• 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:
    MULTILAYER ACOUSTIC TREATMENT PANEL. The invention relates to a multilayer acoustic treatment panel (100) comprising a first core with honeycomb structure (102) sandwiched between a perforated skin (104) and an intermediate skin (106), and a second core with honeycomb structure (108) sandwiched between intermediate skin and full skin (110). The perforated skin comprising at least a pair of highly porous areas that have a perforation rate higher than that of the rest of the perforated skin and which is formed by an entrance zone (114a) and an exit zone (114b) spaced longitudinally one on the other, the porosity zones of the same pair communicating through the first core with an alveolar structure and the intermediate skin with the two ends of a flow channel of sound waves (118) disposed in the second core with an alveolar structure.
    公开号:BR112012029277B1
    申请号:R112012029277-3
    申请日:2011-05-12
    公开日:2020-12-22
    发明作者:Jacques Michel Albert Julliard；Jacky Novi Mardjono；Georges Jean Xavier Riou；Benjamin André François Poirier；Jean-Michel Jean-François Ville
    申请人:Snecma；Centre National De La Recherche Scientifique；Universite De Technologie De Compiegne；
    IPC主号:
    专利说明:

    Background of the invention
    [0001] The present invention refers to the general domain of the so-called "passive" acoustic treatment.
    [0002] The field of application of the invention is notably, but not exclusively, that of aeronautical turbomachinery.
    [0003] The use of passive acoustic treatment panels is frequent in the field of aeronautics to reduce noise emissions from turbomachinery. For example, in the case of a double-body, double-flow turbo-reactor, such panels can be arranged on the inner face of the surrounding nacelle, but also on the outer face of its primary hood.
    [0004] A passive acoustic treatment panel is generally formed by a honeycomb hive structure covered by a thin porous layer that plays the pathway wallpaper and which is closed at the other end by a reflective layer from an acoustic point of view ( also called full skin). More complex panels with intermediate porous layers inserted between layers with honeycomb structures can be built to extend attenuation over a wider frequency range. The present invention aims more especially at such an acoustic treatment panel called "multilayer".
    [0005] Sound attenuation is known to be much more effective when the helical acoustic modes in which sound energy is propagated are of a high order. In fact, these acoustic modes remain in the ducts longer and have an energy closer to the wall that facilitates the dissipation of its energy by panels placed on the walls of the nacelle or turbo-reactor. On the other hand, the sound attenuation of an acoustic treatment panel evolves relatively linearly up to a certain treatment length and above, the sound attenuation grows significantly less quickly. Such behavior can be explained by the evolution of the characteristics of the sound source which, as it propagates on the panel, is less and less rich in high-order acoustic modes. As the sound attenuation depends on the acoustic modes present, the presence of small order acoustic modes in greater numbers to transport the remaining acoustic energy implies that the absorption efficiency of the panels is less. However, the acoustic treatment panels commonly used do not allow to meet these two requirements. Object and summary of the invention
    [0006] The present invention, therefore, has as main objective to correct such disadvantages proposing for this purpose to increase the efficiency of the acoustic treatments of the treated iso-surface acting for this on the characteristics of the sound source.
    [0007] This objective is achieved thanks to a multilayer acoustic treatment panel that comprises a first core of alveolar structure taken in sandwich between a perforated skin and an intermediate skin, and a second core of alveolar structure taken in sandwich between the intermediate skin and a full skin, panel in which, according to the invention, the perforated skin comprising at least a pair of highly porous areas which have a perforation rate higher than that of the rest of the perforated skin and which is formed by an entrance area and through an exit zone spaced longitudinally from each other, the areas of great porosity of the same pair communicating through the first core of alveolar structure and the intermediate skin with the two ends of a flow channel of sound waves disposed in the second core of alveolar structure.
    [0008] The presence of areas of great porosity in the perforated skin of the panel allows to create a large impedance rupture in a small portion, which leads to transfer part of the energy from the acoustic modes of small order to acoustic modes of high order which are easier to mitigate acoustically. In addition to this effect of converting acoustic modes, notably on broadband noise, the panel according to the invention allows, thanks to the presence of sound wave flow channels, to modify the path of one part of the sound wave captured through the entry zones to re-inject it in phase opposition to the further downstream zones. This allows to favor the attenuation of harmful frequencies that correspond to the operating ranges of the turbo-reactor. Thus, with iso-surface, it is possible to considerably improve the efficiency of the acoustic treatment panel.
    [0009] Zones of great porosity of the same pair can communicate with the flow channel of sound waves through wells that cross at the same time the first soul with alveolar structure and the intermediate skin.
    [00010] According to a variant of realization, the areas of great porosity of the same pair can communicate with the flow channel of sound waves through wells that cross the first core of alveolar structure and a plurality of holes made through intermediate skin.
    [00011] According to another variant of realization, the areas of great porosity of the same pair can communicate with the flow channel of sound waves through passages formed between the cavities of the first core with alveolar structure and a plurality of holes made through the intermediate skin.
    [00012] Preferably, the areas of the intermediate skin that cover the flow channel of sound waves are full.
    [00013] The flow channel of sound waves can be formed by a corridor delimited laterally by walls of the second core of alveolar structure. Alternatively, the flow channel of sound waves can be formed by a network of adjacent cavities of the second core with a honeycomb structure that communicate with each other through porous walls.
    [00014] Preferably, the perforated skin comprises a plurality of pairs of highly porous areas spaced transversely from each other. In this case, the entry zones and the exit zones can be aligned according to directions substantially transversal to the panel.
    [00015] The invention also has as object a turbo-reactor nacelle comprising at the level of an internal face at least one acoustic treatment panel as defined above. The perforated skin of the acoustic treatment panel is in this case preferably in contact with a flow path of a cold flow delimited on the outside by the internal face of the nacelle.
    [00016] The invention also has as its object a turbo-reactor that comprises, at the level of an external face, at least one acoustic treatment panel as previously defined. The perforated skin of the acoustic treatment panel is advantageously here in contact with a flow path of a cold flow delimited inside by the external face of the turbo-reactor. Brief description of the drawings
    [00017] Other characteristics and advantages of the present invention will stand out from the description made below, with reference to the accompanying drawings that illustrate examples of realization of the same devoid of any limiting character. In the figures: - figure 1 is a longitudinal sectional view of a turbo-reactor and its nacelle equipped with acoustic treatment panels according to the invention; figure 2 is an enlarged and highlighted view of a multilayer acoustic treatment panel according to the invention; figures 3A to 3C are sectioned in the direction of the thickness of acoustic treatment panels according to various embodiments of the invention; figures 4A and 4B are seen on the path side of acoustic treatment panels according to embodiments of the invention; and - figure 5 is a curve showing the gain of sound attenuation obtained by the acoustic treatment panel according to the invention. Detailed description of embodiments
    [00018] The invention relates to a passive acoustic treatment panel, notably of the type that equips an aircraft turbo-reactor and its nacelle such as those represented in figure 1.
    [00019] The turbo-reactor 10 represented in this figure 1 is of the double body type and double flow. It is surrounded by an annular nacelle 12 centered on a longitudinal axis X-X of the turbo-reactor. In a manner known per se, the turbo-reactor comprises, from upstream to downstream, a fan 14, a low pressure compressor 16, a high pressure compressor 18, a combustion chamber 20, a high pressure turbine 22 and a turbine low pressure 24.
    [00020] Nacelle 12 surrounds the primary hood 26 of the turbo-reactor being concentric to it to define a cold flow flow path 28. Likewise, the primary hood 26 surrounds the central body 30 of the turbo-reactor and is concentric to it to define hot flow flow path 32. Thus, path 28 is delimited radially, on the outside by the internal face of the nacelle, and on the outside, by the external face of the primary hood.
    [00021] For the sequence of the description, upstream and downstream are understood in relation to the flow direction of the gas flow through the turbo-reactor.
    [00022] The inner face of nacelle 12 comprises downstream of the fan 14 of the turbo-reactor acoustic treatment panels 100. The same is true for the primary hood 26, at the level of its outer face around the high pressure compressor 18 and the combustion 20. These acoustic treatment panels 100 have the function of attenuating the sound damage emitted by the turbo-reactor.
    [00023] Figure 2 represents in more detail an example of realization of an acoustic treatment panel 100 according to the so-called "multilayer" invention, that is, composed of a stacking of at least two stages of beehive structures.
    [00024] More precisely, panel 100 comprises a first honeycomb core 102 sandwiched between a perforated skin 104 and a partially perforated intermediate skin 106, and a second honeycomb core 108 sandwiched between the intermediate skin 106 and a full skin 110.
    [00025] The first honeycomb structure 102 is fixed (by gluing or brazing, for example) on the intermediate skin 106 that serves as support. Likewise, the second honeycomb structure 108 is attached to the full skin 110 that serves as a support. These honeycomb structures 102, 108 are each constituted by a network of hive-shaped cavities.
    [00026] According to its implantation on the inside of the nacelle or on the external face of the turbo-reactor's primary hood, the acoustic treatment panel according to the invention is arranged so that its perforated skin 104 is in contact with the path of cold flow flow 28.
    [00027] The perforated skin 104 of the acoustic treatment panel is traversed from side to side by a plurality of holes 112 within which the acoustic energy of the sound waves emitted by the turbo-reactor is dissipated by visco-thermal effect. The perforation rate of the perforated skin (that is to say the ratio between its total perforated surface and its overall surface) is comprised between 7 and 20% (according to the chosen absorbent structure concept and the optimal target acoustic impedance).
    [00028] The perforated skin 104 of the acoustic treatment panel according to the invention on the other hand comprises a plurality of pairs of highly porous areas, that is to say areas of the skin which have a perforation rate higher than that of the rest of the skin. The perforation rate of these highly porous areas is preferably between 20 and 30% (compared to the perforation rate for the rest of the perforated skin which is between 7 and 20%). Such higher porosity is achieved, for example, by locally increasing the density and / or diameter of the holes 112 through the perforated skin.
    [00029] High porosity areas have perforation rates that make them transparent from an acoustic point of view. Such an arrangement allows to minimize the aerodynamic losses in relation to simple openings of great diameter.
    [00030] These highly porous areas 114a, 114b have a shape that can be circular (in the case of figures 4A and 4B) or square for example. As an example, in the case of a circular shape, these circular pores of great porosity have a diameter dl comprised between 5 and 15 cm. For comparison, the diameter d2 of the holes 112 is between 0.75 and 2 mm, which leads to a d1 / d2 ratio between 25 and 200.
    [00031] Each pair of highly porous zones is formed by an entrance zone 114a and an exit zone 114b, the exit zone being spaced longitudinally downstream in relation to the entrance zone. On the other hand, for each of the pairs of highly porous zones, the inlet 114a and outlet 114b zones communicate through the first honeycomb core 102 and the intermediate skin 106 with the two ends of a wave flow channel sounds 118 arranged in the second core of honeycomb structure 108.
    [00032] Different variants can be considered. According to a first embodiment illustrated by figure 3A, the highly porous areas 114a, 114b of the same pair communicate with the flow channel of sound waves 118 through wells 116a, 116b that simultaneously traverse the first core alveolar structure 102 and intermediate skin 106.
    [00033] According to a second embodiment illustrated by figure 3B, the high porosity areas 114a, 114b of the same pair communicate with the flow channel of sound waves 118 through wells 116a, 116b that cross the first core of honeycomb structure 102 and a plurality of holes 120 made through the intermediate skin 106 in front of the wells.
    [00034] According to a third embodiment illustrated by figure 3C, the high porosity zones 114a, 114b of the same pair communicate with the flow channel of sound waves 118 through passages 122a, 122b formed between the cavities of the first core of honeycomb structure 102 and a plurality of holes 120 made through the intermediate skin 106 in front of passages 122a, 122b.
    [00035] It should be noted that the intermediate skin 116 of the acoustic treatment panel according to the invention is perforated by a plurality of holes 124 with the exception of the areas covering the sound wave flow channel 118 disposed in the second honeycomb structure 108 ( in other words, the areas of the intermediate skin that cover the flow channel of sound waves are full). In these non-perforated areas, the acoustic panel therefore functions as a simple resonator with a porous layer on the side of the path (that is, the perforated wall 104) and an unperforated layer at the bottom of the cavity (that is, the intermediate wall 106 ). In the perforated areas, the intermediate skin allows the acoustic treatment to function in a double resonator and presents a perforation rate between 1 and 4% with diameters for the orifices 124 in the order of 0.15 to 0.4 mm.
    [00036] The sound wave flow channel 118 can be realized in several different ways. In the example of figure 3A, it is formed by a corridor bounded laterally by the walls of the cavities of the second honeycomb structure 108. For this purpose, it is obtained, for example, by forming several panels (or “Blocks”) of cavity networks in in the form of hives, these panels being spaced sideways to form such corridors between them.
    [00037] According to a variant of embodiment represented by figures 3B and 3C, each flow channel of sound waves 118 is formed by a network of adjacent cavities of the second honeycomb structure 108 that communicate with each other through walls 122 of great rate of porosity (the porosity rate must be high enough to avoid acoustic couplings between the cavities concerned).
    [00038] As previously indicated, the intermediate skin 116 is not perforated in the areas that cover the flow channel of sound waves 118, the latter is therefore delimited, laterally by walls of the cavities of the second alveolar structure 108, and in the direction of its height, by non-perforated partitions.
    [00039] On the other hand, as shown in the embodiment of figures 3A and 4A, the path formed by the sound wave flow channel 118 can be straight and thus extend substantially parallel to the longitudinal axis X-X of the turbo reactor. In that case, the inlet 114a and the outlet 114b zones are aligned according to that X-X axis.
    [00040] Likewise, even in the example of figure 4A, the entrance areas 114a can be regularly spaced circumferentially from each other and aligned with each other in the same substantially transverse direction (that is perpendicular to the X-X axis). The same is true with exit zones 114b.
    [00041] Of course, other provisions can be considered. Thus, in the exemplary embodiment of Figure 4B, the outlet region 114b is displaced circumferentially with respect to the inlet area 114a and the sound wave flow channel 118 is not only straight.
    [00042] It will be possible to imagine other, more complex forms for the flow channels of sound waves. In particular, the network of channels formed in the second honeycomb structure may take the form of a veritable maze traversed by the sound waves (with upstream and downstream exit zones). The path taken by the sound waves in the second alveolar structure will be predetermined according to the phase delay that you want to apply to the waves.
    [00043] It will be noted that the different flow channels of sound waves made in an acoustic treatment panel according to the invention can eventually communicate with each other through perforations.
    [00044] The benefit in terms of acoustic attenuation obtained by the acoustic treatment panel according to the invention is illustrated by curve 200 in figure 5. This curve represents the sound attenuation (in decibels) in relation to the length of the panel related to the height of the turbo-reactor's cold flow flow path. In dotted lines, a 202 curve obtained with a conventional acoustic treatment panel is represented. After a certain relative length LA of the panel, it is found that a conventional acoustic treatment tends to stagnate in terms of sound attenuation. On the contrary, the acoustic treatment panel according to the invention makes it possible to obtain a large acoustic attenuation gain above that relative LA panel length.
    权利要求:
    Claims (13)
    [0001]
    1. Multilayer acoustic treatment panel (100) comprising: - a first core with a honeycomb structure (102) sandwiched between a perforated skin (104) and an intermediate skin (106); and - a second core of honeycomb structure (108) sandwiched between the intermediate skin and a full skin (110); characterized by the fact that the perforated skin comprising at least a pair of areas of great porosity that have a perforation rate higher than the perforation rate of the rest of the perforated skin and which is formed by an entrance zone (114a) and a zone outlet (114b) spaced longitudinally from each other, the areas of great porosity of the same pair communicating through the first core of alveolar structure and the intermediate skin with the two ends of a flow channel of sound waves (118) disposed in the second core with alveolar structure, and the intermediate skin (106) not being perforated in the areas that cover the flow channel of sound waves (118).
    [0002]
    2. Panel, according to claim 1, characterized by the fact that the areas of great porosity of the same pair communicate with the flow channel of sound waves through wells that traverse both the first core of alveolar structure and the skin intermediate.
    [0003]
    3. Panel, according to claim 1, characterized by the fact that the areas of great porosity of the same pair communicate with the flow channel of sound waves through wells that cross the first core of alveolar structure and a plurality of holes made through the intermediate skin.
    [0004]
    4. Panel, according to claim 1, characterized by the fact that the areas of great porosity of the same pair communicate with the flow channel of sound waves through passages formed between the cavities of the first core of alveolar structure and of a plurality of holes made through the intermediate skin.
    [0005]
    5. Panel according to any one of claims 1 to 4, characterized by the fact that the areas of the intermediate skin that cover the flow channel of sound waves are full.
    [0006]
    6. Panel according to any one of claims 1 to 5, characterized by the fact that the flow channel of sound waves is formed by a corridor delimited laterally by walls of the second core of alveolar structure.
    [0007]
    7. Panel according to any one of claims 1 to 5, characterized by the fact that the flow channel of sound waves is formed by a network of adjacent cavities of the second core of alveolar structure that communicate with each other through porous walls.
    [0008]
    Panel according to any one of claims 1 to 7, characterized in that the perforated skin comprises a plurality of pairs of highly porous zones spaced transversely from each other.
    [0009]
    9. Panel according to claim 8, characterized by the fact that the entrance zones and the exit zones are aligned according to directions substantially transversal to the panel.
    [0010]
    10. Turbo-reactor nacelle (12), characterized by the fact that it comprises at least one acoustic treatment panel (100) at the level of an internal face as defined in any one of claims 1 to 9.
    [0011]
    11. Nacela, according to claim 10, characterized by the fact that the perforated skin (104) of the acoustic treatment panel is in contact with a flow path of a cold flow (28) delimited on the outside by the internal face of the nacelle .
    [0012]
    12. Turboreactor (10), characterized by the fact that it comprises, at the level of an external face, at least one acoustic treatment panel (100) as defined in any one of claims 1 to 9.
    [0013]
    13. Turbocharger, according to claim 12, characterized by the fact that the perforated skin (104) of the acoustic treatment panel in contact with a flow path of a cold flow (28) delimited inside by the external face of the turbo-reactor.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4106587A|1976-07-02|1978-08-15|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Sound-suppressing structure with thermal relief|
    GB2038410B|1978-12-27|1982-11-17|Rolls Royce|Acoustic lining utilising resonance|
    GB2049887B|1979-05-23|1982-12-01|Coal Industry Patents Ltd|Acoustic liner for attenuating noise|
    JP3158876B2|1994-07-19|2001-04-23|日産自動車株式会社|Sound insulation wall structure|
    FR2752392B1|1996-08-14|1999-04-23|Hispano Suiza Sa|VENTILATED HONEYCOMB SANDWICH PANEL AND VENTILATION METHOD FOR SUCH A PANEL|
    US5923003A|1996-09-09|1999-07-13|Northrop Grumman Corporation|Extended reaction acoustic liner for jet engines and the like|
    US5912442A|1997-07-02|1999-06-15|Trw Inc.|Structure having low acoustically-induced vibration response|
    FR2775216B1|1998-02-26|2000-07-13|Snecma|SOUNDPROOFING PANEL AND METHOD FOR PRODUCING THE SAME|
    GB0016149D0|2000-06-30|2000-08-23|Short Brothers Plc|A noise attenuation panel|
    US7047725B2|2003-05-28|2006-05-23|Rohr, Inc.|Assembly and method for aircraft engine noise reduction|
    US20060169532A1|2005-02-03|2006-08-03|Patrick William P|Acoustic liner with nonuniform impedance|
    FR2915522A1|2007-04-30|2008-10-31|Airbus France Sas|Acoustic attenuation panel i.e. acoustic attenuation lining, for propulsion system of aircraft, has cellular structure whose one of characteristics varies acoustic wave to locally oppose acoustic wave to impedance variations|FR2956445B1|2010-02-12|2012-08-24|Turbomeca|NOISE ATTENUATION COATING FOR A GAS GUIDE TUBE, TUBE AND GAS TURBINE ENGINE WITH COATING|
    FR2961175B1|2010-06-14|2013-01-04|Aircelle Sa|TURBOREACTOR NACELLE|
    US9514734B1|2011-06-30|2016-12-06|The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration|Acoustic liners for turbine engines|
    US9752494B2|2013-03-15|2017-09-05|Kohler Co.|Noise suppression systems|
    FR3013076B1|2013-11-13|2017-12-08|Ge Energy Products France Snc|THERMO-ACOUSTIC PROTECTION STRUCTURE FOR ROTATING MACHINE|
    US9693166B2|2014-06-24|2017-06-27|The Boeing Company|Automated production of acoustic structures|
    DE102014218350A1|2014-09-12|2016-03-17|Rolls-Royce Deutschland Ltd & Co Kg|Sound-absorbing arrangement for an engine nacelle and engine nacelle with such an arrangement|
    US9919500B2|2014-09-29|2018-03-20|Pratt & Whitney Canada Corp.|Inner bypass duct|
    GB2533298B|2014-12-15|2017-06-07|Jaguar Land Rover Ltd|Acoustic baffle|
    CA2970780A1|2014-12-18|2016-06-23|Bombardier Inc.|Sound absorbers for airframe components|
    FR3031142B1|2014-12-24|2017-03-24|Aircelle Sa|ACOUSTICAL ATTENUATION PANEL FOR TURBOREACTOR NACELLE|
    EP3281192A1|2015-04-10|2018-02-14|MRA Systems, Inc.|Acoustic liner and method of constructing an acoustic liner|
    US9783316B2|2015-06-22|2017-10-10|Rohr, Inc.|Acoustic panel assembly with a folding chamber|
    FR3048024B1|2016-02-19|2018-03-23|Snecma|DEVICE AND METHOD FOR PERFORATING A PANEL|
    CN105845122B|2016-03-22|2019-12-24|南京大学|Ultra-thin two-way acoustic resistance separates passageway|
    US10253727B2|2016-05-12|2019-04-09|Rohr, Inc.|Backside acoustic treatment of nacelle structural fittings|
    US9732677B1|2016-05-12|2017-08-15|Rohr, Inc.|Broadband acoustic panels coupled with large secondary cavities to attenuate low frequencies|
    FR3054608B1|2016-07-29|2020-06-26|Safran|ACOUSTIC PANEL FOR A TURBOMACHINE AND ITS MANUFACTURING METHOD|
    US10273913B2|2017-05-25|2019-04-30|The United States Of America, As Represented By The Secretary Of The Navy|Multi-mode thermoacoustic actuator|
    US10436118B2|2017-06-19|2019-10-08|Rohr, Inc.|Acoustic panel with folding chamber|
    US11059559B2|2018-03-05|2021-07-13|General Electric Company|Acoustic liners with oblique cellular structures|
    US20190337632A1|2018-05-02|2019-11-07|Rohr, Inc.|Aircraft propulsion system assembly including one or more acoustic panels|
    US11047304B2|2018-08-08|2021-06-29|General Electric Company|Acoustic cores with sound-attenuating protuberances|
    US11174815B2|2018-09-14|2021-11-16|Rohr, Inc.|Inlet deep cavity flutter liner|
    US10823059B2|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|
    RU2716802C1|2019-02-20|2020-03-16|Государственное предприятие "Запорожское машиностроительное конструкторское бюро "Прогресс" имени академика А.Г. Ивченко"|Jacket of turbojet engine with multilayer panels and drainage system|
    FR3100918A1|2019-09-12|2021-03-19|Safran Nacelles|ACOUSTIC PANEL FOR AN AIRCRAFT PROPELLER ASSEMBLY, AND ITS MANUFACTURING PROCESS|
    FR3105553B1|2019-12-20|2022-01-21|Airbus Operations Sas|Acoustic processing system with at least two degrees of freedom comprising a quarter-wave coating allowing the passage of acoustic waves in a cavity mode resonator|
    RU203213U1|2020-07-08|2021-03-26|Государственное предприятие "Запорожское машиностроительное конструкторское бюро "Прогресс" имени академика А.Г. Ивченко|SOUND-ABSORBING STRUCTURE FOR TURBO-JET TWO-CIRCUIT ENGINE|
    RU2745127C1|2020-07-14|2021-03-22|Государственное предприятие "Запорожское машиностроительное конструкторское бюро "Прогресс" имени академика А.Г. Ивченко"|Multi-layer sound-absorbing structure of a double-flow turbojet engine|
    EP3945175A1|2020-07-30|2022-02-02|Z LAB s.r.l.|Modular panel|
    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-11-12| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-10-20| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
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    申请号 | 申请日 | 专利标题
    FR1053881|2010-05-19|
    FR1053881A|FR2960334B1|2010-05-19|2010-05-19|MULTILAYER ACOUSTIC TREATMENT PANEL|
    PCT/FR2011/051062|WO2011144842A2|2010-05-19|2011-05-12|Multi-layer acoustic treatment panel|
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