WO2012045980A1 - Procède de réalisation d'un renfort métallique d'aube de turbomachine - Google Patents
Procède de réalisation d'un renfort métallique d'aube de turbomachine Download PDFInfo
- Publication number
- WO2012045980A1 WO2012045980A1 PCT/FR2011/052324 FR2011052324W WO2012045980A1 WO 2012045980 A1 WO2012045980 A1 WO 2012045980A1 FR 2011052324 W FR2011052324 W FR 2011052324W WO 2012045980 A1 WO2012045980 A1 WO 2012045980A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- metal
- reinforcement
- leading edge
- trailing edge
- producing
- Prior art date
Links
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 146
- 239000002184 metal Substances 0.000 title claims abstract description 146
- 230000002787 reinforcement Effects 0.000 title claims abstract description 95
- 238000004519 manufacturing process Methods 0.000 title abstract description 23
- 239000011888 foil Substances 0.000 claims abstract description 45
- 238000000034 method Methods 0.000 claims abstract description 32
- 238000001513 hot isostatic pressing Methods 0.000 claims abstract description 10
- 238000005520 cutting process Methods 0.000 claims description 15
- 238000003466 welding Methods 0.000 claims description 15
- 239000007787 solid Substances 0.000 claims description 7
- 238000011161 development Methods 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 4
- 238000003780 insertion Methods 0.000 claims description 3
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- 238000004026 adhesive bonding Methods 0.000 claims description 2
- 238000005054 agglomeration Methods 0.000 claims description 2
- 230000002776 aggregation Effects 0.000 claims description 2
- 238000010348 incorporation Methods 0.000 claims 1
- 239000000463 material Substances 0.000 description 17
- 239000002131 composite material Substances 0.000 description 10
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 8
- 239000010936 titanium Substances 0.000 description 8
- 229910052719 titanium Inorganic materials 0.000 description 8
- 239000013043 chemical agent Substances 0.000 description 6
- 238000000462 isostatic pressing Methods 0.000 description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 6
- 238000009792 diffusion process Methods 0.000 description 3
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- 239000012535 impurity Substances 0.000 description 3
- 238000003754 machining Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 238000003486 chemical etching Methods 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000007598 dipping method Methods 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 238000003801 milling Methods 0.000 description 2
- 239000010453 quartz Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 2
- 229910010271 silicon carbide Inorganic materials 0.000 description 2
- 239000000377 silicon dioxide Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000005238 degreasing Methods 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 238000004090 dissolution Methods 0.000 description 1
- 229920006335 epoxy glue Polymers 0.000 description 1
- 238000005530 etching Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000009659 non-destructive testing Methods 0.000 description 1
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K3/00—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like
- B21K3/04—Making engine or like machine parts not covered by sub-groups of B21K1/00; Making propellers or the like blades, e.g. for turbines; Upsetting of blade roots
-
- 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
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D53/00—Making other particular articles
- B21D53/78—Making other particular articles propeller blades; turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
- B22F3/15—Hot isostatic pressing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/021—Isostatic pressure welding
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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
-
- 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
- F01D5/005—Repairing methods or devices
-
- 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
- F01D5/14—Form or construction
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
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- F04D29/388—Blades characterised by construction
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—Turbines
-
- 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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
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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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
-
- 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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/4805—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the type of adhesives
- B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
- B29C65/484—Moisture curing adhesives
-
- 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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
- B29C66/124—Tongue and groove joints
- B29C66/1246—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove
- B29C66/12461—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being rounded, i.e. U-shaped or C-shaped
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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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
- B29C66/12—Joint cross-sections combining only two joint-segments; Tongue and groove joints; Tenon and mortise joints; Stepped joint cross-sections
- B29C66/124—Tongue and groove joints
- B29C66/1246—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove
- B29C66/12463—Tongue and groove joints characterised by the female part, i.e. the part comprising the groove being tapered
-
- 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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/01—General aspects dealing with the joint area or with the area to be joined
- B29C66/05—Particular design of joint configurations
- B29C66/301—Three-dimensional joints, i.e. the joined area being substantially non-flat
-
- 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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/53—Joining single elements to tubular articles, hollow articles or bars
-
- 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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
- B29C66/721—Fibre-reinforced materials
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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
- B29C66/00—General aspects of processes or apparatus for joining preformed parts
- B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
- B29C66/74—Joining plastics material to non-plastics material
- B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
-
- 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
- B29L2031/082—Blades, e.g. for helicopters
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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
- F01D5/288—Protective coatings for blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
-
- 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
- F05D2300/70—Treatment or modification of materials
- F05D2300/702—Reinforcement
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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
Definitions
- the present invention relates to a method for producing a metallic blade reinforcement composite or metal turbomachine.
- the invention relates to a method for producing a turbomachine blade leading edge metal reinforcement.
- the field of the invention is that of turbomachines and more particularly that of the fan blades, made of composite or metallic material, of a turbomachine and whose leading edge comprises a metallic structural reinforcement.
- the invention is also applicable to the production of a metal reinforcement intended to reinforce a leading edge or blade trailing edge of any type of turbomachine, terrestrial or aeronautical, and in particular a helicopter turbine engine or an airplane turbojet engine but also propellers such as propellers of double blowers contrarotative unducted (“open rotor" in English).
- leading edge corresponds to the front part of an airfoil which faces the airflow and which divides the airflow into an intrados airflow and a flow of air. extrados air.
- the trailing edge corresponds to the posterior part of an aerodynamic profile where the intrados and extrados flows meet.
- the turbomachine blades and in particular the fan blades, undergo significant mechanical stress, particularly related to the speed of rotation, and must meet strict conditions of weight and bulk. Therefore, blades made of composite materials are used which are lighter.
- the metallic structural reinforcement protects the leading edge of the composite blade by avoiding risks of delamination, fiber breakage or damage by fiber / matrix decohesion.
- a turbomachine blade has an aerodynamic surface extending, in a first direction, between a leading edge and a trailing edge and, in a second direction substantially perpendicular to the first direction, between a foot and a dawn summit.
- the metallic structural reinforcement follows the shape of the leading edge of the aerodynamic surface of the blade and extends in the first direction beyond the leading edge of the aerodynamic surface of the blade to match the profile of the blade. the intrados and the upper surface of the dawn and in the second direction between the foot and the top of the dawn.
- the metallic structural reinforcement is a metal part made entirely by milling from a block of material.
- the invention aims to solve the problems mentioned above by proposing a method for producing a leading edge metal reinforcement or turbomachine blade trailing edge making it possible to simplify the production range of the machine. such a piece while reducing the costs of realization.
- the invention proposes a method for producing a leading edge metal reinforcement or a turbomachine blade trailing edge. comprising successively:
- each metal pocket being made from two metal foils cut in the previous step
- foil corresponding substantially to the development of said reinforcement means a foil whose general shape is close to the shape of the developed reinforcement but the dimensions of the foil are not necessarily the final dimensions of the reinforcement.
- the metallic structural reinforcement is produced in a simple and fast manner from a stack of thin metal bags of small thickness forming the preform of the metal reinforcement and a hot isostatic pressing or compaction process ( HIP for Hot Isostatic Pressing in English) to obtain a compact piece without porosity by the combination of plastic deformation, creep and diffusion welding.
- HIP Hot Isostatic Pressing in English
- the metal pockets are made by cutting foils, whose geometry corresponds to the development of the metal reinforcement, from at least one sheet or a thin metal strip, the foils being secured so as to make a pocket easy to slide or assemble by insertion on a template or in a form tool.
- This production method thus makes it possible to dispense with the complex realization of the blade reinforcement by machining in the mass, such as milling, broaching, from flats requiring large volume of processing material and consequently costs. important in raw material supply.
- the method also makes it easy to produce metal reinforcements that meet strict requirements of mass and / or geometric.
- the method for producing a turbomachine blade metal reinforcement according to the invention may also have one or more of the following characteristics, considered individually or in any technically possible combination:
- said step of making a plurality of metal pockets is carried out by superposing two distinct metal foils and then assembling at least one edge of said two metal foils by connecting means;
- step of making a plurality of metal pockets is made by folding a junction area between two metal foils and then assembling at least one edge of said two metal foils by connecting means;
- Said connecting means of said step of making a plurality of metal bags are bonding means and / or welding means;
- said welding means are spot welding means
- said cutting step is carried out in at least one metal sheet having a thickness of between 0.1 mm and 0.3 mm;
- said stacking step comprises a sub-step of incorporating an insert between two successive metal bags; said sub-step of incorporating an insert is a step of insertion of a solid metal insert, or woven or a fugitive insert capable of being dissolved by a chemical attack;
- said step of interlocking each of said metal pockets is carried out by stacking said metal pockets by means of a shape template;
- said stacking step by interlocking each of the metal pockets is carried out by stacking said metal pockets in an impression or on a counter-impression of a hot isostatic pressing tool.
- FIG. 1 is a side view of a blade having a hollow metal structural reinforcement leading edge obtained by means of the embodiment of the invention
- Figure 2 is a partial sectional view of Figure 1 along a cutting plane AA;
- FIG. 3 is a block diagram showing the main steps for producing a turbomachine blade leading edge metallic structural reinforcement of the embodiment method according to the invention
- FIG. 4 illustrates a side view of the turbomachine blade leading edge metal reinforcement during the first step of the process illustrated in FIG. 3;
- FIG. 5 illustrates a side view of a second example of turbomachine blade leading edge metal reinforcement during the first step of the process illustrated in FIG. 3;
- FIG. 6 illustrates a perspective view of the turbomachine blade leading edge metal reinforcement during the second step of FIG. process illustrated in Figure 3;
- FIG. 7 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement during the third step of the process illustrated in FIG. 3;
- FIG. 8 illustrates a sectional view of the turbomachine blade leading edge metal reinforcement during the fourth step of the process illustrated in FIG. 3.
- metal reinforcement of leading edge or trailing edge will be indifferently named metal reinforcement or reinforcement.
- FIG. 1 is a side view of a blade comprising a metallic leading edge structural reinforcement obtained by means of the embodiment method according to the invention.
- the blade 10 illustrated is for example a mobile blade of a fan of a turbomachine (not shown).
- the blade 10 has an aerodynamic surface 12 extending in a first axial direction 14 between a leading edge 16 and a trailing edge 18 and in a second radial direction 20 substantially perpendicular to the first direction 14 between a foot 22 and a summit 24.
- the aerodynamic surface 12 forms the extrados face 13 and intrados 1 1 of the blade 10, only the extrados face 13 of the blade 10 is shown in Figure 1.
- the intrados 11 and the extrados 13 form the lateral faces of the blade 10 which connect the leading edge 16 to the trailing edge 18 of the blade 10.
- the blade 10 is a composite blade typically obtained by draping or shaping a woven fiber texture.
- the composite material used may be composed of an assembly of woven carbon fibers and a resinous matrix, the assembly being formed by molding using a resin injection molding method RTM (for "Resin Transfer Molding").
- the blade 10 has a metal structural reinforcement 30 bonded at its leading edge 16 and which extends both in the first direction 14 beyond the leading edge 16 of the aerodynamic surface 12 of the blade. dawn 10 and in the second direction 20 between the foot 22 and the apex 24 of the dawn.
- the structural reinforcement 30 matches the shape of the leading edge 16 of the aerodynamic surface 12 of the blade 10 that it extends to form a leading edge 31, said leading edge of the reinforcement .
- the structural reinforcement 30 is a one-piece piece having a substantially V-shaped section having a base 39 forming the leading edge 31 and extended by two lateral flanks 35 and 37 respectively fitting the intrados 11 and extrados 13 the aerodynamic surface 12 of the dawn.
- Flanks 35, 37 have a tapered or thinned profile towards the trailing edge of the blade.
- the base 39 of the structural reinforcement 30 also has an internal cavity 40 extending over the height of the structural reinforcement 30, from the foot to the top of the blade.
- the structural reinforcement 30 is metallic and preferably based on titanium. This material has indeed a high energy absorption capacity due to shocks.
- the reinforcement is glued on the blade 10 by means of adhesive known to those skilled in the art, such as a cyanoacrylic or epoxy glue.
- FIG. 2 illustrating the reinforcement 30 in its final state.
- FIG. 3 represents a block diagram illustrating the main steps of a method of producing a blade blade leading edge metal structural reinforcement 10 as illustrated in FIGS. 1 and 2.
- the first step 210 of the production method 200 is a step of cutting a plurality of flexible metal pieces 101, 101 ', 102, 102', subsequently called metal foils, from a metal sheet or from a metal sheet. thin metal foil made of titanium. Two examples of cutting foils are illustrated in Figures 4 and 5.
- the metal foils 101, 101 ', 102, 102', as illustrated in FIGS. 4 and 5, are cut by conventional means for cutting thin metal sheets, ie with a thickness of less than 0 , 3mm.
- the metal foils 101, 101 ', 102, 102' can be cut for example by die cutting means, shear cutting means, or by water jet, etc.
- the cut metal foils 101, 101 ', 102, 102' have a geometry corresponding substantially to the development of the blade leading edge metal brace 10, as illustrated in FIGS. 1 and 2.
- the metal foils 101 , 101 'and 102, 102' have a geometry substantially corresponding to the development of the intrados and extrados face of the metal reinforcement 30.
- the second step 220 of the production method 200 is a step of making metal bags 100, as shown in Figure 6, from the flexible metal foils 101, 101 ', 102, 102'.
- the pockets 100 are made by superimposing a first foil 101 corresponding to the geometry of the intrados face of the metal reinforcement 30 with a second foil 101' corresponding to the geometry of the extrados face of the metal reinforcement 30.
- the bonding of the two metal foils 101, 101 'in titanium can be achieved simply by heating two metal foils 101, 101' superimposed under a weakly pressurized atmosphere.
- the weld at the edge 105 is made by known welding means for welding two thin titanium metal sheets.
- the two foils 101, 101 ' are joined by points 1 1 1 of welding by a method of electric spot welding.
- the two foils 102, 102', forming the intrados and extrados faces of the metal reinforcement 30, are held together at a junction zone 103 as well as possibly by two retaining tabs 104 on either side of the junction zone 103 thus ensuring stability of the metal foils after the cutting step 210 during the various handling operations.
- the making of the pocket 100 is made by folding the two foils 102, 102 'at the junction area 103 so as to superimpose the two foils 102, 102' on one another. During the folding operation, the two holding tabs 104 are removed for example by cutting means.
- 100 is made by making a bond, by a bonding process or a welding process, at least at the edges 105 of two foils 102, 102 'defining the profile of the leading edge of the reinforcement.
- the third step 230 is a step of producing a preform 1 10 metal reinforcement 30 by successively interlocking a plurality of pockets 100.
- the stack of the various pockets 100 is made on a shape template (not shown) so as to form the preform 1 10 of the metal reinforcement 30.
- the tool 400 comprises a cavity 410 (matrix) corresponding to the final external shape of the metal reinforcement 30 and a counterprint 420 (punch) corresponding to the final internal shape of the leading edge metal reinforcement.
- the stack of the various pockets 100 is made directly in the impression 410 or on the counter-impression 420.
- the pockets 100 are made from foils having different widths L so that the preform 1 10, formed by stacking the different pockets, meets the material thickness requirements necessary for the production of the final part (ie the metal reinforcement 30).
- the pockets 100 of different sizes also make it easy to carry out an easily transportable stack, in particular by successive stacking in order of decreasing size of the pockets 100 as illustrated in FIG. 7.
- the larger pocket forms the outer surface of the preform 1 10 in contact with the cavity 410 and the smaller pocket forms the inner surface of the preform 1 10 in contact with the the counterpart 420.
- the various pockets 100 of the preform are encompassed and maintained by the outer pocket of larger size.
- an insert may be inserted between two successive bags 100 so as to provide, for example, a greater thickness of material, a specific reinforcement made of a different material or to produce a hollow metal reinforcement.
- the insert may be a solid insert made by a forging, machining or casting process, or an insert woven by means of metal wires, for example with titanium wires and / or threads based on silicon carbide and titanium (SiC-Ti), and / or son coated boron (SiC-Boron), or silicon carbide (SiC-SiC).
- metal wires for example with titanium wires and / or threads based on silicon carbide and titanium (SiC-Ti), and / or son coated boron (SiC-Boron), or silicon carbide (SiC-SiC).
- the insert is a fugitive insert made of a material different from the material of metal foils 100.
- fugitive insert means an insert which is not intended to be permanent and which is only necessary for the realization of the leading edge hollow metal reinforcement.
- the fugitive insert is not present in the metal reinforcement in its final state and does not participate in any mechanical characteristics of the metal reinforcement.
- the fugitive insert is for example made of a material capable of withstanding a high temperature, of the order of 900 ° C., a high pressure, of the order of 1000 bar, and which is compatible with the materials of metal foils 100 so as not to create impurities or oxidation in the preform 1 10.
- the material of the fugitive insert must also be chemically etchable by dissolution using a chemical agent.
- the fugitive insert is made of copper, or quartz or silica.
- the shape of the fugitive insert incorporated in the stack of metal foils 100 is a function of the shape of the final internal cavity desired.
- the fourth step 240 of the production method 200 is a hot isostatic pressing (HIP) step of the preform in the tooling 400, illustrated in FIG. 8.
- HIP hot isostatic pressing
- Hot isostatic pressing is a widely used manufacturing process known to reduce the porosity of metals and affect the density of many metals, such as ceramics.
- the isostatic pressing process also makes it possible to improve the mechanical properties and the exploitability of the materials.
- Isostatic pressing is carried out at high temperature (conventionally between 400 ° C. and 1400 ° C., and of the order of 1000 ° C. for titanium) and at isostatic pressure.
- the application of the heat combined with the internal pressure eliminates the voids of the preform, as well as the microporosities by means of a combination of plastic deformation, creep, and diffusion welding so as to form a solid piece 430 .
- the massive piece 430 resulting from the isostatic pressing step comprises the internal and external profiles of the metal reinforcement 30.
- the solid piece 430 is then demolded from the tool 400.
- the isostatic pressing step is carried out under vacuum, advantageously under secondary vacuum or in a tool welded in wherein the secondary vacuum is achieved, either in autoclave bag, the choice of the method depending on the number of piece to produce.
- the secondary vacuum makes it possible to avoid the presence of oxygen in the tooling and at the level of the fibrous structure, during the titanium isostatic pressing step.
- Tooling 400 is made of a mechanical alloy called superalloy or high performance alloy.
- the isostatic pressing step 240 may previously comprise a step 235 for cleaning, degreasing and / or chemical etching of the various metal bags 100 so as to eliminate the residual impurities of the preform.
- the impurity cleaning step is carried out by dipping the fibrous assembly in a bath of cleaning agent or chemical agent.
- the method according to the invention may comprise an additional chemical etching step of the insert introduced during the step of stacking the various pockets and forming an integral part of the piece. massive 430.
- the chemical attack is performed by means of a chemical agent capable of attacking the material in which the insert is made.
- the chemical attack of the fugitive insert dissolves the fugitive insert so that the space released by the dissolved insert forms the internal cavity in the metal reinforcement.
- the etching step is carried out by dipping the solid piece 430 in a bath comprising the chemical agent capable of dissolving the insert.
- the chemical agent is for example an acid or a base.
- the chemical agent is capable of dissolving copper, quartz or silica.
- the method according to the invention may also include a finishing step and machining of the hollow solid piece obtained at the exit of the tooling so as to obtain the reinforcement 30.
- This recovery step comprises:
- this step consisting in particular of trimming the flanks 35, 37 and the thinning of the intrados and extrados flanks;
- the method according to the invention may also comprise non-destructive testing steps of the reinforcement 30 making it possible to ensure the geometrical and metallurgical conformity of the assembly obtained.
- the non-destructive tests can be carried out by an X-ray method.
- the invention has been particularly described for the realization of a metal reinforcement of a composite-turbomachine blade; however, the invention is also applicable for producing a metal reinforcement of a turbomachine metal blade.
- the invention has been particularly described for producing a metal reinforcement of a turbomachine blade leading edge; however, the invention is also applicable to the production of a metal reinforcement of a trailing edge of a turbomachine blade or to the production of a metallic helical reinforcement composite or metal.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Architecture (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Composite Materials (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/877,985 US9321100B2 (en) | 2010-10-05 | 2011-10-05 | Method for producing a metal reinforcement for a turbomachine blade |
GB1306141.1A GB2502428B (en) | 2010-10-05 | 2011-10-05 | Method for producing a metal reinforcement for a turbomachine blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1058078 | 2010-10-05 | ||
FR1058078A FR2965498B1 (fr) | 2010-10-05 | 2010-10-05 | Procede de realisation d?un renfort metallique d?aube de turbomachine. |
Publications (1)
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WO2012045980A1 true WO2012045980A1 (fr) | 2012-04-12 |
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PCT/FR2011/052324 WO2012045980A1 (fr) | 2010-10-05 | 2011-10-05 | Procède de réalisation d'un renfort métallique d'aube de turbomachine |
Country Status (4)
Country | Link |
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US (1) | US9321100B2 (fr) |
FR (1) | FR2965498B1 (fr) |
GB (1) | GB2502428B (fr) |
WO (1) | WO2012045980A1 (fr) |
Cited By (1)
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CN109483183A (zh) * | 2018-11-20 | 2019-03-19 | 上海交通大学 | 一种航空发动机复材风扇叶片金属加强边的制造方法 |
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FR2957545B1 (fr) * | 2010-03-19 | 2012-07-27 | Snecma | Procede de realisation d'un insert metallique pour la protection d'un bord d'attaque en materiau composite |
FR2970715B1 (fr) * | 2011-01-21 | 2014-10-17 | Snecma | Structure fibreuse tissee multicouches ayant une partie tubulaire creuse, procede de fabrication et piece composite la comportant |
US10458428B2 (en) * | 2013-09-09 | 2019-10-29 | United Technologies Corporation | Fan blades and manufacture methods |
US10487843B2 (en) * | 2013-09-09 | 2019-11-26 | United Technologies Corporation | Fan blades and manufacture methods |
FR3025735B1 (fr) * | 2014-09-17 | 2016-12-09 | Europe Tech | Procede de traitement d'une piece composite |
FR3040902B1 (fr) * | 2015-09-10 | 2017-09-01 | Snecma | Procede de fabrication d'un renfort de protection pour une aube (p) presentant un bord d'attaque ou de fuite courbe |
US11149558B2 (en) | 2018-10-16 | 2021-10-19 | General Electric Company | Frangible gas turbine engine airfoil with layup change |
US11434781B2 (en) | 2018-10-16 | 2022-09-06 | General Electric Company | Frangible gas turbine engine airfoil including an internal cavity |
US10837286B2 (en) | 2018-10-16 | 2020-11-17 | General Electric Company | Frangible gas turbine engine airfoil with chord reduction |
US10760428B2 (en) | 2018-10-16 | 2020-09-01 | General Electric Company | Frangible gas turbine engine airfoil |
US10746045B2 (en) | 2018-10-16 | 2020-08-18 | General Electric Company | Frangible gas turbine engine airfoil including a retaining member |
US11111815B2 (en) | 2018-10-16 | 2021-09-07 | General Electric Company | Frangible gas turbine engine airfoil with fusion cavities |
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- 2011-10-05 US US13/877,985 patent/US9321100B2/en active Active
- 2011-10-05 WO PCT/FR2011/052324 patent/WO2012045980A1/fr active Application Filing
- 2011-10-05 GB GB1306141.1A patent/GB2502428B/en active Active
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GB2168002A (en) * | 1984-12-06 | 1986-06-11 | Rolls Royce | Composite material manufacture |
US4738594A (en) * | 1986-02-05 | 1988-04-19 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Blades for axial fans |
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CN109483183B (zh) * | 2018-11-20 | 2020-08-25 | 上海交通大学 | 一种航空发动机复材风扇叶片金属加强边的制造方法 |
Also Published As
Publication number | Publication date |
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US20130219717A1 (en) | 2013-08-29 |
GB201306141D0 (en) | 2013-05-22 |
GB2502428B (en) | 2015-09-23 |
US9321100B2 (en) | 2016-04-26 |
FR2965498B1 (fr) | 2012-09-28 |
GB2502428A (en) | 2013-11-27 |
FR2965498A1 (fr) | 2012-04-06 |
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