EP3249063B1 - Superalliage à base de ni à haute résistance - Google Patents
Superalliage à base de ni à haute résistance Download PDFInfo
- Publication number
- EP3249063B1 EP3249063B1 EP16171670.9A EP16171670A EP3249063B1 EP 3249063 B1 EP3249063 B1 EP 3249063B1 EP 16171670 A EP16171670 A EP 16171670A EP 3249063 B1 EP3249063 B1 EP 3249063B1
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- European Patent Office
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- alloy
- phase
- temperature
- based superalloy
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- 229910000601 superalloy Inorganic materials 0.000 title claims description 24
- 238000009864 tensile test Methods 0.000 claims description 10
- 239000000203 mixture Substances 0.000 claims description 9
- 239000012535 impurity Substances 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 description 76
- 239000000956 alloy Substances 0.000 description 76
- 230000000052 comparative effect Effects 0.000 description 14
- 230000000694 effects Effects 0.000 description 9
- 229910052719 titanium Inorganic materials 0.000 description 9
- 238000005204 segregation Methods 0.000 description 8
- 229910052782 aluminium Inorganic materials 0.000 description 7
- 238000005728 strengthening Methods 0.000 description 7
- 230000001965 increasing effect Effects 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 229910052758 niobium Inorganic materials 0.000 description 5
- 238000003723 Smelting Methods 0.000 description 4
- 239000013078 crystal Substances 0.000 description 4
- 238000009792 diffusion process Methods 0.000 description 4
- 238000005242 forging Methods 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 229910001068 laves phase Inorganic materials 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 238000001556 precipitation Methods 0.000 description 4
- 239000000470 constituent Substances 0.000 description 3
- 229910052750 molybdenum Inorganic materials 0.000 description 3
- 239000002244 precipitate Substances 0.000 description 3
- 229910052721 tungsten Inorganic materials 0.000 description 3
- 238000005275 alloying Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 229910052804 chromium Inorganic materials 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 229910017060 Fe Cr Inorganic materials 0.000 description 1
- UCKMPCXJQFINFW-UHFFFAOYSA-N Sulphide Chemical compound [S-2] UCKMPCXJQFINFW-UHFFFAOYSA-N 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000000151 deposition Methods 0.000 description 1
- 230000001687 destabilization Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 230000001747 exhibiting effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- 229910000765 intermetallic Inorganic materials 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000009291 secondary effect Effects 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
Definitions
- the present invention relates to a high strength Ni-based superalloy having a high strength.
- a Ni-based superalloy shows excellent mechanical characteristics at high temperatures and is widely used as high-temperature members of aircraft jet engines, etc.
- adding a small amount of Al, Ti as well as Nb and Ta to a Ni-based alloy brings about fine precipitation of a strengthening phase that is called a ⁇ ' (gamma prime) phase of Ni 3 (Al,Ti), or a ⁇ " (gamma double prime) phase of Ni 3 (Al,Ti,Nb) in crystal grains to express an excellent strength.
- a technical tendency is toward an uncooled low-pressure turbine disk in jet engines.
- a low-pressure turbine disk has become desired to have a high strength at higher temperatures, and development of an alloy having an increased strength by increasing the amount of the above-mentioned strengthening phase therein is being made.
- the hot workability of the alloy lowers, and therefore, the alloy becomes difficult to work into a desired shape. Accordingly, it is important to secure hot workability of an alloy while increasing the strength thereof.
- a Ni-based superalloy generally contains large quantities of alloying elements, and in smelting the alloy, there may occur in any way, unevenness in compositional distribution, that is, micro-segregation.
- the solidus temperature is lower than that of the other part, and therefore, when overheated, the micro-segregated part may be partially melted to lower the hot workability of the alloy. Accordingly, before hot working, the alloy must be heat-treated under a suitable condition to relax the micro-segregation.
- Patent Documents 1 to 3 Some proposes have been made for a Ni-based superalloy having excellent hot workability or a technique of improving the hot workability of a Ni-based alloy.
- Patent Documents 1 and 2 propose a Ni-based superalloy excellent in weldability and hot workability.
- these documents refer to nothing relating to hot workability from the viewpoint of the above-mentioned micro-segregation, and there is a possibility of absence of any suitable evaluation therein.
- the contents of Al and Ti capable of contributing to formation of a strengthening phase are smaller than those in the present invention, and therefore, a strengthening phase in an amount required by low-pressure turbine disks to which the present invention is intended to be applied could not be formed, that is, there is a possibility that the strength of the alloys may be insufficient.
- Patent Documents 3 refers to nothing relating to the relationship between micro-segregation and hot workability, and it is unclear whether alloy production would be carried out under a suitable condition.
- the present invention has been made in consideration of the above-mentioned situation, and an object thereof is to provide a Ni-based superalloy excellent in strength and hot workability.
- the present invention relates to the following (1) to (5).
- Ni-based superalloy having a high strength and excellent hot workability.
- C is an additive element to form a carbide to suppress crystal grain coarsening of the alloy, and to precipitate in a grain boundary to improve the high-temperature strength of the alloy; but when the content thereof is small, it is not effective for sufficiently improving the strength, and therefore, the content of C must be 0.005% or more. However, when the content thereof is too large, an excessive carbide may be formed to have a negative influence of decreasing the amount of other useful precipitates such as a ⁇ '-phase, and therefore, the upper limit thereof is 0.05%. For the same reasons, the lower limit thereof is preferably 0.01% and the upper limit thereof is preferably 0.02%.
- Fe is, when the content thereof is increased, effective for alloy cost reduction, but when Fe is incorporated excessively in an Nb-containing alloy, an intermetallic compound called a Laves phase is formed to cause worsening of material characteristics, for example, degradation of hot rollability, etc. Accordingly, the content of Fe is 0.1 to 2.0%. For the same reasons, the lower limit thereof is preferably 0.5% and the upper limit thereof is preferably 1.5%.
- Co is an element of improving the segregation property of the alloy by bringing the partition coefficient of alloying elements such as Al, Ti, Nb and W close to 1.
- the alloy does not contain Co in an amount of 10% or more, the effect could not be sufficiently realized.
- the content of Co is more than 20%, not only the forgeability is worsened but also a Laves phase may be readily formed, whereby, the matrix texture at a high temperature would be rather destabilized and the high-temperature texture stability would be worsened. Accordingly, the content of Co is limited to a range of 10 to 20%.
- the lower limit thereof is preferably 12% and the upper limit thereof is preferably 16%.
- Mo mainly dissolves in a matrix to strengthen it, and also dissolves in a ⁇ ' phase to substitute for the Al site in this phase to thereby increase the stability of the phase, and is therefore effective for increasing both high-temperature strength and texture stability.
- the content of Mo is less than 1.0%, the above-mentioned effect is insufficient, but when the content thereof is more than 8.0%, a Laves phase may be readily formed, whereby the matrix texture at a high temperature would be rather destabilized and the high-temperature texture stability would be worsened.
- the content of Mo is limited to a range of 1.0 to 8.0%.
- the lower limit thereof is preferably 2.0% and the upper limit thereof is preferably 6.0%.
- W Like Mo, W also dissolves in a matrix to strengthen it, and dissolves in a ⁇ ' phase to substitute for the Al site in this phase to thereby increase the stability of the phase, and is therefore effective for increasing both high-temperature strength and texture stability.
- W when W is incorporated excessively, not only ⁇ -W precipitates to lower texture stability but also hot workability is also noticeably worsened. Accordingly, the content of W is limited to a range of 1.0 to 8.0%.
- the lower limit thereof is preferably 2.0% and the upper limit thereof is preferably 6.0%.
- Cr is an element necessary for enhancing oxidation resistance, corrosion resistance and strength of the alloy. Also, it combines with C to form a carbide, thereby enhancing high-temperature strength. However, too large content thereof invites destabilization of matrix and promotes the formation of harmful TCP phases such as a ⁇ phase and ⁇ -Cr, resulting in adverse influences on ductility and toughness. Therefore, the content of Cr is limited to 10 to 20%. For the same reasons, the lower limit thereof is preferably 14% and the upper limit thereof is preferably 18%.
- Ti mainly forms an MC carbide to suppress crystal grain coarsening of the alloy and also combines with Ni to precipitate a ⁇ ' phase, thereby contributing to precipitation strengthening of the alloy.
- the content of Ti is limited to a range of 0.1 to 2.0%.
- the lower limit thereof is preferably 0.5% and the upper limit thereof is preferably 1.5%.
- Al combines with Ni to precipitate a ⁇ ' phase, thereby contributing to precipitation strengthening of the alloy.
- the content of Al is limited to 2.0 to 4.5%.
- the lower limit thereof is preferably 3.0% and the upper limit thereof is preferably 4.0%.
- Nb is an element that stabilizes the ⁇ ' phase and contributes to strength enhancement, but when Nb is exceedingly incorporated, the precipitation of the ⁇ phase, the ⁇ phase, and the Laves phase that are harmful phases is promoted, thereby remarkably lowering texture stability. Therefore, the content ofNb is limited to 0.1 to 2.0%. For the same reasons, the lower limit thereof is preferably 0.5% and the upper limit thereof is preferably 1.5%.
- P is considered to have an effect of reducing local strain accumulation near grain boundaries to prevent creep deformation by depositing precipitates containing P at grain boundaries, thereby lowering the minimum creep speed and prolonging the creep rupture time.
- P when P is exceedingly incorporated, there is a possibility that grain boundary segregation of P becomes excessive to lower the consistency of the grain boundaries, thereby causing ductility reduction and the like. Therefore, when P is incorporated according to the necessity, it is desirable that the lower limit of the content of P is 30 ppm and the upper limit thereof is 100 ppm.
- the lower limit thereof is more preferably 40 ppm and the upper limit thereof is more preferably 80 ppm.
- B segregates at grain boundaries to contribute to high-temperature characteristics, and is therefore incorporated according to the necessity.
- the content of B is preferably 250 ppm or less.
- the content thereof is preferably 50 ppm or more, and for the same reasons as above, the lower limit thereof is more preferably 100 ppm and the upper limit thereof is more preferably 200 ppm.
- Mg mainly combines with S to form a sulfide and enhances hot workability, so that Mg is incorporated according to the necessity.
- the content of Mg is preferably 0.01% or less.
- the lower limit of the Mg content is preferably 0.0005% or more.
- Zr segregates at grain boundaries to contribute to an improvement in high-temperature characteristics, so that Zr is incorporated according to the necessity.
- the content of Zr is preferably 0.50% or less. In order to obtain the above-described effect, it is preferable to incorporate Zr in an amount of 0.01% or more.
- ⁇ ' phase amount at 700°C being 40 to 43% in terms of volume fraction.
- the ⁇ ' phase amount at 700°C in terms of volume fraction is appropriate, a desired strength can be realized. When it is lower than 40%, the strength would be too low and desired characteristics of members could not be satisfied. On the other hand, when it is more than 43%, the strength would be excessive to lower the toughness of members. Accordingly, it is desirable that the ⁇ ' phase amount at 700°C is 40 to 43% in terms of volume fraction.
- the ⁇ ' phase amount in terms of volume fraction may be controlled by varying the balance of Al and Ti that are the constituent elements of the ⁇ ' phase.
- ⁇ ' phase solution temperature being 1100°C or lower.
- the ⁇ ' phase solution temperature is 1100°C or lower, the temperature range within which the alloy exhibits good hot workability can be expanded to lower temperatures, thereby enabling effective bloom-forging at lower temperatures.
- the ⁇ ' phase solution temperature can be controlled by varying the balance of Al and Ti that are the constituent elements of the ⁇ ' phase.
- Temperature range within which reduction of area is 50% or more being 120°C or higher.
- the temperature range that realizes excellent hot workability is expanded, and in a one-time bloom-forging step, a cast structure can be more effectively destroyed.
- the temperature range is less than 120°C, the temperature range capable of realizing excellent hot workability may narrow, and multiple bloom-forging steps would be necessary for sufficiently destroying a cast structure, thereby resulting in cost increase.
- Hot working can be carried out, for example, in a temperature range of 900°C to 1150°C.
- the temperature range for hot working is not limited to the above-described temperature range.
- the temperature range within which the reduction of area is 50% or more is preferably 120°C or higher, and the temperature range can be controlled by varying the balance of Al and Ti that are the constituent elements of the ⁇ ' phase, and the balance of Cr, Mo and Nb that are micro-segregation elements.
- the Ni-based alloy of the present invention is controlled to have a composition including, in terms of % by mass, C: 0.005 to 0.05%, Fe: 0.1 to 2.0%, Cr: 10 to 20%, Co: 10 to 20%, Mo: 1.0 to 8.0%, W: 1.0 to 8.0%, Ti: 0.1 to 2.0%, Al: 2.0 to 4.5%, and Nb: 0.1 to 2.0%, with the balance being Ni and unavoidable impurities.
- the composition may further include according to the necessity, in terms of ppm by mass, at least one of P: 30 to 100 ppm, and B: 50 to 250 ppm, and also according to the necessity, at least one of Mg: 0.01% or less, and Zr: 0.01 to 0.50%.
- the Ni-based alloy of the present invention can be produced according to an ordinary smelting method and, as the invention, the smelting method is not particularly limited.
- the Ni-based alloy may be subjected to diffusion heat treatment.
- an ingot of 5 tons or more is expected in smelting.
- the size of products is not specifically limited, the effect of improving hot workability for large-size members of 5 tons or more brings about especially favorable results.
- Diffusion heat treatment can be carried out under the condition at 1200°C for 50 hours or more.
- the treatment time is preferably 100 hours or less.
- diffusion heat treatment may be omitted.
- the Ni-based alloy may be worked for forging or the like, according to the necessity.
- the condition in working is not specifically limited in the present invention.
- the ⁇ ' phase amount at 700°C is 40 to 43% in terms of volume fraction
- the ⁇ ' phase solution temperature is 1100°C or lower
- the temperature range within which the reduction of area of the alloy in a tensile test is 50% or more, is 120°C or higher; and the alloy realizes good hot workability.
- an Ni-based superalloy that has improved hot workability and contains a sufficient amount of a strengthening phase to secure the strength thereof can be obtained.
- the strength is, for example, 1050 MPa or more at 750°C, but is not limited thereto.
- Ni-based alloy is favorably used in the field where a temperature of 600°C or higher is expected, such as low-pressure turbine disks of jet engines and gas turbine disks for high-efficiency power generation.
- the material was a 25-kg round ingot produced according to a vacuum induction melting method, and nine invention alloys and one comparative alloy were produced.
- the chemical components (with the balance being unavoidable impurities) of the invention alloys and the comparative alloy are shown in Table 1.
- the ⁇ ' phase amount at 700°C and the ⁇ ' phase solution temperature of the invention alloys and the comparative alloy are calculated using a general-purpose thermodynamic calculation software (Thermo-Calc). Table 2 collectively shows them.
- the tensile test was performed as follows.
- each test piece had a diameter in the parallel part of 6 mm and a mark-to-mark distance of 30 mm.
- the test temperature range was 950 to 1225°C, and the following method was employed for avoiding the influence to be provided by the difference in the crystal grain size. Specifically, in the case where the test temperature was 1150°C or higher, the test piece was kept at the test temperature for 30 minutes and then subjected to the tensile test.
- the test piece was once kept at 1150°C for 30 minutes, then cooled down to the test temperature, and further kept at the test temperature for 15 minutes to thereby stabilize the temperature thereof, and thereafter subjected to the tensile test.
- the strain speed in the tensile test was 3 ⁇ 10 -2 s -1 in every case.
- all the invention alloys have a larger ⁇ ' phase amount at 700°C, from 42.0 to 43.1%, than the comparative alloy.
- the ⁇ ' phase solution temperature in the invention alloys is lower than that in the comparative alloy, that is, lower than 1100°C.
- Fig. 1 and Fig. 2 each show a relationship between a reduction of area and a temperature of the invention alloys and the comparative alloy.
- the maximum reduction of area is almost the same between the invention alloys and the comparative alloy, but the temperature range within which the reduction of area is 50% or more is broader for the invention alloys than that for the comparative alloy.
- the broader temperature range means that the forgeable temperature range is broad and the hot workability of the alloy is good.
- Fig. 3 shows the temperature range within which the reduction of area is 50% or more for the invention alloys and the comparative alloy.
- the temperature range for the comparative alloy is 120°C, but all the invention alloys shown in Fig. 3 show a temperature range higher than that for the comparative alloy. Accordingly, it becomes clear that the invention alloys are excellent in hot workability.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (5)
- Superalliage haute résistance à base de Ni ayant une composition comprenant, en termes de % en masse :C : de 0,005 à 0,05 % ;Fe : de 0,1 à 2,0 % ;Cr : de 10 à 20 % ;Co : de 10 à 20 % ;Mo : de 1,0 à 8,0 % ;W : de 1,0 à 8,0 % ;Ti : de 0,1 à 2,0 % ;Al : de 2,0 à 4,5 % ; etNb : de 0,1 à 2,0 %,le reste étant du Ni et des impuretés inévitables,
la composition comprenant en outre éventuellement, en termes de ppm en masse, l'un au moins parmi :P : de 30 à 100 ppm ; etB : de 50 à 250 ppm.et la composition comprenant en outre éventuellement, en termes de % en masse, l'un au moins parmi :Mg : 0,01 % ou moins ; etZr : de 0,01 à 0,50 %. - Superalliage haute résistance à base de Ni selon la revendication 1, ayant une quantité de phase γ' à 700 °C de 40 à 43 % en termes de fraction volumique.
- Superalliage haute résistance à base de Ni selon la revendication 1 ou 2, ayant une quantité de phase γ' à 1 100 °C ou moins.
- Superalliage haute résistance à base de Ni selon l'une quelconque des revendications 1 à 3, où une plage de température dans laquelle une réduction de la surface du superalliage évaluée lors d'un essai de traction est de 50 % ou plus, est de 120 °C ou plus.
- Superalliage haute résistance à base de Ni selon l'une quelconque des revendications 1 à 4, qui est utilisé à une température de 600 °C ou plus.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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EP16171670.9A EP3249063B1 (fr) | 2016-05-27 | 2016-05-27 | Superalliage à base de ni à haute résistance |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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EP16171670.9A EP3249063B1 (fr) | 2016-05-27 | 2016-05-27 | Superalliage à base de ni à haute résistance |
Publications (2)
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EP3249063A1 EP3249063A1 (fr) | 2017-11-29 |
EP3249063B1 true EP3249063B1 (fr) | 2018-10-17 |
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EP16171670.9A Active EP3249063B1 (fr) | 2016-05-27 | 2016-05-27 | Superalliage à base de ni à haute résistance |
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Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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GB2565063B (en) | 2017-07-28 | 2020-05-27 | Oxmet Tech Limited | A nickel-based alloy |
RU2686831C1 (ru) * | 2018-03-22 | 2019-04-30 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | Металлокерамический композиционный материал на основе интерметаллидной матрицы и способ его получения |
CN109504879A (zh) * | 2018-12-28 | 2019-03-22 | 西安欧中材料科技有限公司 | 一种航空发动机用镍基高温合金 |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1227686A (fr) | 1958-06-17 | 1960-08-22 | Mond Nickel Co Ltd | Perfectionnements aux alliages de nickel-chrome |
WO2001053548A2 (fr) | 2000-01-24 | 2001-07-26 | Inco Alloys International, Inc. | Alliage ni-co-cr anticorrosion a limite de rupture a temperature elevee |
EP2008757A1 (fr) | 2006-04-14 | 2008-12-31 | Mitsubishi Materials Corporation | Fil destiné à souder un alliage réfractaire à base de ni |
EP2246449A1 (fr) | 2008-02-13 | 2010-11-03 | The Japan Steel Works, Ltd. | Superalliage à base de ni présentant d'excellentes propriétés de ségrégation |
WO2012047352A2 (fr) | 2010-07-09 | 2012-04-12 | General Electric Company | Alliage à base de nickel, son traitement et les composants formés à partir dudit alliage |
JP2012107328A (ja) | 2010-11-18 | 2012-06-07 | Korea Inst Of Machinery & Materials | 高温での機械的特性に優れた多結晶ニッケル基超耐熱合金 |
WO2014124626A1 (fr) | 2013-02-14 | 2014-08-21 | VDM Metals GmbH | Alliage nickel-cobalt |
EP2826877A2 (fr) | 2013-07-12 | 2015-01-21 | Daido Steel Co.,Ltd. | Superalliage à base de Nickel à forgeage à chaud présentant une excellente résistance aux températures élevées |
EP2940174A1 (fr) | 2012-12-28 | 2015-11-04 | The Japan Steel Works, Ltd. | ALLIAGE À BASE DE Fe-Ni EXCELLENT EN TERMES DE PROPRIÉTÉS AUX HAUTES TEMPÉRATURES ET DE PROPRIÉTÉS DE RÉSISTANCE À LA FRAGILISATION PAR L'HYDROGÈNE AINSI QUE PROCÉDÉ DE FABRICATION ASSOCIÉ |
EP3023509A1 (fr) | 2013-07-17 | 2016-05-25 | Mitsubishi Hitachi Power Systems, Ltd. | PRODUIT D'ALLIAGE À BASE DE Ni ET SON PROCÉDÉ DE PRODUCTION, ET ÉLÉMENT D'ALLIAGE À BASE DE Ni ET SON PROCÉDÉ DE PRODUCTION |
-
2016
- 2016-05-27 EP EP16171670.9A patent/EP3249063B1/fr active Active
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1227686A (fr) | 1958-06-17 | 1960-08-22 | Mond Nickel Co Ltd | Perfectionnements aux alliages de nickel-chrome |
WO2001053548A2 (fr) | 2000-01-24 | 2001-07-26 | Inco Alloys International, Inc. | Alliage ni-co-cr anticorrosion a limite de rupture a temperature elevee |
EP2008757A1 (fr) | 2006-04-14 | 2008-12-31 | Mitsubishi Materials Corporation | Fil destiné à souder un alliage réfractaire à base de ni |
EP2246449A1 (fr) | 2008-02-13 | 2010-11-03 | The Japan Steel Works, Ltd. | Superalliage à base de ni présentant d'excellentes propriétés de ségrégation |
WO2012047352A2 (fr) | 2010-07-09 | 2012-04-12 | General Electric Company | Alliage à base de nickel, son traitement et les composants formés à partir dudit alliage |
JP2012107328A (ja) | 2010-11-18 | 2012-06-07 | Korea Inst Of Machinery & Materials | 高温での機械的特性に優れた多結晶ニッケル基超耐熱合金 |
EP2940174A1 (fr) | 2012-12-28 | 2015-11-04 | The Japan Steel Works, Ltd. | ALLIAGE À BASE DE Fe-Ni EXCELLENT EN TERMES DE PROPRIÉTÉS AUX HAUTES TEMPÉRATURES ET DE PROPRIÉTÉS DE RÉSISTANCE À LA FRAGILISATION PAR L'HYDROGÈNE AINSI QUE PROCÉDÉ DE FABRICATION ASSOCIÉ |
WO2014124626A1 (fr) | 2013-02-14 | 2014-08-21 | VDM Metals GmbH | Alliage nickel-cobalt |
EP2826877A2 (fr) | 2013-07-12 | 2015-01-21 | Daido Steel Co.,Ltd. | Superalliage à base de Nickel à forgeage à chaud présentant une excellente résistance aux températures élevées |
EP3023509A1 (fr) | 2013-07-17 | 2016-05-25 | Mitsubishi Hitachi Power Systems, Ltd. | PRODUIT D'ALLIAGE À BASE DE Ni ET SON PROCÉDÉ DE PRODUCTION, ET ÉLÉMENT D'ALLIAGE À BASE DE Ni ET SON PROCÉDÉ DE PRODUCTION |
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EP3249063A1 (fr) | 2017-11-29 |
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