WO2022229547A1 - Dispositif de moulage d'une piece aubagee de turbomachine - Google Patents
Dispositif de moulage d'une piece aubagee de turbomachine Download PDFInfo
- Publication number
- WO2022229547A1 WO2022229547A1 PCT/FR2022/050765 FR2022050765W WO2022229547A1 WO 2022229547 A1 WO2022229547 A1 WO 2022229547A1 FR 2022050765 W FR2022050765 W FR 2022050765W WO 2022229547 A1 WO2022229547 A1 WO 2022229547A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- mold
- bell
- shell
- base
- molding device
- Prior art date
Links
- 238000000465 moulding Methods 0.000 title claims abstract description 57
- 230000000295 complement effect Effects 0.000 claims abstract description 21
- 238000007789 sealing Methods 0.000 claims abstract description 18
- 230000000694 effects Effects 0.000 claims abstract description 6
- 239000011347 resin Substances 0.000 claims description 39
- 229920005989 resin Polymers 0.000 claims description 39
- 239000007924 injection Substances 0.000 claims description 18
- 238000002347 injection Methods 0.000 claims description 17
- 239000002184 metal Substances 0.000 claims description 17
- 229910052751 metal Inorganic materials 0.000 claims description 17
- 238000000034 method Methods 0.000 claims description 12
- 239000000835 fiber Substances 0.000 claims description 10
- 230000002093 peripheral effect Effects 0.000 claims description 9
- XQCFHQBGMWUEMY-ZPUQHVIOSA-N Nitrovin Chemical compound C=1C=C([N+]([O-])=O)OC=1\C=C\C(=NNC(=N)N)\C=C\C1=CC=C([N+]([O-])=O)O1 XQCFHQBGMWUEMY-ZPUQHVIOSA-N 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 2
- 238000003825 pressing Methods 0.000 claims description 2
- 239000002131 composite material Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000006116 polymerization reaction Methods 0.000 description 5
- 238000013037 co-molding Methods 0.000 description 4
- 238000007493 shaping process Methods 0.000 description 4
- 239000002699 waste material Substances 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000009745 resin transfer moulding Methods 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- 241000272165 Charadriidae Species 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010494 dissociation reaction Methods 0.000 description 1
- 230000005593 dissociations Effects 0.000 description 1
- 229920001971 elastomer Polymers 0.000 description 1
- 239000000806 elastomer Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000005470 impregnation Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 238000001721 transfer moulding Methods 0.000 description 1
- 238000009736 wetting Methods 0.000 description 1
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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/12—Moulds or cores; Details thereof or accessories therefor with incorporated means for positioning inserts, e.g. labels
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
- B29C33/306—Exchangeable mould parts, e.g. cassette moulds, mould inserts
-
- 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
- B29C61/00—Shaping by liberation of internal stresses; Making preforms having internal stresses; Apparatus therefor
- B29C61/06—Making preforms having internal stresses, e.g. plastic memory
- B29C61/0608—Making preforms having internal stresses, e.g. plastic memory characterised by the configuration or structure of the preforms
- B29C61/0658—Making preforms having internal stresses, e.g. plastic memory characterised by the configuration or structure of the preforms consisting of fibrous plastics material, e.g. woven
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/541—Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/68—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
- B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
-
- 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
-
- 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
- B29C43/32—Component parts, details or accessories; Auxiliary operations
- B29C2043/3205—Particular pressure exerting means for making definite articles
- B29C2043/3261—Particular pressure exerting means for making definite articles thermal expansion
-
- 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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/0038—Moulds or cores; Details thereof or accessories therefor with sealing means or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
-
- 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
- B29C70/48—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 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
- 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
Definitions
- TITLE MOLDING DEVICE FOR A BLADED PART OF
- the present invention relates to a device for molding a bladed part of a turbomachine, as well as a method using this device.
- composite materials are advantageous in the aeronautical industry in particular because these materials have advantageous mechanical performance for relatively low masses.
- a process for manufacturing a composite part for the aeronautical industry which is well known to those skilled in the art, is the RTM molding process, the initials of which refer to the Anglo-Saxon acronym for Resin Transfer Molding.
- This is a process for producing a part in composite material based on fibers impregnated with resin.
- Such a method is for example used to manufacture a bladed part of a turbomachine such as a fan blade or a stator blade.
- An RTM process comprises several successive steps.
- this mold has two functions or two successive uses.
- the mold is first used to achieve a shaping of the preform by hot compression, it is thus placed in a press and in an oven in order to compress the preform and stiffen it.
- the mold is then used to inject resin into the preform for its impregnation.
- the resin is injected through a supply port of the mold which is then placed in an oven to cause the polymerization of the resin and its hardening.
- the bladed part is then removed from the mold and can undergo various successive operations, in particular finishing.
- This mold is also not suitable for performing other functions such as the co-injection of a metal shield on a leading edge of the bladed part.
- the composite material of the bladed part is relatively fragile, and in particular sensitive to shocks, and it is known to protect it by means of a metal shield which is attached and fixed to the leading edge of the bladed part.
- the shield can be attached to the blade in several ways.
- a first way consists in bonding the first shield on the bladed part, after polymerization of the resin.
- a second way of fixing a shield on a bladed part consists in fixing the shield by co-molding with the fiber preform.
- the preform is placed in the mold and the shield is positioned on the edge of the preform intended to form the leading edge of the blade.
- the injected resin impregnates the preform and comes into contact with the shield to ensure its attachment to the blade after polymerization and hardening.
- the aforementioned mold of the current technique is not suitable for co-injection and co-molding of the shield.
- this mold comprises a large number of parts which are movable relative to each other to achieve the shaping by compression. This assembly of the parts creates resin leaks during injection, which leads to waste of resin and requires a complete cleaning of the mold after use.
- the present invention proposes a solution to these problems which consists in proposing a molding device specifically adapted to the implementation of only one of the aforementioned functions, namely here the injection of resin into the preform, and which is capable of carrying out concomitantly the attachment of a metal shield to this preform.
- the invention relates to a device for molding at least one bladed part of a turbomachine, this device comprising at least one internal cavity configured to receive a fiber preform, one edge of which is covered with a metal shield and this device being configured to allow the injection of a resin into the cavity to impregnate said preform and secure the shield to said edge, characterized in that it comprises:
- the wetting device is specifically designed and optimized to carry out the injection of resin into the preform but also the co ⁇ injection of the edge of the preform which is covered by the metal shield, that is to say the fixing of this shield on the preform.
- the different parts of the mold facilitate assembly of the mold around the preform as well as disassembly of the mold after injection and hardening of the resin.
- the bell covers the mold and is configured to hold the parts of the mold tight together in order to limit, or even prevent, resin leaks between these parts.
- the base is tightly connected to the mold and to the bell, which prevents resin leakage between these parts, limits the waste of resin, and makes it possible to maintain the pressure at the time of injection, which is important to obtain good quality of the finished part (porosity).
- the invention thus makes it possible to optimize the method of molding a bladed part by injecting resin into a preform equipped with a metal shield, in particular by reducing the waste of resin and therefore the manufacturing cost of the bladed part.
- the molding device according to the invention may comprise one or more of the following characteristics, taken separately from each other, or in combination with each other:
- the base has a generally parallelepipedic shape and comprises a flat lower surface and an upper surface comprising a central recess for mounting and interlocking a lower end of said mold; the base is for example configured to be extended horizontally in use;
- the base comprises around said recess a first peripheral groove for housing said first sealing means and a second peripheral groove for housing said second sealing means;
- the mold has the general shape of a truncated pyramid and comprises four inclined outer side surfaces connected to the four corners of a flat outer upper surface;
- the bell comprises an internal space for housing the mould, this space comprising four interior lateral surfaces which are inclined in a complementary manner to the exterior surfaces of the mould, and which are also connected to the four corners of a flat interior bottom surface of the bell , the side surfaces and the bottom surface of the space of the bell being intended to rest respectively on the side surfaces and the upper surface of the mould; the sliding of the surfaces of the bell on the surfaces of the mold ensure the clamping of the parts of the mold by wedge effect;
- the mold comprises a lower shell which forms a lower end of the mold and a first side of the mold, this lower shell defining a lower part of the said cavity, and this first side being intended to be located at the level of a leading edge of the bladed part and defining with the lower shell a groove configured to receive said shield; the mold is thus optimized to receive the metal shield and ensure its attachment to the preform via the resin, or even with an additional adhesive; - the mold comprises a side shell which forms a second side of the mold, this second side being opposite the first side and intended to be located at a trailing edge of the bladed part;
- the mold comprises an upper shell which forms an upper end of the mold and which defines an upper part of said cavity;
- the upper shell comprises a first inclined surface intended to cooperate with a first complementary surface of the lower shell, and a second inclined surface intended to cooperate with a second complementary surface of the side shell, said first and second surfaces of the upper shell being located on two opposite sides of the hull and being inclined opposite to the inclination of at least some of said inner surfaces of the bell; the inner surfaces of the bell can be tilted in four different directions; the surfaces of the upper shell can themselves be inclined in two directions opposite to each other and opposite to one of the inner surfaces of the bell; the sliding of the surfaces of the upper shell on the surfaces of the lower shell and of the side shell ensure the clamping of the parts of the mold by wedge effect; - Said first surface extends to the level of said groove.
- said cavity comprises a pay zone and two platform zones, the blade zone extending between the two platform zones;
- the mold further comprises a first end shell intended to be located at one of the platform zones of the cavity, and to define at least part of this zone;
- the mold comprises a second end shell intended to be located at the level of the other of the platform zones of the cavity, and to define at least part of this zone;
- the first and second end shells each comprise at least two parts between which is defined at least part of the corresponding platform zone;
- the parts of each of the first and second end shells are mounted on the lower shell, or even on the side shell, and interposed between uprights of the lower shell and of the side shell;
- the lower shell defines a lower part of one of the platform zones of the cavity, and an intermediate piece is attached to the lower shell to define a lower part of the other of the platform zones of the cavity;
- the base and/or the bell comprises at least one resin injection port
- the bell is made in one piece, or in two pieces, namely a belt and a cover;
- the present invention also relates to a process for molding at least one bladed turbomachine part by means of a molding device as described above, characterized in that it comprises the steps of: a) mounting a preform in the cavity of the mold as well as a metal shield arranged on one edge of this preform, b) closing the molding device by enclosing the mold between the base and the bell, c) putting the molding device of so as to clamp the mold between the bell and the base, or even also to heat the device, and d) injection of resin into the molding device in order to impregnate the preform and fix the shield to this preform.
- the stripping of the bladed part can then take place.
- Figure 1 is a schematic perspective view of a bladed part of a turbomachine
- Figure 2 is a schematic perspective view of a molding device according to one embodiment of the invention
- Figure 3 is a schematic sectional view along the line lil-lil of Figure 2, and shows a preform located in the molding device
- Figure 4 is a schematic sectional view along the line IV-IV of Figure 2, and shows the preform located in the molding device
- Figure 5 is a schematic perspective view of a base of the molding device of Figure 2;
- Figure 8 is a schematic perspective view of a lower shell of the molding device of Figure 2;
- Figure 7 is a schematic perspective view of the lower shell and the base of the molding device of Figure 2;
- Figure 8 is a schematic perspective view of the lower shell and the base of the molding device of Figure 2, and the bladed part disposed on the lower shell;
- Figure 9 is a view similar to that of Figure 8 and also shows schematic positioning members
- Figure 10 is a schematic perspective view of the lower shell, the base and the side shell of the molding device of Figure 2, as well as the bladed part disposed between the lower and side shells ;
- Figure 11 is a schematic perspective view of the lower shell, the base, the side shell, and first parts of end shells of the molding device of Figure 2, as well as the bladed part arranged between these shells;
- Figure 12 is a schematic perspective view of the lower shell, the base, the side shell, the first parts of end shells, and an upper shell of the molding device of the Figure 2, as well as the bladed part disposed between these shells;
- Figure 13 is a schematic perspective view of the complete mold and the base of the molding device of Figure 2;
- FIG.14 Figure 14 is a larger scale view of a detail of Figure 4;
- Figure 15 is a larger scale view of another detail of Figure 4;
- Figure 16 is a view similar to that of Figure 2 and shows an alternative embodiment of the molding device and in particular of its bell;
- Figure 17 is a view similar to that of Figure 13 and shows another embodiment of the molding device.
- FIG. 1 illustrates a bladed part 10 made of composite material for a turbomachine, this bladed part 10 being for example a fan blade or a stator blade, for example of a secondary flow in the case of a turbofan engine.
- the bladed part 10 comprises a blade 12.
- this blade 12 is connected by a stilt 14 to a foot 16 which has for example a dovetail shape and is shaped to be engaged in a cell of complementary shape of a rotor disc, in order to retain the blade on this disc.
- blade 12 extends between two platforms 16a, 16b which extend substantially parallel to each other and perpendicular to an axis of elongation of blade 12.
- the blade 12 comprises a leading edge 12a and a trailing edge 12b of the gases which flow in the turbomachine.
- the blade 12 has a curved or even twisted aerodynamic profile and comprises a lower surface 18 and a lower surface 20 extending between the leading 12a and trailing 12b edges.
- the blade 12 is made from a fiber preform obtained by three-dimensional weaving of fibers, for example carbon.
- the leading edge 12a of the blade is reinforced and protected by a metal shield 22 which is fixed to this leading edge 12a.
- the shield 22 is for example made of an alloy based on nickel and cobalt. In the present invention, this attachment is made by co-molding the preform with the shield 22 by means of a molding device 30, a first embodiment of which is shown in Figures 2 to 15.
- the molding device 30 is shown in its entirety in Figure 2. In the example shown, it has a generally parallelepipedic shape.
- Figures 3 and 4 represent sectional views of the device 30 and show that it comprises at least one internal cavity 32 configured to receive the fiber preform and the shield 22 of the bladed part 10 to be produced.
- this bladed part 10 is a stator blade.
- the cavity 32 essentially comprises three parts or zones, a pay zone Z1 intended to receive the part of the preform forming the blade 12 of the bladed part 10, and two platform zones Z2, Z3 intended to receive the parts of the preform forming the platforms 16a, 16b of the bladed part 10.
- the cavity 32 is further configured to receive the metal shield 22 which is previously placed on the edge of the preform intended to form the leading edge 12a of the blade 12.
- the molding device 30 is configured to allow the injection of a thermosetting resin into the cavity 32 in order to impregnate the preform and ensure the fixing of the shield 22 on this resin-impregnated preform. Fixing can be ensured either directly by the resin which acts as glue, or by an added film of glue.
- Figure 4 shows a resin injection port 34 which is located on one side of the device, and this device 30 preferably also includes a port 36 which allows the evacuation of excess resin and also to pull the vacuum and to Avoid trapping air in the cavity (porosity). This port 36 is for example located at an upper end of the device.
- the molding device 30 essentially comprises three elements, namely a base 38, a mold 40 and a bell 42.
- the base 38 forms a support and has a generally parallelepipedal shape in the example shown.
- the base 38 is represented alone in FIG. 5.
- the base 38 comprises a flat lower surface 38a which can be applied directly to a flat and horizontal support surface or rest on a platen of a press.
- the base 38 further comprises an upper surface 38b comprising a central recess 44 for mounting and interlocking a lower end 40aa of the mold 40.
- This recess 44 has a generally rectangular or parallelepipedic shape.
- the base 38 comprises around the recess 44 a first peripheral groove 48a for housing first sealing means, and a second peripheral groove 48b for housing second sealing means.
- These sealing means are, for example, elastomer gaskets which each form a closed loop.
- the groove 46a extends around and close to the recess 44 and that the groove 46b extends between the groove and the outer peripheral edge of the base 38.
- the bell 42 is particularly visible in FIGS. 4. As its name indicates, this element has a bell shape which can be considered as comprising a peripheral belt 42a and a cover 42b covering this belt.
- the bell 42 is formed in one piece while in the variant embodiment of Figure 16, the bell 42 is formed in two parts by the assembly of a belt 42a and a cover 42b.
- the bell 42 is configured to be mounted on the mold 40 and around the mold 40. It is further configured to bear in a sealed manner on the base 38 and to bear against the mold 40 by exerting on the latter a force of wedge pressure.
- the bell 42 externally has the general shape of a parallelepiped whose width and length dimensions are comparable to those of the base 38, so that, when the bell 42 is placed on the base 38, their side faces are substantially aligned in pairs (see Figure 2).
- the bell 42 has a thickness greater than that of the base 38.
- the bell 42 has a flat upper surface 42c which can rest on a jaw or another plate of a press.
- the sealing between the bell 42 and the base 38 is ensured by the sealing means located in the groove 46b.
- the lower end of the bell 42 rests on these sealing means which are thus clamped on assembly between the bell 42 and the base 38.
- the bell 42 comprises an internal space 48 for housing the mold 40. This space 48 opens on a lower surface at the lower end of the bell 42.
- Space 48 delimits a volume in the shape of a truncated pyramid.
- the space 48 thus has four inner side surfaces 48a, 48b, 48c, 48d which are inclined and which are also connected to the four corners of a flat inner bottom surface 48e of the bell 48.
- the surface 48e is rectangular here.
- the side surfaces 48a, 48b, 48c, 48d each have a generally trapezoidal shape.
- the side surfaces 48a, 48b are located on two opposite sides of the bell 42 and at the level of the platform zones Z2, Z3 of the cavity 32 (cf. FIG. 4).
- the side surfaces 48c, 48d are located on two opposite sides of the bell 42 and at the level of the leading 12a and trailing 12b edges of the payroll 12 (cf. FIG. 3).
- Figure 4 shows that the aforementioned injection port 34 opens onto the surface 48a, near the lower end of the bell 42.
- the inner surfaces 48a, 48b, 48c, 48d and 48e of the bell 42 are intended to rest on complementary surfaces of the mold 40 in order to apply by wedge effect a clamping and holding force of the mold 40 which is produced by assembling several parts.
- the mold 40 has the general shape of a truncated pyramid and comprises four outer side surfaces 40a, 40b, 40c, 40d inclined and connected to the four corners of a flat outer top surface 40th.
- the 40th surface is rectangular here.
- the side surfaces 40a, 40b, 40c, 40d each have a generally trapezoidal shape.
- the side surfaces 40a, 40b are located on two opposite sides of the mold 40 and at the level of the platform zones Z2, Z3 of the cavity 32 (cf. FIG. 4).
- the side surfaces 40c, 40d are located on two opposite sides of the mold and at the level of the leading 12a and trailing 12b edges of the payroll 12 (cf. FIG. 3).
- the sur-faces 48a, 48b of the bell 42 are substantially complementary to the surfaces 40a, 40b and intended to cooperate by sliding and bearing with these surfaces 40a, 40b when the bell 42 is mounted on the mold 40.
- the surfaces 48c, 48d of the bell 42 are substantially complementary to the surfaces 40c, 40d and intended to cooperate by sliding and bearing with these surfaces 40c, 40d when the bell 42 is mounted on the mold 40.
- the surface 48e of the bell 42 is intended to bear against the surface 40e when the bell 42 is mounted on the mold 40.
- the lower end 40aa of the mold 40 is engaged in the recess 44 of the base 38 and comprises a complementary shape to be engaged by male-female interlocking and in this recess.
- the lower end 40aa of the mold 40 thus comprises a lower boss 50 (cf. FIGS. 3, 4 and 6) which has a shape complementary to the recess 44.
- the lower end 40aa of the mold 40 comprises a peripheral surface 52 which is extends around the boss 50 and is intended to rest on the sealing means located in the groove 46a of the base 38.
- the mold 40 is obtained by assembling several parts to facilitate its assembly around the preform and the shield 22 and above all to facilitate the demolding of the bladed part 10 after hardening of the resin injected into the mold 40.
- the parts of the mold 40 are here formed by shells or shell elements which are nested into each other in order to define the cavity 32. As can be seen in the drawings, the cavity 32 is entirely delimited by the mold 40, which means that the mold 40 is configured to fully enclose the preform and loop it 22.
- the mold 40 essentially comprises five shells, namely:
- the lower shell 54 is visible alone in FIG. 6 and mounted on the base 38 in FIG. 7.
- This shell 54 forms the lower end 4Gaa of the mold 40, which comprises the boss 50, as well as a first side 57 of the mould, namely the one which comprises the surface 40c located on the side of the leading edge 12a of the blade 12 and therefore of the shield 22.
- the lower shell 54 defines a lower part of the cavity 32 as well as a groove 64 of this cavity which is shaped to receive the metal shield 22.
- This groove 84 is located at the junction of the lower end 40aa and the first side 57 of the mold 40.
- the lower end 40aa of the mold comprises an upper surface 66 having in section a convex curved shape (cf. FIG. 3) intended to be located on the side of the intrados 18 of the blade 12.
- the first side 57 of the mold includes an inclined surface 68 which extends upward from one edge of the surface 68. The intersection of the surfaces 68, 88 forms the aforementioned groove 84.
- Figure 3 shows that the surface 68 is located on the side of the surface 40c of the mold and the surface 48c of the bell 42 and that this surface 68 is inclined in a manner opposite to the inclination of the surfaces 40c, 48c.
- the surfaces 40c, 48c, on the one hand, and the surface 68, on the other hand, converge towards the upper end of the molding device 30.
- Figures 4 and 7 show that the surface 68 is connected at the level of the platform zones Z2, Z3 of the cavity 32 to surfaces end 70 which are substantially parallel to each other and perpendicular to the surface 66,
- the lower shell 54 defines at least a lower part of each of the platform zones Z2, Z3 of the cavity 32.
- One of the surfaces 70 can be formed directly on the shell 54 (on the left side in FIG. 4) and the Another of the surfaces 70 (on the right side in FIG. 3) can be formed by an intermediate part 72 attached to the lower shell 54 in order to facilitate the demolding of the bladed part 10, in particular when it has a complex shape or conformation.
- the side shell 56 is visible in Figures 3, 10 and 11 in particular and forms a second side 74 of the mold 40, namely that which comprises the surface 40d located on the side of the trailing edge 12b of the payroll 12.
- the side shell 56 is mounted and nested on the lower shell 54 and comprises at its lower end a complementary shape (with steps 76 - cf, Figure 3) of part of the mould.
- the side shell 56 includes an inclined surface 78 which extends upward from the steps 76.
- the intersection of the steps 76 and the surface 78 forms a sharp edge 79 which is configured to be positioned along a edge of surface 66 and at the trailing edge 12b of blade 12.
- Surface 78 therefore extends upward from surface 66.
- Figure 3 shows that the surface 78 is located on the side of the surface 40d of the mold and the surface 48d of the bell 42 and that this surface 78 is inclined in a manner opposite to the inclination of the surfaces 40d, 48d, In the example shown, the surfaces 40d, 48d, on the one hand, and the surface 78, on the other hand, converge towards the upper end of the molding device 30.
- FIG. 3 also shows that the surfaces 68 and 78 have reverse tilts.
- Upper shell 62 forms the upper end of mold 40, which includes surface 40e.
- the shell 62 defines an upper part of the cavity 32.
- the lower end of the shell 62 comprises a lower surface 80 having in section a concave curved shape (cf. figure 3) intended to be located on the side of the extrados 20 of the blade 12, and to extend from the trailing edge 12b of the payroll 12 to the leading edge 12a and to the metal shield.
- This surface 80 extends between two inclined lateral surfaces 82, 84 which are complementary to the surfaces 88, 78 and intended to cooperate by sliding and bearing with these surfaces during the assembly of the mold 40.
- the upper shell 82 rests on the upper ends of the lower shell 54 and of the side shell 56 (FIG. 3).
- Surfaces 82, 84 of upper shell 62 are located at the sides of mold 40 having surfaces 40c and 40d.
- the upper shell comprises end surfaces 86 substantially parallel to one another and perpendicular to the upper surface 40e of the mold. As seen in Figure 4, surfaces 86 are aligned with surfaces 70 when mold 40 is assembled.
- the end shells 58, 60 are intended to delimit the platform zones Z2, Z3 of the cavity 32 with a part of the lower shell 54 and of the spacer 72 (FIG. 4).
- a first end shell 58 located on the left in FIG. 4 comprises surface 40a and is formed by assembling two parts 58a, 58b delimiting part of platform zone Z2 between them.
- a first of the parts 58a is mounted between the upper shell 62 and part of the platform 18a.
- This first part 58a comprises a surface 58a1 complementary to the surface 86 and intended to cooperate by sliding with the latter during assembly of the mold.
- This first part 58a further comprises a surface S8a2 delimiting part of the platform zone Z1 (cf. FIG. 14).
- the second part 58b is mounted between the part 58a and the bell 42 and comprises the aforementioned surface 40a.
- the second part 58b further comprises a surface 58b1 delimiting one side of the platform zone Z1, opposite to the blade 12.
- FIG. 14 shows that the platform zone Z1 is delimited by the surface 58b1, on one side, and by the surfaces 70 and 58a2 on the other side.
- the parts 58a, 58b are nested one inside the other thanks to complementary shapes and are also interposed between the first side 57 of the lower shell 54 and the side shell 56. More exactly, as can be seen in Figures 11 at 13, parts 58a, 58b are engaged between uprights 88, 90 of the lower hull 54 and of the side hull 56. Parts 58a, 58b can be mounted by sliding between these uprights by rail-slide systems 92.
- the second end shell 60 located on the right in FIG. 4 comprises the surface 40b and is formed by the assembly of two parts 60a, 60b delimiting between them a part of the platform zone Z3,
- a first of the parts 60a is mounted between the upper shell 62 and part of the platform 16b.
- This first part 60a comprises a surface 60a 1 complementary to the surface 86 and intended to cooperate by sliding with the latter during assembly of the mold.
- This first part 60a further comprises a surface 60a2 delimiting part of the platform zone Z3.
- the second part 60b is mounted between the part 60a and the bell 42 and comprises the aforementioned surface 40b.
- the second part 60b further comprises a surface 60b1 delimiting one side of the platform zone, opposite to the blade 12.
- FIG. 15 shows that the platform zone Z3 is delimited by the surface 6ûb1, on one side, and by the surface 60a2 and by the surface 70 of the spacer 72, on the other side.
- the parts 60a, 60b are nested one inside the other thanks to complementary shapes and are also interposed between the first side 57 of the lower shell 54 and the side shell 56. More exactly, as can be seen in FIGS. at 13, parts 60a, 60b are engaged between uprights 88, 90 of the lower shell 54 and of the side hull 56. Parts 60a, 60b can also be mounted by sliding between these uprights by rail-slide systems 92.
- Figure 16 shows an alternative embodiment of the bell 42 already mentioned in the foregoing and which consists in making it in two parts, a belt 42a which includes the inner surfaces 48a, 48b, 48c and 48d and a cover 42b which includes the 48th bottom surface.
- the line of demarcation between the lid 42a and the belt 42b could advantageously be located so as to encapsulate the upper shell 62, in order to keep it integral with the lower shell 54 of the mold and that it does not remain blocked in the bell 42 during unmoulding.
- FIG. 17 illustrates another embodiment variant, this time of the mold 40, the lower shell 54 of which may also comprise an additional side (in addition to side 57).
- the end shells 58, 60 of the mould, or even just a part such as part 60b or part 58b, could be integrated into the lower shell 54.
- the cavity 32 could be shaped to accommodate several preforms for the simultaneous production of several bladed parts, or even several separate cavities for the production of these bladed parts.
- the present invention also relates to a method of molding at least one bladed part of a turbomachine by means of the molding device 30.
- This method comprises in particular the steps of: a) mounting the preform in the cavity 32 of the mold 40 as well as the metal shield 22 arranged on one edge of this preform, b) closing the molding device 30 by enclosing the mold 40 between the base 38 and the bell 40, c) pressing the molding device 30 so as to clamp the mold 40 between the bell 42 and the base 38, and d) injecting resin into the molding device 30 in order to impregnate the preform and fix the shield 22 to this preform.
- Step a) is illustrated in Figures 8 to 13.
- the preform is placed on the lower shell 54 of the mold 40 so that its lower surface 18 rests on the surface 88 and its edge equipped with the metal shield 22 is located in the groove 64. Parts of the platforms 16a, 16b then rest on the surfaces 70.
- positioning members 91 are arranged on the base 38 at the level of the platforms 16a, 16b so as to hold blocks or layers 94 or of woven preform in place, which are added to the surfaces of the platforms opposite the payroll 12.
- These blocks or layers 94 are particularly visible in FIGS. 14 and 15.
- These blocks or layers can consist of layers of fibers woven by three-dimensional interlocking like the rest of the preform .
- FIG. 8 the preform is placed on the lower shell 54 of the mold 40 so that its lower surface 18 rests on the surface 88 and its edge equipped with the metal shield 22 is located in the groove 64. Parts of the platforms 16a, 16b then rest on the surfaces 70.
- positioning members 91 are arranged on the
- the block or the layer 94 is arranged between sacrificial (machined) or non-sacrificial glass plies, located on the left in the drawing, for resistance to galvanic corrosion or friction, for example, and woven carbon 3D which makes up the blade of the preform, with continuity of the fibers in the radius, located on the right of the drawing.
- the side shell 56 is mounted on the lower shell 54 and makes it possible to wedge the trailing edge 12b of the preform.
- the parts 58a, 60a of the end shells 58, 60 are mounted between the uprights 88, 90 in Figure 11, then the upper shell 62 is mounted between these parts 58a, 58b and on the preform in Figure 12. Its surface lower 80 then rests on the extrados 20 of the pay 12.
- Parts 58b, 60b of end shells 58, 60 58, 60 are then mounted between uprights 88, 90 in Figure 13.
- Step b) is illustrated in FIG. 2 and consists in covering the mold 40 with the bell 42 which rests on the mold 40 and on the base 38. Closing the device by the bell 42 makes it possible to position the parts of the mold relative to each other, to press them against each other, and to guarantee compaction of the preform to a predetermined thickness.
- the device 30 is placed under a press in step d) in order to clamp the shells 54, 56, 58, 60, 62 of the mold 40 against each other, and the resin is injected into the cavity 32 in step d) .
- Resin injection can be done by prior heating of the device 30 to a predetermined temperature in order to fluidize the resin. Once the resin has been completely injected, it is heated again to reach a baking temperature and activate the polymerization of the resin and its hardening.
- the device according to the invention is advantageous insofar as it is adapted and optimized for the injection of resin into the preform and the simultaneous co-molding of the shield. Furthermore, the dissociation of the mold vis-à-vis the base and the bell allows the use of several mold configurations for the same bell and the same base, the different mold configurations differ from one another. by the shape and dimensions of the internal cavities 32 for example. A device according to the invention can thus be used for the manufacture of several different bladed parts using molds adapted to these parts.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Materials Engineering (AREA)
- Textile Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN202280035496.9A CN117355411A (zh) | 2021-04-28 | 2022-04-22 | 用于对涡轮机的轮叶部件进行模制的装置 |
EP22735514.6A EP4330023A1 (fr) | 2021-04-28 | 2022-04-22 | Dispositif de moulage d'une piece aubagee de turbomachine |
US18/557,002 US20240059032A1 (en) | 2021-04-28 | 2022-04-22 | Device for moulding a bladed part of a turbomachine |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US17/242,942 US20220347945A1 (en) | 2021-04-28 | 2021-04-28 | Device for moulding a bladed part of a turbomachine |
US17/242,942 | 2021-04-28 | ||
FR2113614A FR3130678B1 (fr) | 2021-12-16 | 2021-12-16 | Dispositif de moulage d’une piece aubagee de turbomachine |
FRFR2113614 | 2021-12-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2022229547A1 true WO2022229547A1 (fr) | 2022-11-03 |
Family
ID=82321338
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2022/050765 WO2022229547A1 (fr) | 2021-04-28 | 2022-04-22 | Dispositif de moulage d'une piece aubagee de turbomachine |
Country Status (3)
Country | Link |
---|---|
US (1) | US20240059032A1 (fr) |
EP (1) | EP4330023A1 (fr) |
WO (1) | WO2022229547A1 (fr) |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2956057A1 (fr) | 2010-02-10 | 2011-08-12 | Snecma | Decoupe de preformes avant injection rtm par jet d'eau et cryogenisation |
WO2014076408A1 (fr) | 2012-11-13 | 2014-05-22 | Snecma | Preforme et aube monobloc pour turbomachine |
US20140197567A1 (en) * | 2011-05-10 | 2014-07-17 | Snecma | Compacting and injection mold for a fiber preform for fabricating a turbine engine guide vane made of composite material |
FR3014008A1 (fr) | 2013-12-04 | 2015-06-05 | Snecma | Procede d'impregnation d'une preforme fibreuse et dispositif pour la mise en œuvre de ce procede |
US20160009003A1 (en) * | 2013-03-01 | 2016-01-14 | Safran | Injection mould for manufacturing a rotary part made of a composite material having external flanges, in particular of a gas turbine casing |
US20160121562A1 (en) * | 2013-06-13 | 2016-05-05 | ThyssenKrupp Carbon Components GmbH | Device for producing a component from fiber composite material |
FR3029134A1 (fr) | 2014-12-02 | 2016-06-03 | Snecma | Procede de controle de position d'une preforme d'aube composite de turbomachine dans un moule |
FR3032147A1 (fr) | 2015-02-03 | 2016-08-05 | Michelin & Cie | Pneu radial ayant une structure de ceinture amelioree |
FR3046564A1 (fr) | 2016-01-13 | 2017-07-14 | Snecma | Outillage de levage et de transport pour preforme fibreuse et procede de fabrication d'une piece en materiau composite |
FR3051386A1 (fr) | 2016-05-19 | 2017-11-24 | Snecma | Element de moule pour moulage rtm |
US20210010377A1 (en) * | 2018-03-28 | 2021-01-14 | Safran | Method for manufacturing a vane from a composite material with a fitted metal leading edge for a gas turbine |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5190773A (en) * | 1991-11-18 | 1993-03-02 | United Technologies Corporation | Mold for fabricating composite articles having integrally bonded stiffening members |
US5686038A (en) * | 1995-06-06 | 1997-11-11 | The Boeing Company | Resin transfer molding of composite materials that emit volatiles during processing |
US6413074B1 (en) * | 1999-09-28 | 2002-07-02 | Composix Corporation | Assembly for molding plastic material |
CN108995250B (zh) * | 2018-06-21 | 2021-04-20 | 中国航空工业集团公司基础技术研究院 | 一种隔段式回转结构复合材料制件的rtm成型模具 |
-
2022
- 2022-04-22 EP EP22735514.6A patent/EP4330023A1/fr active Pending
- 2022-04-22 WO PCT/FR2022/050765 patent/WO2022229547A1/fr active Application Filing
- 2022-04-22 US US18/557,002 patent/US20240059032A1/en active Pending
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2956057A1 (fr) | 2010-02-10 | 2011-08-12 | Snecma | Decoupe de preformes avant injection rtm par jet d'eau et cryogenisation |
US20140197567A1 (en) * | 2011-05-10 | 2014-07-17 | Snecma | Compacting and injection mold for a fiber preform for fabricating a turbine engine guide vane made of composite material |
WO2014076408A1 (fr) | 2012-11-13 | 2014-05-22 | Snecma | Preforme et aube monobloc pour turbomachine |
US20160009003A1 (en) * | 2013-03-01 | 2016-01-14 | Safran | Injection mould for manufacturing a rotary part made of a composite material having external flanges, in particular of a gas turbine casing |
US20160121562A1 (en) * | 2013-06-13 | 2016-05-05 | ThyssenKrupp Carbon Components GmbH | Device for producing a component from fiber composite material |
FR3014008A1 (fr) | 2013-12-04 | 2015-06-05 | Snecma | Procede d'impregnation d'une preforme fibreuse et dispositif pour la mise en œuvre de ce procede |
FR3029134A1 (fr) | 2014-12-02 | 2016-06-03 | Snecma | Procede de controle de position d'une preforme d'aube composite de turbomachine dans un moule |
FR3032147A1 (fr) | 2015-02-03 | 2016-08-05 | Michelin & Cie | Pneu radial ayant une structure de ceinture amelioree |
FR3046564A1 (fr) | 2016-01-13 | 2017-07-14 | Snecma | Outillage de levage et de transport pour preforme fibreuse et procede de fabrication d'une piece en materiau composite |
FR3051386A1 (fr) | 2016-05-19 | 2017-11-24 | Snecma | Element de moule pour moulage rtm |
US20210010377A1 (en) * | 2018-03-28 | 2021-01-14 | Safran | Method for manufacturing a vane from a composite material with a fitted metal leading edge for a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
US20240059032A1 (en) | 2024-02-22 |
EP4330023A1 (fr) | 2024-03-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2707199B1 (fr) | Moule de compactage et d'injection pour preforme fibreuse destinee a la fabrication d'une aube de redresseur de turbomachine en materiau composite | |
EP0770472B1 (fr) | Procédé de fabrication d'un panneau en matériau composite avec moulage par transfert de résine | |
EP0984853B1 (fr) | Outillage de reparation sur site d'une structure composite presentant une zone endommagee et procede correspondant | |
EP2560808B1 (fr) | Dispositif de fabrication d'un carter en materiau composite et procede de fabrication mettant en oeuvre un tel dispositif | |
FR2559422A1 (fr) | Element a profil de pale creux composite muni d'une structure support interne ondulee et son procede de fabrication | |
EP2083980B1 (fr) | Outil composite pour le moulage de pièces cylindriques | |
FR2559423A1 (fr) | Elements a profil de pale creux composites et leur procede de fabrication | |
EP1755867B1 (fr) | Procede de fabrication d'elements, tels que des ailettes pour cascades d'inverseur de poussee, par moulage d'un materiau composite | |
WO2014009635A1 (fr) | Procede de fixation d'un renfort metallique structurel sur une partie d'une aube de turbine a gaz en materiau composite et moule d'injection pour la mise en œuvre d'un tel procede. | |
EP2077183A1 (fr) | Bride en composite avec partie d'usinage | |
FR3026980A1 (fr) | Procede d'immobilisation d'une preforme dans un moule | |
WO2021105600A1 (fr) | Aube composite pour un moteur d'aeronef et ses procedes de fabrication et de reparation | |
CH711914A2 (fr) | Procédé pour fabriquer un boîtier de montre en fibres de carbone et boîtier de montre en fibres de carbone. | |
FR3017321A1 (fr) | Noyau de moule d'injection pour la realisation d'une piece en materiau composite ayant un caisson ferme | |
WO2022229547A1 (fr) | Dispositif de moulage d'une piece aubagee de turbomachine | |
EP0780213A1 (fr) | Procédé de fabrication d'une pièce en matériau composite par moulage par transfert de résine, et pièce obtenue par ce procédé | |
EP2682257A1 (fr) | Procédé et dispositif de fabrication de pièces en matériau composite par RTM | |
EP2706209B1 (fr) | Procédé de fabrication d'un collecteur d'admission intégrant un échangeur de chaleur et collecteur correspondant | |
EP4330027A1 (fr) | Dispositif de mise en forme d'une preforme fibreuse pour la realisation d'une piece aubagee de turbomachine | |
FR2985213A1 (fr) | Panneau composite auto-raidi et procede de realisation | |
FR3130678A1 (fr) | Dispositif de moulage d’une piece aubagee de turbomachine | |
FR3081761A1 (fr) | Procede de fabrication d'une piece en matiere composite | |
WO2023152356A1 (fr) | Moule pour panneau incurvé | |
FR3130672A1 (fr) | Dispositif de mise en forme d’une preforme fibreuse pour la realisation d’une piece aubagee de turbomachine | |
WO2024069077A1 (fr) | Outillage et procede de fabrication d'une aube composite pour un moteur d'aeronef |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 22735514 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 18557002 Country of ref document: US |
|
WWE | Wipo information: entry into national phase |
Ref document number: 202280035496.9 Country of ref document: CN |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2022735514 Country of ref document: EP |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
ENP | Entry into the national phase |
Ref document number: 2022735514 Country of ref document: EP Effective date: 20231128 |