• 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 production process comprises the steps of producing a preform by selective melting, the preform comprising an assembly surface intended to be brazed to the part to be repaired and containing a brazing material, and then to assemble the preform to the piece. of the turbomachine by soldering-diffusion. The thermal amplitude of the main transformation peak (A1) of the brazing material used to produce the preform will be at least twice each of the respective thermal amplitudes of the secondary peaks (A2, A3) of transformation of this brazing material.
    公开号:FR3028436A1
    申请号:FR1461035
    申请日:2014-11-14
    公开日:2016-05-20
    发明作者:Jean-Baptiste Mottin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method of repair, this does not exclude the manufacture of a turbomachine part.
    [0002] Certain parts of a turbomachine, such in particular as turbine blades, are subject to erosion phenomena or wear, causing significant damage that must be repaired beyond a certain number of cycles. These damages may in particular be in the form of a lack of material. The repair then consists in giving back to the used part its original shapes and dimensions, or very close to them. For this, several techniques are used in the prior art, including the manufacture of a preform by sintering a superalloy powder and a solder powder (whose melting point is lower than the superalloy powder). , then soldering by diffusion of the preform on the part to be repaired (hereinafter the term "metal" includes alloys). It is recalled that brazing is a process consisting in assembling, for example, two metal parts, of identical or different materials, by means of a filler metal whose melting point is much lower than those of the materials of the parts. . The solder contained in the filler metal is brought to the liquid state and the parts are heated by the filler metal, but remain solid. Soldering-diffusion (brazing or transient liquid phase bonding diffusion) is an assembly operation of two metal parts similar to brazing, but in which the difference in composition between the filler metal and the parts to be assembled is gradually absorbed by diffusion heat treatment. This treatment leads to the formation of a quasi-homogeneous chemically bonded and whose characteristics are close to those of the parts to be assembled. Thus, solder-diffusion could be considered a conventional solder to which a diffusion treatment has been added. During the assembly of two parts, a filler metal of chemical composition is used close to that of the parts to be assembled, but having thanks to the solder, a lower melting temperature. During soldering, the solder melts and wets the surfaces to be bonded, then solidifies isothermally by diffusion of the filler additive elements into the workpiece material, the composition of which changes and becomes homogenized. with that of the brazing cord thus formed. In the final stage of solder-diffusion, the filler metal is a body and is indistinguishable from the material of the pieces.
    [0003] Such a method makes it possible to perform, as indicated above, the assembly of several parts while giving the assembled parts and their connections mechanical and metallurgical characteristics comparable to those of the original parts. The temperatures used in such a process are further compatible with the superalloys conventionally used for producing these parts, particularly in the aeronautical field. Repairing a part with a substantially flat preform, however, limits the applications of this method. Thus, FR 2 978 070 proposes, in the case, for example turbine blades, where the area to be repaired may have a three-dimensional profile, with a quantity of material to be added which may not be constant over the entire area ( variable thickness in particular): - to achieve, layer by layer, a preform by selective fusion (also called DMLS - Direct Metal Laser Sintering - or metal powder sintering), a powder containing a base material identical or similar to that of the part, the preform comprising (at least) an assembly surface intended to be brazed to the part of the turbomachine to be repaired and containing for this purpose a brazing material mixed with the base material, said powder containing the mixture having, when heating up heat flux generation, a main peak of brazing material transformation, greater amplitude of the heat flux, and secondary peaks of transformation of the matte brazing electrode, lower amplitudes of heat flow, - and assemble the preform to the part of the turbomachine by soldering-diffusion.
    [0004] But such parts where the area to be repaired can therefore have a three-dimensional profile, with a quantity of material to add that may not be constant over the entire area, are not achievable with the expected quality. In direct manufacture (layer-by-layer production of the preform by selective melting), the molten material is found to be able to crack strongly on cooling, thereby impairing the production. An object of the invention is to avoid these situations. For this it has been imagined to control the withdrawal of the material. More specifically, it has been imagined that the solder has only one main processing peak during heating (and / or cooling). Even more precisely, it is proposed that the heat flux amplitude of the main transformation peak of the brazing material used to make the preform be at least twice (within 20%) of the respective amplitudes of the heat fluxes of the secondary peaks of the transformation of this brazing material, as illustrated in the accompanying figures. Thus after mixing the solder powders and superalloy (including in the case of pre-alloyed powders, that is to say previously mixed together), not only this compound will have two main transformation peaks (one for the fusion of solder, the second for superalloy melting), but secondary transformation peaks for solder melting will be much smaller in magnitude than the main peak. The method according to the invention can therefore be applied to the production of various turbine engine parts and in particular the repair of the turbine blades.
    [0005] The preform can be made with a controlled roughness: the preform is easier to braze when it has a certain roughness, since the solder can then wet more effectively the surfaces to be assembled.
    [0006] The base material is identical or similar to that of the part to be repaired, so as to favor the assembly of the preform by soldering-diffusion. Two "similar" materials have at least the same base (for example: nickel, cobalt, titanium, ...). One application of the invention relates to the metallurgical production of powders of shaped parts intended to be assembled by self-brazing to metal parts capable of receiving them and said receptors. Self-brazing is the autogenous brazing of the shaped part on the receiving metal part, the brazing elements being contained in the shaped part (which will therefore be favorably in three dimensions). The self-brazing of this shaped part on the metal part may comprise or be followed by a solid state diffusion heat treatment, thus constituting what is commonly referred to as a soldering / diffusion operation, a treatment intended for to homogenize the composition and the structure of the shaped parts and the (zone of) connection by self-brazing. In this context, it is recommended that the chemical composition of the abovementioned base material (used to make the preform by selective melting) corresponds to a superalloy based on Ni, Co, Ti or Fe and that brazing material corresponds to a Ni-based alloy, and / or Co, and / or Fe in which the melting element is Si and / or B (as known per se, a melting element, such as silicon or boron, for example, is an element that substantially lowers the melting temperature (solidus) of the alloy in which it is introduced).
    [0007] As for the compound to be supplied to the brazing material so that said amplitude of the heat flux of the main transformation peak of the brazing material is therefore equal to at least twice the respective amplitudes of the heat fluxes of the secondary transformation peaks of this material. Brazing material, it is recommended that it be selected from Cr, Co, Mo, Fe. A weight percentage of this compound is recommended between 7 and 23%. These choices are particularly suitable for producing turbine parts, including turbine blades. In this regard, it is even advisable that in nominal composition and in weight percentages, the brazing material is a Ni-based alloy, with Co, Si, B, but also Cr between 9 and 19% (being specified that all percentages are, in the present description, provided in weight percent). Using the so-called NiCoSiB soldering powder 1060 based on Ni and Co 20, Si 4.5, B 3, an equilibrium result will be obtained between low risk of cracking, resistance to hot corrosion and the final qualities of the product. couple base material / brazing material, especially vis-à-vis the resistance to creep at high temperature. According to another characteristic of the invention, the preform is made by selective melting of a powder of the base material and a brazing powder, the melting temperature of which will be lower than the melting temperature of the base powder. . The dimensional tolerances of the preform will thus be very small and the final assembly optimized. The preform which already contains a brazing material may be brazed directly to the workpiece to be repaired, depending on the amount of brazing material. Preferably, the preform will contain at least 60% of base material, so as to impart sufficient mechanical characteristics to the preform.
    [0008] In one variant of the invention, the preform is made by selective melting of a powder containing only the base material.
    [0009] A deposition of brazing material can then be performed on the assembly surface of the preform. This deposit is for example made by laser projection or by plasma projection of a solder powder, or by co-deposition (electroplating) in an aqueous medium. The thickness of such a deposit will for example be between 20 and 200 lm. The invention also relates to a turbomachine part produced by carrying out the aforementioned method.
    [0010] The invention will be better understood and other details, features and advantages of the invention will become apparent on reading the following description given by way of nonlimiting example with reference to the accompanying drawings in which: FIGS. 1, 2 3 are perspective views of a preform used for the repair of a turbomachine blade, FIG. 4 is a schematic view of a selective powder melting installation, FIGS. 5 to 7 are views. schematic diagrams illustrating various steps of the repair method according to the invention; FIG. 8 is a schematic view of a laser projection installation; FIG. 9 is a schematic view of a plasma projection installation; FIG. shows, on a graph, a situation where there is a significant risk of cracking of the molten material in the case of the use of a known composition, in accordance with a solution of the prior art, - FIG. 11 shows, on a comparable graph, a solution aiming at mitigating this risk, according to what proposes the invention, - and figure 12 compares, on a graph comparable to those which preceded, but with the cooling, the peaks of transformation related to solder, without the addition of Cr in this case (bottom curves, Nos. 1 to 3), and with addition (top curves).
    [0011] FIGS. 1 and 2 show a preform 1 used in a process for repairing a leading edge or a trailing edge of a turbine blade, in a turbomachine such as a turbojet engine or a turbojet engine. 'plane. Figure 3 shows a preform 1 used in a method of repairing a platform of a blade of this type. In both cases, the preforms 1 have complex three-dimensional shapes. In a first embodiment, the repair method according to the invention consists firstly of producing, layer by layer, a sintered preform 1 by selective melting of a mixture of powders comprising a powder of a base material. and a powder of a brazing material, these materials having been premixed or not. The melting temperature of the brazing material is lower than that of the base material. By way of example, the melting temperature of the brazing material will be between 1000 and 1300 ° C. while the melting temperature of the base material will be between 1200 and 1600 ° C. The base material is preferably a superalloy, for example a nickel-based superalloy. The brazing material is in this case also nickel-based, and further comprises melting elements, such as silicon and / or boron. Selective melting is carried out using an installation such as that shown in FIG. 4. This installation comprises a tank 2 containing the mixture of metal powders 3 and whose bottom 4 is movable and displaceable in translation by a rod. 5 of a jack, and a neighboring tank 6 whose bottom is constituted by a movable plate 7, also movable in translation by a rod 8 of a jack. The installation further comprises a scraper 9 for feeding powder from the tank 2 to the tank 6, by displacement along a horizontal plane A, and means 10 for generating a laser beam or for an electron beam, coupled to a computer-controlled device 11 for orienting and moving the beam 12. A receiving pan 13 of the excess powder 14, adjacent to the vessel 6, may also be provided. The operation of this installation is as follows: Firstly, the bottom 4 of the tank 3 is moved upwards so that a certain quantity of powder 3 is located above the horizontal plane A. The scraper 9 is moved from left to right, so as to scrape said powder layer 3 into the reservoir 6 and deposit a thin layer of metal powder on the horizontal flat surface of the plate 7. The amount of powder and the position of the plate 7 are determined so as to form a layer of powder of a selected and constant thickness. A laser beam 12 or an electron beam, perpendicular to the plane A, then scans a certain area of the layer formed in the tank, so as to locally melt the solder powder (and not the base powder). The melted zones then solidify, by agglomerating the grains of the base powder and forming a first layer 15 of a sintered preform 1, this layer 15 having for example a thickness of the order of 10 to 150 pm. More particularly, the thickness of the layer 15 is between 10 and 45 μm, respectively between 45 and 150 μm, when the powder is melted with the aid of a laser beam or with a beam respectively. electron. The plate 7 is then lowered and a second layer of powder is fed, in the same manner as above, to the first layer of powder. By controlled displacement of the beam, a second layer 16 is formed by sintering on the first layer 15. These operations are repeated until the complete formation of the preform 1. The layers 15, 16 have substantially the same thickness.
    [0012] In the case where the preform 1 is built layer by layer by selective melting of the powder with the aid of a laser beam, the powder 3028436 9 has a mean grain size of between 10 and 45 μm. The particle size distributions of the two powders are not necessarily identical. Near average is preferred, that is to say the case where the two powders each have an average particle size of between 10 5 and 45 pm, in order to facilitate the mixing of the powders. In the case where the preform 1 is built layer by layer by selective melting of the powder with the aid of an electron beam, the powder has a mean grain size of between 50 and 100 μm. This preform 1, which contains a sufficient quantity of brazing material, can be brazed directly onto the part to be repaired 17 (FIG. 5). For this, the soldering surfaces of the preform 1 and the part to be repaired 17 are degreased and / or pickled, then the preform 1 is placed on the surface of the part to be repaired (FIG. 6). The preform 1 is then pointed (laser pointing, capacitor discharge, etc.) to the part to be repaired, in order to hold it in position on the part to be repaired. The preform 1 and the part to be repaired 17 are then placed in a oven where they will undergo a soldering-diffusion cycle. For a NK17CDAT base material and a NiCrB solder material, the solder-diffusion may comprise a temperature rise of about 2 hours 30 minutes at 1205 ° C, a first step of 15 minutes at 1205 ° C, followed by a second level of 2 hours at 1160 ° C., then a temperature drop of approximately 1 hour from 1160 ° C. to 20 ° C.
    [0013] In solder-diffusion, the brazing material melts first. The liquid phase to which it gives rise is retained by capillarity and wets the surfaces of the part to be repaired 17 and of the preform 1. After cooling, a solid intermediate layer is formed between the preform 1 and the part to be repaired 17, and a homogeneous metallographic structure diffusion bonded to the surfaces of these parts.
    [0014] The repaired part thus has mechanical characteristics that are identical or similar to those of a new part. The repaired part finally undergoes a finishing operation in which the repaired surfaces are adjusted or machined so that the part finds the dimensions of a new part (FIG. 7). In order to further increase the mechanical characteristics of the preform 1, and therefore of the repaired part, said preform 1 may comprise, at heart, a reduced or zero proportion of brazing material, a deposition of powder rich in soldering material which can then be be made on the surface to be brazed. Thus, the preform 1 can be made by selective melting of a mixture of base powder and solder powder in which the proportion by weight of the base powder is greater than 90%. It is also possible to make the preform 1 by selective melting of a base powder only. In this case, it is necessary to form a layer of a powder enriched in brazing material on the surface of the preform. This layer can be made by laser projection or by plasma spraying, electroplating.
    [0015] The powder used for the formation of this layer may comprise 60 to 90% by weight of base powder and 10 to 40% by weight of solder powder. The principle of laser projection deposition is illustrated in FIG. 8. This deposition method consists of projecting a powder 19 against a surface 18 and heating the projected powder with the aid of a laser beam 20 oriented towards the surface 18 , so that said powder 19 melts and then solidifies on said surface 18. For this, the preform 1 is placed in an enclosure 21 containing for example argon. Means 22 for generating a YAG laser beam produce a laser beam 20 directed towards the surface 18 of the preform 1, through a nozzle 23 oriented perpendicular to this surface 18. The nozzle 23 and the The laser beam 20 can be moved relative to the surface (or vice versa) via a control and appropriate means 24. One or more successive layers 31, rich in solder material, can thus be formed on the surface. corresponding surface 18 of the preform 1. The principle of plasma spraying is illustrated in FIG. 9. This deposition process consists in injecting a powder 19 into a plasma dart 32 where it is melted and projected at high speed towards the surface at The plasma dart 32 is produced inside a torch by an electric arc generated between two electrodes 33, 34 cooled by means of a cooling circuit 35. The melting of the powder grains 19 is caused by the very high temperatures within the plasma, making it possible to deposit high melting point materials. By solidifying, the material of the powder forms a deposit on the surface 18 of the preform 1. The high speeds of the gases and the particles make it possible to obtain a strong adhesion of the deposit, a low porosity, and a level of chemical transformation. reduced. Traditional examples of basic materials are given below. For each material, the reference and the corresponding chemical composition (percentage by weight) are given: Astroloy (NK17CDAT): nickel base, cobalt: 16.9%, chromium: 14.8%, aluminum: 3.87%, titanium: 3.45%, molybdenum: 5.1%, carbon: 0.015%. Rene 77: Nickel base, cobalt: 14 to 15%, chromium: 14 to 15.5%, molybdenum: 3.9 to 4.5%, titanium: 3 to 3.7%, aluminum: 4 to 4.6 %. Co-285: Cobalt base, nickel: 9.5 to 11.5%, chromium: 24.5 to 25.5%, iron: 0 to 2%, manganese: 0 to 1%, silicon: 0 to 1 %, tungsten: 7 to 8%, carbon: 0.45 to 0.55%. 3028436 12 - SYP3: Nickel base, cobalt: 17%, chromium: 15%, molybdenum: 5%, titanium: 3.5%, aluminum: 4%. In the same manner, examples of brazing materials are given below: NiCoSiB 1060 = TY 134b TY 134b: Nickel base, cobalt: 18-22%, silicon: 4-5%, boron: 2.7 at 3.15%, carbon: 0 to 0.06%. TY 135b: nickel base, cobalt: 18 to 22%, silicon: 3.5 to 4%, boron: 2.7 to 3.15%, carbon: 0 to 0.06%.
    [0016] By way of example also, the mixture of powders (base material / brazing material) may comprise 75% by weight of SYP3 type powder (base material) and 25% by weight of TY 134b type powder (material). brazing). Alternatively, this mixture may comprise 70% by weight of Co-285 type powder (base material) and 30% by weight of TY 135b type powder (solder material). FIG. 10 shows that with a composition of the type SYP3 and TY134b mixed there is nevertheless a significant risk of cracking of the molten material. In fact, on the graph of Differential Thermal Analysis illustrated, the mixture of powders above, where the mixture reaches more than 1300 ° C. after more than one hour of heating, is distinguished: a main transformation peak 37 brazing material, of greater thermal amplitude, and, on both sides, two secondary peaks 39, 41 of transformation of this same brazing material, of lesser thermal amplitudes than the main peak, as can be seen. Later, in a comparable temperature range (between 900.degree. C. and 1140.degree. C.), the occurrence of the peak or peaks (marked globally 42) of transformation of the base material, here a superalloy, is noted.
    [0017] The precise values of the temperature and the time they occur can be read in FIG. 10, where the temperatures - in ° C. - are noted directly on the graph. The amplitude of the peaks (A1 / A2 / A3 figure 11) is related to heat flows. The time displayed on the abscissa is not of major interest in our case. For FIGS. 11 and 12, the heat flux is plotted on the ordinate and the temperature on the abscissa. The measurement of the heat flow of the material concerned can be obtained by a "RDF Micro - Foil" ® sensor. It is a sensor that is connected to a microvoltmeter (voltage U). The assembly then provides a direct measurement of the rate of heat transfer or cooling through both the sensor and the mounting surface. There is a direct relationship between the output of the microvoltmeter and the heat flow. In FIGS. 11-12, the negative voltage values indicate that it is an exothermic reaction, with the values being obtained by difference with a standard measurement made with an empty crucible. On a graph of this nature, the two examples of curves 43a and 43b of FIG. 11 therefore each show a solution according to the invention aimed at enabling a part to be produced by direct manufacture, according to one of the techniques presented. above, but with a solder on a base known as "RBD 61" (ie a mixture SYP3 + TY 134b), but with Cr added (here between 9 and 19%, for example at 14% ) having, for example for the curve 43b: - not only a single main peak 44 of transformation of the brazing material used to make the preform, during the heating (this being identical to the cooling), - but also a thermal amplitude (c that is to say heat flux) Al of this main peak 44 which is at least twice each of the thermal amplitudes, respectively A2 and A3, secondary peaks 45,47 of transformation of this same brazing material.
    [0018] Again, at higher temperatures (for temperatures above 1200 ° C), there is found the peak (s) (marked (s) globally 49) transformation of the base superalloy. FIG. 12 further shows that, at cooling, the transformation peaks 51 linked to the "doped" solder (with thus the added chromium in the preferred example retained) are attenuated with respect to what they would have been (see reference numerals 53, for curve No. 3, for example) without adding chromium to the alloy in question. Thus, it will be well limited the risk of cracking parts.
    [0019] In 55 was found the evolution curve of the base material, that is to say here the superalloy retained. For the sake of clarity, we will define: - a "peak of transformation" of the brazing material (this also applying to the base material, here a superalloy) as the temperature (or range of temperatures) of the beginning of fusion of solder (or base material respectively), and "amplitude of a heat flux" (Ai), such as the difference between two heat flux values, for the same sample, at two temperature values very close to each other, less than 50 ° C.
    [0020] Thus, after mixing the solder and superalloy powders, this compound has two transformation peaks (one for the solder melting, the second for the superalloy melting). The reduction in the number of transformation peaks during heating and cooling makes it possible to limit the stresses seen by the part during cooling and to avoid any cracking. As a favorable example of embodiment, a given piece may in particular be made of nickel-based superalloy by the powder metallurgy process with the aid of a base powder A and a solder powder B. The base powder A may be that known under the commercial designation Astroloy (NK17CDAT according to AFNOR designation). This material is entirely compatible with the Rene Maze superalloy 30 used for a blade, in particular from the point of view of solidus temperature and mechanical characteristics. The solidus temperature of the base powder A is 1240 ° C. Its liquidus temperature is 1280 ° C. The brazing powder B used for sintering the Astroloy powder and self-brazing with the blade is a Ni-Co-Si-B alloy powder containing by weight 17% Co, 4% Si, 2, 7% B. The solidus temperature of the solder powder B is 965 ° C. Its liquidus temperature is 1065 ° C and is lower than the solidus temperatures of the base powder A and that of the dawn. These data make it possible to define a self-brazing temperature of 1200 ° C., which is greater than the liquidus temperature of the brazing powder but which is lower than the temperature of the solidus of the René 77 blade and that of the powder. A from Astroloy. Thus, the self-soldering temperature will be higher than the liquidus temperature of the solder powder and lower than the solidus temperatures of the base powder and the receiving part (such as the aforementioned part 17), while the sintering the blank (such as preform 1 above) will have occurred at a temperature above the liquidus temperature of the brazing powder but lower than the temperature of the subsequent self-brazing treatment. It will thus be possible to obtain a piece of shape suitable for self-brazing, the relative density of which will be at least 95%. As taught in FR 2785559, it is recommended that, in practice, in the application intended for aeronautical turbomachines, and in particular for turbine components, in particular vanes and / or low pressure turbine distributors, the following be respected. , in combination or not, in order to optimize the quality of manufacture, taking into account the general state of the prior art: the brazing material will be an alloy containing from 2 to 12% by weight of Si, 3028436 the brazing material will be an alloy containing from 1 to 5% by weight, the brazing material will be an alloy selected from the following alloys: Ni-Si, Ni-B, Ni-Co-Si, Ni -Co-B, Ni-Co-Si-B, Ni-Cr-Al-Si, Ni-Co-Cr- AI-Si, Ni-Cr-B, Ni-Co-Cr-B, -weight percentage of brazing material in the powder containing the brazing material mixed with the base material will be between 5 and 40%, - the preform (1) contains at least 60% of base material.
    [0021] The method according to the invention makes it possible to repair various turbomachine parts. Indeed, the preform being built layer by layer by selective melting of powder, it can have a three-dimensional shape and, if necessary, a variable thickness.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. A method of repairing a turbomachine part (17), characterized in that it comprises the steps of: - producing, layer by layer, a preform (1) by selective melting of a powder (3) containing a material of identical or similar base to that of the piece (17), the preform comprising an assembly surface intended to be brazed on the part (17) to be repaired and containing for this purpose a brazing material mixed with the base material, said powder containing the mixture having, during heating up to heat-generating fusion, a main peak of transformation of the brazing material, greater amplitude of the heat flow, and secondary peaks of conversion of the brazing material, less heat flux amplitudes, - assembling the preform (1) to the part (17) of the turbomachine by soldering-diffusion, characterized in that the amplitude of the heat flow of said main peak of transformation of the material The brazing amount used to make the preform is at least twice the amplitudes of the respective heat fluxes of the secondary processing peaks of this brazing material.
    [0002]
    2. A repair method according to claim 1, wherein the chemical composition of the base material corresponds to a superalloy based on Ni, Co, Ti or Fe and in that that of the brazing material corresponds to a base alloy. Ni, and / or Co, and / or Fe in which the melting element is Si and / or B.
    [0003]
    3. A method of repair according to claim 1 or 2 wherein, in nominal composition by weight percent, the brazing material is a nickel-based alloy, cobalt: 18 to 22%, silicon: 4 to 5%, boron: 2, 7 to 3.15%, carbon: 0 to 0.06%, with further chromium between 9 and 19%.
    [0004]
    The repair method according to claim 1 or 2, wherein the brazing material is an alloy which contains from 2 to 12% Si by weight. 3028436 18
    [0005]
    The repair method according to claim 2, wherein the brazing material is an alloy which contains from 1 to 5% by weight B.
    [0006]
    6. A repair method according to any one of claims 2 to 4, characterized in that the brazing material is an alloy which is selected from the following alloys: Ni-Si, Ni-B, Ni-Si Si, Ni-Co-B, Ni-Co-Si-B, Ni-Cr-Al-Si, Ni-Co-Cr-Al-Si, Ni-Cr-B, Ni-Co-CrB.
    [0007]
    7. A method of repair according to any one of claims 1 to 6, wherein the preform (1) is made by selective melting of a powder of the base material and a solder powder, whose melting temperature is less than the melting temperature of the base material powder.
    [0008]
    A repair method according to any one of claims 1 to 7, wherein said magnitude of the heat flux of the main solder material conversion peak is equal to at least twice the respective amplitudes of the secondary peak heat fluxes. transforming this brazing material with a brazing material comprising a compound selected from Cr, Co, Mo, Fe.
    [0009]
    9. Turbomachine part prepared by performing the method according to one of claims 1 to 8.
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    公开号 | 公开日
    JP6595593B2|2019-10-23|
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    EP3218130B1|2019-05-29|
    RU2017116414A|2018-12-14|
    BR112017009975B1|2021-07-13|
    WO2016075423A1|2016-05-19|
    EP3218130A1|2017-09-20|
    JP2018505334A|2018-02-22|
    RU2703666C2|2019-10-21|
    CN107107194B|2019-08-23|
    CA2967168A1|2016-05-19|
    BR112017009975A2|2018-02-14|
    CN107107194A|2017-08-29|
    US20170320174A1|2017-11-09|
    RU2017116414A3|2019-05-21|
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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
    FR1461035|2014-11-14|
    FR1461035A|FR3028436B1|2014-11-14|2014-11-14|PROCESS FOR PRODUCING A TURBOMACHINE PIECE|FR1461035A| FR3028436B1|2014-11-14|2014-11-14|PROCESS FOR PRODUCING A TURBOMACHINE PIECE|
    RU2017116414A| RU2703666C2|2014-11-14|2015-11-16|Turbine engine component manufacturing method|
    CN201580071273.8A| CN107107194B|2014-11-14|2015-11-16|The manufacturing method of turbine engine components|
    JP2017525954A| JP6595593B2|2014-11-14|2015-11-16|Method for manufacturing turbine engine component|
    US15/526,485| US20170320174A1|2014-11-14|2015-11-16|Method for producing a turbine engine part|
    CA2967168A| CA2967168A1|2014-11-14|2015-11-16|Method for manufacturing a part for a turbomachine|
    PCT/FR2015/053091| WO2016075423A1|2014-11-14|2015-11-16|Method for manufacturing a part for a turbomachine|
    BR112017009975-6A| BR112017009975B1|2014-11-14|2015-11-16|METHOD OF REPAIRING A TURBO MACHINE PART|
    EP15807954.1A| EP3218130B1|2014-11-14|2015-11-16|Method for repairing a part for a turbomachine|
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