• 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 (7) comprising: - a composite material structure (17) comprising a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fiber reinforcement is embedded, the composite material structure (17) comprising a part aerodynamically profiled blade (21) and a blade root portion (22), the blade root portion (22) comprising two portions (23) each connected to the blade portion (21), - a workpiece blade root fastener (9) comprising a wall (25) defining a cavity (28) and an opening (29) formed in the wall (25), the composite material structure (17) extending through the opening (29) so that the blade portion (21) is located outside the attachment piece (9) and the blade root portion (22) is located within the the cavity (28), and - a locking piece (19) disposed in the cavity (28), between the two portions (23) of the blade root portion (22), for holding ir the two portions (23) spaced apart from each other so as to oppose a withdrawal of the blade root portion (22) of the cavity (28) via the opening (29).
    公开号:FR3080322A1
    申请号:FR1853509
    申请日:2018-04-20
    公开日:2019-10-25
    发明作者:Vivien Mickael Courtier；Anthony BINDER
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The invention relates to a blade comprising a structure made of composite material.
    The invention relates more particularly, but not exclusively, to a blade intended for use in a non-faired fan rotor of an aircraft engine (such as an “Open Rotor” type engine having two rotating propellers or a USF type for "Unducted Single Fan" with a mobile vane and a fixed vane or a turboprop with an architecture with a single propeller) or in a wind turbine rotor.
    STATE OF THE ART
    The advantage of non-faired fan motors is that the diameter of the fan is not limited by the presence of a fairing, so that it is possible to design an engine having a high dilution rate, and by therefore reduced fuel consumption.
    Thus, in this type of engine, the blades of the fan can have a large span.
    In addition, these engines generally include a mechanism for changing the setting angle of the blades in order to adapt the thrust generated by the fan according to the different flight phases.
    However, the design of such blades requires taking into account conflicting constraints.
    On the one hand, the dimensioning of these blades must allow optimal aerodynamic performance (maximizing efficiency and providing thrust while minimizing losses). The improvement in the aerodynamic performance of the fan tends to an increase in the dilution rate (BPR), which results in an increase in the external diameter, and therefore in the size of these blades.
    On the other hand, it is also necessary to guarantee resistance to the mechanical stresses which can be exerted on these blades while limiting their acoustic signature.
    Furthermore, on non-faired fan architectures, the engine is generally started with very open timing. Indeed, a very open setting allows power to be consumed by the torque, which ensures machine safety by guaranteeing low fan speeds.
    However, with a very open setting, the blades undergo a turbulent aerodynamic flow, completely detached, which generates a broadband vibrational excitation. Particularly on large, wide-rope blades, the bending force is intense, although the engine speed is not maximum.
    In normal operation, during the ground and flight phases, the setting is changed (the setting angle is more closed). The aerodynamic flow is therefore perfectly healthy (glued to the aerodynamic profile). The broadband stresses disappear, the rotation speed being higher, and the bending force is controlled.
    Currently, these blades are generally made of metallic material. If the blades of metallic material have good mechanical strength, they have the disadvantage of having a relatively large mass.
    In order to reduce this mass, it is desirable to be able to manufacture these blades from composite material. However, the intense aerodynamic forces to which these blades are subjected could risk damaging the blade and / or the hub in the interface zone between these blades and the hub of the fan rotor. This problem arises more particularly when the blades are connected to the hub by means of pin fasteners.
    SUMMARY OF THE INVENTION
    An object of the invention is to provide a blade including a composite material, suitable for use with a variable timing mechanism, while being able to withstand intense aerodynamic forces.
    This object is achieved in the context of the present invention thanks to a blade comprising:
    a structure in composite material comprising a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement is embedded, the structure in composite material comprising a blade part with aerodynamic profile and a blade root part, the part of blade root comprising two portions each connected to the blade portion,
    - a blade root attachment piece comprising a wall delimiting a cavity and an opening formed in the wall, the structure of composite material extending through the opening so that the blade portion is located at the the outside of the attachment piece and the blade root portion is located inside the cavity, and
    - a blocking piece disposed in the cavity, between the two portions of the blade root portion, to keep the two portions separated from one another so as to oppose a withdrawal of the stem portion dawn of the cavity via the opening.
    The proposed assembly prevents the withdrawal of the blade root portion of the fastener and provides a blade root attachment rigid enough to absorb the broadband vibrational stress caused by a completely unstuck aerodynamic flow.
    The proposed dawn may also have the following characteristics:
    the fibrous reinforcement comprises a portion of the fibrous reinforcement of the blade extending inside the blade portion with an aerodynamic profile, and two portions of the fibrous reinforcement of the blade root extending respectively inside the two portions blade root, and the fiber reinforcement portions of the blade root are woven continuously with the fiber reinforcement portion of the blade,
    - the two fiber reinforcement portions of the blade root are separated by an unbinding zone obtained during the three-dimensional weaving of the fiber reinforcement,
    - the blade comprises adaptation parts arranged in the cavity, on either side of the blade root part, so that each portion of the blade root part is sandwiched between the part of blocking and one of the two adaptation parts,
    - the blade includes a clean cover to be fixed on the attachment piece to keep the locking piece in abutment against the two portions of the blade root portion,
    - the blade includes a seal disposed between the composite material structure and an edge of the opening of the fastener,
    - each portion of the blade root portion has an increasing thickness when one traverses the portion away from the blade portion,
    - the attachment piece has an external surface of revolution, the external surface having two circular grooves suitable for forming raceways for balls,
    - the attachment piece is made of metal.
    The invention also relates to a method of manufacturing a blade from a fiber reinforcement obtained by three-dimensional weaving and from a blade root attachment piece, the fiber reinforcement comprising a portion of blade fiber reinforcement and two fiber reinforcement portions of the blade root, and the blade root attachment piece comprising a wall delimiting a cavity and an opening formed in the wall, the method comprising steps of:
    - Insertion of the fibrous reinforcement portions of the blade root in the cavity of the blade root attachment piece via the opening of the attachment piece, the fibrous blade reinforcement portion extending to the outside of the attachment piece,
    - insertion of a temporary filling part in the cavity of the attachment part, between the two portions of fibrous reinforcement of the blade root, to keep the two portions apart from one another,
    - placement of the fibrous reinforcement, the attachment piece and the temporary filling piece in a mold,
    injection of plastic material into the mold so as to form a structure made of composite material comprising the fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded, the structure made of composite material comprising a blade part with aerodynamic profile and a foot part blade, the blade root portion extending inside the cavity of the blade root attachment piece and comprising two portions each connected to the blade portion,
    - removal of the temporary filling part and insertion of a blocking part between the two portions of the blade root portion, to keep the two portions separated from one another so as to oppose a removal of the blade root portion of the cavity via the opening.
    The method can also include a prior step of:
    - weaving of the three-dimensional fiber reinforcement, with warp strands extending both in the fiber reinforcement portion of the blade and in one of the two fiber reinforcement portions of the blade root.
    The step of weaving the fibrous reinforcement can successively comprise the weaving of a portion of temporary fibrous reinforcement, the weaving of the two fibrous reinforcement portions of the blade root, the two fibrous reinforcement portions of the blade root being separated by an unbinding zone, then weaving the fiber reinforcement portion of the blade, the method further comprising a step of cutting out the provisional fiber reinforcement portion.
    The fibrous reinforcement can be woven so that each portion of the dawn root fibrous reinforcement has a decreasing thickness when the portion is traversed as it approaches the blade portion.
    Each blade root reinforcement portion can be obtained by weaving with successive weft strands, the weft strands having different titrations which decrease when the portion is traversed as it approaches the blade portion.
    The method may further comprise a step of inserting adaptation pieces into the cavity, on either side of the blade root portion, so that each portion of the blade root portion s' extension between the temporary filling part and one of the adaptation parts, before the plastic injection step.
    The method may further comprise a step of heating the plastic material so as to cause polymerization of the plastic material, for example by crosslinking.
    The method can also comprise steps of:
    - insertion of a temporary filling piece between the fibrous reinforcement and an edge of the opening of the attachment piece, before the plastic injection step,
    - removal of the temporary filling part, after the plastic injection step, and mounting of a joint between the composite material structure and an edge of the opening of the fastening part.
    The method may also include a step of fixing a cover on the attachment piece to keep the locking piece in abutment against the two portions of the blade root portion.
    The invention also relates to a gas turbine engine comprising a blower, the blower comprising a hub and blades extending radially from the hub, the blades being as described above.
    In such a gas turbine engine, each blade can be rotatably mounted relative to the hub around a respective timing axis, the engine further comprising an actuation mechanism capable of being controlled to rotate the blades around their setting axes so as to modify the setting angle of the blades.
    PRESENTATION OF THE DRAWINGS
    Other characteristics and advantages will also emerge from the description which follows, which is purely illustrative and not limiting and should be read with reference to the appended figures, among which:
    FIG. 1 schematically represents an example of an engine including a non-shrouded fan,
    FIG. 2 schematically represents a fan blade and an actuation mechanism making it possible to modify the setting angle of the blades of the fan,
    FIG. 3 schematically represents a fan blade in accordance with an embodiment of the invention,
    FIG. 4 schematically represents a structure of composite material forming part of the blade,
    - Figures 5 to 16 schematically illustrate steps of a method of manufacturing a blade according to an embodiment of the invention.
    DETAILED DESCRIPTION OF AN EMBODIMENT
    In FIG. 1, the motor 1 represented is an “Open Rotor” type motor, in a configuration commonly qualified as “pusher” (ie the blower is placed at the rear of the power generator with an air inlet located on the side, right in Figure 1).
    The engine comprises a nacelle 2 intended to be fixed to a fuselage of an aircraft, and a non-faired fan 3. The blower 3 comprises two counter-rotating blower rotors 4 and 5. In other words, when the engine 1 is in operation, the rotors 4 and 5 are rotated relative to the nacelle 2 about the same axis of rotation X (which coincides with a main axis of the motor), in opposite directions.
    In the example illustrated in FIG. 1, the motor 1 is an "Open Rotor" type motor, in "pusher" configuration, with counter-rotating fan rotors. However, the invention is not limited to this configuration. The invention also applies to “Open Rotor” type motors, in “puller” configuration (ie the blower is placed upstream of the power generator with an air inlet situated before, between or just behind the two rotors blower).
    In addition, the invention also applies to engines having different architectures, such as an architecture comprising a fan rotor comprising moving blades and a fan stator comprising fixed blades, or else a single fan rotor.
    The invention is applicable to architectures of the turboprop type (comprising a single fan rotor).
    In FIG. 1, each fan rotor 4, 5 comprises a hub 6 rotatably mounted relative to the nacelle 2 and a plurality of blades 7 fixed to the hub 6. The blades 7 extend substantially radially relative to the axis of rotation X of the hub.
    As illustrated in FIG. 2, the fan 3 further comprises an actuation mechanism 8 making it possible to collectively modify the setting angle of the blades of the rotors, in order to adapt the performance of the engine to the different flight phases. For this purpose, each blade 7 comprises a fastening piece 9 arranged at the foot of the blade. The attachment piece 9 is rotatably mounted relative to the hub 6 around a timing axis Y. More specifically, the attachment piece 9 is rotatably mounted inside a housing 10 formed in the hub 6, by means of balls 11 or other rolling elements.
    The actuation mechanism 8 comprises an actuator 12 comprising a body 13 fixed to the hub 6 and a rod 14 suitable for being driven in translation relative to the body 12. The actuation mechanism 8 further comprises an annular slide 15 mounted integral with the rod 14 and a pin 16 mounted integral with the attachment piece 9. The pin 16 is able to slide in the slide 15 and to rotate relative to the slide 15, so as to convert a translational movement of the rod 14 is a rotational movement of the attachment piece 9, and therefore a rotational movement of the blade 7 relative to the hub 6 around its setting axis Y.
    FIG. 3 shows in more detail, in longitudinal section, the fan blade 7. In this figure, the blade 7 shown comprises a structure made of composite material 17, a blade foot attachment piece 9, two pieces adapter 18, a locking piece 19 and a seal 20.
    The composite material structure 17 comprises a blade part 21 with an aerodynamic profile and a blade root part 22. The blade part 21 with an aerodynamic profile is suitable for being placed in an air flow, when the engine is in functioning, in order to generate a lift. The blade root portion 22 is intended to allow the attachment of the composite material structure 17 to the blade root attachment piece 9.
    The blade root portion 22 includes two portions 23 connected continuously to the blade portion 21 at a junction zone
    24. Each portion 23 has a thickness which increases when the portion 23 is traversed while moving away from the blade part 21 with an aerodynamic profile.
    The blade root attachment piece 9 is formed from metal, for example martensitic steel. The attachment piece 9 comprises a wall 25 having an external surface 26 having a shape of revolution. The external surface 26 has two circular grooves 27 capable of forming raceways for balls or other rolling elements.
    The wall 25 of the attachment piece 9 delimits a cavity 28 suitable for housing the blade root portion 22 of the structure made of composite material 17. The wall 25 has a first opening 29 in the general shape of a rectangle through which s 'extends the structure of composite material 17 so that the blade portion 21 is located outside the attachment piece 9. The attachment piece 9 also has a second opening 30 of generally circular shape, more wider than the first opening 29, and located under the blade root portion 22, on an opposite side of the attachment piece 9 relative to the first opening 28.
    The two adapter pieces 18 and the locking piece 19 are also arranged inside the cavity 28.
    The adapter pieces 18 are positioned on either side of the blade root portion 22. The locking piece 19 is disposed between the two portions 23 of the blade root portion 22, so that each of the two portions 23 is sandwiched between one of the adaptation pieces 18 and the blocking piece 19.
    The locking piece 19 has a wedge shape. The locking piece 19 keeps the two portions 23 of the blade root portion 22 apart from one another so as to oppose a withdrawal of the blade root portion 22 from the cavity 28 via the opening 29. The locking piece 19 can be formed of metal, for example aluminum, titanium, or a composite material, such as an organic matrix composite material (CMO) which has the advantage of 'be light.
    The fan blade 7 further comprises a cover 31 suitable for being fixed on the attachment piece 9, for example by screwing. When the cover 31 is fixed to the attachment piece 9, it closes the second opening 30. In addition, the cover 31 exerts on the locking piece 19 a force which tends to press the locking piece 19 against the foot portions blade 23, so that each of the two portions 23 is compressed between one of the adapter pieces 18 and the locking piece 19. The cover 31 is preferably made of metal.
    The seal 20 extends in the first opening 29, between the structure in composite material 17 and the edge of the first opening 29 which surrounds the structure in composite material 17. The seal 20 makes it possible to fill the gap remaining between the structure in material composite 17 and the attachment piece 9.
    FIG. 4 schematically represents the structure of composite material 17.
    The composite material comprises a fibrous reinforcement 33 obtained by three-dimensional weaving and a matrix 34 in which the fibrous reinforcement 33 is embedded.
    The fibrous reinforcement 33 is woven so that it comprises warp threads which extend continuously both inside the airfoil part 21 and inside the foot part. dawn 22.
    The matrix 34 which coats the wires of the fibrous reinforcement 33 is formed from plastic.
    Figures 5 to 16 illustrate steps of a method of manufacturing a fan blade 7 according to a possible embodiment of the invention.
    According to a first step (FIG. 5), the fibrous reinforcement 33 is produced by three-dimensional weaving on a jacquard type loom. During weaving, bundles of warp threads C (or warp strands) are arranged in several layers of several hundred threads each. Weft threads T (or weft strands) are interlaced with the warp threads C so as to link the different layers of warp threads C together.
    In the example illustrated, the three-dimensional weaving is an interlock weaving. By "interlock" is meant a weaving weave in which each layer of weft yarns links several layers of warp yarn with all the yarns of the same weft column having the same movement in the plane of the weave.
    Other types of known three-dimensional weavings can be used, such as in particular those described in document WO 2006/136755.
    The fibrous reinforcement 33 is woven from yarns of carbon fibers.
    As illustrated in FIG. 6, the step of weaving the raw fibrous reinforcement 33 (or preform) successively comprises weaving a portion of temporary fibrous reinforcement 34 (which will be dropped later during the manufacturing process), weaving of the two fibrous reinforcement portions of the blade root 35, then the weaving of a fibrous reinforcement portion of the blade 36.
    The provisional fibrous reinforcement portion 34 is woven by interlacing all the warp strands C necessary for producing the fibrous reinforcement 33. Once the weft column has reached a predetermined width I, a debinding D is initiated between two successive layers of warp yarns C. Then, the two fiber reinforcement portions of the blade root 35 are woven in parallel with one another, being separated by the unbinding zone D. Then, the unbinding D is stopped and the fiber reinforcement portion of blade 36 is woven.
    In this way, each of the two blade root reinforcement portions 35 comprises warp threads C which extend inside the fibrous blade reinforcement portion 36.
    FIG. 7A is an enlarged schematic view, in cross section of a plurality of layers of warp threads Ci to Ce, in a part of the fibrous reinforcement not comprising any unbinding. In this example, the fibrous reinforcement comprises 6 layers of warp threads Ci to Ce extending in a direction transverse to the section plane. The layers of warp threads Ci to Ce are linked together by 5 layers of weft threads Ti to Ts extending in the cutting plane (or weave plane).
    FIG. 7B is an enlarged schematic view, in cross section of a plurality of layers of warp threads Ci to Ce, in a part of the fibrous reinforcement including a debinding. The three layers of warp threads Ci to C are linked together by two layers of weft threads Ti and T2, while the three layers of warp threads C4 to Ce are linked together by two layers of weft threads T4 and T5 . As can be seen in FIG. 7B, two layers of threads of adjacent chains C3 and C4 are not linked together by weft threads, so that a debinding is formed in the fibrous reinforcement.
    Furthermore, as can be seen in FIG. 6, each portion of the fibrous reinforcement of the blade root 35 has been woven with successive weft strands T which have different titrations, which decrease in the weaving direction (weaving direction). indicated by the arrow), that is to say titrations which decrease as one approaches the fiber reinforcement portion of blade 36.
    Remember that "titration" designates a quantity characterizing the fineness of a wire: it is defined as the mass of the wire per unit of length. The standard unit for measuring titration is Tex (mass in grams of 1000 meters of wire) or Décitex (mass in grams of 10,000 meters of wire). Other units can also be used such as the penny, the metric number or the English number.
    In this way, the fiber reinforcement portions of the blade root 35 each have a thickness e which decreases as it approaches the fiber reinforcement portion of the blade 36. Each fiber reinforcement portion of the blade root has a thickness ei in blade root, and a thickness e2 at the junction with the fiber reinforcement portion of the blade 36, less than ei.
    As the fibrous reinforcement 33 is woven, the thickness and width of which vary, a certain number of warp threads C are not woven, which makes it possible to define a continuously variable outline, width and thickness that are desired. fibrous reinforcement 33.
    According to a second step (FIG. 8), the warp threads C and the weft threads T situated at the limit of the woven mass (called "floats") are also cut, so as to extract the fibrous reinforcement 33.
    Then, the finished fibrous reinforcement is obtained by performing a contouring of the preform. Clipping means cutting the preform flat along the leading edge, trailing edge, head (leaving extra lengths on these three cuts). A clipping is also carried out along the lower vein and on the lateral faces of the dawn root portion,
    In addition, the provisional fibrous reinforcement portion 34 is cut in order to be eliminated, so that the unbinding D forms a through opening 37 between the two reinforcement portions of the blade root 35. The trimming and cutting of the portion of blade root can be made with a pressurized water jet.
    According to a third step (FIG. 9), the fiber reinforcement portions of the blade root 35 are inserted into the cavity 28 of the blade root attachment piece 9 via the first opening 29 of the attachment piece 9 Once the fiber reinforcement portions of the blade root 35 are inserted into the cavity 28, the fiber reinforcement portions of the blade root 35 extend inside the cavity 28 of the attachment piece 9 while that the blade fibrous reinforcement portion 36 extends outside of the attachment piece 9.
    According to a fourth step (FIG. 10), the adaptation pieces 18 are inserted into the cavity 28, on either side of the blade root reinforcement part 35, via the second opening 30. The pieces of d adaptation 18 may be parts made of an expanded plastic material. The material forming the adapter parts preferably has closed cells so as to prevent penetration of plastic material which will be injected during the subsequent molding step, and thus maintain its low density.
    According to a fifth step (FIG. 11), a first temporary filling piece 38 in the form of a wedge is inserted into the cavity 28 of the attachment piece 9, between the two fiber reinforcement portions of the blade root 35, in the unbinding zone, to keep the two portions apart from each other. Thus, each fiber reinforcement portion of the blade root 35 extends between the temporary filling part 38 and one of the two adaptation parts 18.
    According to a sixth step (FIG. 12), a second temporary filling piece 39 is inserted into the first opening 29 of the attachment piece 9. More specifically, the second temporary filling piece 39 is inserted between the fibrous reinforcement 33 and the edge of the opening 29 of the attachment piece 9.
    According to a seventh step (FIG. 13), the assembly obtained, comprising the fibrous reinforcement 33, the attachment part 9, the adaptation parts 18 and the filling parts 38 and 39, is placed in a mold 40. The mold 40 is a mold having a cavity 41 having the shape of the final molded part (namely the fan blade 7).
    According to an eighth step, plastic material (called “resin”) is injected into the mold 40 so as to impregnate all of the fibrous reinforcement 33. The injection of plastic material can be carried out by an injection technique called “Resin Transfer Molding ”(RTM). The plastic injected is for example a thermosetting liquid composition containing an organic precursor of the matrix material. The organic precursor is usually in the form of a polymer, such as a resin, optionally diluted in a solvent.
    According to a ninth step, the plastic material is heated so as to cause polymerization of the plastic material, for example by crosslinking. To this end, the mold 40 is placed in an oven.
    According to a tenth step, the part obtained is removed from the mold.
    According to an eleventh step, the part is cut off by machining the leading edge, the trailing edge and the blade head in order to obtain a part having the desired shape. The lower part of the blade is also machined.
    The reinforcement 33 impregnated with plastic material constituting the matrix 34 forms a structure made of composite material 17.
    According to a twelfth step (FIG. 14), the first temporary filling part 38 and the second temporary filling part 39 are removed.
    According to a thirteenth step, the blocking piece 19 is inserted through the second opening 30, in place of the first temporary filling piece 38, between the two portions of the blade root portion 23, to hold the two portions 23 separated from each other.
    In addition, the seal 20 is inserted into the first opening 29, in place of the second temporary filling part 39.
    According to a fourteenth step (Figure 15), the cover 31 is fixed to the attachment piece 9 to keep the locking piece 19 in abutment against the two portions 23 of the blade root portion. In particular, the cover 31 is fixed so that it exerts on the blocking part 19 a compressive force, tending to push the blocking part 19 between the two portions 23 of the blade root portion 22 towards the blade part 21 with aerodynamic profile. Once the cover 31 is fixed to the attachment piece 9, each portion 23 of the blade root portion 22 is compressed between one of the two adaptation pieces 18 and the locking piece 19.
    This arrangement makes it possible to guarantee that the two portions 23 remain apart from one another in order to resist by geometric effect to the centrifugal forces exerted on the blade 7 during the operation of the engine.
    The method can also comprise the following additional steps:
    According to a fifteenth step (FIG. 16), one or more reinforcing piece (s) 42, 43 can be added to the structure of composite material 17. In particular, the reinforcing pieces can comprise a piece leading edge reinforcement 42 and / or a trailing edge reinforcing part 43.
    The reinforcement piece (s) 42, 43 can be formed from metal. It (s) can (be) glued (s) on the structure in composite material
    17.
    According to a sixteenth step, the structure of composite material 17 can be covered with a protective layer, for example a protective layer in polyurethane, in order to protect the dawn against abrasion and the impacts of objects.
    权利要求:
    Claims (18)
    [1" id="c-fr-0001]
    1. Dawn (7) comprising:
    - a structure in composite material (17) comprising a fibrous reinforcement (33) obtained by three-dimensional weaving and a matrix (34) in which the fibrous reinforcement (33) is embedded, the structure in composite material (17) comprising a blade portion (21) with an aerodynamic profile and a blade root part (22), the blade root part (22) comprising two portions (23) each connected to the blade part (21),
    - A blade root attachment piece (9) comprising a wall (25) delimiting a cavity (28) and an opening (29) formed in the wall (25), the structure of composite material (17) s' extending through the opening (29) so that the blade portion (21) is located outside the attachment piece (9) and the blade root portion (22) is located at the '' inside the cavity (28), and
    - a blocking piece (19) disposed in the cavity (28), between the two portions (23) of the blade root portion (22), to hold the two portions (23) apart from one other so as to oppose a withdrawal of the blade root portion (22) from the cavity (28) via the opening (29).
    [2" id="c-fr-0002]
    2. A blade according to claim 1, in which the fibrous reinforcement (33) comprises a blade fibrous reinforcement portion (36) extending inside the blade portion (21) having an aerodynamic profile, and two portions of blade root fiber reinforcement (35) extending respectively inside the two blade root portions (23), and in which the blade root fiber reinforcement portions (35) are each woven from continuously with the fiber reinforcement portion of the blade (36).
    [3" id="c-fr-0003]
    3. Dawn according to claim 2, in which the two fiber reinforcement portions of the blade root (35) are separated by an unbinding zone (D) obtained during the three-dimensional weaving of the fibrous reinforcement (33).
    [4" id="c-fr-0004]
    4. Dawn according to one of claims 1 to 3, comprising adapter parts (18) arranged in the cavity (28), on either side of the blade root portion (22), so that each portion of the blade root portion (23) is clamped between the locking piece (19) and one of the two adaptation pieces (18).
    [5" id="c-fr-0005]
    5. Dawn according to one of claims 1 to 4, comprising a cover (31) adapted to be fixed on the attachment piece (9) to keep the locking piece (19) in abutment against the two portions of the part blade root (23).
    [6" id="c-fr-0006]
    6. Dawn according to one of claims 1 to 5, comprising a seal (20) disposed between the structure of composite material (17) and an edge of the opening (29) of the attachment piece (9).
    [7" id="c-fr-0007]
    7. Dawn according to one of claims 1 to 6, wherein each portion (23) of the blade root portion (22) has a thickness (e) increasing when traversing the portion (23) in s' away from the blade part (21).
    [8" id="c-fr-0008]
    8. Dawn according to one of claims 1 to 7, in which the attachment piece (9) is made of metal.
    [9" id="c-fr-0009]
    9. A method of manufacturing a blade (7) from a fibrous reinforcement (33) obtained by three-dimensional weaving and from a blade root attachment piece (9), the fibrous reinforcement (33) comprising a blade fiber reinforcement portion (36) and two blade root fiber reinforcement portions (35), and the blade root attachment part (9) comprising a wall (25) delimiting a cavity (28 ) and an opening (29) formed in the wall (25), the method comprising steps of:
    - insertion of the fiber reinforcement portions of the blade root (35) into the cavity (28) of the blade root attachment piece (9) via the opening (29) of the attachment piece (9 ), the fibrous blade reinforcement portion (36) extending outside the attachment piece (9),
    - insertion of a temporary filling part (38) in the cavity (28) of the attachment part (9), between the two fiber reinforcement portions of the blade root (35), to keep the two portions apart one from the other,
    - placing the fibrous reinforcement (33), the attachment piece (9) and the temporary filling piece (38) in a mold (40),
    injection of plastic material into the mold (40) so as to form a structure of composite material (17) comprising the fibrous reinforcement (33) and a matrix (34) in which the fibrous reinforcement (33) is embedded, the structure in composite material (17) comprising an airfoil blade portion (21) and a blade root portion (22), the blade root portion (22) extending within the cavity (28 ) of the blade root attachment piece (9) and comprising two portions (23) each connected to the blade portion (21),
    - Removal of the temporary filling part (38) and insertion of a blocking part (19) between the two portions of the blade root portion (23), to keep the two portions (23) apart on the other so as to oppose a withdrawal of the blade root portion (22) from the cavity (28) via the opening (29).
    [10" id="c-fr-0010]
    10. Method according to claim 9, comprising a prior step of:
    - weaving the fibrous reinforcement (33) in three dimensions, with warp strands (C) extending both in the fibrous reinforcement portion of the blade (36) and in one of the two fibrous reinforcement portions of the foot dawn (35).
    [11" id="c-fr-0011]
    11. The method of claim 10, wherein the step of weaving the fibrous reinforcement (33) successively comprises weaving a portion of temporary fibrous reinforcement (34), weaving the two portions of fibrous foot reinforcement. blade (35), the two fiber reinforcement portions of the blade root (35) being separated by an unbinding zone (D), then weaving the fiber reinforcement portion of the blade (36), the method further comprising a step of cutting the portion of temporary fibrous reinforcement (34).
    [12" id="c-fr-0012]
    12. Method according to one of claims 10 and 11, wherein the fibrous reinforcement (33) is woven so that each fiber reinforcement portion of the blade root (35) has a thickness (e) decreasing when traversing the portion approaching the blade portion (36).
    [13" id="c-fr-0013]
    13. The method of claim 12, wherein each blade root reinforcement portion (35) is obtained by weaving with successive weft strands (T), the weft strands (T) having different titrations which decrease when when the portion (35) is traversed while approaching the blade portion (36).
    [14" id="c-fr-0014]
    14. Method according to one of claims 9 to 13, comprising a step of inserting adaptation parts (18) in the cavity (28), on either side of the blade root portion (35 ), so that each portion of the blade root portion (35) extends between the temporary filling part (38) and one of the adaptation parts (18), before the injection step of plastic.
    [15" id="c-fr-0015]
    15. Method according to one of claims 9 to 14, comprising steps of:
    - insertion of a temporary filling piece (39) between the fibrous reinforcement (33) and an edge of the opening (29) of the attachment piece (9), before the plastic injection step,
    - removal of the temporary filling part (39), after the plastic injection step, and mounting of a seal (20) between the composite material structure (33) and an edge of the opening (29 ) of the attachment piece (9).
    [16" id="c-fr-0016]
    16. Method according to one of claims 9 to 15, comprising a step of fixing a cover (31) on the attachment piece (9) to maintain the locking piece (19) in abutment against the two portions of the blade root portion (35).
    [17" id="c-fr-0017]
    17. Gas turbine engine (1) comprising a blower, the blower comprising a hub (6) and blades (7) extending radially from the hub (6), the blades (7) being in accordance with one of claims 1 to
    8.
    [18" id="c-fr-0018]
    18. A gas turbine engine according to claim 17, in which each blade (7) is rotatably mounted relative to the hub (6) around a respective timing axis (Y), the engine (1) further comprising a actuation mechanism (8) suitable for being controlled to rotate the blades (7)
    10 around their setting axes (Y) so as to modify the setting angle of the blades (7).
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    同族专利:
    公开号 | 公开日
    GB201905625D0|2019-06-05|
    US20190323357A1|2019-10-24|
    GB2574319A|2019-12-04|
    US11131197B2|2021-09-28|
    FR3080322B1|2020-03-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3752600A|1971-12-09|1973-08-14|United Aircraft Corp|Root pads for composite blades|
    US4045149A|1976-02-03|1977-08-30|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Platform for a swing root turbomachinery blade|
    US4343593A|1980-01-25|1982-08-10|The United States Of America As Represented By The Secretary Of The Air Force|Composite blade for turbofan engine fan|
    US5672417A|1995-03-29|1997-09-30|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Turbomachine blade made of composite material|
    US20050084379A1|2003-06-06|2005-04-21|Karl Schreiber|Compressor blade root for engine blades of aircraft engines|FR3106364A1|2020-01-20|2021-07-23|Safran Aircraft Engines|Blade comprising a composite material structure and associated manufacturing method|
    WO2021181045A1|2020-03-11|2021-09-16|Safran Aircraft Engines|Blade comprising a structure made of composite material and associated manufacturing method|
    FR3108144A1|2020-03-11|2021-09-17|Safran Aircraft Engines|Blade comprising a composite material structure and associated manufacturing method|
    WO2022018358A1|2020-07-24|2022-01-27|Safran Aircraft Engines|System for controlling the pitch setting of a propeller blade for an aircraft turbine engine|
    WO2022018357A1|2020-07-24|2022-01-27|Safran Aircraft Engines|Aircraft turbine engine comprising variable-pitch propeller blades|
    WO2022018356A1|2020-07-24|2022-01-27|Safran Aircraft Engines|Assembly comprising a blade and a blade pitch setting system|
    FR3112819A1|2020-07-24|2022-01-28|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE COMPRISING VARIABLE-PITCHED PROPELLER BLADE|
    FR3112820A1|2020-07-24|2022-01-28|Safran Aircraft Engines|AIRCRAFT TURBOMACHINE WITH VARIABLE-PITCHED PROPELLER BLADE|NL102164C|1956-11-30|
    US4037990A|1976-06-01|1977-07-26|General Electric Company|Composite turbomachinery rotor|
    GB2260580A|1991-10-16|1993-04-21|Rolls Royce Plc|Gas turbine engine aerofoil structure|
    GB9828484D0|1998-12-24|1999-02-17|Rolls Royce Plc|Improvements in or relating to bladed structures for fluid flow propulsion engines|
    EP1803899A1|2006-01-02|2007-07-04|Siemens Aktiengesellschaft|Blade locking assembly for a turbomachine|
    FR2963383B1|2010-07-27|2016-09-09|Snecma|DUST OF TURBOMACHINE, ROTOR, LOW PRESSURE TURBINE AND TURBOMACHINE EQUIPPED WITH SUCH A DAWN|
    US10590780B2|2013-04-02|2020-03-17|United Technologies Corporation|Engine component having support with intermediate layer|
    US10941665B2|2018-05-04|2021-03-09|General Electric Company|Composite airfoil assembly for an interdigitated rotor|FR3091723B1|2019-01-15|2021-04-02|Safran Aircraft Engines|Composite blade or propeller blade for aircraft incorporating a shaping part|
    法律状态:
    2019-03-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-10-25| PLSC| Publication of the preliminary search report|Effective date: 20191025 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1853509|2018-04-20|
    FR1853509A|FR3080322B1|2018-04-20|2018-04-20|BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND MANUFACTURING METHOD THEREOF|FR1853509A| FR3080322B1|2018-04-20|2018-04-20|BLADE COMPRISING A COMPOSITE MATERIAL STRUCTURE AND MANUFACTURING METHOD THEREOF|
    US16/389,525| US11131197B2|2018-04-20|2019-04-19|Blade comprising a structure made of composite material and method for manufacturing the same|
    GB1905625.8A| GB2574319A|2018-04-20|2019-04-23|Vane comprising a structure made of composite material and method for manufacturing the same|
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