• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates in particular to an acoustic attenuation structure for an aircraft propulsion unit, comprising an acoustically reflecting wall and a sandwich panel, the sandwich panel comprising a honeycomb structure framed by two acoustically porous skins, a rear skin and a skin. the acoustically reflecting wall and the sandwich panel being arranged to be separated by a layer of air.
    公开号:FR3039517A1
    申请号:FR1557431
    申请日:2015-07-31
    公开日:2017-02-03
    发明作者:Laurent Georges Valleroy；Marc Versaevel；Bertrand Desjoyeaux；Patrick Gonidec
    申请人:Aircelle SA；
    IPC主号:
    专利说明:

    The invention lies in the field of acoustic attenuation for aircraft propulsion assembly, that is to say the assembly formed by a turbojet (including a turbofan engine) equipped with a nacelle, the propulsion unit that may possibly include the engine mast.
    In an aircraft propulsion system, the acoustic attenuation is generally performed by means of acoustic attenuation panels. Such panels may take the form of a sandwich structure, comprising a cellular core framed between two skins, one full and the other perforated so as to be acoustically porous. The perforated skin, generally called acoustic skin, is intended to be in contact with the cold air flow passing through the nacelle and / or with the flow of hot gases ejected by the turbojet engine.
    Sound attenuation panels with a degree of freedom of acoustic waves, known as SDOF acoustic panels (for "Single Degree Of Freedom"), are known. Such panels take the form of a sandwich structure as described above.
    Acoustic attenuation panels with two degrees of freedom, known as 2DOF (or Double Degree Of Freedom) acoustic panels, are also known. Unlike SDOF-type panels, DDOF-type panels comprise a two-storey cellular structure, these floors being separated by an acoustically porous wall commonly called a septum. As for the previously described panels, this honeycomb structure is sandwiched between an acoustically reflecting skin and an acoustically porous skin. The DDOF panels have the advantage of attenuating the acoustic waves over a wider frequency band than an SDOF panel. In general, the height of the honeycomb structure (and therefore the height of the cavities that it comprises) and the porosity of the acoustic skin and, where appropriate, the septum are optimized so as to maximize the acoustic attenuation and to target the right sound frequency range. On the other hand, the greater the acoustically treated surface within a propulsion unit (and in particular within a nacelle) is important, the better the overall performance of the acoustic attenuation. The builders thus deploy permanent efforts to increase the acoustically treated surface.
    Figures la and lb show a view of a propulsion unit comprising a nacelle 1 surrounding a turbofan engine, the assembly being integral with a motor pylon 5 (visible only in Figure lb). The nacelle 1 conventionally comprises an air inlet 2, a median section 3 and a rear section 4. FIG. 1a shows the nacelle 1 in "direct jet" configuration, that is to say with the thrust reversal system in the retracted position, while Figure lb shows the nacelle in "reverse jet" configuration, that is to say with the thrust reversal system in the deployed position. Thus it can be seen in FIG. 1b that a movable cowl 20 of the rear section 4 is in the retracted position, revealing a set of reversing gates 21.
    Figures 2a and 2b show a section of the rear section 4 of the nacelle 1, respectively when the reverse thrust system is in the retracted position (or direct jet) and deployed position (or reverse jet).
    The thrust reverser system comprises a movable hood 20, which forms the outer surface of the rear section 4 of the nacelle. The thrust reversal system further comprises reversing grids 21 and locking flaps 22, rotatable, and associated with connecting rods 23. The thrust reverser system comprises actuators (not shown), in particular electromechanical actuators, for sliding the movable cowl between a retracted position (Figure 2a) and an extended position (Figure 2b), and vice versa. This translation takes place along a longitudinal axis of the nacelle, corresponding to the longitudinal axis of the engine.
    When the thrust reverser system is in the retracted position (FIG. 2a): the moving cowl is in the retracted position, corresponding to an advanced position in which it ensures the aerodynamic continuity with the median section of the nacelle; - The locking flaps 22 are in retracted position, in which position they are aligned with the inner surface of the movable cover 20, and housed in a shell 27 of the movable cover 20;
    When the thrust reverser system is in the deployed position (FIG. 2b): the movable cowl is in the extended position, corresponding to a retracted position, in which it discovers the reversing grids 21; - The locking flaps 22 are in the deployed position, in which they at least partially obstruct the vein 24 of cold flow.
    In this configuration, the action of the locking flaps 22 and the inversion gates 21 makes it possible to redirect the cold flow outside the nacelle forwardly in order to create a counter-thrust. The passage in the deployed position of the locking flaps 22 is in the example obtained by the action of connecting rods 23 attached to an internal fixed structure 25 of the nacelle.
    It is known to provide an acoustic attenuation panel 26 on the locking flaps. Examples of acoustically treated blocking shutters are shown in Figures 3a and 3b, which show a longitudinal sectional view of a locking flap. FIGS. 3a and 3b thus show a locking flap 24 equipped with an acoustic attenuation panel 26, respectively with a simple degree of freedom and with a double degree of freedom.
    In FIG. 3a, it can be seen that the acoustic attenuation panel 26 with a degree of freedom comprises a full back skin 28 and a front skin 29, these two skins framing a cellular core 30. The front skin 29 is multi-perforated and therefore acoustically porous. The front skin 29 forms the outer surface of the locking flap 24.
    The search for maximum noise reduction of aircraft propulsion systems has led manufacturers to consider acoustic attenuators with two degrees of freedom.
    Thus, in FIG. 3b, the acoustic attenuation panel 26, with two degrees of freedom, is formed by a solid skin 28 and a perforated skin 29 surrounding a cellular core 30. However, the cellular structure comprises two stages separated by a septum 31. This thus makes it possible to improve the acoustic attenuation performance, especially in medium and high sound frequencies, but leads to expensive and heavy acoustic panels.
    In addition, the acoustic attenuation panel 26 being installed in the shell 27, it must be dimensioned to accommodate the locking flaps (and therefore the sound attenuation panel 26), when the blocking flaps are in position retracted. The size of the acoustic attenuation panel thus constitutes a disadvantage because it requires in this example to increase the dimensions of the shell, and ultimately the nacelle. The invention aims to provide an acoustic attenuation structure with at least two degrees of freedom, adaptable in particular to a thrust reversal blocking louver, which allows to gain space and also mass. For this purpose, the invention relates to an acoustic attenuation structure for an aircraft propulsion assembly, comprising an acoustically reflecting wall and a sandwich panel, the sandwich panel comprising a honeycomb structure framed by two acoustically porous skins, a rear skin and a front skin, the acoustically reflecting wall and the sandwich panel being arranged to be separated by a layer of air.
    Thus, the acoustic attenuation structure in accordance with the invention makes it possible to obtain acoustic attenuation equivalent to that obtained with the known DDOF acoustic attenuation panels. The invention provides compared to these known panels a saving in mass and simplicity of manufacture, since a single-stage honeycomb structure is sufficient. In addition, the acoustic attenuation structure according to the invention can be made on elements that are movable relative to each other, such as for example a thrust reverser locking flap and a ferrule on which this flap is articulated.
    In one embodiment, the panel sandwich panel is integral with a movable member, in particular rotatable, with respect to the acoustically reflecting wall.
    In one embodiment, the sandwich panel is removably attached to the acoustically reflecting wall.
    In one embodiment, the acoustically reflecting wall comprises at least one partition extending towards the rear skin of the sandwich panel.
    In one embodiment, the rear skin of the sandwich panel comprises at least one partition extending towards the acoustically reflecting wall.
    In one embodiment, the structure comprises at least one seal disposed facing the free end of a partition.
    In one embodiment, the sandwich panel has a plurality of honeycomb structures that are separated from each other by an acoustically porous septum.
    In one embodiment, the porosity of the back skin of the sandwich panel is between 1% and 5%.
    In one embodiment, the porosity of the front skin of the sandwich panel is between 8% and 20%.
    In one embodiment, the air layer has a thickness of between 10 and 40 millimeters.
    In one embodiment, the honeycomb structure has a thickness of between 10 and 30 millimeters.
    In one embodiment, the rear skin of the sandwich panel comprises a lattice, in particular a wire mesh. The invention also relates to an aircraft propulsion unit comprising one or more acoustic attenuation structures according to that defined above.
    In one embodiment, the propulsion unit comprises a nacelle equipped with a thrust reversal system, the thrust reversal system comprising at least one locking flap comprising the sandwich panel of the acoustic attenuation structure.
    In one embodiment, the acoustically reflecting wall is formed by a wall of a ferrule on which the locking flap is hinged.
    In one embodiment, the propulsion unit comprises a turbojet engine comprising a fan casing, the fan casing having an inner surface forming the acoustically reflecting wall, the sandwich panel being removably attached to the fan casing.
    In one embodiment, the propulsion unit comprises an ejection nozzle whose inner surface forms the acoustically reflecting wall, the sandwich panel being removably attached to the ejection nozzle. The invention further relates to an aircraft comprising at least one propulsion unit as defined above. The invention will be better understood and other features and advantages will emerge more clearly on reading the following description, given by way of example with reference to the appended drawings, among which: FIGS. 1a and 1b represent a propulsion unit aircraft; Figures 2a and 2b show a sectional view of a rear section of nacelle turbojet turbofan; FIGS. 3a and 3b show a thrust reverser locking louver provided with an acoustic attenuation panel; Figures 4 to 8 are partial sectional views of a nacelle comprising an acoustic attenuation structure according to the invention; Figures 9 and 10 show embodiments of a sandwich panel according to the invention; FIG. 11 is a graph describing acoustic attenuation performance as a function of frequency, for an attenuation structure according to the invention and for two known attenuation structures.
    FIG. 4 shows a partial sectional view of a rear section of a nacelle 40 of a double-flow turbojet engine. The secondary flow (or cold air flow) flowing through the nacelle when the thrust reversal system is not deployed is represented by the arrow F. The nacelle 40 is for example similar to the nacelle 1 of FIGS. and lb. The nacelle 40 thus comprises a thrust reversal system, comprising in particular a movable cover 41 and a plurality of locking flaps 42. In FIG. 4, the thrust reversal system is represented in a "direct jet" configuration, the mobile cover 41 and the locking flap 42 is therefore in the retracted position. Thus, the locking flap 42 is housed in a shell 43 integral with the movable cover 41. The shell 43 has a solid wall 44 whose inner surface 45 facing the locking flap 42 is acoustically reflective.
    The locking flap 42 is acoustically treated in accordance with the invention. It thus comprises a sandwich panel 46 comprising a honeycomb structure 47 framed between two skins, a rear skin 48 and a front skin 49. The front skin 49 forms the outer surface of the locking flap 42. The honeycomb structure comprises in the example a plurality of partitions 47a. The honeycomb structure 47 may be formed in known manner by a honeycomb structure.
    According to the invention, the two skins 48, 49 flanking the cellular structure 47 are perforated (so as to be acoustically porous). Thus, the sandwich panel 46 forms the first stage of a sound attenuation structure with two degrees of freedom, the second stage being formed by the space 50 between the inner surface 45 of the shell 43 and the rear skin 48 of the panel sandwich 46. The acoustic attenuation structure according to the invention therefore comprises in the example of Figure 4 an acoustic skin formed by the front skin 49 and a full skin formed by the wall 44 of the ferrule 43, this wall being full and is therefore acoustically reflective. Furthermore, the perforated rear skin 48 of the sandwich panel 46 forms the septum of this acoustic attenuation structure with two degrees of freedom. The height of the second stage (referenced H2 in FIG. 5) will represent between 40% and 80% of the cumulative height of the first (height h1 in FIG. 5) and the second stage of the structure. The perforation rate of the front skin 49 will for example be between 8% and 20%, while the perforation rate of the rear skin 48 will for example be between 1% and 5%.
    The operating principle of the acoustic attenuation structure according to the invention is therefore analogous to that of a conventional acoustic attenuation panel with two degrees of freedom.
    The acoustically porous front skin 49 is in direct contact with the secondary flow passing through the nacelle (direct jet). Acoustic waves can therefore partially pass through the skins before 49 and back 48, which are both porous. The honeycomb structure 47 imposes a plane propagation within the sandwich panel 46. The waves also propagate in the air layer 50a located in the space 50 (or cavity 50) between the shell 43 and the rear skin 48 of the sandwich panel 46. The waves are reflected by the wall 44 of the ferrule 43. Although the cavity 50 of FIG. 4 is not provided with partitions such as a conventional honeycomb structure, the propagation of the acoustic waves and the effectiveness of the acoustic attenuation are very close to those of a conventional DDOF acoustic attenuation panel.
    The acoustic attenuation structure according to the invention behaves substantially like a panel of the DDOF type, while being lighter and less cumbersome. In addition, a result equivalent to the known attenuation panels is obtained in a simpler and more economical way, since only one sandwich structure (single-stage) is necessary. The invention thus provides many gains over the state of the art, and in particular a saving in weight, bulk, economic, all with identical acoustic performance.
    In a variant shown in FIG. 5, a plurality of partitions 51 extending from the wall 44 of the shell 43 may be provided towards the rear skin 48 of the sandwich panel 46. Advantageously, the height of the partitions 51 is such that their free end is in close proximity to the rear skin 48 of the sandwich panel 46 (for example at a distance of between 1 and 5 millimeters).
    The partitions 51 are in the example of Figure 5 parallel to each other (and further substantially parallel to the partitions of the honeycomb structure 47). As a variant, some of the partitions 51 may also be arranged perpendicular to the others and / or intersecting one another, to form an array of cells.
    The partitions 51 make it possible to confine the propagation of the acoustic waves within the air layer 50a located in the space (or cavity) 50, in order to improve the acoustic attenuation performance of the acoustic attenuation structure. according to the invention. In addition, these partitions 51, acting as stiffeners, improve the mechanical strength of the shell 6.
    In a variant shown in Figure 6, it is expected that partitions 52 extend from the rear skin 48 of the sandwich panel 46 to the wall 44 of the shell 43. Advantageously, the height of the partitions 52 is such that their free end is located in the immediate vicinity of the inner surface 45 of the wall 44 of the ferrule 43. Acoustic walls 53 have an acoustically sounding effect similar to that of the partitions 51 of FIG. 5. In addition, the partitions 52, while playing the role of stiffeners, make it possible to improve the mechanical strength of the sandwich panel 46 and thus of the blocking flap 42.
    Of course, it will be possible to provide both partitions 51, extending from the wall 44 of the ferrule 43, and partitions 52, extending from the rear skin 48 of the sandwich panel 46.
    In a variant shown in Figure 7, is provided opposite the free ends of the partitions 52 a network of seals 53 to achieve contact and / or sealing between the shell 43 and the partitions 52. This results in attenuation improved acoustic waves, these waves being better confined within the air layer 50a located between the inner surface 45 of the shell 43 and the rear skin 48 of the sandwich panel 46. The use of a flexible material for the seal 53 also makes it possible to withstand the mechanical vibrations between the partitions 52 and the shell 43.
    Of course, the use of joints 53 as shown in FIG. 7 can be adapted to the acoustic attenuation structure of FIG. 5 or to a structure comprising partitions 51, 52 some of which are arranged on shell 43 and for others on sandwich panel 46.
    It may further be provided that the network of joints 53 is fixed directly on the free end of the partitions 51 and / or 52, thus making it possible to compensate for any gaps between these partitions 51 and / or 52 and the wall 44 of the ferrule 43 or the back skin 48 of the sandwich panel 46.
    FIG. 8 shows an exemplary embodiment in which both partitions 51, extending from the wall 44 of the shell 43, and partitions 52, extending from the rear skin 48 of the sandwich panel 46 are provided. this example, it is expected that at least some of the partitions 51 of the ferrule 43 and the partitions 52 of the sandwich panel 46 are paired, the proximity of two partitions 51, 52 of a pair forming a baffle. The resulting baffle effect provides a sufficient seal to prevent the use of seals. More generally, the partitions 51 extending from the shell 43 and the partitions 52 extending from the rear skin 48 are positioned in different planes. Thus, the partitions 51, 52 fit into each other. Such a configuration, in addition to the stiffening of the shell 43 and the sandwich panel 46, allows a better channelization of the waves, while maintaining the mobility of the flap 42 relative to the shell 43. In another variant (not shown), the free ends of the partitions 51, 52 are substantially opposite each other. This makes it possible to establish points of contact between the two parts, thus defining the distance between the flap 42 and the ferrule 43.
    The acoustic attenuation structures shown in FIGS. 4 to 8 have the common point of being formed by the combination of the wall 44 of the ferrule 43 and the sandwich panel 46 of the locking flap 42. As mentioned above, this flap locking device is movable in rotation, and is to this effect hinged relative to the shell 43. Figure 9 shows an example of blocking flap 42 according to the invention, including a perforated skin 48 rear. In the example of Figure 9, the flap 42 further comprises partitions 52 extending from the rear skin 48. In order to be fixed to the shell 43, the locking flap 42 comprises yokes 54 to be associated with ferrules or clevises of ferrule 43 (not shown), all of these screeds and fittings being traversed by collinear axes to define the axis of rotation (shown in phantom in FIG. 9) of the shutter relative to the ferrule.
    Alternatively, it can be provided that the acoustic attenuation structure according to the invention does not comprise moving elements. For example, the acoustically reflecting wall may be formed by the inner surface of a fan casing or the inner surface of a nozzle, more generally any surface on which it is beneficial to rely to create a acoustic attenuator with at least two degrees of freedom. In this case, it will be provided that the sandwich panel 46 is fixed to the wall by means of all known removable fastening systems, such as screw-nut assemblies passing right through the two parts, screws tightened in inserts. The spacing between the sandwich panel 46 and the acoustically reflecting wall is made for example by means of fixing studs 55, as shown in FIG. 10 which fix the distance between the sandwich panel and the sandwich panel. the support ferrule to obtain the desired cavity height 50.
    Furthermore, in a variant not shown, it may be provided that the sandwich panel 46 comprises several superimposed cellular structures separated from each other by a porous septum, which makes it possible to obtain an acoustic attenuation structure behaving like an attenuation panel acoustic with three degrees of freedom or more.
    Advantageously, the rear skin 49 of the sandwich panel 46 may comprise a so-called linear acoustic structure then composed of a skin with a high porosity (of the order of 30 to 50%) covered with a very fine mesh (metallic or organic mesh). , or CMO, whose acoustic characteristics are such that the resistance after gluing of the linear skin is of the order of 30 rpm to 70 rpm cgs).
    FIG. 11 compares the acoustic attenuation performance obtained with a locking flap according to the invention (curve C1), with the performances obtained with a similar locking flap, but equipped with a conventional attenuation panel of type SDOF (curve C2), and a similar locking flap but equipped with a conventional attenuation panel of type DDOF (curve C3).
    In the diagram of Figure 11, there is shown the attenuation rate of acoustic waves, as a function of the frequency of the acoustic waves (expressed in hertz) abscissa.
    As can be seen in FIG. 11, an attenuation structure in accordance with the invention exhibits slightly degraded performances in low-medium frequencies (1000 Hz - 2500 Hz) compared to a conventional DDOF. On the other hand, a typical behavior of a DDOF at higher frequencies (from 3000 Hz) is obtained, where the solution according to the invention is much more efficient than a conventional SDOF. Thus, an attenuation structure according to the invention makes it possible to attenuate the acoustic waves over a much larger bandwidth than a panel of SDOF type (curve referenced C2), beyond 2800 Hz in the example presented , and a panel type DDOF (C3 curve) of the state of the art, with negligible loss of efficiency in low and medium frequency (1200Hz to 2500Hz in Figure 11).
    It is understood that the invention is not limited to an acoustic attenuation structure disposed in a thrust reverser, and that a structure according to the invention can be made within any suitable element in a nacelle or a propulsion unit.
    It goes without saying that the invention is not limited either to the embodiments described above as examples but that it includes all the technical equivalents and variants of the means described and their possible combinations.
    权利要求:
    Claims (18)
    [1" id="c-fr-0001]
    An acoustic attenuation structure for an aircraft propulsion assembly, comprising an acoustically reflecting wall (44) and a sandwich panel (46), the sandwich panel (46) having a framed honeycomb structure (47) by two acoustically porous skins, a back skin (49) and a front skin (48), the acoustically reflecting wall (44) and the sandwich panel (46) being arranged to be separated by an air layer (50a).
    [2" id="c-fr-0002]
    2. Structure (3) according to claim 1, characterized in that the panel (46) sandwich is secured to a movable member (42), in particular rotatable relative to the acoustically reflecting wall (44).
    [3" id="c-fr-0003]
    3. Structure according to claim 1 or 2, wherein the sandwich panel (46) is removably attached to the acoustically reflecting wall (44).
    [4" id="c-fr-0004]
    4. Structure according to any one of the preceding claims, characterized in that the acoustically reflecting wall (44) comprises at least one partition (51) extending towards the rear skin (48) of the sandwich panel.
    [5" id="c-fr-0005]
    5. Structure according to any one of the preceding claims characterized in that the rear skin (48) of the sandwich panel (46) comprises at least one partition (52) extending towards the acoustically reflecting wall (44).
    [6" id="c-fr-0006]
    6. Structure according to claim 4 or 5, characterized in that it comprises at least one seal (53) disposed opposite the free end of a partition (51, 52).
    [7" id="c-fr-0007]
    7. Structure according to any one of the preceding claims characterized in that the sandwich panel (46) comprises a plurality of honeycomb structures which are separated from each other by an acoustically porous septum.
    [8" id="c-fr-0008]
    8. Structure according to one of the preceding claims, wherein the porosity of the rear skin (48) of the sandwich panel (46) is between 1% and 5%.
    [9" id="c-fr-0009]
    9. Structure according to one of the preceding claims, wherein the porosity of the front skin (49) of the sandwich panel (46) is between 8% and 20%.
    [10" id="c-fr-0010]
    10. Structure according to one of the preceding claims, characterized in that the air layer (50a) has a thickness of between 10 and 40 millimeters.
    [11" id="c-fr-0011]
    11. Structure according to one of the preceding claims, wherein the honeycomb structure (47) has a thickness of between 10 and 30 millimeters.
    [12" id="c-fr-0012]
    12. Structure according to one of the preceding claims, wherein the rear skin (48) of the sandwich panel (46) comprises a lattice, including a wire mesh.
    [13" id="c-fr-0013]
    13. Aircraft propulsion unit comprising one or more structures according to any one of the preceding claims.
    [14" id="c-fr-0014]
    14. Propulsion unit according to the preceding claim, comprising a nacelle (40) equipped with a thrust reversal system, the thrust reversal system comprising at least one locking flap (42) comprising the sandwich panel (46). of the acoustic attenuation structure.
    [15" id="c-fr-0015]
    15. Propulsion unit according to the preceding claim, wherein the acoustically reflecting wall (44) is formed by a wall of a ferrule (43) on which the locking flap (42) is articulated.
    [16" id="c-fr-0016]
    16. Propulsion unit according to one of claims 13 to 15, comprising a turbojet comprising a fan casing, the fan casing having an inner surface forming the acoustically reflecting wall, the sandwich panel being removably attached to the fan casing.
    [17" id="c-fr-0017]
    17. propulsion unit according to any one of claims 13 to 16, characterized in that it comprises an ejection nozzle whose inner surface forms the acoustically reflecting wall, the sandwich panel being removably attached to the nozzle of ejection.
    [18" id="c-fr-0018]
    Aircraft comprising at least one propulsion unit according to one of claims 13 to 17.
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    同族专利:
    公开号 | 公开日
    US20180148187A1|2018-05-31|
    US10875659B2|2020-12-29|
    WO2017021628A1|2017-02-09|
    FR3039517B1|2019-05-17|
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    法律状态:
    2016-06-30| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-03| PLSC| Publication of the preliminary search report|Effective date: 20170203 |
    2017-06-29| PLFP| Fee payment|Year of fee payment: 3 |
    2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |
    2018-06-28| PLFP| Fee payment|Year of fee payment: 4 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1557431|2015-07-31|
    FR1557431A|FR3039517B1|2015-07-31|2015-07-31|ACOUSTIC ATTENUATION STRUCTURE WITH MULTIPLE DEGREES OF ATTENUATION FOR AN AIRCRAFT PROPULSIVE ASSEMBLY|FR1557431A| FR3039517B1|2015-07-31|2015-07-31|ACOUSTIC ATTENUATION STRUCTURE WITH MULTIPLE DEGREES OF ATTENUATION FOR AN AIRCRAFT PROPULSIVE ASSEMBLY|
    PCT/FR2016/051970| WO2017021628A1|2015-07-31|2016-07-28|Acoustic attenuation structure with a plurality of attenuation degrees for a propulsion assembly of an aircraft|
    US15/884,507| US10875659B2|2015-07-31|2018-01-31|Acoustic attenuation structure with a plurality of attenuation degrees for a propulsion assembly of an aircraft|
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