FR3121853A1 - Improved pairing process of a metal leading edge and a composite blade body - Google Patents
Improved pairing process of a metal leading edge and a composite blade body Download PDFInfo
- Publication number
- FR3121853A1 FR3121853A1 FR2104095A FR2104095A FR3121853A1 FR 3121853 A1 FR3121853 A1 FR 3121853A1 FR 2104095 A FR2104095 A FR 2104095A FR 2104095 A FR2104095 A FR 2104095A FR 3121853 A1 FR3121853 A1 FR 3121853A1
- Authority
- FR
- France
- Prior art keywords
- blade body
- leading edge
- metal
- conductive material
- leading portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000000034 method Methods 0.000 title claims abstract description 20
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 18
- 239000002184 metal Substances 0.000 title claims abstract description 18
- 239000002131 composite material Substances 0.000 title claims abstract description 11
- 239000004020 conductor Substances 0.000 claims abstract description 11
- 238000009760 electrical discharge machining Methods 0.000 claims description 5
- 238000003754 machining Methods 0.000 claims description 4
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 229910052802 copper Inorganic materials 0.000 claims description 2
- 239000010949 copper Substances 0.000 claims description 2
- 238000005304 joining Methods 0.000 claims description 2
- 239000007788 liquid Substances 0.000 claims description 2
- 238000005530 etching Methods 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 4
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 239000011166 3D woven composite Substances 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
-
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
-
- 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
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H1/00—Electrical discharge machining, i.e. removing metal with a series of rapidly recurring electrical discharges between an electrode and a workpiece in the presence of a fluid dielectric
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H3/00—Electrochemical machining, i.e. removing metal by passing current between an electrode and a workpiece in the presence of an electrolyte
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
- B23H9/10—Working turbine blades or nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/11—Manufacture by removing material by electrochemical methods
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/10—Manufacture by removing material
- F05D2230/12—Manufacture by removing material by spark erosion methods
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Composite Materials (AREA)
- Architecture (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Abstract
Procédé d’appairage amélioré d’un bord d’attaque métallique et d’un corps d’aube composite Procédé d’appairage d’un bord d’attaque métallique et d’un corps d’aube composite, dans lequel on fournit un corps d’aube (10) réalisé en matériau composite, comprenant une portion d’attaque, et on fournit un bord d’attaque (30) métallique présentant une face interne (32) et une face externe (34), adapté pour être solidarisé à la portion d’attaque du corps d’aube via sa face interne (32), on recouvre la portion d’attaque du corps d’aube (10) d’un matériau conducteur (20), on usine une face interne du bord d’attaque métallique par électroérosion par enfonçage du corps d’aube (10) dans le bord d’attaque (30), le corps d’aube (10) étant relié à une source de courant pour former une électrode du procédé d’électroérosion. Figure pour l’abrégé : Fig. 2.Method for improved pairing of a metal leading edge and a composite blade body Method of pairing a metal leading edge and a composite blade body, in which a body is provided blade (10) made of composite material, comprising a leading portion, and a metal leading edge (30) is provided having an internal face (32) and an external face (34), adapted to be secured to the leading portion of the blade body via its inner face (32), the leading portion of the blade body (10) is covered with a conductive material (20), an inner face of the edge is machined electroerosion metal etching by sinking the blade body (10) into the leading edge (30), the blade body (10) being connected to a current source to form an electrode of the electroerosion process. Figure for abstract: Fig. 2.
Description
Le présent exposé concerne la réalisation d’aubages composites, comprenant un bord d’attaque rapporté.This presentation concerns the production of composite blading, comprising an added leading edge.
Le présent exposé concerne notamment la réalisation d’aubages pour un compresseur basse pression de turbomachine. Les aubages sont communément réalisés en matériaux composites tissés en 3D, en injectant une résine époxy, par un procédé d’injection par transfert de résine, dans une préforme de fibre de carbone tissée 3D. Un renfort métallique, sous la forme d’un bord d’attaque pouvant par exemple réalisé en Titane, est ensuite collé sur la partie de l’aubage formant le bord d’attaque de la pale composite.This presentation relates in particular to the production of blading for a low-pressure turbomachine compressor. The blades are commonly made of 3D woven composite materials, by injecting an epoxy resin, by a resin transfer injection process, into a 3D woven carbon fiber preform. A metal reinforcement, in the form of a leading edge which can for example be made of titanium, is then bonded to the part of the blade forming the leading edge of the composite blade.
En pratique, les aubages composite ainsi réalisés présentent de nombreuses non-conformités à la fois sur la pièce intermédiaire de fabrication qu’est le bord d’attaque en titane, mais également aussi à la pièce d’entrée de montage lorsque le bord d’attaque est assemblé par collage, ce qui induit un surcoût qualité pour une pièce ayant déjà un coût important par rapport au coût total d’une aube.In practice, the composite blades thus produced have numerous non-conformities both on the intermediate manufacturing part which is the titanium leading edge, but also also on the assembly entry part when the edge of the attack is assembled by gluing, which induces an additional quality cost for a part that already has a high cost compared to the total cost of a blade.
La réalisation de tels aubages pose donc une double problématique, à savoir la difficulté à produire suffisamment de pièces conformes mais également à réduire le coût des pièces et à assurer la robustesse de la gamme.The production of such blades therefore poses a double problem, namely the difficulty of producing enough compliant parts but also of reducing the cost of the parts and ensuring the robustness of the range.
Afin de répondre au moins partiellement à cette problématique, le présent exposé concerne un procédé d’appairage d’un bord d’attaque métallique et d’un corps d’aube composite, dans lequel
- on fournit un corps d’aube réalisé en matériau composite, comprenant une portion d’attaque, et on fournit un bord d’attaque métallique présentant une face interne et une face externe, adapté pour être solidarisé à la portion d’attaque du corps d’aube via sa face interne,
- on recouvre la portion d’attaque du corps d’aube d’un matériau conducteur,
- on usine une face interne du bord d’attaque métallique par électroérosion par enfonçage du corps d’aube dans le bord d’attaque, le corps d’aube étant relié à une source de courant pour former une électrode du procédé d’électroérosion.In order to at least partially respond to this problem, the present presentation concerns a method for pairing a metal leading edge and a composite blade body, in which
- a blade body made of composite material is provided, comprising a leading portion, and a metal leading edge is provided having an inner face and an outer face, adapted to be secured to the leading portion of the body dawn via its internal face,
- the leading portion of the blade body is covered with a conductive material,
- An inner face of the metal leading edge is machined by spark erosion by sinking the blade body into the leading edge, the blade body being connected to a current source to form an electrode of the spark erosion process.
Selon un exemple, le procédé comprend une étape ultérieure de solidarisation du bord d’attaque métallique sur le corps d’aube.According to one example, the method comprises a subsequent step of joining the metal leading edge to the blade body.
Selon un exemple, la portion d’attaque du corps d’aube est recouverte d’une couche uniforme de matériau conducteur, ayant typiquement une épaisseur constante ou sensiblement constante.According to one example, the leading portion of the blade body is covered with a uniform layer of conductive material, typically having a constant or substantially constant thickness.
Selon un exemple, le matériau conducteur est du carbone ou du cuivre.According to one example, the conductive material is carbon or copper.
Selon un exemple, l’électroérosion est réalisée en plongeant le bord d’attaque métallique et le corps d’aube dans un bain de liquide diélectrique et en appliquant un courant électrique au matériau conducteur à la surface du corps d’aube.In one example, EDM is performed by immersing the metallic leading edge and the blade body in a bath of dielectric liquid and applying an electric current to the conductive material on the surface of the blade body.
Selon un exemple, pour la réalisation de l’usinage par électroérosion, on positionne le corps d’aube en regard du bord d’attaque métallique, en maintenant une distance d’espacement non nulle entre le bord d’attaque métallique et le corps d’aube, puis on applique un courant électrique au matériau conducteur du corps d’aube, on rapproche le bord d’attaque métallique et le corps d’aube jusqu’à ce que le bord d’attaque métallique soit au contact du corps d’aube et recouvre la portion d’attaque du corps d’aube, et on stoppe alors l’application du courant électrique.According to one example, for carrying out the machining by electroerosion, the blade body is positioned facing the metal leading edge, while maintaining a non-zero spacing distance between the metal leading edge and the blade body. blade, then an electric current is applied to the conductive material of the blade body, the metallic leading edge and the blade body are brought together until the metallic leading edge is in contact with the blade body. blade and covers the leading portion of the blade body, and the application of the electric current is then stopped.
Selon un exemple, suite à l’étape d’usinage, on solidarise le bord d’attaque métallique à la portion d’attaque du corps d’aube.According to one example, following the machining step, the metal leading edge is secured to the leading portion of the blade body.
Selon un exemple, la solidarisation est réalisée par collage.According to one example, the connection is made by gluing.
L’invention et ses avantages seront mieux compris à la lecture de la description détaillée faite ci-après de différents modes de réalisation de l’invention donnés à titre d’exemples non limitatifs.The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given by way of non-limiting examples.
Sur l’ensemble des figures, les éléments en commun sont repérés par des références numériques identiques.In all the figures, the elements in common are identified by identical numerical references.
Claims (8)
- on fournit un corps d’aube (10) réalisé en matériau composite, comprenant une portion d’attaque, et on fournit un bord d’attaque (30) métallique présentant une face interne (32) et une face externe (34), adapté pour être solidarisé à la portion d’attaque du corps d’aube via sa face interne (32),
- on recouvre la portion d’attaque du corps d’aube (10) d’un matériau conducteur (20),
- on usine une face interne du bord d’attaque métallique par électroérosion par enfonçage du corps d’aube (10) dans le bord d’attaque (30), le corps d’aube (10) étant relié à une source de courant pour former une électrode du procédé d’électroérosion.Method for pairing a metallic leading edge and a composite blade body, in which
- a blade body (10) made of composite material is provided, comprising a leading portion, and a metal leading edge (30) is provided having an inner face (32) and an outer face (34), adapted to be secured to the leading portion of the blade body via its internal face (32),
- the leading portion of the blade body (10) is covered with a conductive material (20),
- an internal face of the metal leading edge is machined by spark erosion by sinking the blade body (10) into the leading edge (30), the blade body (10) being connected to a current source for forming an electrode of the spark erosion process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2104095A FR3121853B1 (en) | 2021-04-20 | 2021-04-20 | Improved method for pairing a metal leading edge and a composite blade body |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2104095A FR3121853B1 (en) | 2021-04-20 | 2021-04-20 | Improved method for pairing a metal leading edge and a composite blade body |
| FR2104095 | 2021-04-20 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR3121853A1 true FR3121853A1 (en) | 2022-10-21 |
| FR3121853B1 FR3121853B1 (en) | 2024-03-29 |
Family
ID=76523093
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR2104095A Active FR3121853B1 (en) | 2021-04-20 | 2021-04-20 | Improved method for pairing a metal leading edge and a composite blade body |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR3121853B1 (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160369635A1 (en) * | 2013-07-09 | 2016-12-22 | United Technologies Corporation | Plating a composite to enhance bonding of metallic components |
| WO2020127551A1 (en) * | 2018-12-21 | 2020-06-25 | Mecachrome France | Method for producing a metal reinforcement for a turbomachine blade |
| EP3110989B1 (en) * | 2014-02-25 | 2020-11-04 | Safran Aircraft Engines | Protective edge for a blade and method of manufacturing said edge |
| EP3574187B1 (en) * | 2017-01-30 | 2020-12-09 | Safran Aircraft Engines | Method for removing a metal element bonded to an element made of composite material |
-
2021
- 2021-04-20 FR FR2104095A patent/FR3121853B1/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160369635A1 (en) * | 2013-07-09 | 2016-12-22 | United Technologies Corporation | Plating a composite to enhance bonding of metallic components |
| EP3110989B1 (en) * | 2014-02-25 | 2020-11-04 | Safran Aircraft Engines | Protective edge for a blade and method of manufacturing said edge |
| EP3574187B1 (en) * | 2017-01-30 | 2020-12-09 | Safran Aircraft Engines | Method for removing a metal element bonded to an element made of composite material |
| WO2020127551A1 (en) * | 2018-12-21 | 2020-06-25 | Mecachrome France | Method for producing a metal reinforcement for a turbomachine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| FR3121853B1 (en) | 2024-03-29 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2077183B1 (en) | Composite flange with machined part | |
| EP0761978B1 (en) | Thermostructural composite material rotor, particularly of large diameter and its method of manufacturing | |
| EP2809503B1 (en) | Method for attaching a piece of equipment to a structure made from composite material | |
| EP2593254A1 (en) | Method for producing a solid part | |
| EP2271850B1 (en) | Method for assembling a piece of metal material to a piece of composite material | |
| FR2965498A1 (en) | PROCESS FOR PRODUCING A TURBOMACHINE METAL TURBINE REINFORCEMENT | |
| CA2788927C (en) | Method for repairing a flange of a housing | |
| FR2941886A1 (en) | FLEXIBLE MEMBRANE FOR PRODUCING PARTS IN COMPOSITE MATERIALS. | |
| FR3102378A1 (en) | Manufacturing process of a composite material blade with attached metal leading edge | |
| FR3121853A1 (en) | Improved pairing process of a metal leading edge and a composite blade body | |
| FR2962483A1 (en) | Method for realizing hollow metal reinforcement of e.g. leading edge of fan blade of turbomachine, involves chemically attacking fugitive insert to form internal cavity in massive part to obtain reinforcement of leading or trailing edge | |
| EP4028645A1 (en) | Attachment of an acoustic shroud to a housing shell for an aircraft turbine engine | |
| EP3574187B1 (en) | Method for removing a metal element bonded to an element made of composite material | |
| CA2801130C (en) | Fibrous structure forming a flange and a counter-flange | |
| WO2021123577A1 (en) | Method for manufacturing a composite turbomachine bladed disk (blisk) with ceramic reinforcement | |
| FR2687195A1 (en) | Fastener with countersunk head, such as a rivet, for joining together pieces of composite material equipped with electrically conductive coatings and structure obtained by this joining | |
| RU2761530C1 (en) | Method for producing cylindrical reinforced elements for manufacturing parts of a bladed disk of a gas turbine engine | |
| US20170149216A1 (en) | Corona ignition device and method for the production thereof | |
| EP4052890A1 (en) | Method of manufacturing a composite tank of pressurised fluid and tank | |
| FR2971319A1 (en) | Coating inner surface of barrel of aluminum alloy cylindrical casing of vehicle including motor by thermal projection, comprises providing a thermal projection of a coating on a layer of a barrel inserted to a cylindrical casing | |
| FR3130192A1 (en) | METHOD FOR MANUFACTURING A BLADED PART FOR AN AIRCRAFT TURBOMACHINE | |
| EP0767026A1 (en) | Electrochemical machining process | |
| FR3045736B1 (en) | HYDRAULIC DEVICE COMPRISING A CERAMIC COATING | |
| CN114025439A (en) | Reflecting cover for welding silicon core and preparation method | |
| CH719680A2 (en) | Process for modifying the surface condition of a part by ion bombardment. |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PLFP | Fee payment |
Year of fee payment: 2 |
|
| PLSC | Publication of the preliminary search report |
Effective date: 20221021 |
|
| PLFP | Fee payment |
Year of fee payment: 3 |
|
| PLFP | Fee payment |
Year of fee payment: 4 |