• 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:
    A method of manufacturing a specific aircraft engine pipe (20), comprising producing a first portion (21) of the pipe (20) by means of a first additive manufacturing method and carrying out a second portion (22) of the piping (20) by a second method of additive manufacturing different from the first method.
    公开号:FR3063920A1
    申请号:FR1752058
    申请日:2017-03-14
    公开日:2018-09-21
    发明作者:Jean-Francois Roche
    申请人:Zodiac Aero Duct Systems SAS；
    IPC主号:
    专利说明:

    ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY © Publication number: 3,063,920 (to be used only for reproduction orders)
    ©) National registration number: 17 52058
    COURBEVOIE © Int Cl 8 : B 21 C 37/06 (2017.01), B 33 Y 10/00, 80/00
    A1 PATENT APPLICATION
    ©) Date of filing: 14.03.17. © Applicant (s): ZODIAC AERO DUCT SYSTEMS ©) Priority: Public limited company - FR. @ Inventor (s): ROCHE JEAN-FRANCOIS. ©) Date of public availability of the request: 21.09.18 Bulletin 18/38.©) List of documents cited in the report preliminary research: Refer to end of present booklet (© References to other national documents ® Holder (s): ZODIAC AERO DUCT SYSTEMS related: Anonimous society. ©) Extension request (s): ©) Agent (s): CASALONGA.
    SPECIFIC PIPING FOR AN AIRCRAFT ENGINE AND ASSOCIATED MANUFACTURING METHOD.
    _ A method of manufacturing a specific pipe (20) for an aircraft engine, comprising the production of a first portion (21) of the pipe (20) by means of a first additive manufacturing method and the production of a second portion (22) of the piping (20) by means of a second additive manufacturing method different from the first method.
    FR 3 063 920 - A1
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    , 7 '^' 1 i ^ © 1 • Z '·

     l * ® '21
    Specific piping for aircraft engine and associated manufacturing process
    The present invention relates, in general to a pipe and its manufacturing process.
    More specifically, the invention relates to the manufacture of piping for an aircraft engine.
    On board an aircraft, air conditioning systems are necessary, on the one hand to maintain passenger comfort in the cabin, and on the other hand to perform the defrosting function.
    Generally, the operation of these systems is based on the intake of air upstream of the combustion chamber of the engine, at the level of the compressors.
    In particular, the air sampling is carried out by means of piping, from the aircraft engine called tubing. The part is suitable for extracting air from both the high pressure compressor and the low pressure compressor.
    The air thus removed is redistributed in the aircraft for the purposes of ventilation, defrosting, or even pressurization, for example.
    In the prior art, it is conventional to produce such piping by assembling by mechanical welding several metal components obtained by boilermaking.
    Figure 1 illustrates a pipe 1 according to the prior art. As can be seen, a tube conventionally comprises a central tube 2 connected to two end tubes 3 and 4. A bent tube 5 is fixed to the end tube 4 by means of a connector 8.
    The two end tubes 3 and 4 as well as the bent tube 5 each comprise a flange, respectively 6, 7 and 9 at their free end. The flanges 7 and 9 ensure the connection of the tubing with the low pressure and high pressure compressors.
    A plurality of fittings 10, 11 and 12, the function of which is to support the tubing in the environment of the engine, are distributed along the tubes. In addition, sensor tips 13 and 14 are provided on the work surface.
    The fittings and the sensors are welded to reinforcements or doublantes 15, 16, 17, 19 arranged around the part, intended to reinforce the structure.
    The long and tedious process for manufacturing such piping requires the assembly of a large number of components. In addition, this process generates deformations which weaken the part.
    The present invention relates to a method of manufacturing specific piping for an aircraft engine making it possible to reduce the number of components to be assembled and to limit deformations of the part during its manufacture.
    A method is therefore proposed for manufacturing specific piping for an aircraft engine, comprising the production of a first portion of the piping by means of a first additive manufacturing method and the production of a second portion of the piping using a second additive manufacturing method different from the first method.
    Advantageously, the first additive manufacturing method is an additive manufacturing method by selective laser melting.
    Even more advantageously, the second additive manufacturing method is an additive manufacturing method by direct additive laser construction.
    Provision may be made for the manufacturing process to include the creation of a flare at one end of the first portion, the flare being intended to form a support for starting the production of the second portion.
    According to one characteristic, the manufacturing process may include a step of producing a bent tube on the first portion by the additive manufacturing method by selective laser melting so that the bent tube and the first portion form a one-piece structure.
    According to another characteristic, the manufacturing process can comprise the formation of at least one flange by an additive manufacturing method, the flange and the portion of the part on which the flange is made forming a one-piece structure.
    The invention also relates to specific piping for an aircraft engine, comprising a first portion obtained by a first additive manufacturing method and a second portion obtained by a second additive manufacturing method.
    Preferably, the first portion is obtained by selective laser melting.
    In addition, the second portion can be obtained by direct additive laser construction.
    According to one embodiment of the invention, the piping corresponds to a tube intended for the sampling of air coming from the engine.
    Other objects, advantages and characteristics will emerge from the description which follows, given by way of purely illustrative example and made with reference to the appended drawings in which:
    - Figure 1 is a perspective view of a manifold for an aircraft engine according to the prior art;
    - Figure 2 illustrates a perspective view of a manifold for an aircraft engine according to the invention; and
    - Figure 3 is a longitudinal sectional view showing the ends of a first and a second portion of the tubing according to an embodiment illustrated in Figure 2, intended to be connected to each other.
    In FIG. 2, a specific structural part or piping for an aircraft engine is shown. In the example illustrated, the piping is a tube intended for taking air from the engine.
    The piping 20 has first and second portions and 22. The two portions 21 and 22 here correspond to two tubes connected by one of their ends forming a junction 23.
    The first portion 21 is advantageously provided with a bent tube 24, the first portion 21 and the bent tube 24 forming a one-piece structure.
    By monoblock is meant more particularly a part produced in a single block, in opposition to a part comprising several elements produced independently and then assembled.
    The free end of the portion 21 illustrated comprises an axial flange 25 intended to be connected to a low pressure compressor of the engine and the free end of the bent tube 24 comprises a lateral flange 26 intended to be connected to a high pressure compressor of the engine . The flanges 25, 26 and the first portion 21 preferably form a one-piece structure.
    In addition, the free end of the second portion 22 includes a flange 27 which can be connected to a system for cooling the air taken from the compressors. The flange 27 and the second portion 22 preferably form a one-piece structure.
    A plurality of fittings 28, 29 and 30, the function of which is to support the pipe in the environment of the engine, are distributed along the two portions 21 and 22. The fittings advantageously form a one-piece structure with the portion on which they are provided.
    Preferably, a surplus of material or reinforcement 31 is provided on the second portion 22, so as to reinforce the fittings 28.
    Also, the second portion 22 is advantageously provided with end caps of sensors 32 and 33. Preferably, the surface of the second portion is reinforced by a surplus of material, this reinforcement and the second portion forming a one-piece structure.
    The portion 21 of the piping is obtained by a first additive manufacturing method and the second portion 22 is obtained by a second additive manufacturing method.
    By additive manufacturing, we mean a method for manufacturing an object by superimposing layers of materials from a 3D digital model.
    On the one hand, the first portion 21 is, in the example illustrated, obtained by an additive manufacturing method by selective laser melting.
    On the other hand, the second portion 22 is preferably obtained by an additive manufacturing method by direct additive laser construction.
    In the example illustrated, when the manufacture of the first portion 21 is completed, the production of the second portion 22 is started from the end of the first portion to which the second portion must be connected. No welding is therefore necessary. However, in a different embodiment, provision may also be made for the two portions 21 and 22 to be produced separately and then connected, for example, by welding.
    In Figure 3, the ends of the first and second portions of the tubing forming the junction 23 are shown. The section plane passing through the longitudinal axis 34 reveals a flare 35 at the end of the first portion illustrated. The flaring 35 is intended to form a support for starting the production of the second portion 22. The flared portion 35 facilitates the start of the step of manufacturing the second portion 22 by direct additive laser construction on the first portion 21 and strengthens the junction 23 between the two portions 21 and 22.
    Preferably, the end of the second portion 22 forming the junction 23 also includes a flare 36 so as to strengthen the connection of the two portions 21 and 22.
    For better visibility of the different elements, the two portions 21 and 22 have been shown separated from each other.
    On the one hand, the additive manufacturing method by selective laser fusion, in which a metal powder is gradually and locally fused using a high-power laser, makes it possible to produce complex geometries such as the first portion 21 of tubing 20.
    On the other hand, the additive manufacturing method by direct additive laser construction, in which metal powder, injected coaxially with a laser beam, is fused to produce metal deposits by successive layers, allows larger parts to be produced and faster.
    The manufacturing process described above makes it possible to form structures of complex design of thin thickness and monoblocks. It is thus possible to considerably reduce the number of parts to be assembled for the production of piping such as the pipe 20 illustrated. For example, it is possible to form the bent tube 24 on the first portion 21 without connection.
    In addition, such a method makes it possible to manufacture a plurality of pipes in a reproducible manner, without welds which are difficult to produce given the complexity of the part 20.
    Of course, provision could be made for the invention to relate to a structural part for an aircraft engine other than a pipe.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A method of manufacturing a specific pipe (20) for an aircraft engine, comprising the production of a first portion (21) of the pipe (20) by means of a first additive manufacturing method and the production of 'a second portion (22) of the piping (20) by means of a second additive manufacturing method different from the first method.
    [2" id="c-fr-0002]
    2. Manufacturing method according to claim 1, characterized in that the first additive manufacturing method is an additive manufacturing method by selective laser melting.
    [3" id="c-fr-0003]
    3. The manufacturing method according to claim 1 or 2, characterized in that the second additive manufacturing method is an additive manufacturing method by direct additive laser construction.
    [4" id="c-fr-0004]
    4. Manufacturing method according to any one of the preceding claims, characterized in that it comprises the production of a flare (35) at one of the ends of the first portion (21), the flare (35) being intended to form a support for starting the production of the second portion (22).
    [5" id="c-fr-0005]
    5. Manufacturing method according to any one of the preceding claims, characterized in that it comprises a step of producing a bent tube (24) on the first portion (21) by the additive manufacturing method by selective melting by laser so that the bent tube (24) and the first portion (22) form a one-piece structure.
    [6" id="c-fr-0006]
    6. Manufacturing method according to any one of the preceding claims, characterized in that it comprises the formation of at least one flange (25) by an additive manufacturing method, the flange (25) and the portion of the part. (21) on which the flange (25) is formed forming a one-piece structure.
    [7" id="c-fr-0007]
    7. Specific piping for an aircraft engine, comprising a first portion (21) obtained by a first additive manufacturing method and a second portion (22) obtained by a second additive manufacturing method.
    [8" id="c-fr-0008]
    8. Pipe according to claim 7, characterized in that the first portion (21) is obtained by selective fusion by laser.
    5
    [9" id="c-fr-0009]
    9. Pipe according to claim 7 or 8, characterized in that the second portion (22) is obtained by direct additive laser construction.
    [10" id="c-fr-0010]
    10. Piping according to any one of claims 7 to 9, characterized in that it corresponds to a tube intended for the
    10 air intake from the engine.
    1/3
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3063920B1|2021-04-23|
    引用文献:
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    CN110864176A|2019-12-04|2020-03-06|中国直升机设计研究所|Integrated into one piece's variable cross section drainage channel|
    EP3730740A1|2019-04-24|2020-10-28|ArianeGroup SAS|Pipe for a turbine engine stator part|
    法律状态:
    2018-03-07| PLFP| Fee payment|Year of fee payment: 2 |
    2018-09-21| PLSC| Publication of the preliminary search report|Effective date: 20180921 |
    2019-02-06| PLFP| Fee payment|Year of fee payment: 3 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-18| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-20| CD| Change of name or company name|Owner name: SAFRAN AEROSYSTEMS DUCTS, FR Effective date: 20210712 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752058A|FR3063920B1|2017-03-14|2017-03-14|SPECIFIC PIPING FOR AIRCRAFT ENGINES AND ASSOCIATED MANUFACTURING PROCESS|
    FR1752058|2017-03-14|FR1752058A| FR3063920B1|2017-03-14|2017-03-14|SPECIFIC PIPING FOR AIRCRAFT ENGINES AND ASSOCIATED MANUFACTURING PROCESS|
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