• 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:
    Turbine ring sector (10) of ceramic matrix composite material having an annular base portion (12) with an inner face for defining the inner face of a turbine ring (1) when the ring sector is mounted to a ring support structure (3) and an outer face from which a hooking portion (14, 16) extends from the ring sector to the ring support structure (3), the ring sector (10) further comprising intersector faces (20) each intended to face an adjacent ring sector when the ring sector (10) is mounted on the support structure of the ring ring (3). The inter-sector faces (20) are coated by an environmental barrier (22) doped with an electrically conductive compound and having at least one slot (24). The invention also relates to a turbine ring assembly, and a turbomachine comprising such a ring sector, and a method of manufacturing a ring sector.
    公开号:FR3048016A1
    申请号:FR1651347
    申请日:2016-02-18
    公开日:2017-08-25
    发明作者:Maxime Carlin；Lisa Pin
    申请人:Herakles SA；
    IPC主号:
    专利说明:

    Background of the invention
    The present invention relates to a turbine ring sector made of a ceramic matrix composite material, a turbine ring assembly, in particular intended to be used in a turbomachine, and a method of manufacturing such a ring sector. .
    In the case of all-metal turbine ring assemblies, it is necessary to cool all the elements of the assembly and in particular the turbine ring which is subjected to the hottest flows. This cooling has a significant impact on the engine performance since the cooling flow used is taken from the main flow of the engine. In addition, the use of metal for the turbine ring limits the possibilities of increasing the temperature at the turbine, which would however improve the performance of aircraft engines.
    In an attempt to solve these problems, it has been envisaged to produce turbine ring sectors made of ceramic matrix composite material (CMC) in order to overcome the implementation of a metallic material.
    CMC materials have good mechanical properties making them suitable for constituting structural elements and advantageously retain these properties at high temperatures. The use of CMC materials has advantageously made it possible to reduce the cooling flow to be imposed during operation and thus to increase the performance of the turbomachines. In addition, the use of CMC materials advantageously makes it possible to reduce the weight of the turbomachines and to reduce the effect of hot expansion encountered with the metal parts.
    In the operating conditions of aeronautical turbines, characterized in particular by high temperatures and a corrosive environment, CMC materials can degrade. To protect the parts of the ring sectors exposed to the corrosive hot air flow of the turbine, it is known to coat these parts with an environmental barrier (also called "EBC" of the English "Environmental
    Barrier Coating "). For example, multilayer environmental barriers of the Si / Mullite / BSAS type (where BSAS corresponds to a barium and strontium aluminosilicate) are known, or those comprising a silicon bonding layer and a layer of a rare earth silicate ( for example Y2S12O7). These environmental barriers can be deposited, in a manner known per se, by thermal spraying, physical vapor deposition (PVD) or slip deposit (for example "dip coating" or "spray coating") processes. .
    The inter-sector faces of each ring sector generally comprise slits in which are placed sealing tabs, which make it possible to prevent the leakage of gas outside the gas flow flow path in the turbine. . These slots, which are so-called "blind" forms, can be formed by conventional machining methods.
    It would be desirable, however, to simplify the formation of slots on the inter-sector faces of ring sectors.
    OBJECT AND SUMMARY OF THE INVENTION To this end, the invention proposes, according to a first aspect, a turbine ring sector made of ceramic matrix composite material having an annular base portion with an internal face intended to define the internal face. of a turbine ring when the ring sector is mounted to a ring support structure and an outer face from which extends a hooking portion of the ring sector to the support structure of ring, the ring sector further comprising intersector faces each intended to face an adjacent ring sector when the ring sector is mounted on the ring support structure. According to the invention, the inter-sector faces are coated by an environmental barrier doped with an electrically conductive compound and having at least one slot.
    By "environmental barrier doped with an electrically conductive compound" is meant that the environmental barrier comprises at least one layer doped with an electrically conductive compound and that the content of electrically conductive element in this layer is sufficient to make this electrically conductive layer while being low enough not to significantly affect the properties of the environmental barrier. In some examples, the doped layer may constitute the outer layer of the environmental barrier. Alternatively, the doped layer may be coated with one or more electrically conductive layers, that is to say comprising an electrically conductive material, for example a layer comprising silicon.
    The doping of the environmental barrier by the electrically conductive compound gives the latter an electrically conductive character and thus makes it possible to form the slot by machining the environmental barrier by an electro-erosion process, thus greatly simplifying the formation of this slot compared to conventional machining methods.
    The slot may extend over the entire thickness of the environmental barrier, or alternatively extend only a portion of the thickness of the environmental barrier. In one example, the slot may extend only in the thickness of the environmental barrier, and not in the underlying CMC material. The slot may also extend into a bonding layer possibly in contact with the ceramic matrix composite material of the ring sector, or even into the CMC material of the ring sector.
    In an exemplary embodiment, the electrically conductive compound may be silicon. In an exemplary embodiment, the electrically conductive compound may be an electrically conductive carbon compound, for example carbon or an electrically conductive carbon polymer. In an exemplary embodiment, the electrically conductive compound may be a metal compound.
    In an exemplary embodiment, the environmental barrier further comprises at least one rare earth silicate. An example of rare earth silicate may be Y2Si207.
    In this case, the environmental barrier may comprise a first layer comprising the rare earth silicate doped with the electrically conductive compound and a second bonding layer, for example made of silicon, located between the first layer and the ceramic matrix composite material of the sector. ring. The second bonding layer ensures in particular the attachment of the first layer and protects the underlying CMC material from oxidation. In general, one can choose the electrically conductive compound so that it is compatible with the majority material forming the doped layer. Thus, the use of silicon is advantageous in the case where the environmental barrier comprises a doped layer of a rare earth silicate because it can be oxidized silica S1O2 which is compatible with the material of this layer. In general, whatever the embodiment considered, the mass content of electrically conductive compound in the layer of the environmental barrier in which this compound is present may be less than or equal to 35%, for example between 5% and 35%.
    In an exemplary embodiment, the environmental barrier comprises at least one layer of a doped rare earth silicate having a silicon mass content of less than or equal to 35%, for example between 5% and 35%. In an exemplary embodiment, the environmental barrier comprises at least one layer of a doped rare earth silicate having a mass content of electrically conductive carbon compound of less than or equal to 35%, for example between 5% and 35%. In an exemplary embodiment, the environmental barrier comprises at least one layer of a doped rare earth silicate having a metal compound content by weight of less than or equal to 35%, for example between 5% and 35%.
    In an exemplary embodiment, the environmental barrier comprises at least one layer of doped barium aluminosilicate and strontium (BSAS) having a silicon mass content of less than or equal to 35%, for example between 5% and 35%. In an exemplary embodiment, the environmental barrier comprises at least one layer of doped barium aluminosilicate and strontium having a mass content of electrically conductive carbon compound of less than or equal to 35%, for example between 5% and 35%. In an exemplary embodiment, the environmental barrier comprises at least one layer of doped barium aluminosilicate and strontium having a mass content of metal compound of less than or equal to 35%, for example between 5% and 35%. The invention also provides a turbine ring assembly comprising a plurality of ring sectors forming a turbine ring and a ring support structure, each ring sector being mounted on the ring support structure and being as defined above, at least one sealing tab being present in the slot of the environmental barrier of each ring sector.
    A turbomachine comprising a turbine ring assembly such as that described above is also an object of the present invention.
    According to a second aspect, the subject of the invention is a method for manufacturing a ring sector such as that presented above, the method comprising at least the following steps: formation on the inter-sector faces of a sector of ring of an environmental barrier doped with an electrically conductive compound, and - formation by electro-erosion of at least one slot in the environmental barrier thus formed.
    BRIEF DESCRIPTION OF THE DRAWINGS Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which: FIG. 1 shows a turbine ring sector mounted on a ring support structure; FIGS. 2 to 5 are sectional views of an intersector face of a turbine ring sector at a slot; according to various embodiments of the invention, and - Figure 6 is a flow chart showing the various steps of a method of manufacturing a turbine ring sector according to one embodiment of the invention.
    detailed description
    FIG. 1 shows a high pressure turbine ring assembly comprising a turbine ring 1 made of ceramic matrix composite material (CMC) and a metal ring support structure 3. The turbine ring 1 surrounds a set of blades rotary (not shown). The turbine ring 1 is formed of a plurality of ring sectors 10, FIG. 1 showing a single ring sector mounted on the ring support structure 3. In the illustrated example, each sector of FIG. ring 10 has, in axial section, a section in the form of π. Throughout the disclosure, the axial (arrow DA) and radial (arrow DR) directions are defined with respect to the axis of the turbine ring, corresponding moreover to the longitudinal axis of the engine.
    Each ring sector 10 has an annular base 12 having an inner face with respect to the radial direction DR and an outer face with respect to the radial direction DR. Each ring sector 10 has a substantially inverted π-shaped section with an annular base 12 whose inner face coated with a layer 13 of abradable material defines the flow stream of gas flow in the turbine. Upstream and downstream tabs 14, 16 extend from the outer face of the annular base 12 in the radial direction DR. The terms "upstream" and "downstream" are used herein with reference to the flow direction of the gas flow in the turbine (arrow F).
    The ring support structure 3 is here secured to a turbine casing 30 and comprises an annular upstream radial flange 32 and an annular downstream radial flange 34. The tabs 14, 16 of each ring sector 10 enclose the upstream flanges. and downstream 32, 34 of the ring support structure 3. In the illustrated example, pins 18 are inserted into bores made in the lugs 14, 16 of each ring sector and ensure the attachment of each sector of the ring. ring 10 on the ring support structure 3. For this purpose, bores (not visible in the figures) may be present in the flanges 32, 34 of the ring support structure for housing the pins 18.
    Each ring sector 10 comprises two intersecting faces 20 intended to face an inter-sector face 20 of a neighboring ring sector 10. The inter-sector faces 20 are each present in a plane defined by the radial direction DR and axial direction DA. Each inter-sector face 20 is coated with an environmental barrier 22 for the purpose of protecting the CMC material of the ring sector 10 from high temperatures and corrosive gases of the vein. This environmental barrier 22 is provided with slots 24 or grooves for accommodating sealing tongues 25 which, when all the ring sectors 10 are assembled to form the turbine ring 1, make it possible to prevent the gases of escaping from the flow stream of gaseous flow between the ring sectors 10. The slots 24 are blind forms, that is to say are non-through.
    FIG. 2 shows a sectional view along a radial plane of the ring sector 10 at an inter-sectoral face 20 and more precisely at a slot 24. In this example, the environmental barrier 22 consists of a first layer 40 doped with the electrically conductive compound and a second bonding layer 42. The bonding layer 42 is directly in contact with the inter-sector face 20 of the ring sector 10 on the one hand, and directly in contact with the first layer 40 on the other hand. The first layer 40 is here an outer layer of the environmental barrier 22, that is to say that it is not covered by another layer of material. The slot 24 is here made only within the first layer 40, that is to say that it does not extend into the second bonding layer 42 nor in the underlying CMC 10 material.
    The first layer 40 may comprise predominantly en masse a rare earth silicate RE2S12O7 where RE denotes a rare earth element, for example Y2Si2O7. Alternatively, the first layer 40 may comprise predominantly bulk aluminosilicate barium and strontium (BSAS). As for the second bonding layer 42, it may for example be silicon. The first layer 40 is doped with an electrically conductive compound. Such an electrically conductive compound may for example be silicon, carbon, an electrically conductive carbon polymer, or a metal compound. Thanks to the electrical conduction properties of the first layer 40 of the environmental barrier 22, the slot 24 can be made by electro-erosion in this first layer 40.
    In the example of Figure 3, the ring sector 10 is coated with an environmental barrier 122 which comprises, as before, a first layer 140 doped with an electrically conductive compound and a second bond layer 142 located between the first layer 140 and the CMC material of the ring sector 10. The inter-sectoral face 20 also comprises a slot 124 which can be made by electro-erosion. Unlike the example of FIG. 2, the slot 124 passes through the entire environmental barrier 122, i.e., the first 140 and second 142 layers, and terminates in the CMC material of the ring 10.
    In the example of Figure 4, the ring sector 10 is coated with an environmental barrier 222 which comprises: a first layer 240 doped with an electrically conductive compound, a second bonding layer 242 directly in contact with the CMC material of the inter-sector face 20 of the ring sector 10 and a third layer 244 directly in contact with the second bonding layer 242 and the first layer 240. The third layer 244 may comprise a material usually used for an environmental barrier, for example for example, a rare earth silicate or a barium and strontium aluminosilicate (BSAS) as for the first layer 240, with the difference that it is not necessarily doped with an electrically conductive compound. A slit 224 that can be machined by electro-erosion is also present within the first layer 240, which is here an outer layer of the environmental barrier 222.
    In the example of FIG. 5, the ring sector 10 is coated with an environmental barrier 322 which comprises: a first layer 340 doped with an electrically conductive compound, a second bonding layer 342 directly in contact with the CMC material of the ring sector 10 and the first layer 340, and a third layer 346 in contact with the first layer 340. The third layer 346, which is here the outer layer of the environmental barrier 322, is traversed by a slot 324 which extends into the first layer 324. The slot 324, however, extends neither in the second bonding layer 342 nor in the CMC ring sector 10 in the illustrated example. The third layer 346 comprises an electrically conductive compound, for example silicon, to enable electro-erosion machining of the slot 324 in the environmental barrier 322.
    A method of manufacturing a ring sector 10 made of CMC material according to the invention, comprising inter-sector faces 20 coated with an environmental barrier 22, 122, 222, 322, will now be described in connection with the flow chart of Figure 6.
    In a first step E1, an environmental barrier 22, 122, 222, 322 may be formed on each inter-sector face 20. To do this, it is first possible to deposit a bonding layer 42, 142, 242, 342 directly on the CMC material. For example, the bonding layer 42, 142, 242, 342 may be deposited, in a manner known per se, by thermal spraying, by a liquid route (for example by "spray coating" or "dip coating") or by physical deposition. vapor phase. As previously described, this link layer may be silicon-based.
    Then, the layer 40, 140, 340 doped with an electrically conductive compound can be deposited directly on the bonding layer 42, 142, 342. This layer 40, 140, 340 can also be deposited by thermal spraying a mixture of powders of the compound majority of said layer and the electrically conductive dopant compound. Alternatively, it can also be deposited by liquid from a mixture of powders in a slip (for example by "spray coating" or "dip coating"); or by physical vapor deposition. As previously described, the major compound of the layer 40, 140, 340 may be a rare earth silicate, or a barium and strontium aluminosilicate (BSAS), and the electrically conductive dopant compound may be silicon or carbon.
    To obtain an environmental barrier such as that illustrated in FIG. 4, it is possible, before depositing the layer 240 doped with an electrically conductive compound, to deposit a layer 244 devoid of an electrically conductive compound, in the same manner as for the layers 40, 140, 340.
    To obtain an environmental barrier such as that illustrated in FIG. 5, it is possible, after having deposited the layer 340 doped with an electrically conductive compound, to deposit a layer 346 based on a conductive element such as silicon, for example by thermal spraying. by liquid or physical vapor deposition.
    Finally, in a last step E2, one can form or finalize the formation of the slot 24, 124, 224, 324 by electro-erosion. To do this, it is possible, in a manner known per se, to immerse the inter-sectoral face 20 in a suitable liquid and to connect the environmental barrier 22, 122, 222, 322 to a terminal of a voltage generator. An electrode also connected to the other terminal of the same generator can then move to the surface of the immersed environmental barrier and, by electrical pulses imposed by the generator, machine the environmental barrier to form the slot 24,124, 224, 324.
    This last step E2 is made possible by the invention thanks to the presence of an electrically conductive compound as a dopant in the environmental barrier. The formation of the slot by electro-erosion makes it possible to obtain an improved accuracy in the dimensions of the slot compared to traditional machining methods, and is easier to implement than the latter.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    A turbine matrix ring sector (10) of ceramic matrix composite material having an annular base portion (12) with an inner face for defining the inner face of a turbine ring (1) when the ring is mounted to a ring support structure (3) and an outer face from which a hooking portion (14, 16) extends from the ring sector to the ring support structure (3). ), the ring sector (10) further comprising inter-sector faces (20) each intended to face an adjacent ring sector when the ring sector (10) is mounted on the structure of the ring. ring support (3), characterized in that the inter-sector faces (20) are coated by an environmental barrier (22; 122; 222; 322) doped with an electrically conductive compound and having at least one slot (24; 124; 224; 324).
    [2" id="c-fr-0002]
    The ring sector of claim 1, wherein the electrically conductive compound is silicon.
    [3" id="c-fr-0003]
    The ring sector of claim 1, wherein the electrically conductive compound is an electrically conductive carbon compound.
    [4" id="c-fr-0004]
    The ring sector of claim 1, wherein the electrically conductive compound is a metal compound.
    [5" id="c-fr-0005]
    Ring sector according to any one of claims 1 to 4, wherein the environmental barrier (22; 122; 222; 322) further comprises at least one rare earth silicate.
    [6" id="c-fr-0006]
    The ring sector of claim 5, wherein the environmental barrier (22; 122; 222; 322) comprises a first layer (40; 140; 240; 340) comprising the rare earth silicate doped with the electrically conductive compound. and a second bond layer (42; 142; 242; 342) located between the first layer and the ceramic matrix composite material of the ring sector (10).
    [7" id="c-fr-0007]
    Ring sector according to any one of claims 1 to 6, wherein the mass content of electrically conductive compound in the layer of the environmental barrier in which this compound is present is between 5% and 35%.
    [8" id="c-fr-0008]
    A turbine ring assembly comprising a plurality of ring sectors (10) forming a turbine ring (1) and a ring support structure (3), each ring sector (10) being mounted on the ring support structure (3) and being as defined in any one of claims 1 to 7, at least one sealing tongue (25) being present in the slot (24; 124; 224; 324); the environmental barrier of each ring sector.
    [9" id="c-fr-0009]
    9. A turbomachine comprising a turbine ring assembly according to claim 8.
    [10" id="c-fr-0010]
    10. A method of manufacturing a ring sector (10) according to any one of claims 1 to 7, the method comprising at least the following steps: - formation on the intersectoral faces (20) of a sector ring of an environmental barrier (22; 122; 222; 322) doped with an electrically conductive compound (step E1); and - electro-erosion formation of at least one slot (24; 124; 224; 324). in the environmental barrier thus formed (step E2).
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    引用文献:
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    法律状态:
    2017-02-10| PLFP| Fee payment|Year of fee payment: 2 |
    2017-08-25| PLSC| Search report ready|Effective date: 20170825 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-08-17| CD| Change of name or company name|Owner name: SAFRAN CERAMICS, FR Effective date: 20180716 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 5 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1651347A|FR3048016B1|2016-02-18|2016-02-18|TURBINE RING SECTOR WITH ENVIRONMENTAL BARRIER DOPED BY AN ELECTRICALLY CONDUCTIVE ELEMENT|
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    PCT/FR2017/050347| WO2017140985A1|2016-02-18|2017-02-16|Turbine shroud sector with environmental barrier doped by an electrically conductive element|
    CN201780012328.7A| CN108698947B|2016-02-18|2017-02-16|Turbine ring segment with an environmental barrier layer doped with a conductive element|
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