• 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:
    Hub (30) for a bladed wheel having a low hub ratio, which can be made of a composite material from a three-dimensionally woven fiber preform, comprising a lower bottom wall (32), a top vein wall (31), two lateral walls (33) extending transversely between the bottom wall (32) and the vein wall (31), wherein the side walls (33) extend longitudinally beyond the upstream end of the wall background (32). The platform (30) further includes a bracket (34) folded from the upstream end of the bottom wall (32).
    公开号:FR3029563A1
    申请号:FR1462037
    申请日:2014-12-08
    公开日:2016-06-10
    发明作者:Roland Mortier；Sylvain Bourseaulx；Antoine Masson；Anne-Laure Ravier；Noemie Steenbakker
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a fibrous preform for manufacturing light platforms and having a low hub ratio. The present disclosure also relates to such a platform, as well as a bladed wheel, a blower for example, and a turbomachine comprising such platforms. Such platforms can in particular be used in the aeronautical field, in turbojet engines or helicopter turbine engines to name just these examples.
    [0002] STATE OF THE PRIOR ART In an airplane turbojet, the platforms of the various bladed wheels, and in particular of the blower, must perform many functions.
    [0003] Mainly, they must define the air flow vein by minimizing the aerodynamic disturbances at their bladed wheel as well as at the level of other downstream bladed stages: in particular, they must define coherent interfaces to borders with the other floors.
    [0004] They must also be able to withstand significant effort without experiencing significant deformation and without detaching themselves from the disc that carries them to ensure the safety and availability of the engine for commercial use. In order to satisfy these different requirements, certain configurations have been proposed in which the platforms have a first part, which makes it possible to define the flow vein of the air and to ensure the retention of the platform when the engine is rotating, and a second part, to limit the deformations of the first part under the effects of centrifugal forces and to maintain the platform in position when the engine is stopped. In some of these configurations, the platforms take the form of a box with a portion of two-dimensional vein retained upstream and downstream and carried by a U-shaped support portion. However, such a box configuration is bulky, which poses problems. problems of mass and integration, leading in particular to a high hub ratio, the hub ratio being the ratio of the radius taken between the axis of rotation and the point of the leading edge of the blade 3029563 2 flush with the surface of the platform, on the radius between the axis of rotation and the point of the outermost leading edge. In other configurations, the vein portion is both retained upstream and downstream and supported by two arms provided at their distal ends with hooks engaging with hooks carried by the wheel disc. Here again, the complexity of such fixing poses mass and integration problems, also leading to a high hub ratio. There is therefore a real need for a fiber preform, a platform, a bladed wheel and a turbomachine which are lacking, at least in part, the drawbacks inherent in the aforementioned known configurations. PRESENTATION OF THE INVENTION The present disclosure relates to a fibrous preform for a bladed wheel platform comprising a first fibrous structure having a bottom portion, and two lateral portions extending transversely from the bottom portion; the lateral portions 20 extend longitudinally beyond the upstream end of the bottom portion, and the first fibrous structure further has a fastening tab folded from the upstream end of the bottom portion. In this disclosure, the terms "longitudinal", "transversal", "inferior", "superior" and their derivatives are defined relative to the principal direction of the platform in question; the terms "axial", "radial", "tangential", "interior", "outside" and their derivatives are themselves defined with respect to the main axis of the turbomachine; "axial plane" means a plane passing through the main axis of the turbomachine and "radial plane" a plane perpendicular to this main axis; finally, the terms "upstream" and "downstream" are defined with respect to the flow of air in the turbomachine. Thanks to such a preform, it is possible to make a composite composite platform for a bladed wheel that is solid, lightweight and compact.
    [0005] Indeed, the use of such a composite material allows a significant weight gain compared to conventional platforms made of metal. Such a mass gain therefore offers increased performance and reduced fuel consumption.
    [0006] This configuration including lateral walls, issuing from the lateral portions of the preform, extending transversely from a bottom wall, issuing from the bottom portion of the preform, also ensures good mechanical resistance to the platform, in particular screws. against centrifugal forces 5 acting radially and therefore in the direction of the side walls. This reduces the deformation of the platform in operation and therefore the disturbances of the aerodynamic vein. In addition, thanks to this portion of bottom whose length is reduced relative to the lateral portions and which does not extend to the upstream end of the preform, the size of the platform is reduced at its level. upstream part, which gives a greater freedom of design of the platform in this zone. Thus, because of this configuration, it is possible to bring the upstream end of a vein portion of the platform, which is the part in contact with the air stream, 15 of the tooth of the disc which carries them, thus revealing a greater blade length and thereby reducing the hub ratio, which increases the performance of the bladed wheel. This preform also has the advantage of providing a fibrous structure including a fastening tongue directly integral with the bottom wall: this makes it possible to obtain a fastening tab for the platform enabling it to be hooked on the tooth of the disc. . This fixing lug is thus integrally formed with the latter, further reinforcing its mechanical strength. This bracket also allows the platforms to be maintained when the turbomachine 25 is stopped and the upstream ferrule is disassembled. In some embodiments, the first fibrous structure is comprised of a single, one-piece, three-dimensionally woven web. The bottom portion, the lateral portions and the fastening tongue are thus easily and in a single weaving step.
    [0007] In some embodiments, the yarns used for weaving the preform are carbon fibers. However, it can be any other type of yarn, for example fiberglass or Kevlar. In some embodiments, the weave used for three-dimensional weaving of the preform may be of the 3D interlock type. However, the weaving of the outer surfaces of the preform can be essentially two-dimensional, of the satin type for example.
    [0008] In some embodiments, the first fiber structure has a constant number of wire layers throughout its surface, thereby facilitating the design and construction of the weave. The first fibrous structure thus has a constant thickness.
    [0009] In some embodiments, the weave is continuous at the juncture between the bottom portion and the attachment tab. Flat, the fastening tongue is an extension of the bottom portion. More precisely, the fixing tongue may be a residual part resulting from the cutting of an initially longer base portion, the upstream portion of this initial base portion being able, in fact, to be partly removed by cutting and, for another, be folded to form the fastening tab. In some embodiments, the weave is continuous at the junctions between the bottom portion and each of the side portions. In flat, the lateral portions thus constitute lateral extensions of the bottom portion. In some embodiments, the height of the lateral portions of the first fibrous structure decreases upstream, the upstream end of said side portions being tapered. This makes it possible to bring the upstream end of the vein portion of the disc's tooth platform closer together, thus revealing a longer blade length and thereby reducing the hub ratio. Preferably, the height of the lateral portions vanishes at the upstream end of the first fibrous structure.
    [0010] In some embodiments, the attachment tab is folded downstream. In this way, the platform is formed with a hook-shaped tab adapted to cooperate with a hook projecting from the top of the teeth of the disc. In some embodiments, the preform further comprises a second fibrous structure having a vein portion and two lateral portions extending transversely from the vein portion. The vein portion makes it possible to form a vein wall of the platform which is the wall directly in contact with the air stream of the turbojet engine.
    [0011] In some embodiments, the second fibrous structure is obtained in one piece by three-dimensional weaving. In some embodiments, each side portion of the second fibrous structure is obtained by deliming with a lateral end portion of the vein portion. Thus, a second Pi-shaped fibrous structure is easily obtained. In some embodiments, the height of the lateral portions of the second fibrous structure decreases upstream with the upstream end of said side portions being tapered. Preferably, the height of the lateral portions vanishes at the upstream end of the second fibrous structure. In some embodiments, the second fibrous structure is interlocked in the first fibrous structure, the side portions of one of the fibrous structures being received between the lateral portions of the other fibrous structures. A well made from two fibrous structures is thus easily obtained, the individual realization of which by three-dimensional weaving is easy. In some embodiments, the side portions of the second fibrous structure are received between the side portions of the first fibrous structure. Of course, the reverse configuration is possible. In other embodiments, the preform comprises a single fibrous structure having a bottom portion, two side portions and a vein portion woven simultaneously in a single step, for example using the method described in the international application. WO 2013/160584, an upstream part of the bottom portion then being cut to form the fastening tongue. The present disclosure also relates to a bladed wheel platform, comprising a lower bottom wall, a top vein wall, two side walls extending transversely between the bottom wall and the vein wall; the side walls extend longitudinally beyond the upstream end of the bottom wall, and the platform further comprises a fastening tab folded from the upstream end of the bottom wall. This configuration including lateral walls extending transversely from the bottom wall provides good mechanical strength to the platform, particularly with respect to the centrifugal forces acting radially and in the direction of the side walls.
    [0012] In addition, thanks to this bottom wall whose length is reduced relative to the side walls and which does not extend to the upstream end of the platform, the size of the platform is reduced at its level. upstream part, which provides greater freedom of 3029563 6 platform design in this area. Thus, because of this configuration, it is possible to bring the upstream end of the vein portion of the disc's tooth platform together, thereby revealing a greater blade length and thus reducing the hub ratio, which increases the performance of the bladed wheel. In some embodiments, the upstream end of the vein wall descends lower than the plane of the bottom wall. The bottom wall can thus rest on an element projecting from the tooth of the disc, for example an assembly hook, without this preventing the upstream end of the vein wall from getting closer to the tooth of the disc to reduce the hub ratio of the bladed wheel. In some embodiments, the vein wall has at its upstream end an upstream assembly portion adapted to cooperate with an upstream assembly member of the turbomachine. This reinforces the hooking of the platform. In some embodiments, the vein wall has at its downstream end a downstream assembly portion adapted to cooperate with a downstream assembly member of the turbomachine. This reinforces the hooking of the platform.
    [0013] In some embodiments, the platform is integrally made of composite material by means of a fibrous preform according to any one of the preceding embodiments, said preform having been shaped in a mold and embedded in a matrix. . The advantages described with reference to the above fibrous preform are thus obtained. In some embodiments, the matrix is of organic type. It may especially be an epoxy resin. In other embodiments, the matrix is of the ceramic type.
    [0014] The present disclosure also relates to a bladed wheel for a turbomachine, comprising a disc, able to be coupled to a shaft of the turbomachine, whose circumference has a succession of grooves and teeth, a plurality of blades mounted in grooves of the disc, and at least one platform according to any one of the preceding embodiments, provided between two blades facing a tooth of the disk, the bracket of the platform cooperating with an assembly member of the tooth.
    [0015] In some embodiments, the bladed wheel is a blower. Such platforms are indeed particularly suitable for this type of bladed wheel provided between an upstream ferrule and a downstream drum whose diameters are very different.
    [0016] The present disclosure also relates to a turbomachine comprising a bladed wheel according to any one of the preceding embodiments. The present disclosure finally relates to a method of manufacturing a bladed wheel platform, comprising the following steps: manufacturing a preform according to one of the embodiments described above, shaping the preform by interlocking the second fibrous structure in the first fibrous structure, molded the preform, co-injection of a matrix into the mold. In some embodiments, the step of manufacturing the preform comprises a step of weaving a first fibrous web, a precursor of the first fibrous structure, and a step of cutting the first fibrous web to reduce the length. from the bottom portion and form the fastening tab. Thus, this cutout easily forms such a bottom portion whose length is less than the lateral portions and such a fastening tongue which remains after this cutting. In some embodiments, the step of cutting the first fibrous web is performed by water jet. Such a water jet cut, which can be automated, is in fact particularly suitable for cutting such fibrous webs. The above-mentioned characteristics and advantages, as well as others, will appear on reading the following detailed description of embodiments of the proposed preform and platform. This detailed description refers to the accompanying drawings.
    [0017] 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 another, elements (or 35 parts of element) identical are identified by the same reference signs. FIG 1 is a schematic sectional plan of a turbomachine according to the invention.
    [0018] FIG. 2 is a sectional view of a fan module. FIG 3 is a front view of a fan disk. FIGS. 4A and 4B are sectional views along planes IVA and IVB, respectively, of FIG.
    [0019] FIG. 5 is a plan view of a first fibrous structure. FIG 6 illustrates the shaping of this first fibrous structure. DETAILED DESCRIPTION OF EMBODIMENT (S) In order to make the invention more concrete, exemplary embodiments of the invention are described in detail hereinafter 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 module 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 blower module 2 is shown in more detail in FIG. 2. It comprises an upstream ferrule 21, a blower disk 22 and a downstream drum 23 also called a "drum booster". The upstream shell 21 has at its downstream end a retaining flange 21a. The downstream drum 23 has meanwhile at its upstream end a retaining flange 23a.
    [0020] As can be seen in FIG. 3, a plurality of grooves 24 are formed in the outer surface of the fan disk 22: these grooves 24 are rectilinear and extend axially from upstream to downstream along the disk 22. are further regularly distributed around the axis A of the disk 22. In this way, each groove 24 defines with its neighbor a tooth 25 which thus extends also axially from upstream to downstream all along the disk 22. The blower module 2 further comprises a plurality of blades 26, each blade 26 having a curvilinear profile being mounted in a respective groove 24 of the blower disk 22. For this purpose, the blade root 26 may have a blade shape. fir or dovetail adapted to the geometry of the grooves 24.
    [0021] The fan module 2 finally comprises a plurality of platforms 30, a platform 30 being provided between each blade 26, therefore facing each tooth 25 of the fan disk 22. The upstream ferrule 21 and the downstream drum 23 are connected to the disc 22, the latter being coupled with the low-pressure shaft of the turbojet engine 1. Thus, during operation of the turbojet, the upstream shell 21, the fan disk 22, the blades 26, and the downstream drum 23 are integrally driven by rotation by the low-pressure turbine 7. The platforms 30, mounted between the upstream shell 21 and the downstream drum 23, are also integrally driven. Each platform 30 essentially takes the form of a box with a vein wall 31, a bottom wall 32 and two side walls 33. The vein wall 31, forming the upper or outer face of the platform 30, extends the ferrule upstream 21 downstream and downstream drum 23 upstream so as to define the flow vein of the air in the blower module 2. The vein portion 31 thus has an inclined profile, the diameter of the drum 23 is greater than that of the upstream ferrule 21. The vein portion 31 further comprises an upstream assembly step 38 at its upstream end and a downstream assembly step 39 at its downstream end. The bottom wall 32 allows the platform to rest on the tooth 22 when the turbojet engine is stopped. According to the invention, the length of the bottom wall 32 is smaller than the length of the vein wall 31 and that of the side walls 33. In particular, the bottom wall 32 ends at its upstream end before the the upstream end of the side walls 33 and before the upstream end of the vein wall 31. As a result, the vein wall 31 can descend downstream upstream, that is to say radially further inwards That the level of the bottom wall 32 is observed in particular in this example that the upstream end of the wall 31 and down to the level of the top of the tooth 25. The platform 30 further comprises a tab of fixing 34 extending from the upstream end of the bottom wall 32 and folded downstream so as to take the form of a hook. In the blower module 2, this lug 34 cooperates with an attachment member 27, taking the form of a complementary hook, protruding from the top of the tooth 25. Said fastening member is not shown at FIG. 3. This fixing lug 34 thus makes it possible to hold the platform 30 against the centrifugal force when the turbojet engine is in operation. It is further noted that the bottom wall 32 rests on the outer surface of this hooking member 27 of the tooth 25 rather than on the outer surface of the tooth 25. This hooking member 27 also allows the maintenance 5 of the platform when the turbomachine is stopped and that the upstream ferrule 21 is disassembled. The side walls 33 connect the vein walls 31 and bottom 32 and act as a stiffener so as to ensure the mechanical strength of the assembly, particularly with respect to the centrifugal forces, and therefore to limit its deformation in operation. Thus, as it clearly visible in FIG. 2, while progressing from downstream to upstream, the bottom wall 32 of the box stops and then the side walls 33, tapering from downstream, stop at turn when the vein wall 31, which descends continuously from the downstream, reaches the plane 15 of the bottom wall 32: only then the vein wall 31 remains at the upstream end of the platform 30 and joins the upstream ferrule 21 at the top of the disc tooth 22. As is best seen in FIGS. 4A and 4B, the platform is made of composite material from two fibrous structures 40 and 50 nested one inside the other and co-injected. The first fibrous structure 40 essentially takes the form of a U. It thus has a bottom portion 42 and two lateral portions 43 extending perpendicularly from the lateral ends of the bottom portion 42. However, it is noted that the lateral portions 43 25 extend upstream beyond the upstream end of the bottom portion 42; their height is reduced further towards the upstream. The second fibrous structure 50 is essentially in the form of a Pi. It thus has a vein portion 51 and two lateral portions 53 extending perpendicularly from the vein portion 51. The height of these lateral portions 53 is also reduces upstream; in addition, it is noted that the vein portion 51 extends upstream beyond the upstream end of the lateral portions 53. It is thus found that the second fibrous structure 50 is engaged in the first fibrous structure 40 by engaging its lateral portions 53 between the lateral portions 43 of the first fibrous structure 40, the gaps between the lateral portions 43 and 53 of the fibrous structures 40 and 50 being adjusted so that each lateral portion 43 of the one 40 is at least 30 cm. a lateral portion 53 of the other 50 so as to form for the platform 30 side walls 33 monoblocs. The weaving and shaping of the first fibrous structure 40 will now be described in detail using FIGS. 5 and 6.
    [0022] In this example, the fibrous structures 40 and 50 are woven three-dimensionally in carbon fibers in 3D interlock weave. Only the surfaces of the fibrous structures 40 and 50 are woven two-dimensionally in a satin-like weave. The weaving of the first fibrous structure 40 comprises the flat weaving of a precursor fibrous web 40 'composed of a constant number of layers of threads. This sheet 40 'comprises a central strip 42' and two lateral wings 43 'delimited by the dotted lines 49 representing fold lines. This ply 40 'is then subjected to an automated cutting by water jet 15 to remove the upstream portion 48' of the central strip 42 'delimited by the broken line 48 representing the cutting line. At the end of this cutting, the part of the central strip 42 'remaining corresponds to the bottom portion 42 and to the tongue 44 of the first fibrous structure 40.
    [0023] The fibrous structure 40 thus obtained is then moistened to soften it and allow easier decadding of the fibers. It is then shaped using the blocks 61, 62 and 63 illustrated in FIG. 6. The fibrous structure 40 is positioned flat on the first block 61 and the tab 44 is folded against the step 61a of the first block 61. The position and the folded form of the tongue 44 are maintained with the aid of the second block 62. Then the lateral portions 43 are folded against the third block 63. The fibrous structure 40 is then dried so that the latter stiffens, thus blocking the geometry imposed during formatting.
    [0024] The second fibrous structure 50 is also obtained by three-dimensional weaving in which each lateral portion 53 is loosely woven with a lateral end section 51a of the vein portion 51 so as to obtain the Pi shape of this second portion. fibrous structure 50. Such a branch can also be obtained by crossing layers. Such debonding and cross-layer techniques are now well known in the field of three-dimensional weaving.
    [0025] The second fibrous structure 50 thus woven is then moistened and then shaped by folding its lateral portions 53 perpendicular to its vein portion 51. The fibrous structure 50 is then dried so that the latter stiffens, thus blocking 5 the geometry imposed during the formatting. The two fibrous structures 40 and 50 thus stiffened are finally nested one inside the other and arranged in an injection mold, to the dimensions of the desired final platform 30, in which a matrix is injected, here an epoxy resin. Such co-injection may for example be carried out by the known method RTM ("resin transfer molding"). Such co-injection in which a matrix is injected and simultaneously impregnates two fibrous structures allows to join the two fibrous structures to obtain a final piece monobloc. It may be noted on this occasion that the opening left in the lower face of the platform between the bottom wall 32 and the vein wall 31 facilitates the design of the core of this mold by allowing the removal of a part of this core. by this opening. At the end of this step, a platform 30 made of a composite material composed of two fibrous structures 40, 50 woven into carbon fibers and embedded in an epoxy matrix is thus obtained. Machining steps may possibly complete this process to finalize the platform 30. When mounting the platform, the upstream collar 21 is absent: it simultaneously engages the downstream step 39 under the flange 23a of the downstream drum 23 and the leg of fixing 34 in the hook 27 of the tooth 25. The upstream ferrule 21 is then attached so that its flange 21a engages over the upstream step 38 of the platform: a clearance is provided between these two elements so to facilitate assembly; this game is small enough that the centrifugal force closes it during the operation of the turbojet engine. 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 particular, throughout the present disclosure, it has been assumed that the diameter of the module to which the bladed wheel belongs increases from upstream to downstream: this is indeed the case of the blower module 3029563 13 which has difference in diameter between its upstream and downstream that the platforms must compensate. However, it goes without saying that the present invention applies equally to modules whose diameter decreases between upstream and downstream: in such a case, it suffices to reverse the upstream and downstream in the whole of the description above. 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. 15
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Fibrous preform for a bladed wheel platform comprising a first fibrous structure (40) having a bottom portion (42), and two lateral portions (43) extending transversely from the bottom portion (42), characterized in that the portions lateral portions (43) extend longitudinally beyond the upstream end of the bottom portion (42), and in that the first fibrous structure (40) further has a fastening tab (44) folded from the upstream end of the bottom portion (42).
    [0002]
    2. Preform according to claim 1, wherein the first fibrous structure (40) consists of a single web woven three-dimensionally in one piece.
    [0003]
    3. Preform according to claim 1 or 2, wherein the height of the lateral portions (43) of the first fibrous structure (40) decreases towards the upstream, the upstream end of said side portions (43) being tapered.
    [0004]
    4. Preform according to any one of claims 1 to 3, further comprising a second fibrous structure (50) having a vein portion (51) and two lateral portions (53) extending transversely from the vein portion (51). ). 30
    [0005]
    5. Preform according to claim 4, wherein the second fibrous structure (50) is nested in the first fibrous structure (40), the lateral portions (53) of one of the fibrous structures (50) being received between the lateral portions. (43) on the other fibrous structures (40).
    [0006]
    6. Bladed wheel platform, comprising a bottom bottom wall (32), a top vein wall (31), two side walls (33) extending transversely between the bottom wall (32) and the wall vein (31), characterized in that the side walls (33) extend longitudinally beyond the upstream end of the bottom wall (32), and in that the platform (30) further comprises a bracket (34) folded from the upstream end of the bottom wall (32). 10
    [0007]
    7. Platform according to claim 6, wherein the upstream end of the vein wall (31) goes lower than the plane of the bottom wall (32). 15
    [0008]
    8. Platform according to claim 6 or 7, made integrally of composite material by means of a fiber preform according to any one of claims 1 to 5, said preform having been shaped in a mold and embedded in a matrix preferably of organic type.
    [0009]
    9. Turbomachine bladed wheel, comprising a disc (22), adapted to be coupled to a shaft of the turbomachine, whose circumference has a succession of grooves (24) and teeth (25), a plurality of blades (26) mounted in grooves (24) of the disc (22), and at least one platform (30) according to any one of claims 6 to 8, provided between two blades (26) opposite a tooth (25) of the disc (22), the bracket (34) of the platform (30) 30 cooperating with an assembly member (27) of the tooth (25).
    [0010]
    10. Turbomachine comprising a bladed wheel (2) according to claim 9. 35
    [0011]
    11. A method of manufacturing a bladed wheel platform, comprising the following steps: manufacturing a preform (40, 50) according to claim 4 or 5, shaping the preform (40, 50) by fitting together the second fibrous structure (50) in the first fibrous structure (40), molded the preform (40, 50), co-injection of a matrix into the mold.
    [0012]
    The method of claim 11, wherein the step of manufacturing the preform comprises a step of weaving a first fibrous web (40 ') precursor of the first fibrous structure (40), and a cutting step of said first fibrous web (40 ') to reduce the length of the bottom portion (42) and form the fastening tab (44).
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    公开号 | 公开日
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    GB201718600D0|2017-11-10|2017-12-27|Rolls Royce Plc|Annulus filler|
    US11092021B2|2019-05-06|2021-08-17|Raytheon Technologies Corporation|Fan platform with core and skin|
    FR3109793A1|2020-05-04|2021-11-05|Safran Aircraft Engines|PLATFORM FOR A BLOWER ROTOR OF AN AIRCRAFT TURBOMACHINE|
    法律状态:
    2015-12-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-10| PLSC| Publication of the preliminary search report|Effective date: 20160610 |
    2016-12-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462037|2014-12-08|
    FR1462037A|FR3029563B1|2014-12-08|2014-12-08|LOW HUB RATIO PLATFORM|FR1462037A| FR3029563B1|2014-12-08|2014-12-08|LOW HUB RATIO PLATFORM|
    GB1521472.9A| GB2534466B|2014-12-08|2015-12-04|A platform of small hub-tip ratio|
    US14/959,272| US10253640B2|2014-12-08|2015-12-04|Platform of small hub-tip ratio|
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