Abstract: A method for making a metallic leading edge guard of the type having a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.

Abstract: A method for increasing tensile strength of a cold workable alpha-beta titanium alloy comprises solution heat treating a cold workable alpha-beta titanium alloy in a temperature range of T?-106° C. to T?-72.2° C. for 15 minutes to 2 hours; cooling the alpha-beta titanium alloy at a cooling rate of at least 3000° C./minute; cold working the alpha-beta titanium alloy to impart an effective strain in the range of 5 percent to 35 percent in the alloy; and aging the alpha-beta titanium alloy in a temperature range of T?-669° C. to T?-517° C. for 1 to 8 hours. Fastener stock and fasteners including solution treated, quenched, cold worked, and aged alpha-beta titanium alloys are also disclosed.

Abstract: Certain embodiments of a method for increasing the strength and toughness of a titanium alloy include plastically deforming a titanium alloy at a temperature in an alpha-beta phase field of the titanium alloy to an equivalent plastic deformation of at least a 25% reduction in area. After plastically deforming the titanium alloy in the alpha-beta phase field, the titanium alloy is not heated to or above the beta transus temperature of the titanium alloy. After plastic deformation, the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beta transus temperature minus 20° F. (11.1° C.).

Abstract: A screen includes a framework of a first material having one or more openings therethrough defining a fluidic filter, and a substance of a second material positioned within the one or more openings in the framework and configured to be removable from the framework during an electrochemical reaction.

Abstract: The present invention provides a ?-type titanium alloy keeping the content of the relatively expensive ?-stabilizing elements such as V or Mo down to a total of 10 mass % or less and reducing the effects of composition segregation of Fe and Cr and thereby able to keep the Young's modulus and density relatively low. The ?-type titanium alloy of the present invention comprises, by mass %, when Al: 2 to 5%, 1) Fe: 2 to 4%, Cr: 6.2 to 11%, and V: 4 to 10%, 2) Fe: 2 to 4%, Cr: 5 to 11%, and Mo: 4 to 10%, or 3) Fe: 2 to 4%, Cr: 5.5 to 11%, and Mo+V (total of Mo and V): 4 to 10% in range, and a balance of substantially Ti. These include Zr added in amounts of 1 to 4 mass %. Furthermore, by making the oxygen equivalent Q 0.15 to 0.30 or leaving the alloy in the work hardened state or by applying both, the tensile strength before aging heat treatment can be further increased.

Abstract: Processes for forming an article from an ?+? titanium alloy are disclosed. The ?+? titanium alloy includes, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, and from 0.10 to 0.30 oxygen. The ?+? titanium alloy is cold worked at a temperature in the range of ambient temperature to 500° F., and then aged at a temperature in the range of 700° F. to 1200° F.

Abstract: Techniques are disclosed related to cables that may be used within a medical device. According to one example, a cable may comprise multiple wires. Each wire may be formed of a biocompatible beta titanium alloy having an elastic modulus ranging from 30 GigaPascals (GPa) to 90 GPa and comprising at least two elements selected from a group of titanium, molybdenum, niobium, tantalum, zirconium, chromium, iron and tin. The cable may be heated to a stress-relieve temperature of the beta titanium alloy to allow the cable to retain a desired configuration while remaining ductile. The cable may be included within a medical device, such as a medical electrical lead.

Abstract: According to an embodiment, two or more sets of knead forging are performed where one set is cold forging processes in directions parallel to and perpendicular to a thickness direction of a columnar titanium material. The titanium material is heated to a temperature of 700° C. or more to induce recrystallization, and thereafter, two or more sets of knead forging are performed where one set is the cold forging processes in the directions parallel to and perpendicular to the thickness direction. Further, the titanium material is cold rolled, and is heat-treated to a temperature of 300° C. or more.

Abstract: Processes for forming an article from an ?+? titanium alloy are disclosed. The ?+? titanium alloy includes, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, and from 0.10 to 0.30 oxygen. The ?+? titanium alloy is cold worked at a temperature in the range of ambient temperature to 500° F., and then aged at a temperature in the range of 700° F. to 1200° F.

Abstract: A timepiece part, such as a balance staff, an oscillating weight or a dial, is made of polycrystalline material having a plurality of crystals each having a size of 0.7 ?m or more and 3 mm or less. The crystals at a surface of the timepiece part have mirror-finished surfaces, and the surfaces may be anodized to provide corrosion resistance. The normal directions of the mirror-finished surfaces are different from one another and provide a metallic luster to the timepiece part.

Abstract: Disclosed is a TiAl alloy for high-temperature applications which comprises not more than 43 at. % of Al, from 3 at. % to 8 at. % of Nb, from 0.2 at. % to 3 at. % of Mo and/or Mn, from 0.05 at. % to 0.5 at. % of B, from 0.1 at. % to 0.5 at. % of C, from 0.1 at. % to 0.5 at. % of Si and Ti as balance. Also disclosed is a process for producing a component made of this TiAl alloy and the use of corresponding TiAl alloys in components of flow machines at operating temperatures up to 850° C.

Abstract: Titanium alloy that is formed by subjecting titanium alloy to a treatment containing a hydrogen storing step for making the titanium alloy store hydrogen therein, a solution-treatment step for heating the titanium alloy having the hydrogen stored therein in the hydrogen storage step to apply a solution treatment to the hydrogen-stored titanium alloy, a cooling step for cooling the heated hydrogen-stored titanium alloy to develop martensitic transformation in the hydrogen-stored titanium alloy, a hot rolling step for heating the martensitic-transformed titanium alloy to a temperature which is not more than a predetermined transformation point and hot-rolling the martensitic-transformed titanium, and a dehydrogenation step for dehydrogenating the hot-rolled titanium alloy, thereby bringing the titanium alloy with the superplastic property.

Abstract: A process for manufacturing a turbine engine component comprises the steps of: casting ingots made of a gamma TiAl material using a double vacuum arc remelting casting technique; subjecting the cast ingots to a hot isostatic pressing to close porosity; forming at least one pancake of the gamma TiAl material by isothermally forging the hot isostatic pressed ingots; sectioning each pancake into a plurality of blanks; heat treating the blanks to produce a desired microstructure and mechanical properties; and machining the blanks into finished turbine engine components. A system for performing the process is also disclosed.

Abstract: According to a thermomechanical treatment process for a titanium alloy including between 23 and 27% niobium in atomic proportion, between 0 and 10% zirconium, and between 0 and 1% oxygen, nitrogen and/or silicon, the following steps are performed: a) an increase of a sample of the alloy to a temperature higher than 900° C., b) a fast quench, c) a severe cold strain, d) an ageing treatment at a temperature included between 200 and 600° C., the time of the ageing treatment being included between 10 seconds and 10 minutes. Alloy obtained by this process and prostheses made from such an alloy.

Abstract: A process for making parts from titanium or a titanium alloy is disclosed. The process includes the step of preparing an intermediate form of titanium or a titanium alloy. The intermediate form is then solution heat treated under conditions of temperature and time that are selected to produce a desired level of strength when the titanium or titanium alloy part is subsequently age hardened. The solution treated intermediate form is then thermomechanically formed into a desired part or a preform for a desired part. The as-formed part or preform is then age-hardened under conditions of temperature and time that are selected to produce the desired level of strength in the finished part. The age-hardening step is performed without solution heat treating the as-formed part or preform again.

Abstract: Method for producing a forging from a gamma titanium aluminum-based alloy. The method includes heating at least a portion of a cylindrical or rod-shaped starting or raw material to a temperature of more than 1150° C. over a cross section of the at least a portion. The at least a portion corresponds to points at which the forging to be shaped has volume concentrations. The method also includes deforming the at least a portion through an applied force to form a biscuit having different cross sectional areas over a longitudinal extension of the biscuit, and finishing the forging through a second heating to a deformation temperature and at least one subsequent step.

Abstract: The invention is directed to a method for producing a titanium aluminide intermetallic alloy composition having an improved wear resistance, the method comprising heating a titanium aluminide intermetallic alloy material in an oxygen-containing environment at a temperature and for a time sufficient to produce a top oxide layer and underlying oxygen-diffused layer, followed by removal of the top oxide layer such that the oxygen-diffused layer is exposed. The invention is also directed to the resulting oxygen-diffused titanium aluminide intermetallic alloy, as well as mechanical components or devices containing the improved alloy composition.

Abstract: A titanium alloy that is created to be formed into a bearing component, wherein the titanium alloy comprises from 5 to 7 wt % Al, from 3.5 to 4.5 wt % V, from 0.5 to 1.5 wt % Mo, from 2.5 to 4.5 wt % Fe, from 2.5 to 4.5 wt % Fe, from 0.05 to 2 wt % Cr. The alloy can optionally include one or more of the following elements: up to 2.5 wt % Zr, up to 2.5 wt % Sn, and up to 0.5 wt % C. The balance of the composition comprises Ti together with unavoidable impurities.

Abstract: Metastable beta titanium alloys and methods of processing metastable (?-titanium alloys are disclosed. For example, certain non-limiting embodiments relate to metastable (?-titanium alloys, such as binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, having tensile strengths of at least 150 ksi and elongations of at least 12 percent. Other non-limiting embodiments relate to methods of processing metastable ?-titanium alloys, and more specifically, methods of processing binary (?-titanium alloys comprising greater than 10 weight percent molybdenum, wherein the method comprises hot working and aging the metastable ?-titanium alloy at a temperature below the (?-transus temperature of the metastable (?-titanium alloy for a time sufficient to form ?-phase precipitates in the metastable ?-titanium alloy. The metastable ?-titanium alloys are not solution heat treated after hot working and prior to aging.

Abstract: A task of the present invention is to provide a Ti—Mo alloy material which can be improved in the yield stress at room temperature by the precipitation of an aged omega phase in the Ti—Mo alloy while maintaining large ductility at room temperature, and a method for producing the same. Provided is a Ti—Mo alloy collectively having an Mo content of 10 to 20 mass %, wherein the Ti—Mo alloy has a winding belt-like or swirly segregation portion having a width of 10 to 20 ?m in the plane of a backscattered electron image (BEI) or an energy dispersive X-ray spectroscopy (EDS) image of the Ti—Mo alloy, as examined under a scanning electron microscope, in which Mo content is larger than the collective Mo content of the Ti—Mo alloy. When generally observing the entire plane examined, a segregation structure in a swirly form can be observed. Further, provided is the Ti—Mo alloy which has been subjected to aging treatment so that an aged omega phase is precipitated along the segregation portion.

Abstract: Metastable beta titanium alloys and methods of processing metastable ?-titanium alloys are disclosed. For example, certain non-limiting embodiments relate to metastable ?-titanium alloys, such as binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, having tensile strengths of at least 150 ksi and elongations of at least 12 percent. Other non-limiting embodiments relate to methods of processing metastable ?-titanium alloys, and more specifically, methods of processing binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, wherein the method comprises hot working and direct aging the metastable ?-titanium alloy at a temperature below the ?-transus temperature of the metastable ?-titanium alloy for a time sufficient to form ?-phase precipitates in the metastable ?-titanium alloy. Articles of manufacture comprising binary ?-titanium alloys according to various non-limiting embodiments disclosed herein are also disclosed.

Abstract: A titanium material for a solid polymer fuel cell separator having a low contact resistance and a method of production of the same, the titanium material having at its surface a surface layer structure in which particles of a Ti compound containing either C or N are dispersed, the particles of Ti compound being covered by titanium oxide and/or metal Ti, characterized in that, when analyzed from the surface by XPS, a Ti2p spectrum of TiO2 is detected, further, at a Ti2p spectral energy range of TiO and/or a Ti2p spectral energy range of metal Ti, a Ti maximum detection peak height is at least 3 times the standard deviations of the background at the respective spectral energy ranges, and at a C1s spectral energy range and N1s spectral energy range, a maximum detection peak height is less than 3 times the standard deviations of the background at the respective spectral energy ranges of C1s and N1s, are provided.

Abstract: Metastable beta titanium alloys and methods of processing metastable ?-titanium alloys are disclosed. For example, certain non-limiting embodiments relate to metastable ?-titanium alloys, such as binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, having tensile strengths of at least 150 ksi and elongations of at least 12 percent. Other non-limiting embodiments relate to methods of processing metastable ?-titanium alloys, and more specifically, methods of processing binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, wherein the method comprises hot working and direct aging the metastable ?-titanium alloy at a temperature below the ?-transus temperature of the metastable ?-titanium alloy for a time sufficient to form ?-phase precipitates in the metastable ?-titanium alloy. Articles of manufacture comprising binary ?-titanium alloys according to various non-limiting embodiments disclosed herein are also disclosed.

Abstract: The invention relates to a monolithic titanium alloy (M) comprising, in a temperature range (?T) and at atmospheric pressure: an outer peripheral zone consisting of a micro-structure (m1) having a modulus of elasticity (E1) and possessing superelastic properties in said range (?T), and a core consisting of a microstructure (m2) having a modulus of elasticity (E2), and possessing elastic properties in said range (?T); said microstructures (m1) and (m2) being different from one another, and said modulus of elasticity (E1) being lower than said modulus of elasticity (E2).

Abstract: A spinal fixation titanium alloy rod fixes a plurality of spinal-fixing screws embedded and fixed in vertebrae of a human body. The rod is cylindrically shaped, has a sufficient length for coupling with the spinal-fixing screws, and has a diameter adjusted to 4 to 7 mm. In the titanium alloy constituting the rod, Nb content is 25 to 35 percent by weight, Ta content is such that the Nb content +0.8×Ta content ranges from 36 to 45 percent by weight, Zr content is 3 to 6 percent by weight, and the remainder is Ti and unavoidable impurities, excluding vanadium. The titanium alloy is manufactured by swaging processing at a cross-sectional reduction rate of at least 90%, and aging the swaged titanium alloy by heating at a temperature of 600 to 800K, preferably 700 to 800K, for 43.2 ks to 604.8 ks.

Abstract: A method is provided for improving the machinability of a titanium alloy includes heating the alloy at a temperature and time period that imparts to the alloy a microstructure having between about 10 and 15 vol. % alpha phase in a beta phase matrix. According to one embodiment, the alloy is thereafter annealed at a temperature lower than the temperature for the initial heating step, and for a duration that is longer than the time period for the initial heating step.

Abstract: A method of producing a seamless, tubular product includes centrifugally casting a corrosion resistant alloy into a tubular workpiece having an inner diameter and an outer diameter. The method then removes material from the inner diameter of the workpiece and subjects the workpiece to at least about a 25% wall reduction at a temperature below a recrystallization temperature of the workpiece using a metal forming process. The metal forming process includes radial forging, rolling, pilgering, and/or flowforming.

Abstract: A process for making an article of a titanium alloy having ?? phase as a major phase according to the present invention includes providing a work piece of a titanium alloy consisting essentially of 7-9 wt % of molybdenum and the balance titanium and having ?? phase as a major phase; and cold working at least a portion of the work piece at room temperature to obtain a green body of the article, wherein the cold worked portion of the green body has a thickness which is 20%-80% of that of the at least a portion of the work piece, and the cold worked portion has ?? phase as a major phase.

Abstract: A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided.

Abstract: A method of making a high strength, high stiffness beta titanium alloy, comprising introducing boron into a beta titanium alloy to produce TiB precipitates; heat treating the titanium alloy with TiB precipitates by homogenization above the beta transus temperature of the alloy; subjecting the heat treated alloy to a hot metalworking operation below the beta transus temperature; heat treating the worked alloy with a solution treatment below the beta transus temperature; and ageing the solution treated alloy below the beta transus temperature.

Abstract: A metallic material is made from at least one refractory metal or an alloy based on at least one refractory metal. The metallic material has an oxygen content of about 1,000 to about 30,000 ?g/g and the oxygen is interstitial.

Abstract: Surface processing of titanium alloy members for aerospace equipment imparts high wear resistance, lubricity and high fatigue strength. The method includes an oxygen diffusion step for causing oxygen to diffuse and penetrate in solid solution form into a surface of a titanium alloy member under an oxygen-containing gas atmosphere and a particle bombardment step for bombarding the surface of the titanium alloy member with an airflow containing particles. The aerospace equipment can include a flap rail member and slat rail member for aircraft.

Abstract: A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided.

Abstract: An article of manufacture selected from a titanium alloy fastener and a titanium alloy fastener stock including an alpha/beta titanium alloy comprising, in percent by weight: 3.9 to 5.4 aluminum; 2.2 to 3.0 vanadium; 1.2 to 1.8 iron; 0.24 to 0.3 oxygen; up to 0.08 carbon; up to 0.05 nitrogen; titanium; and up to a total of 0.3 of other elements. In certain embodiments, article of manufacture has an ultimate tensile strength of at least 170 ksi (1,172 MPa) and a double shear strength of at least 103 ksi (710.2 MPa). A method of manufacturing a titanium alloy fastener and a titanium alloy fastener stock comprising the alpha/beta alloy is disclosed.

Abstract: An article of manufacture selected from a titanium alloy fastener and a titanium alloy fastener stock including an alpha/beta titanium alloy comprising, in percent by weight: 3.9 to 4.5 aluminum; 2.2 to 3.0 vanadium; 1.2 to 1.8 iron; 0.24 to 0.3 oxygen; up to 0.08 carbon; up to 0.05 nitrogen; titanium; and up to a total of 0.3 of other elements. In certain embodiments, article of manufacture has an ultimate tensile strength of at least 170 ksi (1,172 MPa) and a double shear strength of at least 103 ksi (710.2 MPa). A method of manufacturing a titanium alloy fastener and a titanium alloy fastener stock comprising the alpha/beta alloy is disclosed.

Abstract: Processes for forming an article from an ?+? titanium alloy are disclosed. The ?+? titanium alloy includes, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, and from 0.10 to 0.30 oxygen. The ?+? titanium alloy is cold worked at a temperature in the range of ambient temperature to 500° F., and then aged at a temperature in the range of 700° F. to 1200° F.

Abstract: A method (40) of improving the mechanical properties of a component, for example a gas turbine engine turbine disc, (24) comprises isothermally forging (42) a preform to produce a shaped preform with a predetermined shape at a first predetermined temperature, solution heat treating (44) the shaped preform, quenching (46) the shaped preform, forging (48) the shaped preform at a second predetermined temperature to impart a predetermined residual strain in the shaped preform, ageing (50) the shaped preform and finally machining (52) the shaped preform to a finished shape. The second predetermined temperature is less than the first predetermined temperature.

Abstract: A hafnium alloy target containing either or both of Zr and Ti in a gross amount of 100 wtppm-10 wt % in Hf, wherein the average crystal grain size is 1-100 ?m, the impurities of Fe, Cr and Ni are respectively 1 wtppm or less, and the habit plane ratio of the plane {002} and three planes {103}, {014} and {015} lying within 35° from {002} is 55% or greater, and the variation in the total sum of the intensity ratios of these four planes depending on locations is 20% or less. As a result, obtained is a hafnium alloy target having favorable deposition property and deposition speed, which generates few particles, and which is suitable for forming a high dielectric gate insulation film such as HfO or HfON film, and the manufacturing method thereof.

Abstract: A method of producing a high strength, high stiffness and high ductility titanium alloy, comprising combining the titanium alloy with boron so that the boron concentration in the boron-modified titanium alloy does not exceed the eutectic limit. The carbon concentration of the boron-modified titanium alloy is maintained below a predetermined limit to avoid embrittlement. The boron-modified alloy is heated to a temperature above the beta transus temperature to eliminate any supersaturated excess boron. The boron-modified titanium alloy is deformed at a speed slow enough to prevent microstructural damage and reduced ductility.

Abstract: A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided.

Abstract: Metastable beta titanium alloys and methods of processing metastable ?-titanium alloys are disclosed. For example, certain non-limiting embodiments relate to metastable ?-titanium alloys, such as binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, having tensile strengths of at least 150 ksi and elongations of at least 12 percent. Other non-limiting embodiments relate to methods of processing metastable ?-titanium alloys, and more specifically, methods of processing binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, wherein the method comprises hot working and direct aging the metastable ?-titanium alloy at a temperature below the ?-transus temperature of the metastable ?-titanium alloy for a time sufficient to form ?-phase precipitates in the metastable ?-titanium alloy. Articles of manufacture comprising binary ?-titanium alloys according to various non-limiting embodiments disclosed herein are also disclosed.

Abstract: Metastable beta titanium alloys and methods of processing metastable ?-titanium alloys are disclosed. For example, certain non-limiting embodiments relate to metastable ?-titanium alloys, such as binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, having tensile strengths of at least 150 ksi and elongations of at least 12 percent. Other non-limiting embodiments relate to methods of processing metastable ?-titanium alloys, and more specifically, methods of processing binary ?-titanium alloys comprising greater than 10 weight percent molybdenum, wherein the method comprises hot working and direct aging the metastable ?-titanium alloy at a temperature below the ?-transus temperature of the metastable ?-titanium alloy for a time sufficient to form ?-phase precipitates in the metastable ?-titanium alloy. Articles of manufacture comprising binary ?-titanium alloys according to various non-limiting embodiments disclosed herein are also disclosed.

Abstract: Methods for the manufacture of the above-mentioned titanium alloy for use in combustion engine exhaust systems are disclosed herein. An exemplary method of the disclosed subject matter for the manufacture of titanium alloy for use in a high temperature and high stress environment includes performing a first heat treatment of the titanium alloy at a first temperature, rolling the titanium alloy to a desired thickness, performing a second heat treatment of the titanium alloy at a second temperature, and performing a third heat treatment of the titanium alloy at a third temperature. In some embodiments, the first temperature is selected such that recrystallization and softening of the titanium alloy is optimized without substantial coarsening of second phase particles and can be approximately 1500-1600° F. In some embodiments, the rolling of the titanium alloy reduces the thickness of the titanium alloy by at least than 65%.

Abstract: Disclosed are: a structural member for use in an eyeglass which has a super elastic property and shape memory property while retaining an excellent biocompatibility in addition to the fact that it is N-free, and which also has an excellent cold workability; an eyeglass frame comprising the structural member; and a process for producing the structural member or eyeglass frame. A structural member for an eyeglass comprising a Ti—Nb—Zr alloy which comprises (A) 40 to 75% by weight of Ti, (B) 18 to 30% by weight of Nb, (C) 10 to 30% by weight of Zr and (D) 0.2 to 3.7% by weight of at least one additive metal element selected from the group consisting of Al, In and Ga.

Abstract: A method for refurbishing service-degraded gas turbine component can recover the microstructure of the alloy of the gas turbine component, whose material is deteriorated or damaged after its operation, to the extent that is equivalent or more than the characteristic at the time of its manufacture. The method comprises performing a recovery heat treatment, performing a solution heat treatment, and performing an aging heat treatment. The recovery heat treatment heat-treats the component under a predetermined pressure, which is higher than normal pressure, wherein the temperature of the component is increased to a predetermined temperature under the predetermined pressure. The solution heat treatment is processed under reduced pressure or inert gas atmosphere after the recovery heat treatment. The aging heat treatment is processed under reduced pressure or inert gas atmosphere after the recovery heat treatment.

Abstract: A TiAl based alloy having excellent strength as well as an improvement in toughness at room temperature, in particular an improvement in impact properties at room temperature, and a production method thereof, and a blade using the same are provided. This TiAl based alloy has a microstructure in which lamellar grains having a mean grain diameter of from 1 to 50 ?m are closely arranged. The alloy composition is Ti-(42-48)Al-(5-10)(Cr and/or V) or Ti-(38-43)Al-(4-10)Mn. The alloy can be obtained by subjecting the alloy to high-speed plastic working in the cooling process, after the alloy has been held in an equilibrium temperature range of the ? phase or the (?+?) phase.

Abstract: Various non-limiting embodiments of the present invention relate to methods of processing titanium alloys wherein the alloys are subjected to deformation above the beta transus temperature (T?) of the alloys. For example, one non-limiting embodiment provides a method of processing an alpha+beta or a near-beta titanium alloy comprising deforming a body of the alloy at a first temperature (T1) that is above the T? of the alloy; recrystallizing at least a portion of the alloy by deforming and/or holding the body at a second temperature (T2) that is greater than T1; and deforming the body at a third temperature (T3), wherein T1?T3>T?; wherein essentially no deformation of the body occurs at a temperature below T? during the method of processing the titanium alloy.

Abstract: A titanium alloy part has a compressive stress of approximately 270 MPa or more within a depth of about 100 ?m from a surface thereof. Since a large compressive stress exists in the area of the surface, the titanium alloy part exhibits a high fatigue strength.

Abstract: Methods for improving mechanical properties of beta processed, alpha-beta titanium alloy articles involving forging the alloy article above the beta transus to produce a post final forged article, subjecting the post final forged article to a post-forged cooling process to produce a post-forged cooled article, solution heat treating the post-forged cooled article to a temperature below the beta transus to produce a solution heat treated article, subjecting the solution heat-treated article to a controlled post-solution cooling process to produce a post-solution cooled article, and alpha phase precipitation treating the post-solution cooled article to obtain a final article having an average elongation value of at least about 3%.

Abstract: A Ti-6Al-4V-0.2O (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2¼ inches. The forged article is heat treated by solution heat treating at a temperature of from about 50° F. to about 85° F. below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900° F. to about 1350° F.