• 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 rotary assembly for a turbomachine, comprising: - a disc (16) having an outer periphery having an alternation of cells (22) and teeth (20), - blades (14) extending radially from the disc (16) and whose feet (24) are engaged axially and retained radially in the cavities (22) of the disk, - platforms (30) extending circumferentially from the blades (14) and which are arranged circumferentially end to each other, - axial sealing means upstream and / or downstream of an annular zone extending radially from the platforms (30) to the disk. According to the invention, the sealing means comprise radially an inner annular portion (64) and an outer annular portion (70) structurally distinct from each other, and whose outer annular portion is elastically constrained radially towards the inside by the inner annular part.
    公开号:FR3020408A1
    申请号:FR1453717
    申请日:2014-04-24
    公开日:2015-10-30
    发明作者:Stephane Pierre Guillaume Blanchard；Youki Olivier Ito-Lardeau
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to a rotary assembly for a turbomachine, such as in particular an aircraft turbojet, and to a turbomachine comprising such an assembly. Such an assembly, which is found in particular in a turbine, comprises a disk, and blades extending radially outwardly from the disk and whose feet are axially engaged and retained radially in cells of the outer periphery of the disk. disk, said cells being arranged alternately with teeth of the disk. The blades also comprise internal platforms circumferentially arranged end to end so as to together define the internal limit of the flow flow of the hot gases circulating in the turbine. The part of the blade situated internally in relation to the vein, that is to say between the internal platform and the foot, is called stilt. According to this arrangement, spaces are formed between two adjacent stilts, and form inter-stilt or inter-blade cavities. Cavities called cell bottom are also formed by radial spaces between the blade roots and the bottoms of the cells.
    [0002] In order to improve the performance of the turbomachine, and to prevent the disk from overheating by the flow of hot gases from an upstream combustion chamber and flowing through the vein, it is important to limit the maximum circulation of these gases under the platforms and through the inter-blade cavities, using sealing means. Indeed, the part of the vein gas flowing under the platforms does not participate in the drive in rotation of the blades and directly heats the teeth of the disc. It is particularly advantageous to arrange the sealing means downstream of the inter-blade cavities to allow pressurization of these cavities to a value substantially identical to that of the vein gases, which limits the effect of suction in the cavities. To this end, it is known to extend the platforms at their upstream and / or downstream ends by walls extending radially inwards to the teeth of the disc in order to axially close the inter-blade cavities. However, each pair of adjacent walls is inevitably separated circumferentially by a gap allowing the circulation of the vein gases. The number of interstices, corresponding to the number of blades, is then too great to allow an acceptable seal of the inter-blade cavities. According to another known solution, a metal annular ring, formed of a radial annular wall comprising a single radial slot, is arranged downstream of the inter-blade cavities. The outer annular periphery of the ring is inserted into a groove extending on the inner faces of the platforms, and its inner annular periphery is held tight against the teeth of the disk and the blade roots by a downstream element such as a labyrinth ring. The ring, when only split, has the advantage of having virtually no gas flow gap, once mounted, and thus ensures a good seal. However, in this case, the slot induces an imbalance of the rod which is detrimental to the operation of the assembly. Moreover, in all cases, in rotation, the rod is supported on the platforms by centrifugal effect with a relatively high effort, which risks compromising the integrity of the platforms, or requires overloading. to dimension undesirably the latter. In addition, when the blades are made of Ceramic Matrix Composite (in the abbreviated C.M.C.), the platforms also in C.M.C. are even less able to support the weight of the rotating ring, the density ratio between a metallic material and a C.M.C. being between three and four. In addition, since the expansion ratio in temperature increase is between two and three, the differential expansion in operation between the rod on one side, and the blades and the disk on the other hand, may increase the stress. generated on the platforms, or to let appear games allowing the flow of gas veins at the radial ends of the rod. The present invention provides a simple, effective and economical solution to the problem of sealing the inter-blade cavities, while overcoming the disadvantages associated with the solutions of the prior art.
    [0003] To this end, it proposes a rotary assembly for a turbomachine, comprising: - a disc having an outer periphery having an alternation of cells and teeth, - blades extending radially from the disk and whose feet are engaged axially and retained radially in the cavities of the disk, platforms extending circumferentially from the blades and which are arranged circumferentially end to end, with respect to one another, upstream and / or downstream axial sealing means an annular zone extending radially between the platforms and the disc, characterized in that said sealing means comprise radially an inner annular portion and an outer annular portion structurally distinct from each other, the portion outer annulus being elastically constrained radially inwardly by the inner annular portion. Thanks to the invention, during the rotation of the assembly, the platforms generally no longer support any load from the rotating sealing means, because the sealing means are radially dissociated into two parts, the internal part constraining the outer part inward and thus preventing it from leaning against the platforms of the blades, despite the centrifugal effects and expansions. It is thus open more freedom of design at the dawn level, such as a C.M.C. design, and it is more generally allowed to reduce the fatigue of the platforms. In addition, the realization of this constraint between the inner part and the outer part involves a tight fitting or fit between these two parts, which allows to ensure a good seal between the inner part and the outer part regardless of the conditions of operation. It is therefore permissible to maintain an axial seal of the annular zone extending radially from the platforms to the disk, which comprises the inter-blade cavities, this sealing being equivalent to that permitted by sealing means formed by a single annular element. Preferably, the sealing means of the invention are formed downstream from said annular zone in order to allow pressurization of the inter-blade cavities to a value substantially identical to that of the vein gases, which limits the effect of suction in these cavities. According to another characteristic of the invention, the outer annular portion of the sealing means is deformed elastically radially inwards by the inner annular portion. Advantageously, the inner portion is itself deformed elastically radially outwardly by the outer annular portion. This embodiment ensures a relative radial adjustment between the inner portion and the outer portion of the sealing means. The two radially offset parts, one with respect to the other, cooperate with one another and deform elastically radially mutually to a radial equilibrium position where the elastic return forces compensate each other, which position may be predetermined. This assembly constantly prestressed by the elastic restoring forces makes it possible to ensure that the fitted and tight contact is kept between the inner part and the outer part of the sealing means whatever the operating conditions. Advantageously, the inner annular portion and the outer annular portion of the sealing means are formed respectively of an inner split ring and an outer split ring, the respective slots of the rings being diametrically opposed.
    [0004] Thus, two slots oppose and equilibrate in the sealing means, which makes it possible to avoid the appearance of unbalance in operation, unlike the prior art which proposes only one ring and therefore only one slot.
    [0005] Preferably, the slot of the outer split ring is inclined with respect to a radius of the ring, so that the outer split ring has a point opposite the outer end of the slot, this point being bent axially to form a circumferential support against a stop formed on one of the platforms.
    [0006] Thus, it is easy to provide rotational locking between the outer split ring and the rest of the rotating assembly. According to another characteristic, rotational locking means are formed between the inner annular portion and the outer annular portion of the sealing means.
    [0007] This ensures that the two slots described above remain diametrically opposed regardless of the operating conditions. According to another feature, the outer portion of the sealing means comprises an outer end engaged in a radial annular groove formed on the inner faces of the platforms. This groove makes it possible to provide the outer part of the sealing means with axial support against the platforms, in order to ensure a good seal between the platforms and the outer part of the sealing means.
    [0008] The inner part of the sealing means is held axially against the disk by an annular arm of a flange mounted downstream or upstream of the disk. This flange is for example a sealing ring comprising annular wipers intended to cooperate sealingly with an external stator element.
    [0009] Preferably, an axial annular flange formed at the outer end of the inner portion of the sealing means is hooked to an axial annular flange formed at the inner end of the outer portion of the sealing means. In particular, these flanges are cylindrical. The annular rim of the inner part will therefore be engaged outside the rim of the outer part. The elastic recesses tend to radially spread the inner and outer parts, which creates a tight support between the two edges. The support is carried out over the entire circumference of the flanges, which ensures the seal between the inner portion and the outer portion of the sealing means. According to a particular embodiment of the invention, the rim of the outer split ring comprises two cutouts forming a tab, which is folded and arranged in the slot of the inner split ring. This tab ensures the anti-rotation between the two rings. Equivalently, we can form the tab on the inner split ring, and arrange it in the slot of the outer split ring. In a particular embodiment, the sealing means are formed radially outside the bottom of the cells. Indeed, it is important that, despite the mounting of the sealing means according to the invention, a cooling air can flow freely axially through the bottoms of the cells, to ensure the cooling of the disk. This is essentially valid in the first stages of the turbine, in which the vein temperature is very high. In a preferred embodiment of the invention, the blades are ceramic matrix composite. As explained above, the invention allows the use of such a material at the blades without risk of damage to the platforms. The invention also relates to a turbomachine turbine comprising a rotary assembly as described in the present patent application. The invention finally relates to a turbomachine, such as a turbojet engine or a turboprop engine, comprising a rotary assembly as described in the present patent application. Other advantages and characteristics of the invention will appear on reading the following description given by way of nonlimiting example and with reference to the appended drawings in which: FIG. 1 is a partial diagrammatic view in axial section of a turbine low-pressure turbomachine according to the prior art; Figure 2 is a partial schematic view in axial section of a rotary stage of the turbine according to the prior art; Figure 3 is a schematic axial sectional view of a rotary assembly according to the invention; Figure 4 is a view showing a method adapted to obtain the rotating assembly shown in Figure 3; FIG. 5 is a perspective view of one embodiment of the invention, in which rotational locking means are formed between the means for sealing the inter-blade cavities, and the platforms of the blades; Figure 6 is a schematic view showing rotation locking means between the inner portion and the outer portion of the sealing means according to the invention.
    [0010] Reference is first made to FIG. 1, which shows a low-pressure turbine 10 according to the prior art, arranged downstream of a high-pressure turbine 12. The low-pressure turbine 10 comprises an axial alternation of stages of annular rows. fixed vanes 18, called distributors, and stage of rotating disks 16 having at their peripheries a plurality of vanes 14, these stages being arranged around an axis X of the turbomachine. In this document, as in the technical field concerned, the terms upstream and downstream AV AV are defined so that the upstream is located axially on the side from which the flow of general flow of the turbine engine, and the downstream is located axially on the side towards which this same flow flows.
    [0011] Each disc 16 comprises at its outer periphery teeth (the top of which is referenced 20) arranged alternately with cavities (whose bottom is referenced 22) in which are axially engaged and retained radially blade roots (whose end internal is referenced 24), these vanes 14 extending radially from the cells 22 in an annular flow stream 26 of a hot gas flow from an upstream combustion chamber (not shown). More particularly, each blade comprises radially from the outside towards the inside a blade 28, a platform 30 extending substantially perpendicular to the axis of elongation of the blade 14, and a stag 32 connecting the platform at the blade root 24. The blade roots 24 have a shape for example dovetail or the like to ensure their radial retention in the cells 22. The platforms 30 of the blades are arranged circumferentially end to end so as to together define the ideal internal limit of the flow flow of the hot gases flowing in the turbine. According to this arrangement, spaces are formed between two circumferentially adjacent stilts 32 in the annular zone extending radially from the platforms 30 to the disk 16, and are called inter-stilt or inter-blade cavities 34. so-called cell bottom recesses 36 are also formed by radial spaces separating the blade roots 24 of the bottoms 22 of the cells. Walls 38, 40 extend radially inwardly from upstream and downstream of the platforms to the feet 24 of the blades and form axial sealing means of the annular zone extending radially from the platforms to the disk 16, and thus inter-blade cavities 34, ensuring their closure. This axial tightness of the inter-blade cavities 34 is important because if part of the vein gas flows through these cavities, it does not participate in the rotational drive of the blades 14 and directly heats the teeth 20 of the disc forming the bottom of the inter-blade cavities 34, which leads to an increase in the temperature of the disks 16 which can damage them and reduce their service life. The upstream radial wall 38 of the platform is connected to a spoiler 42 extending upstream and the downstream radial wall 40 is connected to a spoiler 44 extending downstream. The spoilers 42, 44 extend axially between the consecutive stages of the turbine in order to partially preserve the structural integrity of the stream 26 between each turbine stage, which limits the circulation of hot gases radially inwardly of the turbine. the turbine. The discs are secured to each other by bolting, at 46, annular flanges 48, 50 extending axially towards each other from each disc. A labyrinth ring 52 is also positioned axially between each pair of adjacent disks 16 and includes upstream and downstream annular arms 54, 56 extending axially to these disks. The fixing flanges 48, 50 between the discs are thus protected from the vein gases by the arms 54, 56 of the labyrinth ring 52. The labyrinth ring 52 further comprises an internal radial annular wall 58 for fixing to the bolting 46 flanges 48, 50 disks, and cooperates by external annular wipers 60 with the inner ends of the vanes 18 of the distributors, to limit the flow of vein gas internally with respect to these vanes 18. In order to ensure the proper operation of the turbomachine, a cooling air A is taken, in a low-pressure or high-pressure compressor, for example, and conveyed to the inner part of the turbine to the cell bottom cavities 36 to ensure the cooling of the disc 16 and protect the latter from heating caused by the hot gases of the stream of vein 26. In order to allow the circulation of cooling air A downstream cavities 36 cell bottom, the latter The ends open downstream internally relative to the arm 54 of the labyrinth ring 52 in axial support on the disk 16. This configuration allows the cooling air A to circulate further downstream radially between the labyrinth ring 52 and the flanges 48. , 50 of fixing between the disks 16, to also ensure cooling. In operation, the hot gases circulating in the vein 26 can circulate through gaps (not shown) formed between the circumferential vis-à-vis edges of the upstream and downstream radial walls 38, 40 connected to the platforms 30 and covering axially the inter-blade cavities 34. The number of interstices 62 is relatively high since it depends directly on the number of platforms forming the internal limit of the vein, which induces a considerable total leakage through the internal cavities. blades, which impairs the performance of the turbine. Moreover, with the industrial tools currently available, the manufacture of the assembly formed by the platform 30 and the radial walls 38 and 40 is not possible in one and the same piece of Ceramic Matrix Composite (CMC). However, the recent developments lead preferably to using blades made of CMC material, because the use of this type of material in particular reduces the weight of the blades and increase their resistance to high temperatures. In another type of embodiment of the prior art, shown in FIG. 2, the walls 40 of FIG. 1, which seal downstream of the inter-blade cavities, are replaced by a split ring 41 which includes a radial wall extending radially between the blade roots 24 and the platforms 30 of the blades 14. More particularly the outer end or periphery of the split ring 41 is engaged in a radial annular groove 31 formed on the inner faces platforms 30.
    [0012] The split ring 41 is further axially pressed against the disk 16 and the blades 14 by the arm 54 of the downstream labyrinth ring 52. In order to mount the split ring 41 in the groove 31, the split ring 41 is constrained. in such a way as to close the slot by elastic deformation, which consequently reduces the radius of the split ring 41. The split ring 41 is then arranged in relation to the groove 31 and inside it, before releasing the stress applied to the ring 41 so that it regains its original diameter and engages in the groove 31. In this embodiment, in operation and thus in rotation, by centrifugal effect, the split ring 41 has tendency to open and therefore to press against the bottom of the groove 31, which generates undesirable stresses on the platforms 30. In addition, when the blades 14 are made of CMC, the relative dilations between the ring split 41 and the blades 14 accentuate these constraints. Finally, the slot of the split ring 41 interrupts the circumferential symmetry of the rotating assembly, which creates an imbalance, or unbalance, in rotation, and adversely affects the performance of the assembly. In order to be able to make the vanes 14 in CMC, to limit the leaks within the inter-vane cavities 34, or to avoid the aforementioned unbalance, it is therefore necessary to design new axial sealing means for the annular zone s'. extending radially from the platforms 30 to the disc 16, these sealing means not having to generate too much weight supported by the rotating platforms, due to the centrifugal effects. The proposed solution, according to the characteristics mentioned above in the present application, is represented in FIGS. 3 to 6. In the embodiment shown, the sealing means according to the invention are formed downstream of the zone. annular extending radially from the platforms 30 to the disk 16, and comprising the inter-blade cavities 34. Equivalently and symmetrically, it is possible to place these sealing means upstream of this zone . Thus, with reference to FIG. 3, the platforms 30 are connected at their upstream ends to walls 38 extending radially to the teeth 20 of the disks, and each comprising, in the vicinity of their internal ends, spoilers 42. extending upstream. The platforms 30 are each further connected at their downstream ends to a spoiler 44 extending downstream.
    [0013] The downstream sealing means are formed of two slotted rings 64, 70, respectively internal and external. The internal split ring 64 is formed of a radial wall extending radially between an area of the disc located at the level of the blade roots 20, and approximately the middle of the stilts 32. The internal split ring 64 is held in abutment against the downstream ends of the stilts 32 and the teeth 20 of the disk by an upstream annular arm 54 of a labyrinth ring 52 downstream. The cooling air A coming from the cavities of cell bottom 36 can escape downstream by circulating inside the split ring 64 and the upstream annular arm 54 of the labyrinth ring 52 downstream, for axially along the downstream flange 48 of the disc. The internal split ring 64 comprises at its ends or inner and outer peripheries respectively two cylindrical annular rims 66, 68 downstream.
    [0014] The outer split ring 70 is formed of a radial wall and extends radially between the outer end of the internal split ring 64, and the groove 31 formed in the platforms 30. The outer split ring 70 comprises at its end or inner periphery a cylindrical annular flange 72 upstream, engaged radially inside and facing the outer flange 68 of the inner split ring 64. The outer split ring 70 is further in axial tight fit between, on the one hand, the downstream wall of the groove 31 bearing against its outer periphery, and on the other hand the internal split ring 64 bearing against its internal rim 72. In this arrangement, the internal split ring 64 is in a state of elastic deformation obtained by widening its slot, so that the split ring 64 has a radius greater than its rest state. An elastic return tends to close the ring 64 inwards. Equivalently, the outer split ring 70 is in a state of elastic deformation obtained by tightening its slot, so that the split ring 70 has a smaller radius than its rest state. An elastic return tends to open the ring 70 to the outside.
    [0015] The two split rings 64, 70 have been dimensioned and adjusted so that the aforementioned elastic return forces radially bear the flanges 68 and 72 over all their circumferences. This support prevents the rings 64, 70 from returning to their respective rest states, which makes it possible to maintain the elastic return forces in a position of equilibrium between the two rings, and thus a tight support between the flanges 68 and 72. tight support ensures tightness between the two rings. The assembly is also adjusted so that in this equilibrium position, the outer periphery of the outer split ring 70 is not in contact with the bottom of the groove 31, although the elastic return force urges it there. Thus, in this equilibrium position, no stress is applied on the platforms 30 of the blades 14, and even if a contact was created in operation due to dilations or centrifugal forces, these constraints would be greatly attenuated by the elastic return inward caused by the internal split ring 64. In order to eliminate any possibility of disengagement of the external split ring 70 from the groove 31, the insertion distance of the ring 70 into the groove 31 is formed in equilibrium position greater than the radial distance separating the internal rim. 72 and the annular arm 54 of the labyrinth ring 52. Thus, the ring 70 will radially abut against the arm 54 before being able to disengage from the groove 31. Preferably, at the equilibrium state, it forms also the radial distance separating the inner flange 66 from the inner split ring 64 and the annular arm 54 of the labyrinth ring 52 smaller than the radial distance separating the outer end of the outer split ring 70 and the bottom of the 31. Thus, if the assembly consisting of the two rings 64, 70 were to deviate and expand in operation, the flange 66 would abut against the arm 54 before the outer ring 70 bears against the bottom of the throat 31, and applies constraints to platforms 30.
    [0016] Although Figure 3 does not allow to represent it, the respective slots of the slotted rings 64, 70 are diametrically opposed, which avoids the creation of unbalance in operation. Figure 4 provides a better understanding of how the two split rings 64, 70 are mounted and arranged relative to each other. It can be seen that, in a first step, a mounting tool 74 is used which makes it possible to keep the internal split ring 64 in an open state, that is to say with a radius greater than its resting state by elastic deformation opening the slot of the ring, and axially against the downstream face of the disc 16 and the blade roots 20. At this stage, the external split ring 70 is put into a closed state, that is to say with a radius smaller than its state of rest thanks to an elastic deformation closing the slot of the ring. In this state, it is permitted to position the outer split ring 70 facing the groove 31, and so that the cylindrical flange 72 fits within the cylindrical flange 68 of the ring 64, which is in an open state. Then release the outer ring 70 so that the latter tends to its state of rest more open. The ring 70 then abuts against the bottom of the groove 31.
    [0017] Then, the mounting tool 74 is withdrawn. The inner ring 64 is closed by elastic return until the rim 68 abuts against the flange 72. The inner ring 64 then continues to close while driving with it the outer ring 70, until the elastic return forces of the respective rings 64, 70 compensate each other. The equilibrium position shown in FIG. 3 is then obtained. FIG. 5 represents an anti-rotational arrangement between the outer split ring 70 and the remainder of the rotating assembly formed by disc 16 and vanes 14. that the slot 76 of the ring 70 is formed inclined with respect to a radius of this ring. In this way, the ring 70 comprises a point 78 formed circumferentially facing the outer end of the slot 76. This tip 78 is bent or folded axially downstream so as to form a circumferential stop, which cooperates with a protrusion 80 formed on the inner face of a platform 30, downstream of the groove 31. Figure 6 shows an anti-rotational arrangement between the outer split ring 70 and the inner split ring 64. The slot 82 of the inner ring 64 is enlarged at its outer periphery which also includes the flange 68. Two radial cuts 84 are formed close to each other in the inner periphery of the outer ring 70, which includes also flange 72. A tab 86 is obtained between these two cuts 84, which is folded downstream and outside. This lug is inserted into the enlarged portion 88 above the slot 82 of the inner ring 64. This lug 86 is thus retained between the circumferential edges of this enlarged portion 88 of the slot 82, which secures the rings. slits 64 and 70 in rotation. Preferably, a circumferential clearance is maintained between the tab 86 and the circumferential edges of the widened portion 88 of the slot 82, equal to at least the width of the slot 82. Thus, the slot 82 can close completely if necessary, without be constrained against the tab 86, in mounting or operating conditions.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Rotary assembly for a turbomachine, comprising: - a disc (16) having an outer periphery having an alternation of cells (22) and teeth (20), - vanes (14) extending radially from the disc (16) and whose feet (24) are engaged axially and retained radially in the cavities (22) of the disc, - platforms (30) extending circumferentially from the blades (14) and which are arranged circumferentially end to end, some vis-à-vis others, - axial sealing means upstream and / or downstream of an annular zone extending radially between the platforms (30) and the disc (16), characterized in that said means sealing members comprise radially an inner annular portion (64) and an outer annular portion (70) structurally distinct from each other, the outer annular portion being elastically constrained radially inwardly by the inner annular portion.
    [0002]
    2. Rotary assembly according to claim 1, characterized in that the outer annular portion (70) of the sealing means is deformed elastically radially inwardly by the inner annular portion (64), which is itself elastically deformed radially. outwardly by the outer annular portion (70).
    [0003]
    3. Rotary assembly according to one of claims 1 or 2, characterized in that the inner annular portion (64) and the outer annular portion (70) of the sealing means are respectively formed of an inner split ring (64) and an outer split ring (70), the respective slots (82, 76) of the rings being diametrically opposed.
    [0004]
    4. Rotary assembly according to claim 3, characterized in that the slot (76) of the outer split ring (70) is inclined relative to unrayon of the same ring (70), so that the split ring outer member (70) has a tip (78) facing the outer end of the slot (76), said tip being axially folded to form a circumferential bearing against a stop (80) formed on one of the platforms (30) .
    [0005]
    Rotary assembly according to one of the preceding claims, characterized in that rotational locking means (86, 88) are formed between the inner annular portion (64) and the outer annular portion (70) of the sealing means. .
    [0006]
    6. Rotary assembly according to one of the preceding claims, characterized in that the outer portion (70) of the sealing means comprises an outer end engaged in a groove (31) radial annular formed on the inner faces of the platforms ( 30).
    [0007]
    7. Rotary assembly according to one of the preceding claims, characterized in that the inner portion (64) of the sealing means is held axially against the disc (16) by an annular arm (54) of a flange mounted to the downstream or upstream of the disk.
    [0008]
    8. Rotary assembly according to one of the preceding claims, characterized in that an axial annular flange (68) formed at the outer end of the inner portion (64) of the sealing means is attached to an axial annular flange ( 72) formed at the inner end of the outer portion (70) of the sealing means.
    [0009]
    9. Rotary assembly according to claim 8, when dependent on claim 3, characterized in that the flange (72) of the outer split ring (70) comprises two cutouts (84) forming a tab (86), which is folded and arranged in the slot (82) of the inner split ring (64).
    [0010]
    10. Rotary assembly according to one of the preceding claims, characterized in that the blades (14) are made of ceramic matrix composite.
    [0011]
    Turbomachine turbine, characterized in that it comprises a rotary assembly according to one of the preceding claims.
    [0012]
    Turbomachine, such as a turbojet engine or a turboprop engine, characterized in that it comprises a rotary assembly according to one of the preceding claims.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3020408B1|2018-04-06|
    US9784114B2|2017-10-10|
    GB201506998D0|2015-06-10|
    US20150308279A1|2015-10-29|
    GB2527192B|2020-05-20|
    GB2527192A|2015-12-16|
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    法律状态:
    2015-04-13| PLFP| Fee payment|Year of fee payment: 2 |
    2015-10-30| PLSC| Publication of the preliminary search report|Effective date: 20151030 |
    2016-04-12| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-07| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 6 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453717|2014-04-24|
    FR1453717A|FR3020408B1|2014-04-24|2014-04-24|ROTARY ASSEMBLY FOR TURBOMACHINE|FR1453717A| FR3020408B1|2014-04-24|2014-04-24|ROTARY ASSEMBLY FOR TURBOMACHINE|
    US14/694,424| US9784114B2|2014-04-24|2015-04-23|Rotating assembly for a turbomachine|
    GB1506998.2A| GB2527192B|2014-04-24|2015-04-24|Rotating assembly for a turbomachine|
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