• 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 an abradable coating of variable density and such an abradable coating of variable density. According to the invention, the method comprises the following steps: providing a substrate (32) having a first portion whose surface is at a first level (A) and a second portion, whose surface is at a second level (B) different from the first level; depositing a precursor material on the first and second portions of the substrate (32); compressing the precursor material between the substrate and a bearing surface; and sintering the precursor material thus compressed to obtain an abradable coating (36) comprising a first portion (36a), facing the first portion of the substrate, having a first density and a second portion (36b), opposite the second portion of the substrate, having a second density distinct from the first.
    公开号:FR3044945A1
    申请号:FR1562318
    申请日:2015-12-14
    公开日:2017-06-16
    发明作者:Biez Philippe Charles Alain Le；Geoffroy Chevallier；Romain Epherre；Claude Estournes；Jean-Baptiste Mottin；Serge Georges Vladimir Selezneff
    申请人:TOULOUSE, University of；Centre National de la Recherche Scientifique CNRS；Universite Paul Sabatier Toulouse III；SNECMA SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present disclosure relates to a method of manufacturing an abradable coating of variable density and such an abradable coating of variable density.
    Such an abradable coating may in particular be used to equip a ring of rotating machine to ensure the tightness of the machine at the top of the rotating blades for example. Such an abradable coating is particularly suitable for equipping the turbine rings in the aeronautical field, and especially in aircraft turbojets.
    STATE OF THE PRIOR ART
    In many rotating machines, it is now known to provide the stator ring with abradable tracks opposite the top of the rotor blades. Such tracks are made using so-called "abradable" materials which, when they come into contact with the rotating blades, wear more easily than the latter. This ensures a minimum clearance between the rotor and the stator, improving the performance of the rotating machine, without the risk of damaging the blades in case of friction of the latter on the stator. On the contrary, such friction abrade the abradable track, which automatically adjusts the diameter of the stator ring to the nearest rotor. Thus, such abradable tracks are often put in place in the turbomachine compressors.
    On the other hand, their use is much rarer in the turbines of such turbomachines, and especially in high pressure turbines in which extreme physicochemical conditions prevail.
    In fact, the flue gases from the combustion chamber open into the high pressure turbine at very high temperature and pressure levels, which leads to the premature erosion of conventional abradable tracks. Therefore, in order to protect the turbine ring, it is often preferred to provide the latter with a coating of the thermal barrier type whose materials and high density, too important for the coating to be effectively abradable, can protect the environment. ring against erosion and corrosion.
    However, it is of course understood that in such a case the integrity of the blades is no longer ensured in case of contact with the stator, which requires to provide a greater clearance between the rotor and the stator and thus increases the leakage rate at the top of the blades and thus reduces the performance of the turbine.
    There is therefore a real need for a method of manufacturing an abradable coating and such an abradable coating which are devoid, at least in part, of the disadvantages inherent in the aforementioned known configurations.
    PRESENTATION OF THE INVENTION
    The present disclosure relates to a method of manufacturing an abradable coating of variable density, comprising the steps of: providing a substrate having a first portion having a surface at a first level and a second portion, the surface of which is at a second level different from the first level; depositing a precursor material on the first and second portions of the substrate; compressing the precursor material between the substrate and a bearing surface; and sintering the precursor material thus compressed to obtain an abradable coating comprising a first portion, facing the first portion of the substrate, having a first density and a second portion, opposite the second portion of the substrate, having a second density distinct from the first one.
    This method makes it possible to obtain a variable density coating. Indeed, thanks to the difference in level between the first portion and the second portion of the substrate, the reduction of the available volume during the compression step is all the more important that the substrate was close to the bearing surface in the initial state: assuming, for example, that the second level is deeper than the first level, the part of the precursor material situated above the first portion of the substrate is thus more compressed than the part of the precursor material situated in the above the second portion of the substrate. Greater pressure prevails in this part of the precursor material, which leads to a higher density of the material after sintering. Conversely, in the second part of the precursor material, the compression being less important, the reduction of the porosity rate in the material and therefore its densification are less important. In the present description, the term "porosity rate" the ratio between the volume of the interstitial spaces separating the grains of the material in question and the overall volume of said material. Therefore, thanks to this method, it is possible to locally adjust the final porosity rate and thus the density of the coating to meet different local requirements or constraints. For example, it is possible to provide the erosion-sensitive areas with a high density and to provide the areas of the pavement intended to come into contact with a moving body of lower density, reinforcing the easily abradable nature of these areas. In addition, it is also possible to have the first portion of coating, having a high density, so as to mask and thus protect the second part of the coating whose density is lower.
    In some embodiments, the second portion of the substrate is obtained by machining at least one groove in a blank of the substrate. Such a two-level substrate is thus easy to manufacture since it is sufficient to manufacture a regular blank and then to machine a groove in this blank only at the desired locations.
    In other embodiments, the first portion of the substrate is obtained by adding at least one wall to a blank of the substrate. This method is particularly suitable for repairing an existing part whose thickness is not sufficient to machine a groove.
    In some embodiments, the wall is manufactured directly on the blank of the substrate by sintering, in particular by a sintering method of the "Spark Plasma Sintering" (SPS) type.
    In other embodiments, the wall is manufactured independently and reported by welding or brazing. It can in particular be reported by a welding method of the type "Tungsten Inert Gas" (TIG).
    In some embodiments, the bearing surface is continuous. Here it is meant that the bearing surface has no discontinuity such as a step or other abrupt change of level.
    In some embodiments, the bearing surface is rectilinear at least in a direction transverse to the first and second portions of the substrate. There is thus a cross-sectional plane through both the first and the second portion of the substrate in which the bearing surface is rectilinear.
    In some embodiments, the bearing surface takes the form of a cylinder sector, preferably a revolution cylinder sector.
    In some embodiments, the bearing surface is a surface of a shaped mold.
    In some embodiments, the first portion of the abradable coating has a final porosity of less than 15%, preferably less than 5%. The first part of the coating thus has a sufficiently high density to resist erosion.
    In some embodiments, the second portion of the abradable coating has a final porosity of greater than 20%, preferably greater than 30%. The second part of the coating thus has a sufficiently low density to exhibit an easily abradable behavior.
    In some embodiments, the first portion of the abradable coating undergoes densification of at least 150%, preferably at least 250%, during the compression and sintering step. In the present description, the term "densification" means the increase in the density of the material constituting the abradable coating between the initial state at the time of the precursor material deposition step and the final state obtained after the compression steps. and sintering. In other words, it is the difference between the final density and the initial density reported on the initial density.
    In some embodiments, the second portion of the abradable coating is densified by at most 150%, preferably at most 100% during the compression and sintering step.
    In some embodiments, the method further comprises, before the step of depositing the precursor material on the first and second portions of the substrate, a sintering step of a bead layer, whose final porosity rate is lower than at 15% and preferably less than 5%, on the second portion of the substrate. This heel layer makes it possible to maintain a highly densified layer beneath the second, low-density portion of the abradable coating. Thus, the substrate remains protected in case of radial displacement of the body flowing opposite the upper coating to the maximum displacement envisaged. This protects in particular the substrate in case of significant imbalance of the moving body for example.
    In some embodiments, the method further comprises, after the step of sintering the precursor material, a sintering step of a surface layer, whose final porosity is less than 15% and preferably less than 15%. 5%, on at least a portion of the abradable coating, preferably on its central portion. This layer provides the coating with a low surface roughness. It is preferably formed over the entire surface of the abradable coating.
    In some embodiments, the thickness of the surface layer is between 0.05 and 0.10 mm.
    In some embodiments, the precursor material is a metal or ceramic powder.
    In some embodiments, the substrate is a ring sector. In particular, it may be a turbine ring sector which will be mounted on the stator of the turbine.
    In some embodiments, the first portion of the substrate extends along the second portion of the substrate.
    In some embodiments, the substrate has a longitudinal channel flanked by two longitudinal shoulders, the shoulders forming part of the first portion of the substrate and the bottom of the channel forming part of the second portion of the substrate. Thus, at the end of the process, a low density band is obtained, which is therefore easily abradable, in the zone likely to come into contact with the blades of a rotor for example and two strips of denser coating on either side of the rotor. the abradable band to protect the latter from erosion caused by the axial flow of an air stream for example.
    The present disclosure also relates to an abradable track of variable density, comprising a first portion comprising a sintered material having a first density, and a second portion, contiguous to and flush with the first portion, comprising a sintered material having a second density distinct from the first density.
    As explained above, this makes it possible to protect the most erosion-sensitive areas while providing an easily abradable layer in the areas intended to come into contact with the moving body.
    In some embodiments, the thickness of the first portion of the abradable track is less than the thickness of the second portion.
    In some embodiments, the abradable track is obtained using a manufacturing method according to any one of the preceding embodiments.
    The present disclosure also relates to a turbine or compressor ring comprising an abradable track according to any one of the preceding embodiments.
    The present disclosure also relates to a turbomachine comprising an abradable track or a turbine ring or compressor according to one of the preceding embodiments.
    The above-mentioned characteristics and advantages, as well as others, will appear on reading the following detailed description of embodiments of the device and the method proposed. This detailed description refers to the accompanying drawings.
    BRIEF DESCRIPTION OF THE DRAWINGS
    The accompanying drawings are schematic and are intended primarily to illustrate the principles of the invention.
    In these drawings, from one figure (FIG) to the other, identical elements (or element parts) are identified by the same reference signs. In addition, elements (or parts of elements) belonging to different exemplary embodiments but having an analogous function are indicated in the figures by incremented numerical references of 100, 200, etc.
    FIG 1 is a sectional plane of a turbomachine according to the invention.
    FIG 2 is a partial perspective view of an example of a stator ring according to the invention.
    FIGS. 3A to 3E illustrate several successive steps of an exemplary method according to the invention.
    FIG 4 is a sectional view of a second example of abradable track.
    FIG 5 is a sectional view of a third example of abradable track.
    DETAILED DESCRIPTION OF EXAMPLE (S) OF REALIZATION
    In order to make the invention more concrete, examples of methods and abradable tracks are described in detail below with reference to the accompanying drawings. It is recalled that the invention is not limited to these examples.
    FIG 1 shows, in section along a vertical plane passing through its main axis A, a turbofan engine 1 according to the invention. It comprises, from upstream to downstream according to the flow of the air flow, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, and a low pressure turbine 7.
    The high pressure turbine 6 comprises a plurality of vanes 6a rotating with the rotor and rectifiers 6b mounted on the stator. The stator of the turbine 6 comprises a plurality of stator rings 10 arranged vis-a-vis the blades 6a of the turbine 6. As can be seen in FIG. 2, each stator ring 10 is divided into several sectors. 11 each provided with an abradable track 20 on which rub the blades 6a in case of radial excursion of the rotor.
    An exemplary embodiment of such an abradable track 20 will be described with reference to FIGS. 3A to 3E. In FIG. 3A, a blank 30 is first provided. In this case, it is a ring sector obtained by a conventional method. Its surface 30s is regular, rectilinear in the axial sectional plane of FIG 3A, and in a circular arc in a radial plane of section.
    As shown in FIG. 3B, a groove 31 is then machined longitudinally, that is to say circumferentially, on the surface of the blank 30 so as to form a channel: a substrate 32 having two shoulders is thus obtained. flanking the groove 31 upstream and downstream respectively.
    The two shoulders together form a first portion 33 of substrate whose surface 33s extends to a first level A corresponding to the initial level of the blank 30. The portion of the substrate 32 located at the bottom of the groove 31 forms a second portion 34 of substrate whose surface 34s extends to a second lower level B, that is to say deeper, than the first level A and corresponding to the bottom of the groove 31. In this example, the groove 31 is 12 mm deep, that is the difference between levels A and B is 12 mm.
    As shown in FIG. 3C, the substrate 32 thus formed is then placed in the cavity of a mold of shape 40 whose axial dimensions correspond to that of the substrate 32.
    A precursor material 35, in this case a metal powder, is then deposited uniformly over the entire substrate 32: the powder 35 thus fills the entire channel 31 and forms a continuous layer of constant thickness over the level A of the shoulders 33 of the substrate 32. The powder 35 is thus added until reaching a third level C: in this example, this level C is provided 20 mm above the level A of the shoulders 33 of the substrate. In the present example, the powder is a nickel powder of particle size centered around 100 μm; its initial porosity is about 70%.
    Naturally, this initial porosity rate may vary according to the type of powder used and the desired final porosity levels: for example, for nickel powders having a particle size of about 4 to 7 μm, this initial porosity rate may be as follows: about 23 to 33%. Preferentially, powders with a high initial porosity level will be used for the low density abradable zone. In addition, it is possible to obtain a higher initial porosity rate by adding to these powders a blowing agent which will be removed later during the process, during a pyrolysis step for example.
    On the other hand, finer powders with a lower initial porosity rate may be used for higher density areas such as low walls, the heel layer or the low roughness surface layer which will be described below.
    Thus, the powder 35 forms a layer 20 mm thick at the shoulders 33 and 32 mm thick at the channel 31.
    As shown in FIG 3D, the mold 40 is then closed. A bearing face 42 of its cover 41, rectilinear in the axial plane of FIG 3D and in a circular arc in a radial plane, then applies against the surface 35s of the powder layer 35.
    A constraint is then exerted on the cover 41 of the mold 40 to press the powder layer 35 and compress the latter between the substrate 32 and the bearing face 42 of the cover 41 of the mold 40. The powder layer 35 is thus compressed to a fourth level D extending in this case 4.2 mm above the shoulders 33 of the substrate is 4.2 mm above the level A.
    During this compression step, the powder particles 35 are packed against each other and thus fill some voids initially present between the particles, the air thus expelled being discharged from the mold 40. The porosity rate of the powder therefore decreases during this compression step and the density of the powder increases.
    However, this densification depends on the position of the volume of powder considered within the powder layer 35. In fact, if we neglect the phenomena of lateral migration of the powder, the powder volumes 35a located between the shoulders 33 and the bearing surface 42 undergoes a decrease in available volume and therefore a greater compression than the volume of powder 35b located in and above the channel 31.
    Indeed, above the shoulders 33, the initially available thickness corresponds to the difference in level between the levels A and C is 20 mm in this example while the thickness available after compression corresponds to the difference in levels between the levels. A and D is 4.2 mm: the volume of powder 35a thus undergoes a reduction of 79% in volume.
    On the other hand, above the second portion 34 of the substrate 32, the initially available thickness corresponds to the difference in level between the levels B and C, ie 32 mm in this example while the thickness available after compression corresponds to the difference levels between levels B and D is 16.2 mm: the volume of powder 35a and undergoes a reduction of 49% volume. Therefore, insofar as the mass of powder remains constant in each volume 35a and 35b of powder, it is possible to calculate the densification of the material using the following formula in which e is the initial thickness of the material and ef is its final thickness:
    It follows that the first volume of powder 35a undergoes densification, that is to say an increase in its density, of 376% while the second volume of 35b powder undergoes a densification of 98%.
    Once such a compressed state is obtained, the powder layer 35 thus differentially compressed is sintered using a conventional method. At the end of this sintering step, the abradable track 20 of FIG. 3E is obtained in which the substrate 32 is covered with a coating 36 comprising a first portion 36a surmounting the shoulders 33, having a thickness of 4.2 mm and a thickness of final porosity rate of 14.7%, and a second portion 36b overlying the channel 31 having a thickness of 16.2 mm and a final porosity rate of 35.7%. In this respect, the final porosity rate Pf can be calculated in general as a function of the initial porosity rate Ρ, and the compression ratio Te, that is to say of the volume reduction, of the portion of material considered: Pf = Pt (l - Te)
    Naturally, the depth of the groove 31, the initial powder thickness 35 and the compression amplitude can be freely adjusted to achieve the desired densities and coating thicknesses.
    In addition, in this example, the channel 31 of the substrate extending at a level B less than that of the shoulders 33 is a groove obtained by machining the blank 30. However, in a variant of the first example, a similar channel could be obtained by bringing walls to the blank 30 forming shoulders 33 flanking the channel 31: in such a case, the initial level of the blank defines the level B of the channel bottom 31 while the top of the walls defines the level AT.
    In a second example, illustrated in FIG. 4, the method comprises an additional step taking place just after the supply of a substrate 132 at two levels A and B. A heel layer 137 of high density, having for example a final porosity of 0 to 15% is set up at the bottom of the channel 131 by sintering a powder. The remainder of the process is unchanged with respect to the first example, the layer of precursor material being deposited above the shoulders 133 and this heel layer 137. At the end of the process, the abradable track 120 of FIG. wherein the second portion of the lower density coating 136b covers the heel layer 137, the latter protecting the substrate in case of radial displacement of the body flowing opposite the upper coating to the maximum displacement envisaged, in the event of significant unbalance of the moving body, for example .
    In a third example, compatible with the first and second examples and illustrated in FIG. 5, the method comprises an additional step taking place just after the compression and sintering steps of the powder, the beginning of the process being unchanged compared to the first one. or the second example. A surface layer 238 of high density, having for example a final porosity of 0 to 15%, and of small thickness, for example between 0.05 and 0.10 mm, is set up by sintering a powder in surface of the variable density coating 236. At the end of the process, the abradable track 220 of FIG. 5 is thus obtained in which the surface layer 238 has a surface roughness smaller than the second portion of the coating 236b at a lower density and therefore a gain on the aerodynamic friction, covers the entire coating 236.
    The modes or examples of embodiment described in the present description are given for illustrative and not limiting, a person skilled in the art can easily, in view of this presentation, modify these modes or embodiments, or consider others, while remaining within the scope of the invention.
    In addition, the various features of these modes or embodiments can be used alone or be combined with each other. When combined, these features may be as described above or differently, the invention not being limited to the specific combinations described herein. In particular, unless otherwise specified, a characteristic described in connection with a mode or example of embodiment may be applied in a similar manner to another embodiment or embodiment.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    A method of manufacturing an abradable variable density coating, comprising the steps of: providing a substrate (32) having a first portion (33) whose surface (33s) is at a first level (A) and a second portion (34) whose surface (34s) is at a second level (B) different from the first level; depositing a precursor material (35) on the first and second portions (33, 34) of the substrate (32); compressing the precursor material (35) between the substrate (32) and a bearing surface (42); and sintering the precursor material (35) thus compressed to obtain an abradable coating (36) comprising a first portion (36a), facing the first portion (33) of the substrate (32), having a first density and a second portion ( 36b), facing the second portion (34) of the substrate (32), having a second density distinct from the first.
    [2" id="c-fr-0002]
    2. The method of claim 1, wherein the second portion (34) of the substrate (32) is obtained by machining at least one groove (31) in a blank (30) of the substrate.
    [3" id="c-fr-0003]
    3. The method of claim 1 or 2, wherein the bearing surface (42) is continuous and rectilinear at least in a direction transverse to the first and second portions (33, 34) of the substrate (32).
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 3, wherein the first portion (36a) of the abradable coating (36) has a final porosity of less than 15%, preferably less than 5%.
    [5" id="c-fr-0005]
    5. Method according to any one of claims 1 to 4, wherein the second portion (36b) of the abradable coating (36) has a final porosity of greater than 20%, preferably greater than 30%.
    [6" id="c-fr-0006]
    6. Method according to any one of claims 1 to 5, further comprising, before the step of depositing the precursor material on the first and second portions of the substrate, a sintering step of a bead layer (137). , whose final porosity is less than 15%, on the second portion of the substrate (132).
    [7" id="c-fr-0007]
    7. Process according to any one of claims 1 to 6, further comprising, after the step of sintering the precursor material, a sintering step of a surface layer (238), whose final porosity rate is less than 15% on at least a portion of the abradable coating (236).
    [8" id="c-fr-0008]
    The method of any one of claims 1 to 7, wherein the substrate is a ring sector (11).
    [9" id="c-fr-0009]
    9. A method according to any one of claims 1 to 8, wherein the substrate (32) has a longitudinal channel (31) flanked by two longitudinal shoulders (33), the shoulders (33) forming part of the first portion of the substrate. and the bottom of the channel (31) forming part of the second portion of the substrate.
    [10" id="c-fr-0010]
    A variable density abradable track, comprising a first portion (36a) having a sintered material having a first density, and a second portion (36b) contiguous with and flush with the first portion (36a), having a sintered material having a second density distinct from the first density.
    [11" id="c-fr-0011]
    11. A turbine or compressor ring comprising an abradable track (20) according to claim 10.
    [12" id="c-fr-0012]
    12. A turbomachine comprising an abradable track (20) according to claim 10 or a turbine ring (10) or compressor according to claim 11.
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2014053754A1|2012-10-05|2014-04-10|Snecma|Method for incorporating abradable material into a housing by isostatic pressing|
    FR2996475A1|2012-10-05|2014-04-11|Snecma|Manufacturing e.g. rotor of turboshaft engine, comprises filling housing with abradable material, heating material, maintaining material at specific temperature until sintering occurs between particles of material, and lowering temperature|
    US20140263579A1|2013-03-14|2014-09-18|Anand A. Kulkarni|Method and apparatus for fabrication and repair of thermal barriers|JP2019519667A|2016-04-13|2019-07-11|フォルシュングスツェントルム・ユーリッヒ・ゲゼルシャフト・ミット・ベシュレンクテル・ハフツング|Method of manufacturing metal or ceramic component and component|JPS4923985B1|1970-11-27|1974-06-19|
    SU977111A1|1981-06-25|1982-11-30|Предприятие П/Я А-1450|Method of producing complex shape articles from metallic powder|
    SU997111A1|1981-08-06|1983-02-15|Предприятие П/Я В-8769|Method of winding wire onto polyhedral framework|
    US4914794A|1986-08-07|1990-04-10|Allied-Signal Inc.|Method of making an abradable strain-tolerant ceramic coated turbine shroud|
    JPS6392842A|1986-10-07|1988-04-23|Toyota Motor Corp|Sintered friction material|
    US5236151A|1991-12-23|1993-08-17|General Electric Company|Thermal barrier structure|
    JP4166977B2|2001-12-17|2008-10-15|三菱重工業株式会社|High temperature corrosion resistant alloy material, thermal barrier coating material, turbine member, and gas turbine|
    RU2320776C2|2002-10-09|2008-03-27|Исикавадзима-Харима Хэви Индастриз Ко.,Лтд.|Rotating member and method for depositing of coating onto the same|
    US8079806B2|2007-11-28|2011-12-20|United Technologies Corporation|Segmented ceramic layer for member of gas turbine engine|
    JP2009256759A|2008-04-21|2009-11-05|Fujifilm Corp|Structure of thermal barrier coating, and method for manufacturing thermal barrier coating|
    FR2930590B1|2008-04-23|2013-05-31|Snecma|TURBOMACHINE HOUSING HAVING A DEVICE WHICH PREVENTS INSTABILITY IN CONTACT BETWEEN THE CARTER AND THE ROTOR|
    EP2317079B1|2009-10-30|2020-05-20|Ansaldo Energia Switzerland AG|Abradable coating system|
    US20120107103A1|2010-09-28|2012-05-03|Yoshitaka Kojima|Gas turbine shroud with ceramic abradable layer|
    FR2972379B1|2011-03-07|2014-01-17|Snecma|METHOD FOR LOCALLY RECHARGING DAMAGED THERMOMECHANICAL PIECE AND PART THEREFORE PRODUCED, IN PARTICULAR TURBINE PIECE|
    US8999226B2|2011-08-30|2015-04-07|Siemens Energy, Inc.|Method of forming a thermal barrier coating system with engineered surface roughness|
    US9034479B2|2011-10-13|2015-05-19|General Electric Company|Thermal barrier coating systems and processes therefor|
    US9186866B2|2012-01-10|2015-11-17|Siemens Aktiengesellschaft|Powder-based material system with stable porosity|
    US10215033B2|2012-04-18|2019-02-26|General Electric Company|Stator seal for turbine rub avoidance|
    US9151175B2|2014-02-25|2015-10-06|Siemens Aktiengesellschaft|Turbine abradable layer with progressive wear zone multi level ridge arrays|
    US10309243B2|2014-05-23|2019-06-04|United Technologies Corporation|Grooved blade outer air seals|
    US20150354392A1|2014-06-10|2015-12-10|General Electric Company|Abradable coatings|
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    RU2761813C1|2021-03-11|2021-12-13|Федеральное государственное бюджетное учреждение науки Институт гидродинамики им. М.А. Лаврентьева Сибирского отделения Российской академии наук |Additive method for obtaining dimension products from conductive ceramics by spark plasma sintering|
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1562318A|FR3044945B1|2015-12-14|2015-12-14|ABRADABLE COATING WITH VARIABLE DENSITY|
    FR1562318|2015-12-14|FR1562318A| FR3044945B1|2015-12-14|2015-12-14|ABRADABLE COATING WITH VARIABLE DENSITY|
    EP16825838.2A| EP3389904A1|2015-12-14|2016-12-13|Abradable coating having variable densities|
    RU2018125846A| RU2728166C2|2015-12-14|2016-12-13|Abradable coating with variable density|
    US16/062,224| US10870152B2|2015-12-14|2016-12-13|Abradable coating having variable densities|
    JP2018549628A| JP2019505688A|2015-12-14|2016-12-13|Abrasive coatings with varying density|
    PCT/FR2016/053358| WO2017103420A1|2015-12-14|2016-12-13|Abradable coating having variable densities|
    BR112018011889-3A| BR112018011889A2|2015-12-14|2016-12-13|method for manufacturing a variable density abrasive coating, variable density abrasive rail, turbine or compressor ring, and turbine engine.|
    CN201680073267.0A| CN108367360B|2015-12-14|2016-12-13|Wear resistant coating with variable density|
    CA3008316A| CA3008316A1|2015-12-14|2016-12-13|Abradable coating having variable densities|
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