EP4251855A1 - Procédé et dispositif de fabrication d'un disque de turbomachine bi-matière et disque obtenu par ce procédé - Google Patents
Procédé et dispositif de fabrication d'un disque de turbomachine bi-matière et disque obtenu par ce procédéInfo
- Publication number
- EP4251855A1 EP4251855A1 EP21820670.4A EP21820670A EP4251855A1 EP 4251855 A1 EP4251855 A1 EP 4251855A1 EP 21820670 A EP21820670 A EP 21820670A EP 4251855 A1 EP4251855 A1 EP 4251855A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- disc
- rough bore
- manufacturing
- turbomachine
- bore
- 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.)
- Pending
Links
- 239000000463 material Substances 0.000 title claims abstract description 128
- 238000000034 method Methods 0.000 title claims abstract description 39
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 26
- 238000007711 solidification Methods 0.000 claims abstract description 18
- 230000008023 solidification Effects 0.000 claims abstract description 18
- 238000003754 machining Methods 0.000 claims abstract description 8
- 238000005507 spraying Methods 0.000 claims abstract description 6
- 239000000843 powder Substances 0.000 claims description 16
- 239000013078 crystal Substances 0.000 claims description 10
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 8
- 238000010438 heat treatment Methods 0.000 claims description 7
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 230000008018 melting Effects 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 description 7
- 239000000956 alloy Substances 0.000 description 7
- 239000011324 bead Substances 0.000 description 7
- 238000001816 cooling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 1
- 239000010779 crude oil Substances 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011343 solid material Substances 0.000 description 1
- 239000007921 spray 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
- F01D5/02—Blade-carrying members, e.g. rotors
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/18—After-treatment
-
- 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
- F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
-
- 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
- F05D2220/32—Application in turbines in gas turbines
-
- 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
-
- 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
- F05D2230/20—Manufacture essentially without removing material
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/22—Manufacture essentially without removing material by sintering
-
- 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
- F05D2230/30—Manufacture with deposition of material
-
- 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
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
- F05D2230/313—Layer deposition by physical vapour deposition
-
- 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
-
- 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
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
-
- 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
- F05D2300/17—Alloys
- F05D2300/177—Ni - Si alloys
Definitions
- TITLE Process and device for manufacturing a bi-material turbomachine disc and disc obtained by this process
- the present invention relates to a method of manufacturing a bi-material turbomachine disc, the central zone of which is made of a first material and the circumference zone is made of a second material.
- the invention also relates to a manufacturing device implementing this process and a bi-material disk obtained by this process.
- the invention finds applications in the field of aeronautics and, in particular, in the field of the manufacture of turbine or turbomachine compressor discs.
- turbomachine disks in a single-crystal or directional solidification material which has the advantage of being more resistant to high temperatures than conventional equiaxed alloys and, in particular, of being resistant in creep.
- monocrystalline discs would exhibit anisotropic material properties.
- the applicant proposes a method for manufacturing a bi-material turbomachine disc, the central zone of which is produced in a first fatigue-resistant material and the circumferential zone is made of a second creep-resistant material with a columnar or monocrystalline solidification structure.
- the invention relates to a method for manufacturing a bi-material turbomachine disk, comprising the following operations: supplying a rough bore made of a first material, mounting the rough bore around an axis of rotation of a rotating device, rotating the rough bore, projecting a second material under solidification conditions generating a columnar or monocrystalline microstructure, different from the first material, onto an outer surface of the rough boring to obtain a bi-material part, and machining the bi-material part to obtain a turbomachine disc.
- This manufacturing method makes it possible to form, around a rough bore in conventional material, a circumferential zone in a material with high resistance to high temperatures, the rough bore subjected to a relatively low temperature being resistant to fatigue and the circumferential zone subjected to high temperatures being resistant to creep.
- the disk manufacturing method may have one or more additional characteristics among the following, considered individually or according to all technically possible combinations :
- the second material is a nickel-based monocrystalline material in powder form.
- the projection operation includes laser projection of the monocrystalline material by making at least one hole in the outer surface of the rough bore, inserting a seed of monocrystalline material therein and melting said seed in order to orient the crystal formed.
- the second material is a directed solidification material in powder form.
- the rough bore has a circular section.
- the second material is projected by a projection device in a direction perpendicular to a tangent to the outer surface of the rough bore.
- a junction between the rough bore and the second material is located in an intermediate zone between a central bore of the disc and a rim of said disc. after machining the bi-material disc, said disc is subjected to a hot isostatic compression treatment.
- Another aspect of the invention relates to a device for manufacturing a bi-material turbomachine disc comprising a spraying device, provided with a second material spraying nozzle and controlled by a control device, said device manufacturing being characterized in that it implements the method as defined above.
- the spray nozzle of this device is oriented perpendicular to a tangent to the outer surface of the rough bore.
- a two-material turbomachine disc characterized in that it is obtained by the process as defined above, said disc comprising a central zone formed in the first material and a circumferential zone formed in the second material and in which the grains or crystals of the second material are oriented in a radial direction.
- Figure 1 shows, in the form of a functional diagram, different operations of an embodiment of the manufacturing method according to the invention
- FIG. 2 represents a schematic view of a device for manufacturing a turbomachine disc according to one embodiment of the invention
- Figure 3 shows a perspective view of an example of a turbomachine disk made with the method of Figure 1;
- Figure 4 shows a perspective view of an example of bladed disc made with the method of Figure 1.
- FIG. 1 An example of an embodiment of the method 100 for manufacturing a bi-material turbomachine disc according to the invention is shown in Figure 1.
- This method 100 consists in applying, by means of a device of projection 200, an example of which is shown in Figure 2, a material with high creep resistance 340 on the circumference 350 of a rough bore 320.
- the rough bore 320 is a part, for example of circular section, produced using a traditional technique, in a metallic material or a conventional alloy usually used in the field of turbomachine discs.
- This material, called first material can for example be inco718®, R65®, TAD730®, N18®, or any other alloy for forged discs conventionally used in the field of manufacturing turbine engine discs.
- This rough bore 320 can be a new part intended to be transformed into a disc by the method according to the invention; as a variant, this rough bore 320 can be a turbomachine disk, the damaged circumference of which is reconstituted by applying a creep-resistant material according to the method of the invention.
- the method 100 includes a step 110 of supplying the rough bore and choosing the material to be projected on the circumference of said rough bore 320.
- This material can be, for example , a nickel-based monocrystalline material, a ceramic or a directed solidification material.
- a monocrystalline material is a solid material, for example a metal or an alloy, consisting of a single crystal, formed from a single seed, or crystal.
- a material with directed solidification is a metal or an alloy whose crystals extend, during the solidification phase, along a predefined direction.
- the term “second material” will be used to speak indiscriminately of monocrystalline material or material with directed solidification, given that these two materials have improved creep properties compared to the first material in which the crude is formed. bore.
- the second material is applied layer by layer on the circumference of the rough bore 320.
- the rough bore 320 is mounted around an axis of rotation 360 of a rotating device (Step 120 of Figure 1) and driven in rotation (Step 130 of Figure 1) by said rotating device, as represented by the arrow R in Figure 2.
- the axis of rotation 360 is an axis parallel to the axis transverse passing through the center of the disc.
- a projection device 200 projects the second material onto the periphery, or circumference, of said rough bore at a predetermined speed to allow the deposition of a layer of a predetermined thickness around the circumference of said rough bore.
- This projection step 140 of the second material 240 is carried out by means of a device for projection 200 such as that represented in FIG. 2.
- This projection device 200 can be, for example, a laser device 210, equipped with a nozzle 230 ensuring the projection of the second material with a chosen orientation.
- the laser device 210 is connected to a control device 220 which ensures the command and control of the parameters of the laser device 210, such as the speed, the flow rate and/or the heating temperature of the second material.
- the laser device 210 can be, for example, the laser device described in patent application FR 2 874 624 or any other laser device suitable for projecting a material in a chosen direction.
- the rough bore 320 is driven in a continuous rotational movement, at a predetermined speed and adapted to the flow of the second material exiting the nozzle 230 of the projection device.
- the second material whether monocrystalline or directed solidification, is in the form of a homogeneous powder 240, projected in the direction of the circumference of the rough bore 320, in the same axis AA as the laser beam 212.
- This powder 240 is melted by the laser beam and is transformed, in contact with the heated rough bore 320, into a fluid bead 340.
- Several thicknesses of the bead 340 can be applied on top of each other and/or next to each other. others to form a uniform layer on the circumference, or outer surface, of the rough bore 320.
- the bead 340 has a thickness determined according to the parameters of the projection device and the second material; this thickness may, for example, be of the order of 1 mm.
- the powder 240 of the second material is transformed into a bead 340 in contact with the rough bore 320.
- the rough bore 320 is heated by a heating device, not visible on the figures, positioned close to said rough bore.
- This heating device may be, for example, a heating plate mounted inside the rough bore or in the immediate vicinity of part of the outer surface of the rough bore receiving the powder, that is to say substantially to the right of the nozzle 230.
- the heating device can be associated with one or more heat control devices, such as for example a thermal sensor, a thermal camera, a pyrometer, etc., so that the heating device can be thermally enslaved.
- the powder 240 of second material is transformed into a fluid bead 340 capable of adhering to the circumferential zone of said rough bore 320.
- the zone of circumference of the rough bore thus increases little by little, in thickness and/or in width, with each new layer of bead 340.
- the powder 240 is a powder of the selected monocrystalline material.
- a seed (piece of single crystal material oriented in the desired direction) is placed (into a hole, in the outer surface of the rough bore, where it is re-melted by the laser during the projection of the powder of the monocrystalline material.
- the monocrystalline material has different mechanical properties depending on the angle, the process makes it possible to generate a curved monocrystal, that is to say with a weak local disorientation, which allows to have the main axis of the monocrystal oriented along the radius of the disc
- the circumferential zone 350 in monocrystalline material is therefore a zone with high resistance to high temperatures and, in particular, to creep.
- the powder 240 is a powder of a material with directed solidification such as, for example, the DS200 alloy.
- the directed solidification material is projected by the projection device, for example a laser device, onto the outer surface of the rough bore where it is transformed into a bead 340.
- the directed solidification material is a anisotropic material whose properties are not the same in all directions. However, the properties of this material in an axial/tangential plane (AA-Tg), that is to say in the direction of the grains of the material and therefore the direction of solidification, are relatively close to those of crude oil. bore.
- the creep resistance properties of the directional solidification material are better than with a conventional equiaxed material and the connection between the rough bore 320 and the zone 350 of circumference in material with directed solidification is greater than that obtained with a monocrystalline material.
- the powder 240 is projected onto the rough bore 320 with a predefined orientation. As shown in Figure 2, the powder 240 is projected along a direction AA, perpendicular to the tangent Tg of the circumference of the rough bore 320.
- the projection of the second material along this direction AA makes it possible to position each grain or crystal of the material along a radial direction of the disk.
- each grain of the second material is deposited along a radius r of the disc so that the area of circumference 350 of the crude bore becomes a zone with optimum creep properties, the central zone of the disc retaining the optimum fatigue properties of conventional materials.
- the disc 300 manufactured according to the method of the invention thus has a temperature gradient extending from the center of the disc towards the circumference of said disc, the grains or crystals of the circumference zone being arranged in the same direction as this temperature gradient.
- a bi-material part is obtained according to any one of the embodiments of the process described above, this part can be machined (step 150 of FIG. 1) in order to obtain a turbomachine disk.
- the part obtained is a bi-material part comprising a central zone in first material and a circumference zone in second material.
- This part can then be machined, like any turbomachine disc, by any known machining technique.
- the disc obtained can be a disc 300 equipped with a blade attachment system, as shown in Figure 3, or a one-piece bladed disc 400, as shown in Figure 4.
- the disc and the blades can be machined in the bi-material part so that the blades, which are the elements most subject to high temperatures, are also made of the second material.
- This type of machining saves mass, not only at the level of the blades, but also at the level of the disc since the mass to be carried is less. It also eliminates the need for mechanical connections between the blades and the disc.
- the disc 300, 400 obtained at the end of the machining step 150 can, like any turbomachine disc, undergo a treatment intended to improve or optimize its intrinsic properties.
- the disk 300, 400 can undergo a Hot Isostatic Compression treatment (more simply called CIC treatment) to remove any porosities on the surface of the disk and thus optimize the properties of the first and second materials. .
- the disc obtained with the method according to the invention consists of two distinct materials forming several areas of the disc: a central zone 351, corresponding at least in part to the rough bore, located in the vicinity of the transverse axis BB of the disc and formed in one of the first materials usually used for the manufacture of turbomachine discs; a rim 352 formed by the circumferential zone of second material; and a fabric 354, or intermediate zone, located between the rim 352 and the central zone 251 .
- the bore is the part least exposed to high temperatures, unlike the rim - and even more so the blades - which are parts very exposed to high temperatures.
- the rim can be exposed to a maximum temperature of 750°C while the blade can be exposed to a maximum temperature of 1150°C.
- the central zone 351 is the least hot part of the disc, it can be formed from a conventional material and thus has good fatigue strength.
- the rim 352 being the part of the disc most exposed to high temperatures, it is advantageous for it to be made of a second material.
- the junction 353 between the first material and the second material can, for example, be housed in the canvas 354, as shown in FIG. 3, since the canvas 354 is the part of the disc that is less stressed mechanically. Indeed, the junction between the two materials being a weak point of the structure, it is preferable to place it in an area that is not very stressed by the loads, such as the fabric for example.
- the method of manufacturing a bi-material disc according to the invention comprises various variants, modifications and improvements which will become evident in skilled in the art, it being understood that these variants, modifications and improvements fall within the scope of the invention.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Metallurgy (AREA)
- Plasma & Fusion (AREA)
- Physics & Mathematics (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Organic Chemistry (AREA)
- Ceramic Engineering (AREA)
- Powder Metallurgy (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2012106A FR3116561B1 (fr) | 2020-11-25 | 2020-11-25 | Procédé et dispositif de fabrication d’un disque de turbomachine bi-matière et disque obtenu par ce procédé |
PCT/FR2021/052022 WO2022112684A1 (fr) | 2020-11-25 | 2021-11-16 | Procédé et dispositif de fabrication d'un disque de turbomachine bi-matière et disque obtenu par ce procédé |
Publications (1)
Publication Number | Publication Date |
---|---|
EP4251855A1 true EP4251855A1 (fr) | 2023-10-04 |
Family
ID=74668988
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP21820670.4A Pending EP4251855A1 (fr) | 2020-11-25 | 2021-11-16 | Procédé et dispositif de fabrication d'un disque de turbomachine bi-matière et disque obtenu par ce procédé |
Country Status (5)
Country | Link |
---|---|
US (1) | US20240003257A1 (fr) |
EP (1) | EP4251855A1 (fr) |
CN (1) | CN116490674A (fr) |
FR (1) | FR3116561B1 (fr) |
WO (1) | WO2022112684A1 (fr) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4436485A (en) * | 1978-04-17 | 1984-03-13 | General Motors Corporation | Turbine wheel with integral DS blades and equiaxed hub |
GB9325135D0 (en) * | 1993-12-08 | 1994-02-09 | Rolls Royce Plc | Manufacture of wear resistant components |
FR2874624B1 (fr) | 2004-08-30 | 2007-04-20 | Snecma Moteurs Sa | Procede de rechargement d'une piece metallique monocristalline ou a solidification dirigee. |
US20100078308A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Process for depositing a coating on a blisk |
US20180104765A1 (en) * | 2016-10-13 | 2018-04-19 | United Technologies Corporation | Hybrid component and method of making |
-
2020
- 2020-11-25 FR FR2012106A patent/FR3116561B1/fr active Active
-
2021
- 2021-11-16 CN CN202180079199.XA patent/CN116490674A/zh active Pending
- 2021-11-16 WO PCT/FR2021/052022 patent/WO2022112684A1/fr active Application Filing
- 2021-11-16 US US18/253,510 patent/US20240003257A1/en active Pending
- 2021-11-16 EP EP21820670.4A patent/EP4251855A1/fr active Pending
Also Published As
Publication number | Publication date |
---|---|
FR3116561A1 (fr) | 2022-05-27 |
CN116490674A (zh) | 2023-07-25 |
FR3116561B1 (fr) | 2023-09-22 |
WO2022112684A1 (fr) | 2022-06-02 |
US20240003257A1 (en) | 2024-01-04 |
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