Patent Publication Number: US-2021164074-A1

Title: High-strength titanium alloy for additive manufacturing

Description:
FIELD 
     This applicant relates to titanium alloys and, more particularly, to high-strength alpha-beta titanium alloys for additive manufacturing. 
     BACKGROUND 
     Titanium alloys typically exhibit high strength-to-weight ratios, excellent corrosion resistance, and high-temperature properties. Therefore, titanium alloys are commonly used in the aerospace industry, such as to manufacture various aircraft components and the like. 
     Titanium alloys are relatively expensive and can be difficult to machine into complex parts that meet aerospace specifications. This has led the aerospace industry to the development of net-shape (or near net-shape) technologies, including additive manufacturing processes which reduce the amount of machining required. 
     Ti-6A1-4V is one of the most common titanium alloys used in the aerospace industry due to its ductility and relatively high tensile and shear strengths. For many applications, the desired mechanical properties of Ti-6A1-4V are achieved in mill annealed condition. Even greater strength can be achieved when Ti-6A1-4V is in solution treated and aged (STA) condition. However, Ti-6A1-4V in solution treated and aged (STA) condition is more expensive to manufacture, and is limited to relatively small cross-sections. Furthermore, the increased strength of Ti-6A1-4V in solution treated and aged (STA) condition is often at the expense of ductility. 
     Accordingly, those skilled in the art continue with research and development efforts in the fields of titanium alloys and additive manufacturing. 
     SUMMARY 
     A titanium alloy that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     A powder composition that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     A wire that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     A method for manufacturing an additive manufacturing feedstock includes the step of powderizing a titanium alloy composition that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     A method for manufacturing an additive manufacturing feedstock from a metallic starting material that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq  =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5,
 
     the method includes the steps of (1) grinding the metallic starting material to yield an intermediate powder; and (2) spheroidizing the intermediate powder to yield the additive manufacturing feedstock. 
     A method for manufacturing an additive manufacturing feedstock that includes steps of (1) melting an ingot that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5,
 
     (2) conversion of the ingot to a forged billet at beta and/or alpha-beta phase field temperatures; (3) machining of the forged billet; (4) hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a rolled stock; (5) annealing of the rolled stock at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour; (6) drawing to produce a wire with a nominal diameter of at most 3.175 mm (0.125 inches); and annealing at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour. 
     A manufacturing method comprising additively manufacturing a part from an additive manufacturing feedstock that includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     Other aspects of the disclosed high-strength titanium alloys for additive manufacturing and associated methods will become apparent from the following detailed description, the accompanying drawings and the appended claims. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a flow diagram depicting the manufacture of a bar made of the disclosed titanium alloy; 
         FIG. 2  is a flow diagram depicting one of the disclosed methods for manufacturing an additive manufacturing feedstock; 
         FIG. 3  is a flow diagram depicting another of the disclosed methods for manufacturing an additive manufacturing feedstock; 
         FIG. 4  is a flow diagram depicting yet another one of the disclosed methods for manufacturing an additive manufacturing feedstock; 
         FIG. 5  depicts the microstructure of a bar stock (diameter=12.7 mm (0.5 inches)) made of the disclosed titanium alloy; 
         FIG. 6  depicts the microstructure of a bar stock (diameter=101.6 mm (4 inches)) made of the disclosed titanium alloy; 
         FIG. 7  depicts the microstructure of a wire (diameter=5.18 mm (0.204 inches)) made of the disclosed titanium alloy; 
         FIG. 8  is a flow diagram of an aircraft manufacturing and service methodology; and 
         FIG. 9  is a block diagram of an aircraft. 
     
    
    
     DETAILED DESCRIPTION 
     Disclosed is a high-strength wrought titanium alloy for additive manufacturing. The disclosed titanium alloy can be prepared as an additive manufacturing feedstock, such as in powdered form or thin wire form, having chemistry effectively balanced with production capabilities and high ultimate tensile strength and double shear strength, while maintaining a high level of plastic properties in the annealed condition. 
     The disclosed titanium alloy includes (e.g., consists essential of) 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); inevitable impurities; and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     The disclosed titanium alloy can be made in the form of a round rolled bar with a diameter of 8 mm to 31.75 mm (0.315 inches to 1.25 inches) and minimum tensile strength of 165 ksi (1138 MPa) and minimum double shear strength of 100 ksi (689 MPa) in the annealed condition. 
     The disclosed titanium alloy can be made in the form of a round rolled bar with a diameter of 32 mm to 101.6 mm (1.25 inches to 4 inches) and minimum tensile strength of 160 ksi (1103 MPa) and minimum double shear strength of 95 ksi (655 MPa) in the annealed condition. 
     Round rolled bars (8 mm to 101.6 mm (0.315 inches to 4.0 inches)) having the disclosed mechanical properties can be achieved using a manufacturing method that includes steps of (1) melting of a titanium alloy ingot that includes 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); inevitable impurities; and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5;
 
     (2) conversion of the ingot to a forged billet at beta and/or alpha-beta phase field temperatures; (3) machining of the forged billet; (4) hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a round stock; and (5) annealing of the round stock at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour. 
     Referring to  FIG. 1 , one particular method for manufacturing a round rolled bar begins with the step of melting an ingot in a vacuum arc furnace to achieve the following chemical composition: 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); inevitable impurities; and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] 4q =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     Further, the ingot is converted to a forging stock (billet) at temperatures of beta and/or alpha-beta phase field which helps to eliminate the as-cast structure and prepare the metal structure for subsequent rolling, i.e., to produce a billet with the equiaxed macrograin. To completely remove a gas-rich layer and surface defects of hot working origin, the forging stock is machined. Hot rolling of a machined billet is carried out at a heating temperature of beta and/or alpha-beta phase field. Subsequent annealing of a rolled billet at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour with cooling down to room temperature is performed to obtain a more equilibrium structure and to lower the internal stresses. Machining of rolled billets is done to remove the scale and gas-rich layer. 
     The disclosed titanium alloy can be made in the form of a round wire with a diameter up to 10 mm (0.394 inches) produced via drawing and having minimum tensile strength of 168 ksi (1158 MPa) and minimum double shear strength of 103 ksi (710 MPa) in the annealed condition. 
     A wire (up to 10 mm (0.394 inches)) having the disclosed mechanical properties can be achieved using a manufacturing method that includes steps of (1) melting of a titanium alloy ingot that includes 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); inevitable impurities; and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5;
 
     (2) conversion of the ingot to a forged billet at beta and/or alpha-beta phase field temperatures; (3) machining of the forged billet; (4) hot rolling at a heating temperature of beta and/or alpha-beta phase field to produce a round stock; (5) annealing of the round stock at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour; (6) drawing to produce a wire; and (7) annealing the wire at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) for at least 0.5 hour. 
     Referring to  FIG. 2 , one particular method for manufacturing a wire begins with the step of melting an ingot in a vacuum arc furnace to achieve the following chemical composition: 5.5 to 6.5 wt % aluminum (Al); 3.0 to 4.5 wt % vanadium (V); 1.0 to 2.0 wt % molybdenum (Mo); 0.3 to 1.5 wt % iron (Fe); 0.3 to 1.5 wt % chromium (Cr); 0.05 to 0.5 wt % zirconium (Zr); 0.2 to 0.3 wt % oxygen (O); maximum of 0.05 wt % nitrogen (N); maximum of 0.08 wt % carbon (C); maximum of 0.25 wt % silicon (Si); inevitable impurities; and balance titanium, wherein a value of an aluminum structural equivalent [Al] eq  ranges from 7.5 to 9.5 wt %, and is defined by the following equation: 
       [Al] eq =[Al]+[O]×10+[Zr]/6, and
 
     wherein a value of a molybdenum structural equivalent [Mo] eq  ranges from 6.0 to 8.5 wt %, and is defined by the following equation: 
       [Mo] eq =[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.
 
     Further, the method includes manufacture of a forging stock (billet), rolling of a machined billet at a metal heating temperature of beta and/or alpha-beta phase field. Rolling is performed to produce a rolled stock for its subsequent coiling. To remove the internal stresses, coils are annealed at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.), followed by cooling down to room temperature. 
     To remove the scale and gas-rich layer, the coils are subjected to chemical processing or machining. After that the rolled stock is drawn to produce a wire with diameter up to 10 mm (0.394 inches). 
     To remove the internal stresses and improve the structural equilibrium, as well as to enhance the plastic properties, the produced wire is annealed at a temperature of 550° C. to 788° C. (1022° F. to 1450° F.) with subsequent air cooling. The annealed wire is either chemically processed or machined to the required size. 
     The disclosed wire may be used as an additive manufacturing feedstock. Therefore, a part (e.g., a component of an aircraft or the like) can be manufactured by additively manufacturing the part using the disclosed wire as the additive manufacturing feedstock. For example, the disclosed wire can be supplied to a three-dimensional printer, and the three-dimensional printer can be supplied with instructions for printing a net-shape (or near net-shape) part using the disclosed wire. 
     Wire having a nominal diameter of at most 10 mm (0.394 inches) is disclosed, and may be used for additive manufacturing. In one expression, the disclosed wire may have a nominal diameter of at most about 3.175 mm (0.125 inches). In another expression, the disclosed wire may have a nominal diameter between about 0.127 mm (0.005 inches) and about 3.175 mm (0.125 inches). In another expression, the disclosed wire may have a nominal diameter between about 0.127 mm (0.005 inches) and about 3 mm (0.118 inches). In another expression, the disclosed wire may have a nominal diameter between about 1.27 mm (0.050 inches) and about 1.778 mm (0.070 inches). In yet another expression, the disclosed wire may have a nominal diameter of about 1.524 mm (0.060 inches). 
     The disclosed titanium alloy can be made in the form of a powder (in powder form). For example, the disclosed titanium alloy can be made in the form of a spheroidized powder (in spheroidized powder form). 
     The disclosed powder may be used as an additive manufacturing feedstock. Therefore, a part (e.g., a component of an aircraft or the like) can be manufactured by additively manufacturing the part using the disclosed powder as the additive manufacturing feedstock. For example, the disclosed powder can be supplied to a three-dimensional printer, and the three-dimensional printer can be supplied with instructions for printing a net-shape (or near net-shape) part using the disclosed powder. 
     An additive manufacturing feedstock in powder form can be manufactured by powderizing a titanium alloy having the disclosed composition. While specific, non-limiting examples suitable powderizing techniques are disclosed, those skilled in the art will appreciate that various powderizing techniques may be used without departing from the scope of the present disclosure. 
     Referring to  FIG. 3 , an additive manufacturing feedstock  16  in powder form can be manufactured from a metallic starting material  14  using a grind-and-spheroidize process  10 . The metallic starting material  14  can be any metallic material having the disclosed titanium alloy composition. For example, the metallic starting material  14  can be an ingot, one or more of the round rolled bars disclosed herein, unused/unwanted parts, swarf or the like. 
     The disclosed grind-and-spheroidize process  10  for manufacturing an additive manufacturing feedstock  16  in powder form may include the step of grinding  24  the metallic starting material  14  to yield an intermediate powder  26 . The grinding  24  can convert the metallic starting material  14  into a powder (the intermediate powder  26 ) having the desired physical properties (e.g., desired average particle size and distribution), which can depend on numerous factors, such as the intended use of the additive manufacturing feedstock  16 . 
     Various techniques for grinding  24  can be used without departing from the scope of the present disclosure. As one non-limiting example, the grinding  24  can be performed in a planetary mill. As another non-limiting example, the grinding  24  can be performed in a roller mill. As yet another non-limiting example, the grinding  24  can be performed in a ball mill. Planetary mills, roller mills and ball mills are capable of producing an intermediate powder  26  having a particle size distribution suitable for, among other things, additive manufacturing. 
     The grinding  24  can be performed such that the intermediate powder  26  has a particle size distribution that facilitates tight packing. In one expression, the grinding  24  can be performed such that the intermediate powder  26  has an average particle size between about 5 μm and about 500 μm. In another expression, the grinding  24  can be performed such that the intermediate powder  26  has an average particle size between about 10 μm and about 100 μm. 
     Optionally, the powder produced by the grinding  24  can be sieved  28  to obtain a desired particle size distribution. For example, sieving  28  can yield an intermediate powder  26  having a narrower particle size distribution, which can increase the density of, and improve the surface quality and mechanical properties of, resulting additively manufactured parts/articles. In one expression, sieving  28  can yield an intermediate powder  26  having a particle size distribution wherein at least 40 percent of the particles of the intermediate powder  26  have a particle size within (+/−) 20 percent of the average particle size. In another expression, sieving  28  can yield an intermediate powder  26  having a particle size distribution wherein at least 60 percent of the particles of the intermediate powder  26  have a particle size within (+/−) 20 percent of the average particle size. In yet another expression, sieving  28  can yield an intermediate powder  26  having a particle size distribution wherein at least 80 percent of the particles of the intermediate powder  26  have a particle size within (+/−) 20 percent of the average particle size. 
     Optionally, the metallic starting material  14  can be hydrided in a hydriding step  30  prior to grinding  24 , thereby rendering the metallic starting material  14  more brittle and susceptible to grinding  24 . For example, the metallic starting material  14  can be hydrided in a hydriding step  30  by heating the metallic starting material  14  in the presence of hydrogen gas (e.g., in a tube furnace) to an elevated temperature (e.g., 600-700° C.) for a period of time (e.g., 24 hours). 
     When a hydriding step  30  is performed, then a corresponding dehydriding step  32  can also be performed. The dehydriding  32  can be performed after grinding  24 , and either before or after the optional sieving  28 , thereby yielding the intermediate powder  26 . For example, dehydriding  32  can be performed under vacuum at an elevated temperature (e.g., 550-700° C.) for a period of time (e.g., 72 hours). 
     Still referring to  FIG. 3 , the disclosed grind-and-spheroidize process  10  can further include spheroidizing  34  the intermediate powder  26  to yield the additive manufacturing feedstock  16  in powder form. Therefore, the particles of the additive manufacturing feedstock  16  in powder form may be substantially spherical. As used herein, “spherical” does not require perfect sphericity, but rather means “substantially spherical.” 
     Various techniques can be used for spheroidizing  34  the intermediate powder  26  without departing from the scope of the present disclosure. In one particular implementation, spheroidizing  34  can include introducing the particles of the intermediate powder  26  to a plasma, such as an induction plasma, to quickly heat and melt the particles, followed by cooling. For example, a TEKSPHERO 200™, which is commercially available from Tekna Plasma Systems Inc. of Quebec, Canada, can be used for spheroidizing  34  the intermediate powder  26  using an induction plasma. 
     Referring to  FIG. 4 , an additive manufacturing feedstock  50  in powder form can be manufactured from wire  52  having the disclosed titanium alloy composition by atomizing  54  the wire  52  to yield the additive manufacturing feedstock  50 . In one particular implementation, the atomizing  54  of the wire  52  may include plasma atomization, wherein the wire  52  is fed through a plasma to yield the additive manufacturing feedstock  50  in powder form. Various other atomizing techniques are contemplated, and may be used without departing from the scope of the present disclosure. 
     While various powderizing techniques are disclosed for obtaining a powder having the disclosed titanium alloy composition, it is also contemplated that alloying may occur at the powder level. In other words, a powder (or a consolidated mass formed from such powder) may be manufactured by admixing various powder compositions to yield a powder having the disclosed titanium alloy composition. 
     The disclosed titanium alloy can be used for additive manufacturing, such as in powder form, in wire form or other suitable form, with a high level of strength properties and double shear strength while maintaining a high level of plastic properties. 
     The disclosed titanium alloy demonstrates a combination of high processing and structural properties, which is achieved by optimal selection of alloying elements, their ratios in titanium alloy, and also by optimized parameters of thermomechanical treatment. 
     The disclosed titanium alloy is made of an alpha-beta titanium alloy containing alpha stabilizers, neutral strengtheners, and beta stabilizers. 
     A group of alpha stabilizers is formed of the elements such as aluminum and oxygen. The introduction of alpha stabilizers into titanium alloys expands the range of titanium solid solutions, reduces the density and improves the modulus of elasticity of the alloy. Aluminum is the most efficient strengthener which increases strength-to-weight ratio of the alloy, while improving the strength and high temperature behavior of titanium. When aluminum concentration in the alloy is less than 5.5 wt %, the required strength is not achieved, while concentration exceeding 6.5% leads to an undesirable decrease in plasticity with a significant increase of beta transus temperature (BTT). Oxygen increases the temperature of titanium allotropic transformation. Presence of oxygen in the range of 0.2 wt % to 0.3 wt % increases the strength without plasticity deterioration. Presence of nitrogen in the alloy in concentrations not exceeding 0.05 wt % and carbon in concentrations not exceeding 0.08 wt % has no significant effect on the decrease in plasticity at room temperature. 
     Neutral strengtheners in the disclosed titanium alloy include zirconium. Zirconium forms a wide range of solid solutions with alpha titanium, has similar a melting point and density, and improves corrosion resistance. A concentration of zirconium taken in the range of 0.05 wt % to 0.5 wt % enhances the tendency of strength increase due to the improved strength of alpha phase and effective influence on the maintenance of metastable state when cooling a stock of a heavier cross section. 
     A group of beta stabilizers disclosed herein consists of isomorphous beta stabilizers and eutectoid beta stabilizers. 
     The chemistry of the disclosed titanium alloy consists of isomorphous beta stabilizers, such as vanadium and molybdenum. A concentration of vanadium in the range of 3.0 wt % to 4.5 wt % ensures stabilization of beta phase, i.e., it hinders formation of alpha 2  superstructure in alpha phase and contributes to the improvement of both strength and plastic properties. A concentration of molybdenum in the range of 1.0 wt % to 2.0 wt % ensures its complete solubility in alpha phase, which results in a high level of strength properties without deterioration of plastic properties. When molybdenum concentration exceeds 2.0 wt %, the alloy specific gravity increases, while the alloy strength-to-weight ratio and plastic properties decrease. 
     The disclosed titanium alloy chemistry is also presented by eutectoid beta stabilizers (Cr, Fe, Si). 
     Addition of iron in the range of 0.3 wt % to 1.5 wt % increases the volume fraction of beta phase, reducing the strain resistance during hot working of the alloy, which helps to prevent defects of hot working origin. The concentration of iron over 1.5 wt % leads to segregation processes with formation of beta flecks during the alloy melting and solidification, which lead to inhomogeneity of structure and mechanical properties, as well as to deterioration of corrosion resistance. 
     Chromium concentration is established in the range of 0.3 wt % to 1.5 wt % due to its capability to strengthen titanium alloys well and act as a strong beta stabilizer. However, there is a high probability of forming embrittling intermetallics at long isothermal exposures and chemical inhomogeneities during ingot melting when alloying with chromium exceeds the established maximum limit. 
     The concentration of silicon is accepted at 0.25 wt % maximum, since silicon in the specified limits completely dissolves in alpha phase, providing for strengthening of alpha solid solution and formation of a small amount of beta phase in the alloy. Moreover, addition of silicon to the alloy increases its high temperature stability. The concentrations of silicon exceeding the above limit result in formation of silicides, which lead to reduction in creep strength and material cracking. 
     The disclosed titanium alloy is based on the possibility of separating the effects of titanium alloy strengthening via alloying with alpha stabilizers and neutral strengtheners and addition of beta stabilizers. This possibility is justified by the following considerations. Elements equivalent to aluminum strengthen titanium alloys mainly as a result of solution strengthening, while beta stabilizers strengthen titanium alloys mainly as a result of the increased amount of stronger beta phase. Therefore, in order to stabilize strength properties, there were marginal concentrations of alloying elements established. For this purpose, there was a mechanism defined for control of their ratios within the ranges of the claimed composition. 
     Structural aluminum ([Al] eq ) and molybdenum ([Mo] eq ) equivalents governed by economic, strength and processing criteria were calculated for the alloy used to make a fastener stock. 
     The structural aluminum equivalent [Al] eq  is set in the range of 7.5 to 9.5. This limitation is explained by the fact that the value of [Al] eq  below 7.5 does not ensure the required consistency of mechanical properties, and the value of [Al] eq  over 9.5 leads to the increase in solid solution strengthening which deteriorates plastic behavior and creates prerequisites for cracking during hot working. 
     The value of the structural molybdenum equivalent [Mo] eq  is taken in the range of 6.0 to 8.5, which ensures stabilization of the required amount of beta phase, phase changes upon thermal exposure to obtain a high level of strength properties of the alloy. 
     [Al] eq  and [Mo] eq  disclosed herein are the baseline categories that are established, controlled and that efficiently manage the manufacturing process to ensure a high quality part precisely meeting the customer requirements for structural and processing characteristics. The principles disclosed herein enable make-up of the deficiency in more expensive chemical elements by equivalent amounts of available less expensive alloying elements within the assigned strength equivalents and alloy chemical composition, including those alloying elements that are contained in certain amounts in the incorporated scrap. At the same time, the cost of the alloy can be reduced by 30 percent with stable preservation of high structural and operational properties of a part. 
     EXAMPLES 
     Example 1 
     To test industrial applicability, an ingot with the chemical composition shown in Table 1 was melted. The beta transus temperature was 998° C. (1828° F.). 
     
       
         
           
               
               
               
             
               
                 TABLE 1 
               
             
            
               
                   
               
               
                   
                   
                 Values of 
               
               
                 Sampling 
                 Concentration of elements, wt. % 
                 structural 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 area 
                 Al 
                 V 
                 Mo 
                 Fe 
                 Cr 
                 Zr 
                 O 
                 N 
                 C 
                 Si 
                   
                 equivalents 
               
               
                   
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 Ingot 
                 5.96 
                 3.72 
                 1.64 
                 0.77 
                 0.69 
                 0.1 
                 0.25 
                 0.002 
                 0.039 
                 0.022 
                 Balance - 
                 [Al]eq = 8.5 
               
               
                 top 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 titanium and 
                 [Mo]eq = 7.0 
               
               
                 Ingot 
                 6.01 
                 3.8 
                 1.6 
                 0.82 
                 0.71 
                 0.1 
                 0.24 
                 0.002 
                 0.047 
                 0.017 
                 inevitable 
                 [Al]eq = 8.4 
               
               
                 bottom 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 impurities 
                 [Mo]eq = 7.1 
               
               
                   
               
            
           
         
       
     
     The ingot was converted to forged billets at temperatures of beta and alpha-beta phase fields. Billets were rolled to produce a bar stock with diameter of 12.7 mm (0.5 inches) at a temperature of final rolling operation of 915° C. (1679° F.). The rolled bar stock was annealed at a temperature of 600° C. (1112° F.) for 60 minutes with air cooling down to room temperature. After that, mechanical tests and structure examination were performed. The results of mechanical tests of the bar stock after heat treatment are presented in Table 2 and the microstructure of the heat treated bar stock at magnification 200× is shown in  FIG. 5 . 
     
       
         
           
               
               
               
             
               
                   
                 TABLE 2 
               
             
            
               
                   
                   
               
               
                   
                 Tensile properties 
                   
               
            
           
           
               
               
               
               
               
               
            
               
                   
                   
                 Ultimate 
                   
                   
                 Double 
               
               
                   
                 Yield 
                 tensile 
                   
                 Reduction 
                 shear 
               
               
                 Specimen 
                 strength, 
                 strength, 
                 Elongation, 
                 of area, 
                 strength, 
               
               
                 number 
                 ksi (MPa) 
                 ksi (MPa) 
                 % 
                 % 
                 ksi (MPa) 
               
               
                   
               
            
           
           
               
               
               
               
               
               
            
               
                 1 
                 168.3 
                 179.2 
                 15.3 
                 56.6 
                 114.2 
               
               
                   
                 (1160) 
                 (1236) 
                   
                   
                 (787) 
               
               
                 2 
                 170.7 
                 181.8 
                 16.3 
                 59 
                 113.5 
               
               
                   
                 (1177) 
                 (1254) 
                   
                   
                 (783) 
               
               
                   
               
            
           
         
       
     
     Example 2 
     To produce a bar stock with diameter of 101.6 mm (4 inches), the ingot with the chemical composition shown in Table 3 was melted. The alloy beta transus temperature (BTT) determined by metallographic method was 988° C. (1810° F.). 
     
       
         
           
               
               
               
             
               
                 TABLE 3 
               
             
            
               
                   
               
               
                   
                   
                 Values of 
               
               
                 Sampling 
                 Concentration of elements, wt. % 
                 structural 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 area 
                 Al 
                 V 
                 Mo 
                 Fe 
                 Cr 
                 Zr 
                 O 
                 N 
                 C 
                 Si 
                   
                 equivalents 
               
               
                   
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 Ingot 
                 5.74 
                 3.84 
                 1.6 
                 0.72 
                 0.69 
                 0.1 
                 0.26 
                 0.006 
                 0.04 
                 0.018 
                 Balance - 
                 [Al]eq = 8.36 
               
               
                 top 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 titanium and 
                 [Mo]eq = 6.82 
               
               
                 Ingot 
                 5.74 
                 3.84 
                 1.59 
                 0.72 
                 0.7 
                 0.11 
                 0.25 
                 0.006 
                 0.038 
                 0.019 
                 inevitable 
                 [Al]eq = 8.26 
               
               
                 bottom 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 impurities 
                 [Mo]eq = 6.83 
               
               
                   
               
            
           
         
       
     
     The ingot was converted to forged billets at temperatures of beta and alpha-beta phase fields. Billets were rolled to produce a bar stock with diameter of 101.6 mm (4 inches) at a temperature of 918° C. (1685° F.). The test coupons of the rolled bar stock with diameter of 101.6 mm (4 inches) and length of 101.6 mm (4 inches) were annealed at a temperature of 600° C. (1112° F.) for 60 minutes. After that, mechanical tests in longitudinal direction and structure examination were performed. The results of mechanical tests of the bar stock after heat treatment are presented in Table 4 and the microstructure of the bar stock at magnification 200× is shown in  FIG. 6 . 
     
       
         
           
               
               
               
             
               
                   
                 TABLE 4 
               
             
            
               
                   
                   
               
               
                   
                 Tensile properties 
                   
               
            
           
           
               
               
               
               
               
               
            
               
                   
                   
                 Ultimate 
                   
                   
                 Double 
               
               
                   
                 Yield 
                 tensile 
                   
                 Reduction 
                 shear 
               
               
                 Specimen 
                 strength, 
                 strength, 
                 Elongation, 
                 of area, 
                 strength, 
               
               
                 number 
                 ksi (MPa) 
                 ksi (MPa) 
                 % 
                 % 
                 ksi (MPa) 
               
               
                   
               
            
           
           
               
               
               
               
               
               
            
               
                 1 
                 149.1 
                 163.3 
                 15.3 
                 48.3 
                 104.6 
               
               
                   
                 (1028) 
                 (1126) 
                   
                   
                 (721) 
               
               
                 2 
                 149.5 
                 162.5 
                 16 
                 52.2 
                 106.6 
               
               
                   
                 (1031) 
                 (1121) 
                   
                   
                 (735) 
               
               
                   
               
            
           
         
       
     
     Example 3 
     To produce a wire with diameter of 5.18 mm (0.204 inches), the ingot with the chemical composition shown in Table 5 was melted. The alloy beta transus temperature (BTT) determined by metallographic method was 988° C. (1810° F.). 
     
       
         
           
               
               
               
             
               
                 TABLE 5 
               
             
            
               
                   
               
               
                   
                   
                 Values of 
               
               
                 Sampling 
                 Concentration of elements, wt. % 
                 structural 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 area 
                 Al 
                 V 
                 Mo 
                 Fe 
                 Cr 
                 Zr 
                 O 
                 N 
                 C 
                 Si 
                   
                 equivalents 
               
               
                   
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
               
               
            
               
                 Ingot 
                 5.74 
                 3.84 
                 1.6 
                 0.72 
                 0.69 
                 0.1 
                 0.26 
                 0.006 
                 0.04 
                 0.018 
                 Balance - 
                 [Al]eq = 8.36 
               
               
                 top 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 titanium and 
                 [Mo]eq = 6.82 
               
               
                 Ingot 
                 5.74 
                 3.84 
                 1.59 
                 0.72 
                 0.7 
                 0.11 
                 0.25 
                 0.006 
                 0.038 
                 0.019 
                 inevitable 
                 [Al]eq = 8.26 
               
               
                 bottom 
                   
                   
                   
                   
                   
                   
                   
                   
                   
                   
                 impurities 
                 [Mo]eq = 6.83 
               
               
                   
               
            
           
         
       
     
     The ingot was converted to forged billets at temperatures of beta and alpha-beta phase fields. Billets were rolled to produce a stock with diameter of 101.6 mm (4 inches) at a temperature of 918° C. (1685° F.). The rolled stock with diameter of 101.6 mm (4 inches) was rolled to a stock with diameter of 7.92 mm (0.312 inches) with the end of hot working in alpha-beta phase field. The rolled stock with diameter of 7.92 mm (0.312 inches) was degassed in a vacuum furnace and then drawn via several stages to produce a wire with diameter of 6.07 mm (0.239 inches). The wire was annealed under the following conditions: heating to 705° C. (1300° F.), soaking for 1 hour, air cooling. Wire grinding and polishing were followed by blasting and pickling. After that, the wire was lubed and sized to diameter of 5.18 mm (0.204 inches). The results of mechanical tests of the wire with diameter of 5.18 mm (0.204 inches) after annealing are presented in Table 6. The microstructure of the wire at magnification 800× is shown in  FIG. 7 . 
     
       
         
           
               
               
               
             
               
                   
                 TABLE 6 
               
             
            
               
                   
                   
               
               
                   
                 Tensile properties 
                   
               
            
           
           
               
               
               
               
               
               
            
               
                   
                   
                 Ultimate 
                   
                   
                 Double 
               
               
                   
                 Yield 
                 tensile 
                   
                 Reduction 
                 shear 
               
               
                 Specimen 
                 strength, 
                 strength, 
                 Elongation, 
                 of area, 
                 strength, 
               
               
                 number 
                 ksi (MPa) 
                 ksi (MPa) 
                 % 
                 % 
                 ksi (MPa) 
               
               
                   
               
               
                 1 
                 164 
                 190 
                 21 
                 58 
                 111 
               
               
                   
                 (1131) 
                 (1310) 
                   
                   
                 (765) 
               
               
                 2 
                 160 
                 188 
                 18 
                 57 
                 110 
               
               
                   
                 (1103) 
                 (1296) 
                   
                   
                 (758) 
               
               
                   
               
            
           
         
       
     
     Examples 4-21 and Comparative Examples C1-C9 
     The disclosed titanium alloy was evaluated for use in additive manufacturing. Test parts having a T-shaped structure were additively manufactured using the disclosed additive manufacturing feedstock. Ten of the test parts (Examples 4-13) had the chemical composition shown in Table 7, while eight of the test parts (Examples 14-21) had the chemical composition shown in Table 8. All eighteen test parts (Examples 4-21) were annealed at 1375° F. (746° C.) for two hours. 
     
       
         
           
               
               
             
               
                 TABLE 7 
               
             
            
               
                   
               
               
                 Exam- 
                   
               
               
                 ples 
                 Concentration of elements, wt. % 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
            
               
                 4-13 
                 Al 
                 V 
                 Fe 
                 Mo 
                 Cr 
                 C 
                 Zr 
                 O 
                 N 
               
               
                   
               
               
                 Target 
                 5.80 
                 4.00 
                 0.80 
                 1.50 
                 0.70 
                 0.040 
                 0.100 
                 0.25 
                   
               
               
                 Bottom 
                 5.82 
                 3.92 
                 0.81 
                 1.65 
                 0.72 
                 0.044 
                 0.100 
                 0.25 
                 0.001 
               
               
                 Top 
                 5.86 
                 3.93 
                 0.75 
                 1.65 
                 0.68 
                 0.051 
                 0.100 
                 0.23 
                 0.001 
               
               
                   
               
            
           
         
       
     
     
       
         
           
               
               
             
               
                 TABLE 8 
               
             
            
               
                   
               
               
                 Exam- 
                   
               
               
                 ples 
                 Concentration of elements, wt. % 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
            
               
                 14-21 
                 Al 
                 V 
                 Fe 
                 Mo 
                 Cr 
                 C 
                 Zr 
                 O 
                 N 
               
               
                   
               
               
                 Target 
                 6.00 
                 3.80 
                 0.80 
                 1.50 
                 0.70 
                 0.040 
                 0.100 
                 0.25 
                   
               
               
                 Bottom 
                 5.96 
                 3.72 
                 0.77 
                 1.64 
                 0.69 
                 0.039 
                 0.100 
                 0.25 
                 0.002 
               
               
                 Top 
                 6.01 
                 3.80 
                 0.82 
                 1.60 
                 0.71 
                 0.047 
                 0.100 
                 0.24 
                 0.002 
               
               
                   
               
            
           
         
       
     
     For comparison, the same T-shaped test parts were additively manufactured using standard Ti-6A1-4V (Comparative Examples C1-C9). The Ti-6A1-4V test parts underwent heat treatment such that they were in solution treated and aged (STA) condition. 
     Tensile coupons were extracted from the test parts and mechanical tests were performed in accordance with ASTM E8. The results are presented in Table 9. 
     
       
         
           
               
               
               
               
               
               
               
             
               
                   
                 TABLE 9 
               
             
            
               
                   
                   
               
               
                   
                   
                 Stressed 
                   
                   
                   
                   
               
               
                   
                 Temp. 
                 Dimension 
                 0.2% Yield 
                 Ultimate 
                 Elong 4D/4W 
                 R of A 
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
            
               
                 Ex. 
                 ° F. 
                 in 
                 lbs 
                 ksi 
                 lbs 
                 ksi 
                 in 
                 % 
                 in 
                 % 
               
               
                   
               
            
           
           
               
               
               
               
               
               
               
               
               
               
               
            
               
                 4 
                 RT 
                 0.250 (d) 
                 7416 
                 151.1 
                 7954 
                 162 
                 1.115 
                 11.5 
                 0.215 
                 26 
               
               
                 5 
                 RT 
                 0.251 (d) 
                 7442 
                 150.4 
                 8045 
                 162.6 
                 1.103 
                 10.3 
                 0.233 
                 13.8 
               
               
                 6 
                 RT 
                 0.251 (d) 
                 7483 
                 151.2 
                 8003 
                 161.7 
                 1.098 
                 9.8 
                 0.223 
                 21.1 
               
               
                 7 
                 RT 
                 0.250 (d) 
                 7474 
                 152.3 
                 8031 
                 163.6 
                 1.122 
                 12.2 
                 0.22 
                 22.6 
               
               
                 8 
                 RT 
                 0.251 (d) 
                 7507 
                 151.7 
                 8009 
                 161.9 
                 1.095 
                 9.5 
                 0.225 
                 19.6 
               
               
                 9 
                 RT 
                 0.251 (d) 
                 7343 
                 148.4 
                 7880 
                 159.3 
                 1.093 
                 9.3 
                 0.224 
                 20.4 
               
               
                 10 
                 RT 
                 0.250 (d) 
                 7407 
                 150.9 
                 7758 
                 158 
                 1.07 
                 7 
                 0.236 
                 10.9 
               
               
                 11 
                 RT 
                 0.251 (d) 
                 7613 
                 153.9 
                 7862 
                 158.9 
                 1.047 
                 4.7 
                 0.24 
                 8.6 
               
               
                 12 
                 RT 
                 0.251 (d) 
                 8228 
                 166.3 
                 8367 
                 169.1 
                 1.035 
                 3.5 
                 0.246 
                 3.9 
               
               
                 13 
                 RT 
                 0.251 (d) 
                 7670 
                 155 
                 8125 
                 164.2 
                 1.07 
                 7 
                 0.24 
                 8.6 
               
               
                 14 
                 RT 
                 0.251 (d) 
                 7685 
                 155.3 
                 8251 
                 166.8 
                 1.101 
                 10.1 
                 0.233 
                 13.8 
               
               
                 15 
                 RT 
                 0.251 (d) 
                 7715 
                 155.9 
                 8241 
                 166.5 
                 1.139 
                 13.9 
                 0.213 
                 28 
               
               
                 16 
                 RT 
                 0.250 (d) 
                 7558 
                 154 
                 8106 
                 165.1 
                 1.141 
                 14.1 
                 0.201 
                 35.4 
               
               
                 17 
                 RT 
                 0.251 (d) 
                 7623 
                 154.1 
                 8217 
                 166.1 
                 1.107 
                 10.7 
                 0.232 
                 14.6 
               
               
                 18 
                 RT 
                 0.250 (d) 
                 7574 
                 154.3 
                 8136 
                 165.7 
                 1.053 
                 5.3 
                 0.24 
                 7.8 
               
               
                 19 
                 RT 
                 0.250 (d) 
                 7669 
                 156.2 
                 7731 
                 157.5 
                 1.013 
                 1.3 
                 0.247 
                 2.4 
               
               
                 20 
                 RT 
                 0.250 (d) 
                 7556 
                 153.9 
                 7813 
                 159.2 
                 1.027 
                 2.7 
                 0.243 
                 5.5 
               
               
                 21 
                 RT 
                 0.251 (d) 
                 8600 
                 173.8 
                 8712 
                 176.1 
                 1.02 
                 2 
                 0.242 
                 7 
               
               
                 C1 
                 RT 
                 0.250 (d) 
                 6512 
                 132.7 
                 7052 
                 143.7 
                 1.119 
                 11.9 
                 0.207 
                 31.4 
               
               
                 C2 
                 RT 
                 0.251 (d) 
                 6449 
                 130.3 
                 6913 
                 139.7 
                 1.127 
                 12.7 
                 0.203 
                 34.6 
               
               
                 C3 
                 RT 
                 0.250 (d) 
                 6461 
                 131.6 
                 6934 
                 141.3 
                 1.135 
                 13.5 
                 0.213 
                 27.4 
               
               
                 C4 
                 RT 
                 0.251 (d) 
                 6517 
                 131.7 
                 6999 
                 141.4 
                 1.12 
                 12 
                 0.218 
                 24.6 
               
               
                 C5 
                 RT 
                 0.251 (d) 
                 6283 
                 127 
                 6814 
                 137.7 
                 1.102 
                 10.2 
                 0.225 
                 19.6 
               
               
                 C6 
                 RT 
                 0.250 (d) 
                 6446 
                 131.3 
                 6856 
                 139.7 
                 1.162 
                 16.2 
                 0.205 
                 32.8 
               
               
                 C7 
                 RT 
                 0.250 (d) 
                 6418 
                 130.7 
                 6964 
                 141.9 
                 1.045 
                 4.5 
                 0.238 
                 9.4 
               
               
                 C8 
                 RT 
                 0.251 (d) 
                 6275 
                 126.8 
                 6821 
                 137.9 
                 1.045 
                 4.5 
                 0.235 
                 12.3 
               
               
                 C9 
                 RT 
                 0.251 (d) 
                 6636 
                 134.1 
                 7239 
                 146.3 
                 1.078 
                 7.8 
                 0.235 
                 12.3 
               
               
                   
               
            
           
         
       
     
     The annealed titanium alloy performed well, as comparted to standard solution treated and aged (STA) Ti-6A1-4V. It is noted that Examples 11-14,17-20, C6 and C7 exhibited a fractured outer-quarter. 
     Examples of the disclosure may be described in the context of an aircraft manufacturing and service method  100 , as shown in  FIG. 8 , and an aircraft  102 , as shown in  FIG. 9 . During pre-production, the aircraft manufacturing and service method  100  may include specification and design  104  of the aircraft  102  and material procurement  106 . During production, component/subassembly manufacturing  108  and system integration  110  of the aircraft  102  takes place. Thereafter, the aircraft  102  may go through certification and delivery  112  in order to be placed in service  114 . While in service by a customer, the aircraft  102  is scheduled for routine maintenance and service  116 , which may also include modification, reconfiguration, refurbishment and the like. 
     Each of the processes of method  100  may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of venders, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on. 
     As shown in  FIG. 9 , the aircraft  102  produced by example method  100  may include an airframe  118  with a plurality of systems  120  and an interior  122 . Examples of the plurality of systems  120  may include one or more of a propulsion system  124 , an electrical system  126 , a hydraulic system  128 , and an environmental system  130 . Any number of other systems may be included. 
     The disclosed high-strength titanium alloy may be employed during any one or more of the stages of the aircraft manufacturing and service method  100 . As one example, components or subassemblies corresponding to component/subassembly manufacturing  108 , system integration  110 , and or maintenance and service  116  may be fabricated or manufactured using the disclosed high-strength titanium alloy. As another example, the airframe  118  maybe constructed using the disclosed high-strength titanium alloy. Also, one or more apparatus examples, method examples, or a combination thereof may be utilized during component/subassembly manufacturing  108  and/or system integration  110 , for example, by substantially expediting assembly of or reducing the cost of an aircraft  102 , such as the airframe  118  and/or the interior  122 . Similarly, one or more of system examples, method examples, or a combination thereof may be utilized while the aircraft  102  is in service, for example and without limitation, to maintenance and service  116 . 
       100861  The disclosed high-strength titanium alloy is described in the context of an aircraft; however, one of ordinary skill in the art will readily recognize that the disclosed high-strength titanium alloy may be utilized for a variety of applications. For example, the disclosed high-strength titanium alloy may be implemented in various types of vehicle including, for example, helicopters, passenger ships, automobiles, marine products (boat, motors, etc.) and the, like. Various non-vehicle applications, such as medical applications, are also contemplated. 
     Although various aspects of the disclosed high-strength titanium alloy for additive manufacturing have been shown and described, modifications may occur to those skilled in the art upon reading the specification. The present application includes such modifications and is limited only by the scope of the claims.