component consists of wicks unidirectional or fabric whose weft or warp threads are oriented along said direction of the aerodynamic flow.
  • the intermediate component is arranged so identical to the first acoustically speaking structural component, that is to say with an identical open area rate and the openings of one of the components facing the openings of the other.
  • the first structural component of such an acoustically layer resistive allows to recover the efforts generated by the flow aerodynamics, as well as those generated by the engine, while the second structural component allows to resume orbital efforts or radial.
  • the invention also relates to an acoustic attenuation panel incorporating such an acoustically resistive layer, in particular a panel reactor nacelle air inlet, whether it consists of several segments or sectors, abutting by splinting, or of a single part comprising a single splits.
  • FIG. 1 there is shown a portion of an attenuation panel acoustic for example a reactor nacelle air inlet panel, constituted, in the known manner, a sandwich formed of a central core 1 of alveolar type, flanked, aerodynamic flow side, of a layer acoustically resistive 2 and, on the opposite side, a total reflector 3.
  • a reactor nacelle air inlet panel constituted, in the known manner, a sandwich formed of a central core 1 of alveolar type, flanked, aerodynamic flow side, of a layer acoustically resistive 2 and, on the opposite side, a total reflector 3.
  • the acoustically resistive layer 2 is consisting of a first structural component 4 directly in contact with the aerodynamic flow whose direction is indicated by the arrow.
  • the first structural component 4 has a surface area appropriate open method defined, in the illustrated embodiment, by rectangular openings 5 arranged in staggered rows, aligned longitudinally along the direction of the aerodynamic flow.
  • Component 4 consists for example of a sheet of material composite obtained from wicks or layers of unidirectional fibers pre-impregnated with a suitable resin, the fibers being oriented according to the direction of aerodynamic flow.
  • the fibers are chosen for example from the group comprising the carbon fiber, glass, Kevlar, aramid fibers, fiber carbon or glass being used preferentially.
  • the impregnating resin is preferably a thermoplastic resin and in particular a resin of the family of polyetheretherketones (PEEK) or the family of polyetherimides (PEI).
  • PEEK polyetheretherketones
  • PEI polyetherimides
  • the openings 5 are made by cutting to the press after polymerization of the fiber impregnating resin for consolidation purposes composite material.
  • the perforated composite sheet constituting component 4 extends over the entire surface to cover the segment or sector of panel to achieve. Several identical sheets can be superimposed to form the component 4.
  • a dissipative component 6 consisting of a metal fabric or "wiremesh", especially a stainless steel fabric.
  • a second structural component 7 constituted, in the embodiment represented, unidirectional fibers oriented orthogonally to the direction of aerodynamic flow. These fibers can be the same as those of component 4.
  • the resin of component 4 is preferably of the type thermoplastic ensuring a good cohesion between the component 4 and the metal fabric 6,
  • the resin of component 7 can be a resin thermosetting material, such as an epoxy resin, which is sufficient for ensure adherence between component 7 and the other constituents of panel, the component 7 not being solicited by the flow aerodynamic.
  • a thermoplastic resin can nevertheless be used.
  • the appropriate open area ratio of component 7 can be obtained, as illustrated, by regular spacings 8 between wicks or groups of fibers 9, the production of the component being obtained by removal Filament.
  • the adhesion between the various constituents 1, 2, 3 of the sandwich is obtained by polymerization of the impregnating resin or resins, in the manner known.
  • Component 4 is first put in place on a mandrel (no shown) to the shape of the panel to be made, the openings 5 being arranged axially to said mandrel.
  • the metal fabric 6 is put in place. Then, the locks or fibers 9 are wound on the mandrel.
  • the alveolar core 1, as well as the rear reflector 3, are place, the whole being then put in an oven or autoclave for the purpose of polymerization.
  • the first structural component 4 may alternatively consist of a fabric whose weft or warp threads are oriented parallel to the direction of the aerodynamic flow, the sheet being pierced with openings, after consolidation of the composite material.
  • openings in the sheet may have variable dimensions and any shape, circular or non-circular.
  • the second structural component 7 may alternatively consist of of a fabric of pre-impregnated fibers whose weft or warp threads are oriented orthogonally to the direction of the aerodynamic flow, the fabric, after consolidation, being pierced with appropriate openings conferring on the component the appropriate open area ratio, the openings may have variable dimensions and any shape, circular or non-circular, in relation to the openings of the first component 4.
  • FIG. 2 illustrates an alternative embodiment of the panel of FIG. 1, according to which between the metallic fabric 6 and the second structural component 7 is interposed an intermediate component 10 reinforcing the action of the structural component 4.
  • the intermediate component 10 comprises fibers, for example carbon or glass oriented parallel to the direction of the aerodynamic flow and includes a open area ratio corresponding to that of the first structural component 4.
  • the impregnating resin of the fibers of component 10 is a thermoplastic type resin providing a better bond with the metal fabric 6.
  • the component 10 can be, as illustrated, identical to the component 4, that is to say formed of one or more composite sheets comprising unidirectional or woven fibers pierced with apertures 11 similar to openings 5 and next to them.
  • Component 10 can of course have a different constitution of that shown, in particular that of component 4.
  • the alveolar core 1 may consist of several layers separated by septa.

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Acoustics & Sound (AREA)
  • Multimedia (AREA)
  • Reinforced Plastic Materials (AREA)
  • Laminated Bodies (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Woven Fabrics (AREA)
  • Building Environments (AREA)
EP03362003A 2002-04-17 2003-04-15 Schallwiderstandsfähige Mehrkomponentenschicht für eine schalldämpfende Platte und Platte unter Verwendung einer solchen Schicht Expired - Lifetime EP1355294B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0204801A FR2838860B1 (fr) 2002-04-17 2002-04-17 Couche acoustiquement resistive multicomposant pour panneau d'attenuation acoustique et panneau ainsi obtenu
FR0204801 2002-04-17

Publications (2)

Publication Number Publication Date
EP1355294A1 true EP1355294A1 (de) 2003-10-22
EP1355294B1 EP1355294B1 (de) 2008-07-16

Family

ID=28459906

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03362003A Expired - Lifetime EP1355294B1 (de) 2002-04-17 2003-04-15 Schallwiderstandsfähige Mehrkomponentenschicht für eine schalldämpfende Platte und Platte unter Verwendung einer solchen Schicht

Country Status (6)

Country Link
US (1) US6840349B2 (de)
EP (1) EP1355294B1 (de)
AT (1) ATE401643T1 (de)
CA (1) CA2425364C (de)
DE (1) DE60322140D1 (de)
FR (1) FR2838860B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2912833A1 (fr) * 2007-02-20 2008-08-22 Airbus France Sas Panneau pour le traitement acoustique
WO2011070279A1 (fr) * 2009-12-11 2011-06-16 Aircelle Procédé de fabrication de panneau acoustique pour nacelle d'aéronef
FR3065472A1 (fr) * 2017-04-25 2018-10-26 Airbus Operations Panneau pour le traitement acoustique comprenant une structure acoustiquement resistive poreuse comportant des canaux de connexion
FR3091670A1 (fr) * 2019-01-15 2020-07-17 Airbus Operations (S.A.S.) Procédé de fabrication d’une structure acoustiquement résistive, structure acoustiquement résistive ainsi obtenue, panneau d’absorption acoustique comportant ladite structure acoustiquement résistive
US10940935B2 (en) 2017-04-25 2021-03-09 Airbus Operations (S.A.S.) Acoustic treatment panel comprising cells which each contain a plurality of conduits

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FR2823590B1 (fr) * 2001-04-17 2003-07-25 Eads Airbus Sa Panneau d'attenuation acoustique comportant une couche resistive a composante structurale renforcee
US7337875B2 (en) * 2004-06-28 2008-03-04 United Technologies Corporation High admittance acoustic liner
US20070104934A1 (en) * 2005-11-10 2007-05-10 General Electric Company Lightweight nacelle for turbines and methods for making same
US7955698B2 (en) * 2006-11-15 2011-06-07 Honeywell International Inc. Fiber-based acoustic treatment material and methods of making the same
US20080248300A1 (en) * 2007-04-05 2008-10-09 United Technologies Corporation Processes for repairing erosion resistant coatings
JP2009062977A (ja) * 2007-08-15 2009-03-26 Rohr Inc 線形音響ライナー
US20090188748A1 (en) * 2008-01-24 2009-07-30 Honeywell International Inc. Noise suppression panels and repair methods therefor
US7757810B2 (en) 2008-04-03 2010-07-20 Soundtech, Inc. Transparent acoustical laminate wall system and method of forming same
US8573358B2 (en) * 2008-05-22 2013-11-05 3M Innovative Properties Company Multilayer sound absorbing structure comprising mesh layer
TWI651455B (zh) * 2009-01-14 2019-02-21 Kuraray Co., Ltd 隔音板、隔音構造及隔音方法
DE102010015638B4 (de) * 2010-04-20 2015-02-12 Airbus Operations Gmbh Luftfahrzeugkabinen-Plattenabsorber
KR101964644B1 (ko) * 2012-05-10 2019-04-02 엘지전자 주식회사 소음저감부가 구비된 가전기기
US9643392B2 (en) 2013-07-29 2017-05-09 The Boeing Company Septumization of honeycomb sandwiches
US8820477B1 (en) * 2013-07-29 2014-09-02 The Boeing Company Acoustic panel
US9708072B2 (en) 2014-04-30 2017-07-18 The Boeing Company Aircraft engine nacelle bulkheads and methods of assembling the same
US9938852B2 (en) * 2014-04-30 2018-04-10 The Boeing Company Noise attenuating lipskin assembly and methods of assembling the same
US9604438B2 (en) 2014-04-30 2017-03-28 The Boeing Company Methods and apparatus for noise attenuation in an engine nacelle
US9656761B2 (en) 2014-04-30 2017-05-23 The Boeing Company Lipskin for a nacelle and methods of making the same
US9693166B2 (en) 2014-06-24 2017-06-27 The Boeing Company Automated production of acoustic structures
US9931825B2 (en) 2014-07-09 2018-04-03 The Boeing Company Septumization of cellular cores
US10443496B2 (en) * 2016-07-18 2019-10-15 The Boeing Company Acoustic paneling
US10720135B2 (en) * 2016-07-18 2020-07-21 The Boeing Company Acoustic panels that include multi-layer facesheets
US10793282B2 (en) 2016-07-28 2020-10-06 The Boeing Company Liner assembly, engine housing, and methods of assembling the same
US11059559B2 (en) 2018-03-05 2021-07-13 General Electric Company Acoustic liners with oblique cellular structures
US11052987B2 (en) * 2018-05-30 2021-07-06 The Boeing Company Integrally damped composite aircraft floor panels
US11047304B2 (en) 2018-08-08 2021-06-29 General Electric Company Acoustic cores with sound-attenuating protuberances
US11353240B2 (en) 2018-10-02 2022-06-07 United States Of America As Represented By The Administrator Of Nasa Low drag, variable-depth acoustic liner
US10823059B2 (en) 2018-10-03 2020-11-03 General Electric Company Acoustic core assemblies with mechanically joined acoustic core segments, and methods of mechanically joining acoustic core segments
US11434819B2 (en) 2019-03-29 2022-09-06 General Electric Company Acoustic liners with enhanced acoustic absorption and reduced drag characteristics
US11668236B2 (en) 2020-07-24 2023-06-06 General Electric Company Acoustic liners with low-frequency sound wave attenuating features
FR3113170A1 (fr) * 2020-07-31 2022-02-04 Airbus Operations Matériau acoustique en bande à bride intégrée, et paroi interne d’une entrée d’air d’aéronef réalisée avec ce matériau
FR3116642A1 (fr) 2020-11-24 2022-05-27 Airbus Operations Coque de peau résistive intégrant des bandes métalliques perforées, et paroi interne acoustique d’une entrée d’air d’aéronef formée à partir de telles coques de peau résistive.
US11970992B2 (en) 2021-06-03 2024-04-30 General Electric Company Acoustic cores and tools and methods for forming the same
EP4169706A1 (de) * 2021-10-25 2023-04-26 Airbus Operations SAS Resistives hautelement für eine akustikplatte für ein flugzeug
FR3129241A1 (fr) * 2021-11-17 2023-05-19 Airbus Operations Peau poreuse pourvue d’une pluralité de bandes et panneau d’atténuation acoustique comprenant une telle peau poreuse.
US11965425B2 (en) 2022-05-31 2024-04-23 General Electric Company Airfoil for a turbofan engine

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US4671841A (en) * 1986-01-06 1987-06-09 Rohr Industries, Inc. Method of making an acoustic panel with a triaxial open-weave face sheet
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EP0895222A2 (de) * 1997-07-30 1999-02-03 The Boeing Company Stützstruktur für Akustikplatten einer Triebwerksgondel

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FR2844304B1 (fr) * 2002-09-10 2004-12-10 Airbus France Couche acoustiquement resistive pour panneau d'attenuation acoustique, panneau utilisant une telle couche

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GB2130963A (en) * 1982-11-30 1984-06-13 Rolls Royce Manufacturing damped resonator acoustical panel
US4671841A (en) * 1986-01-06 1987-06-09 Rohr Industries, Inc. Method of making an acoustic panel with a triaxial open-weave face sheet
US5315820A (en) * 1990-06-28 1994-05-31 Short Brothers Plc Composite structural component
EP0895222A2 (de) * 1997-07-30 1999-02-03 The Boeing Company Stützstruktur für Akustikplatten einer Triebwerksgondel

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2912833A1 (fr) * 2007-02-20 2008-08-22 Airbus France Sas Panneau pour le traitement acoustique
EP2115733B1 (de) * 2007-02-20 2018-01-24 Airbus Opérations SAS Schalldämmplatte
WO2011070279A1 (fr) * 2009-12-11 2011-06-16 Aircelle Procédé de fabrication de panneau acoustique pour nacelle d'aéronef
FR2953973A1 (fr) * 2009-12-11 2011-06-17 Aircelle Sa Procede de fabrication de panneau acoustique pour nacelle d'aeronef
CN102652335A (zh) * 2009-12-11 2012-08-29 埃尔塞乐公司 用于制造用于飞行器发动机舱的声学板的方法
FR3065472A1 (fr) * 2017-04-25 2018-10-26 Airbus Operations Panneau pour le traitement acoustique comprenant une structure acoustiquement resistive poreuse comportant des canaux de connexion
EP3395675A1 (de) * 2017-04-25 2018-10-31 Airbus Operations (S.A.S) Paneel zur akustischen behandlung, das eine akustisch resistive poröse struktur umfasst, die verbindungskanäle enthält
US10940935B2 (en) 2017-04-25 2021-03-09 Airbus Operations (S.A.S.) Acoustic treatment panel comprising cells which each contain a plurality of conduits
US11027817B2 (en) 2017-04-25 2021-06-08 Airbus Operations (S.A.S.) Acoustic treatment panel comprising a porous acoustically resistive structure comprising connecting canals
FR3091670A1 (fr) * 2019-01-15 2020-07-17 Airbus Operations (S.A.S.) Procédé de fabrication d’une structure acoustiquement résistive, structure acoustiquement résistive ainsi obtenue, panneau d’absorption acoustique comportant ladite structure acoustiquement résistive
EP3683056A1 (de) * 2019-01-15 2020-07-22 Airbus Operations (S.A.S.) Herstellungsverfahren einer akustisch resistiven struktur, so erhaltene akustisch resistive struktur und schalldämmplatte, die diese akustisch resistive struktur umfasst
US11325323B2 (en) 2019-01-15 2022-05-10 Airbus Operations S.A.S. Method for producing an acoustically resistive structure, acoustically resistive structure thus obtained, and sound-absorption panel comprising said acoustically resistive structure

Also Published As

Publication number Publication date
CA2425364C (fr) 2011-04-05
FR2838860B1 (fr) 2005-01-21
US6840349B2 (en) 2005-01-11
ATE401643T1 (de) 2008-08-15
FR2838860A1 (fr) 2003-10-24
EP1355294B1 (de) 2008-07-16
DE60322140D1 (de) 2008-08-28
CA2425364A1 (fr) 2003-10-17
US20040016595A1 (en) 2004-01-29

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