• 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:
    It involves frictionally welding a blade (12 ') with a rotor disc (10') of a turbomachine, the disc comprising a stud (18) projecting on an outer surface of which the blade is intended to be welded. . For this, will be made a reloading (24) on at least a portion of the perimeter of the pad, to said outer surface, a machining of the outer surface of the pad and reloading, to level them, then a friction welding between the external surface of the refilled pad and the blade (12 ').
    公开号:FR3028437A1
    申请号:FR1461037
    申请日:2014-11-14
    公开日:2016-05-20
    发明作者:Jean-Baptiste Mottin；Marc Jacky Vassault
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method of friction welding of a blade to a rotor disk of a turbomachine such as a turbojet engine or a turbine engine. airplane turboprop. A turbomachine monoblock bladed disk (DAM) is a rotor disc which has at its outer periphery an annular row of substantially radial vanes, which are in one piece with the disc. This type of disk can be obtained by friction welding of blades on a disc carrying projecting pads, the radially inner end of each blade being welded to a pad of the disk. In the case where at least one blade of the disk is damaged and must be replaced, it is removed, for example by machining, so that a pad of material (corresponding to the radially inner end portion of the blade machined) remains at the periphery of the disc for welding a new blade. In the previous application WO 2014/083275, it is proposed, for repairing a monobloc bladed disc, to use a friction welding of the blade on the rotor disc, the disc having (at the outer periphery) a stud projecting on a outer surface of which the blade is intended to be welded. More specifically, it is provided in this method: a step of mounting cleats on the leading and trailing edges of the stud, each cleat having a recess in which is engaged the leading edge or trailing edge of the stud; whose shape is substantially complementary to that of this edge, - before the friction welding, to secure the tabs to the stud by welding, and - that, during the friction welding operation, the weld beads between the tabs and the At least a portion of the pads are at least partly expelled into two beads of material which form around the connection zone from the blade to the pad and which are intended to be removed or removed, for example by machining. As interesting as it may be, this technique can find its limits when, especially on the DAMs, there is a large variation of section between the master torque and the Attack Edge (BA) or the Leak Edge (BF). which may result in thickness variations of a ratio of more than 15 or more than 18. In addition, the thickness of the trailing and leading edges on these parts is weak (less than 2mm, or even 1.5mm). Due to the geometry of the parts, the thermal aspects can also become critical, since the welding pressure per unit area is greater in BA and BF and causes more affected areas (ZAT), surface or volume. . Such factors can generate frictional localized deformations BA and BF. The aforementioned strong variation of section can also be the source of a heterogeneity in the microstructure of the welded assembly.
    [0002] It is an object of the present invention to at least limit these disadvantages, or even overcome them. A solution proposed for this purpose is: - to perform a reloading on at least part of the periphery of the pad, to said outer surface, 25 - to machine the outer surface of said pad and reloading, to level them, and - Friction welding the outer surface of the refilled pad and the blade. In practice, the accuracy of reloading will be a priori essential to ensure a final assembly with a desired metallurgy.
    [0003] Thus, the machining operation should favorably ensure a flatness fully consistent with the needs of the friction welding process. In this context, it is recommended that the machining step include the achievement of a flatness less than 0.5 mm and preferably less than 0.1 mm between the outer surface of the stud and the reloading. During friction welding, the melted zone associated with the reloading, so a part of the material brought by this reloading, will be expelled in "flash"; indeed, the electric current, confined to very localized contact points, will cause repeated flashing and expulsion of molten metal. Also, is it advisable: - that the stud rising on the disc along a predetermined direction, at a first height, after machining and before friction welding, then at a second height, less than the first, after friction welding, - and that it is expected to perform the reloading at a height less than the difference in heights between the first and second heights, this in a direction perpendicular to the outer surface of the pad and / or parallel to said predetermined direction.
    [0004] Thus, the height of the reloading will be lower than the value of the material consumption on the plot side; and it will prevent a melted zone residue is present in the final assembly and has the effect of weakening the metallurgical bond and cause significant mechanical reductions.
    [0005] In order to minimize the size of the thermally affected zone (ZAT, zone close to the connection zone where the quenching structure is more pronounced than elsewhere) and the residual stresses related to reloading, the following will also be preferred: - reloading by welding or laser fusion, and / or CMT (short-arc arc welding) or laser deposition.
    [0006] In order to take best account of the geometry of the stud and the blade to be welded to it, in particular with regard to the large variation of section between the master torque and the attack edge (BA) or the edge of leakage ( BF), and the thickness of these trailing and attacking edges which can therefore be less than 2mm, or even 1.5mm, it will also be a priori preferable that the welding step comprises a friction welding linear. In addition to the above welding process, the invention also relates to a blisk for a turbomachine, manufactured or repaired by this method, with all or part of its characteristics.
    [0007] This invention will, if necessary, be better understood and other details, characteristics and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example with reference to the appended drawings, in which: FIG. 1 is a partial schematic perspective view of a turbomachine monoblock blisk; - Figure 2 is a partial schematic perspective view of the disk of Figure 1 after machining (cutting) of some of its blades, for replacement; and FIGS. 3 to 6 are partial schematic views in accordance with the invention, in section along the line of one of the pads of FIG. 2, in which FIG. 3 shows the situation at the end of the refueling, FIG. the situation at the end of the machining of the external surface of said stud and of the reloading, to level them, figure 5 shows the situation at the beginning of the friction welding, after a blank of the blade to be 25 place was made on the pad, and Figure 6 shows the situation towards the end of this welding, while the sparking still expels the material. Although in general the invention applies to the manufacture, in particular the repair, of blades by an additive method associated with friction welding, FIG. 1 thus presents a preferred application of the proposed solution with a view to the repair of a blisk 10 (DAM), taking into account what has already been explained.
    [0008] This illustrates a part of a blisk 10 (DAM) of a turbomachine which is intended to be rotatably mounted about an axis of rotation 10a. Thus, what "axial" is here to consider as oriented (substantially) following, or parallel to the axis 10a, and what is "radial" as oriented (substantially) perpendicularly, or radially to the axis 10a. In addition, is radially internal which is closer to the axis 10a than is radially external. The disc 10 carries an annular row of substantially radial vanes or blades12 which are integral (monoblock) with the disc. The blades 12 are connected by their radially inner ends to an annular platform 14 which extends to the outer periphery of the disk. In case of deterioration of blades or blades 12, it is possible to remove them by machining for replacement. Reference 16 designates a cutting plane of a blade 12 to be replaced. This cutting plane, which defines the (radially) outer surface 180, extends substantially parallel to and away from the outer annular surface of the platform 14. The distance between the platform 14 and the cutting plane 16 is 20 determined so that a stud 18 of material (corresponding to the radially inner portion of the blade extending between the platform 14 and the cutting plane 16) remains on the platform 14 to serve as a support for the Friction welded fastening of a new blade blade. FIG. 2 shows a rotor disc 10 'bearing towards its periphery an annular row of studs 18 of the aforementioned type. Thus, each stud 18 thus projects from the platform 14, at its outer periphery. And the joint / cutting plane 16 is positioned radially beyond the blade / platform connection radius of the disk. The disk 10 'can be obtained by machining and removing the blades 30 of a blisk 10 for the repair of this disk, as explained above. Alternatively, the disk 10 'could be obtained directly, for example from a foundry, for the manufacture of a monobloc blisk. In the latter case, the pads would be made during the manufacture of the disk and would each be intended to receive a blade blade.
    [0009] As can be seen in FIG. 2, each stud has a leading edge 20 and a trailing edge 22 interconnected by a lower surface and an upper surface. A blade (not shown) is to be fixed on each pad 18 of the disk by friction welding, potentially linear or orbital.
    [0010] To avoid the problems described above related to the large variation in the transverse dimension of the stud 18 between its master torque and its leading edges 20 and leakage 22, avoiding the use of the cleats mentioned in WO 2014/083275, it is proposed here to perform a reloading of the stud 18, at the location of the cutting plane 16, following the withdrawal of the corresponding blade. Thus, schematically, FIG. 3 shows that the stud 18 of the illustrated disc 10 'has been reloaded, at 24, over at least a portion of the periphery 18a of the stud, towards the (radially) external surface 180 of this stud. Previously, the disk 10 ', and in particular the pad has been prepared; The zone 180 to be welded was stripped and degreased, with a view to this reloading. The material provided by this refueling is the same metal, or alloy, that of the pad, or a physico material chemically compatible with it for the two parts to weld together.
    [0011] At this stage, the reloading 24 has caused the outer surface 180 to present an irregular surface state, with extra thicknesses where the reloading has been carried out, that is to say in particular on the periphery 18a of the cut area. The outer surface 180 of the stud and the refilling 24 are then machined to level them, as shown diagrammatically in FIG. 4. This results in a larger welding surface 26.
    [0012] In order to standardize the forces applied between the two elements (pad and blade) during the friction welding and to homogenize the thermal gradients in the part, it is recommended that the machining step include the production of a The flatness of the (machined) welding surface 26 less than 0.5 mm, and preferably less than 0.1 mm, therefore between the initial external surface 26 of the pad and the initial external surface 240 of the refilling (see FIG. 3). The machining may include grinding or providing for the use of a cutting tool.
    [0013] The figures show that the height H1 of the refilling 24 will be less than the height, called H2, of material of the stud 18 consumed during the friction welding, with H2 = H3-H4. Thus: - if we consider that before welding, but after machining (Figure 4), the pad 15 18 rises, on the platform 14 of the disk, radially (axis 10b Figures 4,5) following a first height H3 (up to the surface 26), and then following a second height H4 (up to the interface with the replacement blade 12 '), lower than the height H3, after the friction welding (FIG. 6), 20 - then, in a direction perpendicular to the outer surface 180 of the pad and / or parallel to said radial direction 10b, reloading will preferably be performed at a height H1 less than the difference in heights H3-H4 (= H2). Note that we will identically define the two reference bases for the heights H3 and H4, namely for example the base of the stud 18 considered, from, and radially outward beyond, where it s flares inward in 181, for its connection to the platform 14 of the disc. The recharged zone 24 will strengthen the finished part at BA 30 and BF and homogenize the thickness of the area to be welded.
    [0014] In FIGS. 5, 6, the heights H5 and H6 are respectively noted perpendicularly to the outer surface 180 and / or parallel to the radial direction 10b, according to which the replacement blade 12 'is raised, typically on its radially inner portion from 5 its interface 120 'with the surface 26 and a part of which will be consumed during friction welding. Moreover, it can be seen from FIG. 6 that the cumulative H5 + H6 heights of pad materials and blade consumed during friction welding (perpendicular to the outer surface 180 and / or parallel to the direction 10b) have been noted. ).
    [0015] For reloading, a method will be preferred by welding or laser fusion. And, in order to minimize the size, in volume, of the thermally affected zone (ZAT) (by reloading and / or welding) and the residual stresses associated with the reloading, CMT (Meta) Inert-type processes will therefore be preferred. Gas Cold Metal Transfer), or LMD (Laser Metal Deposition). As known, CMT welding is an electric arc welding process but, compared to MIG / MAG processes, the wire undergoes back-and-forth movements. As a result, material transfer takes place at reduced electrical current (almost zero), and thus the deposited material is more "cold". Preferably, CMT welding is done exclusively with fully digital Inverter (frequency converter) power sources. This is a short-arc arc welding process with detachment of drops from the welding wire.
    [0016] As for the technique of laser deposition, it is known by various names, among which: laser deposition (LMD), direct metal deposition (DMD), direct deposition. by Laser [Direct Laser Deposition (DLD)], laser [Laser Engineered Net Shaping (LENS)], laser cladding, laser deposition welding and powder fusion welding. . The method involves the use of a laser beam for forming a melt on a metal substrate, into which the powder is introduced. The powder melts, forming a deposit adhering by fusion to the substrate. Having therefore preferably defined a suitable loading height H1 (less than H2) H1 and established the expected flatness of the machined welding surface 26, a new blade 12 'will therefore be placed with its interface 120' against said surface (radially) external 26, as shown schematically in FIG. 5. And the friction welding of these two compatible elements will be able to begin. Given the intended shapes of the surfaces 180 and 26, it is recommended that this friction welding be linear, even if an orbital or other solution is possible. Among the advantages, there can be noted a saving in material, the possibility of using different materials or fiberization between the blades and the (the platform) of the disc and the possibility of welding hollow blades. The pads 18 and blades 12 'may be made of Ti17. For the welding step, the blade 12 'will advantageously still be only a blank, a gross of the new blade, as schematized in the block illustrated in FIGS. The two elements in contact will be assembled in the pasty state by friction, allowing an assembly without mechanical reduction. It is then only after welding that the blank of the blade will be shaped, typically machined, to give the blade its final shape. Figure 6, we see in 28 that the sparking still expels material, so that heights H4 and H6 further decrease. The Fondue Zone (ZF) linked to the reloading will be expelled in flash. This is why it will be favorable for the height H1 to be less than the value of the material consumption on the plot side (H2). Otherwise, a residue of ZF will be present in the final assembly and will result in weakening the metallurgical bond and leading to potentially significant mechanical abatement. Note also that the ZAT from the reloading operation will be transformed during the friction welding operation.
    [0017] The coarse grains of the HAZ will be refined and found to be similar in size to the forged material. Finally, the welded parts usually undergo non-destructive testing, heat treatment operations, as well as machining steps to restore the geometry to the welded part; in this case the final shape of the blade. Shot blasting can also be done as needed. Finally, we will obtain a new rotor disk, here the blisk turbine monoblock expected. 15
    权利要求:
    Claims (7)
    [0001]
    REVENDICATIONS1. A method of friction welding of a blade (12 ') with a rotor disk (10') of a turbomachine, the disk comprising a stud (18) projecting from an outer surface of which the blade is intended to be welded, the method comprising steps in which: - a reloading (24) is performed on at least a part of the periphery of the stud, towards said external surface, - the external surface (180) of the stud is milled and the reloading, to level them - The external surface of the refilled pad is welded by friction and the blade (12 ').
    [0002]
    2. Method according to claim 1, wherein: - the stud (18) rises on the disk along a predetermined direction (10a), at a first height (H3), after machining and before soldering by friction, then following a second height (H4), lower than the first, after friction welding, and - in a direction perpendicular to the outer surface (180) of the stud and / or parallel to said predetermined direction (10a), reloading is performed at a height (H2) less than the height difference between the first and second heights.
    [0003]
    3. The method of claim 1 or 2, wherein the machining step comprises the realization of a flatness less than 0.5mm and preferably less than 0.1mm between the outer surface of the pad and the reloading.
    [0004]
    4. Method according to one of the preceding claims, wherein the reloading step comprises a reloading (24) by welding type fusion or laser.
    [0005]
    5. Method according to one of the preceding claims, wherein the reloading step comprises a reloading (24) by CMT welding or by laser deposition. 3028437 12
    [0006]
    6. Method according to one of the preceding claims, wherein the welding step comprises a linear friction welding.
    [0007]
    7. A one-piece bladder disk (10 ') for a turbomachine, characterized in that it is manufactured or repaired by the method according to one of claims 1 to 6.
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    同族专利:
    公开号 | 公开日
    EP3218141A1|2017-09-20|
    CN107000127B|2019-12-17|
    US20170328225A1|2017-11-16|
    FR3028437B1|2017-07-14|
    EP3218141B1|2019-04-10|
    US10689989B2|2020-06-23|
    CN107000127A|2017-08-01|
    WO2016075391A1|2016-05-19|
    引用文献:
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    法律状态:
    2015-11-13| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-20| PLSC| Publication of the preliminary search report|Effective date: 20160520 |
    2016-11-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 6 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461037A|FR3028437B1|2014-11-14|2014-11-14|PROCESS FOR FRICTION WELDING WITH BLADE REPLACING ON A TURBOMACHINE BLADE|FR1461037A| FR3028437B1|2014-11-14|2014-11-14|PROCESS FOR FRICTION WELDING WITH BLADE REPLACING ON A TURBOMACHINE BLADE|
    CN201580061912.2A| CN107000127B|2014-11-14|2015-11-04|Method of friction welding buckets to turbine buckets including a build-up welding process|
    PCT/FR2015/052983| WO2016075391A1|2014-11-14|2015-11-04|Method for friction-welding a blade to a turbomachine vane, including a surfacing process|
    EP15807950.9A| EP3218141B1|2014-11-14|2015-11-04|Method for friction-welding a blade to a turbomachine vane, including a surfacing process|
    US15/526,527| US10689989B2|2014-11-14|2015-11-04|Method for friction-welding a blade to a turbomachine vane, including a surfacing process|
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