High-temperature titanium alloy

Abstract

To provide titanium alloys having improved creep resistance and / or tensile strength at high temperatures.SOLUTION: A non-limiting embodiment of a titanium alloy comprises, in percent by weight based on the total alloy weight: 5.1 to 6.5 aluminum; 1.9 to 3.2 tin; 1.8 to 3.1 zirconium; 3.3 to 5.5 molybdenum; 3.3 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 non-limiting embodiment of 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 12.8, which has been observed to improve tensile strength at high temperatures.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] This disclosure relates to high-temperature titanium alloys. [Background technology]

[0002] Titanium alloys typically exhibit high strength-to-weight ratio, corrosion resistance, and resistance to creep at moderate temperatures. For example, Ti-5Al-4Mo-4Cr-2Sn-2Zr alloy (also known as "Ti-17 alloy" with the composition specified in UNS R58650) is a commercially available alloy widely used in jet engine applications requiring a combination of high strength, fatigue resistance, and toughness at operating temperatures up to 800°F (approximately 427°C). Other examples of titanium alloys used in high-temperature applications include Ti-6Al-2Sn-4Zr-2Mo alloy (with the composition specified in UNS R54620) and Ti-3Al-8V-6Cr-4Mo-4Zr alloy (with the composition specified in UNS R58640, also known as "Beta-C"). However, these alloys have limitations in creep resistance and / or tensile strength at high temperatures. This has created a need for titanium alloys with improved creep resistance and / or tensile strength at high temperatures. [Overview of the project]

[0003] According to one non-limiting aspect of this disclosure, the titanium alloy comprises, in weight percent based on the total weight of the alloy, 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.

[0004] According to yet another non-limiting aspect of this disclosure, the titanium alloy comprises, in weight percent based on the total weight of the alloy, 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.

[0005] The features and advantages of the alloys, articles, and methods described herein can be better understood by referring to the accompanying drawings. [Brief explanation of the drawing]

[0006] [Figure 1] This plot illustrates non-limiting embodiments of the method for processing non-limiting embodiments of titanium alloys according to the present disclosure. [Figure 2] Figure 1 shows scanning electron microscope images (backscattered electron modes) of the processed titanium alloy, where "a" identifies primary α, "b" identifies grain boundary α, "c" identifies α lath, "d" identifies secondary α, and "e" identifies silicide. [Figure 3] These are scanning electron microscope images (backscattered electron modes) of titanium alloys that have undergone comparative solution treatment and aging. In the figures, "a" identifies primary α, "b" identifies boundary α, "c" identifies α lath, and "d" identifies secondary α. [Figure 4] This figure shows a plot of ultimate tensile strength versus temperature for a non-limiting embodiment of a titanium alloy according to the present disclosure, comparing these properties with those of a comparative titanium alloy and a conventional titanium alloy. [Figure 5] This figure shows a plot of yield strength versus temperature for non-limiting embodiments of titanium alloys according to the present disclosure, comparing their properties with those of a comparative titanium alloy and a conventional titanium alloy. [Figure 6] These are scanning electron microscope images (backscattered electron modes) of non-limiting embodiments of titanium alloys according to the present disclosure, where "a" identifies grain boundary α, "b" identifies α lath, "c" identifies secondary α, and "d" identifies silicide. [Modes for carrying out the invention]

[0007] Readers will understand, in consideration of the following detailed descriptions of certain non-limiting embodiments provided herein, as well as any other details beyond those stated above.

[0008] In the non-limiting embodiments of this specification, unless otherwise specified or in the examples, all numerical values ​​representing quantities or properties shall be understood to be modified in all cases by the term “approximately.” Therefore, unless otherwise indicated, any numerical parameters described in the following specification are approximations that may vary depending on the desired properties sought to be obtained in the materials and methods of this disclosure. At a minimum, and without any intent to limit the application of the doctrine of equivalents to the claims, each numerical parameter should be interpreted in light of at least the number of significant figures reported and by the application of the usual rounding method. All scopes described herein include the endpoints described unless otherwise stated.

[0009] Any patent, publication, or other disclosure incorporated herein by reference, in whole or in part, is incorporated herein to the extent that the incorporated content does not conflict with existing definitions, descriptions, or other disclosures described herein. To this end, to the extent necessary, disclosures described herein take precedence over any conflicting content incorporated herein by reference. Any content or portion incorporated herein by reference that conflicts with existing definitions, descriptions, or other disclosures described herein is incorporated to the extent that it does not create a conflict between the incorporated content and the existing disclosures.

[0010] In high-temperature environments, articles and components may suffer from creep. As used herein, "high temperature" refers to temperatures exceeding approximately 100°F (approximately 37.8°C). Creep is a time-dependent strain that occurs under stress. Creep occurring at a decreasing strain rate is called primary creep; creep occurring at a minimum and nearly constant strain rate is called secondary (steady-state) creep; and creep occurring at an accelerating strain rate is called tertiary creep. Creep strength is the stress that produces a given creep strain in a creep test at a given time under specific constant conditions.

[0011] The creep resistance behavior of titanium and titanium alloys under high temperatures and sustained loads depends primarily on the characteristics of their microstructure. Titanium has two allotropes: the beta ("β") phase, which has a body-centered cubic ("bcc") crystal structure, and the alpha ("α") phase, which has a hexagonal close-packed ("hcp") crystal structure. Generally, β titanium alloys have insufficient high-temperature creep strength. This insufficient high-temperature creep strength is a result of the significant concentration of the β phase exhibited by these alloys at high temperatures, such as 500°C. The β phase, due to its body-centered cubic structure, does not withstand creep sufficiently and dictates numerous deformation mechanisms. As a result of these drawbacks, the use of β titanium alloys is limited.

[0012] One group of titanium alloys widely used in various applications is the α / β titanium alloy. In α / β titanium alloys, the distribution and size of primary α particles can directly affect creep resistance. According to various published reports on α / β titanium alloys containing silicon, silicide precipitation at grain boundaries can further improve creep resistance but causes a loss of room-temperature tensile ductility. The decrease in room-temperature tensile ductility caused by the addition of silicon limits the amount of silicon that can be added to typically 0.2% (by weight).

[0013] This disclosure relates in part to an alloy that addresses certain limitations of conventional titanium alloys. Figure 1 is a diagram illustrating a non-limiting embodiment of a method for processing a non-limiting embodiment of a titanium alloy according to this disclosure. Embodiments of a titanium alloy according to this disclosure include, in weight percentage based on the total weight of the alloy, 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 this disclosure contains, by weight percentage based on the total weight of the alloy, 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. Another embodiment of the titanium alloy according to this disclosure contains, by weight percentage based on the total weight of the alloy, 5.9 to 6.0g of aluminum, 2.3 to 2.5g of tin, 2.3 to 2.6g of zirconium, 4.9 to 5.1g of molybdenum, 4.5 to 4.8g of chromium, 0.08 to 0.13g of oxygen, 0.03 to 0.10g of silicon, up to 0.07g of iron, titanium, and impurities. In non-limiting embodiments of the alloy according to this disclosure, elements and impurities incidentally present in the alloy composition may include, or be essentially composed of, one or more nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt, and copper. Certain non-limiting embodiments of the titanium alloys described herein may include, in weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0014] In certain non-limiting embodiments of the present titanium alloy, the titanium alloy includes an intentional addition of silicon in combination with the addition of certain other alloys so as to achieve aluminum equivalent values of 6.9 to 9.5 and molybdenum equivalent values of 7.4 to 12.8, where the inventors have observed an improvement in tensile strength at high temperatures. As used herein, the "aluminum equivalent value" or "aluminum equivalence" (Al eq ) can be determined as follows (where, as shown, all element concentrations are in weight percentages): Al eq = Al (重量%) + (1 / 6)×Zr (重量%) + (1 / 3)×Sn (重量%) + 10×O (重量%) . As used herein, the "molybdenum equivalent value" or "molybdenum equivalence" (Mo eq ) can be determined as follows (where, as shown, all element concentrations are in weight percentages): Mo eq = Mo (重量%) + (1 / 5)×Ta (重量%) + (1 / 3.6)×Nb (重量%) + (1 / 2.5)×W (重量%) + (1 / 1.5)×V (重量%) + 1.25×Cr (重量%) + 1.25×Ni (重量%) + 1.7×Mn (重量%) + 1.7×Co (重量%) + 2.5×Fe (重量%) .

[0015] It is generally recognized that the mechanical properties of titanium alloys are affected by the size of the test specimens being tested. However, in non-limiting embodiments according to the present disclosure, the titanium alloy has an aluminum equivalent value included in the range of at least 6.9 or, in certain embodiments, 8.0 to 9.5, a molybdenum equivalent value of 9.0 to 12.8, and exhibits an ultimate tensile strength of at least 160 ksi and an elongation of at least 10% at 316 °C. In other non-limiting embodiments according to the present disclosure, the titanium alloy has an aluminum equivalent value included in the range of at least 6.9 or, in certain embodiments, 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 an elongation of at least 10% at 316 °C. In still other non-limiting embodiments according to the present disclosure, it has an aluminum equivalent value included in the range of at least 6.9 or, in certain embodiments, 6.9 to 9.5, a molybdenum equivalent value of 7.4 to 12.8, and shows the time to 0.2% creep strain of 20 hours or more at 427 °C under a load of 60 ksi. In still other non-limiting embodiments, the titanium alloy according to the present disclosure has an aluminum equivalent value of at least 6 .9 or, in certain embodiments, an aluminum equivalent value included in the range of 8.0 to 9.5, a molybdenum equivalent value of 7.4 to 10.4, and shows the time to 0.2% creep strain of 86 hours or more at 427 °C under a load of 60 ksi.

[0016] Table 1 sets forth the elemental compositions of non-limiting embodiments of titanium alloys according to the present disclosure ("Experimental Titanium Alloy No. 1" and "Experimental Titanium Alloy No. 2), embodiments of comparative titanium alloys that do not contain an intentional silicon addition, and embodiments of certain conventional titanium alloys, Al eq and Mo eq . Without being bound by theory, it is considered that the silicon contents of Experimental Titanium Alloy No. 1 and Experimental Titanium Alloy No. 2 set forth in Table 1 may promote the precipitation of one or more silicide phases.

Table 1

[0017] To produce 9-inch diameter electrodes weighing approximately 400 lb to 800 lb each, a large amount of plasma arc melt (PAM) heat from the comparative titanium alloys and experimental titanium alloy No. 1 listed in Table 1 was used in a plasma arc furnace. The electrodes were generated using [a specific method]. The electrodes were then remelted in a vacuum arc remelt (VAR) furnace to produce 10-inch diameter ingots. Each ingot was converted into a 3-inch diameter billet using a hot working press. After a β forging step up to 7 inches in diameter, an α+β presstrain forging step up to 5 inches in diameter, and a β finish forging step up to 3 inches in diameter, the ends of each billet were cropped to remove suck-in and end cracks, and the billets were cut into multiple pieces. The top of each billet and the bottom of the bottommost 7-inch diameter billet were sampled for chemical and β transas. Based on the results of the intermediate billet chemistry, 2-inch long samples were cut from the billets and “pancake”-forged in a press. Pancake specimens were heat-treated using the following heat treatment profiles corresponding to the solution treatment and aging conditions: solution treatment of the titanium alloy at 800°C for 4 hours, water quenching of the titanium alloy to ambient temperature, aging of the titanium alloy at 635°C for 8 hours, and air cooling of the titanium alloy.

[0018] As used herein, the “solution treating and aging (STA)” process refers to a heat treatment process applied to a titanium alloy, which includes solution treating the titanium alloy at a solution treatment temperature below the β-transas temperature of the titanium alloy. In non-limiting embodiments, the solution treatment temperature is in the range of approximately 800°C to approximately 860°C. The solution-treated alloy is then aged by heating the alloy for a certain period of time to an aging temperature range that is below the β-transas temperature and below the solution treatment temperature of the titanium alloy. As used herein with respect to temperature, temperature range, or minimum temperature, terms such as “heated to,” “heating to,” or “heating to” mean that the alloy is heated until at least a desired portion of the alloy has a temperature that is at least equal to or within the reference temperature range of the reference temperature or minimum temperature over its entire portion range. In non-limiting embodiments, the solution treatment time is in the range of approximately 30 minutes to approximately 4 hours. In certain non-limiting embodiments, the solution treatment time may be less than 30 minutes or longer than 4 hours, and is generally recognized to depend on the cross-section and size of the titanium alloy. Upon completion of the solution treatment, the titanium alloy is cooled to ambient temperature at a rate dependent on the thickness of the cross-section of the titanium alloy.

[0019] The solution-treated titanium alloy is then aged at an aging temperature, also referred to herein as the “age hardening temperature,” in an α+β2 phase field below the β-transas temperature of the titanium alloy. In non-limiting embodiments, the aging temperature is in the range of approximately 620°C to approximately 650°C. In certain non-limiting embodiments, the aging time may be in the range of approximately 30 minutes to approximately 8 hours. In certain non-limiting embodiments, the aging time may be shorter than 30 minutes or longer than 8 hours, and is generally recognized to depend on the cross-section and size of the titanium alloy product form. The general techniques used in STA processing of titanium alloys are known to those skilled in the art and are therefore not described further herein.

[0020] Test blanks for tensile tests at room temperature and high temperatures, creep tests, fracture toughness tests, and microstructural analysis were cut from STA-processed pancake specimens. To ensure accurate correlation between chemical and mechanical properties, final chemical analysis was performed on the fracture toughness coupon after testing.

[0021] Examination of the final 3-inch diameter billet revealed a uniform layered alpha / beta microstructure. Referring to Figure 2 (showing experimental titanium alloy No. 1 listed in Table 1) and Figure 3 (showing comparative titanium alloys listed in Table 1), the metallography of the sample removed from the forged and STA heat-treated pancake specimen revealed a fine network of Widmanstatten α with several primary α and grain boundary α. This was clarified. In particular, experimental titanium alloy No. 1 contained silicide precipitates (see Figure 2; in the figure, silicide precipitates are identified as "e"), but the comparative titanium alloys listed in Table 1 did not contain silicide precipitates (see Figure 3).

[0022] Referring to Figures 4 and 5, the mechanical properties of experimental titanium alloy No. 1 (labeled "08BA" in Figures 4 and 5), listed in Table 1, were measured and compared with the mechanical properties of the comparative titanium alloy (labeled "07BA" in Figures 4 and 5), also listed in Table 1, and the conventional Ti17 alloy (having the composition specified in UNS-R58650, labeled "B4E89" in Figures 4 and 5). (American Society for Testing and Materials (ASTM)) Tensile tests were performed according to the standard E8 / E8M-09 ("Standard Test Methods for Tension Testing of Metallic Materials", ASTM International, 2009) of the Testing and Materials (ASTM). As shown in the experimental results in Table 2, experimental titanium alloy No. 1 exhibited significantly greater ultimate tensile strength, yield strength, and ductility (reported as % elongation) at 316°C compared to comparative titanium alloys without intentional silicon addition and certain conventional titanium alloys (e.g., Ti64 alloy and Ti17 alloy), as well as certain conventional titanium alloys containing intentional silicon addition (e.g., Ti834 alloy and Ti6242Si alloy). [Table 2]

[0023] The results of high-temperature tensile tests and creep tests at 427°C for experimental titanium alloy No. 1 (with intentional silicon addition) and experimental titanium alloy No. 2 (with intentional silicon addition) listed in Table 1 were compared with the results for the comparative titanium alloy (without intentional silicon addition) listed in Table 1 and for certain conventional titanium alloys listed in Table 1. The data are shown in Table 3. Experimental titanium alloy No. 1 showed, for example, an increase of approximately 25% in UTS and an increase of approximately 77% in creep life at 427°C compared to the comparative titanium alloy. [Table 3]

[0024] Herein, we describe embodiments of specific alternative titanium alloys. According to one non-limiting aspect of the present disclosure, the titanium alloy comprises, in weight percent based on the total weight of the alloy, 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. Another embodiment of the titanium alloy according to this disclosure contains, by weight percentage based on the total weight of the alloy, 5.1 to 6.1g of aluminum, 2.2 to 3.2g of tin, 2.1 to 3.1g of zirconium, 3.3 to 4.3g of molybdenum, 3.3 to 4.3g of chromium, 0.08 to 0.15g of oxygen, 0.03 to 0.11g of silicon, 0 to 0.30g of iron, titanium, and impurities. A further embodiment of the titanium alloy according to this disclosure contains, by weight percentage based on the total weight of the alloy, 5.6 to 5.8g of aluminum, 2.5 to 2.7g of tin, 2.6 to 2.7g of zirconium, 3.8 to 4.0g of molybdenum, 3.7 to 3.8g of chromium, 0.08 to 0.14g of oxygen, 0.03 to 0.05g of silicon, up to 0.06g of iron, titanium, and impurities. In non-limiting embodiments of the titanium alloys disclosed herein, incidental elements and impurities in the alloy composition may include, or essentially consist of, one or more of nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt, and copper. In certain embodiments of the titanium alloys disclosed herein, 0 to 0.05 of nitrogen, 0 to 0.05 of carbon, 0 to 0.015 of hydrogen, and 0 to a maximum of 0.1 of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, respectively, may be present in the titanium alloys disclosed herein.

[0025] Similar to the titanium alloys described in Figures 1-3 and accompanying those drawings, the alternative titanium alloy has silicon intentionally added. However, the embodiments of the alternative titanium alloy have a reduced chromium content compared to the experimental titanium alloy described in relation to Figures 1-3. Table 1 lists the compositions of non-limiting embodiments of the alternative titanium alloy ("Experimental Titanium Alloy No. 2") with reduced chromium content and intentional silicon addition.

[0026] In certain non-limiting embodiments of the titanium alloys described herein, in order to achieve an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, which have been observed to improve tensile strength at high temperatures, the titanium alloys, in combination with the addition of certain other alloys, This includes the intentional addition of ricon. In non-limiting embodiments of this disclosure, the titanium alloy has an aluminum equivalent value of at least 6.9 or, in specific embodiments, in 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. In other non-limiting embodiments of this disclosure, the titanium alloy has an aluminum equivalent value of at least 6.9 or, in specific embodiments, in 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. In yet other non-limiting embodiments, the titanium alloy according to this disclosure has an aluminum equivalent value of at least 6.9 or, in specific embodiments, in 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 86 hours or more at 427°C under a load of 60 ksi.

[0027] Table 3 contains the results of the high-temperature tensile test and creep test of experimental titanium alloy No. 2 listed in Table 1 at 800°F (427°C). Prior to the tests, the alloy was subjected to the heat treatment identified in the embodiments described above in relation to Figures 1 to 3, namely, solution treatment of the titanium alloy at 800°C for 4 hours, water quenching of the titanium alloy to ambient temperature, aging of the titanium alloy at 635°C for 8 hours, and air cooling of the titanium alloy. Referring to Figure 6, the metallography of experimental alloy No. 2 after STA heat treatment revealed silicide precipitates (one precipitate identified as "d"). Although not bound by theory, the silicon content of experimental titanium alloy No. 2 listed in Table 1 is thought to promote the precipitation of this silicide phase.

[0028] Certain embodiments of the alloys manufactured in accordance with this disclosure and the articles made from such alloys may be advantageously applied to aerospace components and parts, such as jet engine turbine disks and turbofan blades. Those skilled in the art can manufacture the aforementioned devices, parts, and other products from the alloys of this disclosure without further explanation provided herein. The examples of possible applications of the alloys of this disclosure are provided for illustrative purposes only and do not encompass all possible applications to which the product forms of the alloys of the present invention may be applied. Those skilled in the art will readily find further applications of the alloys described herein by reading this disclosure.

[0029] Various non-exclusive and non-limiting embodiments of the novel alloys described herein may be useful alone or in combination with one or more other embodiments described herein. Without limiting the foregoing, in the first non-limiting embodiment of this disclosure, the titanium alloy comprises, by weight percentage based on the total weight of the alloy, 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.

[0030] According to a second non-limiting aspect of the present disclosure, which may be used in combination with the first aspect, the titanium alloy comprises, by weight percentage based on the total weight of the alloy, 5.5 to 6.5 parts aluminum, 2.2 to 2.6 parts tin, 2.0 to 2.8 parts zirconium, 4.8 to 5.2 parts molybdenum, 4.5 to 4.9 parts chromium, 0.08 to 0.13 parts oxygen, 0.03 to 0.11 parts silicon, 0 to 0.25 parts iron, titanium, and impurities.

[0031] According to a third non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy comprises, by weight percentage based on the total weight of the alloy, 5.9 to 6.0 grams of aluminum, 2.3 to 2.5 grams of tin, 2.3 to 2.6 grams of zirconium, 4.9 to 5.1 grams of molybdenum, 4.5 to 4.8 grams of chromium, 0.08 to 0.13 grams of oxygen, 0.03 to 0.10 grams of silicon, up to 0.07 grams of iron, titanium, and impurities.

[0032] According to a fourth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy further comprises, by weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0033] According to a fifth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 160 ksi at 316°C.

[0034] According to a sixth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a yield strength of at least 140 ksi at 316°C.

[0035] According to a seventh non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a time to 0.2% creep strain for at least 20 hours at 427°C under a load of 60 ksi.

[0036] According to an eighth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, 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.

[0037] According to a ninth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of 8.0 to 9.5 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a yield strength of at least 140 ksi at 316°C.

[0038] According to a tenth non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent value of 8.0–9.5 and a molybdenum equivalent value of 7.4–12.8, and exhibits a time to 0.2% creep strain for at least 20 hours at 427°C under a load of 60 ksi.

[0039] According to an eleventh non-limiting aspect of the present disclosure, which may be used in combination with any or all of the aspects described above, the titanium alloy is produced by a process comprising: solution treatment of the titanium alloy at 800°C to 860°C for 4 hours; cooling the titanium alloy to ambient temperature at a rate dependent on the 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.

[0040] According to a twelfth non-limiting aspect of the present disclosure, the present disclosure also provides a titanium alloy comprising, in weight percent based on the total weight of the alloy, 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.

[0041] According to a 13th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy comprises, by weight percentage based on the total weight of the alloy, 5.1 to 6.1 parts aluminum, 2.2 to 3.2 parts tin, 2.1 to 3.1 parts zirconium, 3.3 to 4.3 parts molybdenum, 3.3 to 4.3 parts chromium, 0.08 to 0.15 parts oxygen, 0.03 to 0.11 parts silicon, 0 to 0.30 parts iron, titanium, and impurities.

[0042] According to a 14th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy comprises, by weight percentage based on the total weight of the alloy, 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.

[0043] According to a 15th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy further comprises, by weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0044] According to a 16th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 150 ksi at 316°C.

[0045] According to a 17th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a yield strength of at least 130 ksi at 316°C.

[0046] According to a non-limiting aspect of the present disclosure which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a time to 0.2% creep strain of 86 hours or more at 427°C under a load of 60 ksi.

[0047] According to a 19th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, 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.

[0048] According to a 20th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, 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.

[0049] According to a 21st non-limiting aspect of the present disclosure, which may be used in combination with each or any of the embodiments described above, the titanium alloy comprises an aluminum equivalent value of 8.0–9.5 and a molybdenum equivalent value of 7.4–12.8, and exhibits a time to 0.2% creep strain of 86 hours or more at 427°C under a load of 60 ksi.

[0050] According to a 22nd non-limiting aspect of the present disclosure, which may be used in combination with any or all of the aspects described above, the titanium alloy is produced by a process comprising: solution treatment of the titanium alloy at 800°C to 860°C for 4 hours; water quenching of the titanium alloy to ambient temperature; aging of the titanium alloy at 620°C to 650°C for 8 hours; and air cooling of the titanium alloy.

[0051] According to a 23rd non-limiting aspect of the present disclosure, the present disclosure also provides a method for producing an alloy, comprising: solution treatment of 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 dependent on the 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.

[0052] According to a 24th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy further comprises, by weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0053] According to a 25th non-limiting aspect of the present disclosure, the present disclosure also provides a method for producing an alloy, comprising: solution treatment of a titanium alloy at 800°C to 860°C for 4 hours, wherein the titanium alloy comprises 5.1 to 6.1 parts aluminum, 2.2 to 3.2 parts tin, 1.8 to 3.1 parts zirconium, 3.3 to 4.3 parts molybdenum, 3.3 to 4.3 parts chromium, 0.08 to 0.15 parts oxygen, 0.03 to 0.20 parts silicon, 0 to 0.30 parts iron, titanium, and impurities; cooling the titanium alloy to ambient temperature at a rate dependent on the 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.

[0054] According to a 26th non-limiting aspect of the present disclosure, which may be used in combination with each or any of the aspects described above, the titanium alloy further comprises, by weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0055] This specification is understood to describe aspects of the invention that are appropriate for a clear understanding of the invention. Certain aspects that are obvious to those skilled in the art and therefore do not facilitate a better understanding of the invention are omitted for the sake of brevity. While a limited number of embodiments of the invention are necessarily described herein, those skilled in the art will recognize that many modifications and variations of the invention can be made in consideration of the foregoing description. Any such modifications and variations of the invention are intended to be encompassed by the foregoing description and the following claims. [Modes of the Invention] [1] Titanium alloy, and based on the total weight of the alloy, 5.5-6.5 aluminum, Tin in the range of 1.9 to 2.9, Zirconium of 1.8 to 3.0, 4.5-5.5 molybdenum, Chrome in 4.2~5.2, 0.08-0.15 of oxygen, Silicone with a viscosity of 0.03 to 0.20, Iron with a value of 0-0.30, Titanium and impurities and The titanium alloy, including the above. [2] Based on the total weight of the alloy, as a weight percentage, 5.5-6.5 aluminum, 2.2 to 2.6 tin, Zirconium in the range of 2.0 to 2.8, 4.8-5.2 molybdenum, 4.5-4.9 chrome, 0.08-0.13 of oxygen, Silicon with a thickness of 0.03 to 0.11, Iron with a value of 0-0.25, Titanium and impurities and Titanium alloy as described in 1, including the one described in 1. [3] Based on the total weight of the alloy, as a weight percentage, 5.9~6.0 aluminum, 2.3-2.5 tin, Zirconium in the range of 2.3 to 2.6, 4.9-5.1 molybdenum, Chrome in 4.5-4.8, 0.08-0.13 of oxygen, Silicon with a thickness of 0.03 to 0.10, Iron up to 0.07, Titanium and impurities and Titanium alloy as described in 1, including the one described in 1. [4] Based on the total weight of the alloy, as a weight percentage, 0-0.05 nitrogen, 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1. The titanium alloy described in 1 further includes the following. [5] The titanium alloy according to claim 1, wherein the titanium alloy has 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. [6] The titanium alloy according to claim 1, wherein the titanium alloy has 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. [7] The titanium alloy has an aluminum equivalent value of at least 6.9 and a molecular weight of 7.4 to 12.8. The titanium alloy described in 1, with ribdenum equivalent values, and indicating the time to 0.2% creep strain at 427°C for at least 20 hours under a load of 60 ksi. [8] The titanium alloy according to claim 1, wherein the titanium alloy has 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. [9] The titanium alloy according to claim 1, wherein the titanium alloy has 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 316°C.

[10] The titanium alloy according to claim 1, wherein the titanium alloy has 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.

[11] The titanium alloy described in 1, The titanium alloy is subjected to solution treatment at 800°C to 860°C for 4 hours. Cooling the titanium alloy to ambient temperature at a rate dependent on the thickness of the cross-section of the titanium alloy, Aging the titanium alloy at 620°C to 650°C for 8 hours, and The titanium alloy is cooled with air. The titanium alloy is produced by a process that includes the following steps.

[12] In weight percentage based on the total weight of the alloy, 5.1~6.1 aluminum and 2.2 to 3.2 tin, Zirconium in grades 1.8 to 3.1, 3.3-4.3 molybdenum, 3.3-4.3 chromium, 0.08-0.15 of oxygen, Silicone with a viscosity of 0.03 to 0.20, Iron with a value of 0-0.30, Titanium and impurities and Titanium alloys, including titanium alloys.

[13] Based on the total weight of the alloy, as a weight percentage, 5.1~6.1 aluminum and 2.2 to 3.2 tin, 2.1-3.1 Zirconium, 3.3-4.3 molybdenum, 3.3-4.3 chromium, 0.08-0.15 of oxygen, Silicon with a thickness of 0.03 to 0.11, Iron with a value of 0-0.30, Titanium and impurities and Titanium alloys as described in 12, including the one described in 12.

[14] Based on the total weight of the alloy, as a weight percentage, 5.6~5.8 aluminum, 2.5 to 2.7 tin, Zirconium with a coefficient of 2.6-2.7, 3.8-4.0 molybdenum, 3.7-3.8 chromium, 0.08-0.14 units of oxygen, Silicon of 0.03 to 0.05, Iron up to 0.06, Titanium and impurities and Titanium alloys as described in 12, including the one described in 12.

[15] Based on the total weight of the alloy, as a weight percentage, 0-0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1. Titanium alloys as described in 12, further including the above.

[16] The titanium alloy according to 12, wherein the titanium alloy has 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.

[17] The titanium alloy according to 12, wherein the titanium alloy has 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.

[18] The titanium alloy according to 12, wherein the titanium alloy has 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 86 hours or more at 427°C under a load of 60 ksi.

[19] The titanium alloy according to 12, wherein the titanium alloy has 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.

[20] The titanium alloy according to 12, wherein the titanium alloy has 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. [twenty one] The titanium alloy according to 12, wherein the titanium alloy has 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 86 hours or more at 427°C under a load of 60 ksi. [twenty two] The titanium alloy described in 12, The titanium alloy is subjected to solution treatment at 800°C to 860°C for 4 hours. The titanium alloy is cooled to ambient temperature at a rate that depends on the thickness of the cross-section of the titanium alloy. Aging the titanium alloy at 620°C to 650°C for 8 hours, and The titanium alloy is cooled with air. The titanium alloy produced by a process including the following. [twenty three] A method for making alloys, The solution treatment of a titanium alloy at 800°C to 860°C for 4 hours, wherein the titanium alloy contains 5.5 to 6.5g of aluminum, 1.9 to 2.9g of tin, 1.8 to 3.0g of zirconium, 4.5 to 5.5g of molybdenum, 4.2 to 5.2g of chromium, 0.08 to 0.15g of oxygen, 0.03 to 0.20g of silicon, 0 to 0.30g of iron, titanium, and impurities. Cooling the titanium alloy to ambient temperature at a rate dependent on the thickness of the cross-section of the titanium alloy, Aging the titanium alloy at 620°C to 650°C for 8 hours, and The titanium alloy is cooled with air. The method, including the method described above. [twenty four] The method according to 23, wherein the titanium alloy further comprises, in weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper. [twenty five] A method for making alloys, The solution treatment of a titanium alloy at 800°C to 860°C for 4 hours, wherein the titanium alloy contains 5.1 to 6.1 parts aluminum, 2.2 to 3.2 parts tin, 1.8 to 3.1 parts zirconium, 3.3 to 4.3 parts molybdenum, 3.3 to 4.3 parts chromium, 0.08 to 0.15 parts oxygen, 0.03 to 0.20 parts silicon, 0 to 0.30 parts iron, titanium, and impurities. The titanium alloy is cooled to ambient temperature at a rate that depends on the thickness of the cross-section of the titanium alloy. Aging the titanium alloy at 620°C to 650°C for 8 hours, and Air cooling of titanium alloys, The method, including the method described above.

[26] The method according to 25, wherein the titanium alloy further comprises, in weight percentage based on the total weight of the alloy, 0 to 0.05 parts nitrogen, 0 to 0.05 parts carbon, 0 to 0.015 parts hydrogen, and 0 to a maximum of 0.1 parts each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

Claims

1. An alpha / beta titanium alloy, in weight percentage based on the total weight of the alloy, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a viscosity of 0.03 to 0.20, Iron that is more than 0 and less than or equal to 0.30, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, The alpha / beta titanium alloy contains silicide precipitates, and The alpha / beta titanium alloy exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

2. The alpha / beta titanium alloy according to claim 1, wherein aluminum constitutes 5.6 to 6.1% by weight, based on the total weight of the alloy.

3. The alpha / beta titanium alloy according to claim 1, wherein aluminum constitutes 5.8 to 6.1% by weight, based on the total weight of the alloy.

4. The alpha / beta titanium alloy according to claim 1, wherein tin constitutes 2.5 to 3.2% by weight, based on the total weight of the alloy.

5. The alpha / beta titanium alloy according to claim 1, wherein zirconium constitutes 2.6 to 3.1% by weight, based on the total weight of the alloy.

6. The alpha / beta titanium alloy according to claim 1, wherein molybdenum constitutes 3.8 to 5.0% by weight, based on the total weight of the alloy.

7. The alpha / beta titanium alloy according to claim 1, wherein molybdenum constitutes 3.8 to 4.8 percent by weight, based on the total weight of the alloy.

8. The alpha / beta titanium alloy according to claim 1, wherein molybdenum constitutes 4.3 to 4.9% by weight, based on the total weight of the alloy.

9. The alpha / beta titanium alloy according to claim 1, wherein chromium constitutes 3.3 to 4.3% by weight, based on the total weight of the alloy.

10. The alpha / beta titanium alloy according to claim 1, wherein oxygen constitutes 0.08 to 0.14% by weight, based on the total weight of the alloy.

11. The alpha / beta titanium alloy according to claim 1, wherein silicon constitutes 0.04 to 0.20 by weight percentage based on the total weight of the alloy.

12. The alpha / beta titanium alloy according to claim 6, wherein silicon constitutes 0.05 to 0.20 by weight percentage based on the total weight of the alloy.

13. The alpha / beta titanium alloy according to claim 1, wherein silicon constitutes 0.03 to 0.11 by weight percentage based on the total weight of the alloy.

14. The alpha / beta titanium alloy according to claim 1, wherein iron constitutes more than 0 and less than or equal to 0.25 by weight percentage based on the total weight of the alloy.

15. The alpha / beta titanium alloy according to claim 1, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.

8.

16. Based on the total weight of the alloy, as a weight percentage, 5.6 to 6.1 aluminum, 2.5 to 3.2 tin, 2.6 to 3.1 zirconium, 3.8 to 5.0 molybdenum, 3.3 to 4.3 chromium, Oxygen at 0.08 to 0.14, Silicon with a viscosity of 0.04 to 0.20, Iron that is more than 0 and less than or equal to 0.25, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

17. Based on the total weight of the alloy, as a weight percentage, 5.8 to 6.1 aluminum, 2.5 to 3.2 tin, 2.6 to 3.1 zirconium, 3.8 to 4.8 molybdenum, 3.3 to 4.3 chromium, Oxygen at 0.08 to 0.14, Silicon with a viscosity of 0.05 to 0.20, Iron that is more than 0 and less than or equal to 0.25, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. The alpha / beta titanium alloy according to claim 16.

18. The alpha / beta titanium alloy according to claim 17, wherein silicon constitutes 0.05 to 0.11 by weight percentage based on the total weight of the alloy.

19. Based on the total weight of the alloy, as a weight percentage, 5.8 to 6.1 aluminum, 2.5 to 3.2 tin, 2.6 to 3.1 zirconium, 4.3 to 4.9 molybdenum, 3.3 to 4.3 chromium, Oxygen at 0.08 to 0.14, Silicon with a viscosity of 0.05 to 0.20, Iron that is more than 0 and less than or equal to 0.25, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. The alpha / beta titanium alloy according to claim 16.

20. The alpha / beta titanium alloy according to claim 19, wherein silicon constitutes 0.05 to 0.11 by weight percentage based on the total weight of the alloy.

21. A method for producing the alpha / beta titanium alloy according to Claim 1, The titanium alloy is solution-treated at 800°C to 860°C for 4 hours, where the titanium alloy is In weight percentage based on the total weight of the alloy, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a viscosity of 0.03 to 0.20, Iron that is more than 0 and less than or equal to 0.30, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, The titanium alloy is quenched in water to ambient temperature. Aging the titanium alloy at 620°C to 650°C for 8 hours, and The titanium alloy is cooled with air. including, The method described above.

22. In weight percentage based on the total weight of the alloy, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a viscosity of 0.03 to 0.20, Iron that is more than 0 and less than or equal to 0.30, Vanadium in the range of 0 to 0.1, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

23. Based on the total weight of the alloy, as a weight percentage, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a viscosity of 0.03 to 0.20, Iron that is more than 0 and less than or equal to 0.30, Vanadium in the range of 0 to 0.1, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

24. Based on the total weight of the alloy, as a weight percentage, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a value of 0 to 0.05, Iron that is more than 0 and less than or equal to 0.30, Manganese in the range of 0 to 0.1, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, cobalt, and copper, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

25. Based on the total weight of the alloy, as a weight percentage, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon with a viscosity of 0.03 to 0.20, Iron that is more than 0 and less than or equal to 0.30, Copper with a value of 0 to 0.1, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, and cobalt, each ranging from 0 to a maximum of 0.1, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

26. The alpha / beta titanium alloy according to claim 22, wherein aluminum constitutes 5.6 to 6.1% by weight, based on the total weight of the alloy.

27. The alpha / beta titanium alloy according to claim 22, wherein tin constitutes 2.5 to 3.2% by weight, based on the total weight of the alloy.

28. The alpha / beta titanium alloy according to claim 22, wherein zirconium constitutes 2.6 to 3.1% by weight, based on the total weight of the alloy.

29. The alpha / beta titanium alloy according to claim 22, wherein molybdenum constitutes 3.8 to 5.0 by weight percentage based on the total weight of the alloy.

30. The alpha / beta titanium alloy according to claim 22, wherein chromium constitutes 3.3 to 4.3% by weight, based on the total weight of the alloy.

31. The alpha / beta titanium alloy according to claim 22, wherein oxygen constitutes 0.08 to 0.14% by weight, based on the total weight of the alloy.

32. The alpha / beta titanium alloy according to claim 22, wherein silicon constitutes 0.04 or more and less than 0.1 by weight percentage based on the total weight of the alloy.

33. The alpha / beta titanium alloy according to claim 22, wherein iron constitutes more than 0 and less than or equal to 0.25 by weight percentage based on the total weight of the alloy.

34. The alpha / beta titanium alloy according to claim 22, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.

8.

35. The alpha / beta titanium alloy according to claim 23, wherein aluminum constitutes 5.6 to 6.1% by weight, based on the total weight of the alloy.

36. The alpha / beta titanium alloy according to claim 23, wherein tin constitutes 2.5 to 3.2% by weight, based on the total weight of the alloy.

37. The alpha / beta titanium alloy according to claim 23, wherein zirconium constitutes 2.6 to 3.1% by weight, based on the total weight of the alloy.

38. The alpha / beta titanium alloy according to claim 23, wherein molybdenum constitutes 3.8 to 5.0% by weight, based on the total weight of the alloy.

39. The alpha / beta titanium alloy according to claim 23, wherein chromium constitutes 3.3 to 4.3% by weight, based on the total weight of the alloy.

40. The alpha / beta titanium alloy according to claim 23, wherein oxygen constitutes 0.08 to 0.14% by weight, based on the total weight of the alloy.

41. The alpha / beta titanium alloy according to claim 23, wherein silicon constitutes 0.04 to 0.20 by weight percentage based on the total weight of the alloy.

42. The alpha / beta titanium alloy according to claim 23, wherein iron constitutes more than 0 and less than or equal to 0.25 by weight percentage based on the total weight of the alloy.

43. The alpha / beta titanium alloy according to claim 23, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.

8.

44. The alpha / beta titanium alloy according to claim 24, wherein aluminum constitutes 5.6 to 6.1% by weight, based on the total weight of the alloy.

45. The alpha / beta titanium alloy according to claim 24, wherein tin constitutes 2.5 to 3.2% by weight, based on the total weight of the alloy.

46. The alpha / beta titanium alloy according to claim 24, wherein zirconium constitutes 2.6 to 3.1% by weight, based on the total weight of the alloy.

47. The alpha / beta titanium alloy according to claim 24, wherein molybdenum constitutes 3.8 to 5.0% by weight, based on the total weight of the alloy.

48. The alpha / beta titanium alloy according to claim 24, wherein chromium constitutes 3.3 to 4.3% by weight, based on the total weight of the alloy.

49. The alpha / beta titanium alloy according to claim 24, wherein oxygen constitutes 0.08 to 0.14% by weight, based on the total weight of the alloy.

50. The alpha / beta titanium alloy according to claim 24, wherein silicon constitutes 0.04 or more and less than 0.1 by weight percentage based on the total weight of the alloy.

51. The alpha / beta titanium alloy according to claim 24, wherein iron constitutes more than 0 and less than or equal to 0.25 by weight percentage based on the total weight of the alloy.

52. The alpha / beta titanium alloy according to claim 24, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.

8.

53. The alpha / beta titanium alloy according to claim 25, wherein aluminum constitutes 5.6 to 6.1% by weight, based on the total weight of the alloy.

54. The alpha / beta titanium alloy according to claim 25, wherein tin constitutes 2.5 to 3.2% by weight, based on the total weight of the alloy.

55. The alpha / beta titanium alloy according to claim 25, wherein zirconium constitutes 2.6 to 3.1% by weight, based on the total weight of the alloy.

56. The alpha / beta titanium alloy according to claim 25, wherein molybdenum constitutes 3.8 to 5.0% by weight, based on the total weight of the alloy.

57. The alpha / beta titanium alloy according to claim 25, wherein chromium constitutes 3.3 to 4.3% by weight, based on the total weight of the alloy.

58. The alpha / beta titanium alloy according to claim 25, wherein oxygen constitutes 0.08 to 0.14% by weight, based on the total weight of the alloy.

59. The alpha / beta titanium alloy according to claim 25, wherein silicon constitutes 0.04 to 0.20 by weight percentage based on the total weight of the alloy.

60. The alpha / beta titanium alloy according to claim 25, wherein iron constitutes more than 0 and less than or equal to 0.25 by weight percentage based on the total weight of the alloy.

61. The alpha / beta titanium alloy according to claim 25, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.

8.

62. Based on the total weight of the alloy, as a weight percentage, 5.5 to 6.5 aluminum, 2.2 to 3.2 tin and 1.8 to 3.1 zirconium, 3.8 to 5.5 molybdenum, 3.3 to 4.7 chromium, Oxygen at 0.08 to 0.15, Silicon between 0 and less than 0.1, Iron that is more than 0 and less than or equal to 0.30, Niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, each ranging from 0 to a maximum of 0.1, 0 to 0.05 nitrogen and 0 to 0.05 carbon atoms, Hydrogen in the range of 0 to 0.015, Titanium and impurities and It consists of, It contains silicide precipitates, and It exhibits a yield strength of at least 896 MPa (130 ksi) at 316°C. Alpha / beta titanium alloy.

63. The alpha / beta titanium alloy according to claim 62, comprising an aluminum equivalent value of 6.9 to 9.5 and a molybdenum equivalent value of 7.4 to 12.8.

Images