• 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:
    Preform for a turbomachine blade, comprising a main fiber preform, obtained by three-dimensional weaving and comprising a first longitudinal section, capable of forming a blade root (21), a second longitudinal section, extending upwardly the first longitudinal section, adapted to form a blade portion (22), a first transverse section extending transversely from the junction between the first and second longitudinal sections to a substantially linear distal edge, adapted to form a first platform (23), and the preform further comprising at least one attachment lug provided under the first transverse section at its distal edge, adapted to form a hooking portion (40) of the platform (23).
    公开号:FR3035677A1
    申请号:FR1553850
    申请日:2015-04-29
    公开日:2016-11-04
    发明作者:Gaillard Thomas Alain De；Caroline Jacqueline Denise Berdou；Alexandre Bernard Marie Boisson
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a preform for a turbomachine blade and in particular a monoblock blade that can be formed by means of such a preform, a bladed module and a turbomachine comprising such a blade. Such a preform can be used to make blades comprising aerodynamic platforms provided with attachment portions that can be retained by hooks provided on the rotor of the turbomachine. Such vanes may be including fan blades 10 of an aircraft turbojet engine, to cite only this example. STATE OF THE PRIOR ART In order to reduce the mass of aircraft turbojet engines, and therefore to reduce the consumption of these turbojet engines, it is now known to manufacture certain blades of the reactor made of composite material, which is much lighter than the metal traditionally used. 'so. To this end, it is also known today to use three-dimensional weaving techniques to obtain fibrous preforms resulting in composite blades of very good quality. WO 2014/076408 describes in particular a method of weaving a fibrous preform for obtaining integrally blades having intrados and extrados platforms, these platforms being of constant thickness. However, these platforms must meet a large number of requirements and perform many functions. Mainly, such platforms must provide an aerodynamic function of defining and channeling the flow of air flow in the turbojet engine. However, they must also ensure a guaranteed mechanical strength for all phases of flight and a consistent integration in the environment of the engine including avoiding introducing disturbances in the downstream air vein. Thus, the geometry of the platforms must be finely controlled, and this throughout the operation of the engine, and whatever the phase of the flight. In particular, during tests and simulations carried out on such blades, the inventors have found that different areas of these platforms resulting from a 3D weave deform more or less significantly under the effect of centrifugal forces. exerting during the operation of the turbomachine. The inventors have notably noted that the deformation of an area of a platform is all the more important because it has a large offset relative to the blade.
    [0002] Therefore, these platforms have in operation irregularities of shape likely to disturb the air flow and thus the efficiency of the turbomachine. In addition, the inventors have found that the sag is dependent, inter alia, on the length of the cantilever. Thus, the cantilever being different between the upper and lower surfaces of two consecutive blades, this results in a discontinuity of sagging at this interface and a risk of overlapping platforms. There is therefore a real need for a preform, a blade, a disc, a downstream drum, a bladed module and a turbomachine which are free, at least in part, from the drawbacks inherent in the aforementioned known systems. PRESENTATION OF THE INVENTION The present disclosure relates to a preform for a turbomachine blade, comprising a main fiber preform, obtained by three-dimensional weaving and comprising a first longitudinal section, capable of forming a blade root, a second longitudinal section, extending upwardly, the first longitudinal section, capable of forming a portion of a blade, a first transverse section extending transversely from the junction between the first and second longitudinal sections to a substantially linear distal edge capable of forming a first platform, and the preform further comprising at least one attachment lug provided under the first transverse section at its distal edge, adapted to form a hooking portion of the platform. With such a preform, it is possible to obtain in one piece a blade comprising a blade root, a blade portion and at least one platform provided with a hooking portion. Such a hooking portion is adapted to cooperate with one or more hooks provided on the rotor of the bladed module, for example on the disc, the downstream drum, or the upstream ferrule. The cooperation between these hooks 3 and these attachment portions then allows to retain or block the platforms against the centrifugal forces exerted on the latter during operation of the turbomachine. This limits the deformation of the platform in operation. In particular, such catching portions may be provided in areas of the platform which are usually strongly deflected by centrifugal force. Therefore, the platform maintains in operation a relatively regular profile, not disturbing or little movement of the air stream. Thanks to this preform, the advantages of a 3D woven monobloc blade (mass saving, reduced number of parts, simplified mounting and maintenance, etc.) can be obtained while ensuring aerodynamic regularity of the air stream. In addition, the cooperation between the hooks and the attachment portions of the blades also reduces the discontinuity usually observed in operation at the interface between neighboring platforms. In addition, such a configuration also reduces the risk of overlap of a platform on the neighboring platform, in case of bird ingestion for example.
    [0003] In this presentation, the terms "longitudinal", "transversal", "lower", "superior" and their derivatives are defined in relation to the principal direction of the dawn under consideration, with the blade root being located on the lower side of dawn according to this reference; the terms "proximal", "distal" and their derivatives are defined with respect to the blade of dawn; the terms "axial", "radial", "tangential" and their derivatives are themselves defined with respect to the main axis of the wheel comprising these blades, that is to say in general the axis of the turbomachine . The term "axial plane" means a plane passing through the main axis of the turbomachine and "radial plane" a plane perpendicular to this main axis; the term "longitudinal plane" a plane parallel to the main direction of the blade and perpendicular to the direction of extension of the blade root such a longitudinal plane is a radial plane in the reference system of the turbomachine. In addition, the terms "upstream" and "downstream" are defined relative to the flow of air in the turbomachine.
    [0004] Finally, "three-dimensional weaving" is understood to mean a weaving technique in which weft threads circulate within a matrix of three warp threads so as to form a three-dimensional network of threads in a three-dimensional armor: all the layers of son of such a fibrous structure are then woven during a single weaving step in a three-dimensional weaving loom.
    [0005] In some embodiments, at least one latching lug is an extension of the main fibrous preform extending from the distal edge of the first transverse section and configured to be folded under the first transverse section. The preform can then comprise only one single piece, the main fiber preform, woven in a single step, which simplifies the manufacturing process. The cohesion of the attachment portion thus obtained is further reinforced with the platform. In some embodiments, at least one latch lug is configured to be L-folded under the first transverse section. In some embodiments, at least one latching lug is configured to be U-folded under the first transverse section. During the injection of the matrix, this makes it possible to close the hooking lug and thus to form a hooking portion in the form of a box. In some embodiments, at least one latching lug is at least partially wound around a hollow insert. Such an insert, metallic or composite, for example, reinforces the structure of the fastening portion obtained.
    [0006] In some embodiments, the hollow insert is a cylindrical box with a polygonal base, preferably rectangular. In some embodiments, at least one latching lug is attached under the first transverse section of the main fibrous preform. The fact of bringing back such a fastening tab on the main fiber preform makes it possible to preserve the existing weaving strategy for the main fiber preform, which simplifies the weaving, offers greater freedom in the choice of the geometry of the preform avoiding to weaken the structure of the latter. In addition, the hooking tab is reported under the platform, its design is relatively free: its geometry can be adapted precisely to a type of blade or hook.
    [0007] In certain embodiments, at least one attachment lug thus reported is a cylindrical box with a polygonal base, preferably a rectangular box. In other embodiments, at least one hooking lug thus reported is a box having a prismatic shape. Such a shape is particularly suitable for hooks having a tapered shape, in particular triangular. Such a hook makes it possible to have a horizontal contact between the hook and the hooking tab.
    [0008] In some embodiments, at least one latching lug is provided at the upstream or downstream end of the first transverse section. Indeed, in the case of an extrados platform, these upstream and downstream ends of the platform usually experience strong deformations.
    [0009] In some embodiments, at least one latching lug is provided in the middle zone of the first transverse section. Here it is meant that the latching lug is located mainly in the region centered axially on the midpoint of the distal edge of the first transverse section and extending axially in total over 25% of the length of the distal edge. Indeed, in the case of an intrados platform, this median zone usually knows strong deformations. In some embodiments, the axial length of the latching lug is less than one-fourth, preferably one-fifth, of the length of the distal edge of the first transverse section. In some embodiments, the main fibrous preform comprises a second transverse section extending transversely from the junction between the first and second longitudinal sections to a substantially linear distal edge, in the extension and opposite of the first cross section, adapted to form a second platform, and wherein the preform further comprises at least one attachment lug provided under the second transverse section at its distal edge, adapted to form a hooking portion of the second platform .
    [0010] It will be understood, of course, that all of the features discussed above with respect to the first transverse section can be transposed to the second transverse section. In particular, the fastening tab or lugs of the second transverse section may be identical in nature or different from the fastening lug or tabs of the first transverse section.
    [0011] In some embodiments, the yarns used for weaving the main fiber 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 main fiber preform is 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. The present disclosure also relates to a blade for a turbomachine, comprising a blade root, a portion of blade, extending upwards from the blade root, a platform made of composite material and extending transversely to the blade. portion of blade at the junction between the blade root and the blade portion, and a hooking portion, provided under the platform at its distal end, configured to cooperate with a hook of the turbine engine.
    [0012] It is understood that this blade corresponds to that which can be obtained using the preform above. However, such a blade could also be obtained from the main fiber preform described above, the attachment portion being attached to the platform after consolidation of the main fiber preform. In one case as in the other, all the features and advantages described above are transposed directly to this dawn, whatever its technique of obtaining. In some embodiments, the blade is made integrally of a composite material by means of a preform according to any one of the preceding embodiments, said preform having been shaped in a mold and embedded in a matrix. . 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.
    [0013] In some embodiments, the attachment portion is reported on the platform. The present disclosure also relates to a bladed module disk, the circumference of which has a succession of grooves and teeth, the grooves being configured to receive a blade according to any one of the preceding embodiments, wherein at least one tooth, preferably each tooth, is provided with a hook extending radially from the top of the tooth and configured to cooperate with a gripping portion of a blade.
    [0014] Thanks to the cooperation between the hook of this disk and a blade according to the invention, it is possible to control the displacement of the platform relative to the disk and thus to control the deformation of the platform. In some embodiments, at least one hook is machined into the thickness of the disc. In other embodiments, at least one hook is attached to the disk. For example, such a hook may be attached by bolting, screwing, or assembling complementary shapes (the disc may for example have an inverted T-groove formed in the axial direction of the tooth and the foot of the hook may have a complementary shape to this groove). In some embodiments, at least one tooth, preferably each tooth, is provided with at least one pair of two separate hooks. The neighboring intrados and extrados platforms thus cooperate with a different hook in each pair. Naturally, it is possible to provide as many pairs of hooks as there are attachment portions on a given platform. In some embodiments, at least one tooth, preferably each tooth, is provided with a hook having two distinct hooking fingers. Thus, a given hook can cooperate simultaneously with the neighboring intrados and extrados platforms. The present disclosure also relates to a downstream drum for a bladed module configured to rotate in synchronism with a disc carrying a plurality of blades according to any one of the preceding embodiments, comprising at least one hook extending from the upstream face of the bladder. downstream drum and configured to cooperate with a portion 8 hooking a blade. Such a downstream drum, also sometimes called "booster drum", is in particular present just downstream of the disk and the blades of a turbojet fan. A double hook similar to the one shown above is also possible.
    [0015] The present disclosure also relates to an upstream ferrule for a bladed module configured to rotate in synchronism with a disc carrying a plurality of blades according to any one of the preceding embodiments, comprising at least one hook extending from the upstream face of the bladder. downstream drum and configured to cooperate with a hooking portion of a blade. Such upstream ferrule is in particular present just upstream of the disk and the blades of a turbojet fan. A double hook similar to the one shown above is also possible. The present disclosure also relates to a turbomachine bladed module, comprising a plurality of blades according to any one of the preceding embodiments and a disk, a downstream drum or an upstream ferrule according to any one of the preceding embodiments. In some embodiments, at least one hook, preferably each hook, penetrates into the coinciding latching portion of a blade downstream. This facilitates the assembly and disassembly of the module. In certain embodiments, a radial clearance of at least 0.5 mm is provided between the attachment portion of a given platform 25 and the corresponding hook when the module is stopped. This allows to leave the platform a minimum freedom of movement during operation in order not to accumulate excessive stresses at the attachment portion or the hook. The initial geometry of the platform and this radial clearance are thus preferably adjusted according to the geometry of the platform desired during operation. In some embodiments, a tangential clearance of at least 1 mm is provided between the attachment portion of a given platform and the corresponding hook when the module is stopped. Such a game leaves a certain freedom of lateral movement to the platform so as to be able to withstand a major shock, for example in case of bird ingestion. The hooking portion then retains the platform 3035677 9 tangentially only in case of excessive lateral displacement. The present disclosure also relates to a turbomachine, comprising at least one blade or a module according to any one of the preceding embodiments. The above-mentioned characteristics and advantages, as well as others, will appear on reading the following detailed description of embodiments of the preform, the blade, the disk, the downstream drum, the bladed module and the blade. turbomachine proposed. This detailed description refers to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings are schematic and are intended primarily to illustrate the principles of the invention.
    [0016] In these drawings, from one FIG (FIG) to another, identical elements (or parts of elements) are identified by the same reference signs. In addition, elements (or parts of elements) belonging to different exemplary embodiments but having an analogous function are indicated in the figures by incremented numerals of 100, 200, etc. FIG 1 is a plane in axial section of a turbomachine according to the invention. FIG 2 is a partial diagram in radial section of a bladed module according to the invention.
    [0017] FIG 3 is a diagram in axial section of a bladed module according to the invention. FIG 4 is a partial view in radial section of a bladed module according to a first embodiment. FIG 5 schematically illustrates the preform 30 corresponding to the blade of this first example before it is shaped. FIG 6 schematically illustrates the preform corresponding to the blade of this first example after its shaping. FIG 7 is a partial view in radial section of a bladed module according to a second embodiment.
    [0018] FIG 8 is a partial view in radial section of a bladed module according to a third embodiment.
    [0019] FIG 9 is a partial view in radial section of a bladed module according to a fourth embodiment. FIG 10 is a perspective view of a hook according to the fourth example.
    [0020] DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS In order to make the invention more concrete, exemplary embodiments are described in detail below, with reference to the accompanying drawings. It is recalled that the invention is not limited to these examples.
    [0021] 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 air flow, a fan 2, a low pressure compressor 3, a high pressure compressor 4, a combustion chamber 5, a high pressure turbine 6, 15 and a low turbine The fan module 2 is shown in greater detail in FIGS. 2 and 3. It comprises an upstream shell 14, a fan disk 11 and a downstream drum 15 also called a "drum booster". A plurality of grooves 12 are formed in the outer surface of the fan disk 11: these grooves 12 are rectilinear and extend axially from upstream to downstream along the entire disk 11. They are also regularly distributed all around the disk. In this way, each groove 12 defines with its neighbor a tooth 13 which thus extends also axially from upstream to downstream along the entire disc 11. The fan module 2 further comprises a plurality of vanes 10 mounted in the grooves 12 of the fan disk 11. Each vane 10 includes a dovetail root 21 configured to engage a groove 12 of the disk 11 to secure it to the disk 11 .
    [0022] This blade root 21 is extended upwards by a blade 22 having an extrados face 22e and an intrados face 221 each of which is upstream to downstream between a leading edge 22a and a trailing edge 22f. The blade 10 further comprises an extrados platform 23, extending transversely on the extrados side of the blade from the junction 35 between the blade root 21 and the blade 22, and an intrados platform 24, 303 56 77 11 s extending transversely on the underside side of the blade from the junction between the blade root 21 and the blade 22. The upstream ferrule 14 and the downstream drum 15 are connected to the disk 11, the latter being coupled with the low pressure shaft Thus, during operation of the turbojet engine, the upstream shell 14, the fan disk 11, the blades 10, and the downstream drum 15 are integrally rotated by the low pressure turbine 7. At the distal end of each of the platforms 23, 24, and the inner side thereof, are provided several attachment portions 40.
    [0023] These attachment portions 40 take the form of a box or duct segment provided against the lower surface of the platforms 23, 24, along their distal edge 23a, 24a. These attachment portions 40 thus form cavities 41 substantially cylindrical rectangular base open upstream and downstream.
    [0024] In this example, each platform 23, 24 comprises three attachment portions 40: one at the downstream end of the platform 23, a second in the central zone of the platform 23 and a third at the upstream end of the platform 23. platform 23. However, it will be only a number of attachment portions 40 may be used depending in particular on the length of the platforms 23, 24, the importance of their cantilever and the configuration of the module 2. Each attachment portion 40 is configured to cooperate with a hook of the fan module 2. Three types of hooks are presented in this first example.
    [0025] Each tooth 13 thus has two hooks 50 to cooperate each with the attachment portion 40 located in the central zone of each platform 23, 24 coincident. Each hook 50 thus extends radially from the top of the tooth 13 and has a gripping finger 50a engaging from downstream in the cavity 41 of the attachment portion 40 of the platform 23, 24 considered. The hooking finger 50a may have a triangular shape tapering from the body of the hook: the cavity 41 of the attachment portion 40 of the platform 23, 24 then has a complementary prismatic shape. Alternatively, the latching finger 50a may also have a constant profile.
    [0026] The downstream drum 15 also has several hooks 51 whose gripping fingers 51a are configured to cooperate with the attachment portions 40 located at the downstream end of the platforms 23, 24. Similarly, the upstream ferrule 14 has several hooks 52 whose hooking fingers 52a are configured to cooperate with the attachment portions 40 located at the upstream end of the platforms 23, 24.
    [0027] As best seen in FIG. 4, a radial clearance R is left stationary between the lower face of the latching finger 50a and the lower face of the cavity 41; a tangential clearance T is also left stationary between the proximal face of the hooking finger 50a and the proximal face of the cavity 41. Such games can also exist with the other 10 types of hooks 51 and 52. In the first embodiment, better visible in FIG 4, the blade 10 is obtained in one piece by 3D weaving a preform 30 and injection of an organ resin according to the RTM method known to those skilled in the art.
    [0028] FIG. 5 shows this three-dimensional woven preform 30 for making this blade example 10. FIG. 6 shows the final preform 30 'after it has been shaped. This preform 30 will be described from bottom to top, that is to say upstream downstream in the weaving direction T. It goes without saying, however, that weaving could be done from the other end and in the other direction. In this embodiment, the preform 30 is woven three-dimensionally in carbon fibers in 3D interlock armor. Only the surfaces of the preform 30 are woven two-dimensionally in a satin-like weave.
    [0029] At the lower end, the weaving begins with the production of a first longitudinal section 31 which will form the root 21 of the blade 10. Above this first longitudinal section 31, there begins a debonding zone D in which a first free flange 35, a second longitudinal flange 32, and a second flange 36 are loosely woven together with respective bonding planes 38 and 39. Weaving methods for such unbinding are now well known in the art. 3D weaving. From a certain level, which can vary according to the weaving plane, the free faces 35, 36 have reached the desired length for the platform in question 23, 24 in the considered weaving plane. From this distal edge 33a, 34a thus defined, the weaving continues only in certain planes to form tabs 37 extending from the distal edge 33a, 34a. Alternatively, the weaving may continue from the distal edge 33a, 34a uniformly throughout the free pan 35, 36: in such a case, the tabs 37 are obtained by cutting or machining. Once the weaving is finished, the free faces 35, 36 are cut: on the extrados side, a first transverse section 33 extending to the distal edge 33a, which will form the extrados platform 23 of the blade 10, is thus obtained. and a plurality of latches 37 extending from certain segments of the distal edge 33a, which will form clipping portions; on the intrados side, thus obtaining a second transverse section 34 extending to the distal edge 34a, which will form the intrados platform 24 of the blade 10, and a plurality of hooking tabs 37 extending for some segments of the distal edge 33a, which will form hooking portions. It should be noted here that the qualifiers "transverse" and "longitudinal" are given as a function of the final position of the section considered, the transverse sections being necessarily woven longitudinally before being folded transversely. The preform 30 can then be wetted to soften it and allow for easier decadding of the fibers. The preform 30 is then introduced into a forming mold whose internal space is adjusted to the desired geometry for the preform 30. During this step, the hooking tabs 37 are folded in U under the transverse sections 33 and 34. the ends of the tabs 37 being pressed against the lower surface of the respective transverse section 33, 34. The preform 30 is then dried so that the latter stiffens, thus blocking the geometry imposed during the shaping. The preform thus shaped 30 'is finally disposed in an injection mold, to the dimensions of the desired final blade 10, into which a matrix is injected, here an epoxy resin. Such an injection may for example be carried out by the known method RTM ("resin transfer molding"). This consolidation then makes it possible to block the geometry of the blade and to secure the end of the tabs 37 against the lower surface of the platforms 23, 24. Thus, at the end of this step, the dawn is integrally formed. 10 of composite material provided with attachment portions 40.
    [0030] Naturally, the weaving example described above is only one of many other possible examples that those skilled in the art will readily recognize. In particular, it is possible to imagine other delimitations or to use other weaving techniques such as layer crosses, layer outlets or thickness transitions to obtain a similar preform geometry. Those skilled in the art will find in particular many examples of weavings in the document WO 2014/076408. In a second example, shown in FIG. 7, the attachment portions take the form of boxes 140 having a rectangular section extending against the lower surface of the platforms 123, 124, along certain segments of the distal edge 123a, 124a. This box, metal or composite, is hollow and thus forms a cavity 141 opening axially upstream and downstream.
    [0031] Such a blade 110 may be obtained using a manufacturing method similar to that of the first example. A main fibrous preform similar to the fibrous preform 30 of the preceding example is thus woven and then the caissons 140 acting as hooking tabs are attached against the lower surface of the transverse sections of the main preform, for example to using rivets or points of glue, the completed preform then undergoing co-injection. Alternatively, the boxes 140 can be reported by gluing, riveting, bolting or any other method on an already consolidated composite blade resulting for example from a main fiber preform similar to that described in the first example but without overlength weaving at beyond the distal edge of the transverse sections. In a third example, shown in FIG. 8, the attachment portions 240 take the form of boxes 243 similar to the box 140 of the previous example around which woven tabs 242 similar to the slips of the first example are wound. Each attachment portion 240 is thus also hollow and thus forms a cavity 241 opening axially upstream and downstream. For producing such a blade 210, a main fiber preform similar to that of the first example is first woven. Then caissons 243 similar to those of the second example are attached against the lower surface of the transverse sections of the main preform against the distal edge thereof. The attachment tabs of the main fiber preform are then folded around the boxes 243 which thus play the role of inserts. The preform thus completed and shaped then undergoes a matrix injection and consolidation step similar to that of the first example. FIG 9 illustrates a fourth example in which the blades 310 are similar to those of the first example but in which the disc 311 is provided with different hooks 350. Indeed, as shown in FIG 10, the hooks 350 are provided with in this example two separate gripping fingers 350a, 350b extending side by side and configured to cooperate with the latching portions 340 coincident of two neighboring platforms 323, 324. It is of course understood that such a double hook could be Used with a blade according to any of the examples presented. The modes or examples of embodiment described in the present description are given for illustrative and not limiting, a person skilled in the art can easily, in view of this presentation, modify these modes or embodiments, or consider others, while remaining within the scope of the invention. In addition, the various features of these modes or embodiments can be used alone or be combined with each other. When combined, these features may be as described above or differently, the invention not being limited to the specific combinations described herein. In particular, unless otherwise specified, a characteristic described in connection with a mode or example of embodiment may be applied in a similar manner to another embodiment or embodiment.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Preform for a turbomachine blade, comprising a main fibrous preform (30) obtained by three-dimensional weaving and comprising a first longitudinal section (31) capable of forming a blade root (21), a second longitudinal section (32), extending upwardly the first longitudinal section (31), capable of forming a blade portion (22), a first transverse section (33) extending transversely from the junction between the first and second longitudinal sections (31, 32) to a substantially linear distal edge (33a) capable of forming a first platform (23), and the preform (30 ') further comprising at least one latching lug (37) provided under the first transverse section ( 33) at its distal edge (33a), adapted to form a hooking portion (40) of the platform (23). 20
    [0002]
    2. Preform according to claim 1, wherein at least one hooking tab is an extension (37) of the main fibrous preform (30) extending from the distal edge (33a) of the first transverse section (33) and configured to be folded under the first transverse section (33).
    [0003]
    3. Preform according to claim 1 or 2, wherein at least one latching lug (242) is wound at least partially around a hollow insert (243). 30
    [0004]
    4. Preform according to any one of claims 1 to 3, wherein at least one latching lug (140) is reported under the first transverse section (33) of the main fibrous preform (30). 35
    [0005]
    A preform according to any one of claims 1 to 4, wherein the main fibrous preform (30) comprises a second transverse section (34) extending transversely from the junction between the first and second longitudinal sections. (31, 32) to a substantially linear distal edge (34a), in the extension and opposite of the first transverse section (33), capable of forming a second platform (24), and wherein the preform comprises in addition at least one latching lug (37) provided under the second transverse section (34) at its distal edge (34a), adapted to form a hooking portion (40) of the second platform (24). 10
    [0006]
    6. Turbomachine blade, comprising a blade root (21), a blade portion (22) extending upwardly from the blade root (21), a platform (23), made of composite material and extending transversely to the blade portion (22) at the junction between the blade root (21) and the blade portion (22), and a gripping portion (40) provided under the platform at its distal end (23a), configured to cooperate with a hook (50) of the turbomachine.
    [0007]
    7. blade according to claim 6, made integrally of composite material by means of a preform (30 ') according to any one of claims 1 to 5, said preform (30') having been shaped in a mold and embedded in a matrix, preferably of organic type.
    [0008]
    8. blade according to claim 6, wherein the attachment portion (40) is attached to the platform (23).
    [0009]
    9. Disk for bladed module, whose circumference has a succession of grooves (12) and teeth (13), the grooves (12) being configured to receive a blade (10) according to any one of claims 6 to 8. 303 56 7 7 18 wherein at least one tooth (13) is provided with a hook (50) extending radially from the top of the tooth (13) and configured to cooperate with a hooking portion (40) d a dawn (10). 5
    [0010]
    10. Disc according to claim 9, wherein at least one tooth (13) is provided with a hook (350) having two gripping fingers (350a, 350b) distinct.
    [0011]
    A downstream tumbler for a bladder module configured to rotate in synchronism with a disc (11) carrying a plurality of blades (10) according to any one of claims 6 to 8, comprising at least one hook (51) extending from the upstream face of the downstream drum (15) and configured to cooperate with a hooking portion (40) of a blade (10). 15
    [0012]
    Turbomachine bladder module, comprising a plurality of blades (10) according to any one of claims 6 to 8 and a disc (11) according to claim 9 or 10 or a downstream drum (15) according to claim 11.
    [0013]
    13. Module according to claim 12, wherein a radial clearance (R) of at least 0.5 mm and / or a tangential clearance (T) of at least 1 mm is provided between the attachment portion (40). a given platform (23, 24) and the hook (50) corresponding when the module (2) is stopped.
    [0014]
    14. Turbomachine, comprising at least one blade (10) according to any one of claims 6 to 8 or a module (2) according to claim 12 or 13. 20 25 30
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    WO2021123652A1|2021-06-24|Fan or propeller vane for an aircraft turbomachine and method for manufacturing same
    FR3087831A1|2020-05-01|BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND A METAL STRAINING PART
    WO2021148750A1|2021-07-29|Blade comprising a composite material structure and associated manufacturing method
    FR3108144A1|2021-09-17|Blade comprising a composite material structure and associated manufacturing method
    同族专利:
    公开号 | 公开日
    GB2540244A|2017-01-11|
    FR3035677B1|2017-05-12|
    GB201607489D0|2016-06-15|
    GB2540244B|2020-06-24|
    US20170058912A1|2017-03-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2013079860A1|2011-12-01|2013-06-06|Herakles|Method for producing a turbomachine vane made from composite material and including integrated platforms|
    WO2013104852A2|2012-01-09|2013-07-18|Snecma|Fibrous preform of a turbomachine blade made of composite material with in-built platform, and method of producing same|
    WO2014076408A1|2012-11-13|2014-05-22|Snecma|Monobloc preform and blade for turbo machine|WO2018158522A1|2017-03-01|2018-09-07|Safran Aircraft Engines|Preform and one-piece vane for turbomachine|
    FR3089258A1|2018-12-03|2020-06-05|Safran Aircraft Engines|Blower comprising an inter-blade platform fixed radially by a sacrificial protective sheet|US4453890A|1981-06-18|1984-06-12|General Electric Company|Blading system for a gas turbine engine|
    FR2669686B1|1990-11-28|1994-09-02|Snecma|BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.|
    US6627019B2|2000-12-18|2003-09-30|David C. Jarmon|Process for making ceramic matrix composite parts with cooling channels|
    US8251651B2|2009-01-28|2012-08-28|United Technologies Corporation|Segmented ceramic matrix composite turbine airfoil component|
    US9759226B2|2013-02-15|2017-09-12|United Technologies Corporation|Low profile fan platform attachment|
    US10018048B2|2013-03-12|2018-07-10|United Technologies Corporation|T-shaped platform leading edge anti-rotation tabs|FR3035676B1|2015-04-29|2017-05-12|Snecma|DAWN WITH PLATFORMS POSSESSING A STIFFENER|
    FR3037097B1|2015-06-03|2017-06-23|Snecma|COMPOSITE AUBE COMPRISING A PLATFORM WITH A STIFFENER|
    GB201604473D0|2016-03-16|2016-04-27|Rolls Royce Plc|A bladed rotor arrangement and a lock plate for a bladed rotor arrangement|
    US10436036B2|2016-07-05|2019-10-08|Safran Aircraft Engines|Fitted platform for a turbine engine fan, and a method of fabricating it|
    US10443409B2|2016-10-28|2019-10-15|Rolls-Royce North American Technologies Inc.|Turbine blade with ceramic matrix composite material construction|
    US10577939B2|2016-11-01|2020-03-03|Rolls-Royce Corporation|Turbine blade with three-dimensional CMC construction elements|
    US10392946B2|2016-12-21|2019-08-27|Rolls-Royce North American Technologies Inc.|Turbine blade with reinforced platform for composite material construction|
    FR3084920B1|2018-08-09|2021-05-21|Safran Aircraft Engines|BLADE FOR AIRCRAFT TURBOMACHINE BLOWER WITH AT LEAST ONE DAMPER|
    US11035239B2|2018-10-25|2021-06-15|General Electric Company|Ceramic matrix composite turbine nozzle shell and method of assembly|
    法律状态:
    2016-04-12| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-04| PLSC| Publication of the preliminary search report|Effective date: 20161104 |
    2017-04-07| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1553850A|FR3035677B1|2015-04-29|2015-04-29|DAWN HAVING PLATFORMS HAVING HOISTING PORTIONS|FR1553850A| FR3035677B1|2015-04-29|2015-04-29|DAWN HAVING PLATFORMS HAVING HOISTING PORTIONS|
    US15/141,360| US20170058912A1|2015-04-29|2016-04-28|Blade provided with platforms possessing attachment portions|
    GB1607489.0A| GB2540244B|2015-04-29|2016-04-29|A Blade provided with platforms possessing attachment portions|
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