• 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 present disclosure relates to a method of manufacturing a leading edge metal shield (32) for a fiber-reinforced organic matrix composite blade (16). The method comprises a step of stamping a metal sheet so as to form a general "U" profile, a first wing of the "U" forming a lower winglet (34) and a second wing of the "U" forming a fin extrados connected by a central portion and a step of deposition of at least one metal layer to form a nose (38) of the leading edge shield (32), the deposition being carried out by an additive manufacturing method by melting the central portion by a laser beam and projection of a metal powder beam on the central portion of the leading edge shield (32). The disclosure also relates to a leading edge metal shield (32) and a turbojet comprising a blade having a leading edge metal shield (32).
    公开号:FR3046557A1
    申请号:FR1650139
    申请日:2016-01-08
    公开日:2017-07-14
    发明作者:Damien Hebuterne；Mickael Rancic；Jerome Salmon
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION [0001] The present invention relates to a method of manufacturing a leading edge shield for a blade of composite material. Such leading edge shields are typically designed to protect the leading edges of rotating vanes or guide vanes against impacts. In this context, the term "blades" refers to both the fan blades and the air propeller blades.
    In order to limit their weight, these vanes are typically organic matrix composite, for example polymer, reinforced with fibers. Although these materials have generally very favorable mechanical properties, in particular with respect to their mass, they have a certain sensitivity to point impacts.
    Shields, typically highly resistant metal material, such as titanium alloys, are normally installed on the leading edges of such blades, to protect against these impacts. These shields normally take the form of a thin vane intrados and a thin wing extrados joined by a central part. In this central part, the leading edge shield is thicker and overlaps the leading edge forming a nose of the leading edge shield. The set follows the shape of the dawn on the leading edge and adjacent sections of the intrados and extrados. The intrados and extrados fins extend respectively on these sections of the intrados and the extrados of the blade, and serve mainly to ensure the positioning and fixing of the shield on the leading edge.
    To improve the aerodynamic performance of the blades, their leading edges have increasingly complex shapes, which complicates the manufacture of shields to marry these shapes and the fastening of the shield on the blade.
    The leading edge shield can be machined directly in the mass from a preform. However, the leading edge shields are generally made of titanium-based metal alloy, such as the T6AV, the machining of the leading edge shield is relatively complex and causes the withdrawal of a relatively large amount of material . However, titanium-based alloys are relatively expensive. It is therefore preferable to reduce the amount of titanium that is removed during the machining step.
    Document FR2975734 also discloses a method of manufacturing a leading edge shield for a turbojet fan blade in which the leading edge shield is made by assembling two sheets, for example by welding by diffusion, each plate forming a half central section and a fin of the leading edge shield.
    Generally, the diffusion welding of the two sheets is accompanied by a hot forging of the leading edge shield, for example by hot isostatic pressing. The intrados and extrados fins being relatively thin, the control of their dimensions is relatively difficult during the hot forging step.
    OBJECT AND SUMMARY OF THE INVENTION [0008] The present disclosure aims at remedying at least part of these disadvantages.
    For this purpose, the present disclosure relates to a method of manufacturing a leading edge metal shield for a composite fiber reinforced organic matrix composite blade, comprising the following steps: - hot forming of d a metal foil so as to form a general "U" profile, a first wing of the "U" forming a lower vane and a second wing of the "U" forming an extrados vane, the upper vane and the upper vane being connected by a central part; depositing at least one metal layer to form a nose of the leading edge shield, the deposit being produced by an additive manufacturing process by melting the central portion with a laser beam and by projecting a powder beam metal on the fused middle portion of the leading edge shield.
    The lower and upper fins connected by a central portion being obtained by hot forming of a metal sheet, the metal sheet in the form of "U" thus comprises two fins without welding, especially in the central portion.
    Formatting hot, that is to say at a temperature above room temperature, allows easier deformation of the metal sheet. For example, the metal foil can be heated to a temperature of between 750 and 950 ° C.
    The nose of the leading edge shield is made by additive manufacturing by laser projection, in this case, direct manufacturing by laser projection. This additive manufacturing process is a process in which an interaction between a projected metal powder and a coaxial laser beam is generated. The laser beam may also not be coaxial. The projected powder interacts with the laser beam and feeds a metallic liquid bath formed by the laser on the substrate and causes the formation of a layer of material at each passage of the laser beam and the metal powder bundle.
    Furthermore, the thickness of the metal liquid bath is greater than the thickness of the deposited metal layer. Thus, during the deposition of a metal layer, the previously deposited metal layer is at least partially melted down. This allows homogenization between the deposited metal layers successively. For example, the thickness of the liquid metal bath may be greater than 200 μm and / or the thickness of the liquid metal bath may be less than 700 μm.
    Each metal layer is deposited on the central portion of the leading edge shield so that, layer after layer, the central portion of the leading edge shield is traversed by the laser beam.
    The metal powder may have a chemical composition compatible with the chemical composition of the metal sheet.
    The molten metal powder is thus easily mixed with the metallic liquid bath of the metal sheet.
    The leading edge shield may be made of titanium-based alloy, such as for example the T6AV. The term titanium-based alloy, alloys whose mass content of titanium is the majority. It is understood that titanium is the element whose mass content in the alloy is the highest. The titanium-based alloy has, for example, a mass content of at least 50% titanium, preferably at least 70% titanium, more preferably at least 80% titanium.
    The leading edge shield may also be steel or metal alloy commonly referred to by the trademark Inconel ™. This is later referred to as a nickel-based alloy with nickel and chromium.
    The metal sheet may have a thickness less than or equal to 3 mm, preferably less than or equal to 2 mm, more preferably less than or equal to 1.5 mm.
    This thickness of the metal sheet allows a relatively easy shaping of the metal sheet.
    It can deposit at least two metal layers, each metal layer being deposited by scanning the central portion by the laser beam in a given direction.
    The central portion being scanned by the laser beam in a given direction, the deposition of the metal layer is regular and uniform.
    The given scan direction may be different for two consecutive metal layers deposited on the central portion.
    This allows for improved uniformity of the shield nose. The risk of forming zones in which the interfaces between two consecutive metal layers are not remelted and in which homogenization between two consecutive metal layers is not optimal can also be reduced.
    The scanning data directions for two consecutive metal layers deposited on the central portion may be orthogonal.
    During scanning, the laser beam can be moved by a step less than 2 mm, preferably less than 1.5 mm.
    The thickness of each deposited metal layer may be greater than 150 .mu.m, preferably greater than 200 .mu.m, more preferably greater than 250 .mu.m and less than 600 .mu.m, preferably less than 550 .mu.m, even more preferably less than 500 μm.
    The speed of displacement of the laser beam is greater than 0.5 m / min, preferably greater than 0.7 m / min, more preferably greater than 0.9 m / min.
    The equivalent diameter of the metal powder is less than 200 .mu.m, preferably less than 150 .mu.m.
    The method may also comprise a laser polishing step of the nose of the leading edge metal shield.
    This laser polishing step is performed by means of the laser beam alone. No metal powder is projected on the central part during this stage. This step therefore makes it possible to remelt the outer surface of the nose of the leading edge shield, in particular to homogenize the last deposited metal layer.
    The present disclosure also relates to a leading edge metal shield comprising an extrados vane and an extrados fin obtained by stamping a metal sheet so as to form a general "U" profile, a first wing of the "U" Forming the wing fin and a second wing of the "U" forming the extrados winglet and a nose obtained by an additive manufacturing process by laser projection on a central portion connecting the lower winglet and the extrados winglet.
    The present disclosure also relates to a turbojet comprising at least one blade having a leading edge metal shield as defined above.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will emerge from the following description of embodiments of the invention, given by way of non-limiting examples, with reference to the appended figures, in which: Figure 1 is a schematic perspective view of a turbofan engine; - Figure 2 is a schematic perspective view of the intrados side of a rotating blade of the fan of the turbojet engine of Figure 1; FIG. 3 is a sectional view of the leading edge metal shield of FIG. 2 along section plane III-III; - Figures 4A and 4B are sectional views of two hot forming tools of a metal sheet; FIG. 5 is a perspective view of the U-shaped metal foil; - Figure 6 a sectional view of a layer deposition device by additive manufacturing by laser projection; FIGS. 7 and 8 are cross-sectional views of the leading edge metal shield of FIG. 5 along section plane VII-VII, after deposition of two and six metal layers, respectively; FIG. 9 illustrates two scanning directions for two consecutive metal layers deposited on the central part of the leading edge metal shield; FIG. 10 is a sectional view of the leading edge metal shield of FIG. 5 along section plane VII-VII, after laser polishing of the nose of the leading edge metal shield.
    DETAILED DESCRIPTION OF THE INVENTION FIG. 1 illustrates a turbofan engine 10 comprising a gas generator group 12 and a fan 14. This fan 14 comprises a plurality of rotating vanes 16 arranged radially about an axis. central X, and aerodynamically profiled so as to impulse the air by their rotation.
    Thus, as illustrated in Figure 2, each blade 16 has a leading edge 18, a trailing edge 20, a lower surface 22, an extrados 24, a blade head 26 and a blade root 28 The blade 16 also comprises a blade body 30 made of a composite material, in particular an organic matrix, for example a polymer, reinforced with fibers. The leading edge 18 being particularly exposed to impacts, the leading edge 18 is protected by a leading edge shield 32 integrated with each blade. In other words, the leading edge shield 32 is assembled on the blade body 30.
    The leading edge shield 32 is made of a material having a better resistance to punctual impacts than the composite material of the blade body 30. The leading edge shield 32 is metallic, and more specifically alloy based on titanium, such as TA6V (Ti-6AI-4V). The leading edge shield 32 could also be steel or Inconel.
    As shown in Figures 2 and 3, the leading edge shield 32 comprises a lower wing 34, an upper wing 36 joined by a nose 38 thicker than the lower and upper fins 34, 36. The nose 38 is intended to overlap an edge of the blade body 30 and connects the lower wing 34 and the extrados wing 36. The leading edge shield 32 therefore has a general "U" profile, the wings of " U 'forming the intrados fins 34 and extrados 36. The intrados and extrados fins 34, 36 ensure the positioning of the shield 32 on the blade body 30 by resting on adjacent sections of the intrados 22 and the extrados 24.
    The length of the intrados vane 34 may be equal to the length of the extrados vane. The lengths of the two lower and upper fins may also be different. In FIG. 3, the length of the intrados vane 34 is greater than the length of the extrados vane 36.
    The manufacturing method of the leading edge shield 32 will be described.
    FIG. 4A shows a metal sheet 40 having a thickness of 1 mm and disposed in a hot forming tool 42 having a die 44 and a counter-mold 46. The hot forming tool 42 is evacuated. The metal foil 40, in this example titanium based alloy, such as for example the TA6V, is then heated by the shaping tool 42, for example at a temperature close to the β transce of TA6V. Indeed, the β form of this alloy is easier to deform.
    Once the metal sheet 40 to the desired temperature, a pressurized gas comes to press the metal sheet 40 against the matrix 44 so as to form a general "U" profile of the metal sheet 40. The metal sheet shaped The general "U" is then cooled to room temperature and is output from the hot shaping tool 42. Thus, a metal foil having a general "U" shape is obtained, as shown in FIG. .
    FIG. 4B shows a metal sheet 40 disposed in a hot forming tool 42 comprising a die 44 and a punch 50. As previously described, the hot forming tool 42 is evacuated and the metal foil 40 then heated by the shaping tool 42. Once the metal foil 40 has reached the desired temperature, the punch 50 presses the metal foil 40 against the die 44 so as to form a general U-shaped profile. The metal sheet generally "U" -shaped is then cooled to room temperature and is removed from the hot shaping tool 42. Thus, a metal foil whose overall profile is U ", as shown in Figure 5.
    In FIG. 5, the metal foil 40 comprises a lower fin 34, an extrados fin 36 interconnected by a central portion 48. It can also be seen that the metal foil 40 is arched, that is to say that the central portion 48 is not rectilinear.
    Figure 6 shows a sectional view of a device 52 for deposition of metal layer by additive manufacturing by laser projection. This device 52 comprises a nozzle 54 for projecting a metal powder bundle 56 onto a surface 58 of a metal body 60. The surface 58 is scanned by a laser beam 62. In FIG. 6, the laser beam 62 and the beam of metal powder 56 are coaxial.
    The laser beam 62 creates a bath of metal liquid 64 melting the metal of the metal body 60 to a thickness H. The metal powder 56 which is projected by the nozzle interacts with the laser beam 62 over a distance D and feeds the bath of metal liquid 64 so as to form, at each passage, a metal layer 66 of thickness E.
    Because the thickness H of the metal liquid bath 64 is greater than the thickness E of each metal layer 66 deposited, during the deposition of a metal layer 66, the previously deposited metal layer 66 is at least partially melted down. . This allows homogenization between the metal layers 66 deposited successively. It is therefore clear that the separations between the various deposited metal layers 66 are only shown in FIG. 6 for the understanding of the operation of the additive manufacturing process. In practice, the separations between two deposited metal layers 66 attenuate each time the laser beam 62 passes.
    FIG. 7 shows the leading edge shield 32 after the deposition of two metal layers 66 on the central portion 48 of the metal sheet 40 to form the nose 38 of the leading edge shield 32.
    In this example, the metal powder 56 sprayed onto the metal sheet 40 has the same chemical composition as the metal sheet 40. The powdered metal powder 56 may also be different from the chemical composition of the metal sheet 40 and have a composition chemical compatible with the chemical composition of the metal foil 40.
    Figure 8 shows the leading edge shield 32 after the deposition of six metal layers 66 on the central portion 48 of the metal sheet 40 to form the nose 38 of the leading edge shield 32.
    Figure 9 illustrates two scanning directions for two consecutive metal layers 66 deposited on the central portion 48 of the leading edge shield 32. A first direction is shown in solid line and a second direction is shown in broken lines. In FIG. 9, the two scanning directions are orthogonal. The scanning pitch P, that is to say the distance between two scans of the laser beam 62 for the deposition of a given metal layer 66, is equal between each scan. In FIG. 9, the scanning pitch P is identical from one metal layer 66 to the other.
    For example, the power of the laser beam 62 is 550 W, the gas used to project the metal powder 6 is argon, the scanning speed of the laser beam is 1 m / min, the pitch between two sweeps in a given direction is 1 mm and the thickness E of the deposited metal layers is between 300 and 400 μm.
    The nose 38 of the leading edge shield is made in this example by depositing seven metal layers 66.
    As shown in Figures 7 and 8, the surface of the metal layer 66 which has just been deposited is not smooth.
    FIG. 10 shows the leading edge shield 32 after the laser polishing step of the nose 38 of the leading edge shield 32.
    This laser polishing step is performed by means of the laser beam 62 alone. No metal powder is projected on the central portion 48 during this step. This step therefore makes it possible to remelt the outer surface of the nose 38 of the leading edge shield 32 in order, in particular, to homogenize the last metal layer 66 deposited with the metal layers 66 deposited previously and to smooth the surface of the nose 38 of the edge shield. of attack 32.
    The leading edge shield 32 may then be arched and / or twisted so as to conform to the shape of the blade body 30.
    Although the present description has been described with reference to a specific embodiment, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In addition, individual features of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A method for manufacturing a leading edge metal shield (32) for a blade (16) made of fiber-reinforced organic matrix composite, characterized in that it comprises the following steps: - shaping at hot metal sheet (40) so as to form a general "U" profile, a first wing of the "U" forming a lower vane (34) and a second wing of "U" forming an extrados vane (36) , the lower vane (34) and the upper vane (36) being connected by a central portion (48); depositing at least one metal layer (66) to form a nose (38) of the leading edge shield (32), the deposition being carried out by an additive manufacturing process by melting the central portion (48) by a laser beam (62) and spraying a metal powder beam (56) on the fused central portion (48) of the leading edge shield (32).
    [2" id="c-fr-0002]
    2. Method according to claim 1, wherein depositing at least two metal layers (66), each metal layer (66) being deposited by a scanning of the central portion (48) by the laser beam (62) in a given direction .
    [3" id="c-fr-0003]
    3. Method according to the preceding claim, wherein the scan direction is different for two consecutive metal layers (66) deposited on the central portion (48).
    [4" id="c-fr-0004]
    4. Method according to the preceding claim, wherein the scan data directions for two consecutive metal layers (66) deposited on the central portion (48) are orthogonal.
    [5" id="c-fr-0005]
    5. Method according to any one of claims 2 to 4, wherein during scanning, the laser beam (62) is displaced by a pitch (P) less than 2 mm, preferably less than 1.5 mm.
    [6" id="c-fr-0006]
    6. A method according to any preceding claim, wherein the thickness (E) of each deposited metal layer (66) is greater than 150 μm, preferably greater than 200 μm, still more preferably greater than 250 μm, and less than 600 μm, preferably less than 550 μm, still more preferably less than 500 μm.
    [7" id="c-fr-0007]
    7. Method according to any one of the preceding claims, wherein the speed of displacement of the laser beam (62) is greater than 0.5 m / min, preferably greater than 0.7 m / min, still more preferably greater than 0.9 m / min. min.
    [8" id="c-fr-0008]
    The method of any of the preceding claims, further comprising a laser polishing step of the nose (38) of the leading edge metal shield (32).
    [9" id="c-fr-0009]
    A leading edge metal shield (32) for a blade (16), characterized in that the leading edge shield (32) has an extrados vane (34) and an extrados vane (36) obtained by stamping of a metal foil (40) so as to form a general U-shaped profile, a first wing of the "U" forming the intrados fin (34) and a second wing of the "U" forming the extrados fin (36). ) and a nose (38) obtained by an additive manufacturing process by laser projection on a central portion (48) connecting the intrados fin (34) and the extrados fin (36).
    [10" id="c-fr-0010]
    10. Turbojet engine (10) comprising at least one blade (16) comprising a leading edge metal shield (32) according to claim 9.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3046557B1|2020-05-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20120233859A1|2009-11-30|2012-09-20|Snecma|Method for producing a metal reinforcement for a turbine engine blade|
    US20120301292A1|2010-02-26|2012-11-29|United Technologies Corporation|Hybrid metal fan blade|
    EP2586972A2|2011-10-25|2013-05-01|Whitcraft LLC|Airfoil devices, leading edge components, and methods of making such components|
    EP3050651A1|2015-01-16|2016-08-03|Hamilton Sundstrand Corporation|3d printing of lead edge protective sheaths|WO2020169938A1|2019-02-21|2020-08-27|Safran Aircraft Engines|Method for repairing a turbomachine rotor blade|
    FR3094253A1|2019-03-29|2020-10-02|Safran Aircraft Engines|PROCESS FOR BONDING A METAL PART ON A COMPOSITE MATERIAL ELEMENT OF AN AIRCRAFT TURBOMACHINE|
    FR3108664A1|2020-03-31|2021-10-01|Safran Aircraft Engines|Fan rotor with upstream center of gravity vanes|
    FR3112821A1|2020-07-22|2022-01-28|Safran Aircraft Engines|SHIELD FOR BLADE IN COMPOSITE MATERIAL, BLADE AND TURBOMACHINE COMPRISING THE SHIELD, METHOD FOR MANUFACTURING THE BLADE|
    法律状态:
    2017-01-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-07-14| PLSC| Publication of the preliminary search report|Effective date: 20170714 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1650139A|FR3046557B1|2016-01-08|2016-01-08|METHOD FOR MANUFACTURING A LEADING EDGE SHIELD INCLUDING AN ADDITIVE MANUFACTURING STEP AND LEADING EDGE SHIELD|
    FR1650139|2016-01-08|FR1650139A| FR3046557B1|2016-01-08|2016-01-08|METHOD FOR MANUFACTURING A LEADING EDGE SHIELD INCLUDING AN ADDITIVE MANUFACTURING STEP AND LEADING EDGE SHIELD|
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