A method of titanium rod additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; isostatic pressing the powder blend to form a billet having a cross-sectional profile; cutting the billet to form a rod feedstock having the first cross-sectional profile; loading the rod feedstock into an additive manufacturing machine configured to deposit the rod feedstock; and producing a metallic component from the rod feedstock.

A method of forming a rod feedstock for titanium stir friction welding additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; at least one of die pressing the powder blend to form a die pressed powder or continuously powder rolling the powder blend to form a die pressed powder; and sintering the powder blend to form a rod feedstock having a cross-sectional profile.

A spiral timepiece spring with a two-phase structure, made of a niobium and titanium alloy, and method for manufacturing this spring, including: producing a binary alloy containing niobium and titanium, with: niobium: the remainder to 100%; titanium: strictly greater than 60% and less than or equal to 85% by mass of the total, traces of components from among O, H, C, Fe, Ta, N, Ni, Si, Cu, Al; applying deformations alternated with heat treatments until a two-phase microstructure is obtained comprising a solid solution of niobium with β-phase titanium and a solid solution of niobium with α-phase titanium, the α-phase titanium content being greater than 10% by volume, wire drawing to obtain wire able to be calendered; calendering or insertion into a ring to form a mainspring, in a double clef shape before it is wound for the first time, or winding to form a balance spring.

A controlled thermal coefficient product manufacturing system and method is disclosed. The disclosed product relates to the manufacture of metallic material product (MMP) having a thermal expansion coefficient (TEC) in a predetermined range. The disclosed system and method provides for a first material deformation (FMD) of the MMP that comprises at least some of a first material phase (FMP) wherein the FMP comprises martensite randomly oriented and a first thermal expansion coefficient (FTC). In response to the FMD at least some of the FMP is oriented in at least one predetermined orientation. Subsequent to deformation, the MMP comprises a second thermal expansion coefficient (STC) that is within a predetermined range and wherein the thermal expansion of the MMP is in at least one predetermined direction. The MMP may be comprised of a second material phase (SMP) that may or may not transform to the FMP in response to the FMD.

A method (100) for producing a particulate titanium alloy product can include preparing (110) a composite particulate oxide mixture with TiO.sub.2 powder and at least one alloying element powder. The composite particulate oxide mixture can be co-reduced (120) using a metallic reducing agent under a hydrogen atmosphere at a reduction temperature for a reduction time sufficient to produce a hydrogenated titanium alloy product. The hydrogenated titanium alloy product can then be heat treated (130) under a hydrogen atmosphere and a heat treating temperature to reduce pore size and specific surface area to form a heat treated hydrogenated titanium product. The heat treated hydrogenated titanium product can be deoxygenated (140) to reduce residual oxygen to less than 0.2 wt % to form a deoxygenated hydrogenated titanium product as a particulate. The deoxygenated hydrogenated titanium product can optionally be dehydrogenated (150) to form the titanium alloy product as a particulate.

A method for treating a surface of a metallic part in particular of a turbomachine includes a step of shot-peening a surface of the metallic part using metallic beads and a step of cleaning the surface of the metallic part after the shot peening. The cleaning comprises step includes applying a magnetic cleaning paste to the surface of the metallic part in such a way as to remove any residues of metallic beads.

A high-strength α+β type hot-rolled titanium alloy sheet containing 0.8 to 1.5 mass % Fe, 4.8 to 5.5 mass % Al, 0.030 mass % N, O and N, wherein cracks are prevented from spreading, wherein: (a) ND represents normal direction of a hot-rolled sheet; RD represents hot rolling direction; TD represents hot rolling width direction; θ represents the angle formed between c axis and ND; φ represents angle formed between plane including c axis and ND, and a plane including ND and TD; (b1) XND represents highest (0002) relative intensity of X-ray reflection by grains when θ is from 0° to 30° ; (b2) XTD represents the highest (0002) relative intensity of the X-ray reflection caused by grains when θ is from 80° to 100° and φ is ±10° . (c) The high-strength α+β type hot-rolled titanium alloy sheet has a value for XTD/XND of at least 4.0. Q(%)=[O]+2.77.Math.[N].

Methods for forming a blade for a gas turbine engine include altering the crystallographic texture of the blade in a discrete region relative to the surrounding locations of the blade to minimize flutter and/or mistune the blade by changing the natural frequency response of at least one mode of the blade.

A method for forming large titanium parts includes forming bends into a titanium plate for form a bent part. The bent part is then roll-formed to form contours into the bent part. The surfaces of the contoured part are rough-machined, and the part is then secured to a bladed form fixture. The bladed form fixture comprises a plurality of header boards that secure the part to the fixture. The fixture part is placed in a thermal vacuum furnace and a stress-relieving operation is performed. The part is removed from the fixture and final machining takes place.

There is provided a titanium alloy member including a base metal portion, and an outer hardened layer formed on an outer layer of the base metal portion, the cross sectional hardness of the base metal portion is 330 HV or higher and lower than 400 HV, the cross sectional hardnesses at positions 5 μm and 15 μm from the surface of the outer hardened layer are 450 HV or higher and lower than 600 HV, the outer hardened layer includes an oxygen diffusion layer and a nitrogen diffusion layer, the oxygen diffusion layer is at a depth of 40 to 80 μm from the surface of the outer hardened layer, and the nitrogen diffusion layer is at a depth of 2 to 5 μm from surface of the outer hardened layer. This titanium alloy member includes an outer hardened layer, is high in cross sectional hardness of the base metal portion, and is excellent in fatigue strength and wear resistance.