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
  • B29C70/04—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
  • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
  • B29B11/00—Making preforms
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
  • B29B11/00—Making preforms
  • B29B11/14—Making preforms characterised by structure or composition
  • B29B11/16—Making preforms characterised by structure or composition comprising fillers or reinforcement
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
  • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
  • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
  • B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
  • B29C43/12—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies using bags surrounding the moulding material or using membranes contacting the moulding material
• • 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
  • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
  • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
• • 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
  • B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
  • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
  • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
  • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
• • 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
• • 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

• TITLE PROCESS FOR MANUFACTURING A PREFORM FOR A PART IN COMPOSITE TURBOMACHINE MATERIAL AND CORRESPONDING PART
• the present invention relates to the field of parts made of composite material from a fibrous reinforcement densified by a matrix, in particular parts of a turbomachine.
• the prior art includes documents EP-A1-0 465 169, US-A-4 720 244, US-A-4,169 749 and FR-A1-2 940 173.
• the composite material can be is made from a preform or fabric intended to form a fibrous reinforcement and which is embedded in a matrix.
• the composite material may be of the monolithic type or may include a core so as to form a composite sandwich material.
• the latter provides rigidity and lightness to the final part and has long been the only solution allowing to combine these two characteristics.
• a cellular core such as a honeycomb or of a foam between two skins or monolithic fibrous reinforcement layers (densified by a resin or not impregnated by a resin) allows on the one hand , to considerably increase the bending stiffness of the final part and on the other hand, to control the mass in parallel via the introduction of a material with low core density (for the core), where the mechanical loading is weak.
• sandwich composite materials can exhibit poor resistance to delamination due to a manufacturing problem, excessive stress or impact on the surface.
• the resistance to delamination must be important for the structural turbomachine parts such as the outlet guide vanes (known by the acronym OGV for "Outlet Guide Vane” in English) which are intended to transmit forces passing between the gas generator and the nacelle supporting the gas generator and straightening the secondary air flow in a secondary stream delimited by the housing of the generator gas and the nacelle.
• the outlet guide vanes known by the acronym OGV for "Outlet Guide Vane” in English
• the objective of the present invention is to provide a solution making it possible to improve the manufacturing process of a composite turbomachine part so as to reduce in particular porosity defects in parts made of composite material while being simple and economical.
• the method comprising a step of placing a flexible bag which contains a fluid and which is arranged between the first fibrous part and the second fibrous part before the injection step, the fluid being intended applying additional pressure to the preform during the polymerization step.
• this pocket for example a bladder, flexible, filled with fluid makes it possible to improve the injection process of the matrix so that the latter effectively impregnates all the fibers of the preform so as to considerably reduce the areas of porosity. and the rate of porosities.
• the rate of porosity obtained with this solution is less than 1%, whereas in the prior art the conventional rate of porosity is between 1% and 3%.
• the fluid provides additional pressure directly from the inside of the preform in addition to the injection pressure of the die.
• the method is advantageously improved since the risk of plugging occurring when maintaining the injection pressure of the die is avoided, or even eliminated.
• the injection system has not been structurally modified, which implies that this solution is economical, applicable to all parts and in a simple manner. Note that this process makes it possible to obtain hollow parts which can also improve the weight gain. The mass is reduced to the sole mass of the fibrous reinforcement which is necessary for the structural strength of the part.
• the method also comprises one or more of the following characteristics and / or steps, taken alone or in combination: the fluid is contained under pressure in the flexible bag.
• the additional pressure is obtained by thermal expansion of the fluid in the pocket.
• the polymerization step is followed by a step of piercing the flexible bag so as to extract the fluid.
• the drilling is carried out in an unloaded zone of the turbomachine part.
• the additional pressure in the flexible bag is controlled and controlled via a pressurizing device connected to the flexible bag.
• a duct is intended to connect the bag to the pressurizing device and is arranged in an unloaded zone of the part.
• the fluid is evacuated from the flexible bag via the conduit
• the fibrous reinforcement is obtained by a three-dimensional or two-dimensional weaving
• the fibrous reinforcement is made in one piece and the preform comprises a first fibrous part and a second fibrous part which are woven together in a first zone and a second binding zone, the preform comprising a debinding zone delimited by a first debinding line and in which the first and second parts are separated from each other, the debonding zone being arranged between the first and second unbinding zone in a longitudinal direction L.
• the pocket is sealed.
• the additional pressure in the flexible bag is controlled and controlled manually or by an electronic control system.
• the three-dimensional weave has an interlock structure.
• the weaving step is carried out flat.
• the weaving step is followed by a shaping step of the preform so as to obtain a desired geometry of the turbomachine part; the fluid is a gas or a liquid.
• the invention also relates to a turbomachine part made of composite material comprising a fibrous reinforcement densified by a matrix, the turbomachine part being produced by the method as presented above and comprising a first wall and a second wall enclosing the pocket between them. flexible which is applied to the internal surfaces of the first and second walls, the flexible pouch defining an empty internal cavity.
• the turbomachine part is a turbomachine blade comprising a blade with an intrados surface and an extrados surface opposed along a transverse axis and which are connected upstream by a leading edge and downstream by a trailing edge. , the blade comprising the empty internal cavity extending inside the blade.
• the invention also relates to a turbomachine comprising at least one part made of composite material as mentioned above.
• Figure 1 is an axial and partial sectional view of an example of a turbomachine to which the invention applies;
• Figure 2 is a cross-sectional view of a turbine engine blade according to the invention.
• FIG. 3 is a schematic view in cross section of an exemplary embodiment of a preform with a fibrous reinforcement woven in a single piece for the production of a turbomachine blade blade;
• FIG. 4 is a schematic view in axial section of an example of a preform of a turbomachine blade, after shaping of the preform;
• FIG. 5 Figure 5 is a schematic sectional view along a radial plane perpendicular to a longitudinal direction according to the invention.
• FIG. 6 is a schematic view of an injection system comprising a die injection mold and means for controlling the pressure in the mold and the hardening of the die according to the invention.
• Figure 1 shows an axial and partial sectional view of a turbomachine 1 with a longitudinal axis X which comprises various members that can be made of composite materials such as blades.
• a turbomachine 1 with a longitudinal axis X which comprises various members that can be made of composite materials such as blades.
• the invention applies to all types of parts that can be made of composite materials.
• the turbomachine 1 of FIG. 1 is a double-flow, double-body turbomachine intended to be mounted on an aircraft.
• the turbomachine 1 comprises a fan 2 which is mounted upstream of a gas generator 3 or engine following the flow of gas in the turbomachine and here along the longitudinal axis X (and even from left to right in FIG. 1).
• the gas generator comprises upstream to downstream, a low pressure compressor 4a, a high pressure compressor 4b, a combustion chamber 5, a high pressure turbine 6a and a low pressure turbine 6b.
• the fan 2 comprises a plurality of fan blades 7 which extend along a radial axis Z, around the longitudinal axis X, and the free ends of which are surrounded by a fan casing 8.
• the fan casing 8 is carried by a nacelle 9, the nacelle 9 and the fan casing 8 being centered on the longitudinal axis X.
• the fan 2 divides the air which enters the turbomachine into a primary air flow which passes through the gas generator and in particular in a primary stream 10, and in a secondary air flow which circulates around the gas generator in a secondary stream 11.
• Guide vanes (OGV) 12 which are located downstream of the fan vanes 7, extending around the longitudinal axis X and through the secondary stream 11 to straighten the secondary air flow.
• certain parts or components of a turbomachine are made of a composite material with a fibrous reinforcement embedded in a matrix.
• the process for manufacturing a part in composite material, in particular a turbomachine, in composite material comprises the following steps:
• the fibrous reinforcement is intended to provide strength to the final part, in particular a structural part such as an OGV 12 blade.
• each OGV blade 12 comprises an aerodynamic blade 13 which extends along a stacking axis which is here parallel to the radial axis Z.
• the blade 13 comprises an intrados surface 14 and an extrados surface 15 which are opposed along a transverse axis Y (perpendicular to the longitudinal axis X) and which are connected upstream by a leading edge 16 and downstream by a trailing edge 17.
• the OGV blade 12 also comprises a radially internal platform (not shown) which is connected to a radially inner end of the blade and a radially outer platform (not shown) which is connected to a radially outer end of the blade.
• the radially internal platform is secured to an inter-stream casing 18 (separating the primary stream and the secondary stream) while the radially outer platform is secured to a casing of the nacelle 9.
• the blade is hollow.
• the fibrous reinforcement of the preform is obtained by a three-dimensional (or 3D weaving) or two-dimensional (2D weaving) weaving of threads.
• three-dimensional weaving or “3D weaving” we mean a method of weaving in which warp threads are linked to weft threads in several layers.
• the weaving of the fibrous reinforcement is three-dimensional which offers better resistance to delamination.
• the 3D weaving has an interlock structure (or reinforcement).
• the interlock weave has improved impact resistance, especially compared to a 2D weave.
• the preform is woven in one piece.
• the weaving of the preform is carried out by means of a weaving installation (not shown) comprising a loom which is configured for three-dimensional and / or two-dimensional weaving.
• the fiber reinforcement comprises a plurality of warp yarns and a plurality of weft yarns which are oriented respectively in directions which are perpendicular (in the plane or even in the thickness for 3D weaving).
• the weaving is advantageously carried out flat in a general longitudinal direction.
• the threads or strands used to carry out the weaving comprise fibers of carbon, glass, ceramic, silica, silicon carbide, kevlar, polyamide, alumina or a mixture of these fibers.
• the preform 20 comprises several fibrous parts which include bonding zones and unbinding zones which are produced during weaving.
• the parts of the preform each comprise several layers of threads or fibrous layers woven together.
• the term “unbinding” is understood to mean zones formed voluntarily by layers of threads which are not linked or woven together locally. The unbindings make it possible in particular to be able to unfold or separate the layers or fibrous parts with respect to other adjacent layers or fibrous parts at the level of the unbinding zones.
• the fibrous reinforcement of the preform woven in one piece has a general parallelepipedal shape (rectangular parallelepiped ).
• longitudinal direction L, radial direction R and transverse direction T we use the expressions longitudinal direction L, radial direction R and transverse direction T to define the dimensions thereof. These directions are perpendicular to each other.
• the preform 20 comprises at least a first fibrous part 21 intended to form an intrados wall (carrying the intrados surface 14) of the OGV vane and a second fibrous part 22 intended to form an extrados wall (carrying the extrados surface 15) of the dawn OGV.
• first part 21 and second part 22 extend in the longitudinal direction L and are superimposed in the transverse direction T.
• the first and second parts 21, 22 are woven so as to form at least two connecting zones (called the first zone of bond 23 and second bonding zone 24) and at least one unbinding zone 25.
• the first fibrous part 21 and the second fibrous part 2 are woven together or bonded together on the first zone 23 which is intended to form the edge of attack 16 and on the second zone 24 which is intended to form the trailing edge 17.
• the first fibrous part 21 and the second fibrous part 22 are untied in the unbinding zone 25 of the preform which is located between the first and second zones of connection in the longitudinal direction L. The unbindings make it possible to separate the first fibrous part from the second part.
• the unbinding zone is delimited axially by a first unbinding line 26 and a second unbinding line 27.
• the unbinding lines extend in the radial direction over the entire height of the preform. Lines 26, 27 are defined in the same plane.
• Fibrous parts described below, are also provided to form the radially inner and outer platforms of the blade. These fibrous parts are woven with the first and second parts 21, 22 and are formed by debondings. The weaving step can be followed by a step of cutting the edges of the fibrous reinforcement so that the contour of the preform is as close as desired to that of the final part, here the blade of the blade.
• the method may further comprise wetting in which the fibrous reinforcement of the preform is moistened, for example with water, so that it is easier to handle and in particular to change the orientation of the yarns of the preform. warp relative to the weft yarn (de-framing), then shaping of the preform in which an operator moves the yarns so as to shape the fibrous reinforcement to the profile of the desired blade.
• the shaping step is performed simultaneously with the wetting step.
• the preform is then dried so that the water used for wetting is extracted from it.
• the preform stiffens after drying and maintains the shaping performed by the operator. This step can be carried out by heating the fibrous reinforcement in a suitable chamber.
• the preform shaping step (before the matrix injection explained below) takes place in the injection mold.
• the method then comprises a step of placing a flexible, leaktight bag 30 (such as a bladder) in the preform 20.
• a flexible, leaktight bag 30 such as a bladder
• the flexible pocket 30 is arranged between the first fibrous part 21 and the second fibrous part 22.
• the preform also comprises an insertion unbinding zone through which the pocket 30 is inserted between the first and second fibrous parts 21, 22.
• the flexible pocket has an elongated shape whose the length is identical or substantially identical to the height of the preform (in the radial direction).
• the pocket 30 is made of a material which is compatible with the injected matrix.
• the material of the pouch comprises, for example, a silicone elastomer.
• this silicone elastomer is of the RTV type (that is to say that the latter is obtained from a composition which crosslinks at room temperature).
• the flexible bag 30 contains a fluid which may be a gas or a liquid.
• a fluid which may be a gas or a liquid.
• An example of a gas would be air, nitrogen or helium.
• the liquid comprises an oil or a glycol for example. Water can also be used if the polymerization temperature of the matrix used is less than 100 ° C., for example.
• the fluid is injected under pressure into the flexible bag.
• the bag is connected to a pressurizing device 31.
• the pressure of the fluid inside the flexible bag can be adjusted and / or controlled inside the latter by this pressurizing device 31 which is connected to the flexible bag.
• the pressurizing device is configured so as to be controlled by an operator (either manually) or by an electronic control system 50.
• the preform 20 comprises an orifice 32 passing through a third fibrous part 28 and a fourth fibrous part 29 which are intended to form the radially internal or external platform of the blade.
• the orifices 32, 32 ' are located at the level of the unbindings intended to form the third and fourth fibrous parts 28, 29 and at the level of the insertion unbinding zone of the pocket 30.
• a 32 ”through-hole is formed in one of the first and second fibrous portions.
• a filling material 33 can be used to fill (or close) the through holes 32, 32 'after having slipped the pocket inside the preform 20.
• the filling material also makes it possible to improve the stiffness of the part by. compression.
• the filling material 33 is installed in the mold before injection and after shaping of the dry preform.
• a conduit (35) is provided so as to connect the flexible bag to the pressurizing device 31. More precisely still a passage for connecting the conduit 35 of the device. pressurizing 31 to the flexible bag is optionally arranged at the level of the filling material. At least one of the through holes 32, 32 ’can be connected to the conduit itself connected to the pressurizing device 31.
• the pressurizing device 31 here comprises a pump.
• the preform 20 with the flexible bag 30 is installed beforehand in the injection chamber 41 into which the die will be injected in order to achieve densification therein and obtain the final part (the OGV vane ).
• the pocket could be placed in the preform 20 and in the injection mold 42 once the preform alone is installed in the mold.
• the matrix is injected by the liquid route and according to RTM technology.
• the injection chamber 41 is formed by an injection mold 42 of an injection system 40 shown schematically in FIG. 6.
• the injection mold 42 comprises a first part 43 with a first cavity. 45 to accommodate the preform and to give part of the shape of the desired part.
• the injection mold 42 is closed beforehand by a second part 44 forming a counter-mold and which comprises a second cavity 46 forming the other part of the shape of the desired final part.
• the first and second indentations form the injection enclosure 41 which is sealed for injection.
• the matrix is chosen according to the desired application, here for the OGV dawn.
• the matrix allowing densification of the fibrous reinforcement can be a polymeric matrix such as an epoxy-based thermosetting resin or a phenolic resin such as polybismaleimides (BMI).
• the polymeric matrix can also be a thermoplastic resin.
• the terms “resin” and “matrix” are equivalent.
• the injection mold is connected to an injection device 47 by means of a network of pipes 48. The latter as well as the injection mold 42 are placed under vacuum by suitable means and the die is injected into the enclosure d. 'injection.
• the matrix is injected at a temperature where it has the lowest viscosity (between 100 ° and 200 ° C for example) and advantageously below its polymerization temperature.
• the injection temperature is for example between 100 ° and 160 ° C.
• the injection temperature is for example between 160 ° and 200 ° C.
• the matrix which flows into the enclosure permeates all the fibers of the preform.
• pressure is applied inside the injection chamber. This pressure is between 1 bar and 20 bars.
• the pressure is advantageously applied by the injection device 47.
• the pressure in the pocket 30 is greater than that inside the enclosure.
• the resin is heated here, which makes it possible to harden the resin and obtain a rigid final part.
• the pressure applied during the injection of the resin is maintained during the polymerization so as to reduce the rate of porosities in the final part.
• the fluid which is inside the flexible pouch 30 expands which creates additional pressure on the internal surfaces 34 of the preform 20 which will have the effect of further reducing the losses. porosity rate. It is during the rise in temperature after injection and to reach the polymerization stage, that the fluid confined in the bag expands.
• the pouch 30 being flexible and the resistance opposed by the fibers of the preform, the expansion of the fluid results in an increase in pressure depending on the temperature applied during the polymerization.
• the additional pressure by thermal expansion is uniformly distributed over the entire surface of the preform 20 which improves the process.
• the internal pressure in the pocket 30 can be controlled during the polymerization step by controlling it with the pressurizing device 31. In this case, this pressure control is carried out only in the preliminary phases of the polymerization (before the matrix does not change from liquid to gelled state).
• an outer membrane is placed over the preform contained in the mold and to close the injection mold.
• the role of the outer membrane is to apply pressure on the die to improve injection into the mold and into the preform, and also to ensure that the pressure is sufficient and necessary to reduce the areas and rates of porosity. .
• the flexible bag is pierced so as to extract the fluid it contains.
• a hole is made in an advantageously unloaded area of the part, for example at the level of one of the radially internal and external platforms.
• unloaded we mean an area that is less mechanically stressed.
• the drilling is performed through a platform of the blade or the center of the blade (at one of the internal and external surfaces).
• the pressure in the pocket is obtained by a fluid maintained under pressure with the pressurizing device 31, no drilling of the pocket is necessary.
• the conduit 35 allowing the pressurization must be placed in the unloaded area of the part.
• the fluid is then evacuated from the flexible bag via this conduit 35.
• machining of the final rigid part obtained is carried out at the end of the process.
• the final part here an OGV blade whose cross section is shown, is a single piece (made in one piece) and which comprises a three-dimensional fiber reinforcement densified by a matrix and an internal cavity 19 vacuum defined by the flexible pouch that has been emptied.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Composite Materials (AREA)
• Casting Or Compression Moulding Of Plastics Or The Like (AREA)
• Moulding By Coating Moulds (AREA)
• General Engineering & Computer Science (AREA)
• Reinforced Plastic Materials (AREA)

Applications Claiming Priority (2)

Publications (1)

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Family Applications (1)

Country Status (5)

Family Cites Families (4)

• 2020
  • 2020-04-10 FR FR2003630A patent/FR3109115B1/fr active Active
• 2021
  • 2021-04-09 EP EP21726149.4A patent/EP4132775A1/fr active Pending
  • 2021-04-09 US US17/995,426 patent/US20230166460A1/en active Pending
  • 2021-04-09 CN CN202180026616.4A patent/CN115379946A/zh active Pending
  • 2021-04-09 WO PCT/FR2021/050635 patent/WO2021205132A1/fr unknown

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