EP3678854A1 - Method for manufacturing a composite material part provided with a sensor - Google Patents

Method for manufacturing a composite material part provided with a sensor

Info

Publication number
EP3678854A1
EP3678854A1 EP18783545.9A EP18783545A EP3678854A1 EP 3678854 A1 EP3678854 A1 EP 3678854A1 EP 18783545 A EP18783545 A EP 18783545A EP 3678854 A1 EP3678854 A1 EP 3678854A1
Authority
EP
European Patent Office
Prior art keywords
holding member
preform
densification
sensor
composite material
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP18783545.9A
Other languages
German (de)
French (fr)
Inventor
Eric MARIAGE
Daniel BARRIERE
Rémi Pierre Robert Bouvier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Ceramics SA
Original Assignee
Safran Ceramics SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Ceramics SA filed Critical Safran Ceramics SA
Publication of EP3678854A1 publication Critical patent/EP3678854A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
    • C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
    • C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
    • C04B35/573—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide obtained by reaction sintering or recrystallisation
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62844—Coating fibres
    • C04B35/62857—Coating fibres with non-oxide ceramics
    • C04B35/6286—Carbides
    • C04B35/62863—Silicon carbide
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62884—Coating the powders or the macroscopic reinforcing agents by gas phase techniques
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    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
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    • C04B35/626—Preparing or treating the powders individually or as batches ; preparing or treating macroscopic reinforcing agents for ceramic products, e.g. fibres; mechanical aspects section B
    • C04B35/628—Coating the powders or the macroscopic reinforcing agents
    • C04B35/62886—Coating the powders or the macroscopic reinforcing agents by wet chemical techniques
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/71—Ceramic products containing macroscopic reinforcing agents
    • C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
    • C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
    • C04B37/008—Joining burned ceramic articles with other burned ceramic articles or other articles by heating by means of an interlayer consisting of an organic adhesive, e.g. phenol resin or pitch
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
    • G01K1/14—Supports; Fastening devices; Arrangements for mounting thermometers in particular locations
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
    • G01K7/02—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using thermoelectric elements, e.g. thermocouples
    • C—CHEMISTRY; METALLURGY
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    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/38—Non-oxide ceramic constituents or additives
    • C04B2235/3817—Carbides
    • C04B2235/3826—Silicon carbides
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    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
    • C04B2235/483—Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5244—Silicon carbide
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    • C04B2235/5216—Inorganic
    • C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
    • C04B2235/5248—Carbon, e.g. graphite
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    • C04B2235/5208—Fibers
    • C04B2235/5252—Fibers having a specific pre-form
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    • C04B2235/614—Gas infiltration of green bodies or pre-forms
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
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    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/61—Joining two substrates of which at least one is porous by infiltrating the porous substrate with a liquid, such as a molten metal, causing bonding of the two substrates, e.g. joining two porous carbon substrates by infiltrating with molten silicon
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    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
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    • C04B2237/62—Forming laminates or joined articles comprising holes, channels or other types of openings
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/53—Building or constructing in particular ways by integrally manufacturing a component, e.g. by milling from a billet or one piece construction

Definitions

  • the invention relates to a method of manufacturing a composite material part provided with a sensor, particularly in the context of aeronautical applications.
  • the sensor holding members are fixed on a surface of the part by means of a ceramic adhesive.
  • the measurement sensors are then inserted in housings defined by the holding members.
  • the holding on the piece of such instrumentation must then be provided for several hundred hours.
  • the present invention aims to improve the maintenance of measuring sensors on the surface of a composite material part.
  • the invention proposes a method for manufacturing a composite material part provided with a sensor, the method comprising at least the following steps: assembling a first consolidated or unconsolidated preform of the part to be obtained with a second preform of a holding member,
  • a preform is said to be in the consolidated state when it has undergone a consolidation step during which its initial porosity has been partially filled by a deposition of a consolidation phase, this preform in the consolidated state retaining a residual porosity which can be completely or partially filled during the subsequent co-densification step.
  • consolidation methods are detailed below.
  • a preform is said to be unconsolidated when it lacks such a consolidation phase.
  • the assembly of the first and second preforms is intended to form, after co-densification, the fibrous reinforcement of a structure made of one-piece composite material, which comprises the holding member.
  • the co-densification of the preform of the part and the preform of the holding member makes it possible to obtain better adhesion of the holding member to the underlying part. Keeping the measuring sensors in the workpiece is therefore reinforced.
  • the holding member comprises two parts forming tabs connected to the part and located on either side of the housing, and a connecting portion closing the housing on the side opposite the part and connecting The paws.
  • the holding member comprises two spaced apart holding members located on either side of the housing, the spacing between the two holding elements decreasing as one moves away from the workpiece. .
  • the co-densification is carried out by chemical vapor infiltration.
  • co-densification is carried out by a liquid route.
  • a silicon carbide matrix is deposited in the porosity of the first and second preforms during co-densification.
  • the senor is a temperature sensor.
  • the part is a divergent nozzle.
  • FIGS. 1 to 4 illustrate the various steps of an exemplary method according to the invention
  • FIG. 5 illustrates a composite part provided with sensors obtained by implementing another example method according to the invention
  • FIG. 6 is a photograph of a part of a composite part provided with a holding member similar to that of FIG. 5;
  • FIG. 7 illustrates a divergent provided with holding members and measuring sensors made according to the invention.
  • Figures 1 to 4 illustrate the different steps of manufacturing a composite material part to be instrumented by at least one measuring sensor.
  • FIG. 1 illustrates a first preform 1 of the composite material part to be manufactured and a second preform 2 of a holding member intended to hold at least one measuring sensor on the part to be manufactured.
  • the first preform 1 and the second preform 2 are fibrous preforms, each made by multilayer weaving between a plurality of warp yarn layers and a plurality of weft yarn layers.
  • the multilayer weave produced can be in particular an "interlock" weave weave, that is to say a weave weave in which each layer of weft yarn binds several layers of warp yarns with all the yarns of the same weft column having the same movement in the plane of the weave.
  • each layer of warp yarn binds several layers of weft yarns with all the yarns of the same warp column having the same movement in the plane of the weave, the roles between the warp yarns and the warp yarns. frame being interchangeable.
  • the first and second fibrous preforms 1, 2 may be formed of carbon son.
  • the first and second fibrous preforms 1, 2 may be formed of ceramic son such as silicon carbide son.
  • the son used may be silicon carbide (SiC) son provided under the name "Nicalon”, “Hi-Nicalon” or “Hi-Nicalon-S” by the Japanese company Nippon Carbon or “Tyranno SA3” by the company UBE and having for example a title (number of filaments) of 0.5K (500 filaments).
  • SiC silicon carbide
  • the second preform 2 is made so as to have a profile in the form of arch or bridge. More specifically, the preform 2 of the holding member comprises two parts 2-1, 2-2 forming tabs and a 2-3 joining portion extending between the parts 2-1, 2-2. The parts 2-1, 2-2, 2-3 delimit a cavity 2- 4. The cavity 2-4 is intended to form a housing for receiving at least one measuring sensor once the holding member fixed to the composite part.
  • the first fibrous preform 1 may possibly, but not necessarily, be consolidated by deposition of a consolidation phase in the porosity of the first preform 1, this consolidation phase may be deposited by gaseous or liquid route. known way in itself.
  • the liquid process consists of impregnating the preform with a liquid composition containing a precursor of the material of the consolidation phase.
  • the 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 that can be closed waterproof. Then, the mold is closed and the liquid phase precursor consolidation (eg a resin) is injected into the mold to impregnate the preform.
  • the conversion of the precursor into the consolidation phase is carried out by heat treatment, generally by heating the mold, after removal of the optional solvent and crosslinking of the polymer.
  • the heat treatment comprises a step of pyrolysis of the precursor to form the ceramic material consolidation phase.
  • liquid precursors of ceramics in particular of SiC, may be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type resins.
  • PCS polycarbosilane
  • PTCS polytitanocarbosilane
  • PSZ polysilazane
  • the fiber preform In the gaseous process (chemical vapor infiltration of the consolidation phase, "CVI" process), the fiber preform is placed in an oven in which a gaseous reaction phase is admitted.
  • the pressure and the temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the consolidation phase by deposition at the core of the material. in contact with the fibers, a solid material resulting from a decomposition of a component of the gas phase or a reaction between several constituents.
  • the formation of an SiC consolidation phase can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of the MTS.
  • MTS methyltrichlorosilane
  • the second preform 2 may or may not be consolidated before being assembled with the first preform 1.
  • the preforms 1, 2 are then assembled against each other by superposition, so as to form, after co-densification, the fibrous reinforcement of a composite structure in one piece.
  • the parts 2-1, 2-2 forming tabs of the second preform 2 and a surface 1-1 of the first preform 1 are assembled using a layer of adhesive 3.
  • This adhesive layer 3 is for example a graphite-based ceramic glue, for example glue supplied under the name "Graphi-Bond TM 551-R" from AREMCO.
  • the preforms 1, 2 undergo a co-densification step. After co-densification, a structure is obtained in which the first and second preforms are densified and the leg portions 2-1 and 2-2 are fixed to the underlying piece by co-densification.
  • the co-densification of the first and second preforms 1, 2 can be performed by a liquid route.
  • liquid co-densification is carried out by infiltration in the molten state.
  • charges for example reactive charges, the charges being for example chosen from SiC, S13N4, C, B, and mixtures thereof.
  • the introduction of the feeds may, for example, be carried out by slip ("Slurry cast"), by suction of sub-micron powders (APS) or by an injection molding process of the resin injection molding process (" Resin Transfer Molding "or” RTM ”) in which a heat treatment is performed after the injection to evaporate the liquid medium.
  • the first and second preforms 1, 2 are then infiltrated with a melt infiltration composition comprising, for example, silicon in order to form a matrix co-densifying the first and second preforms 1 and 2.
  • a melt infiltration composition comprising, for example, silicon in order to form a matrix co-densifying the first and second preforms 1 and 2.
  • a composite part 10 is thus obtained provided with at least one holding member 11 forming an integral structure.
  • the infiltration composition may consist of molten silicon or alternatively may be in the form of a molten silicon alloy and one or more other components.
  • the constituent (s) present (s) within the silicon alloy may be selected from B, Al, Mo, Ti, and mixtures thereof.
  • the melt infiltration carried out can make it possible to obtain a matrix by reaction between solid charges, for example of C, SiC or Si 3 N 4 introduced by slip or pre-treatment. impregnated, and a molten alloy based on silicon.
  • the reaction can occur at a temperature greater than or equal to 1420 ° C. Given the high temperatures used, it may be advantageous for at least a portion of the first and second preforms to consist of heat-stable fibers, for example of the Hi-Nicalon or even Hi-Nicalon S type.
  • the matrix formed by co-densification may be ceramic material or carbon.
  • liquid co-densification is carried out by injection of a resin, and then polymerization of the latter, in a manner similar to that mentioned above for consolidation.
  • the polymerization step can optionally, but not necessarily, be followed by a pyrolysis step.
  • the co-densification of the first and second preforms 1, 2 may be performed by chemical vapor infiltration so as to obtain the composite part provided with the holding member 11. This type of process is carried out in a similar manner to what has been mentioned above for consolidation.
  • the yarns of the first and second preforms may, prior to co-densification, have been coated with an interphase layer, for example made of PyC, BN or BN doped with silicon, and possibly with a carbide layer, for example in SiC or S13N4.
  • an interphase layer for example made of PyC, BN or BN doped with silicon, and possibly with a carbide layer, for example in SiC or S13N4.
  • an integral structure of composite material having a profile corresponding to that of the assembly of the preforms 1, 2 is obtained.
  • the structure thus obtained is formed of the part 10 provided with of at least one holding member 11.
  • the holding member 11 is formed of two tabs 11-1, 11-2 spaced apart and connected by co-densification to the rest of the structure 10, the dashed lines symbolizing the junction between the lugs 11-1, 11-2 and the rest of the structure 10.
  • the lugs 11-1, 11-2 and a surface 10-1 of the part 10 s extending between the lugs 11-1, 11-2 delimit a housing 12. This housing 12 is closed on the opposite side to the part 10 by a joining portion 11-3 connecting the legs 11-1, 11-2 between them.
  • At least one measurement sensor is then positioned in the housing 12 in order to measure a physical or chemical parameter of the part 10.
  • a measurement sensor is then positioned in the housing 12 in order to measure a physical or chemical parameter of the part 10.
  • two sensors 20 are inserted in the housing 12, a number higher or lower sensors that can be considered.
  • an adhesive eg a ceramic adhesive
  • Figure 5 illustrates an alternative embodiment of a holding member 31 secured to a part 30 of composite material.
  • the holding member 31 is made from a method similar to that of the holding member 11.
  • the holding member 31 is, this time, manufactured from two basic preforms.
  • the two elementary preforms of the holding member 31 have, for example, a bevel shape and are assembled on a surface of a first preform corresponding to the preform of the piece 30 of composite material to be manufactured.
  • the set of these preforms then undergoes a co-densification step, as previously described, so as to obtain a one-piece structure formed of the composite material part 30 provided with at least one holding member 31.
  • the holding member 31 obtained is formed of two holding elements 31-1, 31-2 spaced apart and linked by co-densification to the piece 30.
  • the dashed lines here symbolize the junction between the holding members 31-1, 31-2 and the rest of the piece 30.
  • the holding members 31-1, 31-2 and a surface 30-1 of the piece 30 extending between these elements delimit a dwelling 32.
  • At least one measuring sensor is then inserted into the housing
  • each holding element 31-1, 31-2 is made to present a bevel shape, the bevels approaching each other as one moves away from the piece 30.
  • an adhesive 50 for example a ceramic adhesive may possibly, but not necessarily, be deposited in the housing 32 so as to fill the residual space existing between the two holding members 31-1, 31-2 and the surface 30-1.
  • FIG. 6 shows a photograph of a part of a composite material part comprising a holding element 31-1 or 31-2 constituting the holding member 31. This part was obtained by co-densification of a elementary preform of the holding member 31 with a preform of the composite part. As can be observed, there is co-infiltration between the holding member and the underlying surface, thereby improving the holding of the holding member on the composite part in comparison with the state of the body. existing art.
  • a first plate hereinafter referred to as “Plate No. 1” was directly subjected to shear forces exerted using mechanical test means.
  • a second plate manufactured similarly to Plate No. 1 and referred to below as “No. 2 Plate”, was subjected to thermal shock at 1400 ° C and then experienced shear forces similar to those of plate no. The shear stresses were applied so as to identify the thresholds leading to the tearing of the holding members 11, 31 of the plates No. 1 and No. 2.
  • the table below gives the values of rupture thresholds that have been measured to obtain the tearing of the holding members 11, 31 of the plates No. 1 and No. 2.
  • the holding members 11 and 31 also have a very satisfactory resistance to shearing forces. Indeed, the shear forces necessary to tear the holding members 11, 31 of the plates No. 1 and No. 2 are about ten times higher than thresholds measured in the past for which sensor holding members were fixed to a plate by means of a ceramic glue. It is further observed that the holding members 31 appear to have an even better resistance to shear forces than the holding members 11, which already have a very high resistance to shearing forces.
  • the results obtained confirm that the manufacture of a piece of composite material provided with at least one holding member, obtained by co-densification of a preform of the workpiece with at least one preform of a holding member, considerably improves the holding of the holding member (s) secured to the composite part.
  • the divergent 100 illustrated here is a piece of composite material provided with a plurality of holding members 11, 31 in which are inserted one or more sensors 20, 40 measurement.
  • the measurement sensors 20, 40 are, for example, temperature sensors, for example thermocouples.
  • any other type of measuring sensor for instrumentalizing the composite part may be used, for example a pressure or deformation sensor.

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Abstract

A method for manufacturing a composite material part (10) provided with a measurement sensor (20), the method comprising at least the following steps: - assembling a first consolidated or unconsolidated preform of the part to be obtained with a second preform of a retaining member, - co-densifying the first and second preforms assembled in this way in order to obtain the composite material part (10) provided with the retaining member, and - positioning at least one sensor (20) for sensing a physical or chemical parameter in a housing (12) defined by the retaining member.

Description

Procédé de fabrication d'une pièce en matériau composite munie d'un capteur  Method of manufacturing a composite material part provided with a sensor
Arrière-plan de l'invention Background of the invention
L'invention concerne un procédé de fabrication d'une pièce en matériau composite munie d'un capteur, notamment dans le cadre d'applications aéronautiques.  The invention relates to a method of manufacturing a composite material part provided with a sensor, particularly in the context of aeronautical applications.
Il est connu d'instrumenter des pièces en matériau composite à l'aide de capteurs de mesure en vue de déterminer les sollicitations physiques ou chimiques auxquelles ces pièces sont soumises. Couramment, les capteurs sont fixés sur une ou plusieurs surfaces de la pièce par l'intermédiaire d'organes de maintien. Les mesures retournées par les capteurs permettent alors d'accéder aux sollicitations réelles vues par la pièce en fonctionnement, tels que la température, la pression ou encore la déformation de la pièce.  It is known to instrument composite parts using measuring sensors to determine the physical or chemical stresses to which these parts are subject. Currently, the sensors are attached to one or more surfaces of the part by means of holding members. The measurements returned by the sensors then make it possible to access the real stresses seen by the part in operation, such as the temperature, the pressure or the deformation of the part.
En pratique, les organes de maintien des capteurs sont fixés sur une surface de la pièce par l'intermédiaire d'une colle céramique. Les capteurs de mesure sont ensuite insérés dans des logements définis par les organes de maintien. La tenue sur la pièce d'une telle instrumentation doit alors être assurée durant plusieurs centaines d'heures.  In practice, the sensor holding members are fixed on a surface of the part by means of a ceramic adhesive. The measurement sensors are then inserted in housings defined by the holding members. The holding on the piece of such instrumentation must then be provided for several hundred hours.
Cependant, lorsque la pièce est soumise à de fortes sollicitations, par exemple à des contraintes vibratoires sévères, il se peut que certains organes de maintien se détachent de la pièce sous-jacente sur laquelle ils sont fixés. Le détachement de ces organes de maintien peut alors conduire aux pertes des mesures des capteurs qui étaient précédemment logés dans ces organes. Il serait donc souhaitable de renforcer la tenue des organes de maintien sur la pièce composite afin de limiter le risque potentiel de détachement de ces organes. Obiet et résumé de l'invention  However, when the part is subjected to high loads, for example to severe vibratory stresses, it may be that some holding members are detached from the underlying part to which they are attached. The detachment of these holding members can then lead to losses of the measurements of the sensors that were previously housed in these organs. It would therefore be desirable to strengthen the holding of the holding members on the composite part in order to limit the potential risk of detachment of these organs. Obiet and summary of the invention
La présente invention a pour but d'améliorer le maintien de capteurs de mesure sur la surface d'une pièce en matériau composite.  The present invention aims to improve the maintenance of measuring sensors on the surface of a composite material part.
A cet effet, l'invention propose un procédé de fabrication d'une pièce en matériau composite munie d'un capteur, le procédé comprenant au moins les étapes suivantes : - assemblage d'une première préforme consolidée ou non consolidée de la pièce à obtenir avec une deuxième préforme d'un organe de maintien, For this purpose, the invention proposes a method for manufacturing a composite material part provided with a sensor, the method comprising at least the following steps: assembling a first consolidated or unconsolidated preform of the part to be obtained with a second preform of a holding member,
- co-densification des première et deuxième préformes ainsi assemblées afin d'obtenir la pièce en matériau composite munie de l'organe de maintien, et  co-densification of the first and second preforms thus assembled to obtain the composite material part provided with the holding member, and
- positionnement d'au moins un capteur de mesure d'un paramètre, physique ou chimique, dans un logement défini par l'organe de maintien.  positioning of at least one sensor for measuring a parameter, physical or chemical, in a housing defined by the holding member.
Une préforme est dite à l'état consolidé lorsqu'elle a subi une étape de consolidation durant laquelle sa porosité initiale a été partiellement comblée par un dépôt d'une phase de consolidation, cette préforme à l'état consolidé conservant une porosité résiduelle laquelle peut être en tout ou partie comblée lors de l'étape de co-densification ultérieure. Divers exemples de méthodes de consolidation sont détaillés dans la suite. Une préforme est dite à l'état non consolidé lorsqu'elle est dépourvue d'une telle phase de consolidation.  A preform is said to be in the consolidated state when it has undergone a consolidation step during which its initial porosity has been partially filled by a deposition of a consolidation phase, this preform in the consolidated state retaining a residual porosity which can be completely or partially filled during the subsequent co-densification step. Various examples of consolidation methods are detailed below. A preform is said to be unconsolidated when it lacks such a consolidation phase.
L'assemblage des première et deuxième préformes est destiné à former, après la co-densification, le renfort fibreux d'une structure en matériau composite d'un seul tenant, qui comprend l'organe de maintien. Avantageusement, la co-densification de la préforme de la pièce et de la préforme de l'organe de maintien permet d'obtenir une meilleure adhésion de l'organe de maintien à la pièce sous-jacente. Le maintien des capteurs de mesure à la pièce s'en voit, par conséquent, renforcé.  The assembly of the first and second preforms is intended to form, after co-densification, the fibrous reinforcement of a structure made of one-piece composite material, which comprises the holding member. Advantageously, the co-densification of the preform of the part and the preform of the holding member makes it possible to obtain better adhesion of the holding member to the underlying part. Keeping the measuring sensors in the workpiece is therefore reinforced.
Dans un exemple de réalisation de ce procédé, l'organe de maintien comprend deux parties formant pattes reliées à la pièce et situées de part et d'autre du logement, et une partie de jonction fermant le logement du côté opposé à la pièce et reliant les pattes.  In an exemplary embodiment of this method, the holding member comprises two parts forming tabs connected to the part and located on either side of the housing, and a connecting portion closing the housing on the side opposite the part and connecting The paws.
Dans un exemple de réalisation de ce procédé, l'organe de maintien comprend deux éléments de maintien espacés situés de part et d'autre du logement, l'espacement entre les deux éléments de maintien diminuant lorsque l'on s'éloigne de la pièce.  In an exemplary embodiment of this method, the holding member comprises two spaced apart holding members located on either side of the housing, the spacing between the two holding elements decreasing as one moves away from the workpiece. .
Dans un exemple de réalisation de ce procédé, la co-densification est réalisée par infiltration chimique en phase vapeur.  In an exemplary embodiment of this method, the co-densification is carried out by chemical vapor infiltration.
Dans un autre exemple de réalisation de ce procédé, la co- densification est réalisée par voie liquide. Dans un exemple de réalisation de ce procédé, on dépose une matrice de carbure de silicium dans la porosité des première et deuxième préformes durant la co-densification. In another embodiment of this process, co-densification is carried out by a liquid route. In an exemplary embodiment of this method, a silicon carbide matrix is deposited in the porosity of the first and second preforms during co-densification.
Dans un exemple de réalisation de ce procédé, le capteur est un capteur de température.  In an exemplary embodiment of this method, the sensor is a temperature sensor.
Dans un exemple de réalisation de ce procédé, la pièce est un divergent de tuyère.  In an exemplary embodiment of this method, the part is a divergent nozzle.
Brève description des dessins Brief description of the drawings
D'autres caractéristiques et avantages de l'invention ressortiront de la description suivante de modes particuliers de réalisation de l'invention, donnés à titre d'exemples non limitatifs, en référence aux dessins annexés, sur lesquels :  Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which:
- les figures 1 à 4 illustrent les différentes étapes d'un exemple de procédé selon l'invention,  FIGS. 1 to 4 illustrate the various steps of an exemplary method according to the invention,
- la figure 5 illustre une pièce composite munie de capteurs obtenue par mise en œuvre d'un autre exemple de procédé selon l'invention,  FIG. 5 illustrates a composite part provided with sensors obtained by implementing another example method according to the invention,
- la figure 6 est une photographie d'une partie d'une pièce composite munie d'un organe de maintien analogue à celui de la figure 5, FIG. 6 is a photograph of a part of a composite part provided with a holding member similar to that of FIG. 5;
- la figure 7 illustre un divergent muni d'organes de maintien et de capteurs de mesure réalisé selon l'invention. - Figure 7 illustrates a divergent provided with holding members and measuring sensors made according to the invention.
Description détaillée de modes de réalisation Detailed description of embodiments
Les figures 1 à 4 illustrent les différentes étapes de fabrication d'une pièce en matériau composite destinée à être instrumentée par au moins un capteur de mesure.  Figures 1 to 4 illustrate the different steps of manufacturing a composite material part to be instrumented by at least one measuring sensor.
La figure 1 illustre une première préforme 1 de la pièce en matériau composite à fabriquer et une deuxième préforme 2 d'un organe de maintien destiné à assurer le maintien d'au moins un capteur de mesure sur la pièce à fabriquer.  FIG. 1 illustrates a first preform 1 of the composite material part to be manufactured and a second preform 2 of a holding member intended to hold at least one measuring sensor on the part to be manufactured.
La première préforme 1 et la deuxième préforme 2 sont des préformes fibreuses, chacune réalisée par tissage multicouche entre une pluralité de couches de fils de chaîne et une pluralité de couches de fils de trame.  The first preform 1 and the second preform 2 are fibrous preforms, each made by multilayer weaving between a plurality of warp yarn layers and a plurality of weft yarn layers.
Le tissage multicouche réalisé peut être notamment un tissage à armure "interlock", c'est-à-dire une armure de tissage dans laquelle chaque couche de fils de trame lie plusieurs couches de fils de chaîne avec tous les fils d'une même colonne de trame ayant le même mouvement dans le plan de l'armure. En alternative, chaque couche de fils de chaîne lie plusieurs couches de fils de trame avec tous les fils d'une même colonne de chaîne ayant le même mouvement dans le plan de l'armure, les rôles entre les fils de chaîne et les fils de trame étant interchangeables. The multilayer weave produced can be in particular an "interlock" weave weave, that is to say a weave weave in which each layer of weft yarn binds several layers of warp yarns with all the yarns of the same weft column having the same movement in the plane of the weave. Alternatively, each layer of warp yarn binds several layers of weft yarns with all the yarns of the same warp column having the same movement in the plane of the weave, the roles between the warp yarns and the warp yarns. frame being interchangeable.
D'autres types de tissage multicouche pourront être utilisés. Différents modes de tissage multicouche utilisables sont notamment décrits dans le document WO 2006/136755.  Other types of multilayer weaving may be used. Various multilayer weave modes that can be used are described in particular in document WO 2006/136755.
Dans un exemple de réalisation, les première et deuxième préformes 1, 2 fibreuses peuvent être formées de fils de carbone. En variante, les première et deuxième préformes fibreuses 1, 2 peuvent être formées de fils céramiques tels que des fils de carbure de silicium.  In an exemplary embodiment, the first and second fibrous preforms 1, 2 may be formed of carbon son. Alternatively, the first and second fibrous preforms 1, 2 may be formed of ceramic son such as silicon carbide son.
Ainsi, dans un exemple de réalisation, les fils utilisés peuvent être des fils de carbure de silicium (SiC) fournis sous la dénomination « Nicalon », « Hi-Nicalon » ou « Hi-Nicalon-S » par la société japonaise Nippon Carbon ou « Tyranno SA3 » par la société UBE et ayant par exemple un titre (nombre de filaments) de 0,5K (500 filaments).  Thus, in one embodiment, the son used may be silicon carbide (SiC) son provided under the name "Nicalon", "Hi-Nicalon" or "Hi-Nicalon-S" by the Japanese company Nippon Carbon or "Tyranno SA3" by the company UBE and having for example a title (number of filaments) of 0.5K (500 filaments).
Dans l'exemple illustré sur les figures 1 à 4, la deuxième préforme 2 est réalisée de sorte à présenter un profil en forme d'arche ou de pontet. Plus précisément, la préforme 2 de l'organe de maintien comprend deux parties 2-1, 2-2 formant pattes et une partie 2-3 de jonction s'étendant entre les parties 2-1, 2-2. Les parties 2-1, 2-2, 2-3 délimitent une cavité 2- 4. La cavité 2-4 est destinée à former un logement pour la réception d'au moins un capteur de mesure une fois l'organe de maintien fixé à la pièce composite.  In the example illustrated in Figures 1 to 4, the second preform 2 is made so as to have a profile in the form of arch or bridge. More specifically, the preform 2 of the holding member comprises two parts 2-1, 2-2 forming tabs and a 2-3 joining portion extending between the parts 2-1, 2-2. The parts 2-1, 2-2, 2-3 delimit a cavity 2- 4. The cavity 2-4 is intended to form a housing for receiving at least one measuring sensor once the holding member fixed to the composite part.
Après tissage, la première préforme 1 fibreuse peut éventuellement, mais non-nécessairement, être consolidée par dépôt d'une phase de consolidation dans la porosité de la première préforme 1, cette phase de consolidation pouvant être déposée par voie gazeuse ou par voie liquide de façon connue en soi.  After weaving, the first fibrous preform 1 may possibly, but not necessarily, be consolidated by deposition of a consolidation phase in the porosity of the first preform 1, this consolidation phase may be deposited by gaseous or liquid route. known way in itself.
Le procédé par voie liquide consiste à imprégner la préforme par une composition liquide contenant un précurseur du matériau de la phase de consolidation. Le précurseur se présente habituellement sous forme d'un polymère, tel qu'une résine, éventuellement dilué dans un solvant. La préforme est placée dans un moule pouvant être fermé de manière étanche. Ensuite, on referme le moule et on injecte le précurseur liquide de phase de consolidation (par exemple une résine) dans le moule afin d'imprégner la préforme. The liquid process consists of impregnating the preform with a liquid composition containing a precursor of the material of the consolidation phase. The 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 that can be closed waterproof. Then, the mold is closed and the liquid phase precursor consolidation (eg a resin) is injected into the mold to impregnate the preform.
La transformation du précurseur en phase de consolidation est réalisée par traitement thermique, généralement par chauffage du moule, après élimination du solvant éventuel et réticulation du polymère.  The conversion of the precursor into the consolidation phase is carried out by heat treatment, generally by heating the mold, after removal of the optional solvent and crosslinking of the polymer.
Dans le cas de la formation d'une phase de consolidation en matériau céramique, le traitement thermique comporte une étape de pyrolyse du précurseur pour former la phase de consolidation en matériau céramique. A titre d'exemple, des précurseurs liquides de céramique, notamment de SiC, peuvent être des résines de type polycarbosilane (PCS) ou polytitanocarbosilane (PTCS) ou polysilazane (PSZ). Plusieurs cycles consécutifs, depuis l'imprégnation jusqu'au traitement thermique, peuvent être réalisés pour parvenir à la consolidation souhaitée.  In the case of the formation of a consolidation phase of ceramic material, the heat treatment comprises a step of pyrolysis of the precursor to form the ceramic material consolidation phase. By way of example, liquid precursors of ceramics, in particular of SiC, may be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) type resins. Several consecutive cycles, from the impregnation to the heat treatment, can be carried out to achieve the desired consolidation.
Dans le procédé par voie gazeuse (infiltration chimique en phase vapeur de la phase de consolidation ; procédé « CVI »), la préforme fibreuse est placée dans un four dans lequel est admise une phase gazeuse réactionnelle. La pression et la température régnant dans le four et la composition de la phase gazeuse sont choisies de manière à permettre la diffusion de la phase gazeuse au sein de la porosité de la préforme pour y former la phase de consolidation par dépôt, au cœur du matériau au contact des fibres, d'un matériau solide résultant d'une décomposition d'un constituant de la phase gazeuse ou d'une réaction entre plusieurs constituants.  In the gaseous process (chemical vapor infiltration of the consolidation phase, "CVI" process), the fiber preform is placed in an oven in which a gaseous reaction phase is admitted. The pressure and the temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform to form the consolidation phase by deposition at the core of the material. in contact with the fibers, a solid material resulting from a decomposition of a component of the gas phase or a reaction between several constituents.
La formation d'une phase de consolidation SiC peut être obtenue avec du méthyltrichlorosilane (MTS) donnant du SiC par décomposition du MTS.  The formation of an SiC consolidation phase can be obtained with methyltrichlorosilane (MTS) giving SiC by decomposition of the MTS.
Par ailleurs, la deuxième préforme 2 peut être ou non consolidée avant d'être assemblée avec la première préforme 1.  Moreover, the second preform 2 may or may not be consolidated before being assembled with the first preform 1.
Les préformes 1, 2 sont ensuite assemblées l'une contre l'autre par superposition, de sorte à former, après la co-densification, le renfort fibreux d'une structure composite d'un seul tenant. Dans l'exemple illustré sur la figure 2, les parties 2-1, 2-2 formant pattes de la deuxième préforme 2 et une surface 1-1 de la première préforme 1 sont assemblées à l'aide d'une couche d'adhésif 3. Cette couche d'adhésif 3 est par exemple une colle céramique à base de graphite, par exemple la colle fournie sous la dénomination « Graphi-Bond™ 551-R » de la société AREMCO. The preforms 1, 2 are then assembled against each other by superposition, so as to form, after co-densification, the fibrous reinforcement of a composite structure in one piece. In the example illustrated in Figure 2, the parts 2-1, 2-2 forming tabs of the second preform 2 and a surface 1-1 of the first preform 1 are assembled using a layer of adhesive 3. This adhesive layer 3 is for example a graphite-based ceramic glue, for example glue supplied under the name "Graphi-Bond ™ 551-R" from AREMCO.
Une fois assemblées l'une à l'autre, les préformes 1, 2 subissent une étape de co-densification. On obtient après la co-densification une structure dans laquelle les première et deuxième préformes sont densifiées et les parties formant pattes 2-1 et 2-2 sont fixées à la pièce sous-jacente par co-densification.  Once assembled to each other, the preforms 1, 2 undergo a co-densification step. After co-densification, a structure is obtained in which the first and second preforms are densified and the leg portions 2-1 and 2-2 are fixed to the underlying piece by co-densification.
La co-densification des première et deuxième préformes 1, 2 peut être réalisée par voie liquide.  The co-densification of the first and second preforms 1, 2 can be performed by a liquid route.
Dans un premier exemple la co-densification par voie liquide est réalisée par infiltration à l'état fondu. Il y a tout d'abord introduction, dans la porosité des première et deuxième préformes 1, 2 assemblées, de charges, par exemple de charges réactives les charges étant par exemple choisies parmi SiC, S13N4, C, B, et leurs mélanges. L'introduction des charges peut, par exemple, être effectuée par voie barbotine (« Slurry cast »), par aspiration de poudres sub-microniques (APS) ou par un procédé d'injection du type procédé de moulage par injection de résine (« Resin Transfer Molding » ou « RTM ») dans lequel un traitement thermique est effectué après l'injection pour faire évaporer le milieu liquide.  In a first example, liquid co-densification is carried out by infiltration in the molten state. First, there is introduced, in the porosity of the first and second preforms 1, 2 assembled, charges, for example reactive charges, the charges being for example chosen from SiC, S13N4, C, B, and mixtures thereof. The introduction of the feeds may, for example, be carried out by slip ("Slurry cast"), by suction of sub-micron powders (APS) or by an injection molding process of the resin injection molding process (" Resin Transfer Molding "or" RTM ") in which a heat treatment is performed after the injection to evaporate the liquid medium.
Une fois les charges introduites, les première et deuxième préformes 1, 2 sont ensuite infiltrées avec une composition d'infiltration à l'état fondu comportant par exemple du silicium afin de former une matrice co-densifiant les première et deuxième préformes 1 et 2. Comme illustré sur la figure 3, on obtient ainsi une pièce 10 composite munie d'au moins un organe de maintien 11 formant une structure d'un seul tenant. La composition d'infiltration peut être constituée de silicium fondu ou en variante être sous la forme d'un alliage fondu de silicium et d'un ou plusieurs autres constituants. Le(s) constitua nt(s) présent(s) au sein de l'alliage de silicium peuvent être choisi(s) parmi B, Al, Mo, Ti, et leurs mélanges.  Once the charges have been introduced, the first and second preforms 1, 2 are then infiltrated with a melt infiltration composition comprising, for example, silicon in order to form a matrix co-densifying the first and second preforms 1 and 2. As illustrated in FIG. 3, a composite part 10 is thus obtained provided with at least one holding member 11 forming an integral structure. The infiltration composition may consist of molten silicon or alternatively may be in the form of a molten silicon alloy and one or more other components. The constituent (s) present (s) within the silicon alloy may be selected from B, Al, Mo, Ti, and mixtures thereof.
Lorsque des charges réactives sont utilisées, sensiblement l'intégralité des charges réactives peut être consommée durant la réaction entre la composition d'infiltration et les charges réactives. En variante, seule une partie des charges réactives est consommée durant cette réaction. Dans un exemple de réalisation, l'infiltration à l'état fondu réalisée peut permettre l'obtention d'une matrice par réaction entre des charges solides, par exemple de type C, SiC ou Si3N4 introduites par voie barbotine ou pré-imprégnées, et un alliage fondu à base de silicium. La réaction peut se produire à une température supérieure ou égale à 1420°C. Compte tenu des températures élevées mises en œuvre, il peut être avantageux qu'une partie au moins des première et deuxième préformes soit constituée de fibres thermostables, par exemple de type Hi-Nicalon voire Hi-Nicalon S. When reactive charges are used, substantially all of the reactive charges may be consumed during the reaction between the infiltration composition and the reactive charges. Alternatively, only a portion of the reactive charges are consumed during this reaction. In one exemplary embodiment, the melt infiltration carried out can make it possible to obtain a matrix by reaction between solid charges, for example of C, SiC or Si 3 N 4 introduced by slip or pre-treatment. impregnated, and a molten alloy based on silicon. The reaction can occur at a temperature greater than or equal to 1420 ° C. Given the high temperatures used, it may be advantageous for at least a portion of the first and second preforms to consist of heat-stable fibers, for example of the Hi-Nicalon or even Hi-Nicalon S type.
La matrice formée par co-densification peut être en matériau céramique ou en carbone.  The matrix formed by co-densification may be ceramic material or carbon.
Dans un deuxième exemple, la co-densification par voie liquide est réalisée par injection d'une résine, puis polymérisation de cette dernière, de manière similaire à ce qui a été évoqué plus haut pour la consolidation. L'étape de polymérisation peut éventuellement, mais non nécessairement, être ensuite suivie d'une étape de pyrolyse.  In a second example, liquid co-densification is carried out by injection of a resin, and then polymerization of the latter, in a manner similar to that mentioned above for consolidation. The polymerization step can optionally, but not necessarily, be followed by a pyrolysis step.
En variante, la co-densification des première et deuxième préformes 1, 2 peut être réalisée par infiltration chimique en phase vapeur de sorte à obtenir la pièce 10 composite munie de l'organe de maintien 11. Ce type de procédé est réalisé de manière similaire a ce qui a été évoqué plus haut pour la consolidation.  Alternatively, the co-densification of the first and second preforms 1, 2 may be performed by chemical vapor infiltration so as to obtain the composite part provided with the holding member 11. This type of process is carried out in a similar manner to what has been mentioned above for consolidation.
Les fils des première et deuxième préformes peuvent, avant la co- densification, avoir été revêtus d'une couche d'interphase, par exemple en PyC, BN ou BN dopé par du silicium, et éventuellement d'une couche de carbure, par exemple en SiC ou S13N4.  The yarns of the first and second preforms may, prior to co-densification, have been coated with an interphase layer, for example made of PyC, BN or BN doped with silicon, and possibly with a carbide layer, for example in SiC or S13N4.
Quel que soit le procédé de co-densification choisi, on obtient une structure d'un seul tenant en matériau composite présentant un profil correspondant à celui de l'assemblage des préformes 1, 2. La structure ainsi obtenue est formée de la pièce 10 munie d'au moins un organe de maintien 11. Dans l'exemple illustré sur la figure 3, l'organe de maintien 11 est formé de deux pattes 11-1, 11-2 espacées entre elles et liées par co-densification au reste de la structure 10, les traits pointillés symbolisant la jonction entre les pattes 11-1, 11-2 et le reste de la structure 10. Les pattes 11-1, 11-2 ainsi qu'une surface 10-1 de la pièce 10 s'étendant entre les pattes 11-1, 11-2 délimitent un logement 12. Ce logement 12 est fermé du côté opposé à la pièce 10 par une partie de jonction 11-3 reliant les pattes 11-1, 11-2 entre elles. Au moins un capteur de mesure est alors positionné dans le logement 12 en vue de mesurer un paramètre physique ou chimique de la pièce 10. A titre d'exemple, sur la figure 4, deux capteurs 20 sont insérés dans le logement 12, un nombre plus élevé ou moins élevé de capteurs pouvant être envisagé. En outre, un adhésif (ex : une colle céramique) peut éventuellement, mais non nécessairement, être déposé dans l'espace restant du logement 12 afin de limiter tout mouvement du ou des capteurs 20 qui sont déjà insérés dans le logement 12. Whatever the co-densification method chosen, an integral structure of composite material having a profile corresponding to that of the assembly of the preforms 1, 2 is obtained. The structure thus obtained is formed of the part 10 provided with of at least one holding member 11. In the example illustrated in Figure 3, the holding member 11 is formed of two tabs 11-1, 11-2 spaced apart and connected by co-densification to the rest of the structure 10, the dashed lines symbolizing the junction between the lugs 11-1, 11-2 and the rest of the structure 10. The lugs 11-1, 11-2 and a surface 10-1 of the part 10 s extending between the lugs 11-1, 11-2 delimit a housing 12. This housing 12 is closed on the opposite side to the part 10 by a joining portion 11-3 connecting the legs 11-1, 11-2 between them. At least one measurement sensor is then positioned in the housing 12 in order to measure a physical or chemical parameter of the part 10. By way of example, in FIG. 4, two sensors 20 are inserted in the housing 12, a number higher or lower sensors that can be considered. In addition, an adhesive (eg a ceramic adhesive) may possibly, but not necessarily, be deposited in the remaining space of the housing 12 to limit any movement of the sensor or sensors 20 that are already inserted into the housing 12.
La figure 5 illustre une variante de réalisation d'un organe de maintien 31 solidarisé à une pièce 30 en matériau composite. L'organe de maintien 31 est réalisé à partir d'un procédé similaire à celui de l'organe de maintien 11. Cependant, à la différence de l'organe de maintien 11, l'organe de maintien 31 est, cette fois, fabriqué à partir de deux préformes élémentaires. Les deux préformes élémentaires de l'organe de maintien 31 présentent, à titre d'exemple, une forme de biseau et sont assemblées sur une surface d'une première préforme correspondant à la préforme de la pièce 30 en matériau composite à fabriquer. L'ensemble de ces préformes subit ensuite une étape de co-densification, telle que précédemment décrite, de manière à obtenir une structure d'un seul tenant formée de la pièce 30 en matériau composite munie d'au moins un organe de maintien 31.  Figure 5 illustrates an alternative embodiment of a holding member 31 secured to a part 30 of composite material. The holding member 31 is made from a method similar to that of the holding member 11. However, unlike the holding member 11, the holding member 31 is, this time, manufactured from two basic preforms. The two elementary preforms of the holding member 31 have, for example, a bevel shape and are assembled on a surface of a first preform corresponding to the preform of the piece 30 of composite material to be manufactured. The set of these preforms then undergoes a co-densification step, as previously described, so as to obtain a one-piece structure formed of the composite material part 30 provided with at least one holding member 31.
Dans l'exemple illustré sur la figure 5, l'organe de maintien 31 obtenu est formé de deux éléments de maintien 31-1, 31-2 espacés entre eux et liés par co-densification à la pièce 30. Les traits pointillés symbolisent ici la jonction entre les éléments de maintien 31-1, 31-2 et le reste de la pièce 30. Les éléments de maintien 31-1, 31-2 et une surface 30-1 de la pièce 30 s'étendant entre ces éléments délimitent un logement 32.  In the example illustrated in FIG. 5, the holding member 31 obtained is formed of two holding elements 31-1, 31-2 spaced apart and linked by co-densification to the piece 30. The dashed lines here symbolize the junction between the holding members 31-1, 31-2 and the rest of the piece 30. The holding members 31-1, 31-2 and a surface 30-1 of the piece 30 extending between these elements delimit a dwelling 32.
Au moins un capteur de mesure est ensuite inséré dans le logement At least one measuring sensor is then inserted into the housing
32. Ainsi, dans l'exemple illustré, deux capteurs 40 de mesure sont insérés dans le logement 32. Par ailleurs, afin de sécuriser le maintien des capteurs 40 présents dans le logement 32, l'espacement entre les éléments de maintien 31-1, 31-2 est réalisé de manière à diminuer au fur et à mesure que l'on s'éloigne de la pièce 30. Ainsi dans l'exemple illustré chaque élément de maintien 31-1, 31-2 est réalisé de manière à présenter une forme de biseau, les biseaux se rapprochant l'un de l'autre au fur et à mesure que l'on s'éloigne de la pièce 30. 32. Thus, in the illustrated example, two measurement sensors 40 are inserted into the housing 32. In addition, in order to secure the maintenance of the sensors 40 present in the housing 32, the spacing between the holding elements 31-1 , 31-2 is made to decrease as one moves away from the part 30. Thus in the illustrated example each holding element 31-1, 31-2 is made to present a bevel shape, the bevels approaching each other as one moves away from the piece 30.
En outre, afin de limiter les mouvements des capteurs 40 de mesure positionnés dans le logement 32, un adhésif 50, par exemple une colle céramique peut éventuellement, mais non-nécessairement, être déposé dans le logement 32 de manière à combler l'espace résiduel existant entre les deux éléments de maintien 31-1, 31-2 et la surface 30- 1.  In addition, in order to limit the movements of the measuring sensors 40 positioned in the housing 32, an adhesive 50, for example a ceramic adhesive may possibly, but not necessarily, be deposited in the housing 32 so as to fill the residual space existing between the two holding members 31-1, 31-2 and the surface 30-1.
La figure 6 montre une photographie d'une partie d'une pièce en matériau composite comprenant un élément de maintien 31-1 ou 31-2 constitutif de l'organe de maintien 31. Cette pièce a été obtenue par co- densification d'une préforme élémentaire de l'organe de maintien 31 avec une préforme de la pièce 30 composite. Comme il peut être observé, on constate une co-infiltration entre l'élément de maintien et la surface sous- jacente, permettant ainsi d'améliorer la tenue de l'organe de maintien sur la pièce composite par comparaison avec l'état de l'art existant.  FIG. 6 shows a photograph of a part of a composite material part comprising a holding element 31-1 or 31-2 constituting the holding member 31. This part was obtained by co-densification of a elementary preform of the holding member 31 with a preform of the composite part. As can be observed, there is co-infiltration between the holding member and the underlying surface, thereby improving the holding of the holding member on the composite part in comparison with the state of the body. existing art.
Deux plaques munies d'organes de maintien 11, 31 et formées d'un même matériau composite, ici en carbone renforcé par fibres de carbones (C/C), ont été fabriquées selon le procédé précédemment décrit en vue d'essais mécaniques. Une première plaque, désignée ci-dessous comme « plaque n°l » a directement été soumise à des efforts de cisaillements exercés à l'aide de moyens d'essai mécaniques. Une deuxième plaque, fabriquée de manière similaire à la plaque n°l et désignée ci-dessous comme « plaque n°2 » a été soumise à un choc thermique à 1400°C et a ensuite subi des efforts de cisaillement similaires à ceux de la plaque n°l. Les contraintes de cisaillement ont été appliquées de sorte à identifier les seuils conduisant à l'arrachement des organes de maintien 11, 31 des plaques n°l et n°2. Le tableau ci-dessous, fournit les valeurs de seuils de rupture qui ont été mesurées pour obtenir l'arrachage des organes de maintien 11, 31 des plaques n°l et n°2.  Two plates provided with holding members 11, 31 and formed of the same composite material, in this case carbon reinforced with carbon fibers (C / C), were manufactured according to the method previously described for mechanical tests. A first plate, hereinafter referred to as "Plate No. 1" was directly subjected to shear forces exerted using mechanical test means. A second plate, manufactured similarly to Plate No. 1 and referred to below as "No. 2 Plate", was subjected to thermal shock at 1400 ° C and then experienced shear forces similar to those of plate no. The shear stresses were applied so as to identify the thresholds leading to the tearing of the holding members 11, 31 of the plates No. 1 and No. 2. The table below gives the values of rupture thresholds that have been measured to obtain the tearing of the holding members 11, 31 of the plates No. 1 and No. 2.
Conditions terms
Effort de cisaillement (daN) d'essais  Shear stress (daN) of tests
Organe de Plaque n°l 43  Plate Organ No. l 43
maintien 11 Plaque n°2 44  hold 11 Plate # 2 44
Organe de Plaque n°l 59,5  Plate Organ No. l 59.5
maintien 31 Plaque n°2 50 D'une manière générale, on observe que l'application du choc thermique sur la plaque n°2 a eu un faible impact sur les seuils mesurés par comparaison avec la plaque n°l qui n'a pas subi un tel choc thermique. Les organes de maintien 11 et 31 présentent par ailleurs une résistance aux efforts de cisaillement très satisfaisante. En effet, les efforts de cisaillement nécessaires pour arracher les organes de maintien 11, 31 des plaques n°l et n°2 s'avèrent environ dix fois supérieurs à des seuils mesurés par le passé pour lesquels des organes de maintien de capteurs étaient fixés à une plaque par l'intermédiaire d'une colle céramique. On observe en outre que les organes de maintien 31 semblent présenter une résistance aux efforts de cisaillement encore meilleure que les organes de maintien 11, qui présentent déjà une résistance très importante aux efforts de cissailement. Ainsi, les résultats obtenus confirment que la fabrication d'une pièce en matériau composite munie d'au moins un organe de maintien, obtenue par co-densification d'une préforme de la pièce avec au moins une préforme d'un organe de maintien, améliore considérablement la tenue du ou des organes de maintien solidarisés à la pièce composite. keeping 31 Plate n ° 2 50 In general, it is observed that the application of the thermal shock on the plate n ° 2 had a small impact on the measured thresholds compared to the plate n ° 1 which did not undergo such a thermal shock. The holding members 11 and 31 also have a very satisfactory resistance to shearing forces. Indeed, the shear forces necessary to tear the holding members 11, 31 of the plates No. 1 and No. 2 are about ten times higher than thresholds measured in the past for which sensor holding members were fixed to a plate by means of a ceramic glue. It is further observed that the holding members 31 appear to have an even better resistance to shear forces than the holding members 11, which already have a very high resistance to shearing forces. Thus, the results obtained confirm that the manufacture of a piece of composite material provided with at least one holding member, obtained by co-densification of a preform of the workpiece with at least one preform of a holding member, considerably improves the holding of the holding member (s) secured to the composite part.
Comme illustré sur la figure 7, le procédé décrit ci-dessus peut notamment s'appliquer à un divergent 100 de tuyère. Néanmoins, ce procédé est applicable à toute autre pièce composite, par exemple un carter aéronautique. Le divergent 100 illustré ici est une pièce en matériau composite munie d'une pluralité d'organes de maintien 11, 31 dans lesquels sont insérés un ou plusieurs capteurs 20, 40 de mesure. Les capteurs 20, 40 de mesure sont à titre d'exemple des capteurs de température, par exemple des thermocouples. Cependant, tout autre type de capteur de mesure destiné à instrumenter la pièce composite peut être utilisé, par exemple un capteur de pression ou de déformation.  As illustrated in FIG. 7, the method described above can in particular be applied to a divergent nozzle 100. Nevertheless, this method is applicable to any other composite part, for example an aerospace casing. The divergent 100 illustrated here is a piece of composite material provided with a plurality of holding members 11, 31 in which are inserted one or more sensors 20, 40 measurement. The measurement sensors 20, 40 are, for example, temperature sensors, for example thermocouples. However, any other type of measuring sensor for instrumentalizing the composite part may be used, for example a pressure or deformation sensor.

Claims

REVENDICATIONS
1. Procédé de fabrication d'une pièce (10, 30, 100) en matériau composite munie d'un capteur (20, 40), le procédé comprenant au moins les étapes suivantes : A method of manufacturing a composite material part (10, 30, 100) with a sensor (20, 40), the method comprising at least the following steps:
- assemblage d'une première préforme (1) consolidée ou non consolidée de la pièce à obtenir avec une deuxième préforme (2) d'un organe de maintien (11, 31),  - Assembling a first preform (1) consolidated or unconsolidated part to be obtained with a second preform (2) of a holding member (11, 31),
- co-densification des première et deuxième préformes (1, 2) ainsi assemblées afin d'obtenir la pièce (10, 30, 100) en matériau composite munie de l'organe de maintien (11, 31), et  - Co-densification of the first and second preforms (1, 2) thus assembled to obtain the part (10, 30, 100) of composite material provided with the holding member (11, 31), and
- positionnement d'au moins un capteur (20, 40) de mesure d'un paramètre, physique ou chimique, dans un logement (12, 32) défini par l'organe de maintien (11, 31).  - Positioning at least one sensor (20, 40) for measuring a parameter, physical or chemical, in a housing (12, 32) defined by the holding member (11, 31).
2. Procédé selon la revendication 1, dans lequel l'organe de maintien (11) comprend deux parties formant pattes (11-1, 11-2) reliées à la pièce (10, 100) et situées de part et d'autre du logement (12), et une partie de jonction (11-3) fermant le logement (12) du côté opposé à la pièce (10) et reliant les pattes (11-1, 11-2). 2. Method according to claim 1, wherein the holding member (11) comprises two leg portions (11-1, 11-2) connected to the workpiece (10, 100) and located on either side of the housing (12), and a joining portion (11-3) closing the housing (12) on the opposite side to the workpiece (10) and connecting the tabs (11-1, 11-2).
3. Procédé selon la revendication 1, dans lequel l'organe de maintien (31) comprend deux éléments de maintien (31-1, 31-2) situés de part et d'autre du logement (32), l'espacement entre les deux éléments de maintien (31-1, 31-2) diminuant lorsque l'on s'éloigne de la pièce (30, 100). 3. The method of claim 1, wherein the holding member (31) comprises two holding elements (31-1, 31-2) located on either side of the housing (32), the spacing between the two holding elements (31-1, 31-2) decreasing as one moves away from the workpiece (30, 100).
4. Procédé selon l'une quelconque des revendications 1 à 3, dans lequel la co-densification est réalisée par infiltration chimique en phase vapeur. 4. Method according to any one of claims 1 to 3, wherein the co-densification is carried out by chemical vapor infiltration.
5. Procédé selon l'une quelconque des revendications 1 à 3, dans lequel la co-densification est réalisée par voie liquide. 5. Method according to any one of claims 1 to 3, wherein the co-densification is carried out by liquid.
6. Procédé selon l'une quelconque des revendications 1 à 5, dans lequel on dépose une matrice de carbure de silicium dans la porosité des première et deuxième préformes durant la co-densification. 6. Method according to any one of claims 1 to 5, wherein depositing a silicon carbide matrix in the porosity of the first and second preforms during co-densification.
7. Procédé selon l'une quelconque des revendications 1 à 6, dans lequel le capteur (20, 40) est un capteur de température. The method of any one of claims 1 to 6, wherein the sensor (20, 40) is a temperature sensor.
8. Procédé selon l'une quelconque des revendications 1 à 7, dans lequel la pièce est un divergent (100) de tuyère. 8. A method according to any one of claims 1 to 7, wherein the part is a divergent (100) nozzle.
EP18783545.9A 2017-09-07 2018-09-06 Method for manufacturing a composite material part provided with a sensor Withdrawn EP3678854A1 (en)

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FR2647534B1 (en) * 1989-05-29 1991-09-13 Europ Propulsion REACTOR CHAMBER AND METHOD FOR THE PRODUCTION THEREOF
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BRPI0909842A2 (en) * 2008-03-10 2019-07-09 Prad Research And Development Limited hose end clamping device, and method of manufacturing a hose end clamping device
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DE102012209620B4 (en) * 2012-06-08 2023-01-19 Robert Bosch Gmbh Method for manufacturing a sensor carrier, sensor carrier and sensor
DE102013007375A1 (en) * 2013-04-27 2014-03-20 Daimler Ag Landing gear part e.g. wishbone, for motor vehicle, has two shell-shaped fiber-reinforced plastic parts provided in base body, and reinforced cavity formed between fiber-reinforced plastic parts by plastic structure
CN106198640B (en) * 2016-06-27 2020-04-17 北京航空航天大学 Braided resistance sensor for composite material and processing method thereof
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Effective date: 20220401