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.

Abstract: This invention relates to production of ?-, near ?- and ?+?-titanium alloys from secondary raw materials, which are used mainly in manufacture of sheet material, structural parts and structural armor for defense and civil sectors. This alloy is characterized by the following chemical composition, weight percentage: 0.01-6.5 Al, 0.01-5.5 V, 0.05-2.0 Mo, 0.01-1.5 Cr, 0.1-2.5 Fe, 0.01-0.5 Ni, 0.01-0.5 Zr, 0.01-0.25 Si, oxygen—up to 0.3, carbon—up to 0.1, nitrogen—up to 0.07 and titanium—remainder. Blend is formulated based on the required tensile strength, while content of alloying elements is calculated based on design value of aluminum and molybdenum strength equivalents. The proposed alloy and the art of its manufacture helps to solve a problem of introduction of a wide range of titanium wastes to make a finished product with the required processing and structural behavior.

Abstract: The invention refers to the non-ferrous metallurgy, i.e. to the creation of the modern titanium alloys, having the high genericity. Titanium-base alloy contains aluminum, vanadium, molybdenum, chromium, iron, zirconium, oxygen and nitrogen. Herewith the components of the alloy have the following ratio by weight %; aluminun—4.0-6.0; vanadium—4.5-6.0; molybdenum—4.5-6.0; chromium—2.0-3.6; iron—0.2-0.5; zirconium—0.1-less than 0.7; oxygen—0.2 max; nitrogen—0.05 max; titanium—balance. Technical result—creation of the titanium alloy with the required strength and plastic properties. The alloy may be used to produce the wide range of the products including the large-size forgings and die-forgings as well as semiproducts of small section, such as bars and plates up to 75 mm thick.

Abstract: This invention relates to nonferrous metallurgy, namely to manufacture of near-beta titanium alloys containing titanium and such alloying elements as molybdenum, vanadium, chromium, zirconium, iron and aluminum. The provided alloy contains the following components, in weight percentages: molybdenum—25 to 27; vanadium—25 to 27; chromium—14 to 16; titanium—9 to 11; with balance aluminum and iron and zirconium in the form of commercially pure metals. The technical result of this invention is capability to produce a near-beta titanium alloy with high chemical homogeneity alloyed by refractory elements and having aluminum content <6 wt %, wherein the alloy is characterized by a combination of stable high strength and high impact strength.

Abstract: This invention relates to nonferrous metallurgy, namely to thermomechanical treatment of titanium alloys and can be used for manufacture of structural parts and components of high-strength near-beta titanium alloys for the aerospace application, mainly landing gear and airframe application. The method for thermomechanical treatment of titanium alloy consists of multiple heating operations to a temperature that is above or below beta transus temperature (BTT), hot working with the specified strain, and cooling. A technical result of this method is manufacture of near-net shape forgings with stable properties having sections with thickness 100 mm and over and length over 6 m with the following mechanical properties: 1. Ultimate tensile strength over 1200 MPa with fracture toughness, ?1C, not less than 35 MPa?m. 2. Fracture toughness, ?1C, over 70 MPa?m with ultimate tensile strength not less than 1100 MPa.

Abstract: This invention relates to production of ?-, near ?- and ?+?-titanium alloys from secondary raw materials, which are used mainly in manufacture of sheet material, structural parts and structural armor for defense and civil sectors. This alloy is characterized by the following chemical composition, weight percentage: 0.01-6.5Al, 0.01-5.5V, 0.05-2.0Mo, 0.01-1.5Cr, 0.1-2.5Fe, 0.01-0.5Ni, 0.01-0.5Zr, 0.01-0.25Si, oxygen—up to 0.3, carbon—up to 0.1, nitrogen—up to 0.07 and titanium—remainder. Blend is formulated based on the required tensile strength, while content of alloying elements is calculated based on design value of aluminum and molybdenum strength equivalents. The proposed alloy and the art of its manufacture helps to solve a problem of introduction of a wide range of titanium wastes to make a finished product with the required processing and structural behavior.

Abstract: The titanium-based alloy consists of aluminum, vanadium, molybdenum, iron, and oxygen in the following weight percent ratio: aluminum 3.5-4.4, vanadium 2.0-4.0, molybdenum 0.1-0.8, iron maximum 0.4, oxygen maximum 0.25, the balance titanium. The technical objective is to provide a versatile alloy to be used for making large forgings and die forgings, rolled sheet products and foil having sufficient strength, ductility and structure.

Abstract: The invention relates to magnesium-based alloy and, more specifically, to a magnesium alloy composition and methods of producing the same. The alloy has finer grain size, which results in improving mechanical properties of the alloy. Those mechanical properties make the alloy suitable for high-pressure casting. The alloy comprises aluminium, zinc, manganese, silicon, and calcium. A method for producing said alloy consists of loading the alloying components, pouring the molten magnesium, introducing a titanium-containing fusion cake with a flux agent and continuously agitating. The alloy is then soaked and cast.

Abstract: The inventive titanium alloy comprises, expressed in mass %: aluminium 4.0-6.0; vanadium 4.5-5.0; molybdenum 4.5-5.0; chromium 2.0-3.6; ferrum 0.2-0.5; the rest being titanium. An equivalent molybdenum content is determined as corresponding to Moequiv.≧13.8. The total aluminum and zirconium content does not exceed 7.2. The inventive method for heat treatment consists in heating to t&bgr;<>&agr;+&bgr;−(30-70)° C., conditioning during 2-5 hrs. at that temperature, air or water cooling and age-hardening at a temperature ranging from 540° C. to 600° C. during 8-16 hrs. Said alloy has a high volumetric deformability and is used for manufacturing massive large-sized forged and pressed pieces having a high strength level, satisfactory characteristics of plasticity and fracture toughness.