Classifications

• • D—TEXTILES; PAPER
  • D03—WEAVING
  • D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
  • D03D25/00—Woven fabrics not otherwise provided for
  • D03D25/005—Three-dimensional woven fabrics
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
  • B29B11/00—Making preforms
  • B29B11/14—Making preforms characterised by structure or composition
  • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
  • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
  • B29C70/06—Fibrous reinforcements only
  • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
  • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
  • B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/12—Blades
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
  • B29L2031/00—Other particular articles
  • B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
  • B29L2031/082—Blades, e.g. for helicopters
• • D—TEXTILES; PAPER
  • D10—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
  • D10B—INDEXING SCHEME ASSOCIATED WITH SUBLASSES OF SECTION D, RELATING TO TEXTILES
  • D10B2505/00—Industrial
  • D10B2505/02—Reinforcing materials; Prepregs
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6033—Ceramic matrix composites [CMC]
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
  • F05D2300/6034—Orientation of fibres, weaving, ply angle
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to the general field of the manufacture of blades in composite material comprising a fibrous reinforcement densified by a matrix, the fibrous reinforcement being obtained by three-dimensional (3D) or multilayer weaving.
• a targeted field is that of gas turbine blades for aeronautical engines or industrial turbines and, more particularly but not exclusively, fan blades for aeronautical engines.
• Three-dimensional (3D) or multi-layer weaving gives the resulting blade in composite material very good mechanical strength.
• Optimizing the performance of aeronautical engines requires designing blades in composite material with increasingly thin edges to meet new aerodynamic requirements.
• 3D or multilayer weaving weaves used up to now to form blades in composite material do not make it possible to form very thin leading and/or trailing blade edges.
• 3D or multi-layer weaving weaves use a minimum number of three weft layers linked together by a minimum number of three warp layers.
• the invention proposes a fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material comprising a fibrous reinforcement densified by a matrix, the texture being in a single piece and having a three-dimensional or multilayer weaving between a first plurality of layers of wires or strands extending in a longitudinal direction and a second plurality of layers of wires or strands extending in a transverse direction, the texture comprising a blade blade portion extending in the direction transverse between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade, said texture comprising a first part with at least three layers of threads of the first plurality of threads and at least three layers of yarns of the second plurality of yarns, characterized in that it further comprises at least a second part present at the level of the first o at the second edge of the blade blade portion of the fibrous texture, the second portion comprising only two layers of yarns from the first plurality of yarn
• the fibrous texture of the invention makes it possible to achieve a minimum thickness in all or part of the edge(s) while retaining sufficient mechanical properties to ensure good mechanical strength of the leading and trailing edges of the final blade.
• the fibrous texture of the invention comprises a second part present at the level of the first edge of the blade blade part of the fibrous texture, the second part comprising only two layers of threads of the first plurality of yarns and two layers of yarns of the second plurality of yarns, yarns of the two layers of yarns of the first plurality of yarns binding yarns of the second plurality of yarns on the two layers of threads of the second plurality of threads according to a first determined bonding frequency and a third part present at the level of the second edge of the blade blade part of the fibrous texture, the third part comprising only two layers of threads of the first plurality of yarns and two layers of yarns of the second plurality of yarns, yarns of the two layers of yarns of the first plurality of yarns binding yarns of the second plurality of yarns to the next two layers of yarns of the second plurality of yarns a second bonding frequency, the second part having a first yarn density of the second plurality of yarns and the
• the fibrous texture has very thin parts which have a good ability to deform, that is to say that these parts are able to withstand significant deformations during the shaping of the texture while maintaining their integrity and, hence their reinforcing function.
• each thread of the first plurality of threads binds threads of the second plurality of threads following a multi-canvas type weave in the second part and following a multi-satin type weave in the third part.
• the second part comprises a first zone having a first density of yarns of the second plurality of yarns and a second zone having a second density of yarns of the second plurality greater than the first density, the bonding frequency in the first zone being greater than the bonding frequency in the second zone.
• each thread of the first plurality of threads binds threads of the second plurality of threads according to a weave of the multi-canvas type in the first zone and according to a weave of the multi-satin type in the second area.
• the invention also relates to a blade made of composite material comprising a fibrous reinforcement densified by a matrix, the blade extending in a longitudinal direction between a root portion or lower portion and a blade tip or an upper portion and , in a transverse direction, between a leading edge and a trailing edge, characterized in that the fibrous reinforcement of the blade body consists of a fibrous texture according to the invention.
• Another subject of the invention is a process for weaving a fibrous structure intended to form the fibrous reinforcement of a blade made of composite material comprising a fibrous reinforcement densified by a matrix, the fibrous structure being woven in a single piece by three-dimensional weaving.
• the texture comprising a blade blade part extending along the transverse direction between a first edge corresponding to a leading edge of the blade and a second edge corresponding to a trailing edge of the blade, the method comprising the weaving of a first part with at least three layers of threads of the first plurality of threads and at least three layers of threads of the second plurality of threads, characterized in that it further comprises the weaving of at least a second part e has at the level of the first or second edge of the blade blade part of the fibrous texture, the second part comprising only two layers of threads from the first plurality of threads and two layers of threads from the second plurality of threads, yarns of the two layers of yarns of the first plurality of yarns binding yarns of the second plurality of yarns to the two layers of yarns of the second plurality of the second plurality of
• the latter comprises the weaving of a second part present at the level of the first edge of the blade blade part of the fibrous texture, the second part comprising only two layers of threads of the first plurality of yarns and two layers of threads of the second plurality of threads, threads of the two layers of threads of the first plurality of threads binding threads of the second plurality of threads on the two layers of threads of the second plurality of threads according to a first determined binding frequency and the weaving of a third part present at the level of the second edge of the blade blade part of the fibrous texture, the third part comprising only two layers of threads of the first plurality of threads and two layers of threads of the second plurality of threads, threads of the two layers of threads of the first plurality of threads binding threads of the second plurality of threads on the two layers of threads of the second plurality of threads according to a second bonding frequency, the second part having a first yarn density of the second plurality of
• each thread of the first plurality of threads binds threads of the second plurality of threads according to a weave of the multi-canvas type in the second part and according to a weave of the multi-satin type in the third part.
• the second part comprises a first zone having a first density of yarns of the second plurality of yarns and a second zone having a second density of yarns of the second plurality greater than the first density , the bonding frequency in the first zone being higher than the bonding frequency in the second zone.
• each thread of the first plurality of threads binds threads of the second plurality of threads according to a weave of the multi-canvas type in the first zone and according to a weave of the multi-satin type in the second area.
• the present invention also relates to a process for manufacturing a composite material blade comprising the following steps:
• Figure 1 is a schematic view illustrating the three-dimensional weaving of a fibrous structure for the manufacture of an aeronautical engine blade in accordance with one embodiment of the invention
• FIGS. 2A to 2D show, along section II-II in FIG. 1, the various successive weaving weave planes of a portion of the fibrous structure of FIG. 1 intended to form part of the edge dawn attack,
• FIGS. 3A to 3D show, along section III-III in FIG. 1, the various successive weaving weave planes of a portion of the fibrous structure of FIG. of dawn flight,
• Figure 4 is a schematic perspective view of a fibrous blade preform from the fibrous structure of Figure 1,
• Figure 5 is a schematic perspective view of a blade made of composite material obtained by densification by a matrix of the preform of Figure 4.
• the invention generally applies to the production of blade bodies or blades in composite material made from a fibrous texture obtained by three-dimensional (3D) or multilayer weaving.
• Non-limiting examples of such blades are in particular fan blades, outlet guide vanes (called OGV for “Outlet Guide Vane”), inlet guide vanes (called IGV for “Inlet Guide Vane”), variable pitch angle (called V SV for “Variable Stator Vane”), etc.
• a method of manufacturing a fibrous structure in accordance with the invention is described in relation to the manufacture of a turbine engine fan blade.
• the fibrous structure of the invention is obtained by three-dimensional weaving or by multi-layer weaving.
• three-dimensional weaving or “3D weaving” is meant here a mode of weaving by which at least some of the warp yarns bind weft yarns over several weft layers.
• multi-layer weave is meant here a 3D weave with several layers of weft whose basic weave of each layer is equivalent to a classic 2D fabric weave, such as a weave of the plain, satin or twill type, but with certain points of the weave that bind the weft layers together.
• the production of the fibrous structure by 3D or multilayer weaving makes it possible to obtain a connection between the layers, therefore to have good mechanical strength of the fibrous structure and of the part made of composite material obtained, in a single textile operation.
• interlock weave weave is meant herein a 3D weave weave in which each warp layer binds several weft layers together with all the yarns of the same warp column having the same movement in the plane of the weave.
• yarns of different chemical natures between different parts of the fibrous structure in particular between core and skin, to confer particular properties on the part made of composite material obtained, in particular in terms of resistance to oxidation or wear.
• thermostructural composite material reinforced with refractory fibers it is possible to use a preform with carbon fibers in the core and ceramic fibers, for example silicon carbide (SiC), on the surface. in order to increase the wear and oxidation resistance of the composite part at this surface portion.
• SiC silicon carbide
• FIG. 1 very schematically shows a fibrous structure 200 intended to form the fibrous reinforcement of an aircraft engine blade.
• the fibrous structure 200 is obtained by three-dimensional weaving, or 3D weaving, or by multi-layer weaving carried out in a known way by means of a loom of the jacquard type on which a bundle of yarns or strands of warps 201 has been placed in a plurality of layers, the warp yarns linking weft yarns or strands 202 also arranged in a plurality of layers.
• a detailed embodiment of a fibrous preform intended to form the fibrous reinforcement of a blade for an aeroengine is in particular described in detail in documents US 7 101 154, US 7241 112 and WO 2010/061140.
• the fibrous structure 200 is woven in the form of a strip extending generally in a direction D c corresponding to the direction of the warp threads 201 and the longitudinal direction of the blade to be produced.
• the fibrous structure has a thickness along a direction D e which is variable both in the direction D c and in a direction D T perpendicular to the direction D c and corresponding to the direction of the weft yarns 202.
• the thickness variations are determined according to the longitudinal thickness and the profile of the blade of the dawn to be produced.
• the fibrous structure 200 In its part intended to form a root preform, the fibrous structure 200 has in the direction D c a part of extra thickness 203 determined according to the thickness of the root of the blade to be produced.
• the fibrous structure 200 is extended by a part of decreasing thickness 204 intended to form the shank of the blade then by a part 205 intended to form the blade of the dawn.
• the fibrous structure 200 is woven in a single piece and must have, after cutting the nonwoven yarns, the shape and the almost final dimensions of the blade (“net shape”).
• the reduction in thickness of the preform is obtained by gradually removing layers of warp and weft during the weaving.
• the part 205 has in the direction D T a profile of variable thickness between its edge 205a intended to form the leading edge of the blade and its edge 205b intended to form the trailing edge of the blade to be produced, a portion extra thickness (portion 212 in Figure 1) being present between the edges 205a and 205b.
• Part 205 includes a first portion 212 constituting the majority of part 205.
• Portion 212 is located between a second portion 210 and a third portion 211 corresponding respectively to edges 205a and 205b of part 205.
• the first portion 212 not needing to be thin, it is produced by three-dimensional weaving, between at least three layers of warp threads and at least three layers of weft threads.
• the edges 205a and 205b of the part 205 each have a thickness along the direction D e that is significantly less than that of the portion 212 in order to allow the formation of a blade with a leading edge and an edge very fine leaks.
• the portions 210 and 211 are woven with only two layers of warp threads and two layers of weft threads, which makes it possible to achieve a minimum thickness while retaining sufficient mechanical properties to ensure mechanical strength of the edges of attack and flight of the final dawn.
• the threads of the two layers of warp threads bind threads of the two layers of weft threads according to a determined binding frequency in order to adapt to the density of threads of frame in the part of the fibrous texture considered. More precisely, if the portion considered has a low density of weft threads which is measured by the number of weft threads per centimeter and which is materialized by more spaced columns of weft threads, a weave weave is used with a frequency bonding of the high warp threads in order to avoid too loose weaving which is detrimental to the mechanical strength of the final blade.
• a weaving weave is used with a lower warp yarn binding frequency to bind the weft yarns.
• the weft yarn density is considered low when the number of weft yarns in the direction D c and per weft layer is less than or equal to 3.33 weft yarns per centimeter while the density of weft threads is considered high when the number of weft threads is greater than 3.33 threads per centimeter.
• the fibrous texture 200 has a higher density of weft yarns in the second portion 210 corresponding to the edge 205a of the part 205 than in the third portion 211 corresponding to the edge 205b of the part 205. Consequently , the portion 211 is woven with a weaving weave having a bonding frequency of the warp threads greater than the bonding frequency of the weaving weave used to weave the portion 210.
• FIGS. 2A to 2D represent the various successive planes of a weaving weave used in the portion 210 which comprises two layers of weft yarns Ti and T 2 .
• the warp yarns 2011 and 202 2 respectively belong to two layers of warp yarns.
• the weaving weave here corresponds to a multi-twill weave with a pitch of 4.
• the warp yarns 201 1 and 201 2 represented in FIGS. 2A to 2D have a low bonding frequency due to the density of yarns of high frame in portion 210.
• FIGS. 3A to 3D represent the different successive planes of a weaving weave used in the portion 211 which comprises two layers of weft threads T 3 and T 4 .
• the warp threads 201 3 and 202 4 respectively belong to two layers of warp threads.
• the weaving weave here corresponds to an alternation, i.e. one weave plane out of two, between a multi-canvas weave and a multi-twill weave with a pitch of 4.
• Warp threads 201 3 and 201 4 shown in Figures 3A have 3D has a high bond frequency and higher than the bond frequency in portion 210 due to the lower weft density in portion 211.
• weaving weaves shown in Figures 2A-2D and 3A-3D are only examples of weaves having different warp yarn bonding frequencies matched to the weft yarn density.
• Other weaving weaves defined from a multi-twill weave, a multi-linen weave, or a mixture of these two types of weave can be used.
• the weft yarn density can vary in particular along the direction D c .
• a first zone of this portion having a low weft yarn density is woven with a weaving weave having a high warp yarn bonding frequency
• a second zone of the same portion having a weft greater than in the first zone is woven with a weaving weave having a bonding frequency of the warp yarns lower than the bonding frequency of the weave in the first zone.
• the first portion 212 is woven with an interlock weave between at least three layers of warp yarns and three layers of warp yarns. frame.
• the reduction in thickness along the direction D e of the second and third portions 210, 211 is obtained by gradually removing weft and warp threads in the first portion 212 near its junction with the second and third portions 210 , 211 .
• the fibrous preform 300 illustrated in FIG. 4 and woven in a single piece is then obtained.
• the preform 300 comprises a portion 303 of extra thickness, corresponding to the portion 203 of the fibrous structure 200, extended by a portion of decreasing thickness 304 corresponding to the portion 204 of the fibrous structure 200.
• the preform 300 also comprises a blade portion 305 corresponding to the part 205 of the fibrous structure 200 which extends in the direction D T between a leading edge part 305a and a trailing edge part 205b corresponding respectively to the edges 205a and 205b of the fibrous structure 200.
• the blade part 305 further has in the direction D T a portion of extra thickness 305e corresponding to the portion 212 of the fibrous structure 200.
• the leading edge part 305a and the trailing edge part 305b present in the direction D e thicknesses e305a and e305b respectively which are much less than the thickness e305c of the extra thickness portion 305e.
• the fibrous preform 300 is then densified in order to form a blade 10 of composite material illustrated in FIG. 5.
• the densification of the fibrous preform intended to form the fibrous reinforcement of the part to be manufactured consists in filling the porosity of the preform, in all or part of the volume thereof, by the material constituting the matrix.
• This densification can be carried out in a manner known per se according to the liquid process (CVL) or the gaseous process (CVI), or the ceramic filler injection process (Slurry Cast) or the impregnation process of a silicon alloy (Ml or RMI) or else following a sequence of one or more of these processes.
• the liquid method consists of impregnating the preform with a liquid composition containing a precursor of the material of the matrix.
• the precursor usually comes in the form of a polymer, such as a high-performance epoxy resin, optionally diluted in a solvent.
• the preform is placed in a sealable mold with a housing having the shape of the final molded vane. Then, we close the mold and inject the liquid matrix precursor (for example a resin) throughout the housing to impregnate the entire fibrous part of the preform.
• the transformation of the precursor into a matrix is carried out by heat treatment, generally by heating the mould, after removal of any solvent and crosslinking of the polymer, the preform still being maintained in the mold having a shape corresponding to that of the part to be made.
• the heat treatment consists in pyrolyzing the precursor to transform the matrix into a carbon or ceramic matrix depending on the precursor used and the pyrolysis conditions.
• liquid ceramic precursors in particular of SiC or SiCN, can be resins of the polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type, while liquid carbon precursors can be resins relatively high coke content, such as phenolic resins.
• the densification of the fibrous preform can be carried out by the well-known process of transfer molding called RTM ("Resin Transfer Moulding").
• RTM Resin Transfer Moulding
• the fiber preform is placed in a mold having the external shape of the part to be produced.
• a thermosetting resin is injected into the internal space of the mold which includes 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 densification of the preform can also be carried out by impregnation of polymer and pyrolysis (PI P), or by impregnation of a slurry ("slurry cast"), containing for example SiC and organic binders, followed by infiltration with liquid silicon (“Melt infiltration”).
• PI P polymer and pyrolysis
• slurry cast a slurry
• SiC silica
• Melt infiltration infiltration with liquid silicon
• the densification of the fibrous preform can also be carried out, in a known way, by gaseous route by chemical vapor infiltration of the matrix (CVI).
• CVI matrix
• the fibrous preform corresponding to the fibrous reinforcement of the blade to be produced is placed in a furnace in which a reaction gas phase is admitted.
• the pressure and the temperature prevailing in the oven and the composition of the gaseous phase are chosen so as to allow the diffusion of the gaseous phase within the porosity of the preform to form the matrix there by deposition, at the heart of the material in contact fibres, of a solid material resulting from the decomposition of a constituent of the gaseous phase or from a reaction between several constituents, contrary to the pressure and temperature conditions specific to CVD ("Chemical Vapor Deposition”) processes which lead to exclusively to a deposit on the surface of the material.
• CVD Chemical Vapor Deposition
• SiC matrix can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of MTS while a carbon matrix can be obtained with hydrocarbon gases such as methane and/or propane giving carbon by cracking.
• MTS methyltrichlorosilane
• a densification combining the liquid route and the gas route can also be used to facilitate the implementation, limit the costs and the manufacturing cycles while obtaining satisfactory characteristics for the intended use.
• the densification processes described above make it possible to produce, from the fibrous structure of the invention, mainly parts made of composite material with an organic matrix (CMO), a carbon matrix (C/C) and a ceramic matrix (CMC). ).
• CMO organic matrix
• C/C carbon matrix
• CMC ceramic matrix
• the fibrous structure is impregnated with a slip loaded with refractory oxide particles. After elimination of the liquid phase of the slip, the preform thus obtained is subjected to a heat treatment in order to sinter the particles and obtain a refractory oxide matrix.
• the impregnation of the structure can be carried out with processes using a pressure gradient, such as injection molding type processes known as “RTM” or submicron powder suction known as “APS”.
• a blade 10 of composite material which, as illustrated in FIG. 5, comprises in its lower part a foot 103 formed by the extra thickness part 303 of the fiber preform 300 which is extended by a stilt 104 formed by the part of decreasing thickness 304 of the preform 300 and a blade 105 formed by the blade part 305 of the fiber preform 300.
• the blade 105 comprises a leading edge 105a and a trailing edge 105b corresponding respectively to the leading edge 305a and trailing edge 305b portions of the fiber preform 300 and a portion of extra thickness 105e corresponding to the portion of extra thickness 305e of the fibrous preform 300.
• the leading edge 105a and the trailing edge 105b have a very small thickness because the fibrous reinforcement in these parts of the blade comprises only two layers of weft yarns bonded together by only two layers of weft threads as explained previously.
• the mechanical strength of these very thin parts is optimized by adapting the bonding frequency as a function of the weft yarn density.
• the fibrous structure and its method of manufacture according to the present invention can in particular be used to produce turbomachine blades having a more complex geometry than the blade represented in FIG. 5, such as blades comprising, in addition to that of FIG. , one or more platforms making it possible to perform functions such as those of vein sealing, anti-tipping, etc.
• the fibrous structure and its method of manufacture according to the present invention can for example be used for the manufacture of sectors of vane for gas turbine distributors or rectifiers.

Landscapes

• Engineering & Computer Science (AREA)
• Textile Engineering (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• Materials Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Woven Fabrics (AREA)
• Turbine Rotor Nozzle Sealing (AREA)
• Treatment Of Fiber Materials (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=77519145

Family Applications (1)

Country Status (5)

Family Cites Families (4)

• 2021
  • 2021-03-03 FR FR2102044A patent/FR3120325B1/fr active Active
• 2022
  • 2022-03-01 EP EP22711271.1A patent/EP4301917A1/de active Pending
  • 2022-03-01 CN CN202280018442.1A patent/CN116940724A/zh active Pending
  • 2022-03-01 WO PCT/FR2022/050365 patent/WO2022185007A1/fr active Application Filing
  • 2022-03-01 US US18/546,902 patent/US20240133086A1/en active Pending

Also Published As

Similar Documents

Legal Events