• 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 subject of the invention is an acoustic structure for an aircraft nacelle which comprises at least one one-piece casing (54) made in one piece which comprises: - ducts (56) delimited by a reflective layer (48), a layer of an acoustically resistive substructure (44), two side walls arranged in two longitudinal planes and at least one intermediate partition arranged in a longitudinal plane between the two side walls, - an end wall (62) to close the ducts (56), - the reflective layer (48), the layer of the acoustically resistive substructure (44), the two side walls, the intermediate partition(s) and the said end wall (62 ) being made in one piece, strips of cells (64) being positioned in each of the ducts (56) of the one-piece housing (54).
    公开号:FR3055612A1
    申请号:FR1658255
    申请日:2016-09-06
    公开日:2018-03-09
    发明作者:Thierry Surply；Alain Porte；Gregory ALBET；Arnaud Bourhis
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    © Publication no .: 3,055,612 (use only for reproduction orders)
    ©) National registration number: 16 58255 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : B 64 D 33/02 (2017.01), B 64 D 15/04
    A1 PATENT APPLICATION
    ©) Date of filing: 06.09.16. ©) Applicant (s): AIRBUS OPERATIONS Company by (30) Priority: simplified actions - FR. @ Inventor (s): SURPLY THIERRY, PORTE ALAIN, ALBET GREGORY and BOURHIS ARNAUD. (43) Date of public availability of the request: 09.03.18 Bulletin 18/10. ©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): AIRBUS OPERATIONS Company by related: simplified actions. ©) Extension request (s): ® Agent (s): CABINET ALLICI.
    COMPARTMENTAL STRUCTURE FOR THE ACOUSTIC TREATMENT AND DEFROSTING OF AN AIRCRAFT NACELLE AND AIRCRAFT NACELLE INCORPORATING THE SAME.
    FR 3 055 612 - A1 (3 /) The subject of the invention is an acoustic structure for an aircraft nacelle which comprises at least one monobloc housing (54) made in one piece which comprises:
    - conduits (56) delimited by a reflective layer (48), a layer of an acoustically resistive substructure (44), two side walls arranged in two longitudinal planes and at least one intermediate partition arranged in a longitudinal plane between the two side walls,
    - an end wall (62) for closing the conduits (56),
    - the reflective layer (48), the layer of the acoustically resistive substructure (44), the two side walls, the intermediate partition (s) and said end wall (62) being made of in one piece, cell strips (64) being positioned in each of the conduits (56) of the monobloc housing (54).

    COMPARTMENTAL STRUCTURE FOR ACOUSTIC TREATMENT AND DEFROSTING
    OF AN AIRCRAFT NACELLE AND AIRCRAFT NACELLE INCORPORATING SAID STRUCTURE
    The present invention relates to a compartmentalized structure for the acoustic treatment and defrosting of an aircraft nacelle as well as to a nacelle incorporating said structure.
    Document FR-2,925,463 describes a structure for acoustic treatment positioned at the level of an air intake of an aircraft nacelle.
    This structure for acoustic treatment comprises at least one acoustically resistive substructure, strips of cells arranged in a direction substantially perpendicular to a direction of flow of the air flow entering the nacelle and at least one reflective layer.
    According to this document FR-2,925,463, the structure comprises boxes oriented perpendicular to the direction of flow. Each box has a U-shaped section, the branches of which are connected to the acoustically resistive substructure, at least one strip of cells being enclosed between each box and the acoustically resistive substructure. According to this configuration, the boxes limit the appearance of air flow inside the cell strips.
    According to one method of assembly, the end of each branch of the boxes comprises a flange which is plated and welded to the acoustically resistive substructure. According to one embodiment, all the boxes are connected and form a partitioning substructure. This partitioning substructure is assembled with the acoustically resistive substructure and then machined to remove the material from the partitioning substructure provided between the channels to release the acoustically resistive substructure. This embodiment is relatively long, complex and therefore expensive.
    According to an embodiment described in this document FR-2,925,463, the acoustically resistive substructure comprises a first layer in contact with the air flow and a second layer interposed between the first layer and the cell strips, said second layer comprising grooves forming channels in the acoustically resistive substructure when the first and second layers are pressed against each other. According to this embodiment, hot air flows through the channels to perform the defrosting function.
    The embodiments proposed by document FR-2,925,463 are not fully satisfactory because the seal depends on the quality of the weld between the boxes and the acoustically resistive layer.
    Also, the present invention aims to remedy the drawbacks of the prior art.
    To this end, the subject of the invention is an acoustic structure for an aircraft nacelle, comprising an acoustically resistive substructure, at least one layer of cells, a reflective layer, elongated elements of a deicing system, characterized in that the acoustic structure comprises at least one monobloc housing which comprises:
    the reflective layer, at least one layer of the acoustically resistive substructure, two side walls connecting said reflective layer and the acoustically resistive substructure and which are arranged in two longitudinal planes, at least one intermediate partition connecting said reflective layer and the acoustically resistive substructure and which is arranged in a longitudinal plane between the side walls, conduits delimited by the reflective layer, the layer of the acoustically resistive substructure the two side walls and the intermediate partition (s), an end wall for closing off the conduits, the reflective layer, the layer of the acoustically resistive substructure, the two side walls, the intermediate partition (s) and said end wall being made of in one piece, and in that the cell layer of the acoustic structure comprises strips of cells which are positi onnées in each of the conduits of the monobloc housing.
    This solution makes it possible to remove the connections by welding and to obtain a perfect seal between two conduits distributed over the circumference of the nacelle.
    According to another characteristic, the end wall is positioned at the front of the one-piece housing.
    According to another characteristic, the end wall comprises at least one wing configured to receive a rear part of a panel forming a lip of the nacelle.
    According to a first variant, the wing comprises a first face configured to receive the rear part of the panel forming the lip and a second face configured to receive a curved edge of the front frame.
    According to another characteristic, the wing comprises at least one conduit.
    According to a second variant, the end wall comprises a first wing configured to receive a rear part of a panel forming a lip of the nacelle and a second wing spaced from the first wing and configured to receive a curved edge of a frame before.
    According to another characteristic, the monobloc housing comprises, for each elongated element of a defrosting system, a duct positioned in a junction zone between the acoustically resistive substructure and one of the intermediate partitions or one of the side walls .
    According to another characteristic, the conduits open out between the first and second wings.
    According to another characteristic, the one-piece housing is obtained from a block of material machined in the mass, by molding, by a foundry process, by a 3D printing process or by a fiber pressure injection process. and thermoplastic or thermosetting resin.
    The invention also relates to a nacelle comprising at least one acoustic structure according to the invention.
    Other characteristics and advantages will emerge from the description which follows of the invention, description given by way of example only, with reference to the appended drawings in which:
    FIG. 1 is a perspective view of an aircraft nacelle,
    FIG. 2 is a section in perspective of an air inlet of an aircraft nacelle which illustrates the invention,
    FIG. 3 is a perspective view of an acoustic structure which illustrates an embodiment of the invention,
    FIG. 4 is a cross section of a monobloc case of an acoustic structure which illustrates an embodiment of the invention,
    FIG. 5 is a section along the line V-V of FIG. 4,
    FIG. 6 is a section along line VI-VI of FIG. 4,
    FIG. 7 is a longitudinal section of several acoustic structures which illustrates an embodiment of the invention,
    FIG. 8 is a longitudinal section of part of an air inlet of a nacelle which illustrates an embodiment of the invention,
    FIG. 9 is a perspective view with a longitudinal section of a one-piece housing of an acoustic structure which illustrates an embodiment of the invention,
    Figure 10 is a longitudinal section of part of an air inlet of a nacelle which illustrates another embodiment of the invention.
    In Figure 1, there is shown a propulsion unit 10 of an aircraft connected to an airfoil via a mast 12. However, this propulsion unit could be connected to other areas of the aircraft.
    This propulsion unit comprises a motorization arranged in a substantially concentric manner in a nacelle 14 which in particular makes it possible to channel an air flow towards the motorization.
    For the following description, the longitudinal direction is parallel to the axis of the nacelle referenced 18. A longitudinal plane is a plane passing through the axis of the nacelle 18. A transverse plane is a plane perpendicular to the longitudinal direction. A radial direction is a direction perpendicular to the axis of the nacelle 18.
    The terms front and rear refer to the direction of flow of the air flow in the nacelle. The front corresponds to an area where the air flow enters the nacelle and the rear corresponds to an area where the air flow exits from the nacelle. In addition, the term aerodynamic surface corresponds to a surface of the nacelle in contact with the air flow. Finally, the term layer designates one or more layers bonded to each other which may be more or less thick.
    The nacelle 14 comprises at the front a lip 20 which is extended inside the nacelle 14 by an interior wall 22 and outside the nacelle 14 by an exterior wall 24. The interior wall 22 defines an interior duct 26 approximately cylindrical which channels the air flow towards the motorization.
    The lip 20 and the interior wall 22 form a subset of the nacelle called the air inlet.
    According to one embodiment, the lip 20 comprises a first radius of curvature in a longitudinal plane (visible in FIG. 2) which forms approximately C and a second radius of curvature in a transverse plane (visible in FIG. 1) approximately circular .
    The nacelle 14 comprises a front frame 30 which connects the inner wall 22 and the outer wall 24 and which forms with the lip 20 an annular duct 31 also called Dduct.
    The nacelle 14 includes a deicing system intended to limit the appearance or accumulation of frost or ice on the aerodynamic surface of the air intake.
    According to a first variant, the deicing system is of the pneumatic type. As illustrated in FIG. 2, the nacelle 14 comprises a supply of hot air connected to the annular duct 31. According to this first variant, the deicing system also comprises ducts 32 positioned close to the aerodynamic surface of the interior wall 22 and configured for channeling hot air from the annular duct 31 to outlets 34 opening into the inner duct 26 and offset backwards relative to the annular duct 31.
    According to a second variant, the defrosting system is of the electrical type. According to an embodiment illustrated in FIG. 9, the defrosting system comprises electrical resistors 36 positioned near the aerodynamic surface of the air inlet.
    The deicing system comprises elongate elements 32 or 36 positioned near the aerodynamic surface of the air inlet, said elongate elements being present on at least part of said aerodynamic surface of the air inlet.
    To limit noise pollution, the nacelle 14 includes at least one panel for the acoustic treatment, hereinafter called an acoustic panel aimed at absorbing part of the sound energy, in particular by using the principle of Helmholtz resonators.
    As illustrated in FIG. 2, an acoustic panel 40 forms a part of the interior wall 22. According to one embodiment, the acoustic panel 40 comprises an acoustically resistive layer, a layer of cells and a reflective layer. According to another embodiment, the acoustic panel 40 comprises a first acoustically resistive layer, a first layer of cells, a second acoustically resistive layer called a septum, a second layer of cells and a reflective layer.
    The acoustic panel 40 is outside the frost accretion zone, distant from the lip, it does not include a defrosting system.
    As the dilution rate of motorizations is higher and higher, the diameter of the nacelles tends to be more and more important. Consequently, to limit the impact of this increase in diameter on the mass of the nacelle, the air intake is becoming shorter. Also, the acoustically treated area extends over the entire length of the inner duct 26 or even at the level of the lip 20.
    To this end, the nacelle 14 comprises at least one acoustic structure 42, having the shape of an acoustic ring over 360 °, which incorporates a deicing system. According to one configuration, the nacelle comprises a plurality of acoustic structures 42, 42 ′ juxtaposed (see FIG. 9) to each other over at least part of the periphery of the inner duct 26, preferably over its entire periphery. Each acoustic structure 42 is delimited by two watertight side walls 43 arranged in longitudinal planes, the side walls 43 of two adjacent acoustic structures being pressed against each other and connected by any suitable means, such as by riveting, by bolting or whatever.
    Each acoustic structure 42 comprises, moving away from the axis of the nacelle 18, an acoustically resistive substructure 44 in contact with the air flow in operation, at least one layer of cells 46 and a reflective layer 48. To simplify their representations, the reflective layer 48 and the acoustically resistive substructure 44 are shown plane. In reality, they have a radius of curvature identical to that of the inner duct 26, as illustrated in FIG. 9.
    This acoustic structure 42 comprises at least one intermediate partition 50, disposed in a longitudinal plane, interposed between the side walls 43. According to an embodiment visible in FIG. 4, the acoustic structure 42 comprises two intermediate partitions 50 distributed regularly between the walls lateral 43. According to another embodiment visible in FIG. 9, the acoustic structure 42 comprises four intermediate partitions 50. The distribution of intermediate partitions 50 is not necessarily regular between the lateral walls 43. Thus, the spacing between a first pair of two adjacent intermediate partitions 50 may be different from that of another pair of two adjacent intermediate partitions, as illustrated in FIG. 9.
    As an indication, the intermediate partitions 50 and the side walls 43 are arranged on at least part of the circumference of the air inlet and are spaced at an angle between 10 and 60 °.
    Each side wall 43 comprises a first edge connected to the acoustically resistive substructure 44 and a second edge connected to the reflective layer 48. Likewise, each intermediate partition 50 comprises a first edge connected to the acoustically resistive substructure 44 and a second edge connected to the reflective layer 48.
    According to one embodiment, the reflective layer 48 is a metal plate.
    According to a first embodiment, the acoustically resistive substructure 44 is a perforated or micro-perforated layer such as a perforated or microperforated plate or sheet. By way of example, this perforated layer is metallic.
    According to a second embodiment, the acoustically resistive substructure 44 comprises two superposed layers, namely a porous layer, such as a metal mesh for example, and a structural layer which comprises large openings closed by the porous layer.
    Whatever the embodiment, the acoustically resistive substructure 44 comprises at least one layer 52 which is perforated or micro-perforated or which comprises openings.
    According to a characteristic of the invention, the acoustic structure 42 comprises at least one monobloc housing 54 formed by the reflective layer 48, the side walls 43, the intermediate partitions 50 and at least one layer of the acoustically resistive substructure 44, the monobloc housing 54 being made in one piece and forming only one piece.
    The one-piece housing 54 comprises a plurality of conduits 56 oriented in the longitudinal direction each delimited by the reflective layer 48, at least the layer 52 of the acoustically resistive substructure 44, and two intermediate partitions 50 or an intermediate partition 50 and a side wall 43 .
    The conduits 56 are perfectly sealed so that the circulation of an air flow from one conduit to the other is impossible depending on the circumference of the nacelle. Advantageously, a reduced number of acoustic structures 42 is necessary to cover the entire circumference of the nacelle 14. The fact of reducing the number of acoustic structures 42 makes it possible to reduce the costs for mounting the various acoustic structures 42 and to reduce the on-board mass by limiting the number of fasteners to connect the acoustic structures together.
    The monobloc housing 54 is obtained from a block of material (aluminum or titanium alloy) machined in the mass, by molding, by a foundry process, by a 3D printing process (or LAM for Laser Additive). Manufacturing in English) or by a process of pressure injection of fibers and thermoplastic or thermosetting resin.
    The one-piece housing 54 comprises, before machining, a first face which corresponds to one face of the reflective layer 48, a second face which corresponds to one face of the acoustically resistive substructure 44, a third face which corresponds to one face of a first side wall. 43, a fourth face which corresponds to a face of a second side wall 43, a fifth face which corresponds to a front face 58 and a sixth face which corresponds to a rear face 60.
    According to a first variant, the conduits 56 of the one-piece housing 54 pass through and open out at the front face 58 and the rear face 60.
    According to another variant, the conduits 56 of the monobloc housing 54 are blind and open out at the front face 58 or the rear face 60. In this case, the monobloc housing 54 comprises an end wall 62 for sealing the conduits 56 According to one embodiment, as illustrated in FIGS. 3, 6, 7, 8 or 9, the conduits 56 of the one-piece housing 54 open out at the rear face 60.
    According to this variant, the one-piece housing 54 comprises an end wall 62 positioned at the front and called the front wall 62, one face of which corresponds to the front face 58 of the one-piece housing 54.
    The one-piece housing 54 includes the reflective layer 48, the side walls 43, the intermediate partitions 50, the front wall 62 and at least the layer 52 of the acoustically resistive substructure 44 which are made in one piece and which do not form only one piece.
    According to a first embodiment, the acoustic structure 42 comprises a plate for closing the conduits 56 at the rear face 60. This plate is fixed to the one-piece housing 54 by any appropriate means, such as by screwing, by riveting, by gluing, by welding.
    According to another embodiment visible in FIG. 2, the conduits 56 of an acoustic structure 42 are closed by a wall of an acoustic panel 40.
    According to another embodiment visible in Figure 7, the nacelle comprises in the longitudinal direction several acoustic structures 42.1, 42.2 arranged end to end, the conduits 56 of a first acoustic structure 42.1 being closed by the front wall 62 of a second acoustic structure 42.2 disposed at the rear of the first acoustic structure 42.1. By having several acoustic structures 42.1, 42.2 in the longitudinal direction, the different front walls 62 form a partition which makes it impossible for air flow from one acoustic structure to the other in the longitudinal direction.
    The layer of cells 46 of the acoustic structure 42 comprises strips of cells 64 which are positioned in each of the conduits 56 of the monobloc housing 54. For each strip, the cells are tubes oriented in radial directions. Thus, each tube comprises a first end oriented towards the reflective layer 48 and a second end oriented towards the acoustically resistive substructure 44.
    According to a first embodiment, each conduit 56 comprises a single strip of cells 64 whose dimensions are substantially identical to those of the conduit 56.
    According to another embodiment, each conduit 56 comprises several strips of cells 64 which are juxtaposed and / or superimposed in the radial direction.
    The dimensions of the cells are determined according to the acoustic characteristics sought.
    According to one embodiment, the strips of cells 64 are made of thermoplastic material and are obtained by injecting thermoplastic material directly into each of the conduits 56. This solution makes it possible to obtain strips of cells with complex geometries adapted to those of the conduits 56 .
    According to another embodiment, the strips of cells 64 of the acoustic structure 42 are introduced into the conduits 56 and connected to the one-piece housing 54 by bonding, for example using a crosslinked adhesive which connects on the one hand a first end of the tubes of the cell strip 64 and the reflective layer 48, and on the other hand, a second end of the tubes of the cell strip 64 and the acoustically resistive substructure 44.
    As illustrated in FIG. 10, the reflective layer 48 and the acoustically resistive substructure 44 are not parallel and form a non-zero angle a to facilitate the introduction of the strips of cells 64 of the acoustic structure 42 into the conduits 56 and do not rub the crosslinked adhesive placed at the ends of the tubes of the cell strips 64 with the monobloc housing 54 before the end of the introduction of the cell strips 64.
    When the de-icing system comprises conduits 32, these conduits 32 are integrated in the intermediate partitions 50 and / or in the side walls 43 near the acoustically resistive substructure 44.
    According to a variant, each conduit 32 comprises a first end which opens out at the front face 58 of the monobloc box 54 and a second end which opens out at the rear face 60 of the monoblock box 54.
    According to another variant, each conduit 32 comprises a first end which opens out at the front face 58 of the monobloc housing 54 and a second end which opens out at the acoustically resistive substructure 44, as illustrated in FIG. 5.
    According to one embodiment, each conduit 32 is obtained by drilling the one-piece housing 54.
    When the defrosting system comprises electrical resistances 36, the monobloc unit 54 comprises through conduits configured to house the electrical resistances 36 and which are positioned at the level of the acoustically resistive substructure 44 in the extension of the intermediate partitions 50 and / or side walls 43.
    Whatever the type of defrosting system, each elongate element 32 or 36 of the defrosting system is disposed in a duct of the monobloc housing 54 positioned in a junction zone between the acoustically resistive substructure 44 and one of the intermediate partitions. 50 or one of the side walls 43.
    According to another characteristic, the monobloc housing 54 comprises a system for connection with the lip 20.
    As illustrated in FIG. 8, the front wall 62 of the one-piece housing 54 comprises a first wing 66 configured to receive a rear part 68 of a panel forming the lip 20. According to one embodiment, the first wing 66 is parallel to the acoustically resistive substructure 44 and offset towards the reflective layer 48 relative to said acoustically resistive substructure 44. Thus, when the rear part 68 of a panel forming the lip 20 is pressed against the first wing 66, the rear part 68 is flush with the acoustically resistive substructure 44.
    The front wall 62 of the monobloc housing 54 comprises a second wing 70 configured to receive a curved edge 72 of the front frame 30. This second wing 70 is parallel and spaced from the first wing 66.
    In the presence of the first and second wings 66 and 70, the conduits 32 of the deicing system open out between the first and second wings 66, 70.
    As a variant, as illustrated in FIG. 10, the front wall 62 of the one-piece housing 54 comprises a single wing 74 connected to the lip 20 and to the front frame 30. This wing 74 is parallel to the acoustically resistive substructure 44 and offset towards the reflective layer 48 relative to said acoustically resistive substructure 44. This wing 74 comprises a first face 74.1 configured to receive a rear part 68 of a panel forming the lip 20 and a second face 74.2 configured to receive a curved edge 72 front frame 30.
    This wing 74 comprises at least one conduit 76 provided with a first end which opens at the level of the conduit 31 and with a second end which opens at the level of the acoustically resistive structure 44 to make the annular conduit 31 and the inner conduit 26 communicate .
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Acoustic structure for an aircraft nacelle, comprising an acoustically resistive substructure (44), at least one cell layer (46), a reflective layer (48), characterized in that the acoustic structure comprises at least one monobloc housing (54) which comprises:
    the reflective layer (48), at least one layer (52) of the acoustically resistive substructure (44), two side walls (43) connecting said reflective layer (48) and the acoustically resistive substructure (44) and which are arranged in two longitudinal planes, at least one intermediate partition (50) connecting said reflective layer (48) and the acoustically resistive substructure (44) and which is arranged in a longitudinal plane between the side walls (43), of the conduits (56) delimited by the reflective layer (48), the layer (52) of the acoustically resistive substructure (44), the two side walls (43) and the intermediate partition (s) (50), a end wall (62) for closing the conduits (56), the reflective layer (48), the layer (52) of the acoustically resistive substructure (44), the two side walls (43), the partition or partitions (s) intermediate (s) (50) and said end wall (62) being made of a s eul tenant, and in that the cell layer (46) of the acoustic structure (42) comprises strips of cells (64) which are positioned in each of the conduits (56) of the monobloc housing (54).
    [2" id="c-fr-0002]
    2. Acoustic structure according to claim 1, characterized in that the end wall (62) is positioned at the front of the monobloc housing (54).
    [3" id="c-fr-0003]
    3. Acoustic structure according to the preceding claim, characterized in that the end wall (62) comprises at least one wing (66, 74) configured to receive a rear part (68) of a panel forming a lip (20) of the gondola.
    [4" id="c-fr-0004]
    4. Acoustic structure according to the preceding claim, characterized in that the wing (74) comprises a first face (74.1) configured to receive the rear part (68) of the panel forming the lip (20) and a second face (74.2) configured to receive a curved edge (72) of the front frame (30).
    [5" id="c-fr-0005]
    5. Acoustic structure according to the preceding claim, characterized in that the wing (74) comprises at least one conduit (78).
    [6" id="c-fr-0006]
    6. acoustic structure according to claim 3, characterized in that the end wall (62) comprises a first wing (66) configured to receive a part
    5 rear (68) of a panel forming a lip (20) of the nacelle and a second wing (70) spaced from the first wing (66) and configured to receive a curved edge (72) of a front frame (30 ).
    [7" id="c-fr-0007]
    7. Acoustic structure according to one of the preceding claims, characterized in that the monobloc housing (54) comprises, for each elongated element (32, 36) of a
    10 defrosting system, a duct (32) positioned in a junction zone between the acoustically resistive substructure (44) and one of the intermediate partitions (50) or one of the side walls (43).
    [8" id="c-fr-0008]
    8. Acoustic structure according to claims 6 and 7, characterized in that the conduits (32) open out between the first and second wings (66, 70).
    15
    [0009]
    9. A method of manufacturing an acoustic structure according to one of the preceding claims, characterized in that the monobloc housing (54) is obtained from a block of material machined in the mass, by molding, by a method of foundry, by a 3D printing process or by a pressure injection process of fibers and thermoplastic or thermosetting resin.
    20
    [0010]
    10. Nacelle comprising at least one acoustic structure according to one of claims 1 to 8.
    1/3
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    同族专利:
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20120048389A1|2009-02-02|2012-03-01|Airbus Operations Sas|Aircraft nacelle including an optimised acoustic processing system|
    EP2537753A1|2011-06-20|2012-12-26|Airbus Opérations SAS|Method for producing an acoustic treatment panel including the function of de-icing with hot air|
    EP2578496A2|2011-10-03|2013-04-10|Airbus Opérations SAS|Acoustic treatment panel including hot-air channels and at least one annular channel|
    EP2832973A1|2013-08-01|2015-02-04|Rolls-Royce plc|Acoustic liner|US10655539B2|2017-10-16|2020-05-19|Rolls-Royce North America Technologies Inc.|Aircraft anti-icing system|
    WO2020217025A1|2019-04-26|2020-10-29|Safran Nacelles|Nacelle air intake and nacelle comprising such an air intake|
    WO2020225563A1|2019-05-09|2020-11-12|Safran Nacelles Limited|Acoustic panel|
    法律状态:
    2017-09-28| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-09| PLSC| Publication of the preliminary search report|Effective date: 20180309 |
    2018-09-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-09-26| PLFP| Fee payment|Year of fee payment: 4 |
    2020-09-14| PLFP| Fee payment|Year of fee payment: 5 |
    2021-09-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1658255|2016-09-06|
    FR1658255A|FR3055612B1|2016-09-06|2016-09-06|COMPARTMENTED STRUCTURE FOR ACOUSTIC TREATMENT AND DE-ICING OF AN AIRCRAFT NACELLE AND AIRCRAFT NACELLE INCORPORATING SAID STRUCTURE|FR1658255A| FR3055612B1|2016-09-06|2016-09-06|COMPARTMENTED STRUCTURE FOR ACOUSTIC TREATMENT AND DE-ICING OF AN AIRCRAFT NACELLE AND AIRCRAFT NACELLE INCORPORATING SAID STRUCTURE|
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