Abstract: A titanium alloy for additive manufacturing 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); 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.

Abstract: This invention generally relates to the field of nonferrous metallurgy, namely to titanium alloy materials with specified mechanical properties for manufacturing the aircraft fasteners. A stock for high strength fastener is manufactured from wrought titanium alloy containing, in weight percentages, 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.15 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, balance titanium and inevitable impurities, having the value of aluminum structural equivalent [Al] eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo] eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al] eq=[Al]+[O]×10+[Zr]/6; [Mo] eq=[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.

Abstract: This invention generally relates to the field of nonferrous metallurgy, namely to titanium alloy materials with specified mechanical properties for manufacturing the aircraft fasteners. A stock for high strength fastener is manufactured from wrought titanium alloy containing, in weight percentages, 5.5 to 6.5 Al, 3.0 to 4.5 V, 1.0 to 2.0 Mo, 0.3 to 1.5 Fe, 0.3 to 1.5 Cr, 0.05 to 0.5 Zr, 0.15 to 0.3 O, 0.05 max. N, 0.08 max. C, 0.25 max. Si, balance titanium and inevitable impurities, having the value of aluminum structural equivalent [Al]eq in the range of 7.5 to 9.5, and the value of molybdenum structural equivalent [Mo]eq in the range of 6.0 to 8.5, where the equivalents are defined by the following equations: [Al]eq=[Al]+[O]×10+[Zr]/6; [Mo]eq=[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5.

Abstract: A titanium alloy for additive manufacturing 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); 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.

Abstract: Herein disclosed includes the manufacture of sheets from a titanium alloy having a chemical composition efficiently balanced with manufacturability based on known conventional manufacturing techniques for finished products exhibiting low temperature superplastic forming properties. The result is achieved by a sheet material for low temperature superplastic made of titanium alloy with the following content of element by % wt.: 4.5-5.5Al, 4.5-5.5V, 0.1-1.0Mo, 0.8-1.5Fe, 0.1-0.5Cr, 0.1-0.5Ni, 0.16-0.25O, remainder is titanium and residual elements and having molybdenum structural equivalent [Mo]eqiv.>5 and aluminum structural equivalent [Al]equiv.<8; the equivalent values are calculated from the expressions: [Mo]eqiv.=[Mo]+[V]/1.5+[Cr]×1.25+[Fe]×2.5+[Ni]/0.8 [Al]eqiv.=[Al]+[O]×10+[Zr]/6.