• 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:
    A fibrous structure (200) of blade reinforcement or propeller blade of composite material is woven in one piece with an aerodynamic profile (211), a portion of spar (222) and a bulged portion (212). The fibrous structure (200) comprises a debonding zone (Zd) extending between the front and rear edges (211a, 211b) of the airfoil (211) and between an intermediate zone (203) and the lower edge (211c) of said profile. The spar portion (222) extends inside the airfoil (211) at the debonding zone (Zd), the spar portion opening outwardly of the airfoil at the lower edge (211c ) of said profile. The bulged portion (212) extends in the extension of the spar portion (222) outside the airfoil (211). The aerodynamic profile (211) comprises, at the level of the debonding zone (Zd), skins (228, 229) which are delimited relative to one another and enclose the portion of the spar (222). The skins define inside the aerodynamic profile (211) respectively two housings (230, 231) present on one side and the other of the spar portion and opening at the lower edge (211c) of the aerodynamic profile ( 211).
    公开号:FR3076814A1
    申请号:FR1850259
    申请日:2018-01-12
    公开日:2019-07-19
    发明作者:Vivien Mickael Courtier
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Invention background
    The present invention relates to the field of propeller blades or blades for aircraft such as those present on turboprop engines.
    The propeller blades or blades for turboprop engines are generally made of metallic material. If the blades or propeller blades made of metallic material have good mechanical strength, they have the disadvantage of having a relatively large mass.
    In order to obtain lighter blades or propeller blades, it is known to produce propeller blades made of composite material, that is to say by making structural parts with fibrous reinforcement and resin matrix.
    The documents US 2013/0017093 and WO 2012/001279 describe the production of a propeller blade from a fibrous structure with an aerodynamic profile inside which is inserted part of a spar, one end of the spar being extended by a bulged portion intended to form the foot of the propeller blade. The fibrous structure, which is produced in a single piece by three-dimensional weaving, comprises an unbinding zone making it possible to form a housing inside the fibrous structure in which part of the spar is inserted.
    The propeller blade thus obtained has both a reduced overall mass and a significant mechanical resistance by the presence in skin of a structure of composite material (fibrous reinforcement densified by a matrix).
    However, keeping the side member added in position in the fibrous structure can be difficult in certain cases, such as when the blade is subjected to significant mechanical loads, impacts or shocks.
    Subject and summary of the invention
    It is therefore desirable to be able to propose a solution for producing aircraft propeller blades or blades of the type described above but which have increased mechanical strength in particular in terms of maintaining the position of the spar inside. of the fibrous structure of aerodynamic profile.
    To this end, according to the invention, there is provided a fibrous structure for reinforcing a blade or a propeller blade made of composite material, the fibrous structure being woven in one piece and having an aerodynamic profile, a portion of spar and a bulging portion, the airfoil extending in a longitudinal direction between a lower end and an upper end and in a transverse direction between a front edge and a rear edge, the fibrous structure comprising a debinding zone extending between the front edges and rear of the aerodynamic profile in the transverse direction and between an intermediate zone and the lower edge of said profile in the longitudinal direction, the spar portion extending inside the aerodynamic profile at the level of the unbinding zone set back from the edges front and rear of said profile in the transverse direction, the spar portion opening out of the aerodynamic profile at the lower edge of said profile, the bulged portion extending in the extension of the spar portion outside the aerodynamic profile, the bulged portion extending in the transverse direction over a length less than the length of the lower edge of the aerodynamic profile, the aerodynamic profile comprising at the level of the unbinding zone of the first and second skins untied relative to each other, the first and second skins extending between the front and rear edges of the aerodynamic profile in the transverse direction and between the intermediate zone and the lower edge of said profile in the longitudinal direction, the skins enclosing the spar portion, the first and second skins delimiting inside the aerodynamic profile of the first and second housings respectively present one side and the other of the spar portion in the transverse direction the, the first and second housings opening at the lower edge of the aerodynamic profile.
    By thus producing a portion of spar integrally formed with the aerodynamic profile of the fibrous structure intended to form the fibrous reinforcement of a blade or of a propeller blade made of composite material, it ensures perfect retention in position of the parts of attachment (stilt and foot) of the blade or propeller blade relative to the aerodynamic profile. Indeed, even in the event of mechanical stresses (impacts, shocks) at the level of the aerodynamic profile of the blade or propeller blade, there is no risk of displacement of the spar portion inside the reinforcement because this is linked to the aerodynamic profile by continuously woven parts of the reinforcement.
    According to one aspect of the fibrous structure of the invention, the front edge and the rear edge each have a slot extending in the longitudinal direction between the intermediate part and the lower end of the fibrous structure. This makes it possible in particular to access the blank of the spar portion for cutting the float yarns after weaving the blank of fibrous structure and to facilitate the fitting of shaping pieces later.
    The invention further relates to a blade or propeller blade comprising a fibrous reinforcement consisting of a fibrous structure according to the invention and densified by a matrix, the blade or propeller blade comprising an aerodynamic profile, a portion spar extending inside the aerodynamic profile, a stilt extending outside the aerodynamic profile, a foot extending outside the aerodynamic profile in the extension of the stilt, a first piece of conformation present in the first housing formed inside the aerodynamic profile and a second conformation piece present in the second housing formed inside the aerodynamic profile.
    As indicated above, the blade or propeller blade of the invention has very good mechanical strength, in particular at the level of the connection between the foot and the aerodynamic profile thanks to the fibrous reinforcement in which the foot, the spar portion form a single piece with the aerodynamic profile.
    According to a first aspect of the blade or propeller blade of the invention, the Péchasse connecting the foot to the spar portion has straight side edges parallel to the longitudinal direction. This forms a short stapled foot without introducing connecting radii between the foot and the aerodynamic profile, which greatly improves the mechanical strength of this part of the blade. In fact, the connection zone between the foot and the aerodynamic profile is an area of the blade or propeller blade very stressed mechanically because it concentrates the mechanical stresses generated by the geometry of the blade or blade of the propeller in motion. and corresponds to a zone of localization of the vibrational criticality which can lead to decohesions between the fibers and the matrix. In the absence of a connection radius, the mechanical resistance of the blade or propeller blade is therefore improved while retaining a high compactness at the foot.
    According to a second aspect of the blade or propeller blade of the invention, the height of the unbinding zone present in the fibrous structure constituting the fibrous reinforcement of the blade or propeller blade is between 10% and 50 %, more preferably between 20% and 40%, of the total height of the aerodynamic profile in the longitudinal direction.
    The invention also relates to an aeronautical engine comprising a plurality of blades or propeller blades according to the invention.
    The invention also relates to an aircraft comprising at least one engine according to the invention.
    The present invention also relates to a process for manufacturing a fibrous structure for reinforcing a blade or propeller blade made of composite material comprising:
    three-dimensional weaving between a plurality of layers of weft yarns and a plurality of layers of warp yarns of a blank of fibrous structure in one piece, the blank extending in a longitudinal direction between a lower part and an upper part and in a transverse direction between a front edge and a rear edge, the blank comprising an aerodynamic profile blank, a spar portion blank and a bulged portion blank, the method comprising during the weaving of the fibrous structure blank the formation of a debinding inside the aerodynamic profile blank, the unbinding extending between an intermediate zone and the lower edge of the fibrous structure blank in the longitudinal direction and between the front and rear edges of the blank of fibrous structure in the transverse direction, the unbinding separating from the first and second portions present on the one hand and on the other side of the spar portion so as to form first and second skin blanks untied from one another, the first and second skin blanks extending between the front and rear edges of the fiber structure blank in the transverse direction and between the intermediate zone and the lower edge of the fiber structure blank in the longitudinal direction, the skin blanks enclosing the spar portion blank, the first and second skin blanks delimiting inside the blank of fibrous structure of the first and second housings present respectively on one side and the other of the blank of spar portion in the transverse direction, the first and second housings emerging at the level of the lower part of the fiber structure blank, the cutting of float yarns present outside the fiber structure blank so as to d finish the outer contour of the fibrous structure, the cutting of float yarns present around the spar portion portion and the bulge portion blank as well as float yarns present at the bottom of the structural blank fibrous so as to obtain a fibrous structure comprising an aerodynamic profile comprising a lower edge from which a bulged portion extends in the extension of a spar portion outside the aerodynamic profile, the bulged portion extending along the transverse direction over a length less than the length of the lower edge of the aerodynamic profile.
    The invention finally relates to a method of manufacturing a blade or propeller blade made of composite material comprising at least:
    the production of a fibrous structure according to the invention, the shaping of the fibrous structure by introduction into the first and second housings present inside the aerodynamic profile of the fibrous structure respectively of a first and a second shaping parts to obtain a blade or propeller blade preform, densification of the preform by a matrix, machining of extra lengths present on the densified preform to obtain a blade or propeller blade having a profile aerodynamics, a spar portion extending inside the aerodynamic profile, a stilt extending outside the aerodynamic profile, a foot extending outside the aerodynamic profile in the extension of the stilt, a first shaping part present in the first housing formed inside the profile and a second shaping part present in the second housing formed inside the aerodynamic profile.
    According to a first aspect of the method of manufacturing a blade or propeller blade according to the invention, the stilt connecting the foot to the spar portion has straight side edges parallel to the longitudinal direction.
    According to a second aspect of the method for manufacturing a blade or propeller blade according to the invention, the height of the unbinding zone present in the fibrous structure constituting the fibrous reinforcement of the blade or propeller blade is between 10% and 50%, more preferably between 20% and 40%, of the total height of the aerodynamic profile in the longitudinal direction.
    Brief description of the drawings
    Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of nonlimiting examples, with reference to the appended drawings, in which:
    Figure 1 is a schematic view of a blade according to an embodiment of the invention, Figures 2A to 2C are cross-sectional views of the blade of Figure 1 respectively according to the section planes A, B and C represented in FIG. 1, FIGS. 2D to 2F are views in longitudinal section of the blade of FIG. 1 according to the section planes D, E and F respectively represented in FIG. 1,
    Figure 3 is a schematic view illustrating the 3D weaving of a blank of fibrous structure for the manufacture of the blade of Figure 1, Figures 4A and 4B are views in longitudinal section of the blank of Figure 3 according to respectively the section planes A and B shown in FIG. 3,
    FIG. 5 is a schematic perspective view of the blank of fibrous structure after cutting of the outer float yarns,
    FIG. 6 is a diagrammatic perspective view of the blank of fibrous structure after cutting of the float yarns present in the lower part of the blank,
    FIG. 7 is a schematic perspective view of the blank of fibrous structure after cutting the float yarns present on the spar portion of the blank,
    FIG. 8 is a schematic perspective view of the fibrous structure obtained as well as its shaping with shaping pieces,
    - Figure 9 is a schematic perspective view of the densified blade preform with a matrix showing the final machining of the foot, the stilt and the lower part of the skins.
    Detailed description of embodiments
    The invention applies generally to different types of blades or propeller blades used in aircraft engines. The invention finds an advantageous but not exclusive application in blades or propeller blades of large dimensions which, because of their size, have a large mass having a significant impact on the overall mass of the engine of the aircraft. The blade according to the invention can in particular constitute a blade for faired movable wheels such as fan blades or a blade for non-faired movable wheels as in aeronautical engines called "open rotor".
    FIG. 1 represents a blade 10 intended to be mounted on an airplane turboprop which comprises, an aerodynamic profile 11 intended to form the aerodynamic part of the blade, a foot 12 formed by a part of greater thickness, for example in cross section bulb-shaped, extended by a stilt 13. The aerodynamic profile structure 11 has in cross section a curved profile of variable thickness between its leading edge 11a and its trailing edge 11b in a transverse direction Dt. The aerodynamic profile 11 extends, in a longitudinal direction Dl, between a lower edge 11c and an upper edge lld. The foot 12 extends in the transverse direction Dt over a length less than the length of the lower edge 11c of the aerodynamic profile 11.
    As shown in FIGS. 1 and 2A to 2F, the blade 10 comprises a fibrous reinforcement 20 densified by a matrix, the fibrous reinforcement 10 consisting of a fibrous structure according to the invention, the structure and manufacture of which are described below. after. As illustrated in FIGS. 2A to 2F, the fibrous reinforcement 20 comprises in one piece a structure with an aerodynamic profile 21 intended to form the aerodynamic profile of the blade 10, a portion of spar 22 extending inside the aerodynamic profile structure 21, a bulged portion 24 forming the blade root 12 extending in the extension of the portion of the spar 22 outside the aerodynamic profile structure 21, the part 22a of the spar portion outside the aerodynamic profile structure 21 and connecting the bulged portion 24 forming the stilt 13 of the blade 10. The fibrous reinforcement 20 mainly comprises first and second parts 25 and 26 separated from each other by an intermediate zone 27. The first part 25 delimits an unbinding zone Zd inside the aerodynamic profile structure 21, the unbinding zone extending between the intermediate zone 27 and the lower edge r 21c of the aerodynamic profile structure 21 corresponding to the lower edge 11c of the aerodynamic profile 11 in the longitudinal direction Dl and between the front and rear edges 21a and 21b of the aerodynamic profile structure 21 corresponding respectively to the leading edge 11a and to the trailing edge 11b of the aerodynamic profile 11 in the transverse direction Dt. The first part 25 comprises first and second skins 28 and 29 untied from one another and untied from the spar portion 22, the first and second skins 28 and 29 extending between the front and rear edges 21a and 21b of the structure with aerodynamic profile 21 in the transverse direction and between the intermediate zone 27 and the lower edge 21c of the structure with aerodynamic profile 21 in the longitudinal direction, the skins 28 and 29 enclosing the spar portion 22. The first and second skins 28 and 29 delimit inside the structure with aerodynamic profile 21 of the first and second housings 30 and 31 present respectively on one side and the other of the spar portion 22 in the transverse direction, the first and second housings 30 and 31 opening out at the lower edge level 21c of the structure with aerodynamic profile 21. A first shaping part 40 is present in the first housing 30. Likewise, a second shaping part 41 is present in the second housing 31.
    In order to conform the fibrous reinforcement 20 without significantly increasing the overall mass of the aerodynamic profile structure of the propeller blade, the parts 40 and 41 are preferably made of rigid cellular material, that is to say a material having a low density such as rigid foam for example. The shaping pieces can be produced by molding or by machining in a block of material.
    The method of manufacturing a blade according to the invention comprises producing a fibrous structure in accordance with the present invention.
    FIG. 3 very schematically shows a blank of fibrous structure 100 intended to form the fibrous preform of the blade to be produced.
    The fiber structure blank 100 is obtained, as shown diagrammatically in FIG. 3, by three-dimensional weaving (3D) produced in a known manner by means of a jacquard type loom on which a bundle of warp threads has been placed. 101 or strands in a plurality of layers of several hundred threads each, the warp threads being linked by weft threads 102. The blank of fibrous structure 100 is woven in one piece, the blank extending in a longitudinal direction between a lower part 100c and an upper part 100d and in a transverse direction between a front edge 100a and a rear edge 100b, the blank comprising an airfoil blank 111, a spar portion blank 122 and a blank bulged portion 112, the spar portion portion 122 extending inside the fiber structure blank 100 set back from the front and rear edges 100a and 100b according to the transverse direction Dt and, in the longitudinal direction Dl, between an intermediate zone 103 situated between the lower and upper parts 100c and 100d of the fiber structure blank, the bulged portion blank 112 extending in the extension of the spar portion 122.
    In the example illustrated, the 3D weaving is an interlock weaving weaving. By interlock weaving is meant here a weaving weave in which each layer of weft threads binds several layers of warp thread with all the threads of the same weft column having the same movement in the plane of the weave.
    Other types of known three-dimensional weaving can be used, such as in particular those described in document WO 2006/136755, the content of which is incorporated herein by reference. This document describes in particular the production by weaving in a single piece of reinforcing fibrous structures for parts such as blades having a first type of core weave and a second type of skin weave which make it possible to confer both the mechanical and aerodynamic properties expected for this type of part.
    The fibrous blank according to the invention can be woven in particular from son of carbon fibers or ceramic such as silicon carbide.
    As the weaving of the fibrous blank, the thickness and width of which varies, a certain number of warp threads are not woven, which makes it possible to define the contour and the desired thickness, continuously variable, of the blank 100. An example of an evolving 3D weaving making it possible in particular to vary the thickness of the blank between a first edge intended to form the leading edge and a second edge of lesser thickness and intended to form the edge leakage is described in document EP 1 526 285, the content of which is incorporated herein by reference.
    In addition, during the weaving of the fibrous blank, an unbinding 110 is produced inside the fibrous blank between successive layers of warp yarns and on an unbinding zone Zd separating said unbinding zone Zd from a Zi bonding zone in the fibrous blank. More specifically, as illustrated in FIGS. 4A and 4B, the unbinding 101 extends between an intermediate zone 103 and the lower edge 100c of the fiber structure blank 100 in the longitudinal direction Dl and between the front and rear edges 100a and 100b of the fiber structure blank 100 in the transverse direction Dt, the unbinding 110 separating first and second portions present on either side of the spar portion blank 122 so as to form first and second blanks skins 104 and 105 untied from each other. The first and second skins blanks 104 and 105 extend between the front and rear edges 100a and 100b of the fiber structure blank 100 in the transverse direction Dt and between the intermediate zone 103 and the bottom edge 100c of the fiber blank fibrous structure in the longitudinal direction. The skin blanks 104 and 105 surround the spar portion portion 122 and the bulged portion blank 112. The first and second skin blanks delimit inside the fibrous structure blank 100 of the first and second housings 130 and 131 respectively present on one side and the other of the blank of the spar portion 122 in the transverse direction Dt.
    Once the blank of the fibrous structure 100 has been woven, the floating threads present outside the woven mass are cut, for example with a water jet, so as to define the external contour of a fibrous structure as illustrated. in FIG. 5. The float threads present on the skin blanks 104 and 105 are also cut out at the lower part of the fiber structure blank so as to release the bulged portion blank 112 intended to later form a foot. blade as well as part of the spar portion portion 122 intended to subsequently form a blade stilt as shown in FIG. 6. The float wires present around the portion blank are also cut out spar 122 and the bulged portion blank 112 by lifting the skin blanks 104 and 105 as shown in FIG. 7. To this end, first and second slots 107 and 108 (FIG. 6) are formed between the skin blanks 104 and 105 respectively at the front edge 100a and the rear edge 100b, the slots 107 and 108 extending in the longitudinal direction Dl. The slots 107 and 108 can be formed during weaving by unbinding at the front and rear edges or by cutting after weaving.
    The skin blanks are preferably of constant thickness. The decreasing thickness of the aerodynamic profile blank according to the height is then managed at the level of the spar portion. The wire outlets are therefore made under the blanks of skins which it is necessary to be able to lift in order to access these wire outlets.
    There is then obtained, as illustrated in FIG. 8, a fibrous structure 200 woven in one piece and having an aerodynamic profile.
    211, a spar portion 222 and a bulged portion 212, the aerodynamic profile 211 extending in the longitudinal direction Dl between a lower end 211c and an upper end 211d and in the transverse direction Dt between a front edge 211a and a rear edge 211b. The fibrous structure 200 comprises a debinding zone Zd extending between the front and rear edges 211a and 21 ld of the aerodynamic profile 211 in the transverse direction Dl and between an intermediate part 203 and the lower edge 211c of the aerodynamic profile 211 in the direction longitudinal. The spar portion 222 extends inside the aerodynamic profile 211 at the unbinding zone Zd set back from the front and rear edges 211a and 211b in the transverse direction Dt and, in the longitudinal direction Dl, between a part intermediate 203 located between the lower and upper edges 211c and 211d of the aerodynamic profile 211 and the lower edge 211c of said aerodynamic profile at which the spar portion 222 opens. The bulged portion 212 extends in the extension of the spar portion 222 outside the aerodynamic profile 211, the bulged portion 212 extending in the transverse direction Dt over a length L212 less than the length L211 of the lower edge 211c aerodynamic profile. The aerodynamic profile 211 comprises, at the unbinding zone Zd, first and second skins 228 and 229 untied with respect to each other, the first and second skins extending between the front and rear edges 211a and 211b of the aerodynamic profile in the transverse direction Dt and between the intermediate part 203 and the lower edge 211c of the aerodynamic profile in the longitudinal direction Dl, the skins 228 and 229 enclosing the spar portion 222.
    The first and second skins 228 and 229 define inside the aerodynamic profile of the first and second housings 230 and 231 present respectively on one side and the other of the spar portion 222 in the transverse direction, the first and second housing
    230 and 231 opening at the lower end of the aerodynamic profile 211.
    In FIG. 8, the fibrous structure 200 is shaped into a blade preform, by introducing into the housings 230 and
    231 respectively the shaping pieces 40 and 41.
    Once the shaping pieces 40 and 41 are introduced into the housings 230 and 231, the fibrous blade preform is densified. The slots 107 and 108 present on the front and rear edges 211a and 211b of the fibrous structure are preferably closed by stitching before densification.
    The densification of the fibrous preform consists in filling the porosity of the preform, in all or part of the volume thereof, with the material constituting the matrix.
    The matrix of the composite material can be obtained in a manner known per se according to the liquid method.
    The liquid method consists in impregnating the preform with a 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. The preform is placed in a mold which can be closed in a leaktight manner with a housing having the shape of the final molded part and which can in particular have a twisted shape corresponding to the final shape of the blade. Then, the mold is closed and the liquid matrix precursor (for example a resin) is injected throughout the housing to impregnate the entire fibrous part of the preform.
    The transformation of the precursor into an organic matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after elimination of the possible solvent and crosslinking of the polymer, the preform always being maintained in the mold having a shape corresponding to that of dawn. The organic matrix can in particular be obtained from epoxy resins, such as the high performance epoxy resin sold under the reference PR 520 by the company CYTEC, or from liquid precursors of carbon or ceramic matrices.
    In the case of the formation of a carbon or ceramic matrix, the heat treatment consists in pyrolyzing the organic precursor in order to transform the organic matrix into a carbon or ceramic matrix according to the precursor used and the pyrolysis conditions. For example, liquid carbon precursors can be relatively high coke resins, such as phenolic resins, while liquid ceramic precursors, in particular SiC, can be polycarbosilane (PCS) resins or polytitanocarbosilane (PTCS) or polysilazane (PSZ). Several consecutive cycles, from impregnation to heat treatment, can be performed to achieve the desired degree of densification.
    According to one aspect of the invention, the densification of the fiber preform can be carried out by the well-known transfer molding process known as RTM (Resin Transfer Molding). According to the RTM process, the fibrous preform is placed in a mold having the outside shape of the blade. A thermosetting resin is injected into the internal space defined between the piece of rigid material and the mold and which comprises the fibrous preform. A pressure gradient is generally established in this internal space between the place where the resin is injected and the evacuation orifices of the latter in order to control and optimize the impregnation of the preform by the resin.
    The resin used can be, for example, an epoxy resin. Resins suitable for RTM processes are well known. They preferably have a low viscosity to facilitate their injection into the fibers. The choice of the temperature class and / or the chemical nature of the resin is determined according to the thermomechanical stresses to which the part must be subjected. Once the resin has been injected into all of the reinforcement, it is polymerized by heat treatment in accordance with the RTM process.
    After injection and polymerization, the part is removed from the mold. As illustrated in FIG. 9, one then proceeds to a machining of over-lengths 50 present at the level of the lower part of the skins and of over-lengths 60 present at the level of the foot and rechasing. The machining is carried out so as not to introduce connecting radii between the foot and the stilt. After machining, the bulged portion forming the blade root 12 is connected to the spar portion via a stilt 13 having straight side edges 13a and 13b substantially parallel to the longitudinal direction Dl (Figure 1). This forms a short stapled foot without introducing connecting radii between the foot and the aerodynamic profile, which greatly improves the mechanical strength of this part of the blade. Indeed, the connection zone between the foot and the aerodynamic profile is a zone of the blade very mechanically stressed because it concentrates the mechanical stresses generated by the geometry of the blade in motion and corresponds to a zone of location of the criticality vibration which can lead to decohesions between the fibers and the matrix. When a connecting radius is present between the aerodynamic profile and the foot, it must be as large as possible, but this then implies increasing the size of the stilt which results in an increase in overall mass of the blade or unwanted propeller blade. In addition, mastering the geometry of the connecting radius complicates the manufacture of the blade or propeller blade.
    In the end, the part is cut out to remove the excess resin and the 10 chamfers are machined. No other machining is necessary since, the part being molded, it respects the required dimensions. A blade made of composite material 10 is then obtained as shown in FIG. 1.
    The rigid honeycomb material used to make the shaping pieces 40 and 41 is preferably a closed-cell material 15 so as to prevent the penetration of the resin therein and thus maintain its low density after densification of the fibrous preform .
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Fibrous structure (200) for reinforcing the blade or propeller blade made of composite material, the fibrous structure (200) being woven in one piece and having an aerodynamic profile (211), a portion of spar (222) and a bulged portion (212), the airfoil extending in a longitudinal direction (Dl) between a lower end (211c) and an upper end (21 ld) and in a transverse direction (Dt) between a front edge (211a) and a rear edge (211b), the fibrous structure (200) comprising a unbinding zone (Zd) extending between the front and rear edges (211a, 211b) of the airfoil (211) in the transverse direction and between an area intermediate (203) and the lower edge (211c) of said profile in the longitudinal direction, the spar portion (222) extending inside the aerodynamic profile (211) at the level of the unbinding zone (Zd) recessed front and rear edges (211a, 211b) of said pro wire in the transverse direction, the spar portion (222) emerging outside the aerodynamic profile at the lower edge (211c) of said profile, the bulged portion (212) extending in the extension of the spar portion ( 222) outside the aerodynamic profile (211), the bulged portion (212) extending in the transverse direction over a length (L212) less than the length (L211) of the lower edge (211c) of the aerodynamic profile, the aerodynamic profile (211) comprising at the level of the unbinding zone (Zd) of the first and second skins (228, 229) untied with respect to each other, the first and second skins extending between the front edges and rear (211a, 211b) of the aerodynamic profile (211) in the transverse direction and between the intermediate zone (203) and the lower edge (211c) of said profile in the longitudinal direction, the skins (228, 229) enclosing the spar portion (222), the first 1st and second skins delimiting inside the aerodynamic profile (211) of the first and second housings (230, 231) present respectively on one side and the other of the spar portion in the transverse direction, the first and second housings (230, 231) opening at the lower edge (211c) of the aerodynamic profile (211).
    [2" id="c-fr-0002]
    2. Structure according to claim 1, in which the front edge (211a) and the rear edge (211b) each have a slot (107, 108) extending in the longitudinal direction (Dl) between the intermediate part (203) and the lower end (211c) of the fibrous structure.
    [3" id="c-fr-0003]
    3. blade (10) or propeller blade comprising a fibrous reinforcement (20) consisting of a fibrous structure according to claim 1 or 2 and densified by a matrix, the blade or propeller blade comprising an aerodynamic profile (11 ), a spar portion (22) extending inside the aerodynamic profile, a stilt (13) extending outside the aerodynamic profile (11), a foot (12) extending at the outside of the aerodynamic profile in the extension of Léchasse, a first shaping part (40) present in the first housing (30) formed inside the aerodynamic profile and a second shaping part (41) present in the second housing (31 ) formed inside the aerodynamic profile.
    [4" id="c-fr-0004]
    4. Dawn or propeller blade according to claim 3, wherein the lechasse (13) connecting the foot to the spar portion has lateral edges (13a, 13b) straight parallel to the longitudinal direction (Dl).
    [5" id="c-fr-0005]
    5. Dawn or propeller blade according to claim 3 or 4, wherein the height of the unbinding zone (Zd) present in the fibrous structure (200) constituting the fibrous reinforcement of the blade or propeller blade between 10% and 50% of the total height (Hn) of the aerodynamic profile (11) in the longitudinal direction (Dl).
    [6" id="c-fr-0006]
    6. An aeronautical engine comprising a plurality of blades or propeller blades according to any one of claims 3 to 5.
    [7" id="c-fr-0007]
    7. Aircraft comprising at least one engine according to claim
    6.
    [8" id="c-fr-0008]
    8. A method of manufacturing a fibrous structure for reinforcing a blade (10) or a propeller blade made of composite material comprising:
    three-dimensional weaving between a plurality of weft yarn layers (102) and a plurality of warp yarn layers (101) of a fiber structure blank (100) in one piece, the blank extending in one direction longitudinal (Dl) between a lower part (100c) and an upper part (100d) and in a transverse direction (Dt) between a front edge (100a) and a rear edge (100d), the blank (100) comprising a blank aerodynamic profile (111), a spar portion portion (122) and a bulged portion blank (112), the method comprising during the weaving of the fiber structure blank (100) the formation of a debinding (110 ) inside the aerodynamic profile blank (111), the unbinding (110) extending between an intermediate zone (103) and the lower edge (100c) of the fibrous structure blank (100) according to the longitudinal direction and between the front and rear edges (100a, 100b) of the blank fibrous structure in the transverse direction, the unbinding (110) separating first and second portions present on either side of the spar portion blank (122) so as to form first and second skin blanks (104, 105) untied from each other, the first and second skins blanks (104, 105) extending between the front and rear edges (100a, 100b) of the fiber structure blank in the transverse direction and between the intermediate zone (103) and the lower edge (100c) of the fiber structure blank (100) in the longitudinal direction, the skin blanks enclosing the spar portion blank (122), the first and second skins blanks (104, 105) delimiting inside the fiber structure blank (100) first and second housings (130, 131) present respectively on one side and on the other side of the blank portion spar (122) in the direction transverse, the first and second housings (130, 131) opening out at the level of the lower part (100c) of the fiber structure blank, the cutting of float yarns present outside the fiber structure blank (100) so as to define the outer contour of the fibrous structure, the cutting of float threads present around the spar portion portion (122) and the bulge portion blank (112) as well as float threads present at the lower part of the fiber structure blank so as to obtain a fiber structure (200) comprising an aerodynamic profile (211) comprising a lower edge (211c) from which a bulged portion (212) extends in the extension d '' a spar portion (222) outside the aerodynamic profile, the bulged portion (212) extending in the transverse direction (Dt) over a length (L212) less than the length (L211) of the lower edge (211c ) of the aerodynamic profile.
    [9" id="c-fr-0009]
    9. Method for manufacturing a blade (10) or propeller blade made of composite material comprising at least:
    producing a fibrous structure (200) according to the method according to claim 8, shaping the fibrous structure (200) by introduction into the first and second housings (230, 231) present inside the aerodynamic profile (211) of the fibrous structure respectively of a first and of a second shaping part (40,41) in order to obtain a blade or propeller blade preform, the densification of the preform by a matrix, the machining of extra lengths (50, 60) present on the densified preform to obtain a blade (10) or propeller blade comprising an aerodynamic profile (11), a spar portion (22) extending inside the aerodynamic profile, a stilt (13) extending outside the aerodynamic profile, a foot (12) extending outside the aerodynamic profile (11) in the extension of the stilt (13), a first conforming part (40) present in the first housing (30) m grooved inside the profile and a second shaping part (41) present in the second housing (31) formed inside the aerodynamic profile (11).
    [10" id="c-fr-0010]
    10. A method of manufacturing a blade or propeller blade of composite material according to claim 9, wherein the stilt (13) connecting the foot to the spar portion has lateral edges (13a, 13b) straight parallel to the longitudinal direction (Dl).
    [11" id="c-fr-0011]
    11. A method of manufacturing a blade or propeller blade according to claim 9 or 10, wherein the height of the connection zone (Zd) present in the fibrous structure (200) constituting the fibrous reinforcement of the blade or propeller blade is between 10% and 50% of the total height (Hii) of the aerodynamic profile (11) in the longitudinal direction (Dl).
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2516263B1|2014-09-10|Aircraft propeller blade
    EP2588758B1|2016-04-13|Blade having an integrated composite spar
    EP3019398B1|2018-03-28|Composite rotor blade for aircraft
    EP2652185B1|2015-06-24|Fibrous structure for a part made of composite material having one or more arch-shaped portions
    EP2528727B1|2019-03-06|Method for manufacturing a vane having composite internal channels and composite turbine engine vane
    EP3259123B1|2018-12-12|Method for manufacturing a turbomachine blade made of composite material
    EP3511240B1|2020-02-12|Single piece woven blade having an integrated composite spar
    WO2012098323A1|2012-07-26|Fibrous structure for a part made of a composite material and having a complex shape
    FR3059268A1|2018-06-01|METHOD FOR MANUFACTURING A PROFILE ELEMENT IN COMPOSITE MATERIAL WITH FIXATION OF A METAL REINFORCEMENT BY RIVET.
    FR3081370A1|2019-11-29|DAWN AND DARK BODY OF COMPOSITE MATERIAL HAVING A FIBROUS REINFORCEMENT COMPRISING A THREE-DIMENSIONAL WEAVING AND SHORT FIBERS AND METHOD FOR THE PRODUCTION THEREOF
    FR3045448A1|2017-06-23|ALTERED CASE OF COMPOSITE MATERIAL AND METHOD OF MANUFACTURING THE SAME
    EP3370951B1|2020-01-01|Method for manufacturing a component made of composite material comprising a body integralwith one or more platforms
    FR3091723A1|2020-07-17|Composite propeller blade or blade for aircraft incorporating a conforming part
    WO2020148490A1|2020-07-23|Propeller blade or vane for an aircraft with particular weaving of a fibre preform receiving a bladder filled with a shaping foam
    WO2020021185A1|2020-01-30|Fiber texture for a casing made of composite material with improved impact resistance
    FR3111660A1|2021-12-24|Blade in two-dimensional woven skin composite material incorporating a metal insert and its manufacturing process
    FR3111658A1|2021-12-24|Blade made of composite material with three-dimensional woven fiber reinforcement and two-dimensional woven skin and its manufacturing process
    WO2021123652A1|2021-06-24|Fan or propeller vane for an aircraft turbomachine and method for manufacturing same
    FR3092787A1|2020-08-21|Repair or resumption of manufacture of a composite material part with three-dimensional woven fiber reinforcement
    WO2021005286A1|2021-01-14|Process for manufacturing a fibrous preform for reinforcement of parts made of composite material with a high local variation in thickness
    FR3093298A1|2020-09-04|Repair or resumption of manufacture of a composite material part
    同族专利:
    公开号 | 公开日
    US20190217943A1|2019-07-18|
    US11155336B2|2021-10-26|
    EP3511240A1|2019-07-17|
    FR3076814B1|2020-01-31|
    EP3511240B1|2020-02-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20130017093A1|2009-12-21|2013-01-17|Snecma|Aircraft propeller blade|
    WO2012001279A1|2010-07-02|2012-01-05|Snecma|Blade having an integrated composite spar|
    WO2015004362A1|2013-07-08|2015-01-15|Snecma|Composite propeller blade for an aircraft|FR3108144A1|2020-03-11|2021-09-17|Safran Aircraft Engines|Blade comprising a composite material structure and associated manufacturing method|FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    US7547193B2|2005-07-22|2009-06-16|Sikorsky Aircraft Corporation|Rotor blade assembly with high pitching moment airfoil section for a rotary wing aircraft|
    FR2940172B1|2008-12-18|2011-01-21|Snecma|PROCESS FOR PRODUCING A TURBOMACHINE BLADE|
    US9771810B2|2012-01-09|2017-09-26|Snecma|Fiber preform for a turbine engine blade made of composite material and having an integrated platform, and a method of making it|
    FR3011253B1|2013-10-01|2016-06-10|Snecma|FIBROUS STRUCTURE WITH FLEET COMBINATION|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:
    2018-12-18| PLFP| Fee payment|Year of fee payment: 2 |
    2019-07-19| PLSC| Publication of the preliminary search report|Effective date: 20190719 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1850259|2018-01-12|
    FR1850259A|FR3076814B1|2018-01-12|2018-01-12|BLADE OR COMPOSITE PROPELLER BLADE WITH INTEGRATED LONGER FOR AIRCRAFT|FR1850259A| FR3076814B1|2018-01-12|2018-01-12|BLADE OR COMPOSITE PROPELLER BLADE WITH INTEGRATED LONGER FOR AIRCRAFT|
    EP19150891.0A| EP3511240B1|2018-01-12|2019-01-09|Single piece woven blade having an integrated composite spar|
    US16/245,875| US11155336B2|2018-01-12|2019-01-11|Composite aircraft propeller blade with an integrated spar|
    [返回顶部]