• 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 invention relates to a method for manufacturing a turbomachine turbine ring (24), comprising the manufacture of at least one turbine ring sector (26), the positioning of the turbine ring sector (26). in a lower mold so that an outer surface of the turbine ring sector is in at least partial contact with the lower mold and depositing a layer of powder on an inner surface (28) of the sector (26) of turbine ring. An upper mold is then positioned on the powder layer and an abradable layer (32) is produced by a sintering process SPS of the powder layer, the abradable layer (32) being intended to be arranged facing a turbine wheel.
    公开号:FR3048629A1
    申请号:FR1652102
    申请日:2016-03-14
    公开日:2017-09-15
    发明作者:Jean-Baptiste Mottin；Yannick Marcel Beynet；Geoffroy Chevallier；Romain Epherre；Claude Estournes
    申请人:Centre National de la Recherche Scientifique CNRS；Universite Paul Sabatier Toulouse III；SNECMA SAS；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION [0001] The present disclosure relates to a method of manufacturing a turbomachine turbine ring.
    In many rotating machines, it is now known to provide the stator ring of abradable tracks opposite the top of the blades of the rotor. 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 erodes 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.
    However, their use is more rare in the turbines of such turbomachines, especially in high pressure turbines in which extreme physicochemical conditions prevail.
    Indeed, the burnt gases from the combustion chamber open into the high pressure turbine at very high temperature and pressure levels, resulting in premature erosion of conventional abradable tracks.
    Therefore, in order to protect the turbine ring, it is often preferred to provide the latter with a thermal barrier type coating whose materials and high density, too important for the coating to be effectively abradable, allow to protect the 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 therefore increases the leakage rate at the top of the blades and thus reduces the performance of the turbine.
    OBJECT AND SUMMARY OF THE INVENTION [0007] The present disclosure aims at remedying at least part of these disadvantages.
    For this purpose, the present disclosure relates to a method of manufacturing a turbomachine turbine ring, comprising the following steps: - manufacture of at least one turbine ring sector; positioning the turbine ring sector in a lower wad so that an outer surface of the turbine ring sector is in contact at least with the lower wad; depositing a layer of powder on an inner surface of the turbine ring sector; positioning of an upper mold on the powder layer; and - producing an abradable layer on the inner surface by an SPS sintering process of the powder layer, the abradable layer being intended to be arranged facing a turbine wheel.
    The turbine ring is generally made of several parts, each part forming a small turbine ring sector compared to the dimensions of the turbine ring compiet. It is therefore simple to arrange a ring sector in a slurry.
    The inner surface of the turbine ring sector is the surface that faces the turbine wheel when the turbine ring is mounted in the turbine, so it is this inner surface on which the powder.
    The sintering process SPS, in accordance with the acronym for "Spark Plasma Sintering", also known as sintering FAST, according to the acronym for "Field Assisted Sintering Technology", or sintering flash, is a sintering process wherein a powder is simultaneously subjected to high intensity pulsed current and uniaxial pressure to form a sintered material. SPS sintering is generally performed under a controlled atmosphere and may be assisted by a heat treatment.
    The sintering time SPS is relatively short and SPS sintering allows a choice of starting powders which is relatively limited. In fact, SPS sintering makes it possible in particular to sinter, that is to say densify, materials whose welding is relatively complicated to achieve, if not impossible, because these materials easily crack when heated. Because of the choice of SPS sintering and the short duration of this sintering, it is therefore possible to produce an abradable layer with a very large variety of materials.
    Furthermore, the SPS sintering being carried out under uniaxial pressure exerted by the lower mold and the upper mold on the powder layer, the shrinkage due to the sintering of the powder layer to give the abradable layer is limited to direction of application of the pressure. There is therefore no removal of the powder layer in directions perpendicular to the direction of application of the pressure. Also, the abradable layer covers the entire inner surface of the ring sector.
    The turbine ring is covered with an abradable layer. It is therefore possible to provide a relatively small clearance between the turbine ring and the rotor, for example the vanes of a turbine wheel, and to improve the performance of the turbine, without the risk of damaging the vanes in the event of friction of the latter on the stator ring.
    In addition, the SPS sintering allows the formation of a diffusion layer between the abradable layer and the material forming the ring sector so that the abradable layer is firmly attached to the material forming the sector of the 'ring. The abradable layer thus formed can not be withdrawn from the ring sector unintentionally.
    The method may further comprise the following steps: - assembling a plurality of turbine ring sectors, the inner surface of each turbine ring sector being covered with an abradable layer; and machining a free surface of the abradable layer.
    Once several turbine ring sectors assembled, the abradable layer of each ring sector has a free surface that may not be in line with the free surface of the adjacent ring sector. Also, the free surfaces of the different ring sectors are machined so as to have a surface intended to face the turbine wheel which has the least possible discontinuity. Indeed, if such discontinuities are present, the blade wheel could come to butter against these discontinuities and thus cause shocks in the turbine, which is not desirable.
    The lower mold may have a shape complementary to the outer surface of the turbine ring sector.
    Thus, the lower mold applies a relatively uniform pressure on the outer surface of the ring sector. However, since the lower mold has a shape complementary to the outer surface of the ring sector, the mold makes it possible to accommodate the dimensional variations of one ring sector to another due to the manufacturing process of the sector. ring. Indeed, the turbine sectors may for example be obtained by a casting process and the dimensions of each turbine sector may vary slightly from one turbine sector to another.
    Before positioning the turbine ring sector in the lower mold and the upper mold, a layer of chemically inert material can be deposited on the lower mold and on the upper mold.
    This layer of chemically inert material reduces the chemical reactions between the powder layer and the turbine ring sector with the lower mold and the upper mold during SPS sintering. The chemically inert material makes it possible in particular to reduce, or even to avoid, the bonding of the abradable layer and / or the ring sector with the parts of the mold.
    The chemically inert material also reduces or even avoid the formation of a carbide layer on the free surface of the abradable layer. It is sought to avoid the formation of this layer of carbide which, if it is formed, must be removed from the abradable layer before use.
    In the lower mold, the chemically inert material can also make it possible to fill the existing spaces between the lower mold and the outer surface of the turbine ring sector. Thus, the uniformity of the pressure exerted by the lower mold on the turbine ring sector and thus on the powder layer is improved.
    The chemically inert material may for example comprise boron nitride or corundum. The term "chemically inert material" comprising boron nitride means a material which comprises at least 95% by weight of boron nitride. Likewise, a chemically inert material comprising corundum is understood to mean a material which comprises at least 95% by weight of corundum.
    The powder may be a metal powder based on cobalt or nickel.
    By "cobalt-based" is meant a metal powder whose cobalt has the highest percentage by mass. Similarly, "nickel-based" means a metal powder whose nickel has the highest mass percentage. Thus, for example, a metal powder comprising 38% by weight of cobalt and 32% by weight of nickel will be designated as a cobalt-based powder, cobalt being the chemical element whose weight percentage is the most important in the powder. metallic.
    The metal powders based on cobalt or nickel are powders which, when sintered, have good resistance to high temperature. They can thus fulfill the double function of abradable and heat shield. For example, mention may be made of CoNiCrAlY superalloys. These metal powders also have the advantage of having a chemical composition similar to the chemical composition of the material forming the turbine ring, for example the AMI or N5 superalloys. The SPS sintering can be carried out for a duration less than or equal to 60 minutes, preferably less than or equal to 30 minutes, more preferably less than or equal to 15 minutes.
    The sintering time SPS is relatively short.
    The upper mold and the lower mold may be made of graphite and SPS sintering may be performed at a temperature greater than or equal to 800 ° C, preferably greater than or equal to 900 ° C.
    The SPS sintering may be performed at a pressure greater than or equal to 10 MPa, preferably greater than or equal to 20 MPa, more preferably greater than or equal to 30M Pa.
    The upper mold and the lower mold may be of tungsten carbide and SPS sintering may be performed at a temperature greater than or equal to 500 ° C, preferably greater than or equal to 600 ° C.
    The SPS sintering may be performed at a pressure greater than or equal to 100 MPa, preferably greater than or equal to 200 MPa, more preferably greater than or equal to 300 MPa.
    The abradable layer may have an open porosity less than or equal to 20%, preferably less than or equal to 15%, more preferably less than or equal to 10%.
    With the SPS sintering method, it is possible, by varying the sintering parameters such as the pressure, the sintering temperature and / or the sintering time and thus vary the porosity of the abradable layer obtained. This method of manufacturing a turbomachine turbine ring therefore allows great flexibility.
    The abradable layer may have a thickness greater than or equal to 0.5 mm, preferably greater than or equal to 4 mm and less than or equal to 15 mm, preferably less than or equal to 10 mm, even more preferably lower or equal to 5 mm.
    The turbine ring may comprise a number of turbine ring sectors greater than or equal to 20, preferably greater than or equal to 30, and even more preferably greater than or equal to 40.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the invention will emerge from the following description of embodiments of the invention, given by way of non-limiting examples, with reference to the appended figures, in which: Figure 1 is a schematic longitudinal sectional view of a turbomachine; FIG. 2 is a schematic perspective view of a turbine ring sector comprising an abradable layer; - Figure 3 is a sectional view of a turbine ring sector in a SPS sintering mold, according to a sectional plane similar to the sectional plane III-III of Figure 2; FIGS. 4A and 4B are schematic lateral views of several turbine ring sectors covered with an abradable layer, respectively before and after machining of a free surface of the abradable layer; FIG. 5 is a scanning electron microscope image of an interface between a ring sector and an abradable layer; FIG. 6 shows the evolution of the concentration of certain chemical elements from the abradable layer to the ring sector; FIGS. 7A-7D are images made using a scanning electron microscope of the microstructure of different abradable layers.
    DETAILED DESCRIPTION OF THE INVENTION FIG. 1 represents, in section along a vertical plane passing through its main axis A, a turbofan engine 10. The turbofan engine 10 comprises, from upstream to downstream according to the circulation. of the air flow, a blower 12, a low-pressure compressor 14, a high-pressure compressor 16, a combustion chamber 18, a high-pressure turbine 20, and a low-pressure turbine 22.
    The high pressure turbine 20 comprises a plurality of rotating blades 20A rotating with the rotor and 20B rectifiers mounted on the stator. The stator of the turbine 20 comprises a plurality of stator rings 24 arranged vis-à-vis the blades 20A of the turbine 20.
    As can be seen in FIG. 2, each stator ring 24 is made of a plurality of ring sectors 26. Each ring sector 26 has an inner surface 28, an outer surface 30 and an abradable layer 32 on which the rotor blades 20A can be rubbed.
    For example, the ring sector 26 is made of cobalt or nickel-based superalloy, such as the AMI superalloy or the N5 superalloy, and the abradable layer 32 is obtained from a metal powder at 25.degree. cobalt or nickel base.
    The method of manufacturing the turbine ring 24 comprises a first step of manufacturing at least one turbine ring sector 26, for example by a casting process.
    Figure 3 shows a sectional view of the turbine ring sector 26 in a SPS sintering mold. The mold comprises a lower mold 34 of complementary shape of the outer surface 30 of the ring sector 26.
    The ring sector 26 is positioned in a lower mold 34 so that the outer surface 30 of the ring sector 26 is at least partially in contact with the lower mold 34. The lower mold 34 is therefore not in contact with the ring sector 26 over the entire outer surface 30 of the ring sector 26. The visible spaces between the ring sector 26 and the lower mold 34 make it possible to accommodate the dimensional variations due to the manufacturing process of the different ring sectors. However, the shape of the lower mold 34 being complementary to the outer surface 30 of the ring sector 26, the pressure exerted by the lower mold 34 on the ring sector 26 is relatively uniform.
    A powder layer 36 is then deposited on the inner surface 28 of the ring sector 26 and the upper mold 38 is positioned on the powder layer 36.
    The SPS sintering step is then carried out which makes it possible to obtain an abradable layer 32 produced directly on the ring sector 26. For example, the upper mold 38 and the lower mold 34 may be made of graphite. They can also be tungsten carbide.
    Before positioning the ring sector 26 in the lower mold 34, a layer of chemically inert material may be deposited in the lower mold 34 and on the upper mold 38. For example, the inert chemical material may be nitride of boron applied with a spray. It is also possible to add boron nitride powder so as to fill the spaces present between the ring sector 26 and the lower mold 34.
    The chemically inert material may also be corundum.
    The ring sector 26 coated with the abradable layer 32 is then removed from the mold.
    As shown in FIG. 4A, to form a complete ring 24, several ring sectors 26 are assembled together, each ring sector 26 being covered with an abradable layer 32. Once these sectors 26 are assembled turbine ring, the abradable layer 32 of each ring sector has a free surface 44 which may not be in line with the free surface 44 of the adjacent ring sector 26. Also, the free surfaces 44 of the different ring sectors 26 are machined so as to have a machined surface 46 for facing the turbine wheel. This machined surface 46 has the least possible discontinuity. Indeed, if such discontinuities are present, the blade wheel could come to butter against these discontinuities and thus cause shocks in the turbine, which is not desirable.
    FIG. 5 is a scanning electron microscope image of an interface between a ring sector 26 and an abradable layer 32. For example, this abradable layer 32 is sintered on the sector 26 of FIG. ring at 950 ° C under a pressure of 40 MPa for 30 minutes.
    The pressure can be applied cold, that is to say from the beginning of the cycle, or hot, during the sintering stage.
    As can be seen in FIGS. 5 and 6, the chemical composition evolves progressively, ie the iong of the line 40 of FIG. 5, starting from the ring sector 26 towards the abradable layer 32 in FIG. defining a diffusion zone 42 at the interface between the ring sector 26 and the abradable layer 32.
    FIGS. 7A-7D represent different microstructures of abradable layers 32 whose open porosity is respectively about 10%, about 7%, about 3% and almost zero.
    Thus, it can be seen that by modifying the SPS sintering parameters, such as temperature, pressure and dwell time, it is possible to obtain abradable layers 32 having a different structure. For example, Figure 7A shows an abradable layer 32 obtained in a SPS sintering step at 925 ° C for 10 minutes applying a pressure of 20 MPa. Figure 7D shows an abradable layer 32 obtained during a SPS sintering step at 950 ° C for 30 minutes applying a pressure of 40 MPa.
    It is understood that the thickness of the abradable layer 32 obtained after SPS sintering depends in particular on the thickness of the powder layer 36 deposited on the inner surface 28 of the ring sector 26 as well as sintering parameters. SPS. The thickness of the abradable layer 32 obtained after SPS sintering can also depend on the particle size and the morphology of the powder used. In particular, the morphology of the powder may depend on the method of manufacturing the powder. Thus a powder produced by gas atomization or rotating electrode will have grains of substantially spherical shape while a powder made by liquid atomization will have grains of less regular shape.
    Although the present description has been described with reference to a specific embodiment, it is obvious that various modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In addition, individual features of the various embodiments mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    REVENDICATONS
    A method of manufacturing a turbomachine turbine ring (24), comprising the steps of: - manufacturing at least one turbine ring sector (26); positioning the turbine ring sector (26) in a lower mold (34) so that an outer surface (30) of the turbine ring sector (26) is in at least partial contact with the lower mold ( 34); depositing a powder layer (36) on an inner surface (28) of the turbine ring sector (26); positioning an upper mold (38) on the powder layer (36); and - producing an abradable layer (32) on the inner surface (28) by an SPS sintering process of the powder layer (36), the abradable layer (32) being intended to be disposed opposite to a turbine wheel.
    [2" id="c-fr-0002]
    The method of claim 1, further comprising the steps of: - assembling a plurality of turbine ring sectors (26), the inner surface (28) of each turbine ring sector (26) being covered with an abradable layer (32); and machining a free surface (44) of the abradable layer (32).
    [3" id="c-fr-0003]
    The method of claim 1 or 2, wherein the lower mold (34) has a shape complementary to the outer surface (30) of the turbine ring sector (26).
    [4" id="c-fr-0004]
    A method according to any one of claims 1 to 3, wherein, before positioning the turbine ring sector (26) in the lower mold (34) and the upper mold (38), a layer of chemically inert material on the lower mold (34) and on the upper mold (38).
    [5" id="c-fr-0005]
    5. Process according to any one of the preceding claims, in which the powder is a metal powder based on cobalt or nickel.
    [6" id="c-fr-0006]
    6. Process according to any one of the preceding claims, in which the SPS sintering is carried out for a duration less than or equal to 60 minutes, preferably less than or equal to 30 minutes, more preferably less than or equal to 15 minutes.
    [7" id="c-fr-0007]
    7. Process according to any one of claims 1 to 6, wherein the upper mold (38) and the lower mold (34) are made of graphite and in which the SPS sintering is carried out at a temperature greater than or equal to 800 ° C. preferably greater than or equal to 900 ° C.
    [8" id="c-fr-0008]
    8. The method of claim 7, wherein the SPS sintering is carried out at a pressure greater than or equal to 10 MPa, preferably greater than or equal to 20 MPa, more preferably greater than or equal to 30M Pa.
    [9" id="c-fr-0009]
    The process according to any one of claims 1 to 6, wherein the upper mold (38) and the lower mold (34) are of tungsten carbide and wherein the SPS sintering is carried out at a temperature greater than or equal to 500 ° C, preferably greater than or equal to 600 ° C.
    [10" id="c-fr-0010]
    10. The method of claim 9, wherein the SPS sintering is carried out at a pressure greater than or equal to 100 MPa, preferably greater than or equal to 200 MPa, still more preferably greater than or equal to 300 MPa.
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    同族专利:
    公开号 | 公开日
    CN109070219A|2018-12-21|
    FR3048629B1|2018-04-06|
    US20190054537A1|2019-02-21|
    US10843271B2|2020-11-24|
    CN109070219B|2021-08-17|
    EP3429784A1|2019-01-23|
    WO2017158264A1|2017-09-21|
    引用文献:
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    EP2159460A1|2008-08-27|2010-03-03|United Technologies Corporation|Preforms and related methods for repairing abradable seals of gas turbine engines|
    FR2941965A1|2009-02-10|2010-08-13|Snecma|Depositing a protection layer on a metallic piece e.g. turbine blade using mold, comprises depositing precursor coating on piece and/or inner walls of mold, and depositing piece in the mold and then mold in a compression enclosure|
    US20130017072A1|2011-07-14|2013-01-17|General Electric Company|Pattern-abradable/abrasive coatings for steam turbine stationary component surfaces|
    US20130177740A1|2012-01-10|2013-07-11|Gary B. Merrill|Powder-based material system with stable porosity|
    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|
    FR3088839A1|2018-11-23|2020-05-29|Safran Aircraft Engines|METHOD FOR MANUFACTURING A METAL PART FOR AN AIRCRAFT TURBOMACHINE|US6976532B2|2003-06-26|2005-12-20|The Regents Of The University Of California|Anisotropic thermal applications of composites of ceramics and carbon nanotubes|
    US20120107103A1|2010-09-28|2012-05-03|Yoshitaka Kojima|Gas turbine shroud with ceramic abradable layer|
    US9056354B2|2011-08-30|2015-06-16|Siemens Aktiengesellschaft|Material system of co-sintered metal and ceramic layers|
    US9149777B2|2011-10-10|2015-10-06|Baker Hughes Incorporated|Combined field assisted sintering techniques and HTHP sintering techniques for forming polycrystalline diamond compacts and earth-boring tools|
    ITFI20120035A1|2012-02-23|2013-08-24|Nuovo Pignone Srl|"IMPELLER PRODUCTION FOR TURBO-MACHINES"|
    US20170009329A1|2015-07-06|2017-01-12|Ngimat Co.|Conductive Additive Electric Current Sintering|FR3048018B1|2016-02-22|2018-03-02|Safran Aircraft Engines|DEVICE FOR APPLYING ABRADABLE MATERIAL TO A SURFACE OF A TURBOMACHINE CASING|
    法律状态:
    2017-03-14| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-15| PLSC| Publication of the preliminary search report|Effective date: 20170915 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, FR Effective date: 20180809 Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 Owner name: UNIVERSITE PAUL SABATIER - TOULOUSE III, FR Effective date: 20180809 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652102A|FR3048629B1|2016-03-14|2016-03-14|PROCESS FOR MANUFACTURING A TURBINE RING FOR TURBOMACHINE|
    FR1652102|2016-03-14|FR1652102A| FR3048629B1|2016-03-14|2016-03-14|PROCESS FOR MANUFACTURING A TURBINE RING FOR TURBOMACHINE|
    EP17715221.2A| EP3429784A1|2016-03-14|2017-03-10|Method for manufacturing a turbine shroud for a turbomachine|
    CN201780023920.7A| CN109070219B|2016-03-14|2017-03-10|Method for manufacturing a turbine shroud of a turbomachine|
    PCT/FR2017/050546| WO2017158264A1|2016-03-14|2017-03-10|Method for manufacturing a turbine shroud for a turbomachine|
    US16/084,567| US10843271B2|2016-03-14|2017-03-10|Method for manufacturing a turbine shroud for a turbomachine|
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