EP2078763A1 - Auf nickel basierende verbindungssuperlegierung mit hervorragender oxidationsbeständigkeit, herstellungsverfahren dafür und hitzebeständiges konstruktionsmaterial - Google Patents

Auf nickel basierende verbindungssuperlegierung mit hervorragender oxidationsbeständigkeit, herstellungsverfahren dafür und hitzebeständiges konstruktionsmaterial Download PDF

Info

Publication number
EP2078763A1
EP2078763A1 EP07828466A EP07828466A EP2078763A1 EP 2078763 A1 EP2078763 A1 EP 2078763A1 EP 07828466 A EP07828466 A EP 07828466A EP 07828466 A EP07828466 A EP 07828466A EP 2078763 A1 EP2078763 A1 EP 2078763A1
Authority
EP
European Patent Office
Prior art keywords
phase
superalloy
based compound
microstructure
less
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.)
Withdrawn
Application number
EP07828466A
Other languages
English (en)
French (fr)
Other versions
EP2078763A4 (de
Inventor
Kazuyoshi Chikugo
Takayuki Takasugi
Yasuyuki Kaneno
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
IHI Corp
Osaka Prefecture University
Original Assignee
IHI Corp
Osaka Prefecture University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by IHI Corp, Osaka Prefecture University filed Critical IHI Corp
Publication of EP2078763A1 publication Critical patent/EP2078763A1/de
Publication of EP2078763A4 publication Critical patent/EP2078763A4/de
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • 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
    • 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
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D2211/00—Microstructure comprising significant phases
    • C21D2211/004—Dispersions; Precipitations

Definitions

  • the present invention relates to a Ni-based compound superalloy having excellent oxidation resistance, which has a multi-phase microstructure including a primary L1 2 phase and an eutectoid microstructure (L1 2 phase + D0 x phase (including D0 22 phase, D0 24 phase, or D0 a phase)).
  • the present invention further relates to a method for manufacturing the aforementioned Ni-based compound superalloy.
  • Ni-based superalloys are Ni-based superalloys. Because at least approximately 35vol% or more of the constituent phases of Ni-based superalloy are metal phases (y), there are limitations in melting point and high-temperature creep strength of Ni-based superalloys. As candidates for high-temperature structural materials that surpass the Ni-based superalloys, high-temperature structural materials including intermetallic compounds in which the yield stress shows positive temperature dependence can be raised. However, single-phase materials have drawbacks of poor ductility at room temperature and low creep strength at high temperature.
  • any of Ni 3 X type intermetallic compounds has a GCP (Geometrically Close Packed) crystal structure, there is a possibility that some of these intermetallic compounds may be combined with high coherency. Since there are a number of Ni 3 X type intermetallic compounds that have superior properties, by forming Ni 3 X type intermetallic compounds in the form of a multi-phase material, a new type of multi-phase intermetallic compounds, that is, multi intermetallics, having further excellent properties and a high freedom for microstructural control are expected to be produced.
  • Non-Patent Document 1 K. Tomihisa, Y. Kaneno, T. Takasugi, Intermetallics, 10 (2002) 247
  • Ni-based superalloys are employed as structural materials for engines and the like where high-temperature heat resistance is required. In engines where this type of material is applied, the engine efficiency is influenced by the operating temperature and the engine weight.
  • the density of the aforementioned Ni-based superalloy is 8.0 to 9.0 g/cm 3 , which is relatively heavy. Accordingly, there has been progress in the development of a Ni-based compound superalloy that has a slightly lighter specific gravity than that of the aforementioned Ni-based superalloy.
  • the present inventors carried out research and development with the goal of developing a superalloy having even more superior properties than these conventional Ni-based superalloys.
  • the present inventors carried out research and development of a Ni-based compound superalloy which includes Al in the amount of 5 to 13 at%, V in the amount of 9.5 to 17.5 at%, Ti in the amount of 0 to 3.5 at%, B in the amount of 1000 ppm (weight) or less, and Ni as the remainder, and has a dual multi-phase microstructure including a primary L1 2 phase and an (L1 2 phase + D0 22 phase) eutectoid microstructure.
  • Ni-based compound superalloy The density of this Ni-based compound superalloy is in the range of 7.5 to 8.5 g/cm 3 , and is lighter in weight than the previously mentioned Ni-based superalloy.
  • This Ni-based compound superalloy also has roughly the same high-temperature strength at temperatures up to around 1000°C as the aforemented Ni-based superalloy.
  • Ni-based compound superalloy is problematic in that its oxidation resistance is inferior.
  • the present invention aims to provide a Ni-based compound superalloy that is lighter in weight than the Ni-based superalloy, has roughly the same high-temperature strength at temperatures up to around 1000°C as the Ni-based superalloy, and, moreover, has superior resistance to oxidation.
  • the present invention employs the following design to achieve the above aims.
  • the present invention provides a Ni-based compound superalloy which includes: Al: more than 5 at% to 13 at% or less; V: 3 at% or more to 9.5 at% or less; and Ti: 0 at% or more to 3.5 at% or less, with the remainder being Ni and unavoidable impurities, and has a multi-phase microstructure including a primary L1 2 phase and an (L1 2 phase + D0 22 phase and/or D0 24 and/or D0 a phase) eutectoid microstructure.
  • the Ni-based compound superalloy according to the present invention has a specific gravity that is slightly less than that of the conventional Ni-based superalloy, superior high-temperature strength at temperatures up to around 1000 °C that is on par with the Ni-based superalloy, and superior resistance to oxidation.
  • the manufacturing method according to the present invention enables the manufacturing of a Ni-based compound superalloy having a multi-phase microstructure including a primary L1 2 phase and an (L1 2 phase + D0 22 phase and/or D0 24 and/or D0 a phase) eutectoid microstructure, this Ni-based compound superalloy has a specific gravity that is slightly less than that of the conventional Ni-based superalloy, a superior high-temperature strength at temperatures up to around 1273 K (1000 °C) that is on par with a Ni-based superalloy, and superior resistance to oxidation.
  • the Ni-based compound superalloy according to the present invention includes: Al: more than 5 at% to 13 at% or less; V: 3 at% or more to 9.5 at% or less; and Ti: 0 at% or more to 3.5 at% or less, with the remainder being Ni and unavoidable impurities, wherein the amount of V is not less than the amount of Nb, and the Ni-based compound superalloy has a multi-phase microstructure including a primary L1 2 phase and an (L1 2 phase + D0 22 phase and/or D0 24 and/or D0 a phase) eutectoid microstructure.
  • the Ni-based compound superalloy according to the present invention may include Co: 15 at% or less in addition to the above composition, and may include Cr: 5 at% or less in addition to the above composition, and also may include B: 1000 ppm (weight) or less in addition to the above composition.
  • the Ni-based compound superalloy according to the present invention has a multi-phase microstructure including a primary L1 2 phase and an (L1 2 phase + D0 22 phase and/or D0 24 and/or D0 a phase) eutectoid microstructure, and it is most preferable that the Ni-based compound superalloy according to the present invention has a dual multi-phase microstructure composed of a primary L1 2 phase and an (L1 2 phase + D0 22 phase and/or D0 24 and/or D0 a phase) eutectoid microstructure.
  • Ni-based compound superalloy can be manufactured by the method which includes: melting an alloy material having a composition that includes: Al: more than 5 at% to 13 at% or less; V: 3 at% or more to 9.5 at% or less; and Ti: 0 at% or more to 3.5 at% or less, with the remainder being Ni and unavoidable impurities, wherein the amount of V is not less than the amount of Nb; carrying out a solid solution treatment (homogenizing treatment); then carrying out a first heat treatment at a temperature at which the primary L1 2 phase and an A1 phase coexist; and then cooling the alloy material to a temperature at which the primary L1 2 phase and a D0 22 phase and/or a D0 24 phase and/or a D0 a phase coexist, or further subjecting the alloy material to a second heat treatment at this temperature, thereby converting the A1 phase to an (L1 2 phase + D0 22 phase and/or D0 a phase) eutectoid microstructure to form
  • FIG. 1 is a longitudinal phase diagram of the alloy related to the composition system according to the present invention.
  • the amount of A 1 (at%) is shown on the horizontal axis, and the absolute temperature (K) is shown on the vertical axis.
  • the amount of Ti is 2.5 at%, and the amount of V is (22.5 - amount of A1) at%.
  • FIG. 2 is a Ni 3 Al-Ni 3 Ti-Ni 3 V pseudo-ternary phase diagram at 1273 K made up from the results of various specific examples related to the composition system according to the present invention.
  • the phrase "carrying out a solid solution heat treatment (homogenizing heat treatment)" as used in the present embodiments means heating to and maintaining at the temperatures in the range indicated by A1 in FIG. 1 .
  • A1 in FIG. 1 .
  • Al 5 to 10 at%, for example, this would be the temperatures between the symbols " ⁇ " and the symbols " ⁇ ” in the region indicated by A1.
  • the alloy material may be first subjected to a solid solution heat treatment (homogenization heat treatment).
  • the homogenization heat treatment is typically carried out at a higher temperature than that of a first heat treatment which is performed subsequently.
  • the homogenization heat treatment is preferably carried out at a temperature in the range of 1523 to 1623 K.
  • the first heat treatment and the homogenization heat treatment may be carried out together.
  • the alloy is subjected to the homogenization heat treatment, and then is subjected to the first heat treatment.
  • the first heat treatment is carried out at a temperature at which both of the primary L1 2 phase and the A1 phase coexist.
  • the temperature at which the primary L1 2 phase and the A1 phase coexist is specifically the temperature at which the alloy is in the A1+L1 2 state shown in FIG. 1 , that is, the temperature between the symbols " ⁇ " and the symbols " ⁇ " in the case of Al: 5 to 10 at% shown in FIG. 1 .
  • the phrase "the first heat treatment is carried out at a temperature at which both of the primary L1 2 phase and the A 1 phase coexist” means carrying out a heat treatment in the region described as A1+L1 2 in FIG. 1 .
  • the L1 2 phase is a Ni 3 Al type intermetallic compound phase
  • the A1 phase is a fcc type Ni solid solution phase.
  • the time for carrying out this first heat treatment is not particularly restricted. However, it is desirable to carry out the first heat treatment over a time period sufficient for the entire alloy to become a microstructure including the primary L1 2 phase and the A1 phase.
  • the time period for carrying out the first heat treatment is, for example, 5 to 20 hours.
  • the phrase "carrying out a second heat treatment in a region indicated by L1 2 +D0 22 on the alloy material which is already subjected to the first heat treatment” means carrying out a heat treatment, for example, at a temperature not more than temperatures indicated by the symbols " ⁇ " in FIG. 1 in the case of Al: 5 to 10 at%.
  • the temperatures at the " ⁇ " symbols in FIG. 1 are 1281 K; however, these temperatures vary depending on the composition of the alloy.
  • the primary L1 2 phase is almost entirely unaffected by the second heat treatment. However, the A1 phase decomposes into a L1 2 phase and a D0 22 phase and/or a D0 24 phase and/or a D0 a phase.
  • a multi-phase microstructure mainly including the L1 2 phase and the D0 22 phase and/or the D0 24 phase and/or the D0 a phase which is provided by the decomposition of the A1 phase is hereinafter referred to as "lower multi-phase microstructure".
  • cooling may be accomplished by natural cooling or forcible cooling such as water-quenching.
  • the natural cooling may be carried out, for example, by taking out the alloy material from a heat-treatment furnace after the first heat treatment and then allowing the resulting alloy material to be put at room temperature, or by turning off a heater of the heat-treatment furnace after the first heat treatment and then allowing the resulting alloy material to be put in the heat-treatment furnace.
  • a temperature for the second heat treatment is, for example, about 1173 K to about 1281 K.
  • a period for the second heat treatment is, for example, about 5 to 20 hours, for example.
  • the A1 phase may be decomposed into the L1 2 phase and the D0 22 phase by the cooling such as the simply water-quenching and the like without the second heat treatment. However, the decomposition can be more reliably achieved by the heat treatment at the relatively high temperature.
  • the resulting alloy material may be cooled to the room temperature by natural cooling or forcible cooling. Note that the word "to" expressing a range as used in the present specification includes the boundary values of the range unless otherwise described.
  • the reasons for defining Al: more than 5 at% to 13 at% or less, and V: 3 at% or more to 9.5 at% or less, are that, within these ranges, the first heat treatment can be carried out at a temperature at which the primary phase L1 2 and the A1 phase coexist, and it is possible to cool to a temperature at which the L1 2 phase and the D0 22 phase and/or the D0 24 phase and/or the D0 a phase coexist, or further to carry out the second heat treatment at this temperature, so that the multi-phase microstructure can be formed.
  • the amount of Nb may be in the range of 3 at% or more to 9.5 at% or less, and may be equal to, or less than the amount of V.
  • the amount of V must be equal to or greater than the amount of Nb. This is because in the Ni-based compound superalloy of the present embodiments, a portion of V is substituted by Nb in order to improve the property of resistance to oxidation. Resistance to oxidation improves more as the amount of the V portion substituted with Nb increases.
  • the Ni-based compound superalloy of the present embodiments includes a smaller amount of V, includes Nb, and includes a larger amount of Al, as compared to the Ni-based compound superalloy which was researched by the present inventors and includes Al: 5 to 13 at%, V: 9.5 to 17.5 at%, Ti: 0 to 3.5 at%, and B: 1000 ppm (weight) or less, with the remainder being Ni, and has a dual multi-phase microstructure including a primary L1 2 phase and an (L1 2 +D0 22 and/or D0 24 phase and/or D0 a phase) eutectoid microstructure.
  • Co and Cr are elements that contribute to improving resistance to oxidation.
  • Co is preferably added in the range of 0 at% or more to 15 at% or less, and Cr is preferably added in the range of 0 at% or more to 5 at% or less.
  • Co is an element which has complete solid solubility in Ni, so that Co is soluble in intermetallic compounds, Ni 3 Al, Ni 3 V, (Ni 3 Ti), and the like.
  • the added amount is set to be up to 15 at%.
  • Cr is effective of improving resistance to oxidation.
  • the solid solubility of Cr in Ni 3 Al is low, there is a concern that unnecessary precipitates will be generated if Cr is added in a quantity of more than 5 at%. Accordingly, it is preferable to set the upper limit for addition of Cr to be 5 at%.
  • V The bonding strength of V with oxygen is high, so that the surface of the alloy material readily oxidizes. Accordingly, by decreasing the amount of V, it is possible to improve resistance to oxidation. At the same time, V can be substituted with Nb which has the same valence number. Further, by increasing the amount of Al, it is possible to generate a fine oxidized film of alumina on the surface. By decreasing the amount of V, resistance to oxidation can be improved. However, if the amount of Nb exceeds the amount of V, it becomes difficult to obtain a multi-phase microstructure. Accordingly, it is necessary to increase the amount of V to be greater than the amount of Nb.
  • the amount of Ti is in the range of 0 at% or more to 3.5 at% or less, preferably in the range of 0.5 to 3.5 at% or less, more preferably in the range of 1 to 3.5 at%, and most preferably in the range of 2 to 3 at%. It is preferable that the Ni-based compound superalloy according to the present invention includes Ti; however, it is also acceptable not to include Ti.
  • the amount ofNi is preferably in the range of 73 to 77 at%, and more preferably in the range of 74 to 76 at%. This is because, in this range, the amount of Ni : the total amount of (Al, Ti, and V) approaches nearly 3:1, and therefore, a solid solution phase of Ni, Al, Ti, or V is essentially non-existent.
  • the amount of B is in the range of 0 ppm (weight) or more to 1000 ppm (weight) or less, preferably in the range of 1 to 1000 ppm (weight), more preferably in the range of 1 to 500 ppm (weight), and even more preferably in the range of 5 to 100 ppm (weight). It is preferable that the Ni-based compound superalloy according to the present invention includes B; however it is also acceptable that B is not included.
  • Mo is an element that has the effect of improving high-temperature strength, and has complete solid solubility in V.
  • the amount of Mo preferably satisfies V > Mo + Nb.
  • the method for strengthening the crystal grain boundary may be considered as an approach for improving ductility.
  • trace quantities of elements such as C, Zr, and Hf may be added up to a maximum of 0.2 at%. It is also acceptable to include any one of elements C, Zr and Hf in a trace amount of 0.2 at% or less.
  • the Ni-based compound superalloy according to the present invention has a multi-phase microstructure which includes an upper multi-phase microstructure and a lower multi-phase microstructure as described above, and it is most preferable that this Ni-based compound superalloy includes a dual multi-phase microstructure including these multi-phase microstructures.
  • the Ni-based compound superalloy according to the present invention has superior mechanical properties at high temperatures and superior resistance to oxidation. It is thought that the reason for these superior properties is because the Ni-based compound superalloy according to the present invention has the multi-phase microstructure that includes the upper multi-phase microstructure and the lower multi-phase microstructure and, the having of the aforementioned dual multi-phase microstructure of the upper multi-phase microstructure and the lower multi-phase microstructure, which is the more preferable feature, is thought to be a contributing factor to attain more superior characteristics.
  • the multi-phase microstructure or the dual multi-phase microstructure forms the entire Ni-based compound superalloy according to the present invention; however, it is not necessary that the entire Ni-based compound superalloy has this microstructure. Rather, it is acceptable that at least a portion, or more preferably 50% or more, of the entire microstructure be composed of the multi-phase microstructure.
  • the crystal structures of the intermetallic compounds employed in the Ni-based compound superalloy according to the present invention are simple as compared to the other three constituent phases (D0 22 phase, D0 24 phase, and D0 a phase).
  • the Ni-based compound superalloy according to the present invention inlcudes a primary phase L1 2 in which dislocations are comparatively activated, and a certain degree of ductility occurs over an entire range of temperatures including a room temperature. Accordingly, this facilitates handling of the Ni-based compound superalloy.
  • the Ni-based compound superalloy according to the present invention has superior mechanical properties at high temperatures. Accordingly, it can be used as a heat resistant structural material. Further, among the component elements, a portion of V is substituted by Nb; thereby, improving the resistance to oxidation. Further, by adding Co and Cr in suitable quantities, resistance to oxidation is also increased.
  • Ni-based compound superalloy can be effectively utilized in a temperature range that is slightly lower than 1523 K (1250 °C), for example, at high temperatures up to 1273 K to 1373 K (1000 to 1100 °C), and is suitable for low-pressure turbine blades of a turbo charger or an engine.
  • the high-temperature strength is high in this temperature range, the effect of achieving the same resistance to pressure at a lower weight can be realized.
  • this is beneficial from the perspective of engine efficiency and fuel costs.
  • Examples of the alloy material employed to manufacture the Ni-based compound superalloy according to the present invention include a casting material, a forging material, a single crystal material, and the like.
  • the casting material can be formed by melting (arc melting, high frequency melting, and the like) a pre-weighed raw metal, then pouring it into a casting mould, and permitting it to solidify.
  • the casting material is a polycrystal typically having crystal grains on the order of several hundred microns to several millimeters, and has a disadvantage of readily fracturing at boundaries between the crystal grains (crystal grain boundaries), and a disadvantage of having casting defects such as shrinkage cavities and the like.
  • the forging material improves on these disadvantages.
  • the forging material is formed by subjecting a casting material to a hot forging and a recrystallization annealing. These hot forging and recrystallization annealing are typically carried out at temperatures which are higher than the temperature of the first heat treatment.
  • the temperatures at which the hot forging and the recrystallization annealing are carried out may be the same or different. It is preferable to carry out the hot forging at around 1523 to 1623 K, and the recrystallization annealing at around 1423 to 1573 K.
  • the alloy material Prior to the first heat treatment, the alloy material may be subjected to a homogenization heat treatment.
  • the homogenization heat treatment is typically carried out at a temperature which is higher than that of the first heat treatment.
  • the homogenization heat treatment is preferably carried out in the range of around 1523 to 1623 K.
  • the first heat treatment may be carried out together with the homogenization heat treatment.
  • the hot forging and the recrystallization annealing may be carried out together with the homogenization heat treatment.
  • the time period for carrying out the homogenization heat treatment is not restricted; however, for example, it is on the order of 24 to 96 hours.
  • the alloy material is a polycrystal material (casting material, forging material, or the like)
  • Ni-based compound superalloy having a multi-phase microstructure which is formed by heat-treating a casting material, a forging material, or a single crystal material, it can be confirmed that the Ni-based compound superalloy has superior mechanical properties on any of these testing.
  • Ni-based compound superalloys having multi-phase microstructures were manufactured by carrying out heat treatments, and the mechanical properties thereof were investigated.
  • the heat treatment at 1373 K corresponds to the first heat treatment (primary precipitation heat treatment) at a temperature at which the primary L1 2 phase and the A1 phase coexist (first state), and the water-quenching carried out after performing the heat treatment at 1373 K corresponds to cooling to a temperature at which the L1 2 phase and the D0 22 phase coexist.
  • the heat treatment at 1173 K or 1273 K carried out after performing the heat treatment at 1373 K corresponds to the second heat treatment (secondary precipitation heat treatment) at a temperature at which the L1 2 phase and the D0 22 phase coexist.
  • Ni, Al, Ti, and V raw metals (each having 99.9 wt% purity) in the proportions indicated in Nos. 1 to 20 in Table 1 were melted in an arc melting furnace for obtaining casting materials for prescribing the composition limits of alloys resembling the present invention.
  • the atmosphere inside the arc melting furnace the melting chamber was evacuated and then the atmosphere was replaced with an inert gas (argon gas).
  • argon gas an inert gas
  • a non-consumable tungsten electrode was employed for the electrode, and a water-cooled copper hearth was employed for the casting mold.
  • Ni, Al, Ti, and V raw metals were employed to obtain samples so as to produce Test Materials Nos. 1 to 20 having the various compositions shown in Table 1, in order to obtain a phase diagram of the basic composition system of the Ni-based compound superalloy according to the present invention.
  • a sample having a composition in which the amount of Al is in a range from more than 5 at% to 13 at% or less becomes to have a Ni-based superalloy microstructure which is A1+L1 2 phase at 1373 K, and that cooling to a temperature not more than the eutectoid temperature (1281 K) results in the occurrence of a eutectoid reaction which is A1 ⁇ L1 2 + D0 22 , D0 24 , D0 a , and formation of a dual multi-phase microstructure including a primary L1 2 phase and an (L1 2 +D0 22 , D0 24 , D0 a ) eutectoid microstructure.
  • phase coexisting microstructure which is present in a region of low Ti content, is of particular interest as a microstructure in which the constituent phases positioned at the three vertices of the phase diagram are directly equilibrated.
  • Ni 3 Al-Ni 3 Ti-Ni 3 V pseudo-ternary phase diagram at 1273 K was determined in accordance with the phase diagram shown in FIG. 1 .
  • Test Materials Nos. 1 to 20 were vacuum-sealed in quartz tubes, and each was subjected to a heat treatment at 1273 K for 7 days, and then was subjected to a water-quenching. Next, in order to form the phase diagram at 1273 K, an observation of microstructure and an analysis of each constituent phase were performed for each of Test Materials Nos. 1 to 20.
  • the observation of microstructure was carried out using OM (Optical Microscope), SEM, and TEM.
  • the analysis of the various constituent phases was carried out using SEM-EPMA (Scanning Electron Microscope-Electron Probe MicroAnalyzer). The results of this observation and analysis are shown in Table 1.
  • the Ni 3 Al-Ni 3 Ti-Ni 3 V pseudo-ternary phase diagram at 1273 K obtained from this observation and an analysis is shown in FIG. 2 .
  • composition range surrounded by points A, B, C, D, and E shown in FIG. 2 is the region in which the multi-phase microstructure or the dual multi-phase microstructure is obtained with certainty.
  • the present invention is realized by reducing the amount of V and substituting a portion of V with Nb within the above composition range.
  • point A Al: 14.0 at%, Ti: 0 at%, (V+Nb): 11.0 at%, Ni: 75 at%)
  • point B Al: 12.5 at%, Ti: 2.8 at%, (V+Nb): 9.8 at%, Ni: 75 at%)
  • point C Al: 8.0 at%, Ti: 3.8 at%, (V+Nb): 13.3 at%, Ni: 75 at%)
  • point D Al: 2.3 at%, Ti: 2.0 at%, (V+Nb): 20.8 at%, Ni: 75 at%)
  • point E Al: 2.0 at%, Ti: 0 at%, (V+Nb): 23.0 at%, Ni: 75 at%), in the Ni 3 Al-Ni 3 Ti-Ni 3 V pseudo-ternary phase diagram shown in FIG. 2
  • Test materials having the compositions shown in Table 2 below were prepared, and then the properties thereof were evaluated in order to investigate the composition and the microstructure of the Ni-based compound superalloy having the composition system according to the present invention, based on the Ni 3 Al-Ni 3 Ti-Ni 3 V pseudo-ternary phase diagram shown in FIG. 2 .
  • Each sample having the compositions shown in Table 2 was melted and subjected to a heat treatment at 1573 K (1300 °C) for 10 hours in a vacuum furnace. This treatment corresponds to a homogenizing treatment.
  • argon gas was introduced into the furnace by means of a gas fan cooling, and stirring and cooling was performed.
  • gas fan cooling was carried out at 1373 K (1100 °C) for 10 hours (first heat treatment), and then gas fan cooling was carried out at 1273 K (1000 °C) for 10 hours (second heat treatment).
  • Each test material was thus obtained and supplied for the following compression tests.
  • Test Materials Nos. 21, 22 and 28 shown in Table 2 were employed.
  • the compression test was performed using square test pieces having dimensions of 2 ⁇ 2 ⁇ 5 mm 3 under conditions where the temperature is in a range of the room temperature to 1273 K, the atmosphere is vacuum, and the strain rate is 3.3 ⁇ 10 -4 s -1 . These results are shown in FIG. 3.
  • FIG. 3 shows the 0.2% yield stresses (MPa) measured at the various temperatures of 298 K, 673 K, 773 K, 873 K 973 K, 1073 K, 1173 K, and 1273 K.
  • FIG. 4 shows the results of measurements of the amount of weight increase, including peeling, after Test Materials Nos. 21 to 28 (dimensions: 10 ⁇ 10 ⁇ 10 mm) were subjected to exposure for a specific time period at 1000 °C in air.
  • Test Material No. 10 Al: 7.5%) in Table 1; Test Material CMSX-4 (trade name, manufactured by Cannon-Muskegon Corp. (United States)) (Ti: 1.0 wt%, Co: 9.0, Cr: 6.5, Mo: 0.6, Al: 5.6, Ta: 6.5, Hf: 0.10, rare earth (Re) 3.0, with the remainder being Ni); a test material containing Al: 14% (Al: 14%, Ti: 2.5%, V: 8.5%, Ni: 75%); and a test material containing Co: 5% (Co: 5%, Al: 7.5%, Ti: 2.5%, V: 15%, Ni: 75%) are shown for comparison.
  • Test Material CMSX-4 trade name, manufactured by Cannon-Muskegon Corp. (United States)
  • Ti 1.0 wt%, Co: 9.0, Cr: 6.5, Mo: 0.6, Al: 5.6, Ta: 6.5, Hf: 0.10, rare earth (Re) 3.0, with the remainder being Ni
  • FIG. 4 there are six different time periods for exposure noted on the plot in order from the left: 24 hours, 50 hours, 100 hours, 200 hours, 400 hours, and 500 hours.
  • Test Material CMSX-4 is a well-known Ni-based superalloy.
  • the oxidation resistance properties of Test Materials Nos. 22, 23, and 28 were clearly superior to this superalloy.
  • the oxidation resistance of Test Material No. 21 was superior to that of the Test Material CMSX-4 in the case of time periods being 400 hours or less.
  • the oxidation resistances of Test Materials Nos. 24 and 25 were superior to that of the Test Material CMSX-4 in the case of time periods up to 200 hours.
  • test material containing Al: 7.5% in FIG. 4 researched by the present inventors.
  • FIG. 5 shows a photo of a metallographic structure of Test Material No. 21 (see FIG. 5(A) ), a partially enlarged view (5000-fold magnification) of the photo of the metallographic structure of the same test material (see FIG. 5(B) ), a photo of a metallographic structure of Test Material No. 22 (see FIG. 5(A) ), and a photo of a metallographic structure of Test Material No. 23 (see FIG. 5(A) ).
  • the magnification of the photos of the various test materials shown in FIG. 5(A) is 100-fold, and a 100 ⁇ m white line is recorded in each photo for showing the magnification scale.
  • those that include a multi-phase microstructure or include a dual multi-phase microstructure do not readily undergo large changes in microstructure even at high temperatures. Due to this stability, a large high-temperature strength is attained. Further, it is important to form a microstructure in which these multi-phase microstructures are formed as finely and as coherently as possible for the purpose of enabling a microstructure which has superior mechanical properties at even higher temperatures.
  • FIGS. 6 and 7 show photos of a metallographic structure of Test Material No. 28 (1000-fold magnification).
  • FIG. 8 shows a partially enlarged view (2500-fold magnification) of the photo of the metallographic structure of the same test material.
  • the fine granular portion in the photo of the metallographic structure shown in FIG. 6 is a Ll 2 -D0 24 -D0 a microstructure and occupies the majority of the microstructure in the photo.
  • this fine granular portion is enlarged at 2500-fold magnification, it could be confirmed that this portion becomes a microstructure in which numerous irregular Ni 3 Al (L1 2 ) crystal grains are spread out as shown in FIG. 8 .
  • L1 2 -D0 24 -D0 a phases exist at the boundary regions between the Ni 3 Al (L1 2 ) crystal grains in the same way as the test material shown in FIG 5 .
  • test materials to which the combined addition of Cr and Co as well as the combined addition of V and Nb is employed such as Test Material No. 28, also have a multi-phase microstructure.
  • Ni 3 Ti phase is observed in the lower left side of the photos of the metallographic structures in FIGS. 6 and 7 , it is desirable that this type of coarse plate-like Ni 3 Ti phase is not present.
  • the specific gravity of Test Material No. 21 was 7.90.
  • the specific gravity of Test Material No. 22 was 7.95.
  • the specific gravity of Test Material No. 23 was 8.07.
  • the specific gravity of Test Material No. 24 was 7.90.
  • the specific gravity of Test Material No. 25 was 7.87.
  • the specific gravity of Test Material No. 26 was 7.88.
  • the specific gravity of Test Material No. 27 was 7.8.
  • the specific gravity of Test Material No. 28 was 7.86. From these, it is clear that it is possible to achieve a reduction in weight as compared to the typical Ni-based superalloys such as MarM247 (registered trademark): 8.54 g/cm 3 and CMSX-4 (registered trademark): 8.70 g/cm 3 .
  • test materials having the compositions shown in Table 3 below were produced and the properties of those test materials were evaluated in order to investigate the effects of the addition of Al, the effects of the addition of Nb, the effects of the addition of Cr, and the effects of the addition of Co, in a Ni-based compound superalloy having the composition system according to the present invention.
  • Test materials having the compositions shown in Table 3 were produced in the same manner as the test materials shown in Table 2, and the oxidation resistance test was performed for each test material at a testing temperature of 1000 °C. These results are shown in FIG. 9 .
  • FIG. 10 shows the results of oxidation tests for Test Materials Nos. 41 to 48 shown in Table 4, which were obtained by measuring the amount of weight increase including peeling after each test material (dimensions: 10 ⁇ 10 ⁇ 10 mm) was subjected to exposure at 1000 °C for a specific time period in air.
  • the results for Test Material No. 10 Al: 7.5%) shown in the previous Table 1 are also shown for comparison.
  • Test Materials Nos. 41 to 48 demonstrated excellent oxidation resistance as compared to Test Material No. 10. More specifically, Test Materials Nos. 28, 41, 46, 42, and 47 showed, in this order, superior oxidation resistance.
  • Test Materials Nos. 51 to 58 and Test Materials Nos. 63 to 67 shown in Table 4 were conducted for Test Materials Nos. 51 to 58 and Test Materials Nos. 63 to 67 shown in Table 4, and the results of Test Materials Nos. 51 to 58 are shown in FIG. 11 , and the results of Test Materials Nos. 63 to 67 are shown in FIG. 12 . In FIGS. 11 and 12 , the results of Test Materials Nos. 10, 28, and 41 are also included.
  • Test Material No. 67 is a test material that includes Zr in the amount of 1.5 at%, in addition to prescribed amounts of Co, Cr, Al, Ti, V, and Nb.
  • Test Material No. 67 demonstrates oxidation resistance properties which are superior to those of Test Material No. 10. Accordingly, it became clear that a Ni-based compound superalloy having superior oxidation resistance can be obtained in the case of a composition system in which Zr is added to the composition according to the present invention.
  • Test Materials Nos. 28, 41, and 65 shown in Tables 2 and 4 are shown in FIG. 13 .
  • the test materials used in these tensile tests are test materials in which boron (B) was added in the amount of 100 ppm for substituting Ni. From these tests, it may be understood that, while the tensile strength of Test Materials Nos. 28, 41 and 65 was slightly less than that of the Test Material No. 10 in the temperature range from the room temperature to 700 °C, the rates of reduction in tensile strength for Test Materials Nos. 28, 41 and 65 were less than that of Test Material No. 10 in the temperature range from more than 700 °C to 1000 °C. Further, Test Materials Nos.
  • Ni-based compound superalloy according to the present invention is suitable as a structural material required to have high-temperature heat resistance, such as for an engine or the like where high-temperature strength is particularly demanded.
  • FIG. 14 shows a photo of a metallographic structure in which the surface of Test Material No. 41 is enlarged at 1000-fold magnification.
  • FIG. 15 shows a photo of a metallographic structure in which the surface of the same test material is enlarged at 5000-fold magnification.
  • the fine granular portions in the photos of the metallographic structures are the L1 2 -D0 24 -D0 a microstructures and occupy the majority (entirety) of the microstructures in the photos.
  • this fine granular portion becomes a microstructure in which numerous irregular Ni 3 Al(L1 2 ) crystal grains are spread out as shown in FIG. 15 .
  • L1 2 -D0 24 -D0 a phases exist at the boundary regions between the Ni 3 Al(L1 2 ) crystal grains in the same way as the previous test material.
  • the magnification scale indicated by the 11 white points shown in FIG. 14 is 30 ⁇ m
  • the magnification scale indicated by the 11 white points shown in FIG. 15 is 6 ⁇ m.
  • FIG. 16 shows a photo of a metallographic structure in which the surface of Test Material No. 47 is enlarged at 5000-fold magnification.
  • FIG. 17 shows a photo of a metallographic structure in which the surface of Test Material No. 48 is enlarged at 5000-fold magnification.
  • FIG. 18 shows a photo of a metallographic structure in which the surface of the Test Material No. 52 is enlarged at 2500-fold magnification.
  • FIG. 19 shows a photo of a metallographic structure in which the surface of Test Material No. 57 is enlarged at 2500-fold magnification.
  • FIG. 20 shows a photo of a metallographic structure in which the surface of Test Material No. 65 is enlarged at 50-fold magnification.
  • FIG. 65 shows a photo of a metallographic structure in which the surface of Test Material No. 65 is enlarged at 50-fold magnification.
  • FIG. 21 shows a photo of a metallographic structure in which the surface of Test Material No. 65 is enlarged at 100-fold magnification.
  • FIG. 22 shows a photo of a metallographic structure in which the surface of Test Material No. 65 is enlarged at 5000-fold magnification.
  • the magnification scales indicated by the white lines shown in FIGS. 16 and 17 are 5 ⁇ m; the magnification scales indicated by the white lines shown in FIGS. 18 and 19 are 10 ⁇ m;
  • the magnification scale indicated by the white line shown in FIG. 20 is 500 ⁇ m;
  • the fine granular portion in the photo of the metallographic structure is the L1 2 -D0 24 -D0 a microstructure and occupies the majority (entirety) of the microstructure in the photo for each of Test Materials Nos. 47, 48, 52, 57 and 65.
  • FIG. 23 shows the results of tensile testing at room temperature for test materials that were prepared by adding various amounts of boron to Test Material No. 65 for substituting Ni.
  • Test Material No. 65 for the test material shown in FIG. 23 , there was absolutely no plastic elongation, and the tensile strength was low in the case when no (0 ppm) boron was added.
  • the added amount of boron was increased to 25 ppm, the elongation increased, plastic elongation was demonstrated, and the tensile strength increased.
  • boron was added in excess of the upper limit of 1000 ppm, any plastic elongation was not demonstrated again, and the fracture strength was low. From these results, it is desirable that the amount of boron added to the superalloy according to the present invention is 0 ppm or more to 1000 ppm or less, or less than 1000 ppm from the perspective of elongation.
  • FIG. 24 shows the photo of a metallographic structure (3000-fold magnification, white line magnification scale: 5 ⁇ m) for a test material which was obtained by adding 25 ppm of boron to Test Material No. 65 and was subjected to a homogenizing treatment at 1300 °C for 3 hours.
  • FIG. 25 shows the photo of a metallographic structure (3000-fold magnification, white line magnification scale: 5 ⁇ m) for a test material which was obtained by adding 25 ppm of boron to Test Material No. 65 and was subjected to a homogenizing treatment at 1330 °C for 3 hours.
  • test materials were subjected to the homogenization treatment at 1300 °C or 1330 °C for 3 hours, and then were cooled. Thereafter, both of them were subjected to a same heat treatment which includes a process of heating including heating at 1100 °C for 10 hours and then cooling, and a process of heating including heating at 1000 °C for 10 hours and then cooling.
  • the Ni-based compound superalloy according to the present invention can be employed as a structural material where high-temperature heat resistance is required, such as for an engine.
  • the Ni-based superalloy according to the present invention has a slightly lower specific gravity than those of conventional Ni-based superalloys, and has superior in oxidation resistance and excellent tensile strength at high temperatures. As a result, an improvement in engine efficiency can be attained in the engine in which the Ni-based compound superalloy according to the present invention is employed.
EP07828466.8A 2006-09-26 2007-09-26 Auf nickel basierende verbindungssuperlegierung mit hervorragender oxidationsbeständigkeit, herstellungsverfahren dafür und hitzebeständiges konstruktionsmaterial Withdrawn EP2078763A4 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2006261569 2006-09-26
PCT/JP2007/068720 WO2008041592A1 (en) 2006-09-26 2007-09-26 Ni-based compound superalloy having excellent oxidation resistance, process for production thereof, and heat-resistant structural material

Publications (2)

Publication Number Publication Date
EP2078763A1 true EP2078763A1 (de) 2009-07-15
EP2078763A4 EP2078763A4 (de) 2014-09-03

Family

ID=39268454

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07828466.8A Withdrawn EP2078763A4 (de) 2006-09-26 2007-09-26 Auf nickel basierende verbindungssuperlegierung mit hervorragender oxidationsbeständigkeit, herstellungsverfahren dafür und hitzebeständiges konstruktionsmaterial

Country Status (4)

Country Link
US (1) US20090308507A1 (de)
EP (1) EP2078763A4 (de)
JP (1) JP5224246B2 (de)
WO (1) WO2008041592A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2447222B (en) * 2006-01-30 2011-04-13 Univ Osaka Prefect Public Corp Ni3Al-based intermetallic compound with dual multi-phase microstructure, production method thereof, and heat-resistant structural material
EP2554695A1 (de) * 2010-03-26 2013-02-06 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür
EP2554696A1 (de) * 2010-03-26 2013-02-06 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5371139B2 (ja) * 2008-03-27 2013-12-18 公立大学法人大阪府立大学 摩擦攪拌加工用ツール
JP5998325B2 (ja) * 2011-03-29 2016-09-28 公立大学法人大阪府立大学 摩擦攪拌加工用ツール及びこれを用いた摩擦攪拌加工方法
JP6607680B2 (ja) * 2015-03-03 2019-11-20 本田技研工業株式会社 Ｍｏ添加Ｎｉ基金属間化合物合金及びその製造方法
JP6861363B2 (ja) * 2017-02-27 2021-04-21 本田技研工業株式会社 Ｎｉ基金属間化合物合金及びその製造方法
CN117431432B (zh) * 2023-12-20 2024-03-12 北京北冶功能材料有限公司 一种长时氧化性能好的镍基高温合金箔材及其制备方法

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4478791A (en) * 1982-11-29 1984-10-23 General Electric Company Method for imparting strength and ductility to intermetallic phases
US4710247A (en) * 1984-09-04 1987-12-01 General Electric Company Rapidly solidified tri-nickel aluminide base alloy
JPS62274040A (ja) * 1986-05-22 1987-11-28 Mitsubishi Heavy Ind Ltd Ｎｉ基合金
GB2191505B (en) * 1986-06-09 1991-02-13 Gen Electric Dispersion strengthened single crystal alloys
US4849030A (en) * 1986-06-09 1989-07-18 General Electric Company Dispersion strengthened single crystal alloys and method
US5935349A (en) * 1994-05-21 1999-08-10 Siemens Aktiengesellschaft Intermetallic nickel-aluminum base alloy and material formed of the alloy
JP2006261569A (ja) 2005-03-18 2006-09-28 Dowa Mining Co Ltd サブマウントおよびその製造方法
JP5127144B2 (ja) * 2005-03-25 2013-01-23 公立大学法人大阪府立大学 ２重複相組織からなるＶおよびＴｉを含有するＮｉ３Ａｌ基金属間化合物及びその製造方法，耐熱構造材
JP5146935B2 (ja) * 2006-01-30 2013-02-20 公立大学法人大阪府立大学 ＶおよびＮｂを含有し，かつ，二重複相組織を有するＮｉ３Ａｌ基金属間化合物，およびその製造方法，耐熱構造材

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
See also references of WO2008041592A1 *
SOGA W ET AL: "Phase relation and microstructure in multi-phase intermetallic alloys based on Ni3Al-Ni3Nb-Ni3V pseudo-ternary alloy system", INTERMETALLICS, ELSEVIER SCIENCE PUBLISHERS B.V, GB, vol. 14, no. 2, 1 February 2006 (2006-02-01), pages 170-179, XP027905541, ISSN: 0966-9795 [retrieved on 2006-02-01] *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2447222B (en) * 2006-01-30 2011-04-13 Univ Osaka Prefect Public Corp Ni3Al-based intermetallic compound with dual multi-phase microstructure, production method thereof, and heat-resistant structural material
US8197618B2 (en) 2006-01-30 2012-06-12 Osaka Prefecture University Public Corporation Ni3A1-based intermetallic compound including V and Nb, and having dual multi-phase microstructure, production method thereof, and heat resistant structural material
EP2554695A1 (de) * 2010-03-26 2013-02-06 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür
EP2554696A1 (de) * 2010-03-26 2013-02-06 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür
EP2554695A4 (de) * 2010-03-26 2017-03-29 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür
EP2554696A4 (de) * 2010-03-26 2017-03-29 Osaka Prefecture University Public Corporation Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür

Also Published As

Publication number Publication date
WO2008041592A1 (en) 2008-04-10
US20090308507A1 (en) 2009-12-17
EP2078763A4 (de) 2014-09-03
JPWO2008041592A1 (ja) 2010-02-04
JP5224246B2 (ja) 2013-07-03

Similar Documents

Publication Publication Date Title
US9945019B2 (en) Nickel-based heat-resistant superalloy
EP2503013B1 (de) Hitzeresistente superlegierung
KR100862346B1 (ko) 니켈계 초합금 및 그로부터 제조된 터빈 구성요소
EP2078763A1 (de) Auf nickel basierende verbindungssuperlegierung mit hervorragender oxidationsbeständigkeit, herstellungsverfahren dafür und hitzebeständiges konstruktionsmaterial
EP1717326B1 (de) Werkstück aus Nickelbasislegierung, Herstellungsmethode und Turbinenteil
US8197618B2 (en) Ni3A1-based intermetallic compound including V and Nb, and having dual multi-phase microstructure, production method thereof, and heat resistant structural material
CN113166855B (zh) 镍基超合金
US11718897B2 (en) Precipitation hardenable cobalt-nickel base superalloy and article made therefrom
EP1433865A1 (de) Hochfeste Superlegierung auf Nickelbasis und Gasturbinenschaufeln
US8696833B2 (en) Ni3Al-based intermetallic compound with dual multi-phase microstructure, production method thereof, and heat resistant structural material
JP3559670B2 (ja) 方向性凝固用高強度Ｎｉ基超合金
KR20180043361A (ko) 저열팽창 초내열 합금 및 그의 제조 방법
JP2006299410A (ja) Ｎｉ３Ｓｉ−Ｎｉ３Ｔｉ−Ｎｉ３Ｎｂ系複相金属間化合物，その製造方法，高温構造材料
JPH11246924A (ja) Ｎｉ基単結晶超合金、その製造方法およびガスタービン部品
US9249488B2 (en) Ni-base dual multi-phase intermetallic compound alloy containing Nb and C, and manufacturing method for same
JP3679973B2 (ja) 単結晶Ｎｉ基耐熱合金およびタービン翼およびガスタービン
EP3957761A1 (de) Legierung
JP2003138334A (ja) 高温耐酸化性及び高温延性に優れたＮｉ基合金
EP2554695A1 (de) Intermetallische zweiphasen-verbundlegierung auf nickelbasis mit ti und c sowie herstellungsverfahren dafür
EP2620514A1 (de) Zweiphasige intermetallische verbundlegierung auf nickelbasis mit rheniumzusatz sowie herstellungsverfahren dafür
RU2356965C1 (ru) СПОСОБ ПОЛУЧЕНИЯ ЛИТЕЙНОГО ЖАРОПРОЧНОГО СПЛАВА ИЛИ ИЗДЕЛИЯ ИЗ СПЛАВА ТИПА ВКНА НА ОСНОВЕ ИНТЕРМЕТАЛЛИДА Ni3Al (ВАРИАНТЫ) И ИЗДЕЛИЯ, ПОЛУЧЕННЫЕ ЭТИМИ СПОСОБАМИ
EP4159360A1 (de) Legierungsprodukt auf kobaltbasis und verfahren zur herstellung eines legierungsprodukts auf kobaltbasis
EP4353859A1 (de) Legierungsmaterial, legierungsprodukt mit dem legierungsmaterial und maschinenvorrichtung mit dem legierungsprodukt
WO2023243146A1 (ja) Ｎｉ基合金部材の製造方法
JP2022045612A (ja) チタン合金、その製造方法およびそれを用いたエンジン部品

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20090327

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

RTI1 Title (correction)

Free format text: NI-BASED COMPOUND SUPERALLOY HAVING EXCELLENT OXIDATION RESISTANCE, METHOD FOR MANUFACTURING THE SAME, AND HEAT-RESISTANT STRUCTURAL MATERIAL

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB

DAX Request for extension of the european patent (deleted)
A4 Supplementary search report drawn up and despatched

Effective date: 20140805

RIC1 Information provided on ipc code assigned before grant

Ipc: C22C 19/05 20060101ALI20140730BHEP

Ipc: C22C 19/03 20060101AFI20140730BHEP

Ipc: C22F 1/10 20060101ALI20140730BHEP

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20141103