Abstract: 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 ?-phase titanium and a solid solution of niobium with ?-phase titanium, the ?-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.

Abstract: The present disclosure relates to a titanium or titanium alloy member and to a surface hardening method for the titanium or titanium alloy member. The titanium or titanium alloy member includes a base material of titanium or titanium alloy, and at a surface of the base material, a hardened layer formed by diffusion of oxygen into the surface. The method includes: a heating step of heating the titanium or titanium alloy base material of the member to a predetermined temperature under an inert gas atmosphere; a hardening step of introducing (i) a mixed gas including an inert gas, and (ii) oxygen gas as a hardening treatment gas, to perform hardening treatment of the surface of the base material; and a cooling step of cooling the base material down to room temperature under the inert gas atmosphere.

Abstract: A TiAl alloy member for hot forging includes a substrate made of TiAl alloy, and an Al layer formed on a surface of the substrate, the Al layer containing Al as a main constituent and containing Ti.

Abstract: A method for manufacturing an ?+? Ti-6Al-4V alloy includes providing a near-net shape part made of an ?+? Ti-6Al-4V alloy, The part is heat treated in the ?+? field between 875 and 920° C. The heat treated part is water quenched to transform the ? phase into ?? martensite. There is no further heat treatment after the quenching step.

Abstract: 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.

Abstract: The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200° C. and is maintained for 6 to 10 hours and then the component is cooled.

Abstract: Disclosed herein is a shape memory alloy comprising 48 to 50 atomic percent nickel, 15 to 30 atomic percent hathium, 1 to 5 atomic percent aluminum; with the remainder being titanium. Disclosed herein too is a method of manufacturing a shape memory alloy comprising mixing together to form an alloy nickel, hafnium, aluminum and titanium in amounts of 48 to 50 atomic percent nickel, 15 to 30 atomic percent hafnium, 1 to 5 atomic percent aluminum; with the remainder being titanium; solution treating the alloy at a temperature of 700 to 1300° C. for 50 to 200 hours; and aging the alloy at a temperature of 400 to 800° C. for a time period of 50 to 200 hours to form a shape memory alloy.

Abstract: Components include a low pressure turbine having a plurality of rotor assemblies including a first gamma TiAl intermetallic blade having a maximum operating temperature over 1180° F. (638° C.). At least two of the rotor assemblies include gamma TiAl intermetallic alloy blades. In an embodiment, a method of making a turbine having a plurality of rotor assemblies includes attaching a first gamma TiAl intermetallic alloy blade to an upstream stage of the plurality of rotor assemblies.

Abstract: The present invention provides a ?-type titanium alloy that includes, 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: A method and a product made through it by utilizing Zirconium alloys containing Titanium in the manufacture of metal articles of sports, night stealth compatible articles for law enforcement and military equipment, night-stealth personal and body adornments for members of such forces, garden and household implements, fashion accessories, body art articles, and medical and dental implants, and other articles. The articles benefit from any combination of properties from being hypo-allergenic, possessing high tensile strength, abrasion resistance, and hardness, having low ductility and elasticity and of having the outer appearance within the scale of dark grey to blackness. In this method an alloy of components in their respective ratios from within the method's stipulated preferred range is shaped into a workpiece by conventional metal forming devices and methods, and then subjected to an oxidation process and optional quenching steps.

Abstract: Systems and methods for hydrogen out gas of a porous metal scaffold are disclosed. A method can comprise heating a porous metal scaffold for a period of time sufficient to remove at least a portion of a hydrogen concentration from the scaffold, subjecting the porous metal scaffold to a vacuum while heating it, flowing an inert gas through or around the porous metal scaffold while heating it, and enhancing a mechanical property of the porous metal scaffold. Heating of the porous metal scaffold can include maintaining a temperature of the scaffold between 1035° C. and 1065° C., inclusive. A system can comprise a reaction chamber, a heater, a gas feed, and a vacuum apparatus. The heater can be configured to heat the reaction chamber and the porous metal scaffold, while the gas feed and the vacuum apparatus respectively flow inert gas and subject the porous metal scaffold to a vacuum.

Abstract: Substantially defect-free titanium aluminide components and methods are provided for manufacturing the same from articles formed by consolidation processes. The method includes providing an intermediate article comprised of a titanium aluminide alloy and formed by a consolidation process. The intermediate article is encapsulated with an aluminum-containing encapsulation layer. The intermediate article is compacted after the encapsulation step. A substantially defect-free titanium aluminide component comprises a compacted three-dimensional article comprised of titanium aluminide and formed by a consolidation process and an aluminum-containing encapsulation layer on at least one surface of the compacted three-dimensional article. The aluminum-containing encapsulation layer comprises an aluminide material, MCrAlY wherein M is cobalt, nickel, or a combination of cobalt and nickel, or TiAlCr.

Abstract: A titanium based, ceramic reinforced alloy ingot for use in producing medical implants. An ingot is formed from an alloy having comprising from about 5 to about 35 wt. % niobium, from about 0.5 to about 3.5 wt. % silicon, and from about 61.5 to about 94.5 wt. % of titanium. The alloy has a hexagonal crystal lattice ? phase of from about 20 vol % to about 70 vol %, and a cubic body centered ? crystal lattice phase of from about 30 vol. % to about 80 vol. %. The ingot has an ultimate tensile strength of about 940 MPa or more, and a Young's modulus of about 150 GPa or less. A molten substantially uniform admixture of a niobium, silicon, and titanium alloy is formed, cast into a shape, and cooled into an ingot. The ingot may then be formed into a medical implant and optionally annealed.

Abstract: A golf club head with an improved striking face is disclosed herein. More specifically, the present invention utilizes an innovative die quenching method that can alter the Young's modulus of the material of the striking face. The striking face portion of the present invention generally created from an ?+? titanium alloy such as SP 700 that contains a ? rich alloy composition to create more phase change in the alloying elements. In a preferred embodiment, the die quenching process could create a localized change in the material's Young's modulus throughout different regions of the striking face, resulting in a change in the Young's modulus of the material within the same striking face.

Abstract: In a method for beam welding on components with a laser beam or electron beam generated by a beam source, the heat treatment of the welded component required to remove stresses is integrated into the welding process. In a work cycle combined with the welding process, a regulated heat supply to a selected region takes place, according to its residual heat resulting from the welding process and the predicted stresses in that region, using the residual heat remaining from the welding process following the welding process from the same or other beam source(s). The welding region is cooled in a controlled manner, so that welded components which are likely to be subject to high stress in use, provided for example for a aircraft engine, can be made available without inherent stresses and with the desired microstructure in a single—combined—work 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: Disclosed is a method of producing an object, the object being made of metal or an alloy, having a desired shape and being non-porous, the method comprising: providing some metal or alloy having a first average solute level; using the provided metal or alloy, performing a net-shape or near-net shape manufacturing process to produce an intermediate object, the intermediate object having the desired shape, being non-porous, and having a second average solute level, the second average solute level being greater than or equal to the first average solute level; and performing a solute level changing process on the intermediate object to change the solute level of at least the bulk of the intermediate object such as to provide the intermediate object with a third average solute level, thereby providing the object, the third average solute level being different to the second.

Abstract: A method for preparing 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, and 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. The alloy is heated to a temperature T below the (?+?/?)-transition temperature T? and then quenched. The alloy is then aged a temperature of from 400 to 600° C.

Abstract: A cathodic member for electrochemical cells used in hypochlorite production comprises a zirconium plate coated with a zirconium oxide layer, which is particularly suitable for minimising the decomposition of the hypochlorite product while ensuring a prolonged lifetime. The coated zirconium plate can be used as the cathodic plate in a monopolar cell, or can be welded to a titanium plate for use in a bipolar configuration.

Abstract: A method of forming an article from an ?-? titanium including, in weight percentages, from about 2.9 to about 5.0 aluminum, from about 2.0 to about 3.0 vanadium, from about 0.4 to about 2.0 iron, from about 0.2 to about 0.3 oxygen, from about 0.005 to about 0.3 carbon, from about 0.001 to about 0.02 nitrogen, and less than about 0.5 of other elements. The method comprises cold working the ?-? titanium alloy.

Abstract: A method of forming an article from an ??? titanium including, in weight percentages, from about 2.9 to about 5.0 aluminum, from about 2.0 to about 3.0 vanadium, from about 0.4 to about 2.0 iron, from about 0.2 to about 0.3 oxygen, from about 0.005 to about 0.3 carbon, from about 0.001 to about 0.02 nitrogen, and less than about 0.5 of other elements. The method comprises cold working the ??? titanium alloy.

Abstract: The present invention is aimed at providing a method for producing a vacuum-insulated double container that exhibits a remarkable and heretofore unobtainable operating effect. The invention provides a method for producing a vacuum-insulated double container by placing a titanium internal cylinder (2) into a titanium external cylinder (1) via a space section (S), and using the space section (S) between the external cylinder (1) and the internal cylinder (2) as a vacuum-insulating space section, the method comprising the steps of degassing the space section (S) of a workpiece (3) that includes the external cylinder (1) and the internal cylinder (2), and vacuum sealing a degassing hole while the workpiece (3) is heated in a vacuum heating furnace (6); and then providing concavoconvex portions (4, 5) to a surface of the recrystallized external cylinder (1) and the internal cylinder (2) by placing the workpiece (3) in an atmospheric-pressure environment.

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: An alloy having from about 5 to about 15 wt % Ta, from 0 to about 5 wt % Nb, from about 0.5 to about 15 wt % Zr, and the balance Ti is disclosed. The alloy is particularly intended for medical devices, such as implants for the body.

Abstract: A titanium-molybdenum alloy having ?? phase as a major phase is subjected to an aging treatment, so that yield strength of the aged alloy is increased by 10% to 120% with elongation to failure thereof being not less than about 5.0%.

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: Shape Memory Alloy tube is protected from damage during drawing, caused by galling-type interaction between the tube and high-carbon dies, by forming an oxide surface layer. This invention protects the tube internal diameter from oxidation while allowing the tube outside diameter to be oxidized, by using an oxygen getter located within the tube during the oxidation step. The method yields a higher quality internal diameter and improves productivity.

Abstract: A description is given of a method for the heat treatment of a workpiece produced from a titanium alloy for obtaining a fine-grained microstructure by annealing the same above its ?-transus temperature T?. According to the invention, the workpiece is heated in a furnace to a temperature level TH above its ?-transus temperature T?. Reaching the temperature level TH determines the beginning of a predefined holding time, for which the workpiece is kept at this temperature level TH. The workpiece subsequently undergoes a cooling process. To carry out the heat treatment, the furnace temperature TF is set such that, for heating up the workpiece to the temperature level intended for carrying out the holding, it lies above the temperature level TH of the workpiece determining the beginning of the holding time.

Abstract: The invention relates to a process for the preparation of a part made of titanium alloy, comprising a thermal treatment for relaxing the internal stresses of the part, the thermal treatment comprising maintaining at a temperature “T1” greater than the beta transus (beta transition) temperature, referred to as “Tbt”, and the part being free to deform by creeping. The invention also relates to a tool for carrying out this process.

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: A method of improving the properties of a component of a medical device entails constraining the component, which comprises about 45-55 at. % Ni, about 45-55 at. % Ti, and about 0.3 at. % Cr, into a predetermined configuration. The component also includes at least about 35% cold work. The component is heated during the constraining at a temperature of between about 425° C. and about 500° C. for a time duration of between about 5 minutes and about 30 minutes, thereby improving the superelastic and mechanical properties of the component. A medical device includes a superelastic component for use in a body vessel that comprises about 45-55 at. % Ni, about 45-55 at. % Ti, and about 0.3 at. % Cr, where the component has an upper plateau strength of at least about 75 ksi, a residual elongation of about 0.1% or less, and an austenite finish temperature (Af) of about 30° C. or less.

Abstract: The present disclosure describes methods of heat treating Ti-based alloys and various improvements that can be realized using such heat treatments. In one exemplary implementation, the invention provides a method of forming a metal member that involves forming an alloy into a utile shape and cooling the alloy from a first temperature above a beta transus temperature of the alloy to a second temperature below the beta transus temperature at a cooling rate of no more than about 30° F./minute. If so desired, the alloy my be treated for a period of about 1-12 hours at about 700-1100° F. Titanium alloys treated according to aspects of the invention may have higher tensile strengths and higher fracture toughness than conventional wrought, mill-annealed Ti 64 alloy.

Abstract: Method, and articles therefrom, for providing a hard, abrasion-resistant, attractive, oxide surface layer of selectable thickness and having an outer appearance within the scale from gray to blackness, to a zirconium titanium alloy article by heating the article in an oxygen containing atmosphere.

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: The disclosure provides bearing sleeves or bushings made of memory shape material, and processes for installing such bearing sleeves or bushings. In one process, inner and outer surfaces of a bearing sleeve, made of a memory shape material, may be compressed at least one first temperature. A bearing may be inserted in a cavity of the bearing sleeve, and the bearing sleeve may be disposed adjacent to a surface of a structure, while the bearing sleeve is at the at least one first temperature. The inner and outer surfaces of the bearing sleeve may be expanded, at least one second temperature, to abut against the bearing and the surface of the structure.

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 for refining the microstructure of titanium alloys in a single thermomechanical processing step, wherein the titanium alloy comprises boron. In some embodiments, the method comprises the steps of first adding boron to the titanium alloy then subjecting the boron-containing titanium alloy to a thermomechanical processing step. Also provided is a method for achieving superplasticity in titanium alloys comprising the steps of selecting a boron-containing titanium alloy, determining the temperature and strain rate necessary to achieve beta superplasticity, and applying sufficient temperature and strain rate to the boron-containing titanium alloy to deform the alloy to the desired shape. Also provided methods of forming titanium alloy parts and the parts prepared by these methods.

Abstract: A titanium alloy having at least 4% by weight aluminum and at least 0.1% by weight oxygen, the alloy also including at least one element selected from vanadium, molybdenum, chromium, and iron. The titanium alloy also includes hafnium in a proportion by weight of at least 0.1%.

Abstract: A titanium alloy having high strength, fine grain size, and low cost and a method of manufacturing the same is disclosed. In particular, the inventive alloy offers a strength increase of about 100 MPa over Ti 6-4, with a comparable density and near equivalent ductility. The inventive alloy is particularly useful for a multitude of applications including components of aircraft engines. The Ti alloy comprises, in weight percent, about 6.0 to about 6.7% aluminum, about 1.4 to about 2.0% vanadium, about 1.4 to about 2.0% molybdenum, about 0.20 to about 0.42% silicon, about 0.17 to about 0.23% oxygen, maximum about 0.24% iron, maximum about 0.08% carbon and balance titanium with incidental impurities.

Abstract: A description is given of a method for the heat treatment of a workpiece produced from a titanium alloy for obtaining a fine-grained microstructure by annealing the same above its ?-transus temperature T?. According to the invention, the workpiece is heated in a furnace to a temperature level TH above its ?-transus temperature T?. Reaching the temperature level TH determines the beginning of a predefined holding time, for which the workpiece is kept at this temperature level TH. The workpiece subsequently undergoes a cooling process. To carry out the heat treatment, the furnace temperature TF is set such that, for heating up the workpiece to the temperature level intended for carrying out the holding, it lies above the temperature level TH of the workpiece determining the beginning of the holding time.

Abstract: Endodontic instruments for use in performing root canal therapy on a tooth are disclosed. In one form, the instruments include an elongate shank having a cutting edge extending from a distal end of the shank along an axial length of the shank. The shank comprises a titanium alloy, and the shank is prepared by heat-treating the shank at a temperature above 25° C. in an atmosphere consisting essentially of a gas unreactive with the shank. In another form, the endodontic instruments have an elongate shank having a cutting edge extending from a distal end of the shank along an axial length of the shank. The shank consists essentially of a titanium alloy selected from alpha-titanium alloys, beta-titanium alloys, and alpha-beta-titanium alloys. The instruments solve the problems encountered when cleaning and enlarging a curved root canal.

Abstract: A production of precision castings by centrifugal casting, includes the following steps: a) providing in a crucible (8) a melt of the following composition: Ti45-52 at. %Al45-50 at. %Xl1-3 at. %X22-4 at. %X30-1 at. %/ where Xl =Cr, Mn, V, X2=Nb, Ta, W, Mo, X3=Si, B, C; b) forcing the melt by means of centrifugal forces from the crucible (8) into a mold (4); c) solidifying the melt within the mold thereby creating a casting consisting of a titanium alloy having a lamellar microstructure; and d) reheating the casting for a duration of 60 to 150 hours at a temperature higher than the eutectic temperature and lower than the alpha-transus temperature of the composition.

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 forming an article from an ??? titanium including, in weight percentages, from about 2.9 to about 5.0 aluminum, from about 2.0 to about 3.0 vanadium, from about 0.4 to about 2.0 iron, from about 0.2 to about 0.3 oxygen, from about 0.005 to about 0.3 carbon, from about 0.001 to about 0.02 nitrogen, and less than about 0.5 of other elements. The method comprises cold working the ??? titanium alloy.

Abstract: Article (e.g., turbine engine fan or compressor blade) comprising a titanium alloy has a first portion with alpha+beta microstructure and a second portion with martensitic or a bimodal microstructure. The modified microstructure of the second portion is provided by selectively heating, and immediately quenching, the second portion without substantially heating the first portion. An exemplary method includes providing a near net-shaped article having a first portion (e.g., an airfoil region) and a second portion (e.g., an unfinished dovetail region). Initially, the article comprises an alpha+beta microstructure throughout. Thereafter, the second portion is selectively heated, followed by immediate quenching, without substantially heating the first portion, to modify the microstructure of the second portion to a martensitic or bimodal microstructure without substantially modifying the microstructure of the first portion. Thereafter, the second portion may be processed to a final body dimension.

Abstract: Endodontic instruments for use in performing root canal therapy on a tooth are disclosed. In one form, the instruments include an elongate shank having a cutting edge extending from a distal end of the shank along an axial length of the shank. The shank comprises a titanium alloy, and the shank is prepared by heat-treating the shank at a temperature above 25° C. in an atmosphere consisting essentially of a gas unreactive with the shank. In another form, the endodontic instruments have an elongate shank having a cutting edge extending from a distal end of the shank along an axial length of the shank. The shank consists essentially of a titanium alloy selected from alpha-titanium alloys, beta-titanium alloys, and alpha-beta-titanium alloys. The instruments solve the problems encountered when cleaning and enlarging a curved root canal.

Abstract: A titanium alloy subjected to thermal treatment followed by quenching. The thermal treatment raises the temperature of the alloy to a temperature above the alloy's recrystallization temperature and below the alloy's beta-transus temperature to cause a phase shift within the alloy. After the thermal treatment has been applied for a predetermined time, the alloy is rapidly quenched, preserving the phase shift induced by the thermal treatment. By the present method, the microstructure of the titanium alloy is changed from a fine grained alpha-beta phase to a microstructure substantially comprised of an equiaxed alpha phase and an acicular or plate-like alpha phase. The resulting prostheses may have a microstructure including between 25% and 75% percent acicular alpha phase, for example.

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: To provide a method of producing a strengthened alloy capable of shortening the time necessary for aging treatment and obtaining a strengthened alloy with enhanced tensile strength. The method of producing a strengthened alloy comprises a solution treatment step S1 of immersing an alloy material into molten lithium held at a solution treatment temperature higher than solution temperature of solute metal of the alloy material, a solution stop step S2 of immersing the alloy material into molten lithium held at a cooling temperature lower than the solution treatment temperature after the solution treatment step S1, an aging treatment step S3 of immersing the alloy material into molten lithium held at an aging treatment temperature lower than the solution temperature after the solution stop step S2, and an aging stop step S4 of immersing the alloy material into molten lithium held at an aging stop temperature lower than the aging treatment temperature after the aging treatment step S3.