EP1380027B1 - Lärmdämpfungsplatte mit widerstandschicht mit verstärktem strukturteil - Google Patents

Lärmdämpfungsplatte mit widerstandschicht mit verstärktem strukturteil Download PDF

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Publication number
EP1380027B1
EP1380027B1 EP02738201A EP02738201A EP1380027B1 EP 1380027 B1 EP1380027 B1 EP 1380027B1 EP 02738201 A EP02738201 A EP 02738201A EP 02738201 A EP02738201 A EP 02738201A EP 1380027 B1 EP1380027 B1 EP 1380027B1
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EP
European Patent Office
Prior art keywords
holes
layer
attenuation panel
acoustic attenuation
panel according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP02738201A
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English (en)
French (fr)
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EP1380027A1 (de
Inventor
Alain Porte
Jacques Lalane
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Airbus Operations SAS
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Airbus Operations SAS
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Publication date
Application filed by Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP1380027A1 publication Critical patent/EP1380027A1/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
    • G10K11/162—Selection of materials
    • G10K11/168—Plural layers of different materials, e.g. sandwiches

Definitions

  • the present invention relates to acoustic attenuation panels, in particular panels intended to be mounted in the nacelle walls of aircraft turbojets, in reactor housings, in ducts to be soundproofed and, in general , panels combining good properties both acoustic and structural strength.
  • 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 invention aims more precisely panels of the latter type, that is to say having a resistive layer structural component facing the incident sound wave, but also applies to panels whose resistive layer has a component structural interposed between the dissipative component and the honeycomb structure.
  • the structure of the panel according to EP 0 911 803 has the disadvantage of a resistive layer formed of two superposed metal layers, namely a fabric and a sheet.
  • the metal used to make the metal fabric is preferably stainless steel, while the structural layer is aluminum foil.
  • the use of two metals of different structure induces corrosion by the appearance of a galvanic couple.
  • the density, although low, of the metals used substantially increases the mass of the acoustic panel.
  • sandwich type acoustic attenuation panels having an acoustically resistive layer formed of a non-metallic pierced sheet used alone or in combination with a porous layer.
  • these sheets are generally made of plastics with high temperature resistance or fiber-reinforced plastics, especially graphite.
  • these sheets metallic or non-metallic combining structural and acoustic characteristics, all have circular perforations, aligned or substantially staggered.
  • the present invention aims precisely to overcome these disadvantages.
  • the subject of the invention is an acoustic attenuation panel according to claim 1.
  • the smallest dimension of the holes is greater than or equal to 0.5 mm and the largest dimension is greater than or equal to 1.5 times the smallest.
  • the largest dimension of the holes is parallel to the direction of the main efforts to be supported.
  • the largest dimension of holes is parallel to the longitudinal axis of the motor and the holes are distributed in alignments both parallel to said axis of the motor and orthogonal to the latter.
  • the perforated structural layer consists of mineral or organic fibers, natural or synthetic, impregnated with a polymerized thermosetting or thermoplastic resin.
  • the fibers may be unidirectional and parallel in particular to said direction of main efforts.
  • the fibers may also be in the form of a fabric or a stack of fabrics whose weft or warp threads are parallel to said direction of main efforts.
  • the shape of the holes is selected from the group consisting of rectangular, oblong, hexagonal shapes.
  • the panels produced in accordance with the invention have the essential advantage that the thus perforated structural layer offers, compared with a perforated structural layer of the prior art and with an even open surface area, a better distributed material between the holes. that is to say, grouped according to one and / or the other of the two preferred axes defined respectively by the largest dimension and the smallest dimension of the holes.
  • said inter-hole material is grouped into wider strips or corridors between the hole alignments, thus allowing a more efficient transfer of forces, via said strips, to the structures surrounding the panels.
  • Such an improvement in the transfer of forces can be obtained by maintaining an open area ratio of the structural layer adapted to the desired acoustic attenuation conditions, while minimizing the thickness of said structural layer.
  • the particular shape and arrangement of the perforated holes make it possible to best preserve the continuity of the fibers, in particular to the right of said strips or inter-perforations corridors, thus ensuring a better transfer of efforts.
  • FIG. 1 diagrammatically shows a sandwich structure of the acoustic attenuation panel according to the invention, comprising a cellular central structure 1 flanked, on one side, by an acoustically resistive layer 2 called before, formed of two components , and on the other side, a layer 3, said rear, forming a total reflector.
  • the cellular central structure 1 is formed, in the embodiment shown, of a single layer of honeycomb type. Of course, several layers of honeycomb separated by septa may be provided, in the known manner, to form several superimposed resonators.
  • the resistive layer 2 is said before in that it is in contact with the aerodynamic flow or the gaseous medium in which the sound waves to be damped move.
  • the layer 2 comprises a so-called structural component 2a, responsible for transferring the mechanical, aerodynamic and inertial forces to the crankcase, in the case of the use of such a panel for upholstering for example the outer wall delimiting the fan duct. a turbojet.
  • This structural layer 2a directly in contact with said aerodynamic flow also has an acoustic role because it must pass the sound waves towards the resonator (s) and, for this purpose, is pierced with openings or holes 4, of shape and distributions in accordance with the invention.
  • the second component 2b of the resistive layer is interposed between the structural layer 2a and the cellular layer 1 and formed in the known manner of a layer of breathable material, for example a fabric or a superposition of metal fabrics formed of stainless steel wire, or one or more carbon fiber fabrics.
  • a layer of breathable material for example a fabric or a superposition of metal fabrics formed of stainless steel wire, or one or more carbon fiber fabrics.
  • the rear layer 3 is for example and also in the known manner, a non-perforated aluminum foil.
  • the structural layer 2a is formed of a rigid or semi-rigid sheet material, which may be a metal, such as aluminum or stainless steel, a composite material, such as a plastic material with a high temperature resistance or a plastic material reinforced with fibers, in particular graphite, or a composite material consisting of mineral or organic fibers, natural or synthetic, impregnated with a polymerized thermosetting or thermoplastic resin.
  • a rigid or semi-rigid sheet material which may be a metal, such as aluminum or stainless steel, a composite material, such as a plastic material with a high temperature resistance or a plastic material reinforced with fibers, in particular graphite, or a composite material consisting of mineral or organic fibers, natural or synthetic, impregnated with a polymerized thermosetting or thermoplastic resin.
  • the layer 2a is unique or well formed by the superposition of several layers of strips such as those shown in FIG.
  • the layer 2a is identically pierced with identical, rectangular holes 4 aligned in both the lengthwise direction and the widthwise direction.
  • the two superimposed components 2a, 2b are schematically represented in plan view.
  • the holes 4 have a length to width ratio of 2 and their longitudinal axis is parallel to the direction 5 of passage of the main forces to be supported by the panel.
  • This direction 5 corresponds, for a turbojet for example, to the axis of the engine, which exerts its thrust, as well as during the reverse thrust, along its axis.
  • FIG. 3 shows in comparison a conventional two-component resistive layer 2'a, 2'b corresponding to components 2a, 2b of the invention.
  • the component 2'a is made of the same material as the component 2a, has the same surface as the latter and same total open area, the openings being constituted by a regular distribution of circular holes 4 'equidistant from each other and aligned to both following the direction 5 ' counterpart of the direction 5 of Figure 2 and in a direction 6 'perpendicular to the direction 5' and homologous to the direction 6 of Figure 2.
  • the gap 7 between two rows of holes 4 is greater than the interval 7 'between two homologous alignments of holes. 4 'and in the component 2a, the sum of the intervals 7 (including the outer intervals) is greater than the sum of the intervals 7' of the component 2'a.
  • the total width of material that is to say the sum of the intervals 7, available to transfer the forces in the direction 5, is very substantially greater than the corresponding total width of material in the component 2'a.
  • the component 2a according to the invention therefore has a better mechanical strength in the direction 5.
  • the direction 5 is also that of the aerodynamic flow in a motor, the holes 4 are also aligned in the direction of this flow in the air inlet duct, which minimizes the aerodynamic drag.
  • the perforation of the layer 2a gives the acoustic attenuation panels fitted to the air intakes of turbojets a better passage of the main forces, mechanical, aerodynamic and inertial, while maintaining a surface ratio open adapted to said panels, while minimizing the thickness of said structural layer 2a.
  • the perforation according to the invention of the structural layer 2a is particularly advantageous in the case where said layer 2a is made from fibers, for example carbon, glass or "Kevlar", pre-impregnated with a suitable resin.
  • the component 2a is constituted from a unidirectional fiber ply parallel to the direction 5 of the main forces, the fibers in the corridors between the alignments in the direction 5 of the holes 4 will not be cut during the perforations and thus ensure a transfer of effort to the maximum of their capacity.
  • the weft and warp threads of the fabric or fabrics are advantageously arranged parallel to the directions 5 and 6 so as to have the least fiber cut during the perforation of the holes 4, both parallel to the direction 5 and parallel to the direction 6.
  • the perforation of the holes 4 is carried out by any appropriate means, for example by punching, all the holes 4 of a band being perforated in a single pass with the aid of a multi-punch press.
  • the perforations are made for example on rectangular strips of dimensions appropriate to those of the panel to be made, flat, regardless of the nature of the constituent material. The strips will then be put in place according to the type of panel to be made.
  • the composite material In the case of fibers pre-impregnated with resin, the composite material will be consolidated by polymerization of the resin, before being perforated.
  • the direction of the main efforts (5) of course depends on the type of panel to achieve and its destination. Those skilled in the art will know in each case to determine this direction and to adapt the alignment of the holes 4.
  • the ratio between length and width of the holes 4 is obviously variable. Preferably, it will be greater than or equal to 2.
  • the alignment of the holes 4 may be only in one direction, the direction 5 for example as illustrated in Figure 4 in which the distribution of said holes 4 in the component 2 "is substantially staggered.
  • the shape of the perforated holes in the structural layer according to the invention may vary insofar as this shape lends itself to the realization of a passage opening having two main perpendicular axes, one of which is substantially more long than the other so as to allow the structural layer a better passage of the efforts along one or other of the two aforementioned axes.
  • Figures 5 and 6 illustrate two further embodiments of elongated holes.
  • the component 2 "'has holes 4" distributed as the rectangular holes 4 of Figure 2 and oblong, including rectangular with rounded ends.
  • the component 2 IV has 4 "holes distributed as those of Figure 5 and also oblong shape, namely rectangular with tips ends, or hexagonal.
  • the elongated shape of the holes combined with an alignment of all the holes in the direction of their elongation makes it possible, with respect to circular holes and with the same opening ratio, to obtain a structural layer ensuring better transfer of forces in the direction of the greatest length of the elongated holes, regardless of the desired opening rate.

Claims (8)

  1. Lärmdämpfungsplatte umfassend mindestens eine Schicht einer wabenartigen Struktur (1), die flankiert ist auf einer Seite von einer widerstandsfähigen Schicht (2), bestehend aus mindestens einer luftdurchlässigen Schicht (2b) und mindestens einer perforierten Strukturschicht (2a), und auf der anderen Seite von einer Totalreflexionsschicht (3), wobei die Strukturschicht (2a) mit identischen, nicht runden Löchern versehen ist, deren Achsen entlang ihrer kleinsten Dimension und entlang ihrer größten Dimension jeweils rechtwinklig zueinander stehen, und die Löcher wenigstens in Richtung ihrer Ausdehnung ausgerichtet sind, dadurch gekennzeichnet, dass
    - die größte Dimension der Löcher (4,4",4"') parallel zur Richtung der wesentlichen aufzunehmenden Beanspruchungen verläuft,
    - das Material der Strukturschicht (2a, 2"a, 2'''a, 2IVa) ausgewählt ist aus der Gruppe umfassend die Kompositmaterialen bestehend aus natürlichen oder synthetischen Mineralfasern oder organischen Fasern, die mit einem polymerisierten, thermisch härtbaren oder thermoplastischen Harz getränkt sind,
    - das Material der Strukturschicht (2a, 2", 2"'a, 2IVa) einseitig gerichtete Fasern enthält, die parallel zur größten Dimension (5) der Löcher (4, 4", 4'") ausgerichtet sind, oder ein oder mehrere Gewebe enthält, deren Schussfäden oder Kettfäden angeordnet sind in Richtung der größten bzw. der kleinsten Dimension der Löcher (4, 4", 4"').
  2. Lärmdämpfungsplatte nach Ansprach 1, dadurch gekennzeichnet, dass die kleinste Dimension der Löcher (4) größer oder gleich 0,5 mm und die größte Dimension großer oder gleich 1,5 mal die kleinste Dimension ist.
  3. Lärmdämpfungsplatte nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die Löcher ausgewählt sind aus der Gruppe umfassend rechteckige Löcher (4), längliche Löcher, insgesondere mit abgerundeten Enden (4") oder mit Spitzen (4'"), und sechseckige Löcher.
  4. Lärmdämpfungsplatte nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Löcher (4, 4", 4'") in zwei zueinander rechtwinkligen Richtungen (5, 6) ausgerichtet sind.
  5. Lärmdämpfungsplatte nach einem der Ansprüche 1 bis 4, insbesondere vorgesehen zur Auskleidung der Wandung der Gondel einer Strahlturbine, dadurch gekennzeichnet, dass die die größte Dimension der Löcher (4, 4", 4''') parallel zur Längsachse (5) des Motors ist.
  6. Lärmdämpfungsplatte nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Fasern ausgewählt sind aus der Gruppe umfassend Karbonfasern, Glasfasern und Kevlarfasern.
  7. Lärmdämpfungsplatte nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass das Material der Strukturschicht (2a, 2'"a, 2IVa) ein oder mehrere Gewebe umfasst, deren Schuss- und Kettfäden angeordnet sind in Richtung der größten Dimension bzw. in Richtung der kleinsten Dimension der Löcher (4, 4", 4'").
  8. Lärmdämpfungsptatte nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die luftdurchlässige Schicht (2b) zwischen der wabenartigen Schicht (1) und der Strukturschicht (2a) liegt.
EP02738201A 2001-04-17 2002-04-17 Lärmdämpfungsplatte mit widerstandschicht mit verstärktem strukturteil Expired - Lifetime EP1380027B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0105209 2001-04-17
FR0105209A FR2823590B1 (fr) 2001-04-17 2001-04-17 Panneau d'attenuation acoustique comportant une couche resistive a composante structurale renforcee
PCT/FR2002/001322 WO2002084642A1 (fr) 2001-04-17 2002-04-17 Panneau d'attenuation acoustique comportant une couche resistive a composante structurale renforcee

Publications (2)

Publication Number Publication Date
EP1380027A1 EP1380027A1 (de) 2004-01-14
EP1380027B1 true EP1380027B1 (de) 2008-02-06

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EP02738201A Expired - Lifetime EP1380027B1 (de) 2001-04-17 2002-04-17 Lärmdämpfungsplatte mit widerstandschicht mit verstärktem strukturteil

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Country Link
US (1) US7484592B2 (de)
EP (1) EP1380027B1 (de)
AT (1) ATE385602T1 (de)
CA (1) CA2441477C (de)
DE (1) DE60224924T2 (de)
FR (1) FR2823590B1 (de)
WO (1) WO2002084642A1 (de)

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Also Published As

Publication number Publication date
ATE385602T1 (de) 2008-02-15
US7484592B2 (en) 2009-02-03
FR2823590A1 (fr) 2002-10-18
WO2002084642A1 (fr) 2002-10-24
CA2441477A1 (fr) 2002-10-24
EP1380027A1 (de) 2004-01-14
CA2441477C (fr) 2010-12-07
DE60224924D1 (de) 2008-03-20
US20040148891A1 (en) 2004-08-05
FR2823590B1 (fr) 2003-07-25
DE60224924T2 (de) 2009-04-16

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