Abstract: A near-&bgr; or &bgr; titanium alloy having high strength, high ductility, and high toughness which is capable of coil rolling at a high temperature and recoiling for high productivity, and a process for producing said titanium alloy. The titanium alloy contains not more than 1.0% (excluding 0%) of Si alone or in combination with not more than 10% of Sn. The process comprises heating a &bgr; alloy or near-&bgr; alloy containing not more than 1.0% (excluding 0%) of Si alone or in combination with not more than 10% of Sn and subjecting said alloy to plastic deformation while keeping silicides solved in it at a temperature above the &bgr;-transus, so that silicides precipitate in the form of fine particles, with recrystallization suppressed. The resulting titanium alloy is good in workability and has high strength after aging treatment.

Abstract: Described is a method for producing a diffusion bonded sputtering target assembly which is thermally treated to precipitation harden the backing plate without compromising the diffusion bond integrity. The method includes heat treating and quenching to alloy solution and artificially age the backing plate material after diffusion bonding to a target. Thermal treatment of the diffusion bonded sputtering target assembly includes quenching by partial-immersion in a quenchant and is performed after diffusion bonding and allows for various tempers in the backing plate.

Abstract: Described is a titanium sputtering target to provide improved step coverage and a method of making same.

Abstract: An alpha-beta titanium-base alloy is heat treated to improve its dwell fatigue properties while retaining a good balance of mechanical properties. The heat treatment includes first heating the alpha-beta titanium-base alloy to a first heat-treatment temperature in a first range of from about 70° F. below a beta transus temperature of the alpha-beta titanium-base alloy to the beta transus temperature of the alpha-beta titanium-base alloy, and quenching the alpha-beta titanium-base alloy at a rate of greater than about 200° F. per minute. The alpha-beta titanium-base alloy is second heated to a second heat-treatment temperature in a second range of from about 100° F. to about 400° F. below the beta transus temperature of the alpha-beta titanium-base alloy, and thereafter cooling the alpha-beta titanium-base alloy to ambient temperature at a rate of from about 10° F. per minute to about 200° F. per minute.

Abstract: A titanium alloy having improved heat resistance in addition to the inherent properties of lightness and corrosion resistance. The alloy consists essentially of, by weight %, Al: 5.0-7.0%, Sn: 3.0-5.0%, Zr: 2.5-6.0%, Mo: 2.0-4.0%, Si: 0.05-0.80%, C: 0.001-0.200%, O: 0.05-0.20%, optionally further one or two of Nb and Ta: 0.3-2.0%, and the balance of Ti and inevitable impurities. A method of producing parts from this alloy comprises subjecting the titanium alloy of the above described alloy composition to heat treatment at a temperature of &bgr;-region, combination of rapid cooling and slow cooling or combination of water quenching and annealing, hot processing in &agr;+&bgr; region, solution treatment and aging treatment.

Abstract: A monolithic refractory depositing system capable of improving working environment and working efficiency and of spraying a material in a uniform thickness is provided. The monolithic refractory depositing system is capable of carrying out both a spraying process and a casting process.

Abstract: A method for making a titanium or titanium alloy strip or strips having homogeneous gloss between the strips and throughout the same strip comprises subjecting the strip or strips to a continuous annealing and pickling line or only in a pickling line, wherein the strip or strips are passed through a pickling vessel having an immersion roll plural times and are appropriately inverted at least once during the plural times.

Abstract: The disclosed &bgr; titanium alloys contain alloying elements of molybdenum between 10.0 and 12.0 weight percent, aluminum between 2.8 and 4.0 weight percent, chromium and vanadium between 0.0 and 2.0 weight percent, and niobium between 0.0 and 4.0 weight percent. Orthodontic arch wires and appliances of nickel-free &bgr; titanium alloys having pseudo-elastic properties associated with stress-induced martensitic transformation. These arch wires and appliances were found to possess a high strain recovery up to 3.5% strain of deformation, a lower stiffness yielding relatively constant force for tooth movement and improved formability over that of pseudo-elastic nitinol. Eyeglasses having parts made of such materials can be welded. Stents made of this material avoid problems which a certain percentage of the population have when nickel is included within alloys used in the human body. Other medical devices which are used in the body also have this benefit.

Abstract: Disposing the titanium or titanium alloy in a vacuum vessel, and applying annealing treatment thereto by heating (a heating process); feeding a mixed gas consisting primarily of nitrogen with a trace of oxygen component into the vessel, and heating inside the vacuum vessel at temperatures in the range of 700 to 800° C. in a predetermined reduced pressure condition for a predetermined length of time such that nitrogen and oxygen are diffused into the interior of the titanium or titanium alloy from the surface thereof so as to pass into solid solution therein (a hardening treatment process); and cooling the titanium or titanium alloy to room temperature after the hardening treatment process (a cooling process), are carried out. After completion of the processes described above, a hard surface layer 101 is formed in the surface region of the titanium or titanium alloy 100.

Abstract: A process for treating an alpha-beta titanium alloy to improve cryogenic notch tensile ratio comprises heating the alloy to near or above its beta transus temperature for a sufficient time to dissolve substantially all alpha grains and thus transform the alloy to the beta form, rapidly cooling the alloy from this temperature to induce a martensitic transformation and produce a fine platelet microstructure, isothermally forging the alloy about 50 to 80 percent at about 300° C. below the beta transus temperature to attain a fine equiaxed microstructure such that the largest microstructural unit is about 2-5 &mgr;m, and then aging the alloy at a temperature about 25° C. to 75° C. below the beta transus to grow the refined equiaxed microstructure such that the largest microstructural unit is about 5-10 &mgr;m.

Abstract: Alloy of the Ti2AlX type composed at least essentially of the elements Ti, Al, Nb, Ta and Mo and in which the relative amounts as atoms of said elements and of silicon are substantially within the following intervals: Al: 20 to 25% Nb: 10 to 15% Ta: 1.4 to 5%   Mo: 2 to 4% Ti: remainder to 100%. This alloy exhibits properties superior to those of the known titanium alloys.

Abstract: An improved guiding member for use within a body lumen having a unique combination of superelastic characteristics. The superelastic alloy material has a composition consisting of about 30% to about 52% (atomic) titanium, and about 38% to 52% nickel and may have one or more elements selected from the group consisting of iron, cobalt, platinum, palladium, vanadium, copper, zirconium, hafnium and niobium. The alloy material is subjected to thermomechanical processing which includes a final cold working of about 10 to about 75% and then a heat treatment at a temperature between about 450.degree. and about 600.degree. C. and preferably about 475.degree. to about 550.degree. C. Before the heat treatment the cold worked alloy material is preferably subjected to mechanical straightening. The alloy material is preferably subjected to stresses equal to about 5 to about 50% of the room temperature ultimate yield stress of the material during the thermal treatment.

Abstract: Modern brake rotors require enhanced resistance to thermal stress in order to withstand vigorous operating conditions. A brake rotor manufactured from (.alpha.+.beta.) titanium alloy will fulfill the thermal stress requirements when an equiaxed grain structure is imposed on the alloy. The equiaxed grains can preferably range from 300 .mu.m to 3 mm in size. The equiaxed grain structure is attained by heat treating the brake rotor at the .beta. phase transformation temperature, followed by quenching. When Ti-6Al-4V titanium alloy is used to form the brake rotor, .beta. phase transformation temperature is 1000.degree. C. the heat treatment temperature range is 986-1200.degree. C. The preferable heat treatment for Ti-6Al-4V alloy is 1050.degree. C. for 2 hours.

Abstract: A titanium-based intermetallic alloy having a high yield stress, a high creep resistance and sufficient ductility at ambient temperature has the following chemical composition as measured in atomic percentages:Al, from 16 to 26; Nb, from 18 to 28; Mo, from 0 to 2; Si, from 0 to 0.8; Ta, from 0 to 2; Zr, from 0 to 2; and Ti as the balance to 100; with the condition that Mo+Si+Zr+Ta>0.4%.Production, working and heat-treatment ranges adapted to the intended use of the material are also defined.

Abstract: A method for producing titanium alloy turbine blades comprising the steps of (a) forming turbine blades of titanium alloy through hot forging or machining, (b) cooling leading edges on tip portions of the turbine blades including covers thereof formed through hot forging or machining faster than blade main body after final hot forging or solid solution treatment, and (c) heat treating the cooled turbine blades. With this method, it is possible to manufacture titanium turbine blades in an economical fashion and obtain titanium alloy turbine blades superior in reliability by preventing erosion.

Abstract: An alpha-beta titanium alloy preform is processed in the beta phase field, by heat treating or beta forging. The processed preform is thereafter heated into the alpha-beta phase field, and a preselected portion is forged, leaving a nonselected portion that is not forged in the alpha-beta phase field. The resulting article has a beta-processed structure in the nonselected portion, and a beta-processed plus alpha-beta forged structure in the preselected portion. In one application, the preform has the shape of a disk useful in the manufacture of an aircraft gas turbine engine. Depending upon specific requirements, either the center or the rim of the disk may be the selected portion.

Abstract: A high purity titanium polycrystalline target with uniform grain size and near ideal (103) crystallographic orientation and a method of making. Uniform grain size from 10 .mu.m-500 .mu.m is achieved by using a fine grain five inch diameter titanium billet produced by hot working an electron beam cast billet. Greater than 80% (103) crystallographic orientation is achieved while maintaining uniform and optimal grain size in the target. The result is a higher collimated deposition rate with increased efficiency of bottom coverage of vias and a highly (002) oriented titanium film.

Abstract: This invention relates to a hydrogen-absorbing alloy, and particularly provides a hydrogen-absorbing alloy having a body-centered cubic structure which has a periodical structure formed by spinodal decomposition, has a large hydrogen storage amount, has excellent hydrogen desorption characteristics and can mitigate activation conditions, the alloy comprises at least two elements of alloy components, wherein the relational curve between chemical free energy of solid solutions and an alloy composition has a shape describing an upwardly convexed curve, or said alloy comprises two solid solutions having a regular periodical structure formed by spinodal decomposition within a region satisfying the relation d.sup.2 G/dX.sub.B.sup.2 <0 (where G is chemical free energy and X.sub.B is a solute alloy concentration) as the principal phase.

Abstract: Process for improving the mechanical properties and ultrasonic inspection efficiency of alpha-2 titanium aluminide forged products, parts or components and for preserving or retaining these improved properties at use temperatures up to about 1200.degree. F. The process involves heating a billet of the alloy below its beta transus temperature, forging the heated billet within a true strain range of about 1.2 and 1.4 and within a strain rate of about 0.1 and 0.15 per second to produce >90% refinement of prior .beta. grains to a typical size less than about 0.2 mm, preferably about 0.02 mm, and cooling the forged billet to room temperature.

Abstract: The present invention provides a high strength titanium alloy useful as a material for products such as ornaments, products such as ornaments made of the titanium alloy, and a method for producing the products using the titanium alloy as a material. The high strength titanium alloy is capable of attaining high machinability, and the product made of the titanium alloy is excellent in beauty and decorativeness while being hard to made flawed or concaved. According to the present invention, the titanium alloy includes iron of 0.20 to 0.8 mass percent and oxygen of 0.20 to 0.6 mass percent, or iron of 0.2 to 1.0 mass percent, oxygen of 0.15 to 0.6 mass percent and silicon of 0.20 to 1.0 mass percent, with the balance of titanium and inevitable impurities. A method for producing a product using the titanium alloy as a material includes a steps of hot forging the titanium alloy at a temperature of (.beta.-transformation temperature -200.degree. C.

Abstract: A method for forming titanium alloys is described comprising first forming an ingot that includes: (a) from about 5.5 to about 6.75 weight percent aluminum (preferably from about 5.75 to about 6.5 weight percent aluminum), (b) from about 3.5 to about 4.5 weight percent vanadium (preferably from about 3.75 to about 4.25 weight percent vanadium), (c) from about 0.2 to about 0.8 weight percent iron, (d) from about 0.02 to about 0.2 weight percent chromium, (e) from about 0.04 to 0.2 weight percent nickel, (f) from about 0.004 to about 0.1 weight percent cobalt, (g) from about 0.006 to 0.1 weight percent niobium, (h) from about 0 to about 0.20 weight percent carbon, (i) from about 0.22 to about 0.32 weight percent oxygen, (j) from about 0 to about 0.1 weight percent nitrogen, the balance being titanium and unavoidable impurities, each impurity totalling no more than about 0.2 weight percent, with the combined weight of the impurities totalling no more than about 0.5 weight percent.

Abstract: TiAl-besed intermetallic compound alloys contain chromium and consist essentially of a dual-phase microstructure of .gamma. and .beta. phases, with the .beta. phase precipitating at .gamma. grain boundaries. The .beta. phase precipitating at .gamma. grain boundaries is 2% to 25% by volume fraction. A process for preparing TiAl-based intermetallic compound alloys comprises the steps of preparing a molten TiAl-based intermetallic compound alloy of a desired composition, solidifying the molten alloy, homogenizing the solidified alloy by heat treatment, and thermomechanically working the homogenized alloy.

Abstract: Additions of a first alloy constituent of at least one element from the group consisting of Y, Sc, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu, or any combinations of them, and a second alloy constituent of at least one element from the group consisting of C, Si, Ge, Sn and Pb, or any combinations of them, to Ti-base alloys can be employed so as to result in an alloy containing an very fine, substantially homogeneous oxide dispersoid of the first constituent, and produce alloys having improved tensile properties, especially tensile elongation. The dispersoid results from the decomposition of an intermediate phase dispersoid comprising a compound of the first and second constituents which results from rapid solidification of the alloy from a melt. It is preferred that the second alloy constituent should be at a concentration sufficient to form the intermediate phase with all of the element or elements comprising the first alloy constituent.

Abstract: An alpha-beta titanium alloy preform is processed in the beta phase field, by heat treating or beta forging. The processed preform is thereafter heated into the alpha-beta phase field, and a preselected portion is forged, leaving a nonselected portion that is not forged in the alpha-beta phase field. The resulting article has a beta-processed structure in the nonselected portion, and a beta-processed plus alpha-beta forged structure in the preselected portion. In one application, the preform has the shape of a disk useful in the manufacture of an aircraft gas turbine engine. Depending upon specific requirements, either the center or the rim of the disk may be the selected portion.

Abstract: A process for manufacturing an aneurysm clip (10) having a coil spring (22), a first arm (26) ending in a first clamping jaw, and a second arm (34) ending in a second clamping jaw (40). The method includes: (a) providing a cylindrical starting rod (1) of titanium or titanium alloy; (b) cold drawing the rod to reduce its diameter and increase its strength; (c) cutting the rod to form a single resilient member (12); (d) winding the member about a mandrel to form the coil spring while incorporating the deflection of the arms into the clamping force of the clip; (e) shaping the member into two end sections (16) forming the clamping jaws and two connecting sections (18) forming connecting elements for the jaws; (f) coining the two end sections of the member a temperature between 900 and 1000 degrees F.; and (g) bending the clamping jaws into a position assuring that the clamping jaws are parallel when clamped onto tissue (70).

Abstract: Gamma titanium aluminide alloys having the composition Ti-(45.5-47.5)Al-(0-3.0)X-(1-5)Y-(0.05-1.0)W, where X is Cr, Mn or any combination thereof, and Y is Nb, Ta or any combination thereof (at %), are treated to provide specific microstructures. To obtain duplex microstructures, the annealing temperature (T.sub.a) range is the eutectoid temperature (T.sub.e)+100.degree. C. to the alpha transus temperature (T.sub..alpha.)-30.degree. C.; to obtain nearly lamellar microstructures, the annealing temperature range is T.sub..alpha. -20.degree. C. to T.sub..alpha. -1.degree. C.; to obtain fully lamellar microstructures, the annealing temperature range is T.sub..alpha. to T.sub..alpha. +50.degree. C. The times required for producing these microstructures range from 0.25 to 15 hours, depending on the desired microstructure, alloy composition, annealing temperature selected, material section size and grain size desired.

Abstract: A method for manufacturing an .alpha.+.beta. type titanium alloy plate having a small anisotropy in strength by subjecting an .alpha.+.beta. type titanium alloy slab to a hot-rolling, which comprises: the hot-rolling comprising a cross-rolling which comprises a hot-rolling in a L-direction and a hot-rolling in a C-direction, the L-direction being a final rolling direction in the hot-rolling and the C-direction being a direction at right angles to the L-direction; and controlling the cross-rolling so that a value of an overall cross ratio of rolling (CR.sub.total) determined by means of the following formula is kept within a range of from 0.5 to 2.0:CR.sub.total =(CR.sub.1).sup.0.6 .times.(CR.sub.2).sup.0.8 .times.(CR.sub.3).sup.1.0where, CR.sub.1 is a cross ratio of rolling within a rolling temperature region of from under T.beta. .degree.C. to T.beta. .degree.C.-50.degree. C., CR.sub.2 is a cross ratio of rolling within a rolling temperature region of from under T.beta. .degree.C.-50.degree. C. to T.beta. .

Abstract: The invention is a process for simultaneously improving at least two mechanical properties of mill-processed (.alpha.+.beta.) titanium alloy, which may or may not contain silicon, which includes steps of heat treating the mill-processed titanium alloy such that the (.alpha.+.beta.) microstructure of said alloy is transformed into an (.alpha.+.alpha..sub.2 +.beta.) microstructure, preferably containing no silicides. The heat treating steps involve subjecting the mill-processed titanium alloy to a sequence of thermomechanical process steps, and the mechanical properties which are simultaneously improved include (a) tensile strength at room, cryogenic, and elevated temperatures; (b) fracture toughness; (c) creep resistance; (d) elastic stiffness; (e) thermal stability; (f) hydrogen embrittlement resistance; (g) fatigue; and (h) cryogenic temperature embrittlement resistance. As a consequence of the process, the (.alpha.+.alpha..sub.2 +.beta.) microstructure contains equiaxed alpha phase strengthened with .alpha.

Abstract: A method for making an .alpha.+.beta. titanium alloy comprising: preparing an .alpha.+.beta. titanium alloy, hot-working the titanium alloy in an .alpha.+.beta. phase region, heating and then heat treating the hot-worked titanium alloy to a temperature from the .beta.-transus minus 55.degree. C. to the .beta.-transus minus 10.degree. C., air cooling the heat treated titanium alloy, heating and then heat treating the air cooled titanium alloy to a temperature from the .beta.-transus minus 250.degree. C. to the .beta.-transus minus 120.degree. C., and air cooling the heat treated titanium alloy.

Abstract: A titanium alloy possessing an equiaxial two-phase (.alpha.+.beta.) structure having an average grain size in the range of from 1 .mu.m to 10 .mu.m is obtained by a prescribed heat treatment of a titanium alloy material having a composition represented by the following formula 1,Ti.sub.100-a-b-c-d-e Al.sub.a V.sub.b Fe.sub.c Mo.sub.d O.sub.e(1)(wherein a, b, c, d, and e respectively satisfy the relations, 3.0.ltoreq.a.ltoreq.5.0, 2.1.ltoreq.b.ltoreq.3.7, 0.85.ltoreq.c.ltoreq.3.15, 0.85.ltoreq.d.ltoreq.3.15, and 0.06.ltoreq.e.ltoreq.0.20). The titanium alloy is formed in prescribed shape and size and finished with a mirror surface. It is produced by a method which comprises subjecting a titanium alloy material having a composition represented by the formula 1 to a solid solution treatment at a temperature in an .alpha.+.beta. range 25.degree. C.-100.degree. C. lower than the .beta.

Abstract: A method for producing fine-grained lamellar microstructures in powder metallurgy (P/M) and wrought gamma titanium aluminides comprises the steps of: (a) a cyclic heat treatment at a maximum temperature in the range of about 10.degree. C. above to about 10.degree. C. below the alpha-transus temperature (T.sub..alpha.) of the alloy, and (b) a secondary heat treatment of thus cyclically heat treated alloy at a temperature between 750.degree. C. and 1050.degree. C. for 4 to 100 hours. For cast gamma alloys, the method comprises additionally the step of a solution treatment at a temperature in the range of about 30.degree. C. to 70.degree. C. above T.sub..alpha. followed by a water or an oil quench before the two steps described above. The alloys with the resulting fine-grained lamellar microstructure have an advantageous combination of mechanical properties--tensile strength, ductility, fracture toughness, and creep resistance.

Abstract: A gamma titanium aluminide alloy article is produced from a piece of cast gamma titanium aluminide alloy by consolidating the gamma titanium aluminide alloy piece at a temperature above the eutectoid to reduce porosity therein, preferably by hot isostatic pressing. The piece is first heat treated at a temperature above the eutectoid for a time sufficient to form a structure of gamma grains plus lamellar colonies of alpha and gamma phases, and thereafter second heat treated at a temperature below the eutectoid to grow gamma grains within the colony structure, thereby reducing the effective grain size of the colony structure. There may follow an additional heat treatment just below the alpha transus to reform any remaining colony structure to produce a structure having isolated alpha-two laths within gamma grains.

Abstract: An as-cast gamma titanium-aluminide alloy, typically having a composition of from about 45.0 to about 48.5 atomic percent aluminum, is pre-HIP heat treated at a temperature of from about 1900.degree. F. to about 2100.degree. F. for a time of from about 50 to about 5 hours. The gamma titanium-aluminide alloy is thereafter hot isostatically pressed at a temperature of about 2200.degree. F. Hot isostatic pressing is preferably followed by a further heat treatment at a temperature of about 1850.degree.-2200.degree. F.

Abstract: Gamma titanium aluminide alloys having the composition Ti--(45.5-47.5)Al--(0-3.0)X--(1-5)Y--(0.05-1.0)W, where X is Cr, Mn or any combination thereof, and Y is Nb, Ta or any combination thereof (at %), are treated to provide specific microstructures. To obtain duplex microstructures, the annealing temperature (T.sub.a) range is the eutectoid temperature (T.sub.e)+100.degree. C. to the alpha transus temperature (T.sub..alpha.)-30.degree. C.; to obtain nearly lamellar microstructures, the annealing temperature range is T.sub..alpha. -20.degree. C. to T.sub..alpha. -1.degree. C.; to obtain fully lamellar microstructures, the annealing temperature range is T.sub..alpha. to T.sub..alpha. +50.degree. C. The times required for producing these microstructures range from 0.25 to 15 hours, depending on the desired microstructure, alloy composition, annealing temperature selected, material section size and grain size desired.

Abstract: A semi-finished product is taken made of a metastable beta titanium alloy containing oxygen in the range 0.4% to 0.7% by weight, and nitrogen in the range 0.1% to 0.2% by weight (oxygen+nitrogen.ltoreq.0.8%). The product is subjected to solution treatment at a temperature in the range 800.degree. C. to 900.degree. C. It is then cooled very quickly (.gtoreq.200.degree. C. per hour), the part is machined, ageing treatment is applied at a temperature in the range 550.degree. C. to 650.degree. C. for in the range 10 minutes to 2 hours so as to transform half of the beta titanium into alpha prime titanium. The titanium alloy part contains 40% to 60% of beta alloy, the remainder being alpha prime alloy. The part has good mechanical properties, good breaking strength, and a good elastic limit.

Abstract: A method for making titanium alloy products comprises the steps of:superplastic-forming .alpha.+.beta.-titanium alloy at a predetermined temperature, said .alpha.+.beta.-titanium alloy consisting essentially of 3.45 to 5 wt. % Al, 2.1 to 5 wt. % V, 0.85 to 2.85 wt. % Mo, 0.85 to 3.15 wt. % Fe, 0.01 to 0.25 wt. % 0 and the balance being titanium;cooling the superplastically formed titanium alloy at a cooling rate of 0.05 to 5.degree. C./sec; andaging the cooled titanium alloy at a temperature of 400.degree. to 600.degree. C.The superplastically formed titanium alloy can be diffusion-bonded, thereafter the diffusion-bonded titanium alloy can be cooled and aged.

Abstract: A method of manufacturing golf club is to design the contour of a club head and a club shaft. Sheet metal forming for divided golf club head are formed by stretching the Titanium Alloy plate within the forming dies, then processed with stress relief. Assembly welding are processed in a vacuum chamber where inner-gas, argon, is filled therein to avoid any inpurity may occur on the product during manufacture. Temperatures for stress relief, solid solution and aging are controlled in various degree depending upon each different procedures in order to form a best quality in vacuum furnace where vacuum gauge is best under ten to the negative fourth power of TORR.

Abstract: Gamma titanium aluminide alloy articles having improved properties are produced by the following methods:The first of these methods comprises the steps of: (a) heat treating an alloy billet or preform at a temperature in the approximate range of T.sub..alpha. to T.sub..alpha. +100.degree. C. for about 0.5 to 8 hours, (b) shaping the billet at a temperature between T.sub..alpha. -30.degree. C. and T.sub..alpha. to produce a shaped article, and (c) aging the thus-shaped article at a temperature between about 750.degree. and 1050.degree. C. for about 2 to 24 hours.The second method comprises (a) rapidly preheating an alloy preform to a temperature in the approximate range of T.sub..alpha. to T.sub..alpha. +100.degree. C., (b) shaping the billet at a temperature between T.sub..alpha. and T.sub..alpha. +100.degree. C. to produce a shaped article, and (c) aging the thus-shaped article at a temperature between about 750.degree. and 1050.degree. C. for about 2 to 24 hours.

Abstract: A method of making a titanium base alloy comprising the steps of heating a titanium base alloy to a temperature ranging from .beta.-transus minus 250.degree. C. to .beta.-transus; and hot working the heated alloy with a reduction ratio of at least 50%. The titanium base alloy consists essentially of about 3.42 to 5 wt. % Al, 2.1 to 3.7 wt. % V, 0.85 to 2.37 wt. % Mo, at least 0.01 wt. % O, at least one element selected from the group consisting of Fe, Co, Cr, and the balance being titanium. The invention also includes superplastic forming of said alloys. The titanium alloy satisfies the following equations:0.85 wt. %.ltoreq.X wt. %.ltoreq.3.15 wt. %,7 wt. %.ltoreq.Y wt. %.ltoreq.13 wt. %,X wt. %=Fe wt. %+Co wt. %+0.9 Cr wt. %Y wt. %=2.times.Fe wt. %+2.times.Co wt. %+1.8.times.Cr wt. %+1.5.times.V wt. %+Mo wt. %.

Abstract: An alpha/beta titanium alloy having improved fatigue crack growth resistance can be prepared through a thermomechanical process using a three-step thermal treatment. The first step includes a heat up and hold at a temperature above the beta transition temperature, while the second step is a stabilization treatment which includes a heat up and hold below the beta transition temperature, in the alpha/beta range. The third thermal treatment is an aging treatment. The invention is particularly useful in preparing forged parts for aircraft.

Abstract: Novel Ti-Al-Nb-Cr alloys incorporating in their microstructure the hexagonal DO.sub.19 phase, the omega-type B8.sub.2 phase, the cubic B2 phase, and, optionally, the orthorhombic O phase. The intermetallic alloys consist essentially of, in atomic percent, about 48-62% Ti, about 28-32% Al, and about 10-20% Nb with Cr, wherein Cr is preferably present at about 4-16% of the total concentration.

Abstract: TiAl-besed intermetallic compound alloys contain chromium and consist essentially of a dual-phase microstructure of .gamma. and .beta. phases, with the .beta. phase precipitating at .gamma. grain boundaries. The .beta. phase precipitating at .gamma. grain boundaries is 2% to 25% by volume fraction. A process for preparing TiAl-based intermetallic compound alloys comprises the steps of preparing a molten TiAl-based intermetallic compound alloy of a desired composition, solidifying the molten alloy, homogenizing the solidified alloy by heat treatment, and thermomechanically working the homogenized alloy.

Abstract: A Ti--Al--V--Cr intermetallic alloy having an atomic percent composition of 5-35 Al, 10-15 (V+Cr), the balance being Ti. The alloy is partially of DO.sub.19 type and partially of B2 type and has high temperature strength and excellent room temperature ductility. The alloy is produced by arc melting the metallic components Ti, Al and at least one of V and Cr; followed by homogenizing the melted components; solidifying the melted components to form an alloy; hot working the solidified alloy by isothermal forming to form a beta-phase polycrystalline microstructure; transforming the metastable .beta.-phase into a two-phase microstructure; and equilibrating the two-phase microstructure by prolonged annealing.

Abstract: The invention relates to a process for improving the aging response and uniformity in a beta titanium alloy comprising the steps of:(a) cold working said beta titanium alloy to at least about 5% so that a reasonable degree of recrystallization can be obtained during subsequent solution treatment;(b) pre-aging said cold worked alloy at about 900.degree. to about 1300.degree. F. for a time in excess of about 5 minutes to obtain a pre-aged alloy;(c) solution treating said pre-aged alloy at a time and temperature to achieve a reasonable degree of recrystallization of said pre-aged alloy above the beta transus; and(d) aging said solution treated alloy at temperature and times to achieve a pre-aged, solution treated and aged beta titanium alloy substantially in a state of metallurgical equilibrium.

Abstract: This invention relates to TiAl based intermetallic compound alloy and process for producing; the object of this invention is to improve high temperature deformability. The alloy comprises basic components: Ti.sub.y AlCr.sub.x, wherein 1%.ltoreq.X.ltoreq.5%, 47.5%.ltoreq.Y.ltoreq.52%, and X+2Y.gtoreq.100%, and comprises a fine-grain structure with a .beta. phase precipitated on a grain boundary of equiaxed .gamma. grain having grain size of less than 30 .mu.m, and possessing a superplasticity such that the strain rate sensitivity factors (m value) is 0.40 or more and tensile elongation is 400% or more tested at 1200.degree. C. and a strain rate of 5.times.10.sup.-4 S.sup.-1.

Abstract: An alpha-beta titanium-base alloy having a good combination of strength and ductility with a relatively low cost composition. The composition, in percent by weight, is 5.5 to 6.5 aluminum, 1.5 to 2.2 iron, 0.07 to 0.13 silicon and balance titanium. The alloy may have oxygen restricted in an amount up to 0.25%. The alloy may be hot-worked solely at a temperature above the beta transus temperature of the alloy to result in low-cost processing with improved product yields. The hot-working may include forging, which may be conducted at a temperature of 25.degree. to 450.degree. F. above the beta transus temperature of the alloy. The hot-working may also include hot-rolling, which also may be conducted at a temperature of 25.degree. to 450.degree. F. above the beta transus temperature of the alloy.

Abstract: A method of manufacturing corrosion resistant tubing from seam welded stock of a titanium or titanium alloy metallic material having a hexagonal close-packed crystal structure. The method includes cold pilgering a seam welded tube hollow having a weld area along the seam in a single pass to a final sized tube. The cold pilgering effects a reduction in cross sectional area of the tube hollow of at least 50% and a reduction of wall thickness of at least 50% thereby orienting the crystals in a radial direction. The method also includes annealing the final sized tubing at a temperature and for a time sufficient to effect complete recrystallization and reform grains in the weld area into smaller, homogeneous radially oriented grains. After the recrystallization annealing step, the tubing exhibits enhanced corrosion resistance which is similar to seamless tubing.

Abstract: A method for hot forging coarse grain materials to enhance hot workability and to refine microstructure is described which comprises the steps of imposing minimum initial deformation at low strain rate to effect initial dynamic recrystallization and grain refinement without fracture, and thereafter increasing the deformation rate to recrystallize the material and further refine grain structure. Depending on the deformation required to achieve full recrystallization at a given rate, deformation rate can be increased a number of times to further refine grain structure.

Abstract: Methods are presented to produce duplex (DP) microstructures, nearly lamellar (NL) microstructures, and fully TMT lamellar (TMTL) microstructures in gamma titanium aluminide alloy articles. The key step for obtaining a specific type of microstructure is the post-hot work annealing treatment at a temperature in a specific range for the desired microstructure. The annealing temperatures range from Te+100° C. to T&agr;−25° C. for duplex (DP) microstructures, from T&agr;−25° C. to T&agr;−5° C. for nearly lamellar (NL) microstructures, and from T&agr; to T&agr;+60° C. for fully TMT lamellar (TMTL) microstructures, where Te is the titanium-aluminum eutectoid temperature of the alloy and T&agr; is the alpha transus temperature of the alloy. The times required for producing specific microstructures range from 2 min to 15 hours depending on microstructural type, alloy composition, annealing temperature selected, material section size, and desired grain-size.

Abstract: A heat treatment method for producing moderate .alpha. grain size (50-250 .mu.m) fully lamellar, microstructures in thin cross section near-.gamma. titanium aluminide alloy products is described, wherein a wrought, fine y grain starting microstructure is heated at a temperature high in the two-phase .alpha.+.gamma. phase field and 30-60.degree. C. below the .alpha. transus temperature to produce a structure of small equiaxed .alpha. grains (about 25 .mu.m dim) and fine .gamma. phase grains, which is then briefly heated to a temperature in the single-phase .alpha. field in order to complete dissolution of remnant .gamma. grains and to minimize growth of .alpha. grains. The material is then cooled to transform the microstructure to fully lamellar .alpha..sub.2 +.gamma..