WO2013079860A1 - Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees - Google Patents
Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees Download PDFInfo
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- WO2013079860A1 WO2013079860A1 PCT/FR2012/052723 FR2012052723W WO2013079860A1 WO 2013079860 A1 WO2013079860 A1 WO 2013079860A1 FR 2012052723 W FR2012052723 W FR 2012052723W WO 2013079860 A1 WO2013079860 A1 WO 2013079860A1
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- blade
- preform
- blank
- segments
- shaping
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- 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
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
- B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/24—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/10—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on aluminium oxide
- C04B35/111—Fine ceramics
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
- C04B35/565—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides based on silicon carbide
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- D—TEXTILES; PAPER
- D03—WEAVING
- D03D—WOVEN FABRICS; METHODS OF WEAVING; LOOMS
- D03D25/00—Woven fabrics not otherwise provided for
- D03D25/005—Three-dimensional woven fabrics
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- 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
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- 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
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- 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
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/522—Oxidic
- C04B2235/5224—Alumina or aluminates
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/614—Gas infiltration of green bodies or pre-forms
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2253/00—Other material characteristics; Treatment of material
- F05C2253/04—Composite, e.g. fibre-reinforced
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- 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
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- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
- Y10T29/49337—Composite blade
Definitions
- the invention relates to turbines or compressors for turbomachines, in particular for aeronautical turboshaft engines or industrial turbines, and more particularly to the manufacture of a turbomachine blade with integrated inner and outer platforms for a turbine distributor or a compressor rectifier.
- CMC ceramic matrix composite materials
- the object of the invention is to provide a simplified method for producing a turbomachine blade of composite material having a blade integral with inner and outer platforms.
- a method comprising: the multilayer weave formation of a fibrous blank having a longitudinal direction corresponding to that of the blade to be produced and comprising in its thickness a first part with several layers of yarns bonded together by weaving, a second woven part and a third part; woven part, the first part being situated between the second part and the third part to which it is connected by weaving on only part of its longitudinal dimension,
- the first part of the blank has an inner zone of delimitation between two layers of adjacent son which extends over the entire longitudinal dimension of the first part of the blank and opens only at the longitudinal ends. of the first portion of the blank so, after shaping, to form a preform portion for the hollow blade.
- the segments of the second part and the third part of the blank not connected to the first part are located in longitudinal end portions of the second part and the third part of the blank. .
- the second and third parts of the blank are woven together at the first part of the blank in longitudinal end portions and the segments of the second part and the third part of the blank. blank not bonded to the first portion of the blank extend between said longitudinal end portions.
- the preform part for the blade has a width smaller than those of the preform parts for the blades.
- inner and outer platforms and the excess width of the first part of the blank is removed by cutting to shape the preform portion for the blade while leaving a connection between the second part and the third part of the blank, via a portion of the first portion of the blank, over the entire width of the blank, along the connections of said segments with the remainder of the blank.
- the preform of the blade is formed with an external extension extending beyond the preform portion for the external platform of the outer side thereof and, when producing the preform of the blade, the outer extension is shaped to form a preform portion for a mounting portion in a housing of turbine or compressor.
- the blade preform is formed with an inner extension extending below the preform portion. for an inner platform, on the inner side thereof and, when making the preform of the blade, the inner extension is shaped to form a preform portion for a hooking portion.
- FIG. 1 is a schematic perspective view of a turbomachine blade
- FIG. 2 is a diagrammatic plan view of a woven fiber blank intended for producing a fibrous preform for a blade of the type of that of FIG. 1;
- FIGS. 5 and 6 are diagrammatic views on an enlarged scale of planes of weaving of the blank of FIG. 2, seen in section along planes V-V and VI-VI of FIG. 2;
- FIGS. 7 to 9 are schematic views showing steps of making a blade preform from the fiber blank of Figures 2 to 6;
- FIG. 10 is a diagrammatic plan view of another embodiment of a woven fiber blank intended for producing a fibrous preform for a blade of the type of that of FIG. 1;
- FIG. 11 is a side view of the blank of Figure 10;
- Figure 12 is a schematic sectional view along the plane XII-XII of Figure 10;
- FIG. 13 to 15 are schematic views showing steps of making a blade preform from the fiber blank of Figures 10 to 12;
- FIG. 16 is a partial view showing an alternative embodiment of the blade of FIG.
- FIG. 1 very schematically shows a blade 10, for example a fixed blade of turbine distributor of an aeronautical turbomachine.
- the blade 10 comprises a blade 12 and inner and outer platforms 14 and 14.
- the outer face 14b of the platform 14 and the inner face 16a of the platform 16 are intended to define the flow of gas flow in the turbine after mounting the blade 10 in a turbine casing.
- the blade 12 extends between the platforms 14 and 16, of which it is integral, and at its ends protrudes from the inside of the platform. form 14 and the outer side of the platform 16.
- the blade 12 is hollow with a longitudinal internal passage 12a which extends all along the blade and opens at both ends.
- the passage 12a is in particular intended to allow the passage of a flow of cooling air.
- the platforms 14, 16 extend between their upstream and downstream ends along general directions which form non-zero angles with respect to a plane normal to the longitudinal direction of the blade 12.
- upstream and downstream are used with reference to the direction of flow in the turbomachine.
- the blade 10 is made of composite material. Its manufacture comprises the formation of a fibrous preform having a shape corresponding to that of the blade and the densification of the preform by a matrix.
- Figure 2 shows in plan a fiber blank 101 from which a fibrous preform of the blade 10 can be formed.
- the blank 101 is obtained from a three-dimensional woven web (100) or multi-layer web 100, the web 100 extending generally in a direction X corresponding to the longitudinal direction of the blade to be manufactured.
- the weaving is carried out for example with warp yarns extending in the X direction, being noted that weaving with weft yarns extending in this direction is also possible.
- a plurality of blanks 101 may be woven one after the other in the X direction. Several parallel rows of blanks 101 may also be woven simultaneously.
- a blank 101 comprises, in its thickness, a first portion 102, a second portion 104 and a third portion 106.
- the portion 102 is located between the portion 104 and the portion 106 and is connected to portions 104 and 106 by 3D weaving except at the level of delimitations 103a, 105a between portion 102 and portion 104 and delimitation 103b, 105b between portion 102 and portion 106.
- Deliveries 103a, 103b extend over any the width of the blank 101 (raster size) from one end 101a of the blank 101 to the debonding bottoms 103c and 103d.
- the debonding bottoms 103c and 103d extend between the longitudinal edges 101c and 101d of the blank 101 in a direction forming a non-zero angle with respect to the weft direction to respect the orientation of the inner platform 14.
- the delimitations 105a, 105b extend over the entire width of the blank 101 from the other end 101b of the blank 101 to divestment funds 105c and 105d.
- the debonding bottoms 105c and 105d extend between the longitudinal edges 101c and 101d of the blank 101 in a direction forming a non-zero angle with respect to the weft direction in order to respect the orientation of the outer platform 16.
- a debonding 102a is formed substantially in the middle of the portion 102, over the entire length of the blank 101 and at a distance between the longitudinal edges 101c and 101d, between limits 102b and 102c.
- the debonding 102a is intended to allow the formation of the internal passage of the hollow blade of the blade to be manufactured.
- a debonding is provided between two layers of warp yarns by omitting to pass a weft thread through the debonding zone to bind son of warp layers located on either side of the debonding.
- FIGS. 5 and 6 show an example of 3D weaving with interlock weave and delimitations 102a, 105a and 105b, the delimitations 103a and 103b being obtained in the same way as the delimitations 105a and 105b.
- the deliaisons are represented by dashes.
- Part 102 includes a plurality of warp yarn layers (six in the illustrated example) which are bonded by 3D weave except at debonding 102a.
- the portions 104 and 106 each comprise a plurality of layers of warp yarns (three in the illustrated example) which are linked together by 3D weaving.
- the warp layers of the parts 102, 104 and 106 are, in the example shown, all related to each other.
- the segments 104a, 104b and 106a, 106b of the portions 104, 106 unrelated to the portion 102 are unfolded as shown in FIG. 7 to form preform portions for the platforms 14, 16, the segments 104a, 104b being adjacent to the delimitations 103a, 105a and the segments 106a, 106b being adjacent to the delimitations 103b, 105b.
- the unfoldings are made at the level of the disbursement funds.
- the cuts are made according to the lines indicated in dashed lines in FIG. 8 to eliminate the portions in the segments of the portion 102 on the inner side of the unfolded segments 104a, 106a and on the outer side of the unfolded segments 104b, 106b and, on the other hand, in the segment of the blank 101 extending between the unfolded segments, so as to leave only the parts useful for forming a preform portion for the blade of the blade to be manufactured.
- a woven bond is also left between the portions 102, 104 and 106 across the entire width of the blank 101 in areas extending along the connections of the segments 104a, 104b, 106a, 106b with the remainder of the blank, thereby forming cords 104c, 106c and 104d, 106d.
- This makes it possible to secure the continuity of the connection between segments 104a, 106a and between segments 104b, 106b.
- Surplus portions of portion 102 on the inner side of segments 104a, 106a and the outer side of segments 104b, 106b may also be removed by cutting.
- a fibrous preform of the blade to be manufactured is then molded by means of conformation tooling with deformations to obtain the desired hollow blade profile and the desired shapes for the platforms.
- a preform 110 (FIG. 9) is obtained with a portion 112 of preform for the hollow blade, and portions 114, 116 of preforms for the inner and outer platforms.
- the inner passage 112a of the preform portion 112 for the hollow blade is formed by introducing a tool element into the debonding 102a.
- a hollow CMC blade such as that of FIG. 1 can be manufactured as follows.
- a fibrous web 100 is woven by three-dimensional weaving, comprising a plurality of fibrous blanks 101 oriented for example in a warp direction, with debonding zones, as shown in FIG. 2.
- Ceramic yarns, especially yarns, can be used for weaving.
- silicon carbide (SiC) -based wires for example those supplied under the name "Nicalon" by the Japanese company Nippon Carbon.
- Other ceramic son can be used, including refractory oxide son, such as Al2O3 alumina-based son, especially for CMC materials of the oxide / oxide type (fibers of the fiber reinforcement and matrix oxide refractory). It would also be possible to use carbon threads for a CMC material with carbon fiber reinforcement.
- the fibrous web may be treated to remove the size present on the fibers and the presence of oxide on the surface of the fibers.
- a thin layer of defrosting interphase coating can then be formed on the fibers of the fibrous band by chemical vapor infiltration, or CVI ("Chemical Vapor Infiltration").
- the interphase material is, for example, pyrolytic carbon PyC, boron nitride BN or boron doped carbon BC.
- the thickness of the layer formed is for example between 10 nanometers and 100 nanometers to maintain a deformation capacity of fibrous blanks.
- the fibrous web is then impregnated with a consolidation composition, typically a carbon precursor resin or a ceramic precursor resin optionally diluted in a solvent. After drying, the individual fibrous blanks are cut. Each blank is shaped (as illustrated in Figures 7 to 9) and placed in a tooling for shaping the blade preform parts and inner and outer platforms.
- a consolidation composition typically a carbon precursor resin or a ceramic precursor resin optionally diluted in a solvent.
- the resin is crosslinked and then pyrolyzed after removing the preform from the shaping tool to obtain a blade preform consolidated by the pyrolysis residue.
- the amount of consolidation resin is chosen to be sufficient but not excessively so that the pyrolysis residue binds the fibers of the preform so that it can be manipulated while retaining its shape without the assistance of a tool.
- a second debritting interphase coating layer may be formed by CVI, for example PyC, BN or BC.
- CVI for example PyC, BN or BC.
- the production of a two-layer interphase coating before and after consolidation is described in EP 2 154 119.
- a ceramic matrix densification of the consolidated preform is then carried out for example by CVI.
- the matrix may be SiC or be a self-healing matrix comprising PyC pyrolytic carbon matrix, boron carbide B 4 C or ternary Si-BC system as described in particular in documents US 5 246 756 and US 5 965 266.
- Other types of ceramic matrix can such as refractory oxide matrices, for example alumina, in particular for CMC materials of the oxide / oxide type, may be envisaged.
- the densification is preferably carried out in two steps separated by a step of machining the blade to its desired dimensions, in particular to eliminate the ribs from the cords 104c, 106c, 104d and 106d, to obtain the desired final shape for the platforms 14, 16 and possibly to obtain the desired profile of the blade 12.
- FIGS. 10 to 15 Another embodiment of a fibrous preform for a blade of the type of that of FIG. 1 will now be described with reference to FIGS. 10 to 15.
- a blank 201, from which a fibrous blade preform can be formed, is obtained from a 3D woven web in a manner similar to the web 100 of FIG.
- the blank 201 comprises in its thickness a first portion 202, a second portion 204 and a third portion 206.
- the portion 202 is located between the portion 204 and the portion 206 and is connected to the portions 204 and 206 by 3D weaving except at the of a debinding 203 between the part 202 and the part 204 and a debinding 205 between the part 202 and the part 206.
- the debonding 203, 205 extend over the whole width of the blank 201 and between funds of debonding 203a, 203b and 205a, 205b which are spaced apart from the opposite ends 201a, 201b of the blank 201.
- the debonding bottoms extend between the longitudinal edges 201c, 201d of the blank 201 in directions making angles non-zero with respect to the weft direction in order to respect the orientations of the inner and outer platforms of the blade to be manufactured.
- a debonding 202a is formed substantially in the middle of the portion 202, over the entire width of the blank 201 and at a distance of its longitudinal edges 201c and 201d, between 202b and 202c limits.
- the debonding 202a is intended to allow the formation of the internal passage of the hollow blade of the blade to be manufactured.
- segments 204a and 204b of portion 204 adjacent to debonding 203 and extending from debonding bottoms 203a, 203b are unfolded as shown in FIG. 13.
- segments 206a and 206b of FIG. part 206 adjacent to the Debonding 205 and extending from the debonding funds 205a, 205b are unfolded as shown in Figure 13.
- the unfoldings are made at the level of funds déliaisons.
- the segments 204a, 206a, on the one hand, and the segments 204b, 206b, on the other hand, are intended to form preform parts for the inner and outer platforms of the blade to be manufactured.
- the lengths of the segments may be limited to the dimensions necessary for this purpose by cutting off surplus portions of the portions 204 and 206 in the middle regions thereof, the cutting lines being shown in dashed lines in FIGS. 10 and 11.
- cutouts are made along the lines indicated in dotted lines in FIG. 14 to eliminate excess portions, on the one hand, in the segments of the blank 201 situated on the inside of the unfolded segments 204a, 206a and on the outer side of the segments.
- a woven bond is also left between the portions 202, 204, and 206 across the entire width of the blank 201 in areas extending along the connections of the unfolded segments with the remainder of the blank, thereby forming cords 204c, 206c, and 204d, 206d.
- a 3D weave could be omitted in at least a portion of the portions eliminated by cutting.
- a fiber preform of the blade to be manufactured is then made by molding by means of conformation tooling with deformation to obtain the desired hollow blade profile and the desired shapes for the platforms.
- a preform 210 (FIG. 15) is obtained with a portion 212 of hollow blade preform having an internal passage 212a, and portions 214, 216 of inner and outer platform preforms.
- FIG. 16 very schematically shows the outer part of a turbine nozzle vane 30 according to an embodiment variant of the blade 10 of FIG.
- the blade 30 comprises a hollow blade 32 integral with an inner platform (not shown) and an outer platform 36.
- the blade 30 is distinguished from the blade 10 of FIG. 1 in that it comprises upstream and downstream hooks 38 which are formed in the continuity of the blade 32 on the outer side of the outer platform 36.
- the portion of the fiber preform forming the blade preform is extended on the outer side beyond the location of the outer platform and the this extension is shaped by cuts and deformations to obtain preform parts corresponding to the hooks 18.
- the hooks 18 constitute blade mounting portions in a turbine casing.
- a similar arrangement may be provided on the inner side of the blade by extending the portion of the fibrous blank forming the blade preform on the inner side below the location of the inner platform, this extension being shaped. by cutting and deformation to obtain preform parts corresponding to attachment parts.
- Such attachment portions may be used for connection to an inner housing or to support a ring bearing an abradable coating.
- CMC organic matrix composite material
- each blade preform obtained maintained in its tooling is impregnated by a resin by injection or infusion.
- Crosslinking heat treatment resin is made to obtain a blade preform.
- Several successive cycles of impregnation with a resin and crosslinking thereof can be carried out. Final machining may possibly be performed.
- the resin used for consolidation and densification is a polymer matrix precursor resin, such as an epoxy, bismaleimide or polyimide resin, for example.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Ceramic Engineering (AREA)
- Materials Engineering (AREA)
- Textile Engineering (AREA)
- Composite Materials (AREA)
- Organic Chemistry (AREA)
- Structural Engineering (AREA)
- Manufacturing & Machinery (AREA)
- General Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Woven Fabrics (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12806573.7A EP2785520B1 (fr) | 2011-12-01 | 2012-11-26 | Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees |
RU2014121516A RU2608422C2 (ru) | 2011-12-01 | 2012-11-26 | Способ изготовления композитных лопаток турбинного двигателя со встроенными полками |
JP2014543956A JP5973589B2 (ja) | 2011-12-01 | 2012-11-26 | 組み込まれたプラットフォームを備えた複合材料製のターボ機械のベーンを製造する方法 |
US14/361,942 US9427834B2 (en) | 2011-12-01 | 2012-11-26 | Method of fabricating a composite material turbine engine vane with incorporated platforms |
CN201280059268.1A CN103974824B (zh) | 2011-12-01 | 2012-11-26 | 由复合材料制造并包括结合的平台的涡轮机叶片的制备方法 |
CA2857453A CA2857453C (fr) | 2011-12-01 | 2012-11-26 | Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1103663 | 2011-12-01 | ||
FR1103663A FR2983428B1 (fr) | 2011-12-01 | 2011-12-01 | Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2013079860A1 true WO2013079860A1 (fr) | 2013-06-06 |
Family
ID=47436070
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/052723 WO2013079860A1 (fr) | 2011-12-01 | 2012-11-26 | Procede de fabrication d'une aube de turbomachine en materiau composite a plates-formes integrees |
Country Status (8)
Country | Link |
---|---|
US (1) | US9427834B2 (fr) |
EP (1) | EP2785520B1 (fr) |
JP (1) | JP5973589B2 (fr) |
CN (1) | CN103974824B (fr) |
CA (1) | CA2857453C (fr) |
FR (1) | FR2983428B1 (fr) |
RU (1) | RU2608422C2 (fr) |
WO (1) | WO2013079860A1 (fr) |
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US10508559B2 (en) | 2012-11-13 | 2019-12-17 | Safran Aircraft Engines | Monobloc preform and blade for turbo machine |
WO2014076408A1 (fr) * | 2012-11-13 | 2014-05-22 | Snecma | Preforme et aube monobloc pour turbomachine |
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CN105682903B (zh) * | 2013-10-23 | 2017-10-03 | 斯奈克玛 | 用于涡轮机空心叶片的纤维预成形件 |
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FR3035677A1 (fr) * | 2015-04-29 | 2016-11-04 | Snecma | Aube munie de plateformes possedant des portions d'accrochage |
US10619493B2 (en) | 2015-04-29 | 2020-04-14 | Safran Aircraft Engines | Blade equipped with platforms comprising a retaining leg |
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FR3035678A1 (fr) * | 2015-04-29 | 2016-11-04 | Snecma | Aube munie de plateformes possedant une jambe de retenue |
FR3035675A1 (fr) * | 2015-04-29 | 2016-11-04 | Snecma | Aube munie de plateformes comportant des inserts |
WO2016174346A1 (fr) * | 2015-04-29 | 2016-11-03 | Snecma | Aube munie de plateformes possedant une jambe de retenue. |
WO2016174343A1 (fr) * | 2015-04-29 | 2016-11-03 | Snecma | Aube munie de plateformes possedant un raidisseur |
US10519776B2 (en) | 2015-04-29 | 2019-12-31 | Safran Aircraft Engines | Blade comprising lands with a stiffener |
FR3035676A1 (fr) * | 2015-04-29 | 2016-11-04 | Snecma | Aube munie de plateformes possedant un raidisseur |
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WO2016174345A1 (fr) * | 2015-04-29 | 2016-11-03 | Snecma | Aube munie de plateformes comportant des inserts |
RU2699649C2 (ru) * | 2015-04-29 | 2019-09-06 | Сафран Эркрафт Энджинз | Лопатка, оснащенная полками, имеющими элемент жесткости |
FR3037097A1 (fr) * | 2015-06-03 | 2016-12-09 | Snecma | Aube composite comprenant une plateforme munie d'un raidisseur |
RU2717808C2 (ru) * | 2015-11-06 | 2020-03-25 | Сафран | Способ изготовления детали из композиционного материала, имеющей тело, составляющее одно целое с одной или более платформами |
FR3043355A1 (fr) * | 2015-11-06 | 2017-05-12 | Safran | Procede de fabrication d'une piece en materiau composite comprenant un corps solidaire d'une ou plusieurs plates-formes |
US10532521B2 (en) | 2015-11-06 | 2020-01-14 | Safran | Method of fabricating a composite material part having a body integral with one or more platforms |
WO2017077240A1 (fr) | 2015-11-06 | 2017-05-11 | Safran | Procede de fabrication d'une piece en materiau composite comprenant un corps solidaire d'une ou plusieurs plates-formes |
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US11141938B2 (en) | 2017-04-13 | 2021-10-12 | Safran | Method for manufacturing a composite material part comprising a body extended by a reinforced attachment end |
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FR3124106A1 (fr) * | 2021-06-17 | 2022-12-23 | Safran Aircraft Engines | Préforme fibreuse avec zone cousue d’amortissement des vibrations |
CN117597221A (zh) * | 2021-06-17 | 2024-02-23 | 赛峰飞机发动机公司 | 具有由单向纱线层形成的加强件的纤维预制件 |
FR3142929A1 (fr) * | 2021-06-17 | 2024-06-14 | Safran Aircraft Engines | Préforme fibreuse avec raidisseurs formés par des couches unidirectionnelles de fils |
WO2023156751A1 (fr) * | 2022-02-21 | 2023-08-24 | Safran Aircraft Engines | Systeme de fixation d'aube de turbomachine |
FR3132927A1 (fr) * | 2022-02-21 | 2023-08-25 | Safran Aircraft Engines | Préforme d’aube, aube et système de fixation d’aube de turbomachine |
Also Published As
Publication number | Publication date |
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JP2015500416A (ja) | 2015-01-05 |
US20150040396A1 (en) | 2015-02-12 |
FR2983428A1 (fr) | 2013-06-07 |
RU2608422C2 (ru) | 2017-01-18 |
CA2857453A1 (fr) | 2013-06-06 |
CA2857453C (fr) | 2019-07-02 |
EP2785520A1 (fr) | 2014-10-08 |
RU2014121516A (ru) | 2016-02-10 |
EP2785520B1 (fr) | 2016-03-30 |
CN103974824A (zh) | 2014-08-06 |
JP5973589B2 (ja) | 2016-08-23 |
CN103974824B (zh) | 2016-08-24 |
FR2983428B1 (fr) | 2014-01-17 |
US9427834B2 (en) | 2016-08-30 |
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