EP3899081A1 - Procede de fabrication d'un noyau - Google Patents
Procede de fabrication d'un noyauInfo
- Publication number
- EP3899081A1 EP3899081A1 EP19848898.3A EP19848898A EP3899081A1 EP 3899081 A1 EP3899081 A1 EP 3899081A1 EP 19848898 A EP19848898 A EP 19848898A EP 3899081 A1 EP3899081 A1 EP 3899081A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- core
- layer
- chromium
- molybdenum
- cobalt
- 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 48
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 20
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 24
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 24
- 239000011651 chromium Substances 0.000 claims abstract description 24
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 23
- 239000000956 alloy Substances 0.000 claims abstract description 23
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 23
- 239000011733 molybdenum Substances 0.000 claims abstract description 23
- 238000007751 thermal spraying Methods 0.000 claims abstract description 16
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims abstract description 16
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 16
- 239000010937 tungsten Substances 0.000 claims abstract description 16
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 34
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 18
- 229910052799 carbon Inorganic materials 0.000 claims description 18
- 229910000531 Co alloy Inorganic materials 0.000 claims description 17
- 229910052759 nickel Inorganic materials 0.000 claims description 17
- 229910052710 silicon Inorganic materials 0.000 claims description 14
- 239000010703 silicon Substances 0.000 claims description 14
- 239000010941 cobalt Substances 0.000 claims description 12
- 229910017052 cobalt Inorganic materials 0.000 claims description 12
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 12
- 239000003570 air Substances 0.000 claims description 7
- 238000003754 machining Methods 0.000 claims description 7
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 4
- 239000012080 ambient air Substances 0.000 claims description 3
- 230000008021 deposition Effects 0.000 claims description 3
- 238000007669 thermal treatment Methods 0.000 claims description 3
- 239000000377 silicon dioxide Substances 0.000 claims description 2
- 239000011162 core material Substances 0.000 description 45
- 239000010410 layer Substances 0.000 description 27
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 7
- 239000010936 titanium Substances 0.000 description 7
- 229910052719 titanium Inorganic materials 0.000 description 7
- 239000000126 substance Substances 0.000 description 6
- 230000000930 thermomechanical effect Effects 0.000 description 6
- 230000004888 barrier function Effects 0.000 description 5
- 239000002131 composite material Substances 0.000 description 5
- 238000011109 contamination Methods 0.000 description 5
- 238000009792 diffusion process Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 5
- 229910052752 metalloid Inorganic materials 0.000 description 4
- 150000002738 metalloids Chemical class 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005056 compaction Methods 0.000 description 2
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 0.000 description 2
- 238000010286 high velocity air fuel Methods 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 238000005121 nitriding Methods 0.000 description 2
- 230000035515 penetration Effects 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 229910052787 antimony Inorganic materials 0.000 description 1
- WATWJIUSRGPENY-UHFFFAOYSA-N antimony atom Chemical compound [Sb] WATWJIUSRGPENY-UHFFFAOYSA-N 0.000 description 1
- 229910052785 arsenic Inorganic materials 0.000 description 1
- RQNWIZPPADIBDY-UHFFFAOYSA-N arsenic atom Chemical compound [As] RQNWIZPPADIBDY-UHFFFAOYSA-N 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 238000005256 carbonitriding Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000009390 chemical decontamination Methods 0.000 description 1
- 229910052729 chemical element Inorganic materials 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052732 germanium Inorganic materials 0.000 description 1
- GNPVGFCGXDBREM-UHFFFAOYSA-N germanium atom Chemical compound [Ge] GNPVGFCGXDBREM-UHFFFAOYSA-N 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 150000002843 nonmetals Chemical class 0.000 description 1
- 238000002161 passivation Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229910000753 refractory alloy Inorganic materials 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
- 229910052714 tellurium Inorganic materials 0.000 description 1
- PORWMNRCUJJQNO-UHFFFAOYSA-N tellurium atom Chemical compound [Te] PORWMNRCUJJQNO-UHFFFAOYSA-N 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Classifications
-
- 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
-
- 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
- C23C4/04—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
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-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
- C23C4/131—Wire arc 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
-
- 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
- C23C4/129—Flame 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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
Definitions
- the invention relates to the field of manufacturing the leading edge for organic matrix composite (CMO) fan blades.
- CMO organic matrix composite
- Document FR1051992 describes a known method of manufacturing such a blade. This method takes place as follows: two sheets, intrados and extrados, formed, are shaped, via an isostatic hot compaction operation, around a core of refractory alloy whose geometry corresponds to the internal geometry of the desired leading edge . After shaping, the core, which is a reusable tool, is removed and the leading edge is machined only on its outer surfaces to obtain the final geometry of the part.
- the latter must have three main characteristics in relation to the fact that the shaping step is carried out via a thermomechanical cycle at high temperature, of the order of 800 - 1000 ° C., during which, the core is in contact with the elements of the leading edge in titanium for several hours:
- the core must be non-deformable in the thermomechanical range of manufacture of the leading edge in order to ensure the shape of the internal cavity of the leading edge
- the core must not allow any chemical reaction between its material and the material of the leading edge
- the core must not allow any adhesion or bonding between its material and the material of the leading edge
- the second avoids or minimizes chemical decontamination of the surfaces of the internal cavity of the leading edge.
- the metal alloys retained for the core are nickel-based or cobalt-based alloys so as to be rigid enough not to deform during conforming cycles at high temperature.
- this type of alloy brought into contact at high temperature with the titanium alloys of the part are reactive with one another and form solid solutions or intermetallic compounds, which leads at best to contamination of the titanium alloy, worse an unacceptable bond between nickel / cobalt and titanium.
- a technical solution consists in interposing an anti-diffusion barrier between the two metallic alloys in contact that are the nickel or cobalt base alloy of the core and the titanium alloy of the leading edge which will undergo a thermomechanical treatment at high temperature for many hours.
- a method described by the document FR 1653221 is the production of nitriding or nitro-carburization of the nickel or cobalt base core. This treatment generates a surface layer rich in nitrogen and carbon of a few tens of microns on the surface of the core ensuring the role of anti-diffusion barrier.
- the invention provides a method of manufacturing a core for the production of a leading edge of a fan blade, characterized in that it comprises the steps of:
- the cobalt-based alloy may include carbon.
- the cobalt-based alloy can comprise between 26% and 32% of molybdenum, between 7% and 20% of chromium between 1% and 5% of silicon and less than 1% of carbon.
- the cobalt-based alloy can comprise between 25% and 35% of chromium, between 0% and 10% of tungsten, between 0% and 7% of molybdenum, between 0% and 4% of nickel, between 1% and 3% of silicon and less than 2% carbon.
- the cobalt-based alloy can comprise between 28% and 30% of chromium, between 1.2% and 1.6% of carbon and, between 1.2% and 1.8% of silicon.
- the deposited layer may have a thickness of 100 microns and 2 millimeters, preferably 500 microns.
- the method may further comprise, following step (b) of thermal spraying, a step (d) of machining by rectification.
- the method may further comprise, following step (b) of thermal spraying, a step (e) of air heat treatment, comprising a first stage of approximately thirty minutes at a temperature between 300 ° C and 400 ° C, a second stage of approximately thirty minutes at a temperature between 500 ° C and 700 ° C, a third stage of approximately thirty minutes at a temperature between 800 ° C and 1000 ° C, and cooling to ambient air, to oxidize the layer.
- step (e) of air heat treatment comprising a first stage of approximately thirty minutes at a temperature between 300 ° C and 400 ° C, a second stage of approximately thirty minutes at a temperature between 500 ° C and 700 ° C, a third stage of approximately thirty minutes at a temperature between 800 ° C and 1000 ° C, and cooling to ambient air, to oxidize the layer.
- Figure 1 is a microscopic sectional view of the surface of a core according to the invention.
- FIG. 2 is a block diagram of a method according to the invention.
- the invention relates to a process for manufacturing a core 1 for the production of a leading edge of a fan blade, the process essentially comprises the steps of:
- step (a2) the initial core 11 can be cleaned and degreased. This step guarantees a surface condition of the initial core 11, which is optimal for the next projection step (b).
- step (b) consists in the thermal spraying onto the initial core 11 of a layer 12 of a cobalt-based alloy, comprising chromium and at least one element from tungsten and / or molybdenum. It is specified that tungsten, molybdenum and chromium can be present in the form of carbide.
- the cobalt base alloy can have the following composition, in mass percentage: between 26% and 32% of molybdenum, between 7% and 20% of chromium, between 0% and 10% of tungsten, between 1% and 5% silicon and less than 1% carbon.
- the cobalt-based alloy can comprise 28% of chromium, 5.5% of molybdenum, 2.5% of nickel, 2% of silicon and 0.25% of carbon.
- the cobalt-based alloy can comprise 29.5% of chromium, 8% of tungsten, 1.5% of silicon and 1.4% of carbon.
- the cobalt-based alloy can comprise between 26% and 32% of molybdenum, between 7% and 20% of chromium between 1% and 5% of silicon and less than 1% of carbon.
- the cobalt-based alloy can comprise 29% of molybdenum, 8.5% of chromium, 2.6% of silicon and less than 0.08% of carbon.
- the cobalt-based alloy can comprise 28% of molybdenum, 18% of chromium, 3.4% of silicon and less than 0.08% of carbon.
- the thermal projection of these types of alloys provides chemical inertness which makes it possible to produce an anti-diffusion barrier between the initial core 1 1 made of a nickel base alloy and sheets made of titanium used for the manufacture of the fan blade.
- the layer can be projected by blown arc plasma.
- This method leads to a porous layer but having good mechanical grip on the surface of the core.
- This method can optionally consider vacuum pumping during projection.
- the layer can be deposited by a plasma torch according to the so-called “Plasma Transferred Arc” (PTA) method.
- PTA Plasma Transferred Arc
- the method can include a rectification step (d) to reduce a thickness of the layer 12.
- the layer 12 can have a thickness of between 100 and 500 microns. This step can also serve as a practical verification of the adhesion of the deposit.
- the method may include a step (e) of air heat treatment, comprising a first stage of approximately thirty minutes at a temperature between 300 ° C and 400 ° C, a second stage d 'about thirty minutes at a temperature between 500 ° C and 700 ° C, a third stage of about thirty minutes at a temperature between 800 ° C and 1000 ° C, and cooling in ambient air.
- a step (e) of air heat treatment comprising a first stage of approximately thirty minutes at a temperature between 300 ° C and 400 ° C, a second stage d 'about thirty minutes at a temperature between 500 ° C and 700 ° C, a third stage of about thirty minutes at a temperature between 800 ° C and 1000 ° C, and cooling in ambient air.
- the layer 12 can have a hardness of between 35 and 65 HRC, preferably between 45 and 55 HRC. It is specified that the hardness is expressed and measured according to the so-called Rockwell test, using a penetrator to which an initial charge is applied and then an additional charge. Hardness is measured by comparing the depth of penetration of the indenter when applying the initial load and when applying the additional load. For the HRC scale, In this case, the test is carried out with a penetrator consisting of a diamond cone of circular section with a spherical rounded point of 0.2 millimeters. In addition, the initial charge applied is 98N and the total charge (corresponding to the initial charge plus the additional charge) is 1471.5N. One HRC hardness unit corresponds to a penetration of 0.002 millimeters.
- the HR15N scale is preferred because the initial load applied is only 29N and the total load (corresponding to the initial load plus the additional load) is only 147.1 N.
- the invention relates to a core 1 of nickel base alloy obtained by a method according to the invention.
- the core 1 has a layer 12 composed of a cobalt base alloy comprising chromium and at least one element from tungsten and / or molybdenum obtained by thermal spraying of a cobalt base alloy comprising chromium and at least one element from tungsten and / or molybdenum.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1873958A FR3090427B1 (fr) | 2018-12-21 | 2018-12-21 | Procede de fabrication d’un noyau |
PCT/FR2019/053241 WO2020128391A1 (fr) | 2018-12-21 | 2019-12-20 | Procede de fabrication d'un noyau |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3899081A1 true EP3899081A1 (fr) | 2021-10-27 |
EP3899081B1 EP3899081B1 (fr) | 2022-06-15 |
Family
ID=67001904
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19848898.3A Active EP3899081B1 (fr) | 2018-12-21 | 2019-12-20 | Procede de fabrication d'un noyau |
Country Status (5)
Country | Link |
---|---|
US (1) | US20220064776A1 (fr) |
EP (1) | EP3899081B1 (fr) |
CN (1) | CN113260731B (fr) |
FR (1) | FR3090427B1 (fr) |
WO (1) | WO2020128391A1 (fr) |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1051992A (fr) | 1952-03-03 | 1954-01-20 | Mécanisme de commande de la barre faucheuse sur tracteurs de voirie | |
GB933406A (en) * | 1960-11-17 | 1963-08-08 | Deloro Stellite Ltd | A cobalt-chromium base alloy |
US3642519A (en) * | 1969-03-21 | 1972-02-15 | Us Air Force | Method for the development of hard coat seal surfaces |
US4339509A (en) * | 1979-05-29 | 1982-07-13 | Howmet Turbine Components Corporation | Superalloy coating composition with oxidation and/or sulfidation resistance |
US4837389A (en) * | 1984-06-04 | 1989-06-06 | Turbine Components Corporation | Composite alloy structures |
DE10041974B4 (de) * | 2000-08-25 | 2008-02-14 | Daimler Ag | Beschichtungsverfahren für Zylinderköpfe und Verwendung |
DE10334703A1 (de) * | 2003-07-30 | 2005-02-24 | Daimlerchrysler Ag | Ventilsitzringe aus Co oder Co/Mo-Basislegierungen und deren Herstellung |
US6933052B2 (en) * | 2003-10-08 | 2005-08-23 | General Electric Company | Diffusion barrier and protective coating for turbine engine component and method for forming |
CA2588988A1 (fr) * | 2004-11-30 | 2006-06-08 | Deloro Stellite Holdings Corporation | Alliage soudable a base de co resistant a la fissuration |
EP1715140A1 (fr) * | 2005-04-21 | 2006-10-25 | Siemens Aktiengesellschaft | Aube de turbine ayant une bande couvrante et une couche de protection sur la bande couvrante |
JP5529366B2 (ja) * | 2007-03-29 | 2014-06-25 | 三菱重工業株式会社 | コーティング材料及びその製造方法並びにコーティング方法並びにシュラウド付き動翼 |
FR2920440B1 (fr) * | 2007-08-31 | 2010-11-05 | Commissariat Energie Atomique | Procede de traitement anti-corrosion d'une piece par depot d'une couche de zirconium et/ou d'alliage de zirconium |
DE102009043097A1 (de) * | 2009-09-25 | 2011-03-31 | Siemens Aktiengesellschaft | Laufschaufel zur Verwendung in Zweiphasenströmungen sowie Verfahren zum Herstellen einer solchen Laufschaufel |
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 |
US20130180432A1 (en) * | 2012-01-18 | 2013-07-18 | General Electric Company | Coating, a turbine component, and a process of fabricating a turbine component |
JP5842772B2 (ja) * | 2012-09-11 | 2016-01-13 | Jfeスチール株式会社 | 継目無鋼管圧延用プラグおよびその製造方法 |
ITUB20152136A1 (it) * | 2015-07-13 | 2017-01-13 | Nuovo Pignone Srl | Pala di turbomacchina con struttura protettiva, turbomacchina, e metodo per formare una struttura protettiva |
CN107083502B (zh) * | 2016-02-12 | 2023-10-13 | 肯纳金属公司 | 耐磨且耐蚀的钴基合金粉末及其施加方法 |
-
2018
- 2018-12-21 FR FR1873958A patent/FR3090427B1/fr active Active
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2019
- 2019-12-20 WO PCT/FR2019/053241 patent/WO2020128391A1/fr unknown
- 2019-12-20 CN CN201980084161.4A patent/CN113260731B/zh active Active
- 2019-12-20 EP EP19848898.3A patent/EP3899081B1/fr active Active
- 2019-12-20 US US17/416,139 patent/US20220064776A1/en active Pending
Also Published As
Publication number | Publication date |
---|---|
US20220064776A1 (en) | 2022-03-03 |
WO2020128391A1 (fr) | 2020-06-25 |
FR3090427B1 (fr) | 2023-11-10 |
EP3899081B1 (fr) | 2022-06-15 |
CN113260731B (zh) | 2023-07-28 |
CN113260731A (zh) | 2021-08-13 |
FR3090427A1 (fr) | 2020-06-26 |
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