• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a blade (1) made of an organic matrix composite material for a gas turbine engine comprising: an aerodynamic blade (8) extending transversely between a leading edge (4) and a trailing edge (6) ), and a metal foil (3) positioned on the leading edge of the blade, said metal foil having two wings (3a, 3b) extending on either side of said leading edge on a part of lateral faces of the infield (7) and extrados (5) blading so that the foil matches the profile of the leading edge, the metal foil being fixed on the leading edge of the blading by at least a sewing thread (9), characterized in that said sewing thread comprises at least one outer thread segment (20) extending substantially transversely between a hole (42a) formed through a wing of the foil and a passage (41) practiced in a portion of the vane having at least one uncoated surface by the metallic foil.
    公开号:FR3033725A1
    申请号:FR1552114
    申请日:2015-03-16
    公开日:2016-09-23
    发明作者:Gilles Pierre-Marie Notarianni；Matthieu Arnaud Gimat；Jeremy Guivarc'h；Thibault Ruf
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to a blade of an organic matrix composite material with an integrated metal leading edge for a gas turbine engine and a process for attaching a metal foil to a fibrous preform. such a dawn. In the aeronautical field, in particular that of aircraft turbojet engines, the reduction in the mass of the parts constituting the turbojet engine is a major problem both in terms of the manufacturing costs of these parts, as well as in terms of energy efficiency and turbojet engines. This problem quickly led to the development of composite material parts, including organic matrix (CMO) to replace the traditional metal parts in different parts of the turbojet engine. However, the realization of blades made of organic matrix composite material poses certain problems, in particular in terms of impact resistance. Indeed, the location of these blades, for example in the blower or the compressor, can expose them to impacts of objects of various natures (birds, gravel, ice blocks, sand, etc.) 20 and the blades in CM0 can then be damaged or eroded. A known solution is to protect the leading edge of these blades with a metal foil glued to the leading edge, the foil being for example titanium. The above solution provides good dawn protection in case of object impact, but it is possible that the foil will come off in some places depending on the impact energy. In addition, such detachments entail in particular additional repair costs and an impairment of the performance of the turbomachine due to the degradation of the aerodynamics of the blade, which is not desirable. OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to overcome such drawbacks by proposing to effectively fix a metal foil 35 to a blade made of organic matrix composite material so as to limit the delamination of the foil, in particular in the case of impact of objects. This goal is achieved by means of a blade made of an organic matrix composite material for a gas turbine engine comprising: an aerodynamic blade extending transversely between a leading edge and a trailing edge, and a metal foil positioned on the leading edge of the vane, said metal foil comprising two wings extending on either side of said leading edge on a portion of the lateral faces of the vane forming intrados and extrados so that the The foil conforms to the profile of the leading edge, the metal foil being attached to the leading edge of the blade by at least one sewing thread. According to the invention, the sewing thread comprises at least one outer wire segment extending substantially transversely between a hole formed through a wing of the foil and a passage made in a portion of the blade having at least one face not covered by metallic foil. The metal foil is mechanically fastened to the dawn by a sewing thread which ensures an effective maintenance on the leading edge of the blade. The seam of the foil is made in such a way that exposed outer wire segments on the foil are oriented transversely, that is to say in the direction of flow of air on the blade when it is rotating. . The aerodynamics of the dawn is thus very little affected by the presence of these outer wire segments. In addition, the changes in the aerodynamics of the blade due to these wire segments are negligible compared to segments of wires which would be oriented in a direction different from that of the flow of air on the blade. operation. Therefore, there is advantageously no need to machine the foil to make grooves to hide these wire segments, which limits the difficulties and production costs.
    [0002] Preferably, the two wings of the metal foil are interconnected by the sewing thread. With such an arrangement, the two wings of the metal foil enclose the leading edge of the blade, which ensures a better hold of the metal foil that pinches the leading edge.
    [0003] According to a first embodiment of the invention, the sewing thread binding the two wings of the metal foil together has at least one seam loop which comprises: a first segment of inner thread passing through the vane in the direction of its thickness from its extrados face to its intrados face by the passage in the blade, a first outer wire segment extending from a free end of the first inner wire segment substantially transversely to the side of the intrados face of the blading, a second inner wire segment extending from a free end of the first outer wire segment and traversing the blade in the direction of its thickness from its intrados face to its extrados face, a second segment outer wire extending from the free end of the second inner wire segment substantially transversely to the extrados face side of the blade to the first segment t of inner wire, and a third inner wire segment traversing the blade in the direction of its thickness from its extrados face to its intrados face along the path of the first inner wire segment. When the sewing thread has a plurality of sewing loops, the outer thread segments which connect two sewing loops together can be advantageously positioned on the parts of the vane not covered by the foil to be hidden within those here, so as not to form an aerodynamic step. According to a second embodiment of the invention, the sewing thread linking the two wings of the metal foil together comprises at least a double seam loop which comprises: a first segment of inner wire passing through the blade in the direction of its thickness from its extrados face towards its intrados face by the passage in the blade, a first segment of outer wire extending from a free end of the first inner wire segment substantially transversely to the side of the intrados face of the blade, a second inner wire segment extending from a free end of the first outer wire segment and traversing the blade 3033725 4 in the direction of its thickness from its intrados face to its extrados face, a second segment outer wire extending from a free end of the second inner wire segment substantially transversely to the side of the extrados face of the blade in the op direction placed on the first inner wire segment, a third inner wire segment extending from a free end of the second outer wire segment and traversing the blade in the direction of its thickness from its extrados face to its lower face. a third outer wire segment extending from a free end of the third inner wire segment substantially transversely to the underside side of the blade to the second inner wire segment, a fourth wire segment interior extending from a free end of the third outer wire segment and passing through the blade along the path of the second inner wire segment, a fourth outer wire segment extending from a free end of the outer wire segment; fourth inner wire segment substantially transversely on the extrados face side of the blade to the first inner wire segment, and a fifth uth inner wire segment extending from a free end of the fourth outer wire segment and traversing the blade along the path of the first inner wire segment.
    [0004] The blade may comprise a plurality of seam loops and / or double seam loops spaced longitudinally from one another over the height of the blade. The same sewing thread can travel at least twice a seam loop or a double seam loop.
    [0005] The invention also relates to a method for attaching a metal foil to a gas turbine preform of aeronautic gas turbine engine, the method comprising: a step of positioning the metal foil on a leading edge of the preform fibrous dawn, a step of attaching the metal foil to the fibrous preform of the blade, the fixing step comprising forming at least one seam loop with at least one sewing thread, said sewing thread comprising at least one outer thread segment extending substantially transversely between a hole formed through a wing of the foil and a passage made in a portion of the fibrous preform having at least one face not covered by the foil metallic. According to an embodiment of the method, to form a seam loop, the seam first passes through the vane from its extrados face to its intrados face at the passage in the preform so as to form a first segment of inner wire, said wire then passes through the preform in the direction of its thickness from its intrados face to its intrados face through the holes formed on each wing of the foil so as to form a second segment of inner wire, the first segment inner wire and the second inner wire segment being connected by a first transversely extending outer wire segment, and said wire finally traverses the preform in the direction of its thickness following the path of the first inner wire segment so as to forming a third inner wire segment, the second inner wire segment and the third inner wire segment being bonded by a second outer wire segment transversely extending.
    [0006] Preferably, the method may further comprise a step of injecting a thermoplastic resin into an injection tool in which has been placed the fibrous preform of the blade on which the metal foil has been fixed so as to drown the sewing thread in the resin and overmold the metal foil.
    [0007] This additional step advantageously makes it possible to reduce the size of the steps formed by the longitudinal outer wire segments connecting the different loops, while still ensuring better hold of the metal foil on the blade since it is overmolded. The free ends of the sewing thread are embedded in the resin during this step, and the foil is formed on the leading edge by the material front of the injected resin to best marry the leading edge of the resin. blading. The invention also relates to a turbomachine comprising a blade as described above or comprising a metal foil 35 fixed on a fibrous blade preform by a method as described above.
    [0008] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will be apparent from the description given below, with reference to the accompanying drawings which illustrate exemplary embodiments without any limiting character. In the figures: FIG. 1 schematically represents a turbomachine fan blade provided with a metal foil; FIG. 2 is a diagrammatic view of a blade according to one embodiment of the invention, FIG. FIG. 4 is a diagrammatic view of a blade according to another embodiment of the invention, FIG. 5 is a view of the blade of FIG. in cross-section of the blade of FIG. 4 along the plane V; FIG. 6 is a longitudinal sectional view of the blade of FIG. 4 along the plane VI; FIG. 7 is a schematic view of a According to a third embodiment of the invention, FIG. 8 is a cross-sectional view of the blading of FIG. 7 along plane VIII, and FIG. 9 is a diagrammatic view of a blading according to FIG. a fourth embodiment of the invention.
    [0009] DETAILED DESCRIPTION OF THE INVENTION FIG. 1 very schematically represents a blade 1 of an aeronautical gas turbine engine fan made of an organic matrix composite material.
    [0010] In a manner known per se, the blade 1 comprises a foot 2 and an aerodynamic vane 8 intended to be located in the air flow passing through the turbomachine. The blading 8 extends longitudinally in a first direction along the axis XX from the foot 2 to an apex of the blade, extends transversely in a second direction along the axis YY between an edge of 4 and a trailing edge 6, and extends in a third direction along the axis ZZ perpendicular to the axes XX and YY between a lateral face 7 and an extrados side face 5 (Figure 2). The leading edge 4 of the blade is covered by a metal foil 3 fixed to it and acting as a protective reinforcement. This foil comprises two wings 3a, 3b (Figure 2) which extend on either side of the leading edge 4 on a portion of the lateral faces of the blade forming extrados 5 and intrados 7. In a manner known per se the metal foil 3 may be titanium, nickel, aluminum, or any other metal or alloy or metal matrix composite. According to the invention, the metal foil 3 is sewn by means of a seaming thread at the blading 8. The seam of the blading can be performed with silicon-titanium alloy seam threads made of carbon. , KevlarC), metal, etc. A method of fixing the metal foil 3 on a fibrous preform to achieve the blading 8 of Figures 2 and 3 will now be described. The seaming operations of the foil are carried out on a fibrous preform of the blade 1 to be produced, prior to a resin injection step, on which the metal foil 3 has been positioned. In a manner known per se, the fibrous preform can be made by three-dimensional weaving or multilayer of carbon fibers, glass, SIC, metal, etc. According to a first embodiment of the invention, the two wings 3a, 3b of the metal foil 3 are sewn together by a wire 9 via a set of seam loops 10a, 10b, 10c, 10d regularly spaced along the height of the 8.
    [0011] The seam loop 10b starts with a first end of thread 12 that can be tied to another seam loop 10c. To make a seam loop 10b, the thread is passed through an inlet 40a located on the extrados face 5 of a passage 41 in a part of the vane 8 not covered by the metal foil 3, and is brought out on the intrados face 7 through an outlet 40b of the passage 41. The portion of the wire passing through the vane at the end of this step is a first inner wire segment 14. The wire is then passed through a hole 42b formed in the wing 3b, which forms a first outer wire segment 16 which extends transversely between the outlet 40b and the hole 42b. The yarn then passes through the vane from its intrados face 7 to its extrados face 5 at a passage 43 between the hole 42b and the opposite hole 42a formed in the flange 3a (i.e. that the holes 42b and 42a are substantially aligned along the axis ZZ) forming a second inner wire segment 18. The next step is to go through the vane again at the passage 41 from the upper surface 5 towards the 7, which defines a second outer wire segment 20 extending transversely between the hole 42a and the inlet 40a, and a third inner wire segment 22 which follows the path of the first inner wire segment 14 and exits at the outlet 40b. The seam loop 10b terminates with a thread end 24 which can then be used to make another seam loop 10a. It is possible to repeat these operations several times to increase the strength of a seam loop. For example, the same sewing thread can be passed twice through the same sewing loop. The seam loops 10a, 10b, 10c, 10d are straddling the wings 3a, 3b of the metal foil 3 and the part of the blade 8 not covered by the metal foil.
    [0012] The longitudinal wire ends 12, 24 connecting two stitching loops can be brought closer to the edges of the foil to reduce the impact on the aerodynamics of the blade 1. FIGS. 4, 5 and 6 show schematically a blade according to a second embodiment of the invention.
    [0013] In this embodiment of the invention, the two wings 3a, 3b of the metal foil 3 are sewn together by a wire 9 'via a set of double seam loops 110a, 110b, 110c, 110d regularly spaced over the height The double seam loop 110c starts with a first thread end 112 which can be linked to another double seam loop 110d.
    [0014] 303 3 7 2 5 9 To produce a double seam loop 110c the yarn is passed through an inlet 140a situated on the extrados face 5 of a passage 141 in a part of the blade 8 not covered by the metal foil 3, and is brought out on the intrados face 7 by an outlet 140b of the passage 141 so that it passes through the vane 8. The portion of the wire passing through the vane 8 during this step is a first inner wire segment 114. The wire is then passed through a hole 142b formed in the flange 3b, which forms a first outer wire segment 116 which extends transversely between the outlet 140b and the hole 142b.
    [0015] The yarn then passes through the vane 8 at a passage 143 between the hole 142b and a hole 142a formed in the flange 3a opposite the hole 142b forming a second inner thread segment 118. The next step is to passing through the blade at the passage 145 located between two opposed holes 144a and 144b respectively formed in the face 3a and the face 3b closer to the leading edge than the holes 142a and 142b, which forms a second segment of wire Outer 120 extends transversely between the hole 142a and the hole 144a, as well as a third inner wire segment 122 traversing the blade from the extrados face 5 to the intrados face 7 between the holes 144a and 144b. The wire then again passes through the vane at the passage 143 between the holes 142b and 142a from the intrados face 7 to the extrados face 5, which forms a third outer wire segment 124 extending transversely between the hole 144b and the hole 142b, as well as a fourth inner wire segment 126 traversing the blade between the holes 142b and 142a along the path of the second inner wire segment 118. The double seam loop 110c ends with the crossing by the the vane sewing thread 8 from its extrados face 5 to its intrados face 7 at the passage 141, which forms a fourth outer thread segment 128 extending transversely between the hole 142a and the inlet 140a, and a fifth inner wire segment 130 traversing the blade between the input 140a and the output 140b following the path of the first inner wire segment 114.
    [0016] The double seam loop 110c ends with one end of thread 132 which can then be used to make another double seam loop 110b. The longitudinal wire segments 112, 132 connecting two double seam loops can be brought closer to the edges of the foil to reduce their impact on aerodynamics of the blade 1. To correctly perform a double seam loop 110c according to the invention, it is necessary to that the holes 142a, 144a and 142b, 144b on the foil, the inlet 140a and the outlet 140b of a passage are aligned in a transverse direction on each face. It is possible to repeat these operations several times to increase the strength of a double seam loop. For example, the same sewing thread can be passed twice through the same double seam loop.
    [0017] The seam of the metal foil on the fiber preform can be achieved by using both seam loops and double seam loops distributed over all or a portion of the height of the vane. It is preferable to insert the free ends of the wire 9, 9 'after the finished seam, inside the woven fiber preform so that they are embedded during the injection. Figures 7 and 8 show schematically a blade 8 according to a third embodiment of the invention. The wing 3'h extending on the lower face 7 of the blading is larger than the wing 3a extending on the extrados face 5. In one case, the outlet 40b of the passage 41 in the blading 8 illustrated in Figures 2 and 3 is in front of a hole 40'b formed in the wing 3'b of the metal foil which now covers an additional portion of the intrados face 7. There is thus an additional row 30 of holes aligned longitudinally on the wing 3'b. It is possible to perform a seam loop 10'a, 10'b, 10'c, 10'd in the same manner as in the embodiment of FIGS. 2 and 3, replacing the outlet 40b of the passage 41 with the hole 40 'b. It is also conceivable to make double stitching loops in the same manner as illustrated in FIGS. 4, 5 and 6 by adding a row of longitudinally aligned and opposed holes on the flange wings 3a and 3b. metallic 3 '. The presence of the holes 40'b on the wing 3'b covering a portion of the intrados face 7 imposes the presence of steps on the metal foil formed by longitudinal outer segments 24. It will be possible to adapt the manner of sewing so as to maximize the number of these longitudinal outer segments on the wing 3'b and to minimize the number of longitudinal outer segments present on the upper surface 5 as a function of the number of loops that the we will achieve. Indeed, it is preferable to reduce the number of steps on the upper surface 5 to minimize the impacts on the aerodynamics of the dawn. In another case (not illustrated), the metal foil 3 'is not pierced with additional holes 40'b on its flange 3'b, the seam can then be performed identically to the embodiments of FIGS. Figure 9 illustrates a fourth embodiment of the invention. A return loop 10 "is made to reinforce the attachment of the metal foil to the leading edge, preferably in the vicinity of the longitudinal end of the blade The return loop 10" comprises a seam loop 10 ' identical to the loops 10'a, 10'b, 10'c, 10'd of the embodiment illustrated in FIGS. 7 and 8. In addition, after making a seam loop 25 ', the ends of the yarn 12, 14 of the seam loop 10 'again pass through the vane at the passage 39 located between a hole 38b formed in the wing 3'b and an inlet 38a on the upper surface 5 of the vane. The hole 38b and the inlet 38a are substantially aligned longitudinally with the hole 40'b and the inlet 40a.
    [0018] Once the seam is finished, the ends of a seam loop 10'a, 10'b, 10'c, 10'd or a return loop 10 "can be inserted into the fibrous preform of the dawn In order to be subsequently embedded in a resin during the injection, after the seaming of the foil on the fibrous preform of the blade, the assembly can be placed in an injection mold in order to injecting a thermoactive or thermoplastic resin and obtaining, once the solidified resin, a blade 1 made of an organic matrix composite material provided with a metal foil like that of FIG. 1. During the injection, the material front created by the resin being injected forms the foil on the leading edge of the blade, drowns the seams 5 of the seam and overmoulds the foil.The mentions made to the faces "intrados" and "extrados" of the blade interchangeable interchangeably in the above description and should not be interpreted exhaustively.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A blade (1) made of an organic matrix composite material for a gas turbine engine comprising: an aerodynamic blade (8) extending transversely between a leading edge (4) and a trailing edge (6), and a foil metal (3, 3 ') positioned on the leading edge of the blade, said metal foil having two wings (3a, 3b, 3'b) extending on either side of said leading edge on a part of the lateral faces of the vane (7) and suction surface (5) so that the foil matches the profile of the leading edge, the metal foil being fixed on the leading edge of the vane by at least one sewing thread (9, 91 characterized in that said sewing thread comprises at least one outer thread segment (20, 128) extending substantially transversely between a hole (42a, 142a) formed through a wing of the foil and a passage (41, 141) formed in a portion of the blade having at least one uncoated surface e by the metallic foil.
    [0002]
    2. blade according to claim 1, characterized in that the two wings (3a, 3b, 3'b) of the metal foil are interconnected by the sewing thread (9, 9 ').
    [0003]
    3. blade according to claim 2, characterized in that the sewing thread binding the two wings of the metal foil together has at least one seam loop (10a, 10b, 10c, 10d, 10'a, 10'b, 10 'c, 10'd) which comprises: a first inner wire segment (14) traversing the blade in the direction of its thickness from its extrados face (5) to its lower face (7) through the passage (41) in the blade, a first outer wire segment (16) extending from a free end of the first inner wire segment (14) substantially transversely to the side of the intrados face (7) of the blade, a second inner wire segment (18) extending from a free end of the first outer wire segment (16) and traversing the blade in the direction of its thickness from its intrados face (7) to its extrados face (5), a second outer wire segment (20) extending from the free end of the second inner wire segment (18) substantially transversely on the side of the extrados face (5) of the blade to the first inner wire segment (14), and a third inner wire segment (22) passing through the blade in the direction of its thickness from its extrados face (5) to its intrados face (7) following the path of the first inner wire segment (14). 10
    [0004]
    4. blade according to any one of claims 2 to 3, characterized in that the sewing thread connecting the two wings (3a, 3b) of the metal foil between them comprises at least one double seam loop (110a, 110b, 110c 110d) which comprises: a first inner wire segment (114) traversing the blade in the direction of its thickness from its extrados (5) to its lower surface (7) through the passage (141) in the blade a first outer wire segment (116) extending from a free end of the first inner wire segment substantially transversely to the side of the airfoil face (7) of the blade, a second inner wire segment ( 118) extending from a free end of the first outer wire segment (116) and traversing the blade in the direction of its thickness from its intrados face (7) to its extrados face (5), a second outer wire segment (120) extending from a free end of the second wire an inner wire groove (118) substantially transversely to the upper surface side (5) of the blade in the direction opposite to the first inner wire segment (114), a third inner wire segment (122) extending from of a free end of the second outer wire segment (120) and passing through the blade in the direction of its thickness from its extrados face (5) to its lower face (7), a third outer wire segment (124) s extending from a free end of the third inner wire segment (122) substantially transversely to the side of the intrados face (7) of the blading towards the second inner wire segment (118), a fourth inner wire segment (126) extending from a free end of the third outer wire segment (124) and traversing the blade along the path of the second inner wire segment (118), a fourth segment of outer wire (128) extending to p forming a free end of the fourth inner wire segment (126) substantially transversely on the upper surface side (5) of the blade to the first inner wire segment (114), and a fifth inner wire segment ( 130) extending from a free end of the fourth outer wire segment (128) and traversing the blade along the path of the first inner wire segment (114).
    [0005]
    5. A blade according to any one of claims 3 or 4, characterized in that it comprises a plurality of seam loops (10a, 10b, 10c, 10d, 10'a, 10'b, 10'c, d) and / or double seam loops (110a, 110b, 110c, 110d) spaced longitudinally from one another over the height of the blade. 20
    [0006]
    6. blade according to any one of claims 3 to 5, characterized in that the same sewing thread (9, 9 ') travels at least twice a seam loop (10a, 10b, 10c, 10d, 10' a, 10'b, 10'c, 10'd) or a double seam loop (110a, 110b, 110c, 110d). 25
    [0007]
    7. A method of fixing a metal foil (3, 3 ') on a gas turbine preform (1) of a gas turbine engine, the method comprising: a step of positioning the metal foil on an edge of etching (4) of the fibrous preform of the blade, a step of fixing the metal foil on the fibrous preform of the blade, the fixing step comprising forming at least one seam loop (10a, 10b , 10c, 10d, 10'a, 10'b, 10'c, 10'd) with at least one sewing thread (9), said sewing thread having at least one outer thread segment (20) extending substantially transversely between a hole (42a) formed through a wing (3a) of the foil and a passage (41) formed in a portion of the fibrous preform having at least one face not covered by the metal foil.
    [0008]
    8. A method according to claim 7, wherein for forming a seam loop (10a, 10b, 10c, 10d, 10'a, 10'b, 10'c, 10'd), the sewing thread (9 ) firstly passes through the vane from its extrados face (5) towards its underside (7) at the passage (41) in the preform so as to form a first inner wire segment (14), which wire then passes therethrough the preform in the direction of its thickness from its intrados face (7) to its intrados face (5) through the holes (42b, 42a) formed on each flange (3a, 3b, 3'b) of the foil so forming a second inner wire segment (18), the first inner wire segment (14) and the second inner wire segment (18) being bonded by a first transversely extending outer wire segment (16), and said The wire finally traverses the preform in the direction of its thickness following the path of the first inner wire segment (14) so as to form a third inner wire segment. r (22), the second inner wire segment (18) and the third inner wire segment (22) being connected by a second transversely extending outer wire segment (20). 20
    [0009]
    9. Method according to any one of claims 7 or 8, further comprising a step of injecting a thermoactive or thermoplastic resin into an injection tool in which has been placed the fibrous preform of the blade (1) on which the metal foil (3, 3 ') has been fixed so as to embed the sewing thread (9) in the resin and to overmold the metal foil.
    [0010]
    10. A turbomachine comprising a blade according to any one of claims 1 to 6 or comprising a metal foil fixed to a fibrous blade preform by a process according to any one of claims 7 to 9.
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    US10240463B2|2019-03-26|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2718101A1|1994-04-05|1995-10-06|Mtu Muenchen Gmbh|Blade according to a fiber-based composite manufacturing method having a protective profile in case of encountering foreign bodies, ice blocks, birds or others.|
    FR2988785A1|2012-03-28|2013-10-04|Snecma|Blade for double flow turboshaft engine, has reinforcement extended into longitudinal dimension from edge, where reinforcements include anchoring units and/or fixing units for fixing reinforcements on blade|FR3090465A1|2018-12-20|2020-06-26|Safran|PROCESS FOR MANUFACTURING A TURBOMACHINE PART IN COMPOSITE MATERIAL AND CORRESPONDING TURBOMACHINE PART|US6431837B1|1999-06-01|2002-08-13|Alexander Velicki|Stitched composite fan blade|FR3008920B1|2013-07-29|2015-12-25|Safran|METHOD FOR MANUFACTURING A BLADE IN COMPOSITE MATERIAL WITH INTEGRATED METAL ATTACK FRAME FOR AERONAUTICAL GAS TURBINE ENGINE|
    FR3041684B1|2015-09-28|2021-12-10|Snecma|DAWN INCLUDING AN ATTACK EDGE SHIELD AND PROCESS FOR MANUFACTURING THE DAWN|
    ES2799935T3|2016-02-29|2020-12-22|Airbus Operations Sl|Aircraft aerodynamic profile with a dotted trailing edge and manufacturing procedure for the same|
    法律状态:
    2016-02-24| PLFP| Fee payment|Year of fee payment: 2 |
    2016-09-23| PLSC| Publication of the preliminary search report|Effective date: 20160923 |
    2017-03-15| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 6 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 7 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1552114A|FR3033725B1|2015-03-16|2015-03-16|DAWN IN ORGANIC MATRIX COMPOSITE MATERIAL COMPRISING A METAL CLINKER, AND METHOD FOR FIXING A METAL CLINKER ON A FIBROUS WAVE PREFORM.|FR1552114A| FR3033725B1|2015-03-16|2015-03-16|DAWN IN ORGANIC MATRIX COMPOSITE MATERIAL COMPRISING A METAL CLINKER, AND METHOD FOR FIXING A METAL CLINKER ON A FIBROUS WAVE PREFORM.|
    GB1604141.0A| GB2538350B|2015-03-16|2016-03-10|A blade made of organic matrix composite material provided with a metal strip, and a method of fastening a metal strip on a blade fiber preform|
    US15/070,585| US10240463B2|2015-03-16|2016-03-15|Blade made of organic matrix composite material provided with a metal strip, and a method of fastening a metal strip on a blade fiber preform|
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