• 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, capable of forming a first platform (23), in which the preform further comprises at least a stiffener (40) attached to the main fibrous preform along at least one segment of the distal edge of the first transverse section.
    公开号:FR3035676A1
    申请号:FR1553849
    申请日:2015-04-29
    公开日:2016-11-04
    发明作者:Caroline Jacqueline Denise Berdou；Gaillard Thomas Alain De
    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 a monobloc blade that can be formed by means of such a preform, a bladed wheel and a turbomachine comprising such a blade. Such a preform can be used to make blades comprising aerodynamic platforms provided with a stiffener. Such vanes may be including fan blades of an aircraft turbojet engine, to cite only this example.
    [0002] STATE OF THE PRIOR ART In order to reduce the mass of aircraft turbojet engines, and thus to reduce the consumption of these turbojet engines, it is now known to manufacture some blades of the composite material reactor, which is much lighter than the metal traditionally used until 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. The document WO 2014/076408 describes in particular a method of weaving a fibrous preform for obtaining in one-piece manner blades provided with 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 into the engine environment by avoiding in particular 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 the centrifugal forces exerted during the 3035676 2 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. 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 of the platforms. There is therefore a real need for a preform, a blade, a bladed wheel and a turbomachine which are lacking, at least in part, the disadvantages inherent in the aforementioned known systems.
    [0003] 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 upwards 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, able to form a first platform, in which the preform comprises in addition at least one stiffener attached to the main fibrous preform along at least one segment of the distal edge of the first transverse section. With such a preform, it is possible to obtain in one piece a blade comprising a blade root, a portion of blade and at least one platform provided with a stiffener ensuring a more even deformation of the platform. formed under the effect of the centrifugal force during operation of the turbomachine. Indeed, the presence of this stiffener makes it possible to better secure the different zones of the platform, and particularly the distal zones of the platform, in order to tend towards a uniformization of their radial deformations at the end of the platform. . The deformations of the platform are thus somehow averaged, with the usually strongly deflected areas pulling out the usually less deflected areas while the latter retain the areas of high displacement inward. Therefore, the platform 5 keeps in operation a relatively regular profile, not disturbing or little movement of the air stream. Thanks to this preform, one can thus benefit from the advantages of a 3D woven monobloc blade (mass gain, reduced number of parts, simplified assembly and maintenance, etc.) while ensuring an aerodynamic regularity of the air stream. In addition, the fact of bringing such a stiffener onto the main fiber preform, rather than extending the platform with a woven strip, for example, preserves the existing weaving strategy for the main fiber preform, which simplifies weaving, offers greater freedom in choosing the geometry of the preform by avoiding weakening the structure of the latter. In this specification, the terms "longitudinal", "transverse", "lower", "superior" and their derivatives are defined in relation to the principal direction of the blade under consideration, with the blade root 20 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 .
    [0004] By "axial plane" is meant a plane passing through the main axis of the turbomachine and by "radial plane" a plane perpendicular to this main axis; the term "longitudinal plane" means 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 of the turbomachine. In addition, the terms "upstream" and "downstream" are defined relative to the flow of air in the turbomachine. Finally, "three-dimensional weaving" is understood to mean a weaving technique in which weft threads circulate within a matrix of warp threads so as to form a three-dimensional network of threads in three-dimensional weave: all the layers of threads Such a fibrous structure is then woven during the same weaving step within a three-dimensional weaving machine. In some embodiments, the stiffener is made of metallic material. Such a metallic material thus offers significant rigidity. In some embodiments, the stiffener is made of composite material. Such a composite material, although generally less rigid than metal, is lighter than the latter. The material of the stiffener will therefore be chosen according to the particular needs and constraints of a given piece. In some embodiments, the stiffener extends for at least one third of the length of the distal edge of the first transverse section. It may for example be provided only in the areas of the platform normally experiencing the largest deformations, that is to say those most remote from the blade. In some embodiments, the stiffener extends along the distal edge of the first transverse section at least from the upstream or downstream end. Indeed, in the case of an extrados platform, these upstream and downstream ends of the platform usually experience strong deformations. In some embodiments, the stiffener extends all along the distal edge of the first transverse section. This balances the deformations and stiffens the platform over its entire length. In some embodiments, the stiffener is a foil having a U-section and enclosing the distal edge of the first transverse section. Such a foil is easy to manufacture and put in place. In some embodiments, the upper lug and the lower lug of the U-shaped foil have the same length. However, in other embodiments, the lower leg could be of a different length to limit the appearance of areas of weakness. In particular, the lower leg could be longer than the upper leg to better distribute the efforts on the foil. In some embodiments, the upper end of the foil engages in a recess formed in the upper surface of the first transverse section such that the upper surface of the foil is flush with the upper surface of the first transverse section.
    [0005] This makes it possible to obtain a smooth vein surface at the interface between the platform and the foil. Such a withdrawal can be obtained during weaving by wire outlets or later, particularly after consolidation, by machining.
    [0006] In some embodiments, the lower end of the foil engages in a recess formed in the lower surface of the first transverse section such that the lower surface of the foil is flush with the lower surface of the first transverse section. The same training options are available for this lower withdrawal.
    [0007] In some embodiments, the stiffener is a box attached to the lower surface of the first transverse section. With this box-shaped, such a stiffener has a significant stiffness. In addition, the box being attached under the platform, the design of the box is relatively free: it may in particular have a wide, to stiffen the platform over a larger area, or a large thickness, to benefit from a stiffer more important. In some embodiments, the box has a polygonal section. It is preferably hollow, thus having an internal cavity.
    [0008] However, the section of the box can also be scalable: this makes it possible to adjust the stiffness of the stiffener along the platform. In some embodiments, the stiffener has an axial rib or an axial notch configured to cooperate respectively with the axial notch or the axial rib of a platform stiffener 25 of a neighboring blade. This improves the tightness of the vein at the interface between the two platforms. In addition, such a device reduces the risk of overlap of a platform on the neighboring platform, in case of bird ingestion for example. In some embodiments, the stiffener is a roller 30 around which is wound the distal end of the first transverse section. In such a case, it may be necessary to provide weaving of an excess length at the distal end of the transverse section of the main fiber preform. Important cohesion is thus ensured between the main fiber preform and the stiffener.
    [0009] In some embodiments, the roller is provided with stitches configured to engage the fibrous surface of the first transverse section. In the manner of a hair curler, the grip of the roll with the main preform is thus improved. In some embodiments, the stiffener has an axial internal cavity. Such a cavity reduces the mass of the stiffener. It can also be used for hooking a fastening device or retaining the platform, such as a hook or a retaining tab, equipping the rotor. In some embodiments, the stiffener section is scalable. In this way, it is possible to take into account the geometry of the platform in order to more optimally compensate the deformations of the latter. In particular, an evolutionary width makes it possible to adjust, on the one hand, the stiffness of the stiffener, and therefore the transmission of forces from one zone to another of the platform, and on the other hand to adjust the mass added locally to the platform , and thus locally adjust the centrifugal forces exerted on the platform. In particular, by locally adding mass to a usually less deflected area of the platform, the intensity of the centrifugal force in this area is increased so that the latter will be a little more deflected and will align more easily with neighboring areas naturally more deflected.
    [0010] In certain embodiments, the main fibrous preform comprises a second transverse section, extending transversely from the junction between the first and second longitudinal sections, in the extension and opposite of the first transverse section, capable of forming a second transverse section. platform, and wherein the preform further comprises a second stiffener attached to the main preform along at least one segment of the distal edge of the second transverse section. It will be understood, of course, that all the features mentioned above with respect to the first transverse section can be transposed to the second transverse section. In particular, the stiffener of the second transverse section may be of the same or different nature to the stiffener of the first transverse section. In some embodiments, the yarns used for weaving the preform are carbon fibers. However, it may be any other type of yarn, for example fiberglass or Kevlar.
    [0011] In some embodiments, the weave used for the three-dimensional weaving of the 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.
    [0012] 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, wherein the platform is provided with a stiffener extending along at least one segment of the distal edge of said platform. 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 fibrous preform described above, the stiffener being attached to the platform after consolidation of the main fibrous preform. In either case, all the features and advantages described above are directly transposed to this dawn, whatever its technique of obtaining.
    [0013] 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. In some embodiments, the stiffener is attached to the platform.
    [0014] The present disclosure also relates to a turbomachine bladed wheel comprising a plurality of blades according to one of the preceding embodiments. It may be a rotor wheel, such as a fan, in which the vanes are angularly disposed around a rotating hub, or a stator wheel, in which the vanes are arranged angularly within the rotor. a fixed ferrule.
    [0015] The present disclosure also relates to a turbomachine, comprising at least one blade or a bladed wheel according to one of the preceding embodiments. The aforementioned features and advantages, as well as others, will appear on reading the detailed description which follows, of exemplary embodiments of the preform, the blade, the bladed wheel and the turbomachine proposed. This detailed description refers to the accompanying drawings.
    [0016] 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 the other, identical elements (or 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 numerical references 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 wheel according to the invention. FIG 3 is a partial perspective view of a blade according to an exemplary embodiment.
    [0017] FIG. 4 is a sectional view of the stiffener according to the first example. FIG 5 schematically illustrates the preform corresponding to this example of blade before shaping. FIG 6 schematically illustrates the preform 30 corresponding to this example of blade after shaping. FIG 7 is a sectional view of the stiffener according to a variant of the first example. FIG 8 is a sectional view of the stiffener according to another variant of the first example.
    [0018] FIGS. 9 and 10 are partial perspective views of a blade according to a second embodiment.
    [0019] FIG. 11 is a partial perspective view of a blade according to a third exemplary embodiment. FIG 12 is a diagram illustrating a step of manufacturing the preform of the blade of FIG 11.
    [0020] FIG. 13 is an axial sectional view of a bladed wheel according to the third example. 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. 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 blower 2, a low-pressure compressor 3, a high-pressure compressor 4, a combustion chamber 5, a high-pressure turbine 6, and a low turbine pressure 7. As shown in FIG. 2, the fan 2 is provided with a plurality of fan blades 10 mounted angularly about the axis A on a disc 11 connected to the low-pressure shaft of the turbomachine 1. Such a fan blade is shown on FIG. FIG. 3. It comprises a dovetail blade root 21 configured to engage a groove 12 of the disk 11 in order to fix it to the disk 11. This blade root 21 is extended upwards by a blade 22 having an extrados face 22e and an intrados face 22i each upstream upstream 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 30 between the blade root 21 and the blade 22, and an intrados platform 24, extending transversely of the blade the intrados side of the blade from the junction between the blade root 21 and the blade 22. At the distal end of each of the platforms 23, 24 is provided a foil 40 forming a stiffener. This foil 40, better visible in FIG. 4, is a profile having a U-shaped cross-section: it comprises an upper tab 41 and a lower tab 42 enclosing the distal end of the platform 23. The upper surface of this plate distal end of the platform 23 has a recess 43 whose depth corresponds to the thickness of the upper lug 41 of the foil 40. Thus, when the foil 40 is attached to the distal end of the platform 23, its upper lug 41 engaged in the recess 43 so that the foil 40 is flush with the upper surface of the platform 23. In this example, the blade 10 is obtained in a monobloc manner by 3D weaving of a main fiber preform 30, implemented place foils 40 on this main fiber preform 30 and injection of an organ resin according to the RTM method known to those skilled in the art. 5 represents this three-dimensionally woven preform 30 for producing this example of blade 10. FIG. 6 represents the final preform 30 'after it has been shaped and put in place with foils 40. This preform 30 will be described from below. at the top, that is to say upstream downstream in the weaving direction T. However, it goes without saying that weaving could be done from the other end and in the other direction.
    [0021] In this exemplary embodiment, the preform 30 is woven three-dimensionally in carbon fibers in a 3D interlock weave. Only the surfaces of the preform 30 are woven two-dimensionally in a satin-like weave. 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, a debonding zone D begins in which a first free pan 33a, a second longitudinal section 32, and a second free pan 34a are loosely woven together with respective disbonding planes 38 and 39. Weaving methods for such unbinding are now well known in the art. 3D weaving. Layers outlets may also be made along the weaving T between the second longitudinal section 32 and each of the free sections 33a, 34a in order to refine the second longitudinal section 32 and therefore the future blade 22. Weaving methods allowing such layer exits are now well known in the field of 3D weaving.
    [0022] Layer outlets 35 and 36 are also made from a certain level along the free sides 33a and 34a. Once the weaving is completed, the free sections 33a and 34a are cut so as to form, for the first, a first transverse section 33 which will form the extrados platform 23 of the blade 10 and, for the second, a second cross section 34 which will form the intrados platform 24 of the blade 10. It should be noted here that the qualifiers "transverse" and "longitudinal" are given as a function of the final position of the section 10 considered, the transverse sections being necessarily woven longitudinally before being folded transversely. Once the free sections 33a and 34a have been cut, the float wires resulting from the layer outlets made on the surface of the second longitudinal section 32 and the free sides 33a, 34a are accessible and can be shaved. The layer outlets 35 and 36 then form withdrawals which will result in the recesses 43 of the distal end of the platforms 23, 24 The preform 30 may then be wetted to soften it and allow easier decadding of the fibers. The main preform 30 is then introduced into a forming mold whose internal space is adjusted to the desired geometry for the preform 30. The preform 30 is then dried so that the latter stiffens, thus blocking the geometry imposed during Formatting. As shown in FIG. 6, the foils 40 are then attached to the end of the transverse sections of the main preform 30, their upper tab engaging in the recesses 35 and 36 of the main preform. The preform thus completed 30 'is finally disposed in an injection mold, to the dimensions of the desired final blade 10, in 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 co-injection then makes it possible to secure the foils 40 on the main preform 30 so that, at the end of this step, the blade 10 made of composite material provided with foils 40 is obtained in one piece. Naturally, the The above-described example of weaving is only one of a number of other possibilities 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 many examples of weavings in document WO 2014/076408. In addition, in another example, the main preform 30 could first be consolidated by injection of the matrix then the foils 40 could be reported in a second time by gluing, riveting, bolting or any other method of attachment. In such a case, the shrinkage 43 could be obtained by machining the platform 23 after consolidation rather than by producing layer outlets during weaving. In a first alternative embodiment, shown in FIG. 7, the lower surface of the distal end of the platform 23 'may also have a recess 44' whose depth corresponds to the thickness of the lower lug 42 'of the foil 40. In a second variant embodiment, represented in FIG. 8, the foils 40a of the extrados platforms 23 have at their distal end a groove 45 while the foils 40b of the intrados platforms 24 have at their distal end a rib 46 capable of cooperating with the groove 45 of the foil 40a neighbor. Of course, the reverse configuration is possible. FIGS. 9 and 10 illustrate a second example of blade 110. In this second example, the stiffener takes the form of a box 150 having a rectangular or trapezoidal section and extending against the lower surface of the platforms 123, 124, all along the distal end. This box is hollow over its entire length and thus forms cavities 151 and 152 opening axially upstream and downstream respectively.
    [0023] Such a blade 110 can be obtained using a manufacturing method similar to that of the first example. A similar main fibrous preform is thus woven, then the caissons 150 are brought against the lower surface of the transverse sections of the main preform, for example by means of rivets 159 or points of glue, the completed preform then undergoing a co-operation. injection.
    [0024] Alternatively, the boxes 150 may be reported by gluing, riveting, bolting or any other method on an already consolidated composite blade resulting for example from the main fiber preform 30 described above.
    [0025] In addition, it is noted that it is possible to provide these boxes 150 with an anti-overlap device similar to that of FIG 6, the extrados boxes carrying for example a groove and the boxes intrados a corresponding rib. FIG. 11 illustrates a third example of blade 210. In this third example, the stiffener takes the form of a roller 260 having a circular or oval section and extending all along the distal end of the platforms 223, 224, enclosed in the thickness of the latter. As can be seen in FIG. 12, this roller 260 is hollow over its entire length and thus forms cavities 261 and 262 opening axially upstream and downstream respectively. This roller also has quills 263 distributed on its outer surface. The manufacture of such a blade 210 is similar to the first and second examples presented above. A main fiber preform 230 is first of all woven similarly to the previous examples, but with the longer cross sections 233 being provided. Once the weaving of the main preform 230 has been completed, the transverse sections 233 are folded transversely and then the distal end of each transverse section 233 is wound around a roller 260: the quills 263 of the roll then penetrate between the fibers of the transverse section 233. The preform thus completed is then consolidated by injection of a matrix in a similar manner to the preceding examples.
    [0026] FIG. 13 schematically illustrates in axial section the blade 210 mounted on the fan disk 211. In this FIG. 13, the upstream shell 213 and the downstream drum 214 of the fan 2 are shown: these two members 213 and 214 are located at the rotor and thus rotate synchronously with the disk 211 and the blades 210.
    [0027] It will be noted in this FIG. 13 that the upstream collar 213 is equipped with a plurality of fingers 213a engaging in the upstream cavity 261 of the rollers 260 while the downstream drum 214 is also equipped with a plurality of fingers 214a engage in the downstream cavity 262 of the rollers 260, such devices for retaining the rollers 260 and thus avoid excessive deformation of the platforms 223 5 in operation. It is moreover understood that such a retaining mechanism is also possible with the box-shaped stiffeners 150 of the second example. 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 examples of embodiment, or consider others, all remaining within the scope of the invention. In addition, the various features of these modes or embodiments may be used alone or may be combined with one another. 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 feature described in connection with a mode or example embodiment may be similarly applied to another embodiment or embodiment.
    权利要求:
    Claims (13)
    [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) , capable of forming a first platform (23), in which the preform (30 ') further comprises at least one stiffener (40) attached to the main fibrous preform (30) along at least one segment of the distal edge of the first transverse section (33).
    [0002]
    2. Preform according to claim 1, wherein the stiffener is a foil (40) having a U-shaped section and enclosing the distal edge of the first transverse section (33).
    [0003]
    3. Preform according to claim 2, wherein the upper end of the foil (40) engages in a recess (35) formed in the upper surface of the first transverse section (33) so that the upper surface of the foil ( 40) is flush with the upper surface of the first transverse section (33).
    [0004]
    4. Preform according to claim 1, wherein the stiffener is a box (150) attached against the lower surface of the first transverse section.
    [0005]
    5. Preform according to any one of claims 1 to 4, wherein the stiffener (40a) has an axial rib or an axial notch (45) configured to cooperate respectively with the axial notch or the axial rib (46) of a platform stiffener (40b) of a neighboring dawn. 3035676 16
    [0006]
    6. Preform according to claim 1, wherein the stiffener is a roller (260), preferably provided with stitches (263), around which is wound the distal end of the first transverse section 5 (233).
    [0007]
    7. Preform according to any one of claims 4 to 6, wherein the stiffener (150) has an axial inner cavity (151, 152). 10
    [0008]
    8. Preform according to any one of claims 1 to 8, wherein the main fiber preform (30) comprises a second transverse section (34) extending transversely from the junction between the first and second longitudinal sections (31, 32). ), in the extension and opposite of the first transverse section (33), capable of forming a second platform (24), and wherein the preform (30 ') further comprises a second stiffener (40) attached to the main fibrous preform (30) along at least one segment of the distal edge of the second transverse section (34). 20
    [0009]
    9. A turbine engine blade, comprising a blade root (21), a blade portion (22) extending upwardly from the blade root (21), a platform (23) made of material composite and extending transversely to the blade portion (22) at the junction between the blade root (21) and the blade portion (22), wherein the platform (23) is provided with a stiffener (40) extending along at least one segment of the distal edge of said platform (23).
    [0010]
    10. The blade according to claim 9, made integrally of a composite material by means of a preform (30 ') according to any one of claims 1 to 8, said preform (30') having been shaped in a mold and embedded in a matrix, preferably of organic type. 3035676 17
    [0011]
    11. A blade according to claim 9, wherein the stiffener (40) is attached to the platform (23).
    [0012]
    Turbomachine bladed wheel, comprising a plurality of blades (10) according to any one of claims 9 to 11.
    [0013]
    13. A turbomachine, comprising at least one blade (10) according to any one of claims 9 to 11 or a bladed wheel (2) according to claim 12. 10
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    同族专利:
    公开号 | 公开日
    EP3288736A1|2018-03-07|
    US20180119550A1|2018-05-03|
    BR112017023307A2|2018-08-14|
    CN107548428B|2019-12-17|
    RU2017141349A3|2019-07-26|
    RU2017141349A|2019-05-29|
    FR3035676B1|2017-05-12|
    CA2984127A1|2016-11-03|
    JP2018523040A|2018-08-16|
    RU2699649C2|2019-09-06|
    CN107548428A|2018-01-05|
    EP3288736B1|2019-03-13|
    JP6816022B2|2021-01-20|
    US10519776B2|2019-12-31|
    WO2016174343A1|2016-11-03|
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    FR3037097B1|2015-06-03|2017-06-23|Snecma|COMPOSITE AUBE COMPRISING A PLATFORM WITH A STIFFENER|
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    US10731479B2|2017-01-03|2020-08-04|Raytheon Technologies Corporation|Blade platform with damper restraint|FR3035675B1|2015-04-29|2017-05-12|Snecma|DAWN WITH PLATFORMS COMPRISING INSERTS|
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    US10738630B2|2018-02-19|2020-08-11|General Electric Company|Platform apparatus for propulsion rotor|
    FR3089844B1|2018-12-13|2022-02-18|Safran Aircraft Engines|Fiber preform of a turbomachine part|
    法律状态:
    2016-04-12| PLFP| Fee payment|Year of fee payment: 2 |
    2016-11-04| PLSC| Search report ready|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
    FR1553849A|FR3035676B1|2015-04-29|2015-04-29|DAWN WITH PLATFORMS POSSESSING A STIFFENER|FR1553849A| FR3035676B1|2015-04-29|2015-04-29|DAWN WITH PLATFORMS POSSESSING A STIFFENER|
    JP2017556595A| JP6816022B2|2015-04-29|2016-04-26|Blade with land containing reinforcement|
    BR112017023307-0A| BR112017023307A2|2015-04-29|2016-04-26|preform blade, blade wheel and turbomachine|
    CN201680024880.3A| CN107548428B|2015-04-29|2016-04-26|Blade comprising a platform with a reinforcement|
    EP16722311.4A| EP3288736B1|2015-04-29|2016-04-26|Blade comprising lands with a stiffener|
    RU2017141349A| RU2699649C2|2015-04-29|2016-04-26|Blade equipped with shelves, having stiffness element|
    US15/569,665| US10519776B2|2015-04-29|2016-04-26|Blade comprising lands with a stiffener|
    CA2984127A| CA2984127A1|2015-04-29|2016-04-26|Blade comprising lands with a stiffener|
    PCT/FR2016/050979| WO2016174343A1|2015-04-29|2016-04-26|Blade comprising lands with a stiffener|
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