Classifications

• • 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
  • F01D9/00—Stators
  • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
• • 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
  • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
  • B29C45/0005—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor using fibre reinforcements
• • 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
  • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
  • B29C45/14—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor incorporating preformed parts or layers, e.g. injection moulding around inserts or for coating articles
• • 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
  • B29C45/00—Injection moulding, i.e. forcing the required volume of moulding material through a nozzle into a closed mould; Apparatus therefor
  • B29C45/17—Component parts, details or accessories; Auxiliary operations
  • B29C45/40—Removing or ejecting moulded articles
• • 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
  • B29C70/28—Shaping operations therefor
  • B29C70/40—Shaping or impregnating by compression not applied
  • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
  • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
• • 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
  • B29C70/78—Moulding material on one side only of the preformed part
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
  • B29D99/00—Subject matter not provided for in other groups of this subclass
  • B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
• • 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
• • 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
  • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
• • 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
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
• • 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
  • F05D2230/20—Manufacture essentially without removing material
• • 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
• • 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 stator vanes for a gas turbine engine.
• Examples of application of the invention are in particular the exit guide vanes (called OGVs for “Outlet Guide Vane”), the inlet guide vanes (called IGVs for “Inlet Guide Vane”), and the variable-pitch vanes. (called VSV for “Variable Stator Vane”) of an aerospace turbomachine.
• OGVs exit guide vanes
• IGVs inlet guide vanes
• VSV variable-pitch vanes
• stator vanes of an aeronautical gas turbine engine each have two platforms (inner and outer) which are attached to the vane. These stator vanes form rows of stationary vanes which guide the flow of gas passing through the motor at an appropriate speed and angle.
• stator vanes are generally metallic, but it has become common practice to make them out of composite material in particular to reduce their mass. However, the manufacturing processes of the stator vanes of metal material or composite material have certain disadvantages.
• stator vanes are typically obtained from foundry, which requires two different imprints, namely a permanent core which is expensive and time consuming to manufacture and requires a treatment against wear, and a sand core with binder which must be redone very frequently.
• this type of stator blade requires a finishing phase by machining or chemical treatment to finalize the workpiece.
• the rectifier vanes made of composite material they are most often produced by different manufacturing processes, such as, for example, the manual laminate / draping process, the injection molding process of a fibrous preform (RTM for "Resin”). Transfer Molding "), the liquid resin infusion process, the embroidery process, the thermo-compression process, etc.
• Laminate / draping processes are expensive and are not, however, suitable for the manufacture of stator vanes that have small sizes or complex form factors.
• the resin injection processes cause defects in the preform of the fibrous preform during its shaping or during its consolidation and present risks of inter-laminar delamination.
• some of these manufacturing processes require the reporting of the platforms on the vane, which induces additional manufacturing costs.
• stator vane made of composite material requires a metal foil on their leading edge to protect it against erosion, abrasion and the impact of foreign bodies.
• shaping and assembly of the metal foil on the leading edge of the blade is an additional operation that is long and expensive.
• a blade for a gas turbine engine comprising a blade of composite material having a fiber reinforcement densified by a matrix, the fibrous reinforcement being obtained from pre-impregnated long fibers and agglomerated in mat form, the blade being provided on at least one leading edge of a reinforcing strip, and at least one platform positioned at a radial end of the blade, the platform being made of composite material having a reinforcement matrix densified fibrous material, the fibrous reinforcement being obtained from long staple prepreg fibers.
• the straightener blade according to the invention is remarkable in that it has a hybrid architecture composed of a mat vane formed by an agglomerate of long fibers pre-impregnated on the leading edge of which is assembled a reinforcing strip .
• the term "mat” here means a set of filaments, staple fibers or base yarns, cut or not, and held together in the form of a tablecloth, carpet or billet.
• the mat in long fibers for example discontinuous, makes it possible to give an overall stiffness to the straightener blade and the reinforcing strip accentuates the local stiffness in order to limit the bending of the straightener blade and to avoid unacceptable vibratory modes while limiting its deformation.
• the long fiber mat structure also makes it possible to impart an isotropic structure and homogeneous mechanical properties in the plane of the blade.
• the reinforcing strip may be positioned at the leading edge of the blade and cover at least partially one of the side faces of the blade.
• This reinforcement strip makes it possible to produce a leading edge of composite material for blading, which is intended to protect it from problems of abrasion, erosion and the impact of foreign bodies.
• the reinforcing strip also makes it possible to further accentuate the stiffness of the blade, and in particular in its thickness.
• the lateral face of the vane not covered by the reinforcing strip is advantageously covered in part by another unidirectional fabric strip so as to limit stiffness and shrinkage asymmetries during the manufacture of the blade.
• the reinforcing strip may be positioned at the leading edge of the blade and cover at least partially the two side faces of the blade. In this configuration, the reinforcing strip thus greatly increases the stiffness of the blade.
• stator vane With the same architecture of the stator vane, it is possible, simply by modifying the width of the reinforcing strip, to make rectifier vanes of different categories, namely a stator vane with a purely aerodynamic solicitation, a vane. of non-structural straightener and a semi-structural straightener blade, while providing protection from the leading edge of its blade.
• the reinforcing strip is positioned on the vane and on at least one connection fillet between the vane and the platform.
• the straightener vane may further comprise a layer of viscoelastic material interposed between the vane and the reinforcing strip or positioned within the reinforcing strip.
• a viscoelastic layer or patch
• the reinforcing strip is made from the same unidirectional fabric or textile strip, or by a stack of several plies pre-impregnated with unidirectional fabric or carbon fiber textile (of type qualified as follows: M for Standard , IM for intermediate module, HR for high resistance, HM for high module) or fiberglass.
• M Standard
• IM intermediate module
• HR high resistance
• HM high module
• fiberglass fiberglass
• the width of this reinforcing strip and the type of carbon used will be a function of the forces experienced by the straightener blade.
• a pre-impregnated fabric can thus be used with a weave pattern and / or a sequence of predefined pleats depending on the stiffness required for blading.
• the preferred orientation may vary to facilitate its implementation on the blade.
• said fabric or textile reinforcement having these glass fibers may slightly increase the stiffness but also serve as protection against abrasion and / or erosion and thus protect the dawn .
• the constituent mats of the fibrous reinforcements of the vane and the platform are made from strips of carbon fiber.
• the size of these strips (length and width) and the type of carbon used will depend on the solicitations of the vane.
• the invention also relates to a turbomachine comprising at least one stator blade as defined above.
• the subject of the invention is also a process for manufacturing a stator blade as defined above, comprising successively: the positioning of the reinforcing strip and fibers long pre-impregnated and agglomerated mats in cavities of a compression tool for the realization of the fibrous reinforcements constituting the vane and the platform, the closure of the compression tooling, the compression of the mats and the band reinforcement by regulating the temperature and the closing pressure of the compression tooling to obtain a transformation of the composite used, the opening of the compression tooling, and the demolding of the stator blade obtained.
• the method of manufacturing a stator vane as defined above comprises successively: the positioning of the reinforcing strip and long fibers pre-impregnated and agglomerated in mats in cavities of a compression tool for the realization of the fibrous reinforcement constituting the blading, the closure of the compression tooling, the compression of the mats and the reinforcing strip by regulating the temperature and the closing pressure of the compression tooling to obtain a transformation of the composite used, the opening of the compression tooling, the demolding of the blade obtained, and the overmolding of a platform previously made on the blade by a resin injection process under pressure.
• the method of manufacturing a stator blade as defined above comprises successively: the positioning of the reinforcement strip and long fibers pre-impregnated and agglomerated in mats in cavities of a compression tool for the realization of the fibrous reinforcement constituting the blading, the closure of the compression tooling, the compression of the mats and the reinforcement strip by regulating the temperature and the closing pressure of the compression tooling to obtain a transformation of the composite used, the opening of the compression tooling, the demolding of the blade obtained, and gluing on the blading of a previously made platform.
• FIG. 1 is a perspective view of a stator blade according to the invention
• FIGS. 2A and 2B are views of the stator blade of Figure 1, respectively in cross-section and in longitudinal section;
• FIG. 3 to 6 are cross-sectional views of the stator vanes according to alternative embodiments of the invention.
• the invention applies to the realization of stator vanes for a gas turbine engine having a leading edge.
• stator vanes are in particular the exit guide vanes (OGV), the inlet guide vanes (IGV), and the variable-pitch vanes (VSV), etc.
• FIG. 1 schematically and in perspective shows an example of such a stator vane 2.
• the stator vane 2 comprises a vane 4 having a lower face 4a and an extrados face 4b, an inner platform 6 assembled on an inner radial end of the vane, and an outer platform 8 assembled on the outside. outer radial end of the vane.
• the blading 4 is made of composite material with a fiber reinforcement densified by a matrix, the fibrous reinforcement being obtained from pre-impregnated long fibers, for example discontinuous, and agglomerated in the form of "mat" (that is to say in the form of a sheet, a carpet or a slug made from the agglomeration of these fibers).
• matrix that is to say in the form of a sheet, a carpet or a slug made from the agglomeration of these fibers.
• the inner 6 and outer 8 platforms are made of composite material with a fiber reinforcement also obtained from long prepreg fibers, for example discontinuous, and agglomerated in the form of mat.
• the leading edge of the blade 4 is formed by a reinforcing strip 10-1 unidirectional fabric (UD) or pre-impregnated textile , this reinforcing strip being positioned on the blade at the edge and at least on the connecting fillet 12 between the vane and the inner 6 and outer 8 platforms.
• the reinforcing strip may not cover these connection fillet.
• the reinforcing strip 10-1 extends only over the connection fillets 12 between the vane and the inner and outer platforms 6 and 8.
• the reinforcing strip 10-2 can extend both on these connection fillets, but also on the platforms 6, 8.
• the reinforcing strip may be directly embedded in the thickness of the platforms 6, 8. This solution avoids delamination between the reinforcing strip and the constituent mat platforms during holes and countersinks of the latter for their attachment to the housing.
• the reinforcing strip 10-1 may have a so-called “simple” positioning in which it is positioned only on the leading edge of the blade 4.
• the reinforcing strip 10-3 has an asymmetrical positioning in which it covers not only the leading edge of the blade, but also partly one of the side faces of the blade (ie here the intrados face 4a). This configuration increases the stiffness of the blade, which improves its resistance to stress and its protection against erosion.
• the reinforcing strip 10-4 has a symmetrical positioning in which it covers not only the leading edge of the blade 4, but also partly the two side faces of the blade (ie the intrados faces 4a and extrados 4b). Compared with the present variant, this configuration makes it possible to further increase the stiffness of the blade and to avoid post-manufacturing deformations.
• the shape of the reinforcing strip is not necessarily rectangular: for example it may be in the form of wave so as to respond to the problems of deformation along the trailing edge at the same frequency.
• the reinforcing strip 10-5 has an asymmetrical positioning in which it covers the leading edge and in part the extrados face 4b of the blading 4.
• the lateral face vane which is not covered by the reinforcing strip namely the intrados face 4a
• another strip 14 also unidirectional fabric or pre-impregnated textile.
• this additional strip 14 makes it possible to limit the asymmetries of stiffness and shrinkage / deformation during the manufacture of the blade.
• the width of this band 14 will be a function of the amount of deformation experienced during the manufacture of the blade.
• the stator vane 2 further comprises a layer of viscoelastic material 16 which is interposed between the vane 4 and the reinforcing strip 10-6.
• This layer (or patch) 16 is in the example shown in Figure 6 positioned at the intrados face 4a of the blade and covered by the reinforcing strip 10-6, the latter may have a symmetrical positioning in which it partially covers the intrados and extrados faces of the vane.
• this layer of viscoelastic material 16 thus makes it possible to respond to vibratory, acoustic or damping problems encountered by the straightener blade. Indeed, this layer allows the absorption of energy, of frequencies and attenuates the vibratory modes in order to thus limit the vibrations and the deformations that the stator vane undergoes in operation.
• the layer of viscoelastic material 16 may be interposed between the blading and the reinforcing strip. Alternatively, it can be positioned within the reinforcing strip, that is to say, be added between two successive folds constituting the reinforcing strip.
• the viscoelastic material used will be of the elastomer, rubber, etc. type.
• a first manufacturing process is called "thermocompression”. It allows to realize a stator blade according to the invention which is monobloc.
• thermo-compression requires a compression tooling consisting of a carcass in which are reported the cavities (or cavities) of the stator blade to be manufactured and optionally provided with an ejection system for extracting the part manufactured. These impressions are thermally regulated to bring the injected resin to its melting temperature and thus "transform" the mat.
• a first step of this process consists in carrying out the fibrous reinforcement intended for performing the blading and the platforms of the stator blade.
• pre-impregnated strips are cut in a unidirectional fabric or textile web, typically made of carbon fibers, the dimensions (length and width) and the type of carbon used for these strips being depending on the level of stiffness desired in the stator vane.
• the strips may have a width of between 4 and 15 mm and a length of between 4 and 150 mm, or even 2 mm in width and / or length.
• the long fibers may be continuous or discontinuous before transformation depending on the chosen injection method.
• the staple fibers will have a length of substantially between 2 mm and 100 mm depending on the size of the granule comprising the resin.
• These fibers are often discontinuous or may be continuous depending on the topology of the part, the fiber volume ratio present in the resin, the process used, transformation process parameters, rheological phenomena and / or interaction between fibers. . These fibers will retain their initial lengths or will be broken during the dynamic phase corresponding to filling to present a final fiber length distribution substantially between 0.1 mm and 100 mm.
• These strips of carbon fibers are then agglomerated in carpet or piece to form a mat.
• This solution makes it easy to handle these strips before positioning in the compression tooling.
• a simple cluster of strips can also be created (then positioned, "injected” and inserted into the compression tooling).
• the superimposition and positioning of the strips within the mat is random but with a repetitive pattern if possible to allow a reproducibility of the stator blade.
• the mat will have an isotropic structure to allow to obtain homogeneous mechanical properties in the plane.
• the shape of the mat it depends on the complexity of the stator blade to manufacture (size, thickness, shape evolution, etc.).
• the fibrous reinforcement for the realization of the platforms of the stator blade can be made with the same mat as that for performing the blading.
• the mat may be pre-polymerized, typically up to 20-50%, prior to its positioning in the cavities of the compression tooling, this pre-polymerization thus making it possible to preserve resin for the cohesion between the strips and the reinforcing tape.
• this pre-polymerization thus making it possible to preserve resin for the cohesion between the strips and the reinforcing tape.
• the mat may be pre-polymerized to 30%.
• the method of manufacturing by thermo-compression consists in creating the reinforcing strip.
• UD fabric or textile typically carbon fiber
• the reinforcing strip may be made by stacking several plies pre-impregnated with UD fabric or textile, also made of carbon fibers.
• the reinforcing strip and the mat for producing the fibrous reinforcements constituting the vane and the platforms thus produced are positioned in the cavities of the compression tooling.
• the mat for the realization of the fibrous reinforcement of the vane will be positioned at first in a cavity of the compression tooling with the reinforcing strip, then the mat for the realization of the platforms will be positioned in a second time.
• they can be positioned at the same time in the same compression tooling.
• they can be positioned at the same time in the same compression tool to undergo pre-consolidation prior to their positioning in the final compression tooling.
• the resin used for the pre-impregnated strips may be a thermosetting resin belonging to the family of epoxides, bismaleimides, polyimides, polyesters, vinlyesters, cyanate esters, phenolics, etc.
• the resin may be a thermoplastic resin of the phenylene polysulfide (PPS), polysulfone (PS), polyethersulfone (PES), polyamide-imide (PAI), polyetherimide (PEI) or polyaryletherketone (PAEK) family : PEK, PEKK, PEEK, PEKKEK, etc.
• the closure of the compression tooling causes a compression of the mats and the reinforcement band placed inside it, which allows the mats to get into shape in the cavities of the compression tooling.
• This compression step may be carried out either by the closure of the compression tool or by the displacement of moving cores present inside the compression tooling.
• a resin conversion and polymerization i.e., baking for a thermosetting resin and cooling for a thermoplastic resin.
• thermosetting resin it is advantageous to use a first specific heating cycle close to the melting temperature of the resin with controlled temperature ramps for shaping the mats, followed by a second heating cycle also controlled for the consolidation / crosslinking / polymerization of the resin. This allows for the shaping and the cohesive / adhesive aspect of the mats and the reinforcing strip.
• this second cycle will consist of a cooling cycle in order to reach the ejection temperature of the part and thus well crystallize / polymerize the semi-crystalline or amorphous polymers in order to obtain optimal mechanical properties and to limit residual stresses and post-injection deformations.
• the thermal regulation of the compression tooling can be carried out by any known means of regulation, for example by the use of heating cartridges, by regulation under water or oil, by an induction heating system, etc.
• the compression tooling is then opened and the rectifier blade thus obtained is extracted (by means of an ejection system or manually or automatically by a gripper).
• a second method of manufacturing the stator blade applies the previously described thermo-compression method for obtaining the vane of the stator vane (without the platforms), followed by a step of overmolding the platforms previously performed on the grinding by a process of injection of resin under pressure.
• the method of manufacturing the trimming by thermo-compression is thus strictly identical to that described above.
• the bladed composite material thus produced is then placed in an injection mold to perform an overmoulding of the weft for producing the platforms using a thermoplastic or thermosetting resin (possibly filled).
• this overmolding method provides for a dynamic phase of filling the cavity of the injection mold by injection of resin under pressure, followed by a switching phase, then a static phase of compaction / maintenance and a phase solidification or crosslinking / baking of the injected resin. After solidification of the resin, the injection mold is opened and the part (blading with its overmolded platforms) is ejected.
• a third method of manufacturing the stator blade applies the previously described thermo-compression method for obtaining the vane of the stator vane with possibly the platforms, a known injection process for the manufacture of the platforms. (if necessary), then a gluing step on the blading of the platforms. This bonding step may be performed by known methods such as ultrasonic bonding, glue removal, etc.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• General Engineering & Computer Science (AREA)
• Materials Engineering (AREA)
• Manufacturing & Machinery (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Moulding By Coating Moulds (AREA)
• Casting Or Compression Moulding Of Plastics Or The Like (AREA)

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• 2014
  • 2014-08-27 FR FR1458020A patent/FR3025248B1/fr active Active
• 2015
  • 2015-08-20 CA CA2957834A patent/CA2957834C/fr active Active
  • 2015-08-20 US US15/506,343 patent/US20170254212A1/en not_active Abandoned
  • 2015-08-20 EP EP15763962.6A patent/EP3194151A1/de not_active Withdrawn
  • 2015-08-20 BR BR112017003641-0A patent/BR112017003641B1/pt active IP Right Grant
  • 2015-08-20 RU RU2017109815A patent/RU2703225C2/ru active
  • 2015-08-20 CN CN201580045790.8A patent/CN106794641A/zh active Pending
  • 2015-08-20 WO PCT/FR2015/052237 patent/WO2016030613A1/fr active Application Filing
  • 2015-08-20 JP JP2017511286A patent/JP2017528641A/ja active Pending

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