EP1355294B1 - Multicomponent acoustically-resistive layer for a sound-absorbing panel and panel having such a layer - Google Patents

Multicomponent acoustically-resistive layer for a sound-absorbing panel and panel having such a layer Download PDF

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Publication number
EP1355294B1
EP1355294B1 EP03362003A EP03362003A EP1355294B1 EP 1355294 B1 EP1355294 B1 EP 1355294B1 EP 03362003 A EP03362003 A EP 03362003A EP 03362003 A EP03362003 A EP 03362003A EP 1355294 B1 EP1355294 B1 EP 1355294B1
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EP
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Prior art keywords
component
structural component
layer according
layer
fibres
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German (de)
French (fr)
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EP1355294A1 (en
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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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    • 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 bonded components and intended to constitute one of the elements of an acoustic attenuation panel, in particular a panel intended to be mounted in walls. nacelles of aircraft turbojets.
  • this type of panel incorporates a cellular core, such as a honeycomb structure flanked, incident sound wave side, an acoustic damping layer and, on the opposite side, a rear reflector.
  • a cellular core such as a honeycomb structure flanked, incident sound wave side, an acoustic damping layer and, on the opposite side, a rear reflector.
  • the acoustic damping layer is a porous structure dissipative role, that is to say, partially transforming the acoustic energy of the sound wave passing through heat.
  • This porous structure may be, for example, a metal fabric or a fabric of carbon fibers whose weaving makes it possible to fulfill its dissipative function.
  • acoustic panels in front of, for example in the case of panels equipping nacelles of turbojet engines also have sufficient structural properties to notably receive and transfer the aerodynamic forces, inertial and those related to the maintenance of the nacelle, to the structural links nacelle / motor, it is necessary to give the acoustic damping layer structural properties.
  • the present invention aims to improve these types of acoustic damping layer by optimizing their ability to withstand the forces requiring the panels equipped with such resistive layers, both axially and radially, forces generated by the aerodynamic flow, the thrust of the engine and during thrust reversal.
  • the fibers of the first structural component consist of wicks or unidirectional layers, for example of carbon or glass, pre-impregnated with thermoplastic resin, in particular a resin of the family of polyetheretherketones (PEEK) or of the family of polyetherimides (PEI).
  • thermoplastic resin in particular a resin of the family of polyetheretherketones (PEEK) or of the family of polyetherimides (PEI).
  • the fibers of the second structural component may also consist of wicks or unidirectional sheets 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 warp threads of said fabric being oriented in said direction of the aerodynamic flow.
  • the fibers of the second structural component may also consist of a carbon or glass fabric, the weft or warp threads of said fabric being oriented orthogonally to said direction of the aerodynamic flow.
  • the first and second structural components have non-circular openings each having their largest dimension respectively parallel to the direction of the aerodynamic flow and orthogonally to the latter, said openings being preferably rectangular.
  • an intermediate component is interposed between the dissipative component and the second structural component, said intermediate component having an appropriate open surface ratio and being formed.
  • at least one layer of fibers for example carbon or glass bonded by a resin preferably thermoplastic, said fibers being oriented in the direction of the aerodynamic flow.
  • the intermediate component consists of unidirectional locks or a fabric whose weft or warp threads are oriented along said direction of the aerodynamic flow.
  • the intermediate component is arranged identically to the first acoustically speaking structural component, that is to say with an identical open area ratio and the openings of one of the components facing the openings of the other.
  • the first structural component of such an acoustically resistive layer makes it possible to take up the forces generated by the aerodynamic flow, as well as those generated by the motor, while the second structural component makes it possible to take up the orbital or radial forces.
  • a resistive layer is obtained particularly resistant to tearing.
  • the subject of the invention is also an acoustic attenuation panel incorporating such an acoustically resistive layer, in particular a reactor nacelle air inlet panel, whether it consists of several segments or sectors, butt jointed, or of a single part with a single splint.
  • an acoustic attenuation panel for example a reactor nacelle air intake panel, constituted, in the known manner, a sandwich formed of a central core 1 of alveolar type flanked, on the aerodynamic flow side, of an acoustically resistive layer 2 and, on the opposite side, of a total reflector 3.
  • the acoustically resistive layer 2 consists 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 suitable open surface ratio defined, in the illustrated embodiment, by rectangular openings 5 staggered, aligned longitudinally in the direction of the aerodynamic flow.
  • the component 4 is constituted for example by a sheet of composite material obtained from strands or layers of unidirectional fibers pre-impregnated with a suitable resin, the fibers being oriented in the direction of the aerodynamic flow.
  • the fibers are chosen for example from the group comprising carbon, glass, Kevlar fibers, aramid fibers, carbon or glass fibers being used preferentially.
  • the impregnating resin is preferably a thermoplastic resin and in particular a resin of the family of polyetheretherketones (PEEK) or of the family of polyetherimides (PEI).
  • PEEK polyetheretherketones
  • PEI polyetherimides
  • the openings 5 are made by press cutting after polymerization of the fiber impregnating resin to consolidate the composite material.
  • the perforated composite sheet constituting component 4 extends over the entire surface to be covered with the segment or sector of panel to be produced. Several identical sheets can be superimposed to form 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 shown, unidirectional fibers oriented orthogonal to the direction of the aerodynamic flow. These fibers can be of the same type as those of component 4.
  • the resin of the component 4 is preferably of the thermoplastic type ensuring a good cohesion between the component 4 and the metal fabric 6,
  • the resin of the component 7 may be a thermosetting resin, such as an epoxy resin, which is sufficient to ensure adhesion between the component 7 and the other constituents of the panel, the component 7 not being solicited by the aerodynamic flow.
  • a thermoplastic resin can nevertheless be used.
  • the appropriate open area ratio of the component 7 can be obtained, as illustrated, by regular spacings 8 between strands or groups of fibers 9, the embodiment of the component being obtained by filamentary deposition.
  • the adhesion between the various constituents 1, 2, 3 of the sandwich is obtained by polymerization of the impregnating resin or resins, in the known manner.
  • the component 4 is first put in place on a mandrel (not shown) in the form of the panel to be made, the openings 5 being disposed axially to said mandrel.
  • the metal fabric 6 is put in place. Then, the locks or fibers 9 are wound on the mandrel.
  • the cellular core 1, as well as the rear reflector 3, are put in place, the assembly then being put in an oven or autoclave for polymerization purposes.
  • the first structural component 4 may alternatively consist of a fabric whose weft son, or warp, 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 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 apertures conferring on the component the appropriate open area ratio, the openings being able to have variable dimensions and any shape, circular or non-circular circular, in relation to the openings of the first component 4.
  • the figure 2 illustrates an alternative embodiment of the panel of the figure 1 , according to which between the metal fabric 6 and the second structural component 7 is interposed an intermediate component 10 for reinforcing the action of the first structural component 4.
  • the intermediate component 10 comprises fibers, for example carbon fibers or oriented parallel to the direction of the aerodynamic flow and has an open area ratio corresponding to that of the first structural component 4.
  • the fiber impregnating resin of the component 10 is a thermoplastic-type resin providing a better bond with the metal fabric 6.
  • the component 10 may 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 openings 11 similar to the openings 5 and opposite these last.
  • the component 10 can of course have a constitution different from that shown, in particular as a function of that of the component 4.
  • the alveolar core 1 may consist of several layers separated by septa.

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  • 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)
  • Building Environments (AREA)
  • Woven Fabrics (AREA)

Abstract

The panel, comprising a cellular core (1) with a sounddamping layer (2) on one side and a total reflective layer (3) on the other, has the sound-damping layer made from a structural component (4) of resinbound fibres in contact with and parallel to the aerodynamic flow, a dissipating layer (6) of metallic fabric and a second structural component (7) of resin-bound fibres lying orthogonal to the aerodynamic flow. The two structural components have open surfaces and are made from glass, carbon or polymer fibres, and the metallic fabric is preferably of stainless steel.

Description

La présente invention a trait à une couche acoustiquement résistive constituée d'une pluralité de composantes superposées et liées et destinée à constituer l'un des éléments d'un panneau d'atténuation acoustique, notamment d'un panneau destiné à être monté dans des parois de nacelles de turboréacteurs d'aéronefs.The present invention relates to an acoustically resistive layer consisting of a plurality of superimposed and bonded components and intended to constitute one of the elements of an acoustic attenuation panel, in particular a panel intended to be mounted in walls. nacelles of aircraft turbojets.

Dans la pratique, ce type de panneau intègre une âme alvéolaire, telle qu'une structure en nid d'abeilles flanquée, côté onde sonore incidente, d'une couche d'amortissement acoustique et, du côté opposé, d'un réflecteur arrière.In practice, this type of panel incorporates a cellular core, such as a honeycomb structure flanked, incident sound wave side, an acoustic damping layer and, on the opposite side, a rear reflector.

La couche d'amortissement acoustique est une structure poreuse à rôle dissipatif, c'est-à-dire transformant partiellement l'énergie acoustique de l'onde sonore la traversant en chaleur.The acoustic damping layer is a porous structure dissipative role, that is to say, partially transforming the acoustic energy of the sound wave passing through heat.

Cette structure poreuse peut être, par exemple, un tissu métallique ou un tissu de fibres de carbone dont le tissage permet de remplir sa fonction dissipatrice.This porous structure may be, for example, a metal fabric or a fabric of carbon fibers whose weaving makes it possible to fulfill its dissipative function.

Ces panneaux acoustiques devant, par exemple dans le cas de panneaux équipant des nacelles de turboréacteurs, également avoir des propriétés structurales suffisantes pour notamment recevoir et transférer les efforts aérodynamiques, inertiels et ceux liés à la maintenance de la nacelle, vers les liaisons structurales nacelle / moteur, il est nécessaire de conférer à la couche d'amortissement acoustique des propriétés structurales.These acoustic panels in front of, for example in the case of panels equipping nacelles of turbojet engines, also have sufficient structural properties to notably receive and transfer the aerodynamic forces, inertial and those related to the maintenance of the nacelle, to the structural links nacelle / motor, it is necessary to give the acoustic damping layer structural properties.

A cette fin on a déjà proposé de réaliser une couche d'amortissement acoustique à deux composantes superposées, l'une structurale et l'autre poreuse et dissipatrice, la composante structurale étant, soit disposée entre la structure alvéolaire et la composante dissipatrice, comme illustré par le brevet GB 2 130 963 , soit disposée au contact avec l'onde sonore incidente, comme illustré par le document EP 0 911 803 .For this purpose, it has already been proposed to produce an acoustic damping layer with two superimposed components, one structural and the other porous and dissipative, the structural component being either disposed between the cellular structure and the dissipative component, as illustrated. speak GB Patent 2,130,963 , arranged in contact with the incident sound wave, as illustrated by the document EP 0 911 803 .

La présente invention vise à perfectionner ces types de couche d'amortissement acoustique en optimisant leur capacité de résistance aux efforts sollicitant les panneaux équipés de telles couches résistives, à la fois axialement et radialement, efforts générés par l'écoulement aérodynamique, la poussée du moteur et lors de l'inversion de poussée.The present invention aims to improve these types of acoustic damping layer by optimizing their ability to withstand the forces requiring the panels equipped with such resistive layers, both axially and radially, forces generated by the aerodynamic flow, the thrust of the engine and during thrust reversal.

A cet effet, l'invention a pour objet une couche acoustiquement résistive multicomposant, pour panneau d'atténuation acoustique du type constitué d'une âme alvéolaire flanquée, côté onde sonore incidente, d'une couche d'amortissement acoustique et, du côté opposé, d'un réflecteur arrière, caractérisée en ce qu'elle est constituée :

  • d'une première composante structurale en contact avec l'écoulement aérodynamique et formée d'au moins une couche de fibres liées par une résine appropriée et orientées selon la direction de l'écoulement aérodynamique, ladite composante comportant un taux de surface ouverte approprié ;
  • d'une composante dissipatrice disposée contre la face de ladite première composante opposée audit écoulement, formée d'un tissu métallique ;
  • et d'une seconde composante structurale formée d'au moins une couche de fibres liées par une résine appropriée, orientées orthogonalement à ladite direction d'écoulement aérodynamique, ladite seconde composante structurale étant liée à ladite âme alvéolaire et comportant un taux de surface ouverte approprié.
For this purpose, the subject of the invention is an acoustically resistive multicomponent layer for an acoustic attenuation panel of the type consisting of a cellular core flanked, on the incident sound wave side, of an acoustic damping layer and, on the opposite side , a rear reflector, characterized in that it consists of:
  • a first structural component in contact with the aerodynamic flow and formed of at least one layer of fibers bonded by a suitable resin and oriented in the direction of the aerodynamic flow, said component having an appropriate open surface ratio;
  • a dissipating component disposed against the face of said first component opposite said flow, formed of a metal fabric;
  • and a second structural component formed of at least one fiber layer bonded by a suitable resin, oriented orthogonally to said aerodynamic flow direction, said second structural component being bonded to said cellular core and having an appropriate open surface ratio .

Suivant un mode de mise en oeuvre, les fibres de la première composante structurale sont constituées de mèches ou nappes unidirectionnelles par exemple de carbone ou de verre pré-imprégnées d'une résine thermoplastique, notamment une résine de la famille de polyétheréthercétones (PEEK) ou de la famille des polyétherimides (PEI).According to one embodiment, the fibers of the first structural component consist of wicks or unidirectional layers, for example of carbon or glass, pre-impregnated with thermoplastic resin, in particular a resin of the family of polyetheretherketones (PEEK) or of the family of polyetherimides (PEI).

Les fibres de la seconde composante structurale peuvent être également constituées de mèches ou nappes unidirectionnelles, de carbone ou de verre, pré-imprégnées d'une résine thermoplastique ou thermodurcissable.The fibers of the second structural component may also consist of wicks or unidirectional sheets of carbon or glass pre-impregnated with a thermoplastic or thermosetting resin.

Suivant un autre mode de mise en oeuvre, les fibres de la première composante structurale sont constituées d'un tissu par exemple de carbone ou de verre, pré-imprégnées d'une résine de type PEI, les fils de trame ou de chaîne dudit tissu étant orientés selon ladite direction de l'écoulement aérodynamique.According to another embodiment, 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 warp threads of said fabric being oriented in said direction of the aerodynamic flow.

Les fibres de la seconde composante structurale peuvent également être constituées d'un tissu de carbone ou de verre, les fils de trame ou de chaîne dudit tissu étant orientés orthogonalement à ladite direction de l'écoulement aérodynamique.The fibers of the second structural component may also consist of a carbon or glass fabric, the weft or warp threads of said fabric being oriented orthogonally to said direction of the aerodynamic flow.

Avantageusement, les première et seconde composantes structurales présentent des ouvertures non-circulaires présentant chacune leur plus grande dimension respectivement parallèlement à la direction de l'écoulement aérodynamique et orthogonalement à cette dernière, lesdites ouvertures étant de préférence rectangulaires.Advantageously, the first and second structural components have non-circular openings each having their largest dimension respectively parallel to the direction of the aerodynamic flow and orthogonally to the latter, said openings being preferably rectangular.

Suivant encore un autre mode de réalisation, afin de renforcer la tenue à l'effort de la première composante structurale une composante intermédiaire est interposée entre la composante dissipatrice et la seconde composante structurale, ladite composante intermédiaire comportant un taux de surface ouverte approprié et étant formée d'au moins une couche de fibres par exemple de carbone ou de verre liées par une résine de préférence thermoplastique, lesdites fibres, étant orientées selon la direction de l'écoulement aérodynamique.According to yet another embodiment, in order to reinforce the stress resistance of the first structural component, an intermediate component is interposed between the dissipative component and the second structural component, said intermediate component having an appropriate open surface ratio and being formed. at least one layer of fibers, for example carbon or glass bonded by a resin preferably thermoplastic, said fibers being oriented in the direction of the aerodynamic flow.

La composante intermédiaire est constituée de mèches unidirectionnelles ou d'un tissu dont les fils de trame ou de chaîne sont orientés suivant ladite direction de l'écoulement aérodynamique.The intermediate component consists of unidirectional locks or a fabric whose weft or warp threads are oriented along said direction of the aerodynamic flow.

De préférence, la composante intermédiaire est disposée de manière identique à la première composante structurale acoustiquement parlant, c'est-à-dire avec un taux de surface ouverte identique et les ouvertures de l'une des composantes en regard des ouvertures de l'autre.Preferably, the intermediate component is arranged identically to the first acoustically speaking structural component, that is to say with an identical open area ratio and the openings of one of the components facing the openings of the other.

La première composante structurale d'une telle couche acoustiquement résistive permet de reprendre les efforts générés par l'écoulement aérodynamique, ainsi que ceux générés par le moteur, cependant que la seconde composante structurale permet de reprendre les efforts orbitaux ou radiaux.The first structural component of such an acoustically resistive layer makes it possible to take up the forces generated by the aerodynamic flow, as well as those generated by the motor, while the second structural component makes it possible to take up the orbital or radial forces.

En dissociant les éléments de reprise des efforts, on améliore la reprise de chaque effort.By separating the recovery elements from the efforts, the recovery of each effort is improved.

Par ailleurs, notamment dans le cas de la réalisation de la première composante structurale avec des ouvertures rectangulaires longitudinalement orientées selon la direction de l'écoulement aérodynamique, on obtient une couche résistive particulièrement résistante à l'arrachement.Moreover, particularly in the case of the realization of the first structural component with rectangular openings longitudinally oriented in the direction of the aerodynamic flow, a resistive layer is obtained particularly resistant to tearing.

L'invention a également pour objet un panneau d'atténuation acoustique incorporant une telle couche acoustiquement résistive, notamment un panneau d'entrée d'air de nacelle de réacteur, qu'il soit constitué de plusieurs segments ou secteurs, aboutés par éclissage, ou d'une seule partie comportant une unique éclisse.The subject of the invention is also an acoustic attenuation panel incorporating such an acoustically resistive layer, in particular a reactor nacelle air inlet panel, whether it consists of several segments or sectors, butt jointed, or of a single part with a single splint.

D'autres caractéristiques et avantages ressortiront de la description qui va suivre de modes de mise en oeuvre du dispositif de l'invention, description donnée à titre d'exemple uniquement et en regard des dessins annexés sur lesquels :

  • la figure 1 est une vue partielle en perspective d'un panneau d'atténuation acoustique muni d'une couche acoustiquement résistive conforme à l'invention, et
  • la figure 2 est une vue analogue à celle de la figure 1, illustrant une variante de réalisation.
Other features and advantages will emerge from the following description of embodiments of the device of the invention, a description given by way of example only and with reference to the appended drawings in which:
  • the figure 1 is a partial perspective view of an acoustic attenuation panel provided with an acoustically resistive layer according to the invention, and
  • the figure 2 is a view similar to that of the figure 1 , illustrating an alternative embodiment.

Sur la figure 1, on a représenté une partie d'un panneau d'atténuation acoustique par exemple un panneau d'entrée d'air de nacelle de réacteur, constitué, à la manière connue, d'un sandwich formé d'une âme centrale 1 de type alvéolaire, flanquée, côté écoulement aérodynamique, d'une couche acoustiquement résistive 2 et, côté opposé, d'un réflecteur total 3.On the figure 1 , there is shown a portion of an acoustic attenuation panel, for example a reactor nacelle air intake panel, constituted, in the known manner, a sandwich formed of a central core 1 of alveolar type flanked, on the aerodynamic flow side, of an acoustically resistive layer 2 and, on the opposite side, of a total reflector 3.

Conformément à l'invention, la couche acoustiquement résistive 2 est constituée d'une première composante structurale 4 directement en contact avec l'écoulement aérodynamique dont le sens est indiqué par la flèche.According to the invention, the acoustically resistive layer 2 consists of a first structural component 4 directly in contact with the aerodynamic flow whose direction is indicated by the arrow.

La première composante structurale 4 présente un taux de surface ouverte approprié défini, dans le mode de réalisation illustré, par des ouvertures rectangulaires 5 disposées en quinconce, alignées longitudinalement suivant la direction de l'écoulement aérodynamique.The first structural component 4 has a suitable open surface ratio defined, in the illustrated embodiment, by rectangular openings 5 staggered, aligned longitudinally in the direction of the aerodynamic flow.

La composante 4 est constituée par exemple par une tôle en matériau composite obtenue à partir de mèches ou nappes de fibres unidirectionnelles pré-imprégnées d'une résine appropriée, les fibres étant orientées suivant la direction de l'écoulement aérodynamique.The component 4 is constituted for example by a sheet of composite material obtained from strands or layers of unidirectional fibers pre-impregnated with a suitable resin, the fibers being oriented in the direction of the aerodynamic flow.

Les fibres sont choisies par exemple dans le groupe comprenant les fibres de carbone, de verre, de Kevlar, les fibres aramides, les fibres de carbone ou de verre étant utilisées préférentiellement.The fibers are chosen for example from the group comprising carbon, glass, Kevlar fibers, aramid fibers, carbon or glass fibers being used preferentially.

La résine d'imprégnation est de préférence une résine thermoplastique et notamment une résine de la famille des polyétheréthercétones (PEEK) ou de la famille des polyétherimides (PEI).The impregnating resin is preferably a thermoplastic resin and in particular a resin of the family of polyetheretherketones (PEEK) or of the family of polyetherimides (PEI).

Les ouvertures 5 sont réalisées par découpe à la presse après polymérisation de la résine d'imprégnation des fibres aux fins de consolidation du matériau composite.The openings 5 are made by press cutting after polymerization of the fiber impregnating resin to consolidate the composite material.

La tôle composite perforée constituant la composante 4 s'étend sur toute la surface à recouvrir du segment ou secteur de panneau à réaliser. Plusieurs tôles identiques peuvent être superposées pour former la composante 4.The perforated composite sheet constituting component 4 extends over the entire surface to be covered with the segment or sector of panel to be produced. Several identical sheets can be superimposed to form component 4.

Sous la première composante structurale 4 est disposée une composante dissipatrice 6 constituée d'un tissu métallique ou "wiremesh", tout particulièrement un tissu en acier inoxydable.Under the first structural component 4 is disposed a dissipative component 6 consisting of a metal fabric or "wiremesh", especially a stainless steel fabric.

Entre le tissu métallique 6 et l'âme alvéolaire 1 est interposée une seconde composante structurale 7 constituée, dans le mode de réalisation représenté, de fibres unidirectionnelles orientées orthogonalement à la direction de l'écoulement aérodynamique. Ces fibres peuvent être du même type que celles de la composante 4.Between the metal fabric 6 and the alveolar core 1 is interposed a second structural component 7 constituted, in the embodiment shown, unidirectional fibers oriented orthogonal to the direction of the aerodynamic flow. These fibers can be of the same type as those of component 4.

Alors que la résine de la composante 4 est de préférence du type thermoplastique assurant une bonne cohésion entre la composante 4 et le tissu métallique 6, la résine de la composante 7 peut être une résine thermodurcissable, telle qu'une résine époxyde, ce qui est suffisant pour assurer l'adhérence entre la composante 7 et les autres constituants du panneau, la composante 7 n'étant pas sollicitée par l'écoulement aérodynamique. Une résine thermoplastique peut néanmoins être utilisée.While the resin of the component 4 is preferably of the thermoplastic type ensuring a good cohesion between the component 4 and the metal fabric 6, the resin of the component 7 may be a thermosetting resin, such as an epoxy resin, which is sufficient to ensure adhesion between the component 7 and the other constituents of the panel, the component 7 not being solicited by the aerodynamic flow. A thermoplastic resin can nevertheless be used.

Le taux approprié de surface ouverte de la composante 7 peut être obtenu, comme illustré, par des espacements réguliers 8 entre mèches ou groupes de fibres 9, la réalisation de la composante étant obtenue par dépose filamentaire.The appropriate open area ratio of the component 7 can be obtained, as illustrated, by regular spacings 8 between strands or groups of fibers 9, the embodiment of the component being obtained by filamentary deposition.

L'adhésion entre les divers constituants 1, 2, 3 du sandwich est obtenue par polymérisation de la ou des résines d'imprégnation, à la manière connue.The adhesion between the various constituents 1, 2, 3 of the sandwich is obtained by polymerization of the impregnating resin or resins, in the known manner.

La composante 4 est en premier lieu mise en place sur un mandrin (non représenté) à la forme du panneau à réaliser, les ouvertures 5 étant disposées axialement audit mandrin.The component 4 is first put in place on a mandrel (not shown) in the form of the panel to be made, the openings 5 being disposed axially to said mandrel.

Puis, le tissu métallique 6 est mis en place. Ensuite, les mèches ou fibres 9 sont bobinées sur le mandrin.Then, the metal fabric 6 is put in place. Then, the locks or fibers 9 are wound on the mandrel.

Enfin, l'âme alvéolaire 1, ainsi que le réflecteur arrière 3, sont mis en place, l'ensemble étant ensuite mis en étuve ou en autoclave à des fins de polymérisation.Finally, the cellular core 1, as well as the rear reflector 3, are put in place, the assembly then being put in an oven or autoclave for polymerization purposes.

Sur un même mandrin, il est possible de réaliser simultanément les divers segments ou secteurs constituant un panneau d'entrée d'air.On the same mandrel, it is possible to simultaneously realize the various segments or sectors constituting an air inlet panel.

La première composante structurale 4 peut être en variante constituée d'un tissu dont les fils de trame, ou de chaîne, sont orientés parallèlement à la direction de l'écoulement aérodynamique, la tôle étant percée d'ouvertures, après consolidation du matériau composite.The first structural component 4 may alternatively consist of a fabric whose weft son, or warp, are oriented parallel to the direction of the aerodynamic flow, the sheet being pierced with openings after consolidation of the composite material.

Il est à noter que les ouvertures ménagées dans la tôle peuvent avoir des dimensions variables et une forme quelconque, circulaire ou non-circulaire.It should be noted that the openings in the sheet may have variable dimensions and any shape, circular or non-circular.

La seconde composante structurale 7 peut être en variante constituée d'un tissu de fibres pré-imprégnées dont les fils de trame ou de chaîne sont orientées orthogonalement à la direction de l'écoulement aérodynamique, le tissu, après consolidation, étant percé d'ouvertures appropriées conférant à la composante le taux de surface ouverte approprié, les ouvertures pouvant avoir des dimensions variables et une forme quelconque, circulaire ou non-circulaire, en rapport avec les ouvertures de la première composante 4.The second structural component 7 may alternatively consist 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 apertures conferring on the component the appropriate open area ratio, the openings being able to have variable dimensions and any shape, circular or non-circular circular, in relation to the openings of the first component 4.

La figure 2 illustre une variante de réalisation du panneau de la figure 1, selon laquelle entre le tissu métallique 6 et la seconde composante structurale 7 est interposée une composante intermédiaire 10 de renfort de l'action de la première composante structurale 4. A cet effet, la composante intermédiaire 10 comporte des fibres par exemple de carbone ou de verre orientées parallèlement à la direction de l'écoulement aérodynamique et comporte un taux de surface ouverte en correspondance avec celui de la première composante structurale 4.The figure 2 illustrates an alternative embodiment of the panel of the figure 1 , according to which between the metal fabric 6 and the second structural component 7 is interposed an intermediate component 10 for reinforcing the action of the first structural component 4. For this purpose, the intermediate component 10 comprises fibers, for example carbon fibers or oriented parallel to the direction of the aerodynamic flow and has an open area ratio corresponding to that of the first structural component 4.

De préférence, la résine d'imprégnation des fibres de la composante 10 est une résine de type thermoplastique assurant une meilleure liaison avec le tissu métallique 6.Preferably, the fiber impregnating resin of the component 10 is a thermoplastic-type resin providing a better bond with the metal fabric 6.

La composante 10 peut être, comme illustré, identique à la composante 4, c'est-à-dire formée d'une ou plusieurs tôles composites comportant des fibres unidirectionnelles ou tissées, percées d'ouvertures 11 analogues aux ouvertures 5 et en regard de ces dernières.The component 10 may 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 openings 11 similar to the openings 5 and opposite these last.

La composante 10 peut bien entendu avoir une constitution différente de celle représentée, en fonction notamment de celle de la composante 4.The component 10 can of course have a constitution different from that shown, in particular as a function of that of the component 4.

Il est à noter que l'âme alvéolaire 1 peut être constituée de plusieurs couches séparées par des septums.It should be noted that the alveolar core 1 may consist of several layers separated by septa.

Claims (12)

  1. A multi-component acoustically resistive layer for an acoustic attenuation panel of the type consisting of an alveolar core (1) flanked, on the incident sound wave side, by an acoustic damping layer (2) and, on the opposite side, by a rear reflector (3), characterised in that it comprises:
    - a first structural component (4) in contact with the aerodynamic flow and formed by at least one layer of fibres connected by a suitable resin and oriented in the direction of the aerodynamic flow, said component (4) having a suitable open surface ratio;
    - a dissipating component (6) disposed against the face of said first component (4) opposite to said flow, formed from a metal fabric;
    - and a second structural component (7) formed from at least one layer of fibres bound by a suitable resin, oriented orthogonally to said direction of aerodynamic flow, said second structural component (7) being bound to said alveolar core (1) and having a suitable open surface ratio.
  2. A layer according to claim 1, characterised in that the fibres of the first and second structural components (4, 7) comprise unidirectional strands or layers.
  3. A layer according to claim 1, characterised in that the first and second structural components (4, 7) comprise a fabric whose threads, weft or warp, are parallel to said direction of aerodynamic flow.
  4. A layer according to claim 2, characterised in that the fibres are carbon or glass fibres.
  5. A layer according to one of claims 1 to 4, characterised in that the fibres of the first structural component (4) are pre-impregnated with a thermoplastic resin.
  6. A layer according to one of claims 1 to 4, characterised in that the fibres of the second structural component (7) are pre-impregnated with a thermosetting resin.
  7. A layer according to one of claims 1 to 6, characterised in that the first structural component (4) has non-circular openings in it, in particular rectangular openings (5) oriented parallel to said direction of aerodynamic flow.
  8. A layer according to one of claims 1 to 7, characterised in that the dissipating component (6) is a metal fabric, in particular stainless steel.
  9. A layer according to one of claims 1 to 8, characterised in that the second structural component (7) is formed from parallel strands of fibres (9) forming between them a given spacing (8).
  10. A layer according to one of claims 1 to 9, characterised in that it also comprises an intermediate component (10) for reinforcing the first structural component (4), interposed between the dissipating component (6) and the second structural component (7), formed and disposed in an identical manner to the first structural component (4).
  11. A layer according to claim 10, characterised in that the first structural component (4) and the intermediate component (10) comprise at least one sheet of composite material with rectangular openings (5, 11) in it, the openings in the two components (4, 10) being opposite each other.
  12. An acoustic attenuation panel comprising at least one splice, comprising one or more segments or sectors, the edges of which are joined by splicing and each provided with an acoustically resistive layer according to any one of claims 1 to 11.
EP03362003A 2002-04-17 2003-04-15 Multicomponent acoustically-resistive layer for a sound-absorbing panel and panel having such a layer Expired - Lifetime EP1355294B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0204801A FR2838860B1 (en) 2002-04-17 2002-04-17 MULTICOMPONENT ACOUSTICALLY RESISTIVE LAYER FOR ACOUSTICAL ATTENUATION PANEL AND PANEL THUS OBTAINED
FR0204801 2002-04-17

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EP1355294A1 EP1355294A1 (en) 2003-10-22
EP1355294B1 true EP1355294B1 (en) 2008-07-16

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EP03362003A Expired - Lifetime EP1355294B1 (en) 2002-04-17 2003-04-15 Multicomponent acoustically-resistive layer for a sound-absorbing panel and panel having such a layer

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US (1) US6840349B2 (en)
EP (1) EP1355294B1 (en)
AT (1) ATE401643T1 (en)
CA (1) CA2425364C (en)
DE (1) DE60322140D1 (en)
FR (1) FR2838860B1 (en)

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US20040016595A1 (en) 2004-01-29
CA2425364A1 (en) 2003-10-17
FR2838860A1 (en) 2003-10-24
US6840349B2 (en) 2005-01-11
FR2838860B1 (en) 2005-01-21
ATE401643T1 (en) 2008-08-15
EP1355294A1 (en) 2003-10-22
CA2425364C (en) 2011-04-05
DE60322140D1 (en) 2008-08-28

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