• 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 to a method and a device for manufacturing a structural and / or acoustic panel for an aircraft propulsion unit nacelle. According to the invention, at least one skin (11) of the structural and / or acoustic panel is heated by heating means (3) producing electromagnetic radiation, so as to assemble the skin (11) with a structure alveolar (13) of the structural and / or acoustic panel by soldering or diffusion welding. This heating means (3) can also be used to conform the skin (11) to the honeycomb structure (13) prior to assembly.
    公开号:FR3073206A1
    申请号:FR1760487
    申请日:2017-11-08
    公开日:2019-05-10
    发明作者:Philippe Bienvenu；Aurelie Soula；Thomas Perrotin
    申请人:Safran Nacelles SAS；
    IPC主号:
    专利说明:

    Method for manufacturing a structural and / or acoustic panel for an aircraft propulsion unit nacelle, and device relating thereto
    The present invention relates to the field of manufacturing parts for nacelle for an aircraft propulsion assembly such as an aircraft turbojet engine nacelle. More specifically, the invention relates to a method for manufacturing a structural and / or acoustic panel, in particular for an ejection nozzle or internal fixed structure of such a nacelle. The invention also relates to a device making it possible to implement such a method.
    In this area, it is known to use structural panels commonly known as “sandwich panels”. Such a panel typically comprises two skins and a honeycomb structure connecting the two skins. Typically, the honeycomb structure consists of transverse partitions contributing to the structural strength of the panel, in particular ensuring the connection between the two skins and supporting mechanical and thermal stresses. Such a honeycomb structure makes it possible to reduce the overall mass of the panel.
    Such a panel can also have an acoustic treatment function in order to attenuate the noise generated by the propulsion unit. To do this, the transverse partitions of the alveolar structure are arranged so as to delimit alveoli forming Helmholtz cavities. One of the skins, oriented towards the source of the noise, is breathable in order to absorb the acoustic energy within the honeycomb structure.
    In this document, the expression “manufacturing of structural and / or acoustic panel” designates both, on the one hand, the manufacturing of the structural and / or acoustic panel as such, in particular by assembling the skins and the honeycomb structure and, on the other hand, the manufacture of skins and the honeycomb structure, in particular by forming these elements to be assembled.
    Techniques for assembling a structural and / or acoustic panel by brazing or by diffusion welding are known in the prior art. Brazing consists of heating a filler metal to its melting temperature, which can take the form of a solder sheet or a powder or tape (powder in an organic binder). Typically, the solder sheet is placed between a skin and the honeycomb structure of the panel. The filler metal is chosen so that its melting temperature is lower than the melting temperature of the elements to be assembled, that is to say in this example of the skin and the alveolar structure. Unlike brazing, diffusion welding does not require filler metal.
    In order to arrange the elements to be assembled in the configuration in which they are to be brazed or welded, it is known to apply a gas pressure making it possible to press and maintain these elements in such a configuration.
    In these different techniques of the prior art, the assembly is carried out within a vacuum enclosure, or vacuum oven, the rise in temperature of which is generally carried out by electrical resistors.
    Heating by electrical resistances is relatively long and may require the use of a thermal bell to limit the thermal gradients between the inner skin and the outer skin, the heating generally taking place on the side of the outer skin.
    Other disadvantages of the techniques of the prior art relate to the impossibility of modulating the temperatures on the parts and the long duration of a manufacturing cycle: the parts are generally formed separately and then assembled by heating.
    Furthermore, an internal fixed structure of a nacelle generally has non-planar surfaces, the shape of which can be relatively complex. Correlatively, the shape to be given to a structural and / or acoustic panel for an internal fixed structure of a nacelle, in particular, can be relatively complex.
    The assembly of a structural and / or acoustic panel with a non-planar surface and / or of relatively complex shape may require finalizing the shape of a skin, prior to the assembly of this skin with the corresponding cellular structure. To do this, it is known to form the skin hot under gas pressure, the pressure making it possible to press the skin against the alveolar structure of which it takes shape under the effect of temperature.
    Such forming and / or hot assembly under gas pressure can result in local crushing of the honeycomb structure. Indeed, the central part of the skin deforms faster than its ends so that the alveolar structure is subjected to non-uniform mechanical stresses in space, that is to say a force to push the skin against the alveolar structure more important at the level of the central part of the skin than at its ends.
    Cold hydroforming is an alternative solution which has other drawbacks, such as the risk of water leakage and bursting of the bladder or the part. This technique is also difficult to apply on an industrial scale and does not allow the forming of complex shapes.
    The invention aims to solve all or part of the drawbacks associated with known techniques for manufacturing structural and / or acoustic panels for nacelles.
    To this end, the invention relates to a method of manufacturing a structural and / or acoustic panel for a nacelle for an aircraft propulsion assembly. The structural and / or acoustic panel comprises two metallic skins and a metallic cellular structure, for example made of titanium. Preferably, the honeycomb structure can be of the honeycomb type. The method comprises an arrangement of one of the two skins, called the working skin, so that the working skin defines a first volume and a second volume of an enclosure. The method also includes an arrangement of the honeycomb structure in the second volume of the enclosure. According to the invention, the method further comprises an assembly step in which the working skin is heated by electromagnetic radiation so as to assemble the working skin and the cellular structure by brazing or diffusion welding. Preferably, the electromagnetic radiation can be infrared. Alternatively, this radiation can be laser.
    Such a method makes it possible to selectively heat the elements to be assembled, thanks to the directivity of the electromagnetic radiation. It is thus possible to selectively heat the working skin by limiting or canceling the rise in temperature of the tool.
    The directivity of the heating also makes it possible to simplify the sealing means thanks to the conservation of relatively cold zones. It is thus possible to seal the enclosure by rubber seals.
    Compared to electrical resistance heating techniques, the method according to the invention makes it possible to reduce the manufacturing time of the structural and / or acoustic panel and to avoid the use of a thermal bell.
    Preferably, the method can also comprise gas pressurization of the first volume of the enclosure so as to press and hold the working skin against the alveolar structure.
    In one embodiment, the method may further comprise, before the assembly step, a forming step in which the working skin is heated by electromagnetic radiation so as to conform the working skin to the cellular structure, the first volume of the enclosure being pressurized by a gas during this forming step. The electromagnetic radiation can be infrared or laser and can preferably be produced by a common heating means for this forming step and for said assembly step.
    In one embodiment, the heating by electromagnetic radiation during the forming step can be carried out by selective heating of the working skin from the ends to a center of this working skin, so as to uniform its deformation at during the forming stage.
    A forming step thus carried out makes it possible in particular to obtain a more homogeneous skin thickness and, for certain materials such as inconel 625, to avoid a necking phenomenon.
    In addition, a forming step thus carried out makes it possible to avoid or limit the phenomenon of crushing of the alveolar structure at the level of the central part of the working skin, relative to the hot forming techniques under gas pressure of the prior art, while avoiding the use of cold hydroforming techniques.
    Preferably, the method can also comprise placing the second volume of the enclosure under vacuum using a pumping means.
    In one embodiment, the method may include placing the first volume of the enclosure under vacuum using a pumping means, before putting the first volume of the enclosure under gas pressure.
    Vacuuming prevents oxidation of the elements to be assembled and, in the event of assembly by brazing, improves the spreading of the solder and the mechanical properties of the structural and / or acoustic panel.
    Compared to a vacuum oven of the prior art, said first volume and said second volume each have a smaller volume, which reduces the pumping time.
    The invention also relates to a device for manufacturing a structural and / or acoustic panel for an aircraft propulsion assembly nacelle, the structural and / or acoustic panel comprising two metallic skins and a metallic cellular structure, for example made of titanium. Preferably, the honeycomb structure can be of the honeycomb type. This device comprises an enclosure capable of receiving one of the two skins, called the working skin, so that the working skin delimits a first volume and a second volume of the enclosure. The enclosure is able to receive the honeycomb structure in the second volume. According to the invention, this device further comprises a heating means arranged to heat the work skin by electromagnetic radiation so as to assemble the work skin and the cellular structure by brazing or diffusion welding during an assembly step. Preferably, the electromagnetic radiation can be infrared. Alternatively, this radiation can be laser.
    In one embodiment, the device may further comprise means for pressurizing the first volume of the enclosure with a gas, this pressurizing means being able to press and hold the working skin against the alveolar structure.
    In one embodiment, the heating means can also be arranged to heat the working skin by electromagnetic radiation so as to conform the working skin to the cellular structure during a forming step preceding the assembly step. . In this embodiment, the device can be arranged to put the first volume of the enclosure under pressure during the forming step.
    Preferably, the heating means can be arranged to heat, during the forming step, the working skin by electromagnetic radiation selectively from the ends to a center of this working skin, so as to uniformize its deformation during the forming step.
    In one embodiment, the device can comprise a pumping means arranged to put the first volume and / or second volume of the enclosure under vacuum.
    The advantages conferred by the method according to the invention are also found in the device according to the invention.
    Other characteristics and advantages of the invention will appear on reading the non-limiting description which follows and the appended figures, in which:
    FIG. 1 is a schematic view of an aircraft turbojet engine nacelle;
    FIG. 2 illustrates an ejection nozzle for an ejection nozzle for an aircraft turbojet engine nacelle;
    FIG. 3 illustrates an internal fixed structure of an aircraft turbojet engine nacelle, in the form of two half-barrels with their islands 12H and 6H;
    Figures 4 to 7 illustrate devices according to the invention suitable for the manufacture of panels of different shapes;
    FIG. 8 illustrates a heating means implemented in a device according to the invention.
    Identical or similar elements are identified by identical reference signs in all of the figures.
    The invention relates to a method and a device for manufacturing a structural and / or acoustic panel for a nacelle for a propulsion unit of an aircraft.
    An example of nacelle 9 is illustrated in FIG. 1. This nacelle 9 is suspended from a pylon 8 intended to be fixed to a wing (not shown) of an aircraft (not shown). The nacelle 9 comprises an upstream section 71 provided with a lip 70 forming an air inlet 99, a middle section 72 receiving a blower (not shown) from a turbofan engine (not shown), and a downstream section 73 .
    The downstream section 73 comprises a fixed internal structure 93 surrounding an upstream part of the turbojet engine (not shown) and a fixed external structure 94. The fixed internal structure 93 and the fixed external structure 94 define an annular vein defining a passage for a flow of main air entering the nacelle 9 at the air inlet 99.
    The nacelle 9 comprises an ejection nozzle comprising a gas ejection cone 91 ("plug" in English) and an ejection nozzle 92 ("nozzle" in English). An ejection nozzle 92 is shown in FIG. 2. The ejection cone 91 and the ejection nozzle 92 of the ejection nozzle define a passage for a flow of hot air leaving the turbojet engine (not shown).
    FIG. 3 shows two parts 931 and 932 of the internal fixed structure 93. Parts 931 and 932 have the shape of a half-barrel so that, once assembled, they give the internal fixed structure 93 the shape of a barrel.
    The internal fixed structure 93 also includes parts 933, 934, 935, 936 to provide a structural connection between the internal fixed structure 93 and the fixed external structure 94. Parts 933 and 934 constitute an island known as 12H placed vertically above the barrel. Parts 935 and 936 constitute an island known as 6H placed vertically below the barrel.
    The invention relates to the manufacture of structural and / or acoustic panels in particular for an ejection nozzle 92 of the ejection nozzle as illustrated in FIG. 2, for an internal fixed structure 93 as illustrated in FIG. 3, or for any other part of the basket 9.
    An acoustic panel 1 is illustrated in particular in FIG. 4 which shows a device according to the invention. The acoustic panel 1 comprises two metallic skins 11 and 12 and a metallic honeycomb structure 13 of the honeycomb type. By way of nonlimiting example, the elements 11, 12 and 13 can be made of the same material such as titanium. Alternatively, the elements 11, 12 and 13 can be made from different materials: for example, the elements 11 and 12 can be made from a first metallic material and the element 13 can be made from a second metallic material; or again, the elements 11, 12 and 13 can be produced respectively from a first, a second and a third material.
    The examples of FIGS. 4 to 7 illustrate a simultaneous assembly of the elements 11, 12 and 13. The invention however makes it possible to assemble these elements separately, for example only the elements 11 and 13.
    The device according to the invention comprises an enclosure 20 capable of receiving at least one of the two skins, called the working skin 11, so that the working skin 11 defines a first volume 20A and a second volume 20B of the enclosure 20. This delimitation can be obtained by pinching the working skin 11 between pinching zones (not shown) of the enclosure 20.
    The enclosure 20 is also able to receive the honeycomb structure 13 in the second volume 20B. In the examples of FIGS. 4 to 6, the second volume 20B of the enclosure 20 receives both the cellular structure 13 as well as the skin 12.
    The device according to the invention comprises a heating means 3 shown separately in FIG. 8. The heating means 3 is arranged to produce electromagnetic radiation 31 which can be infrared, laser, or the like.
    Referring to Figure 4, the heating means 3 comprises a heating means 3a arranged to heat the working skin 11 by electromagnetic radiation so as to assemble the working skin 11 and the cellular structure 13 by brazing or diffusion welding during 'an assembly step. To do this, the heating means 3a is placed in the first volume 20A of the enclosure 20. In other words, the method according to the invention comprises such an assembly step in which the working skin is heated by electromagnetic radiation 31 11 so as to assemble the working skin 11 and the cellular structure 13 by brazing or diffusion welding.
    In this example, the heating means 3 also comprises a heating means 3b. During the assembly step, electromagnetic radiation 31 is also heated, using the heating means 3b, a tool 21 on which the skin 12 rests. This makes it possible to improve the assembly of the panel and in particular to the skin 12 with the honeycomb structure 13. The heating of the tool 21 is however optional.
    Preferably, the first volume 20A of the enclosure 20 is put under gas pressure so as to press and hold the working skin 11 against the alveolar structure 13 and if necessary the alveolar structure 13 against the skin 12.
    In this example, the skin 12 is made permeable to air, for example by means of holes (not shown). Vacuuming is therefore also obtained within the honeycomb structure 13.
    In the example of FIG. 4, the elements 11, 12 and 13 are planar and form, after assembly, a planar panel.
    It appears from the examples of FIGS. 2 and 3 that certain parts of the nacelle 9 have surfaces that are not flat and / or of relatively complex shape. The acoustic panels equipping or forming such parts must therefore have such non-planar surfaces and / or of relatively complex shape, which may require finalizing the formation of a skin before it is assembled with the preformed cellular structure.
    Figures 5 to 7 show devices comprising non-planar elements to be assembled which are referred to in the following.
    According to the invention, a forming step can be carried out before the assembly step. During this forming step, the working skin 11 is heated by electromagnetic radiation 31, in the example of FIGS. 5 to 7, using the heating means 3a so as to conform the working skin 11 to the structure alveolar 13. During this forming step, the first volume 20A of the enclosure 20 is put under gas pressure, which makes it possible to push the working skin 11 against the alveolar structure 13. When the skin 12 is present, this allows also to better press the skin 12 on the tool 21 through the honeycomb structure 13 and the working skin 11.
    The working skin 11 is therefore preferably a full skin, that is to say one which is not permeable to air, to allow the first volume 20A and the second volume 20B of the enclosure 20 to be put under differential pressure.
    In an exemplary embodiment compatible with the various embodiments illustrated in FIGS. 4 to 7, the heating by electromagnetic radiation during the forming step is carried out by selective heating of the working skin 11 from ends to a center of this working skin 11, so as to standardize its deformation during the forming step.
    In the example of FIG. 6, the acoustic panel 1 corresponds to a fixed internal half structure as illustrated in FIG. 3, for example that comprising the half barrel 931 and the two parts 933 and 935.
    In order to avoid oxidation of the elements to be assembled and to ensure contact between these elements, the second volume 20B of the enclosure 20 can be put under vacuum using a pumping means during the thermal cycle.
    The first volume 20A of the enclosure 20 can also be evacuated using a pumping means during the thermal cycle, in the embodiments not involving putting this first volume 20A under gas pressure. In the embodiments in which the first volume 20A is put under gas pressure, the first volume 20A can also be put under vacuum using a pumping means before putting under gas pressure.
    By way of nonlimiting example, with reference to FIGS. 4 to 6, an inert gas pressure is applied in the first volume 20A and therefore on the working skin 11 as soon as the temperature reaches 800 ° C. and this until the end of thermal cycle. Optionally, the pressure can be reduced after the solder has solidified.
    FIG. 7 illustrates the case of an enclosure 20 arranged to assemble an acoustic panel 1a in the form of a part of revolution, this acoustic panel 1a comprising the working skin 11, the cellular structure 13 and the skin 12. The panel acoustic the manufactured according to the invention can for example constitute an ejection nozzle 92 as illustrated in FIG. 2.
    Unlike the embodiments of FIGS. 4 to 6, the enclosure 20 is delimited by the tool 21 and by walls 22, this enclosure 20 being able itself to be placed in a chamber 29 receiving a heating means 3b for the heating of the tools 21.
    Of course, the invention is not limited to the examples which have just been described and numerous modifications can be made to these examples without departing from the scope of the invention. For example, the invention also makes it possible to manufacture structural panels that do not have an acoustic treatment function.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    1. Method for manufacturing a structural and / or acoustic panel (1) for a nacelle (9) for an aircraft propulsion assembly, the structural and / or acoustic panel (1) comprising two metallic skins (11, 12) and a metallic honeycomb structure (13), this method comprising an arrangement of one of the two skins, called the working skin (11), so that the working skin (11) delimits a first volume (20A) and a second volume (20B) of an enclosure (20), and an arrangement of the honeycomb structure (13) in the second volume (20B) of the enclosure (20), characterized in that it further comprises an assembly step in which the working skin (11) is heated by electromagnetic radiation (31) so as to assemble the working skin (11) and the cellular structure (13) by brazing or diffusion welding.
    [2" id="c-fr-0002]
    2. Method according to claim 1, further comprising a gas pressure of the first volume (20A) of the enclosure (20) so as to press and hold the working skin (11) against the honeycomb structure (13).
    [3" id="c-fr-0003]
    3. Method according to claim 2, further comprising, before the assembly step, a forming step in which the working skin (11) is heated by electromagnetic radiation (31) so as to conform the working skin ( 11) to the honeycomb structure (13), the first volume (20A) of the enclosure (20) being pressurized by a gas during this forming step.
    [4" id="c-fr-0004]
    4. Method according to claim 3, in which the heating by electromagnetic radiation during the forming step is carried out by selective heating of the working skin (11) from ends to a center of this working skin (11 ), so as to standardize its deformation during the forming step.
    [5" id="c-fr-0005]
    5. Method according to any one of claims 1 to 4, further comprising evacuating the first volume (20A) and / or the second volume (20B) of the enclosure (20) using a pumping means.
    [6" id="c-fr-0006]
    6. Device for manufacturing a structural and / or acoustic panel (1) for a nacelle (9) for an aircraft propulsion assembly, the structural and / or acoustic panel (1) comprising two metallic skins (11, 12) and a metallic honeycomb structure (13), this device comprising an enclosure (20) capable of receiving one of the two skins, called the working skin (11), so that the working skin (11) delimits a first volume (20A ) and a second volume (20B) of the enclosure (20), the enclosure (20) being able to receive the honeycomb structure (13) in the second volume (20B), characterized in that it further comprises a heating means (3) arranged to heat the working skin (11) by electromagnetic radiation (31) so as to assemble the working skin (11) and the cellular structure (13) by brazing or diffusion welding during a assembly step.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3073206B1|2021-03-19|
    US20200316701A1|2020-10-08|
    WO2019092371A1|2019-05-16|
    EP3707074A1|2020-09-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3612387A|1970-01-07|1971-10-12|Aeronca Inc|Brazing method and apparatus|
    US3930605A|1973-08-06|1976-01-06|International Harvester Company|Method of fabricating a conformable sandwich structure|
    US5705794A|1991-10-15|1998-01-06|The Boeing Company|Combined heating cycles to improve efficiency in inductive heating operations|
    US20060210821A1|2005-03-21|2006-09-21|The Boeing Company|Method and apparatus for forming complex contour structural assemblies|
    EP2879830A1|2012-08-02|2015-06-10|Aircelle|Method for manufacturing of a metal part|
    WO2016062978A1|2014-10-23|2016-04-28|Aircelle|Improved method for producing an especially large aeronautical part|
    FR3106290B1|2019-09-09|2022-01-14|Safran Nacelles|Structural and/or acoustic panel for aircraft propulsion system|
    CN111465260B|2020-03-19|2022-03-04|北京空间机电研究所|Large-area radiation heat dissipation device for spacecraft for reducing mass|
    CN111452997B|2020-04-13|2022-02-11|北京中科宇航技术有限公司|Carrier rocket aluminum honeycomb fin of brazing|
    法律状态:
    2019-05-10| PLSC| Publication of the preliminary search report|Effective date: 20190510 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 3 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 4 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1760487|2017-11-08|
    FR1760487A|FR3073206B1|2017-11-08|2017-11-08|PROCESS FOR MANUFACTURING A STRUCTURAL AND / OR ACOUSTIC PANEL FOR AN AIRCRAFT PROPULSIFY NACELLE, AND RELATED DEVICE|FR1760487A| FR3073206B1|2017-11-08|2017-11-08|PROCESS FOR MANUFACTURING A STRUCTURAL AND / OR ACOUSTIC PANEL FOR AN AIRCRAFT PROPULSIFY NACELLE, AND RELATED DEVICE|
    EP18819177.9A| EP3707074A1|2017-11-08|2018-11-08|Method for manufacturing a structural and/or acoustic panel for a nacelle of an aircraft propulsion assembly, and corresponding device|
    PCT/FR2018/052768| WO2019092371A1|2017-11-08|2018-11-08|Method for manufacturing a structural and/or acoustic panel for a nacelle of an aircraft propulsion assembly, and corresponding device|
    US16/870,391| US20200316701A1|2017-11-08|2020-05-08|Method for manufacturing a structural and/or acoustic panel for a nacelle of an aircraft propulsion unit, and corresponding device|
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