High-temperature titanium alloy

Abstract

The invention relates to a high temperature titanium alloy. A non-limiting embodiment of a titanium alloy comprises, in weight percent based on the total alloy weight: 5.1 to 6.5 aluminum; 1.9 to 3.2 of tin; 1.8 to 3.1 of zirconium; 3.3 to 5.5 of molybdenum; 3.3 to 5.2% of chromium; from 0.08 to 0.15 of oxygen; from 0.03 to 0.20 of silicon; from 0 to 0.30 of iron; titanium; and impurities. A non-limiting embodiment of the titanium alloy comprises intentionally added silicon and certain other alloy additives to achieve an aluminum equivalent value of at least 8.9 and a molybdenum equivalent value of 7.4 to 12.8, which is observed to increase tensile strength at high temperatures.

Description

[0001] This application is a divisional of application number 201980024264.1, filed March 20, 2019, having the title “High Temperature Titanium Alloy”. TECHNICAL FIELD

[0002] The present disclosure relates to high temperature titanium alloys. BACKGROUND

[0003] Titanium alloys generally exhibit high strength-to-weight ratios, corrosion resistance, and creep resistance at moderately high temperatures. For example, Ti-5Al-4Mo-4Cr-2Sn-2Zr alloy (also known as “Ti-17 alloy,” which has a composition specified in UNS R58650) is a commercial alloy widely used in jet engine applications requiring a combination of high strength, fatigue resistance, and toughness at operating temperatures up to 800°F (about 427°C). Other examples of titanium alloys for high temperature applications include Ti-6Al-2Sn-4Zr-2Mo alloy (having a composition specified in UNS R54620) and Ti-3Al-8V-6Cr-4Mo-4Zr alloy (also known as “β-C,” having a composition specified in UNS R58640). However, these alloys have limitations in creep resistance and / or tensile strength at elevated temperatures. There is a need for titanium alloys having improved creep resistance and / or tensile strength at elevated temperatures. SUMMARY

[0004] According to one non-limiting aspect of the present disclosure, a titanium alloy includes, by weight percentage 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.

[0005] According to another non-limiting aspect of the present disclosure, a titanium alloy includes, by weight percentage 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. BRIEF DESCRIPTION OF DRAWINGS

[0006] The features and advantages of the alloys, articles, and methods described herein will be better understood by reference to the accompanying drawings, in which:

[0007] Figure 1 is a graph illustrating a non-limiting embodiment of a method of processing a non-limiting embodiment of a titanium alloy according to the present disclosure;

[0008] Figure 2 Is it like this? Figure 1 Scanning electron microscope images (in backscattered electron mode) of titanium alloys processed in the process, where “a” indicates primary α, “b” indicates grain boundary α, “c” indicates α lamellae, “d” indicates secondary α, and “e” indicates silicides;

[0009] Figure 3 These are scanning electron microscope images (in backscattered electron mode) of solution-treated and aged titanium alloys, where "a" indicates primary α, "b" indicates grain boundary α, "c" indicates α lamellae, and "d" indicates secondary α.

[0010] Figure 4 It is a graph of the ultimate tensile strength versus temperature of a non-limiting embodiment of the titanium alloy according to the present disclosure, which compares these properties with comparative titanium alloys and conventional titanium alloys.

[0011] Figure 5 This is a yield strength versus temperature curve of a titanium alloy according to a non-limiting embodiment of the present disclosure, which compares these properties with comparative titanium alloys and conventional titanium alloys; and

[0012] Figure 6 The images are scanning electron microscope images (in backscattered electron mode) of a non-limiting embodiment of a titanium alloy according to the present disclosure, wherein “a” identifies a grain boundary α, “b” identifies an α lamellar, “c” identifies a secondary α, and “d” identifies a silicide.

[0013] The foregoing details, as well as others, will be understood after considering the following detailed description of certain non-limiting embodiments according to this disclosure. Detailed Implementation

[0014] In the description of the non-limiting embodiments herein, all figures representing quantities or characteristics, except as indicated in operational embodiments or otherwise, should be understood to be modified by the term "about" in all cases. Therefore, unless indicated to the contrary, any numerical parameter set forth in the following description is an approximation that may vary depending on the desired characteristics sought in the material by the methods according to this disclosure. To a minimum, and without attempting to limit the application of the doctrine of equivalence to the scope of the claims, each numerical parameter should be interpreted at least according to the number of reported significant bits and by applying general rounding methods. Unless otherwise stated, all scopes described herein include the described endpoints.

[0015] Any patent, publication, or other disclosure allegedly incorporated herein by reference, in whole or in part, is incorporated only if the incorporated material does not conflict with any existing definitions, statements, or other disclosures set forth herein. Therefore, and to the extent necessary, any conflicting material incorporated herein by reference shall supersede any material incorporated herein by reference that is conflicting with any existing definitions, statements, or other disclosures set forth herein. Any material, or a portion thereof, allegedly incorporated herein by reference but conflicting with any existing definitions, statements, or other disclosures set forth herein, shall be incorporated only if it does not create a conflict between the incorporated material and any existing disclosures.

[0016] Products and parts exposed to high temperatures may suffer from creep. As used herein, “high temperature” refers to a temperature exceeding approximately 100℉ (approximately 37.8℃). 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 almost constant strain rate is called second-order (steady-state) creep; and creep occurring at an accelerating strain rate is called third-order creep. Creep strength is the stress that induces a given creep strain in a creep test over a given time in a specified constant environment.

[0017] The creep resistance of titanium and titanium alloys under high temperatures and sustained loads depends primarily on their microstructure characteristics. Titanium exists in two allotropic forms: 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 speaking, β titanium alloys exhibit poor creep strength at elevated temperatures. This poor high-temperature creep strength is a result of the significant concentration of the β phase present in these alloys at elevated temperatures (such as, for example, 500 °C). The β phase, due to its body-centered cubic structure, does not resist creep well, which provides numerous deformation mechanisms. These drawbacks limit the use of β titanium alloys.

[0018] A group of titanium alloys widely used in various applications is α / β titanium alloys. In α / β titanium alloys, the distribution and size of primary α particles directly affect creep resistance. According to various published studies on silicon-containing α / β titanium alloys, silicide precipitation at grain boundaries can further improve creep resistance, but is detrimental to room temperature tensile ductility. The decrease in room temperature tensile ductility with silicon addition limits the amount of silicon that can be added, typically to 0.2% (by weight).

[0019] This disclosure relates in part to alloys that address certain limitations of conventional titanium alloys. Figure 1This is a diagram illustrating a non-limiting embodiment of a method for processing a titanium alloy according to the present disclosure. One embodiment of the titanium alloy according to the present disclosure comprises, by weight percentage, the following: 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 comprises, by weight percentage, the following: 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 includes, by weight percentage based on the 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. In a non-limiting embodiment of the alloy according to this disclosure, occasional elements and impurities in the alloy composition may comprise one or more of nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt, and copper, or consist substantially of them. Certain non-limiting embodiments of the titanium alloy according to this disclosure may include, by weight percentage based on the total alloy weight: 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0020] In certain non-limiting embodiments of the titanium alloy of the present invention, the titanium alloy comprises intentionally added silicon and certain other alloying additives 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 inventors have observed to improve tensile strength at high temperatures. As used herein, “aluminum equivalent value” or “aluminum equivalent” (Al) 当量 The following can be determined (as indicated, where all element concentrations are weight percentages): Al 当量 = Al (wt%) + (1 / 6)×Zr (wt%) + (1 / 3)×Sn (wt%) + 10×O (wt%) As used in this article, "molybdenum equivalent value" or "molybdenum equivalent" (Mo) 当量 The concentration of Mo can be determined as follows (as indicated, all element concentrations are weight percentages): 当量 = Mo (wt%) + (1 / 5)×Ta (wt%) + (1 / 3.6)×Nb(wt%) + (1 / 2.5)×W (wt%) + (1 / 1.5)×V (wt%) + 1.25×Cr (wt%) + 1.25×Ni (wt%) + 1.7×Mn (wt%) + 1.7×Co (wt%) + 2.5×Fe (wt%) .

[0021] While it is recognized that the mechanical properties of titanium alloys are generally affected by the size of the tested specimens, in a non-limiting embodiment according to this disclosure, the titanium alloy contains an aluminum equivalent value of at least 6.9 (or in some embodiments, in 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 160 ksi and an elongation of at least 10% at 316°C. In other non-limiting embodiments according to this disclosure, the titanium alloy contains an aluminum equivalent value of at least 6.9 (or in some embodiments, in 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 an elongation of at least 10% at 316°C. In other non-limiting embodiments, the titanium alloy according to this disclosure contains an aluminum equivalent value of at least 6.9 (or in some embodiments in the range of 6.9 to 9.5), a molybdenum equivalent value of 7.4 to 12.8, and exhibits a creep strain of at least 0.2% for at least 20 hours at 427°C and a load of 60 ksi. In other non-limiting embodiments, the titanium alloy according to this disclosure contains an aluminum equivalent value of at least 6.9 (or in some embodiments in the range of 8.0 to 9.5), a molybdenum equivalent value of 7.4 to 10.4, and exhibits a creep strain of at least 0.2% for at least 86 hours at 427°C and a load of 60 ksi.

[0022] Table 1 lists the elemental composition of the following implementation schemes. 当量 and Mo 当量 The present disclosure includes non-limiting embodiments of titanium alloys (“Experimental Titanium Alloy No. 1” and “Experimental Alloy No. 2”), embodiments of comparative titanium alloys excluding intentionally added silicon, and embodiments of certain conventional titanium alloys. Without being bound by any theory, it is believed that the silicon content of Experimental Titanium Alloy No. 1 and Experimental Titanium Alloy No. 2 listed in Table 1 can promote the precipitation of one or more silicide phases.

[0023] Table 1

[0024]

[0025] Multiple plasma arc melting (PAM) cycles were used to produce electrodes of the comparative and experimental titanium alloys No. 1 listed in Table 1, produced in a plasma arc furnace, to produce 9-inch diameter electrodes, each weighing approximately 400–800 lb. The electrodes were remelted in a vacuum arc remelting (VAR) furnace to produce 10-inch diameter ingots. Each ingot was converted into a 3-inch diameter billet using a hot-working press. After reaching a 7-inch diameter through a β-forging step, a 5-inch diameter through an α+β pre-straining step, and a 3-inch diameter through a β precision forging step, the ends of each billet were trimmed to remove suck-in and end-cracks, and the billets were cut into multiple pieces. Samples were taken from the top of each billet and the bottom of the bottom 7-inch diameter billet for chemical and β-transformation. Based on the intermediate billet chemical results, a 2-inch sample was cut from the billet and “flattened” forged on the press. The flat samples were heat-treated using the following heat treatment curves (corresponding to solution treatment and aging conditions): the titanium alloy was solution treated at 800°C for 4 hours; the titanium alloy was water-quenched to ambient temperature; the titanium alloy was aged at 635°C for 8 hours; and the titanium alloy was air-cooled.

[0026] As used herein, the “solution treatment and aging (STA)” process refers to a heat treatment process applied to titanium alloys, which includes solution treatment of the titanium alloy at a temperature below the β-transformation temperature of the titanium alloy. In a non-limiting embodiment, the solution treatment temperature is in the temperature range of about 800°C to about 860°C. The solution-treated alloy is then aged by heating the alloy for a period of time to an aging temperature range that is below the β-transformation temperature of the titanium alloy and below the solution treatment temperature. As used herein, terms such as “heated to” or “heated to” refer to heating the alloy until at least a desired portion of the alloy is at least equal to a reference temperature or minimum temperature, or the temperature is within the reference temperature range over the entire portion. In one non-limiting embodiment, the solution treatment time ranges from about 30 minutes to about 4 hours. It should be recognized that in some non-limiting embodiments, the solution treatment time may be less than 30 minutes or longer than 4 hours, and generally depends on the size and cross-section of the titanium alloy. After solution treatment, the titanium alloy is cooled to ambient temperature at a rate depending on the cross-sectional thickness of the titanium alloy.

[0027] The solution-treated titanium alloy is then aged at an aging temperature, also referred to herein as the "age hardening temperature," which is below the β transformation temperature of the titanium alloy in the α+β two-phase field. In one non-limiting embodiment, the aging temperature is in the range of about 620°C to about 650°C. In some non-limiting embodiments, the aging time can range from about 30 minutes to about 8 hours. It should be recognized that in some non-limiting embodiments, the aging time can be less than 30 minutes or longer than 8 hours, and generally depends on the size and cross-section of the titanium alloy product. The general techniques used in the STA processing of titanium alloys are known to those skilled in the art and therefore will not be discussed further herein.

[0028] Test blanks were cut from flat samples processed by STA for indoor and high-temperature tensile testing, creep testing, fracture toughness, and microstructure analysis. Following testing, the fracture toughness specimens underwent final chemical analysis to ensure an accurate correlation between chemical and mechanical properties.

[0029] Inspection of the final 3-inch diameter billet revealed a uniform layered α / β microstructure. (Reference) Figure 2 (The experimental titanium alloy No. 1 listed in Table 1 is shown) and Figure 3 (The comparative titanium alloys listed in Table 1 are shown.) Metallographic analysis of samples taken from forged and STA-heat-treated flat specimens revealed a good Widmanstätten α network with some primary α and grain boundary α. Notably, experimental titanium alloy No. 1 included silicide precipitates (see Table 1). Figure 2 Silicide precipitates are indicated as "e", while the comparative titanium alloys listed in Table 1 do not include silicide precipitates (see Table 1). Figure 3 ).

[0030] refer to Figures 4-5 The experimental titanium alloy No. 1 listed in Table 1 was measured. Figures 4-5 The mechanical properties of titanium alloys (represented as "08BA") are compared with those listed in Table 1. Figures 4-5 (represented as "07BA") and conventional Ti17 alloy (with the composition specified in UNS-R58650, in Figures 4-5The mechanical properties of the alloy were compared, with the alloy designated as "B4E89". Tensile tests were performed according to ASTM Standard E8 / E8M-09 ("Standard Test Methods for Tension Testing of Metallic Materials", ASTM International, 2009). As shown in Table 2, compared to the comparative titanium alloy and certain conventional titanium alloys without intentionally added silicon (e.g., Ti64 and Ti17 alloys), and compared to certain conventional titanium alloys including intentionally added silicon (e.g., Ti834 and Ti6242Si alloys), experimental titanium alloy No. 1 exhibited significantly greater ultimate tensile strength, yield strength, and ductility (reported as % elongation) at 316 °C.

[0031] Table 2

[0032]

[0033] The high-temperature tensile and creep test results at 427°C for experimental titanium alloys No. 1 (containing intentionally added silicon) and No. 2 (containing intentionally added silicon) listed in Table 1 were compared with the test results of the comparative titanium alloy (without intentionally added silicon) and some conventional titanium alloy samples listed in Table 1. The data are shown in Table 3. For example, experimental titanium alloy No. 1 showed an approximately 25% increase in UTS and an approximately 77% increase in creep life at 427°C compared to the comparative titanium alloy.

[0034] Table 3

[0035]

[0036] Certain alternative titanium alloy embodiments are now described. According to one non-limiting aspect of this disclosure, the titanium alloy comprises, by weight percentage, 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 comprises, by weight percentage, 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. Another embodiment of the titanium alloy according to this disclosure includes, by weight percentage based on the 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 a non-limiting embodiment of the alloy according to this disclosure, occasional elements and impurities in the alloy composition may comprise one or more of nitrogen, carbon, hydrogen, niobium, tungsten, vanadium, tantalum, manganese, nickel, hafnium, gallium, antimony, cobalt, and copper, or substantially consist of them. In certain embodiments of the titanium alloy according to this disclosure, 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper may be present in the titanium alloy disclosed herein.

[0037] Similar to Figures 1-3 The titanium alloys shown and described in conjunction with these figures are alternative titanium alloys that contain intentionally added silicon. However, embodiments of the alternative titanium alloys include those relative to... Figures 1-3 The experimental titanium alloys with reduced chromium content are shown and described in conjunction with these figures. Table 1 lists the composition of a non-limiting embodiment of an alternative titanium alloy (“Experimental Titanium Alloy No. 2”) with reduced chromium content and intentionally added silicon.

[0038] In certain non-limiting embodiments of the titanium alloy according to this disclosure, the titanium alloy contains intentionally added silicon and certain other alloying additives to achieve an aluminum equivalent value of at least 6.9 and a molybdenum equivalent value of 7.4 to 12.8, which is observed to improve tensile strength at high temperatures. In a non-limiting embodiment according to this disclosure, the titanium alloy contains an aluminum equivalent value of at least 6.9 (or in some 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 according to this disclosure, the titanium alloy contains an aluminum equivalent value of at least 6.9 (or in some 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 other non-limiting embodiments, the titanium alloy according to this disclosure contains an aluminum equivalent value of at least 6.9 (or in some embodiments in the range of 8.0 to 9.5), a molybdenum equivalent value of 7.4 to 12.8, and exhibits a creep strain of not less than 0.2% for at least 86 hours at 427°C and a load of 60 ksi.

[0039] Table 3 lists the high-temperature tensile test results and creep test results of experimental titanium alloy No. 2 in Table 1 at 800℉ (427℃). Prior to the tests, the alloy underwent the above-mentioned bonding process. Figures 1-3 The heat treatments defined in the described implementation scheme include: 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. (Reference) Figure 6 Metallography of experimental alloy No. 2, which underwent STA heat treatment, revealed silicide precipitates (one precipitate is identified as "d"). Without being bound by any theory, it is believed that the silicon content of experimental titanium alloy No. 2 listed in Table 1 promotes the precipitation of this silicide phase.

[0040] Certain embodiments of the alloys prepared according to this disclosure and articles made from these alloys can be advantageously applied to aerospace parts and components, such as, for example, jet engine turbine disks and turbofan blades. Those skilled in the art will be able to manufacture the aforementioned devices, parts, and other articles from the alloys according to this disclosure without further description herein. The foregoing examples of possible applications of the alloys according to this disclosure are provided by way of example only and are not exhaustive of all applications to which the alloy product forms of the invention may be applied. By reading this disclosure, those skilled in the art can readily identify other applications of the alloys as described herein.

[0041] Various non-exhaustive, non-limiting aspects of the novel alloys according to this disclosure may be used alone or in combination with one or more other aspects described herein. Without limiting the foregoing description, in a first non-limiting aspect of this disclosure, the titanium alloy comprises, based on the total alloy weight as a percentage by 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.

[0042] According to a second non-limiting aspect of this disclosure, which may be used in combination with the first aspect, the titanium alloy comprises, by weight percentage based on the 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.

[0043] According to a third non-limiting aspect of this disclosure, which may be used in combination with any of the foregoing aspects, the titanium alloy comprises, by weight percentage based on the 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.

[0044] According to the fourth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy further comprises, by weight percentage, 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0045] According to the fifth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains 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.

[0046] According to the sixth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains 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.

[0047] According to the seventh non-limiting aspect of this disclosure, which may be used in combination with any or all of the foregoing aspects, the titanium alloy contains an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a creep strain of 0.2% for at least 20 hours at 427°C and a load of 60 ksi.

[0048] According to the eighth non-limiting aspect of this disclosure, which may be used in combination with any or all of the foregoing aspects, 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 an ultimate tensile strength of at least 160 ksi at 316 °C.

[0049] According to the ninth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, 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.

[0050] According to the tenth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains an aluminum equivalent of 8.0 to 9.5 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a creep strain of 0.2% for at least 20 hours at 427°C and a load of 60 ksi.

[0051] According to the eleventh non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy is prepared by a process comprising the following steps: solution treating the titanium alloy at 800°C to 860°C for 4 hours; cooling the titanium alloy to ambient temperature at a rate depending 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 the twelfth non-limiting aspect of this disclosure, this disclosure also provides a titanium alloy comprising, by weight percentage based on the 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.

[0053] According to the thirteenth non-limiting aspect of this disclosure, which may be used in combination with any of the foregoing aspects, the titanium alloy comprises, based on the total alloy weight as a percentage by 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.

[0054] According to the fourteenth non-limiting aspect of this disclosure, which may be used in combination with any of the foregoing aspects, the titanium alloy comprises, by weight percentage based on the 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.

[0055] According to the fifteenth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy further comprises, by weight percentage, 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0056] According to the sixteenth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains 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.

[0057] According to the seventeenth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains 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.

[0058] According to the eighteenth non-limiting aspect of this disclosure, which may be used in combination with any or all of the foregoing aspects, the titanium alloy contains an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, and exhibits a creep strain of not less than 0.2% for at least 86 hours at 427°C and a load of 60 ksi.

[0059] According to the nineteenth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy contains an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.8, and exhibits an ultimate tensile strength of at least 150 ksi at 316°C.

[0060] According to the twentieth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, 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 130 ksi at 316°C.

[0061] According to the twenty-first non-limiting aspect of this disclosure, which may be used in combination with any or all of the foregoing aspects, 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 creep strain of not less than 0.2% for 86 hours at 427°C and a load of 60 ksi.

[0062] According to the twenty-second non-limiting aspect of this disclosure, which may be used in combination with any of the foregoing aspects, the titanium alloy is prepared by a process comprising the following steps: solution treating the titanium alloy at 800°C to 860°C 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.

[0063] According to the twenty-third non-limiting aspect of this disclosure, this disclosure also provides a method for preparing an alloy, the method 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 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.

[0064] According to the twenty-fourth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy further comprises, by weight percentage, 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0065] According to the twenty-fifth non-limiting aspect of this disclosure, this disclosure also provides a method for preparing an alloy, the method 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 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.

[0066] According to the twenty-sixth non-limiting aspect of this disclosure, which may be used in combination with each or any of the foregoing aspects, the titanium alloy further comprises, by weight percentage, 0 to 0.05% nitrogen, 0 to 0.05% carbon, 0 to 0.015% hydrogen, and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper.

[0067] It should be understood that this specification describes those aspects of the invention relevant to a clear understanding of the invention. Therefore, for the sake of simplicity, certain aspects that would be obvious to those skilled in the art and thus detrimental to a better understanding of the invention have not been presented. Although only a limited number of embodiments of the invention are necessarily described herein, those skilled in the art will recognize, upon considering the foregoing description, that many modifications and variations of the invention may be employed. All such variations and modifications of the invention are intended to be covered by the foregoing description and the following claims.

Claims

1. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 1.9 to 2.9; Zirconium content ranging from 1.8 to 3.0; Molybdenum of 4.5 to 5.5; Chromium content of 4.2 to 5.2; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron content between 0 and 0.30; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen from 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Balanced titanium; and impurities.

2. The titanium alloy according to claim 1, comprising: Tin with a strength of 2.2 to 2.6; Zirconium of 2.0 to 2.8; Molybdenum content: 4.8 to 5.2; Chromium content of 4.5 to 4.9; Oxygen content of 0.08 to 0.13; 0.03 to 0.11% silicon; Iron from 0 to 0.

25.

3. The titanium alloy according to claim 1, comprising: Aluminum of 5.9 to 6.0; Tin with a strength of 2.3 to 2.5; Zirconium of 2.3 to 2.6; Molybdenum content: 4.9 to 5.1; Chromium content of 4.5 to 4.8; Oxygen content of 0.08 to 0.13; 0.03 to 0.10% silicon; At most 0.07g of iron.

4. The titanium alloy of claim 1, wherein the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.8, wherein the aluminum equivalent (Al) eq = Al(wt.%) + (1 / 6)×Zr(wt.%) + (1 / 3)×Sn(wt.%) + 10×O(wt.%) and molybdenum equivalent (Mo) eq ) = Mo (wt.%) + (1 / 5) 1.7×Co(wt.%) + 2.5×Fe(wt.%).

5. The titanium alloy of claim 4, wherein the titanium alloy comprises an aluminum equivalent of 8.0 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

6. A method for preparing an alloy, the method comprising: The titanium alloy is solution treated at 800°C to 860°C for 4 hours, wherein the titanium alloy includes the titanium alloy according to claim 1. The titanium alloy is cooled to ambient temperature at a rate depending on the cross-sectional thickness of the titanium alloy; The titanium alloy was aged at 620°C to 650°C for 8 hours. as well as The titanium alloy was air-cooled.

7. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.1 to 6.1; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content of 3.3 to 4.3; Chromium content of 3.3 to 4.3; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron content between 0 and 0.30; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen from 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Balanced titanium; and impurities.

8. The titanium alloy according to claim 7, comprising: Zirconium of 2.1 to 3.1; and Silicon content ranging from 0.03 to 0.

11.

9. The titanium alloy according to claim 7 or claim 8, comprising: Aluminum of 5.6 to 5.8; Tin with a strength of 2.5 to 2.7; Zirconium of 2.6 to 2.7; Molybdenum content: 3.8 to 4.0; Chromium content of 3.7 to 3.8; Oxygen content: 0.08 to 0.14; 0.03 to 0.05% silicon; and Iron from 0 to 0.

06.

10. The titanium alloy according to any one of claims 7 to 9, wherein the titanium alloy comprises an aluminum equivalent of at least 6.9 and a molybdenum equivalent of 7.4 to 12.

8.

11. The titanium alloy according to any one of claims 7 to 10, wherein the titanium alloy comprises an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

12. An α / β titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 1.9 to 2.9; Zirconium content ranging from 1.8 to 3.0; Molybdenum of 4.5 to 5.5; Chromium content of 4.2 to 5.2; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; titanium; as well as Impurities; The α / β titanium alloy contains an aluminum equivalent value of 8.0 to 9.5; The α / β titanium alloy contains silicide precipitates; and The α / β titanium alloy contains a molybdenum equivalent value of 7.4 to 12.8 and exhibits an ultimate tensile strength of at least 1103 MPa (160 ksi) at 316°C, as measured according to ASTM E8 / E8M-09.

13. An α / β titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 1.9 to 2.9; Zirconium content ranging from 1.8 to 3.0; Molybdenum of 4.5 to 5.5; Chromium content of 4.2 to 5.2; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; titanium; as well as Impurities; The α / β titanium alloy contains an aluminum equivalent value of 8.0 to 9.5; The α / β titanium alloy contains silicide precipitates; and The α / β titanium alloy contains a molybdenum equivalent value of 7.4 to 12.8 and exhibits a yield strength of at least 966 MPa (140 ksi) at 316 °C as measured according to ASTM E8 / E8M-09.

14. The α / β titanium alloy according to claim 12 or 13, based on the total alloy weight as a percentage by weight, comprises the following: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 2.6; Zirconium of 2.0 to 2.8; Molybdenum content: 4.8 to 5.2; Chromium content of 4.5 to 4.9; Oxygen content of 0.08 to 0.13; 0.03 to 0.11% silicon; Iron with a content greater than 0 to 0.25; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

15. The α / β titanium alloy according to claim 12 or 13, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.9 to 6.0; Tin with a strength of 2.3 to 2.5; Zirconium of 2.3 to 2.6; Molybdenum content: 4.9 to 5.1; Chromium content of 4.5 to 4.8; Oxygen content of 0.08 to 0.13; 0.03 to 0.10% silicon; Iron content greater than 0 to 0.07; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

16. A method for preparing the α / β titanium alloy according to claim 12 or 13, the method comprising: The titanium alloy is solution treated at 800°C to 860°C for 4 hours, wherein the titanium alloy, based on the total alloy weight percentage, 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; greater than 0 to 0.30% iron; 0 to 0.05% nitrogen; 0 to 0.05% carbon; 0 to 0.015% hydrogen; and 0 to 0.1% each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper; titanium; and impurities; and wherein the titanium alloy contains an aluminum equivalent of 8.0 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8. The titanium alloy was cooled to ambient temperature. The titanium alloy was aged at 620°C to 650°C for 8 hours; and The titanium alloy was air-cooled.

17. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

18. The titanium alloy of claim 17, comprising 5.6 to 6.1% aluminum by weight percentage based on the total alloy weight.

19. The titanium alloy of claim 17, comprising 5.8 to 6.1% aluminum by weight percentage based on the total alloy weight.

20. The titanium alloy of claim 17, comprising 2.5 to 3.2% tin by weight percentage based on the total alloy weight.

21. The titanium alloy of claim 17, comprising 2.6 to 3.1 zirconium by weight percentage based on the total alloy weight.

22. The titanium alloy of claim 17, comprising 3.8 to 5.0% molybdenum by weight percentage based on the total alloy weight.

23. The titanium alloy of claim 17, comprising 3.8 to 4.8% molybdenum by weight percentage based on the total alloy weight.

24. The titanium alloy of claim 17, comprising 4.3 to 4.9% molybdenum by weight percentage based on the total alloy weight.

25. The titanium alloy of claim 17, comprising 3.3 to 4.3% chromium by weight percentage based on the total alloy weight.

26. The titanium alloy of claim 17, wherein it contains 0.08 to 0.14% oxygen by weight percentage based on the total alloy weight.

27. The titanium alloy of claim 17, comprising 0.04 to 0.20% silicon by weight percentage based on the total alloy weight.

28. The titanium alloy of claim 22, comprising 0.05 to 0.20% silicon by weight percentage based on the total alloy weight.

29. The titanium alloy of claim 17, comprising 0.03 to 0.11% silicon by weight percentage based on the total alloy weight.

30. The titanium alloy of claim 17, wherein it contains 0 to 0.25% iron by weight percentage based on the total alloy weight.

31. The titanium alloy according to claim 17, further comprising: Nitrogen content of 0 to 0.05; Carbon from 0 to 0.05; and Hydrogen from 0 to 0.

015.

32. The titanium alloy of claim 17, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

33. The titanium alloy of claim 32, wherein the titanium alloy exhibits a yield strength of at least 130 ksi at 316°C.

34. The titanium alloy of claim 32, wherein the titanium alloy exhibits a creep strain of not less than 0.2% for at least 86 hours at 427°C and a load of 60 ksi.

35. The titanium alloy of claim 32, wherein the titanium alloy exhibits an ultimate tensile strength of at least 150 ksi at 316°C.

36. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.6 to 6.1; Tin with a strength of 2.5 to 3.2 ppm; Zirconium content of 2.6 to 3.1; Molybdenum content: 3.8 to 5.0; Chromium content of 3.3 to 4.3; Oxygen content: 0.08 to 0.14; 0.04 to 0.20% silicon; Iron with a content greater than 0 to 0.25; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

37. The titanium alloy according to claim 36, comprising: Aluminum of 5.8 to 6.1; Tin with a strength of 2.5 to 3.2 ppm; Zirconium content of 2.6 to 3.1; Molybdenum content of 3.8 to 4.8; Chromium content of 3.3 to 4.3; Oxygen content: 0.08 to 0.14; 0.05 to 0.20% silicon; Iron with a content greater than 0 to 0.25; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

38. The titanium alloy of claim 37, comprising 0.05 to 0.11% silicon by weight percentage based on the total alloy weight.

39. The titanium alloy according to claim 36, comprising: Aluminum of 5.8 to 6.1; Tin with a strength of 2.5 to 3.2 ppm; Zirconium content of 2.6 to 3.1; Molybdenum of 4.3 to 4.9; Chromium content of 3.3 to 4.3; Oxygen content: 0.08 to 0.14; 0.05 to 0.20% silicon; Iron with a content greater than 0 to 0.25; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; and Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Titanium; and Impurities.

40. The titanium alloy of claim 39, comprising 0.05 to 0.11% silicon by weight percentage based on the total alloy weight.

41. A method for preparing an alloy, the method comprising: The titanium alloy is solution treated at 800°C to 860°C for about 30 minutes to about 4 hours, wherein the titanium alloy includes the titanium alloy according to claim 17. The titanium alloy is cooled to ambient temperature at a rate depending on the cross-sectional thickness of the titanium alloy; The titanium alloy was aged at 620°C to 650°C for about 30 minutes to about 8 hours. as well as The titanium alloy was air-cooled.

42. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Vanadium ranging from 0 to 0.1; titanium; as well as Impurities.

43. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Vanadium ranging from 0 to no more than 0.1; Titanium; and Impurities.

44. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon content of 0 to 0.05; Iron with a content greater than 0 to 0.30; Manganese content of 0 to no more than 0.1; Titanium; and Impurities.

45. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon content of 0.03 to 0.20; Iron with a content greater than 0 to 0.30; Copper with a content of 0 to no more than 0.1; titanium; as well as Impurities.

46. ​​The titanium alloy of claim 42, comprising 5.6 to 6.1% aluminum by weight percentage based on the total alloy weight.

47. The titanium alloy of claim 42, comprising 2.5 to 3.2% tin by weight percentage based on the total alloy weight.

48. The titanium alloy of claim 42, comprising 2.6 to 3.1 zirconium by weight percentage based on the total alloy weight.

49. The titanium alloy of claim 42, wherein it contains 3.8 to 5.0% molybdenum by weight percentage based on the total alloy weight.

50. The titanium alloy of claim 42, comprising 3.3 to 4.3% chromium by weight percentage based on the total alloy weight.

51. The titanium alloy of claim 42, wherein it contains 0.08 to 0.14% oxygen by weight percentage based on the total alloy weight.

52. The titanium alloy of claim 42, comprising 0.04 to less than 0.1% silicon by weight percentage based on the total alloy weight.

53. The titanium alloy of claim 42, wherein it contains more than 0 to 0.25% iron by weight percentage based on the total alloy weight.

54. The titanium alloy according to claim 42, further comprising: Nitrogen content of 0 to 0.05; Carbon from 0 to 0.05; and Hydrogen from 0 to 0.

015.

55. The titanium alloy of claim 42, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

56. The titanium alloy of claim 43, comprising 5.6 to 6.1% aluminum by weight percentage based on the total alloy weight.

57. The titanium alloy of claim 43, comprising 2.5 to 3.2% tin by weight percentage based on the total alloy weight.

58. The titanium alloy of claim 43, comprising 2.6 to 3.1 zirconium by weight percentage based on the total alloy weight.

59. The titanium alloy of claim 43, comprising 3.8 to 5.0% molybdenum by weight percentage based on the total alloy weight.

60. The titanium alloy of claim 43, comprising 3.3 to 4.3% chromium by weight percentage based on the total alloy weight.

61. The titanium alloy of claim 43, wherein it contains 0.08 to 0.14% oxygen by weight percentage based on the total alloy weight.

62. The titanium alloy of claim 43, comprising 0.04 to 0.20% silicon by weight percentage based on the total alloy weight.

63. The titanium alloy of claim 43, wherein it contains more than 0 to 0.25% iron by weight percentage based on the total alloy weight.

64. The titanium alloy according to claim 43, further comprising: Nitrogen content of 0 to 0.05; Carbon from 0 to 0.05; and Hydrogen from 0 to 0.

015.

65. The titanium alloy of claim 43, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

66. The titanium alloy of claim 44, comprising 5.6 to 6.1% aluminum by weight percentage based on the total alloy weight.

67. The titanium alloy of claim 44, comprising 2.5 to 3.2% tin by weight percentage based on the total alloy weight.

68. The titanium alloy of claim 44, comprising 2.6 to 3.1 zirconium by weight percentage based on the total alloy weight.

69. The titanium alloy of claim 44, comprising 3.8 to 5.0% molybdenum by weight percentage based on the total alloy weight.

70. The titanium alloy of claim 44, comprising 3.3 to 4.3% chromium by weight percentage based on the total alloy weight.

71. The titanium alloy of claim 44, wherein it contains 0.08 to 0.14% oxygen by weight percentage based on the total alloy weight.

72. The titanium alloy of claim 44, comprising 0.04 to less than 0.1% silicon by weight percentage based on the total alloy weight.

73. The titanium alloy of claim 44, wherein it contains more than 0 to 0.25% iron by weight percentage based on the total alloy weight.

74. The titanium alloy according to claim 44, further comprising: Nitrogen content of 0 to 0.05; Carbon from 0 to 0.05; and Hydrogen from 0 to 0.

015.

75. The titanium alloy of claim 44, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

76. The titanium alloy of claim 45, comprising 5.6 to 6.1% aluminum by weight percentage based on the total alloy weight.

77. The titanium alloy of claim 45, comprising 2.5 to 3.2% tin by weight percentage based on the total alloy weight.

78. The titanium alloy of claim 45, comprising 2.6 to 3.1 zirconium by weight percentage based on the total alloy weight.

79. The titanium alloy of claim 45, comprising 3.8 to 5.0% molybdenum by weight percentage based on the total alloy weight.

80. The titanium alloy of claim 45, comprising 3.3 to 4.3% chromium by weight percentage based on the total alloy weight.

81. The titanium alloy of claim 45, wherein it contains 0.08 to 0.14% oxygen by weight percentage based on the total alloy weight.

82. The titanium alloy of claim 45, comprising 0.04 to 0.20% silicon by weight percentage based on the total alloy weight.

83. The titanium alloy of claim 45, wherein the alloy contains more than 0 to 0.25% iron by weight percentage based on the total alloy weight.

84. The titanium alloy according to claim 45, further comprising: Nitrogen content of 0 to 0.05; Carbon from 0 to 0.05; and Hydrogen from 0 to 0.

015.

85. The titanium alloy of claim 45, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.

8.

86. A titanium alloy, comprising, by weight percentage, the following based on the total alloy weight: Aluminum of 5.5 to 6.5; Tin with a strength of 2.2 to 3.2; Zirconium content ranging from 1.8 to 3.1; Molybdenum content: 3.8 to 5.5; Chromium content of 3.3 to 4.7; Oxygen content of 0.08 to 0.15; Silicon ranging from 0 to less than 0.1; Iron with a content greater than 0 to 0.30; Each of niobium, tungsten, hafnium, nickel, gallium, antimony, vanadium, tantalum, manganese, cobalt, and copper, in amounts from 0 to 0.1; Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen concentrations of 0 to 0.015; titanium; as well as Impurities.

87. The titanium alloy according to claim 86, further comprising: Nitrogen content of 0 to 0.05; Carbon content of 0 to 0.05; Hydrogen from 0 to 0.

015.

88. The titanium alloy of claim 86, comprising an aluminum equivalent of 6.9 to 9.5 and a molybdenum equivalent of 7.4 to 12.8.

Images