• 专利附录
  • 专利说明
  • 权利要求
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    • 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) comprising a first portion (33) and a second portion (34); depositing a first precursor material on the first portion (33) of the substrate (32); compressing the first precursor material between the substrate (32) and a first bearing surface; sintering the first precursor material thus compressed to obtain a first abradable coating portion (36a), facing the first portion (33) of the substrate (32), having a first density; depositing a second precursor material on the second portion (34) of the substrate (32); compressing the second precursor material between the substrate (32) and a second bearing surface; sintering the second precursor material thus compressed to obtain a second abradable coating portion (36b), facing the second portion (33) of the substrate (32), having a second density distinct from the first.
    公开号:FR3044946A1
    申请号:FR1562324
    申请日:2015-12-14
    公开日:2017-06-16
    发明作者:Biez Philippe Charles Alain Le
    申请人: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 a variable density abradable coating, comprising the steps of: providing a substrate having a first portion and a second portion; depositing a first precursor material on the first portion of the substrate; compressing the first precursor material between the substrate and a first bearing surface; sintering the first precursor material thus compressed to obtain a first abradable coating portion, facing the first portion of the substrate, having a first density; depositing a second precursor material on the second portion of the substrate; compressing the second precursor material between the substrate and a second bearing surface; sintering the second precursor material thus compressed to obtain a second abradable coating portion, opposite the second portion of the substrate, having a second density distinct from the first.
    This method makes it possible to obtain a variable density coating. Indeed, several parameters can be set differently for each portion of the substrate so as to obtain abradable coating portions having different properties. First, it is possible to choose different precursor materials. In particular, the size of the particles constituting the precursor material or the initial porosity rate of the precursor material make it possible to influence the final porosity rate of the abradable coating and therefore its density.
    It is also possible to deposit a greater or lesser quantity of precursor material before the compression step, that is to say to deposit a layer of precursor material of greater or lesser thickness. This amount of material will thus influence the final density of the abradable coating.
    It is also possible to compress the precursor materials to a greater or lesser extent during the compression steps in order to compact them more or less before sintering: their porosity levels are thus reduced more or less, which influences the rate of final porosity and thus the final density of each part of the abradable coating.
    It is also possible to play on the temperature and / or the duration of the sintering steps in order to influence the micro-structure of the abradable coating and in particular on its final porosity rate and on its density.
    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 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 deposition, compression and sintering steps of the second precursor material take place after the deposition, compression and sintering steps of the first precursor material. By thus separating these steps, it is possible to individualize the deposition, compression and sintering parameters for each substrate portion and thus easily obtain different properties for each part of the abradable coating.
    In some embodiments, the compression and sintering steps of the first precursor material are performed within a first mold; the compression and sintering steps of the second precursor material are carried out within a second mold; and the second mold is distinct from the first mold.
    In some embodiments, the first and second molds are one and the same mold.
    In certain embodiments, the first mold comprises the first bearing surface and at least one protective wall provided so as to flank the first precursor material at the interface between the first and the second portion of the substrate during compression and sintering steps of the first precursor material. This protective wall makes it possible to prevent pieces of the first precursor material from moving and attaching to the second portion of the substrate.
    In some embodiments, the second mold comprises a movable portion extending opposite the second portion of the substrate and including the second bearing surface, and a stationary portion extending in opposite relation of, preferably against, the first portion of the substrate. This immobile portion protects the first portion of abradable coating which is completed. Thus, preferably, only the portion of the mold that faces the second portion of the substrate is movable.
    In certain embodiments, the deposition steps of the first and second precursor materials take place simultaneously or successively, the compression steps of the first and second precursor materials take place simultaneously, and the sintering steps of the first and second precursor materials take place simultaneously. . The total duration of the process is therefore reduced. It is also possible to use only one mold. In such a case, the difference in final density can be obtained, for example, thanks to different precursor materials, different thicknesses of layers of precursor material, or differential compression. Such differential compression can be obtained, for example, using a mold having bearing surfaces extending at different levels, or using a mold having a plurality of independent moving parts.
    In some embodiments, the first portion of the substrate is at a first level, and the second portion of the substrate is at a second level different from the first level. Thanks to this difference in level between the first portion and the second portion of the substrate, the reduction in the volume available 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 located above the first portion of the substrate is thus more compressed than the part of the precursor material situated above the first level; 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 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 some 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 some 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 first and second bearing surfaces are continuous, one in line with the other. Here it is meant that the bearing surfaces do not include any discontinuity such as a step or other abrupt change of level within them or at their interface.
    In some embodiments, the bearing surfaces are rectilinear at least in a direction transverse to the first and second portions of the substrate. There is thus a cutting plane passing through both the first and second portions of the substrate in which the bearing surfaces are rectilinear.
    In some embodiments, at least one bearing surface, preferably each bearing surface, takes the form of a cylinder sector, preferably a revolution cylinder sector.
    In some embodiments, at least one bearing surface, preferably each 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 low porosity rate, and therefore 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 high porosity rate, and therefore 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 80%, preferably at least 100%, during the compression and sintering step. In the present description, "densification" is understood to mean increasing the density of the material composing the abradable coating between the initial state at the time of the step of depositing the precursor material 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 undergoes a densification of at most 70%, preferably at most 50%, and preferably at most 10% during the compression and sintering step .
    In certain embodiments, the method further comprises, before the step of depositing the precursor material on one of the portions of the substrate, preferably on the second portion of the substrate, a step of forming by sintering a heel layer , the porosity of which is less than 15% and preferably less than 5%, on the portion of the substrate considered. 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, this step of sintering a bead layer is performed in the second mold or in a mold identical to the second mold.
    In certain embodiments, the method further comprises, after the sintering step of one of the precursor materials, a sintering step of a surface layer, whose final porosity rate is less than 15%. and preferably less than 5%, on at least one of the parts of the abradable coating, preferentially on its second part. This layer provides the coating with a low surface roughness. It can also be formed on the entire surface of the abradable coating.
    In some embodiments, this sintering step of a surface layer is performed in the second mold or in a mold identical to the second mold.
    In some embodiments, the thickness of the surface layer is between 0.05 and 0.10 mm.
    In some embodiments, at least one precursor material, preferably each precursor material, is a metal or ceramic powder.
    In some embodiments, the first and second precursor materials are different. In other embodiments, they are identical.
    In some embodiments, the first precursor material is a powder whose particle size is less than 20 μm.
    In certain embodiments, the second precursor material is a powder whose particle size is greater than 45 μm.
    In certain embodiments, the second precursor material is a powder whose particle size is less than 100 μm.
    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 adjacent 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 materials of the first and second portions of the abradable track are different. In other embodiments, they are identical.
    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 3G illustrate several successive steps of an exemplary method according to the invention.
    FIGS. 4A to 4E illustrate several successive steps of an exemplary method according to the invention.
    FIGS. 5A to 5E illustrate several successive steps of an exemplary method according to the invention.
    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 3G. 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. In the present disclosure this groove 31 has a depth of 5 mm. However, the realization of such a groove is optional: other embodiments of the method can indeed be applied to a regular substrate having no difference in level.
    The two shoulders together form a first portion 33 of substrate; the portion of the substrate 32 located at the bottom of the groove 31 in turn forms a second portion 34 of the substrate.
    As shown in FIG. 3C, the substrate 32 thus formed is then placed in the cavity 42 of a first shape mold 40. This first shape mold 40 comprises a main portion 41, comprising the cavity 42 whose axial dimensions corresponding to that of the substrate 32, and a lid portion 43 (visible in FIG 3D).
    A first precursor material 35a, in this case a metal powder, is then deposited on the shoulders 33, that is to say the first portion of the substrate 32, while leaving the groove 31, and therefore the second portion 34 of the substrate, powder free. On this occasion, a removable masking block can be arranged in the groove 31 in order to prevent the powder of the first precursor material 35a from being deposited on the second portion 34.
    The powder 35a then forms a continuous layer of constant thickness above the shoulders 33 of the substrate 32. In the present example, the powder is an alumina powder with a particle size centered around 5 μm; this layer has a thickness of 10 mm. and an initial porosity of about 30%.
    As shown in FIG 3D, the mold 40 is then closed by returning its lid portion 43 to its main portion 41. This lid portion 43 includes a central protection block 44 and two bearing surfaces 45 extending on both sides of the protection block 44.
    These bearing surfaces 45, rectilinear in the axial plane of FIG 3D and arc in a radial plane, then apply against the upper surface of each powder layer of the first precursor material 35a. The protection block 44 is inserted between the layers of powder 35a and penetrates into the groove 31 so as to block it: the powder layers of the first precursor material 35a are thus enclosed in the space defined by the first portion. 33 of the substrate, the walls of the cavity 42 of the main portion 41 of the mold 40, the bearing surfaces 45 of the cover 43 of the mold 40 and the side walls 44a of the protective block 44 of the cover 41 of the mold 40.
    A constraint is then exerted on the lid 43 of the mold 40 to press on the layers of powder 35a and compress the latter between the substrate 32 and the bearing surfaces 45 of the lid 43 of the mold 40. The layer of powder 35a is thus compressed until its thickness is reduced to 2 mm. In this example, the front surface 44b of the protective block 44 of the cover 43 of the mold 40 is then in abutment against the second portion 34 of the substrate.
    During this compression step, the powder particles of the first precursor material 35a 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. Porosity of the powder therefore decreases during this compression step and the density of the powder increases.
    Once such a compressed state has been obtained, the powder layer 35a thus compressed is sintered using a conventional method so as to obtain a first portion 36a of coating 36 surmounting the first portion 33 of the substrate 32 and having a thickness of 2 mm and a porosity rate of 6%.
    The substrate 32 is then transferred into a second shaped mold 50 comprising a main portion 51, having a cavity 52 whose axial dimensions corresponding to that of the substrate 32, and a lid portion 53 (visible in FIG 3F) comprising two parts fixed 54, that is to say immobile, and a movable portion 55.
    As shown in FIG. 3E, a second precursor material 35b, in this case a metal powder, is then deposited in the groove 31, that is to say on the second portion 34 of the substrate 32, while leaving the first coating portion 36a is powder free. On this occasion, removable masking blocks may be placed on these parts 36a of the coating in order to prevent the powder of the second precursor material 35b from settling thereon.
    The powder 35b then forms a continuous layer of constant thickness above the second portion 34 of the substrate 32. In the present example, the powder is a powder of alumina of particle size centered around 100 μm; this layer has a thickness of 12 mm and an initial porosity of about 70%. On this occasion, it is noted that it is possible to obtain a higher initial porosity rate by adding to this powder a blowing agent which will be removed later during the process, during a pyrolysis step for example.
    As shown in FIG. 3F, the mold 50 is then closed by returning its lid portion 53 to its main portion 51. The fixed parts 54 of the lid are provided to cover and apply against the first portion 36a of the abradable coating obtained previously. The movable portion 55 of the cover has for its part a front bearing surface 55a, rectilinear in the axial plane of FIG 3F and in an arc in a radial plane, provided opposite the second portion 34 of the substrate 32 so that it then applies against the upper surface of the powder layer of the second precursor material 35b. This powder layer of the second precursor material 35b is enclosed in the space defined by the groove 31 of the substrate, the flanks of the first coating portion 36a, the lateral surfaces of the fixed portions 54 of the cover 53 of the mold 50 and the surface of the support 55a of the movable portion 55 of the cover 53 of the mold 50.
    A constraint is then exerted on the movable portion 55 of the cover 53 of the mold 50 to press the powder layer 35b and compress the latter between the substrate 32 and the bearing surface 55a of the cover 53 of the mold 50. The powder layer 35b is thus compressed until its thickness is reduced to 7 mm. In this example, the surface level of the powder layer 35b is then flush with the surface level of the first coating portion 36a.
    During this compression step, the powder particles of the second precursor material 35b are packed against each other and thus fill some voids initially present between the particles, the air thus expelled being discharged from the mold 50. The porosity of the powder therefore decreases during this compression step and the density of the powder increases, but however less than in the case of the first precursor material 35a.
    Once such a compressed state has been obtained, the powder layer 35b thus compressed is sintered using a conventional method. At the end of this sintering step, the abradable track 20 of FIG 3G 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 2 mm and a thickness of porosity rate of 6%, and a second portion 36b surmounting the second portion of substrate 34 having a thickness of 7 mm and a porosity of 40.6%.
    Naturally, the depth of the groove 31 (which may be zero), the materials 35a, 35b used, the initial thickness of the powder layers 35a, 35b, and the amplitude of the compressions made can be freely adjusted to reach the densities and the desired coating thicknesses.
    In a second example, illustrated in FIGS. 4A to 4E, the method comprises additional steps, taking place after the completion of the first coating portion 136a and before making the second coating portion 136b, to form a heel layer 137 of high density, having for example a porosity of the order of 6%, on the second portion 134 of the substrate and under the second coating portion 136b.
    The process begins in the same manner as the previous embodiment with the realization of a first portion of coating 136a high density. These steps will not be described again. At the end of these steps, as shown in FIG 4A, the substrate 132 is transferred into a mold 150 similar to the second mold 50 of the first embodiment.
    A third precursor material 135c is then deposited in the groove 131, that is to say on the second portion 34 of the substrate 32, so as to form a continuous layer of constant thickness above the second portion 34 of the In the present example, the third precursor material 135c is identical to the first precursor material used to make the first coating portion 136a; in addition, this layer has a thickness of 10 mm and an initial porosity of about 30%.
    As shown in FIG 4B, the mold 150 is then closed and a stress is then exerted on the movable portion 155 of the cover 153 of the mold 50 to compress the powder layer 135c between the substrate 32 and the bearing surface of the cover 153 of the mold 150 until its thickness is reduced to 2 mm. Once such a compressed state has been obtained, the powder layer 135c thus compressed is sintered using a conventional method. At the end of this sintering step, a heel layer 137 is then obtained covering the second portion 134 of the substrate 132, having a thickness of 2 mm and a porosity of 6%.
    As shown in FIGS. 4C and 4D, the rest of the process is then analogous to the first embodiment except that the second precursor material 135b is deposited on the heel layer 137. At the end of the process, we obtain thus the abradable track 120 of FIG 4E in which the second portion of the coating 136b of lower density covers the heel layer 137, the latter protecting the substrate 132 in case of radial displacement of the body flowing opposite the upper coating to the maximum displacement envisaged, in case of significant imbalance of the moving body for example.
    In a third example, compatible with the first and second examples and illustrated in FIGS. 5A to 5E, the method comprises additional steps, taking place immediately after the realization of the second coating portion 236b, to form a surface layer 238 of high density, having for example a porosity of 15%, on the second coating portion 236b and / or the first coating portion 236a.
    The process begins in the same manner as the first embodiment with the realization of a first high density coating portion 236a and a second low density coating portion 236b. These steps will not be described again.
    However, it should be noted in FIGS. 5A and 5B that the thicknesses of the second precursor material layer 235b in its initial state and its compressed state are possibly adapted, that is to say reduced, so as to leave on the surface of the second coating portion 236b has sufficient space to receive the surface layer 238 when it is desired for the latter to be flush with the first coating portion 236a. At the end of these steps, as shown in FIG. 5C, a fourth precursor material 235d is deposited on the second coating portion 236b thus produced, so as to form a continuous layer of constant thickness. In the present example, the fourth precursor material 235d is identical to the second precursor material used to make the second coating portion 236b; in addition, this layer has a thickness of 0.6 mm and an initial porosity of about 70%.
    As shown in FIG. 5D, the mold 250 is then closed again and a stress is then exerted on the movable portion 255 of the mold cover 250 to compress the powder layer 235d between the second coating portion 236b and the surface of the mold. supporting the lid 153 of the mold 150 until its thickness is reduced to 0.10 mm. Once such a compressed state has been obtained, the powder layer 235d thus compressed is sintered using a conventional method. At the end of the process, the abradable track 220 of FIG. 5E is obtained in which the second part of the lower density coating 236b is covered by a surface layer 238, flush with the first portion of the coating 236b, having a thickness of 0.10 mm and a porosity of 11.9%. This surface layer 238 has a lower surface roughness than the second portion of the coating 236b and therefore provides a gain on the aerodynamic friction.
    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 (13)
    [1" id="c-fr-0001]
    A method of manufacturing a variable density abradable coating, comprising the steps of: providing a substrate (32) having a first portion (33) and a second portion (34); depositing a first precursor material (35a) on the first portion (33) of the substrate (32); compressing the first precursor material (35a) between the substrate (32) and a first bearing surface (45); sintering the first precursor material (35a) thus compressed to obtain a first abradable coating portion (36a), opposite the first portion (33) of the substrate (32), having a first density; depositing a second precursor material (35b) on the second portion (34) of the substrate (32); compressing the second precursor material (35b) between the substrate (32) and a second bearing surface (55a); sintering the second precursor material (35b) thus compressed to obtain a second abradable coating portion (36b), facing the second portion (33) of the substrate (32), having a second density distinct from the first.
    [2" id="c-fr-0002]
    The method of claim 1, wherein the steps of compressing and sintering the first precursor material (35a) are performed within a first mold (40), and wherein the first mold comprises the first bearing surface. (45) and at least one shield wall (44a) provided for flanking the first precursor material (35a) at the interface between the first and second portions of the substrate (33, 34) during the steps of compression and sintering of the first precursor material (35a).
    [3" id="c-fr-0003]
    The method according to claim 1 or 2, wherein the steps of compressing and sintering the second precursor material (35b) are performed within a second mold (50), and wherein the second mold (50) comprises a movable portion (55) extending opposite the second portion (34) of the substrate (32) and including the second bearing surface (55a), and a stationary portion (54) extending in a screw-like manner to the first portion of the substrate.
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 3, wherein the first portion of the abradable coating (36a) 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 of the abradable coating (36b) 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 one of the portions of the substrate, preferably on the second portion (134) of the substrate (132). , a sintering step of a bead layer (137), the final porosity of which is less than 15% and preferably less than 5%, on the portion of the substrate considered.
    [7" id="c-fr-0007]
    The method according to any one of claims 1 to 6, further comprising, after the step of sintering one of the precursor materials, a sintering step of a surface layer (238), the final porosity rate is less than 15% and preferably less than 5%, on at least one part of the abradable coating, preferably on its second part (236b).
    [8" id="c-fr-0008]
    The method according to any one of claims 1 to 7, wherein the first precursor material (35a) is a powder whose particle size is less than 20 μm, and wherein the second precursor material (35b) is a powder whose particle size is between 45 pm and 100 pm.
    [9" id="c-fr-0009]
    The method of any one of claims 1 to 8, wherein the substrate is a ring sector (11).
    [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 the first portion, having a sintered material having a second density distinct from the first density.
    [11" id="c-fr-0011]
    11. Abradable track according to claim 10, obtained using a manufacturing method according to any one of claims 1 to 9.
    [12" id="c-fr-0012]
    A turbine or compressor ring comprising an abradable track (20) according to claim 10 or 11.
    [13" id="c-fr-0013]
    13. A turbomachine comprising an abradable track (20) according to claim 10 or 11, or a turbine ring or compressor (10) according to claim 12.
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    同族专利:
    公开号 | 公开日
    CN108367359A|2018-08-03|
    CN108367359B|2021-07-27|
    FR3044946B1|2018-01-12|
    WO2017103422A1|2017-06-22|
    EP3389903A1|2018-10-24|
    US20180371932A1|2018-12-27|
    US11174749B2|2021-11-16|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1361814A|1970-12-21|1974-07-30|Clevite Corp|Powder metal honeycomb|
    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|FR3082765A1|2018-06-25|2019-12-27|Safran Aircraft Engines|METHOD FOR MANUFACTURING AN ABRADABLE LAYER|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|
    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|
    CN104451519B|2014-11-26|2017-01-18|华东理工大学|Multi-layer thermal barrier coating and forming method thereof|
    US10273192B2|2015-02-17|2019-04-30|Rolls-Royce Corporation|Patterned abradable coating and methods for the manufacture thereof|
    US20160305319A1|2015-04-17|2016-10-20|General Electric Company|Variable coating porosity to influence shroud and rotor durability|
    FR3044945B1|2015-12-14|2018-01-12|Centre National De La Recherche Scientifique|ABRADABLE COATING WITH VARIABLE DENSITY|US11215070B2|2019-12-13|2022-01-04|Pratt & Whitney Canada Corp.|Dual density abradable panels|
    CN111546006A|2020-05-12|2020-08-18|华能国际电力股份有限公司玉环电厂|Method for improving abrasion resistance of boiler tube elbow through foamed aluminum|
    法律状态:
    2016-12-05| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-16| PLSC| Publication of the preliminary search report|Effective date: 20170616 |
    2017-11-21| 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 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1562324|2015-12-14|
    FR1562324A|FR3044946B1|2015-12-14|2015-12-14|ABRADABLE COATING WITH VARIABLE DENSITY|FR1562324A| FR3044946B1|2015-12-14|2015-12-14|ABRADABLE COATING WITH VARIABLE DENSITY|
    US16/062,249| US11174749B2|2015-12-14|2016-12-13|Abradable coating having variable densities|
    CN201680073260.9A| CN108367359B|2015-12-14|2016-12-13|Wear resistant coating with variable density|
    EP16825487.8A| EP3389903A1|2015-12-14|2016-12-13|Abradable coating having variable densities|
    PCT/FR2016/053360| WO2017103422A1|2015-12-14|2016-12-13|Abradable coating having variable densities|
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