WO2019194972A1 - High temperature titanium alloys - Google Patents

High temperature titanium alloys Download PDF

Info

Publication number
WO2019194972A1
WO2019194972A1 PCT/US2019/023061 US2019023061W WO2019194972A1 WO 2019194972 A1 WO2019194972 A1 WO 2019194972A1 US 2019023061 W US2019023061 W US 2019023061W WO 2019194972 A1 WO2019194972 A1 WO 2019194972A1
Authority
WO
WIPO (PCT)
Prior art keywords
titanium alloy
equivalent value
titanium
molybdenum
alloy
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.)
Ceased
Application number
PCT/US2019/023061
Other languages
English (en)
French (fr)
Inventor
John V. MANTIONE
David J. Bryan
Matias GARCIA-AVILA
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.)
ATI Properties LLC
Original Assignee
ATI Properties LLC
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
Priority to KR1020207030881A priority Critical patent/KR102695594B1/ko
Priority to KR1020247026854A priority patent/KR102882057B1/ko
Priority to RU2020136110A priority patent/RU2772375C2/ru
Priority to CN201980024264.1A priority patent/CN112004949A/zh
Priority to UAA202007043A priority patent/UA127192C2/uk
Priority to KR1020257036691A priority patent/KR20250161049A/ko
Priority to EP19715321.6A priority patent/EP3775307B1/en
Priority to IL290097A priority patent/IL290097B2/en
Priority to EP22185407.8A priority patent/EP4148155A1/en
Priority to ES19715321T priority patent/ES2926777T3/es
Priority to IL324616A priority patent/IL324616A/en
Priority to MX2020010132A priority patent/MX2020010132A/es
Priority to CN202511715672.5A priority patent/CN121320784A/zh
Application filed by ATI Properties LLC filed Critical ATI Properties LLC
Priority to IL314834A priority patent/IL314834B2/en
Priority to AU2019249801A priority patent/AU2019249801B2/en
Priority to CA3095429A priority patent/CA3095429A1/en
Priority to PL19715321.6T priority patent/PL3775307T3/pl
Priority to JP2020551361A priority patent/JP7250811B2/ja
Publication of WO2019194972A1 publication Critical patent/WO2019194972A1/en
Priority to MX2025002642A priority patent/MX2025002642A/es
Priority to IL277714A priority patent/IL277714B/en
Anticipated expiration legal-status Critical
Priority to AU2024201537A priority patent/AU2024201537B2/en
Priority to AU2025203184A priority patent/AU2025203184A1/en
Ceased legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • 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
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Definitions

  • the present disclosure relates to high temperature titanium alloys. DESCRIPTION OF THE BACKGROUND OF THE TECHNOLOGY
  • Titanium alloys typically exhibit a high strength-to-weight ratio, are corrosion resistant, and are resistant to creep at moderately high temperatures.
  • Ti-5AI-4Mo-4Cr-2Sn-2Zr alloy also denoted“Ti-17 alloy,” having a composition specified in UNS R58650
  • Ti-17 alloy having a composition specified in UNS R58650
  • UNS R58650 is a commercial alloy that is widely used for jet engine applications requiring a combination of high strength, fatigue resistance, and toughness at operating temperatures up to 800°F (about 427°C).
  • titanium alloys used for high temperature applications include T ⁇ -6AI- 2Sn-4Zr-2Mo alloy (having a composition specified in UNS R54620) and Ti-3AI-8V- 6Cr ⁇ 4Mo ⁇ 4Zr alloy (also denoted“Beta-C”, having a composition specified in UNS R58640).
  • T ⁇ -6AI- 2Sn-4Zr-2Mo alloy having a composition specified in UNS R54620
  • Ti-3AI-8V- 6Cr ⁇ 4Mo ⁇ 4Zr alloy also denoted“Beta-C”
  • a titanium alloy comprises, in percent by weight based on total alloy weight: 5 5 to 6 5 aluminum; 1.9 to 2.9 tin; 1 8 to 3 0 zirconium; 4 5 to 5 5 molybdenum; 4.2 to 5.2 chromium; 0.08 to 0.15 oxygen; 0.03 to 0.20 silicon; 0 to 0.30 iron; titanium; and impurities.
  • a titanium alloy comprises, in percent by weight based on total alloy weight: 5.1 to 8.1 aluminum; 2.2 to 3.2 tin; 1.8 to 3.1 zirconium; 3.3 to 4.3 molybdenum; 3.3 to 4.3 chromium; 0.08 to 0.15 oxygen; 0.03 to 0.20 silicon; 0 to 0.30 iron; titanium; and impurities.
  • FIG. 1 is a plot illustrating a non-limiting embodiment of a method of processing a non-limiting embodiment of a titanium alloy according to the present disclosure
  • FIG. 2 is a scanning electron microscopy image (in backscatter electron mode) of a titanium alloy processed as in Figure 1 , wherein“a” identifies primary a,“b” identifies grain boundary a,“c” identifies a laths,“d” identifies secondary a, and“e” identifies a silicide;
  • FIG. 3 is a scanning electron microscopy image (in backscatter electron mode) of a comparative solution treated and aged titanium alloy, wherein“a” identifies primary a,“b” identifies boundary a,“c” identifies a laths, and“d” identifies secondary a;
  • FIG. 4 is a plot of ultimate tensile strength versus temperature for non-limiting embodiments of a titanium alloy according to the present disclosure, comparing those properties with a comparative titanium alloy and conventional titanium alloys;
  • FIG. 5 Is a plot of yield strength versus temperature for non-limiting embodiments of a titanium alloy according to the present disclosure, comparing those properties with a comparative titanium alloy and conventional titanium alloys; and
  • FIG. 6 is a scanning electron microscopy image (in backscatter electron mode) of a non-limiting embodiment of a titanium alloy according to the present disclosure, wherein“a” identifies grain boundary a,“b” identifies a laths,“c” identifies secondary a, and“d” identifies a siiicide
  • Creep occurring at a diminishing strain rate is referred to as primary creep; creep occurring at a minimum and almost constant strain rate is referred to as secondary (steady-state) creep; and creep occurring at an accelerating strain rate is referred to as tertiary creep.
  • Creep strength is the stress that will cause a given creep strain in a creep test at a given time in a specified constant environment.
  • Titanium has two ailotropic forms: a beta (“P") ⁇ phase, which has a body centered cubic (“bcc”) crystal structure; and an alpha ("a")-phase, which has a hexagonal dose packed (“hep”) crystal structure.
  • b titanium alloys have poor elevated-temperature creep strength.
  • the poor elevated-temperature creep strength is a result of the significant concentration of b phase these alloys exhibit at elevated temperatures such as, for example, 500°C.
  • b phase does not resist creep well due to its body centered cubic structure, which provides for a large number of deformation mechanisms.
  • the use of b titanium alloys has been limited.
  • One group of titanium alloys widely used in a variety of applications is the a/b titanium alloy in a/b titanium alloys, the distribution and size of the primary a particles can directly impact the creep resistance.
  • the precipitation of silicides at the grain boundaries can further improve creep resistance, but to the detriment of room temperature tensile ductility.
  • the reduction in room temperature tensile ductility that occurs with silicon addition limits the amount of silicon that can be added, typically, to 0.2% (by weight).
  • FIG. 1 is a diagram illustrating a non-limiting embodiment of a method of processing a non-limiting embodiment of a titanium alloy according to the present disclosure.
  • An embodiment of the titanium alloy according to the present disclosure includes, in percent by weight based on total alloy weight, 5 5 to 6 5 aluminum, 1.9 to 2.9 tin, 1 8 to 3 0 zirconium, 4 5 to 5 5 molybdenum, 4.2 to 5.2 chromium, 0 08 to 0 15 oxygen, 0.03 to 0.20 silicon, 0 to 0.30 iron, titanium, and impurities.
  • Another embodiment of the titanium alloy according to the present disclosure includes, in weight percentages based on total alloy weight, 5.5 to 6.5 aluminum, 2.2 to 2.6 tin, 2.0 to 2.8 zirconium,
  • titanium alloy according to the present disclosure includes, in weight percentages based on total alloy weight, 5 9 to 6.0 aluminum, 2.3 to 2 5 tin, 2 3 to 2 6 zirconium,
  • incidental elements and impurities in the alloy composition may comprise or consist essentially of one or more of nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt, and copper.
  • titanium alloys according to the present disclosure may comprise, in weight percentages based on total alloy weight, 0 to 0.05 nitrogen, 0 to 0.05 carbon, 0 to 0.015 hydrogen, and 0 up to 0.1 of each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.
  • the titanium alloy comprises an intentional addition of silicon in conjunction with certain other alloying additions to achieve an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, which the inventers have observed improves tensile strength at high temperatures.
  • “molybdenum equivalent value” or“molybdenum equivalent” may be determined as follows (wherein all elemental concentrations are in weight percentages, as indicated): Mo eq [0020] VVvette it is recognized that the mechanical properties of titanium alloys are generally influenced by the size of the specimen being tested, in non limiting embodiments according to the present disclosure, a titanium alloy comprises an aluminum equivalent value of at least 8.9, or in certain embodiments within the range of 8.0 to 9.5, a molybdenum equivalent value of 9.0 to 12 8, and exhibits an ultimate tensile strength of at least 180 ksi and at least 10% elongation at 316°C.
  • a titanium alloy comprises an aluminum equivalent value of at least 8.9, or in certain embodiments within the range of 8.0 to 9.5, a molybdenum equivalent value of 8.0 to 12.8, and exhibits a yield strength of at least 150 ksi and at least 10% elongation at 316°C.
  • a titanium alloy according to the present disclosure comprises an aluminum equivalent value of at least 6.9, or in certain embodiments within the range of 6.9 to 9.5, a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of no less than 20 hours at 427°C under a load of 60 ksi.
  • a titanium alloy according to the present disclosure comprises an aluminum equivalent value of at least 6.9, or in certain embodiments within the range of 8.0 to 9.5, a molybdenum equivalent value of 7.4 to1Q.4, and exhibits a time to 0.2% creep strain of no less than 86 hours at 427°C under a load of 60 ksi.
  • Table 1 list elemental compositions, Al eq , and Mo eq of non-limiting embodiments of a titanium alloy according to the present disclosure (“Experimental Titanium Alloy No. 1” and’’Experimental Alloy No. 2”), an embodiment of a comparative titanium alloy that does not include an intentional silicon addition, and embodiments of certain conventional titanium alloys. Without intending to be bound to any theory, it is believed that the silicon content of the Experimental Titanium Alloy No. 1 and the Experimental Titanium Alloy No. 2 listed in Table 1 may promote precipitation of one or more silicide phases. Table 1
  • each billet and the bottom of the bottom-most billet at 7 inch diameter were sampled for chemistry and b transus. Based on the intermediate billet chemistry results, 2 inch long samples were cut from the billets and“pancake”-forged on the press.
  • the pancake specimens were heat treated using the following heat treatment profile, corresponding to a solution treated and aged condition: solution treating the titanium alloy at 800°C for 4 hours; water quenching the titanium alloy to ambient
  • a“solution treating and aging (STA)” process refers to a heat treating process applied to titanium alloys that includes solution treating a titanium alloy at a solution treating temperature below the b-transus temperature of the titanium alloy.
  • the solution treating temperature is in a temperature range from about 800°C to about 860°C.
  • the solution treated alloy is subsequently aged by heating the alloy for a period of time to an aging
  • a solution treatment time ranges from about 30 minutes to about 4 hours it is recognized that in certain non-limiting embodiments, the solution treatment time may be shorter than 30 minutes or longer than 4 hours and is generally dependent upon the size and cross-section of the titanium alloy.
  • the solution treated titanium alloy is subsequently aged at an aging temperature, also referred to herein as an“age hardening temperature”, that is in the a+b two-phase field below the b transus temperature of the titanium alloy.
  • the aging temperature is in a temperature range from about 620°C to about 650°C
  • the aging time may range from about 30 minutes to about 8 hours. It is recognized that in certain non limiting embodiments, the aging time may be shorter than 30 minutes or longer than 8 hours, and is generally dependent upon the size and cross-section of the titanium alloy product form.
  • General techniques used in STA processing of titanium alloys are known to practitioners of ordinary skill in the art and, therefore, are not further discussed herein
  • Test blanks for room and high temperature tensile tests, creep tests, fracture toughness, and microstructure analysis were cut from the STA processed pancake specimens. A final chemistry analysis was performed on the fracture toughness coupon after testing to ensure accurate correlation between chemistry and mechanical properties.
  • a titanium alloy comprises, in percent by weight based on total alloy weight, 5.1 to 8.1 aluminum, 2.2 to 3.2 tin, 1.8 to 3.1 zirconium, 3.3 to 4.3 molybdenum, 3 3 to 4 3 chromium, 0.08 to 0.15 oxygen, 0.03 to 0.20 silicon, 0 to 0.30 iron, titanium, and impurities.
  • Yet another embodiment of the titanium alloy according to the present disclosure includes, in weight percentages based on total alloy weight, 5.1 to 8.1 aluminum, 2.2 to 3.2 tin,
  • a further embodiment of the titanium alloy according to the present disclosure includes, in weight percentages based on total alloy weight, 5.6 to 5 8 aluminum, 2.5 to 2.7 tin, 2.6 to 2.7 zirconium, 3.8 to 4.0 molybdenum, 3.7 to 3.8 chromium, 0.08 to 0.14 oxygen, 0.03 to 0.05 silicon, up to 0.06 iron, titanium, and impurities in non-limiting embodiments of alloys according to this disclosure, incidental elements and impurities in the alloy composition may comprise or consist essentially of one or more of nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt and copper.
  • 0 to 0 05 nitrogen, 0 to 0.05 carbon, 0 to 0 015 hydrogen, and 0 up to 0 1 each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper may be present in the titanium alloys disclosed herein.
  • an alternative titanium alloy comprises an intentional addition of silicon.
  • the alternative titanium alloy embodiments include a reduced chromium content relative to the experimental titanium alloy illustrated in and described in connection with Figures 1-3.
  • Table 1 lists the composition of a non limiting embodiment of the alternative titanium alloy (“Experimental Titanium Alloy No. 2”) having a reduced chromium content and an intentional silicon addition.
  • the titanium alloy comprises an intentional addition of silicon in conjunction with certain other alloying additions to achieve an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.3, which was observed to improve tensile strength at high temperatures.
  • a titanium alloy comprises an aluminum equivalent value of at least 6.9, or in certain embodiments within the range of 6.9 to 9.5, a molybdenum equivalent value of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 150 ksi at 316°C
  • a titanium alloy comprises an aluminum equivalent value of at least 6.9, or in certain embodiments within the range of 8.0 to 9.5, a molybdenum equivalent value of 7.4 to 12.8, and exhibits a yield strength of at least 130 ksi at 316°C.
  • a titanium alloy according to the present disclosure comprises an aluminum equivalent value of at least 6.9, or in certain embodiments within the range of 8.0 to 9.5, a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of no less than 86 hours at 427°C under a load of 60 ksi.
  • Experimental Alloy No. 2 revealed silicide precipitates (one precipitate identified as “d”). Without intending to be bound to any theory, it is believed that the silicon content of Experimental Titanium Alloy No. 2 listed in Table 1 may promote precipitation of this silicide phase.
  • alloys produced according the present disclosure and articles made from those alloys may be advantageously applied in aeronautical parts and components such as, for example, jet engine turbine discs and turbofan blades.
  • Those having ordinary skill in the art will be capable of fabricating the foregoing equipment, parts, and other articles of manufacture from alloys according to the present disclosure without the need to provide further description herein.
  • the foregoing examples of possible applications for alloys according to the present disclosure are offered by way of example only, and are not exhaustive of all applications in which the present alloy product forms may be applied. Those having ordinary skill, upon reading the present disclosure, may readily identify additional applications for the alloys as described herein.
  • a titanium alloy comprises, in percent by weight based on total alloy weight: 5.5 to 6.5 aluminum; 1.9 to 2.9 tin; 1.8 to 3.0 zirconium; 4.5 to 5.5 molybdenum; 4.2 to 5.2 chromium; 0.08 to 0.15 oxygen; 0 03 to 0.20 silicon; 0 to 0 30 iron; titanium; and impurities
  • the titanium alloy comprises, in weight percentages based on total alloy weight: 5.5 to 6.5 aluminum; 2.2 to 2.6 tin; 2.0 to 2.8 zirconium; 4.8 to 5.2 molybdenum; 4.5 to 4.9 chromium; 0.08 to 0.13 oxygen; 0.03 to 0.11 silicon; 0 to 0.25 iron; titanium; and impurities.
  • the titanium alloy comprises, in weight percentages based on total alloy weight: 5.9 to 6.0 aluminum; 2.3 to 2.5 tin; 2.3 to 2.6 zirconium; 4.9 to 5.1 molybdenum; 4.5 to 4.8 chromium; 0.08 to 0.13 oxygen; 0.03 to 0.10 silicon; up to 0.07 iron; titanium; and impurities.
  • the titanium alloy further comprises, in weight percentages based on total alloy weight: 0 to 0.05 nitrogen; 0 to 0.05 carbon; 0 to 0 015 hydrogen, and 0 up to 0.1 each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 160 ksi at 316°C.
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a yield strength of at least 140 ksi at 316°C
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of at least 20 hours at 427X under a load of 60 ksi.
  • the titanium alloy comprises an aluminum equivalent value of 8.0 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 160 ksi at 316°C.
  • the titanium alloy comprises an aluminum equivalent value of 8.0 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a yield strength of at least 140 ksi at 318°C.
  • the titanium alloy comprises an aluminum equivalent value of 8.0 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of at least 20 hours at 427°C under a load of 60 ksi.
  • the titanium alloy is prepared by a process comprising: solution treating the titanium alloy at 800°C to 880°C for 4 hours; cooling the titanium alloy to ambient temperature at a rate depending on a cross-sectional thickness of the titanium alloy; aging the titanium alloy at 620°C to 650°C for 8 hours; and air cooling the titanium alloy.
  • the present disclosure also provides a titanium alloy comprising, in percent by weight based on total alloy weight: 5 1 to 6.1 aluminum; 2.2 to 3.2 tin; 1 8 to 3.1 zirconium; 3.3 to 4.3 molybdenum; 3.3 to 4.3 chromium; 0.08 to 0.15 oxygen; 0.03 to 0.20 silicon; 0 to 0.30 iron; titanium; and impurities.
  • the titanium alloy comprises, in weight percentages based on total alloy weight: 5.1 to 6.1 aluminum; 2.2 to 3.2 tin; 2.1 to 3.1 zirconium; 3.3 to 4.3 molybdenum; 3.3 to 4.3 chromium; 0.08 to 0.15 oxygen; 0.03 to 0.11 silicon; 0 to 0.30 iron; titanium; and impurities.
  • the titanium alloy comprises, in weight percentages based on total alloy weight: 5.6 to 5.8 aluminum; 2.5 to 2.7 tin; 2.6 to 2.7 zirconium; 3.8 to 4.0 molybdenum; 3.7 to 3.8 chromium; 0.08 to 0.14 oxygen; 0.03 to 0.05 silicon; up to 0.06 iron; titanium; and impurities.
  • the titanium alloy further comprises, in weight percentages based on total alloy weight: 0 to 0.05 nitrogen; 0 to 0.05 carbon; 0 to 0.015 hydrogen; and 0 up to 0.1 each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 150 ksi at 316°C.
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a yield strength of at least 130 ksi at 316°C.
  • the titanium alloy comprises an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0 2% creep strain of no less than 86 hours at 427°C under a load of 60 ksi.
  • the titanium alloy comprises an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 150 ksi at 316°C.
  • the titanium alloy comprises an aluminum equivalent value of 8.0 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a yield strength of at least 130 ksi at 316°C
  • the titanium alloy comprises an aluminum equivalent value of 8.0 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of no less than 86 hours at 427°C under a load of 60 ksi.
  • the titanium alloy is made by a process comprising: solution treating the titanium alloy at 800°C to 860X for 4 hours; water quenching the titanium alloy to ambient temperature; aging the titanium alloy at 620°C to 650°C for 8 hours; and air cooling the titanium alloy.
  • the present disclosure also provides a method for making an alloy, comprising: solution treating a titanium alloy at 800°C to 860°C for 4 hours, wherein the titanium alloy comprises 5.5 to 6.5 aluminum, 1.9 to 2.9 tin, 1.8 to 3.0 zirconium, 4.5 to 5.5 molybdenum, 4.2 to 5.2 chromium, 0.08 to 0.15 oxygen, 0.03 to 0.20 silicon, 0 to 0.30 iron, titanium, and impurities; cooling the titanium alloy to ambient temperature at a rate depending on a cross-sectional thickness of the titanium alloy; aging the titanium alloy at 620°C to 650°C for 8 hours; and air cooling the titanium alloy.
  • the titanium alloy further comprises, in weight percentages based on total alloy weight, 0 to 0.05 nitrogen, 0 to 0.05 carbon, 0 to 0.015 hydrogen, and 0 up to 0.1 each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.
  • the present disclosure also provides a method for making an alloy, comprising: solution treating a titanium alloy at 800°C to 860°C for 4 hours, wherein the titanium alloy comprises 5.1 to 6.1 aluminum, 2.2 to 3.2 tin, 1.8 to 3.1 zirconium, 3.3 to 4.3 molybdenum, 3.3 to 4.3 chromium, 0.08 to 0.15 oxygen, 0.03 to 0.20 silicon, 0 to 0.30 iron, titanium, and impurities; cooling the titanium alloy to ambient temperature at a rate depending on a cross-sectional thickness of the titanium alloy; aging the titanium alloy at 620°C to 650°C for 8 hours; and air cooling the titanium alloy.
  • the titanium alloy further comprises, in weight percentages based on total alloy weight, 0 to 0.05 nitrogen, 0 to 0.05 carbon, 0 to 0.015 hydrogen, and 0 up to 0.1 each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Powder Metallurgy (AREA)
  • Conductive Materials (AREA)
  • Heat Treatment Of Steel (AREA)
  • Cell Electrode Carriers And Collectors (AREA)
PCT/US2019/023061 2018-04-04 2019-03-20 High temperature titanium alloys Ceased WO2019194972A1 (en)

Priority Applications (22)

Application Number Priority Date Filing Date Title
CN202511715672.5A CN121320784A (zh) 2018-04-04 2019-03-20 高温钛合金
RU2020136110A RU2772375C2 (ru) 2018-04-04 2019-03-20 Высокотемпературные титановые сплавы
CN201980024264.1A CN112004949A (zh) 2018-04-04 2019-03-20 高温钛合金
UAA202007043A UA127192C2 (uk) 2018-04-04 2019-03-20 Високотемпературний титановий сплав і спосіб його виготовлення
KR1020257036691A KR20250161049A (ko) 2018-04-04 2019-03-20 고온 티타늄 합금
EP19715321.6A EP3775307B1 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
IL290097A IL290097B2 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
EP22185407.8A EP4148155A1 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
KR1020247026854A KR102882057B1 (ko) 2018-04-04 2019-03-20 고온 티타늄 합금
IL324616A IL324616A (en) 2018-04-04 2019-03-20 High temperature titanium alloys
MX2020010132A MX2020010132A (es) 2018-04-04 2019-03-20 Aleaciones de titanio de alta temperatura.
KR1020207030881A KR102695594B1 (ko) 2018-04-04 2019-03-20 고온 티타늄 합금
ES19715321T ES2926777T3 (es) 2018-04-04 2019-03-20 Aleaciones de titanio a alta temperatura
JP2020551361A JP7250811B2 (ja) 2018-04-04 2019-03-20 高温チタン合金
AU2019249801A AU2019249801B2 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
CA3095429A CA3095429A1 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
PL19715321.6T PL3775307T3 (pl) 2018-04-04 2019-03-20 Wysokotemperaturowe stopy tytanu
IL314834A IL314834B2 (en) 2018-04-04 2019-03-20 High temperature titanium alloys
MX2025002642A MX2025002642A (es) 2018-04-04 2020-09-25 Aleaciones de titanio de alta temperatura
IL277714A IL277714B (en) 2018-04-04 2020-10-01 High temperature titanium alloys
AU2024201537A AU2024201537B2 (en) 2018-04-04 2024-03-07 High Temperature Titanium Alloys
AU2025203184A AU2025203184A1 (en) 2018-04-04 2025-05-05 High Temperature Titanium Alloys

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US15/945,037 2018-04-04
US15/945,037 US10913991B2 (en) 2018-04-04 2018-04-04 High temperature titanium alloys

Publications (1)

Publication Number Publication Date
WO2019194972A1 true WO2019194972A1 (en) 2019-10-10

Family

ID=66001357

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2019/023061 Ceased WO2019194972A1 (en) 2018-04-04 2019-03-20 High temperature titanium alloys

Country Status (13)

Country Link
US (3) US10913991B2 (https=)
EP (2) EP3775307B1 (https=)
JP (3) JP7250811B2 (https=)
KR (3) KR20250161049A (https=)
CN (2) CN121320784A (https=)
AU (3) AU2019249801B2 (https=)
CA (1) CA3095429A1 (https=)
ES (1) ES2926777T3 (https=)
IL (4) IL314834B2 (https=)
MX (2) MX2020010132A (https=)
PL (1) PL3775307T3 (https=)
UA (2) UA130626C2 (https=)
WO (1) WO2019194972A1 (https=)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10913991B2 (en) 2018-04-04 2021-02-09 Ati Properties Llc High temperature titanium alloys
US11001909B2 (en) 2018-05-07 2021-05-11 Ati Properties Llc High strength titanium alloys
US11268179B2 (en) 2018-08-28 2022-03-08 Ati Properties Llc Creep resistant titanium alloys
TWI750748B (zh) * 2020-07-27 2021-12-21 日商日本製鐵股份有限公司 金屬箔製造用鈦材及金屬箔製造用鈦材之製造方法及金屬箔製造滾筒
CN115449665B (zh) * 2022-07-08 2024-08-27 重庆大学 一种钛合金及其制备方法
US12344918B2 (en) 2023-07-12 2025-07-01 Ati Properties Llc Titanium alloys
CN117123968A (zh) * 2023-09-14 2023-11-28 西北有色金属研究院 一种船用钛合金焊丝及其短流程制备方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040231756A1 (en) * 2003-05-22 2004-11-25 Bania Paul J. High strength titanium alloy
EP1882752A2 (en) * 2005-05-16 2008-01-30 Public Stock Company "VSMPO-AVISMA" Corporation Titanium-based alloy

Family Cites Families (79)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1070589A (fr) 1952-11-19 1954-07-29 Rem Cru Titanium Alliages à base de titane
US2918367A (en) 1954-10-27 1959-12-22 Armour Res Found Titanium base alloy
GB888865A (en) 1957-03-08 1962-02-07 Crucible Steel Co America Titanium base alloys
US2893864A (en) 1958-02-04 1959-07-07 Harris Geoffrey Thomas Titanium base alloys
US3131059A (en) 1961-09-13 1964-04-28 Gen Dynamics Corp Chromium-titanium base alloys resistant to high temperatures
US3595645A (en) 1966-03-16 1971-07-27 Titanium Metals Corp Heat treatable beta titanium base alloy and processing thereof
US3565591A (en) 1969-03-28 1971-02-23 Atomic Energy Commission Titanium-zirconium-germanium brazing alloy
US3986868A (en) 1969-09-02 1976-10-19 Lockheed Missiles Space Titanium base alloy
IT949979B (it) * 1971-07-01 1973-06-11 Gen Electric Elemento in perfezionata lega di tipo alfa beta a base di titanio
US3756810A (en) 1972-04-04 1973-09-04 Titanium Metals Corp High temperature titanium alloy
US3833363A (en) 1972-04-05 1974-09-03 Rmi Co Titanium-base alloy and method of improving creep properties
SU524847A1 (ru) 1975-02-21 1976-08-15 Ордена Ленина Предприятие П/Я Р-6209 Литейный сплав на основе титана
US4309226A (en) 1978-10-10 1982-01-05 Chen Charlie C Process for preparation of near-alpha titanium alloys
JPH0686638B2 (ja) 1985-06-27 1994-11-02 三菱マテリアル株式会社 加工性の優れた高強度Ｔｉ合金材及びその製造方法
EP0243056B1 (en) 1986-04-18 1990-03-07 Imi Titanium Limited Titanium-base alloys and methods of manufacturing such alloys
JPS62267438A (ja) 1986-05-13 1987-11-20 Mitsubishi Metal Corp 低温での恒温鍛造が可能なＴｉ合金材およびこれを用いたＴｉ合金部材の製造法
DE3622433A1 (de) 1986-07-03 1988-01-21 Deutsche Forsch Luft Raumfahrt Verfahren zur verbesserung der statischen und dynamischen mechanischen eigenschaften von ((alpha)+ss)-titanlegierungen
US4738822A (en) 1986-10-31 1988-04-19 Titanium Metals Corporation Of America (Timet) Titanium alloy for elevated temperature applications
RU1593259C (ru) 1989-02-20 1994-11-15 Всероссийский научно-исследовательский институт авиационных материалов Сплав на основе титана
FR2676460B1 (fr) * 1991-05-14 1993-07-23 Cezus Co Europ Zirconium Procede de fabrication d'une piece en alliage de titane comprenant un corroyage a chaud modifie et piece obtenue.
JP3362428B2 (ja) 1993-01-11 2003-01-07 大同特殊鋼株式会社 β型チタン合金熱間成形品の処理方法
JP3395443B2 (ja) 1994-08-22 2003-04-14 住友金属工業株式会社 高クリープ強度チタン合金とその製造方法
US5472526A (en) 1994-09-30 1995-12-05 General Electric Company Method for heat treating Ti/Al-base alloys
US5698050A (en) 1994-11-15 1997-12-16 Rockwell International Corporation Method for processing-microstructure-property optimization of α-β beta titanium alloys to obtain simultaneous improvements in mechanical properties and fracture resistance
JP3959766B2 (ja) 1996-12-27 2007-08-15 大同特殊鋼株式会社 耐熱性にすぐれたＴｉ合金の処理方法
JP3409278B2 (ja) * 1998-05-28 2003-05-26 株式会社神戸製鋼所 高強度・高延性・高靱性チタン合金部材およびその製法
JP4152050B2 (ja) 1999-04-23 2008-09-17 テルモ株式会社 Ｔｉ−Ｚｒ系合金
RU2169782C1 (ru) 2000-07-19 2001-06-27 ОАО Верхнесалдинское металлургическое производственное объединение Сплав на основе титана и способ термической обработки крупногабаритных полуфабрикатов из этого сплава
CN1253272C (zh) 2001-05-15 2006-04-26 三德株式会社 用各向同性石墨模具浇铸合金的方法
CA2468263A1 (en) 2001-12-14 2003-06-26 Ati Properties, Inc. Method for processing beta titanium alloys
JP4253452B2 (ja) * 2001-12-27 2009-04-15 清仁 石田 快削Ｔｉ合金
JP2003293051A (ja) * 2002-04-01 2003-10-15 Daido Steel Co Ltd 低融点金属および高融点金属を含有するＴｉ合金の製造方法
JP3884316B2 (ja) 2002-04-04 2007-02-21 株式会社古河テクノマテリアル 生体用超弾性チタン合金
JP2004010963A (ja) 2002-06-06 2004-01-15 Daido Steel Co Ltd 高強度Ｔｉ合金およびその製造方法
US20040241037A1 (en) 2002-06-27 2004-12-02 Wu Ming H. Beta titanium compositions and methods of manufacture thereof
JP4548652B2 (ja) 2004-05-07 2010-09-22 株式会社神戸製鋼所 被削性に優れたα−β型チタン合金
EP1772528B1 (en) 2004-06-02 2013-01-30 Nippon Steel & Sumitomo Metal Corporation Titanium alloy and method of manufacturing titanium alloy material
JP2006034414A (ja) 2004-07-23 2006-02-09 Sumitomo Metal Ind Ltd シューズ用スパイク
DE102006031469B4 (de) 2006-07-05 2008-04-30 Wickeder Westfalenstahl Gmbh Verfahren zum Herstellen eines Bauteils aus einem Titan-Flachprodukt für Hochtemperaturanwendungen
CN100503855C (zh) 2006-07-27 2009-06-24 昆明冶金研究院 新型β钛合金产品、熔炼方法及热处理工艺
US20080181808A1 (en) 2007-01-31 2008-07-31 Samuel Vinod Thamboo Methods and articles relating to high strength erosion resistant titanium alloy
TW200932921A (en) 2008-01-16 2009-08-01 Advanced Int Multitech Co Ltd Titanium-aluminum-tin alloy applied in golf club head
CN101514412A (zh) 2008-02-19 2009-08-26 明安国际企业股份有限公司 应用于高尔夫球杆头的钛铝锡合金
CN101597703A (zh) 2008-06-04 2009-12-09 东港市东方高新金属材料有限公司 一种钛合金Ti-62222s及其制备方法
GB2470613B (en) 2009-05-29 2011-05-25 Titanium Metals Corp Alloy
FR2946363B1 (fr) 2009-06-08 2011-05-27 Messier Dowty Sa Composition d'alliage de titane a caracteristiques mecaniques elevees pour la fabrication de pieces a hautes performances notamment pour l'industrie aeronautique
US20100326571A1 (en) 2009-06-30 2010-12-30 General Electric Company Titanium-containing article and method for making
CN101967581B (zh) 2009-07-28 2015-03-04 中国科学院金属研究所 一种具有细片层显微组织钛合金及其制造方法
CN101886189B (zh) 2010-04-08 2012-09-12 厦门大学 一种β钛合金及其制备方法
JP5592818B2 (ja) * 2010-08-03 2014-09-17 株式会社神戸製鋼所 疲労強度に優れたα−β型チタン合金押出材およびそのα−β型チタン合金押出材の製造方法
JP5625646B2 (ja) 2010-09-07 2014-11-19 新日鐵住金株式会社 圧延幅方向の剛性に優れたチタン板及びその製造方法
US20120076686A1 (en) 2010-09-23 2012-03-29 Ati Properties, Inc. High strength alpha/beta titanium alloy
US10513755B2 (en) 2010-09-23 2019-12-24 Ati Properties Llc High strength alpha/beta titanium alloy fasteners and fastener stock
CN102952968A (zh) 2011-08-23 2013-03-06 上海航天精密机械研究所 一种颗粒强化的耐热钛合金
FR2982618B1 (fr) 2011-11-10 2014-08-01 Institut Nat Des Sciences Appliquees De Rennes Insa De Rennes Procede de fabrication d'un alliage a base de titane pour dispositifs biomedicaux
US10119178B2 (en) 2012-01-12 2018-11-06 Titanium Metals Corporation Titanium alloy with improved properties
US9957836B2 (en) 2012-07-19 2018-05-01 Rti International Metals, Inc. Titanium alloy having good oxidation resistance and high strength at elevated temperatures
JP6212976B2 (ja) 2013-06-20 2017-10-18 新日鐵住金株式会社 α＋β型チタン合金部材およびその製造方法
US10023942B2 (en) 2014-04-28 2018-07-17 Arconic Inc. Titanium alloy, parts made thereof and method of use
CN104018027B (zh) 2014-05-09 2016-10-05 中国科学院金属研究所 一种耐热钛合金及其加工制造方法和应用
UA111002C2 (uk) 2014-06-19 2016-03-10 Інститут Електрозварювання Ім. Є.О. Патона Національної Академії Наук України Високоміцний титановий сплав
US9956629B2 (en) 2014-07-10 2018-05-01 The Boeing Company Titanium alloy for fastener applications
RU2583556C2 (ru) 2014-09-16 2016-05-10 Публичное Акционерное Общество "Корпорация Всмпо-Ависма" Экономнолегированный титановый сплав
CN104532057B (zh) 2014-12-11 2017-01-04 西部超导材料科技股份有限公司 一种Ti6242钛合金及其小规格棒材的制备方法
US10094003B2 (en) 2015-01-12 2018-10-09 Ati Properties Llc Titanium alloy
US10041150B2 (en) 2015-05-04 2018-08-07 Titanium Metals Corporation Beta titanium alloy sheet for elevated temperature applications
JP6515359B2 (ja) * 2015-07-29 2019-05-22 日本製鉄株式会社 チタン複合材および熱間圧延用チタン材
TWI605129B (zh) 2015-07-29 2017-11-11 Nippon Steel & Sumitomo Metal Corp Titanium for hot rolling
TWI617670B (zh) 2015-07-29 2018-03-11 Nippon Steel & Sumitomo Metal Corp Titanium material for hot rolling
RU2610657C1 (ru) 2015-10-13 2017-02-14 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Сплав на основе титана и изделие, выполненное из него
US10502252B2 (en) 2015-11-23 2019-12-10 Ati Properties Llc Processing of alpha-beta titanium alloys
RU2614356C1 (ru) 2016-04-13 2017-03-24 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Сплав на основе титана и изделие, выполненное из него
CN105671366B (zh) 2016-04-20 2017-08-25 沈阳工业大学 一种高强高硬合金的制备方法
JP2017210658A (ja) * 2016-05-26 2017-11-30 国立大学法人東北大学 耐熱Ｔｉ合金および耐熱Ｔｉ合金材
JP6454768B2 (ja) * 2017-10-10 2019-01-16 株式会社神戸製鋼所 チタン合金β鍛造材、および、超音波探傷検査方法
US10913991B2 (en) 2018-04-04 2021-02-09 Ati Properties Llc High temperature titanium alloys
US11001909B2 (en) 2018-05-07 2021-05-11 Ati Properties Llc High strength titanium alloys
US11268179B2 (en) 2018-08-28 2022-03-08 Ati Properties Llc Creep resistant titanium alloys
RU2690257C1 (ru) 2018-11-28 2019-05-31 Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) Сплав на основе титана

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040231756A1 (en) * 2003-05-22 2004-11-25 Bania Paul J. High strength titanium alloy
EP1882752A2 (en) * 2005-05-16 2008-01-30 Public Stock Company "VSMPO-AVISMA" Corporation Titanium-based alloy

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
"Standard Test Methods for Tension Testing of Metallic Materials", 2009, ASTM INTERNATIONAL
ATI METALS: "Data Technical Data Sheet ATI 17(TM) ATI Ti-5Al-2Sn-2Zr-4Cr-4Mo Alloy", 1 January 2011 (2011-01-01), XP055599380, Retrieved from the Internet <URL:https://www.atimetals.com/Products/Documents/datasheets/titanium/alloyed/ati_Ti-17_tds_en_v1.pdf> [retrieved on 20190625] *
ATI METALS: "NIPPON STEEL & SUMITOMO METAL TECHNICAL REPORT No. 106 JULY 2014 -22", 1 July 2014 (2014-07-01), XP055599411, Retrieved from the Internet <URL:https://www.nipponsteel.com/en/tech/report/nssmc/pdf/106-05.pdf> [retrieved on 20190625] *

Also Published As

Publication number Publication date
AU2024201537A1 (en) 2024-03-28
CN112004949A (zh) 2020-11-27
IL290097A (en) 2022-03-01
JP7765959B2 (ja) 2025-11-07
MX2020010132A (es) 2020-10-19
JP7250811B2 (ja) 2023-04-03
US20190309393A1 (en) 2019-10-10
EP3775307B1 (en) 2022-08-24
AU2025203184A1 (en) 2025-05-22
AU2024201537B2 (en) 2025-05-08
KR20200132992A (ko) 2020-11-25
IL314834B2 (en) 2026-04-01
IL277714B (en) 2022-03-01
US20230090733A1 (en) 2023-03-23
CA3095429A1 (en) 2019-10-10
US12601035B2 (en) 2026-04-14
JP2021510771A (ja) 2021-04-30
AU2019249801A1 (en) 2020-11-12
KR102882057B1 (ko) 2025-11-07
IL290097B1 (en) 2024-09-01
EP4148155A1 (en) 2023-03-15
EP3775307A1 (en) 2021-02-17
AU2019249801B2 (en) 2024-04-04
US10913991B2 (en) 2021-02-09
JP7836345B2 (ja) 2026-03-26
KR102695594B1 (ko) 2024-08-14
IL324616A (en) 2026-01-01
IL314834A (en) 2024-10-01
RU2020136110A (ru) 2022-05-05
UA130626C2 (uk) 2026-04-01
US20200208241A1 (en) 2020-07-02
RU2020136110A3 (https=) 2022-05-05
KR20240125708A (ko) 2024-08-19
US11384413B2 (en) 2022-07-12
JP2022037155A (ja) 2022-03-08
IL314834B1 (en) 2025-12-01
MX2025002642A (es) 2025-04-02
ES2926777T3 (es) 2022-10-28
IL290097B2 (en) 2025-01-01
PL3775307T3 (pl) 2022-12-27
IL277714A (en) 2020-11-30
KR20250161049A (ko) 2025-11-14
UA127192C2 (uk) 2023-05-31
JP2024069237A (ja) 2024-05-21
CN121320784A (zh) 2026-01-13

Similar Documents

Publication Publication Date Title
AU2024201537B2 (en) High Temperature Titanium Alloys
AU2023282167B2 (en) Creep Resistant Titanium Alloys
RU2772375C2 (ru) Высокотемпературные титановые сплавы

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19715321

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2020551361

Country of ref document: JP

Kind code of ref document: A

ENP Entry into the national phase

Ref document number: 3095429

Country of ref document: CA

NENP Non-entry into the national phase

Ref country code: DE

ENP Entry into the national phase

Ref document number: 20207030881

Country of ref document: KR

Kind code of ref document: A

ENP Entry into the national phase

Ref document number: 2019715321

Country of ref document: EP

Effective date: 20201104

ENP Entry into the national phase

Ref document number: 2019249801

Country of ref document: AU

Date of ref document: 20190320

Kind code of ref document: A

WWG Wipo information: grant in national office

Ref document number: MX/A/2020/010132

Country of ref document: MX

WWD Wipo information: divisional of initial pct application

Ref document number: 324616

Country of ref document: IL

WWP Wipo information: published in national office

Ref document number: 324616

Country of ref document: IL

WWG Wipo information: grant in national office

Ref document number: 314834

Country of ref document: IL