EP3520915A1 - Verfahren zur herstellung eines extrudierten materials aus einer ni-basierten, extrem hitzebeständigen legierung und extrudiertes material aus einer ni-basierten, extrem hitzebeständigen legierung - Google Patents

Verfahren zur herstellung eines extrudierten materials aus einer ni-basierten, extrem hitzebeständigen legierung und extrudiertes material aus einer ni-basierten, extrem hitzebeständigen legierung Download PDF

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Publication number
EP3520915A1
EP3520915A1 EP17855276.6A EP17855276A EP3520915A1 EP 3520915 A1 EP3520915 A1 EP 3520915A1 EP 17855276 A EP17855276 A EP 17855276A EP 3520915 A1 EP3520915 A1 EP 3520915A1
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EP
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Prior art keywords
billet
heat resistant
super heat
gamma prime
extruded material
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EP17855276.6A
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English (en)
French (fr)
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EP3520915A4 (de
Inventor
Gang Han
Ichirou Kishigami
Tomoiku Ohtani
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Proterial Ltd
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Hitachi Metals Ltd
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Publication of EP3520915A1 publication Critical patent/EP3520915A1/de
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Withdrawn legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/002—Extruding materials of special alloys so far as the composition of the alloy requires or permits special extruding methods of sequences
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/21—Presses specially adapted for extruding metal
    • B21C23/212—Details
    • 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
    • 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
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • 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

Definitions

  • the present invention relates to a method of manufacturing an extruded material of a super heat resistant Ni-based alloy, and to the extruded material of the super heat resistant Ni-based alloy.
  • a "precipitation strengthening type" super heat resistant Ni-based alloy which has excellent heat resistance (high-temperature strength), has been used for a material for a component of e.g. an engine of an aircraft or a gas turbine for power generation.
  • the Ni-based alloy is strengthened by "a gamma prime ( ⁇ ') phase (hereinafter also referred to as "gamma prime” simply)".
  • the gamma prime is a precipitation strengthening phase of an intermetallic compound, for example Ni 3 Al, Ni 3 Ti, or Ni 3 (TiAl). It is effective to increase an amount of the gamma prime in order to further improve the heat resistance of the Ni-based alloy.
  • the extrusion is a method of, for example, inserting a billet heated at a hot-working temperature into a container and applying a compressive force to the billet from one end of the container to extrude the billet through a hole of a dice installed at the other end of the container to produce an extruded material.
  • a billet heated at a hot-working temperature into a container and applying a compressive force to the billet from one end of the container to extrude the billet through a hole of a dice installed at the other end of the container to produce an extruded material.
  • an ingot produced by casting a molten metal having a composition of the Ni-based alloy is used as a billet and extruding the billet being the ingot (see Patent Literature 1).
  • PATENT LITERATURE 1 JP 63-125649 A
  • An object of the present invention is to provide a method of manufacturing an extruded material of a precipitation strengthening type super heat resistant Ni-based alloy, wherein a billet is an ingot having a composition of the Ni-based alloy and including a large amount of gamma prime, as well as to provide the extruded material of the Ni-based alloy.
  • a method of manufacturing an extruded material of a super heat resistant Ni-based alloy includes: a first step of heating a billet made of the Ni-based alloy at a hot-working temperature; and a second step of inserting the billet heated at the hot-working temperature into a container, and applying a compressive force to the billet from one end of the container to extrude the billet through a hole of a dice at the other end of the container, thereby producing the extruded material of the Ni-based alloy.
  • the billet of the Ni-based alloy is an ingot produced by casting a molten metal having a composition of the Ni-based alloy.
  • an amount of precipitated gamma prime in equilibrium at 700°C is not less than 40 mol %.
  • the hot-working temperature is not lower than 1030°C but lower than a gamma prime solvus temperature of the billet of the Ni-based alloy, and the billet is extruded at an extruding speed of 10 to 300 mm/s.
  • an extruded material of a super heat resistant Ni-based alloy has a composition of a precipitation strengthening type super heat resistant Ni-based alloy.
  • an amount of precipitated gamma prime in equilibrium at 700°C is not less than 40 mol%.
  • the material has an average crystal grain size in a cross-sectional structure of not more than 20 ⁇ min in an equivalent circle diameter.
  • an extruded material having a composition of a precipitation strengthening type super heat resistant Ni-based alloy including a greater amount of gamma prime can be manufactured.
  • an extruded material of the super heat resistant Ni-based alloy having the above composition can be provided.
  • a billet is inserted into a container and a compressive force is applied to the billet from one end of the container so that the billet is extruded from a dice hole at the other end of the container. That is, "direct extrusion" is employed.
  • the method according to the present invention by this direct extrusion has following features for manufacturing an extruded material having a composition of the precipitation strengthening type super heat resistant Ni-based alloy including a large amount of gamma prime.
  • a structure of the Ni-based alloy is substantially composed of a gamma phase in which alloying elements solid-solute in a Ni matrix, and gamma prime that is a precipitation strengthening phase of an intermetallic compound typically such as Ni 3 (TiAl) or the like.
  • the Ni-based alloy is hot-worked typically at a temperature between a solid solution temperature of the gamma prime (gamma prime solvus temperature) and a solidus temperature of the Ni-based alloy (for example, at a temperature between 900°C and 1200°C). If the alloy includes a large amount of the gamma prime during the hot working, the alloy has higher deforming resistance and thus the hot-workability of the alloy is decreased.
  • An amount of gamma prime in the Ni-based alloy changes depending on a temperature thereof.
  • the equilibrium precipitation amount of gamma prime (that is an amount of gamma prime in a thermodynamic equilibrium state) increases from the minimum as a temperature decreases from the gamma prime precipitation start temperature (i.e. gamma prime solvus temperature), and the temperature dependence becomes smaller (or becomes approximately constant) below about 700°C. Therefore, an overall tendency of the precipitation amount of gamma prime can be understood based on a value at 700°C.
  • the billet of Ni-based alloy including not less than 40 mol % of precipitated gamma prime at 700°C in an equilibrium state includes a large amount of gamma prime and the gamma prime phase does not disappear in the temperature range, and the billet has been difficult to be extruded at a temperature of not lower than the gamma prime solvus temperature.
  • the present invention makes it possible to extrude the billet of the super heat resistant Ni-based alloy that has been hard to be hot-worked.
  • an amount of precipitated gamma prime in equilibrium at 700°C is preferably not less than 50 mol% , more preferably not less than 60 mol%. While it is not particularly necessary to define an upper limit, its practical value is about 75 mol%.
  • the amount of precipitated gamma prime in equilibrium can be obtained from the composition of the alloy.
  • the amount in "mol%” can be obtained by analysis through a thermodynamic equilibrium calculation. The amount can be obtained correctly and easily by using various kinds of thermodynamic equilibrium calculation software for the analysis.
  • the precipitation strengthening type super heat resistant Ni-based alloy in which an amount of precipitated gamma prime in equilibrium at 700°C is not less than 40 mol%, has a basic composition, for example, including (by mass %, hereinafter “mass %” is simply referred to as "%") C: 0.001 to 0.25%, Cr: 8.0 to 22.0%, Mo: 2.0 to 7.0%, Al: 2.0 to 8.0%, Ti: 0.4 to 7.0%, and the balance of Ni and impurities.
  • the alloy may further include one or more of Co: not more than 28.0%, W: not more than 6.0%, Nb: not more than 4.0%, Ta: not more than 3.0%, Fe: not more than 10.0%, V: not more than 1.2%, Hf: not more than 1.0%, B: not more than 0.300%, and Zr: not more than 0.30%.
  • Examples of such an alloy include Alloy 713C, UDIMET720 (UDIMET is a registered trademark of Special Metals Corporation), and IN100.
  • coarse eutectic carbides precipitate in a last solidification portion of the cast ingot.
  • more eutectic carbides are generated and as a result, the carbides become coarse.
  • the carbides becomes cracking start points during plastic working, and ductility of the alloy in the plastic working deteriorates.
  • the carbon content is preferably 0.001 to 0.25%. More preferably, the carbon content is not more than 0.10%, further more preferably not more than 0.05%, and particularly preferably not more than 0.02%. Also, the carbon content is more preferably not less than 0.003%, further more preferably not less than 0.005%, and particularly preferably not less than 0.008%.
  • Chromium (Cr) improves oxidation resistance and corrosion resistance. However, excessive amount of Cr forms a brittle phase, such as a ⁇ phase, to deteriorate strength and hot-workability. Therefore, the Cr content is preferably 8.0 to 22.0%. More preferably, the Cr content is not less than 9.0%, further more preferably not less 9.5%, and particularly preferably not less 10.0%. Also, the Cr content is more preferably not more than 18.0%, further more preferably not more than 16.0%, and particularly preferably not more than 14.0%.
  • Molybdenum (Mo) contributes to solid-solution strengthening of a matrix, and has an effect of improving high-temperature strength. However, excessive amount of Mo forms an intermetallic compound phase and deteriorates high-temperature strength. Therefore, the Mo content is preferably 2.0 to 7.0%. More preferably, the Mo content is not less than 2.5%, further more preferably not less than 3.0%. Also, the Mo content is more preferably not more than 6.0%, further more preferably not more than 5.5%, and particularly preferably not more than 5.0%.
  • the Al content is preferably 2.0 to 8.0%. More preferably, the Al content is not less than 2.5%, further more preferably not less than 3.5%, and particularly preferably not less than 4.5%. Also, the Al content is more preferably not more than 7.5%, further more preferably not more than 7.0%, and particularly preferably not more than 6.5%.
  • Titanium (Ti) forms, similar to Al, the gamma prime and increases high-temperature strength through forming of the gamma prime.
  • an excessive amount of Ti forms a harmful ⁇ (eta) phase and deteriorates hot-workability. Therefore, the Ti content is preferably 0.4 to 7.0%. More preferably, the Ti content is not less than 0.45%, and further more preferably not less than 0.5%. Also, the Ti content is more preferably not more than 5.0%, further more preferably not more than3.0%, and particularly preferably not more than1.0%.
  • Co Co
  • the Co content is preferably up to 28.0%, more preferably up to 18.0%, further more preferably up to 16.0%, and particularly preferably up to 13.0%. If Co is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of Co is 0%. Furthermore, the Co content may be less than 1.0%.
  • the Co content is preferably not less than 1.0%, more preferably not less than 3.0%, further more preferably not less than 8.0%, and particularly preferably not less than 10.0%.
  • Tungsten (W) is an optional element that contributes to solid-solution strengthening of a matrix, similar to Mo.
  • W is an optional element that contributes to solid-solution strengthening of a matrix, similar to Mo.
  • the W content is preferably not more than 6.0%, more preferably not more than 5.5%, further more preferably not more than 5.0%, and particularly preferably not more than 4.5%. If W is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of W is 0%.
  • the W content may be less than 1.0%, further less than 0.8%.
  • the W content is preferably not less than 1.0%. Addition of both W and Mo is more effective in achieving the solid-solution strengthening. In the case where the alloy includes W in combination with Mo, the W content is preferably not less than 0.8%.
  • Niobium (Nb) is an optional element that forms the gamma prime and increases high-temperature strength through solid-solution strengthening of the gamma prime, similar to Al and Ti.
  • Nb content is preferably not more than 4.0%, more preferably not more than 3.5%, further more preferably not more than 3.0%, and particularly preferably not more than 2.5%. If Nb is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of Nb is 0%. Then, the Nb content is less than 0.5%.
  • the Nb content is preferably not less than 0.5%, more preferably not less than 1.0%, further more preferably not less than 1.5%, and particularly preferably not less than 2.0%.
  • Tantalum (Ta) is an optical element that forms the gamma prime and increases high-temperature strength through solid-solution strengthening of the gamma prime, similar to Al and Ti.
  • excessive amount of Ta makes the gamma prime phase unstable and coarse at a high temperature.
  • Ta forms a harmful ⁇ (eta) phase to deteriorate hot-workability. Therefore, even when the alloy includes Ta, the Ta content is preferably not more than 3.0%, more preferably not more than 2.5%, further more preferably not more than 2.0%, and particularly preferably not more than 1.5%.
  • the lower limit of Ta is 0%. Then, the Ta content is less than 0.3%.
  • the Ta content is preferably not less than 0.3%, more preferably not less than 0.5%, further more preferably not less than 0.7%, and particularly preferably not less than 1.0%.
  • Fe is an optional element that can be included in the alloy instead of expensive Ni or Co and is effective in reducing the cost.
  • excessive amount of Fe forms a brittle phase such as a ⁇ phase to deteriorate strength and hot-workability. Therefore, even when the alloy includes Fe, the Fe content is preferably not more than 10.0%, more preferably not more than 8.0%, further more preferably not more than 6.0%, and particularly preferably not more than 3.0%. If Fe is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of Fe is 0%. Then, the Fe content is less than 0.1%.
  • an amount of Fe that is instituted of Ni or Co is preferably not less than 0.1%, more preferably not less than 0.4%, further more preferably not less than 0.6%, and particularly preferably not less than 0.8%.
  • Vanadium (V) is an optical element that is effective for solid-solution strengthening of a matrix and generation of carbide to increase grain boundary strength.
  • V vanadium
  • the V content is preferably not more than 1.2%, more preferably not more than 1.0%, further more preferably not more than 0.8%, and particularly preferably not more than 0.7%. If V is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of V is 0%. Then, the V content is less than 0.1%.
  • the V content is preferably not less than 0.1%, more preferably the V content 0.2%, further more preferably the V content 0.3%, and particularly preferably the V content 0.5%.
  • Hafnium (Hf) is an optional element that is effective for improving oxidation resistance of the alloy and generation of carbide to increase grain boundary strength.
  • Hf content is preferably not more than 1.0%, more preferably not more than 0.7%, further more preferably not more than 0.5%, and particularly preferably not more than 0.3%. If Hf is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of Hf is 0%. Then, the Hf content is less than 0.02%.
  • the Hf content is preferably not less than 0.02%, more preferably not less than 0.05%, further more preferably not less than 0.1%, and particularly preferably not less than 0.15%.
  • B Boron
  • B is an optional element that can strengthen grain boundaries and improve creep strength and ductility.
  • excessive amount of B drastically decreases a melting point of the alloy and forms coarse boride to deteriorate workability. Therefore, even when the alloy includes B, the B content is preferably not more than 0.300%, more preferably not more than 0.100%, further more preferably not more than 0.050%, and particularly preferably not more than 0.020%. If B is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of B is 0%. Then, the B content is less than 0.001%.
  • the B content is preferably not less than 0.001%, more preferably not less than 0.003%, further more preferably not less than 0.005%, and particularly preferably not less than 0.007%.
  • Zirconium is an optional element that has an effect of improving grain boundary strength, similar to B.
  • excessive amount of Zr drastically decreases a melting point of the alloy and decreases high-temperature strength and hot-workability. Therefore, even when the alloy includes Zr, the Zr content is preferably not more than 0.30%, more preferably not more than 0.25%, further more preferably not more than 0.20%, and particularly preferably not more than 0.15%. If Zr is not intentionally added (i.e. it is inevitable impurity in a raw material), the lower limit of Zr is 0%. Then, the Zr content is less than 0.001%.
  • the Zr content is preferably not less than 0.001%, more preferably not less than 0.005%, further more preferably not less than 0.01%, and particularly preferably not less than 0.03%.
  • the billet that is to be extruded in the method according to present invention is "an ingot" produced by casting a molten metal having a composition of the precipitation strengthening type super heat resistant Ni-based alloy which includes gamma prime in an equilibrium precipitation amount at 700°C of not less than 40 mol%.
  • the ingot having the above composition tends to segregate during solidification in the casting and a number of brittle phases are formed in the solidified cast structure.
  • the billet is subject to cracks from grain boundaries of the cast structure during the extrusion, and thus it has been difficult to produce the extruded material having a fine recrystallization structure.
  • the method in accordance with the present invention makes it possible to successfully extrude such ingot of the Ni-based alloy as the billet.
  • a hot-working temperature of the ingot, as the billet is not lower than1030°C but lower than "the gamma prime solvus temperature" of the Ni-based alloy.
  • the present inventors have found that it is effective to consider heat generated from the deformation as well as reduction of the deforming resistance for improving the possibility of extrusion of the billet. Since the deforming resistance of the billet, from which the working heat can be generated, very sensitively depends on a hot-working temperature, it is important to manage the hot-working temperature.
  • the hot-working temperature is set to "not lower than 1030°C". Thereby the working heat can be used effectively. Even when the gamma prime exists in the billet (i.e. at the hot-working temperature below the gamma prime solvus temperature), the extrusion ability of the billet can be wholly improved.
  • the hot-working temperature is preferably not lower than 1050°C, more preferably not lower than 1080°C, further more preferably not lower than 1100°C, and particularly preferably not lower than 1130°C.
  • the hot-working temperature achieves the gamma prime solvus temperature
  • recrystallized grains grow to form a coarse recrystallization structure.
  • the extruded material becomes brittle. It is important that, when the hot-working temperature is higher than the gamma prime solvus temperature, the billet of the Ni-based alloy, in which the amount of precipitated gamma prime in equilibrium at 700°C is not less than 40 mol %, becomes to have no ductility in a very narrow temperature range between the gamma prime solvus temperature and the solidus temperature. Thus, the extrusion is difficult. Therefore, the hot-working temperature is determined at a temperature lower than "the gamma prime solvus temperature" of the billet of the Ni-based alloy.
  • the hot-working temperature is preferably not higher than 1180°C, more preferably not higher than 1170°C, and further more preferably not higher than 1150°C.
  • the gamma prime solvus temperature is determined by the composition of the Ni-based alloy.
  • the gamma prime solvus temperature can be obtained by analysis through a thermodynamic equilibrium calculation.
  • Various type of thermodynamic equilibrium calculation software can be used for the analysis to obtain the gamma prime solvus temperature correctly and easily.
  • the billet i.e. the ingot is extruded at an extruding speed of 10 to 300 mm/s.
  • FIG. 3 shows a result of tensile tests at 1150°C of Alloy 713C (an amount of precipitated gamma prime in equilibrium at 700°C is 69 mol%, and gamma prime solvus temperature is 1185°C).
  • an amount of precipitated gamma prime in equilibrium at 700°C is 69 mol%, and gamma prime solvus temperature is 1185°C.
  • reduction of area increases as strain rate increases.
  • This effective phenomenon similarly applies to the extrusion.
  • the ductility of the Ni-based alloy is improved by increasing the extruding speed in the temperature range lower than the gamma prime solvus temperature. The extruding speed is increased, i.e.
  • This extruding speed may correspond to the moving speed of a stem which pushes the billet in the extrusion.
  • the extruding speed is preferably not less than 12 mm/s, more preferably not less than 14 mm/s.
  • a mechanism of improving the ductility of the billet by increasing the extruding speed is presumed as follows. It is considered that the gamma prime in the Ni-based alloy interrupts dynamic recrystallization during the hot working and smooth deformation of the Ni-based alloy. Therefore, it is necessary to introduce higher strain energy so as to generate the dynamic recrystallization to cause the smooth deformation during the hot working of the Ni-based alloy in which the amount of the precipitated gamma prime in equilibrium at 700°C is not less than 40 mol%. It is considered that the increase of the strain rate (extruding speed) during the hot working makes the strain energy introduced into the Ni-based alloy be less relieved, and causes the sufficient dynamic recrystallization. Therefore, the smooth deformation of the Ni-based alloy becomes possible.
  • the extruding speed is determined to be not more than"300 mm/s.
  • the increase of the extruding speed is advantageous for improving the ductility of the billet, when the extruding speed is greater than a certain value, the degree of improving the ductility slows down and is saturated.
  • the upper limit of the extruding speed i.e. moving speed of the stem
  • the extruding speed is preferably not more than 280 mm/s, more preferably not more than 260 mm/s. Even if the extruding speed is not more than 100 mm/s or not more than 90 mm/s, the effect of the present invention can be obtained.
  • the billet is preferably an ingot that has been heat-treated.
  • the present invention even if an as-cast ingot is used as the billet, it can be extruded. However, by heating the as-cast ingot, segregation in the ingot for the billet can be reduced to improve high extrusion workability.
  • the heat treatment is preferably conducted in a temperature range around the gamma prime solvus temperature of the Ni-based alloy. Specifically, the temperature range of 1170 to 1250°C is preferable. It is more preferably not higher than1240°C and further more preferably not higher than 1230°C.
  • Too low heat treatment temperature leads to reduction of the effect.
  • the heat treatment temperature is higher, for example, far above the gamma prime solvus temperature, coarse grains of the gamma phase that have been formed at the casting grows further to make grain boundaries in the billet more brittle. It is supposed that the embrittlement is caused by segregation of trace elements in the grain boundaries in the billet.
  • a time period of the heat treatment time may be that of a typical soaking process for various kinds of ingots.
  • the time period is 3 to 30 hours, preferably not shorter than 10 hours.
  • the billet is the as-cast ingot having the composition of the precipitation strengthening type super heat resistant Ni-based alloy in which the amount of precipitated gamma prime in equilibrium at 700°C is not less than 40 mol%, it can be successfully extruded by employing the above hot-working temperature and extruding speed. Even if an average grain size in a cross-section may be large, such as not less than 6.3 mm, or even not less than 7 mm in equivalent circle diameter (practically, upper limit is about 30 mm), the extrusion is possible.
  • the extruded material manufactured by the extrusion can have a fine recrystallization structure, for example.
  • the average grain size in the cross-sectional structure of the extruded material may be not more than 20 ⁇ m in equivalent circle diameter (practically, lower limit is about 2 ⁇ m). Furthermore, it may be not more than 15 ⁇ m, or even not more than 10 ⁇ m, in equivalent circle diameter.
  • the average grain size in the cross-sectional structure of the extruded material can be made fine to 1/400, further to 1/1000, of the average grain size in the cross-sectional structure of the billet.
  • the billet and the extruded material are halved in an extraction direction, and a cross-sectional structure at a position of a central axis of the cross section (that is, a cross section including the central axis in the longitudinal direction of the billet or the extruded material) can be observed. Then, equivalent circle diameters of crystal grains are measured in the cross section at the position of the central axis, and an average grain size is obtained.
  • the extrusion ratio (a cross-sectional area of the billet / a cross-sectional area of the extruded material) of the extrusion may be that in typical extrusion.
  • the extruding ratio may be 2 to 40.
  • the extruding ratio may be not more than 30, or not more than 20.
  • the extruded material produced in this manner has, for example, a shape of a wire.
  • the wire material has a diameter of, for example, 1.4 to 20 mm.
  • the extruded material may be subjected to hot working or cold working to produce a thin wire with a diameter of 1 to 3 mm.
  • Molten metals having predetermined compositions were produced by vacuum melting and were cast to produce ingots with a diameter of 110 mm and a length of 120 mm.
  • each ingot was heat-treated in a furnace in an atmosphere at 1200°C for 20 hours, and then cooled in the furnace.
  • the heat-treated ingots were machined into a shape with a diameter of 82 mm and a length of 105 mm to produce billets for extrusion.
  • billets for measuring average grain size were produced.
  • a cross section of each billet at a position of the central axis in the longitudinal direction of the billet was etched with a ferric chloride solution and it was observed with an optical microscope at a magnification of 10. In a field of view of 50 mm ⁇ 40 mm, the image analysis was performed to measure an average grain size.
  • the average grain size in equivalent circle diameter was about 10 mm.
  • Table 1 shows the compositions of the molten metals (that is, compositions of billet). Since Co, W, Ta, V, and Hf are impurity elements, the compositions satisfied Co ⁇ 28.0%, W ⁇ 6.0%, Ta ⁇ 3.0%, V ⁇ 1.2%, and Hf ⁇ 1.0%,.
  • gamma prime solvus temperatures and amounts of gamma prime precipitated in equilibrium at 700°C were obtained with use of thermodynamic equilibrium calculation software "JMatPro (Version 8.0.1, Sente Software Ltd.)".
  • compositions (mass%) C Cr Mo Al Ti Nb Fe Zr B Ni* 1 0.0127 12.20 4.51 5.85 0.61 2.04 1.05 0.09 0.0090 balance 2 0.0172 12.00 4.51 5.86 0.59 2.02 1.06 0.09 0.0089 balance 3 0.0135 11.97 4.50 5.86 0.59 2.00 1.06 0.09 0.0095 balance 4 0.0138 11.98 4.50 5.88 0.59 2.01 1.05 0.09 0.0097 balance 5 0.0147 12.03 4.56 5.92 0.61 2.06 1.06 0.09 0.0091 balance 6 0.0159 12.20 4.48 5.82 0.59 1.99 1.07 0.09 0.0092 balance *including impurities (Co ⁇ 28.0%, W ⁇ 6.0%, Ta ⁇ 3.0%, V ⁇ 1.2%, and Hf ⁇ 1.0%)
  • the materials Nos. 1 to 4 have the composition of the precipitation strengthening type super heat resistant Ni-based alloy in which the amount of gamma prime precipitated in equilibrium at 700°C is not less than 40 mol% were produced by extruding the billets (ingots) at the hot-working temperature and the extruding speed according to the present invention.
  • Table 2 shows that the materials Nos. 1 to 4 were not subject to cracking.
  • the materials Nos. 1 to 4 had fine recrystallization structure.
  • the material No. 5 was extruded at a hot-working temperature higher than the gamma prime solvus temperature.
  • its billet had low ductility in the extrusion and was cracked.
  • the billet of the material No. 6 was extruded with a low extruding speed and has less ductility in the extrusion, thereby it was cracked.
  • the dynamic recrystallization did not occur sufficiently and a non-recrystallized structure existed.
  • FIG. 1 shows a cross-sectional macro structure of a billet at a reduced cross-sectional area portion during the extrusion in the material No. 4.
  • a cast structure 1 having a coarse grain size of about 10 mm at the position of the reduced cross-sectional area portion has changed into a fine recrystallization structure 2 after the extrusion (after the cross sectional area was reduced).
  • FIG. 2 shows an EBSD image of the cross-sectional microstructure of the material No. 4.
  • a scan step was 0.1 ⁇ m and an orientation difference of not less than 15° was defined as a grain boundary. This microstructure was observed at a position of the central axis in a cross section halved in the longitudinal direction of the material.
  • the material No. 4 in accordance with the invention had a fine recrystallization structure with an average grain size of about 2.1 ⁇ m in an equivalent circle diameter.
  • the materials Nos. 1 to 3 had fine recrystallization structures with an average grain size of about not more than 20 ⁇ m in an equivalent circle diameter, as similarly measured of the average grain size, since they were extruded at a higher hot-working temperature,
  • Another material was produced by performing extrusion at a lower hot-working temperature of 1025°C and under the same conditions as that of the extruded material No. 1 except the hot-working temperature. As a result, the material could not have fine recrystallization structure since a deforming resistance of the billet increased drastically and sufficient heat was not generated in the extrusion.

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EP17855276.6A 2016-09-30 2017-05-30 Verfahren zur herstellung eines extrudierten materials aus einer ni-basierten, extrem hitzebeständigen legierung und extrudiertes material aus einer ni-basierten, extrem hitzebeständigen legierung Withdrawn EP3520915A4 (de)

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CN112813294B (zh) * 2020-12-30 2022-03-08 北京钢研高纳科技股份有限公司 高强高弹Ni-Cr-Co-W基合金丝材及其制备方法
JP2022160167A (ja) * 2021-04-06 2022-10-19 大同特殊鋼株式会社 耐熱合金部材、これに用いる素材及びこれらの製造方法
EP4212639A1 (de) * 2022-01-18 2023-07-19 Garrett Transportation I Inc. Nickelbasierte legierung und turbinenrad damit
CN118272628A (zh) * 2024-03-12 2024-07-02 北京钢研高纳科技股份有限公司 一种大型涡轮盘锻件及其制备方法

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US3824097A (en) * 1972-12-19 1974-07-16 Federal Mogul Corp Process for compacting metal powder
US4832112A (en) * 1985-10-03 1989-05-23 Howmet Corporation Method of forming a fine-grained equiaxed casting
US4769087A (en) 1986-06-02 1988-09-06 United Technologies Corporation Nickel base superalloy articles and method for making
US4820353A (en) * 1986-09-15 1989-04-11 General Electric Company Method of forming fatigue crack resistant nickel base superalloys and product formed
US5759305A (en) * 1996-02-07 1998-06-02 General Electric Company Grain size control in nickel base superalloys
US6908519B2 (en) * 2002-07-19 2005-06-21 General Electric Company Isothermal forging of nickel-base superalloys in air
CA2723526C (en) * 2008-05-22 2013-07-23 Sumitomo Metal Industries, Ltd. High-strength ni-based alloy tube for nuclear power use and method for manufacturing the same
US9267184B2 (en) * 2010-02-05 2016-02-23 Ati Properties, Inc. Systems and methods for processing alloy ingots
CN105283574B (zh) * 2013-03-28 2017-05-03 日立金属株式会社 Ni基超耐热合金及其生产方法
US10266926B2 (en) * 2013-04-23 2019-04-23 General Electric Company Cast nickel-base alloys including iron
CN104060203B (zh) * 2014-06-25 2016-04-20 攀钢集团江油长城特殊钢有限公司 一种合金挤压棒材的生产工艺
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CN109789457A (zh) 2019-05-21
JPWO2018061317A1 (ja) 2019-04-11

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