巴西专利BR112013001367B1 PROCESS TO FORM A TITANIUM ALLOY ARTICLE a + ß

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专利摘要:
processing of titanium alpha / beta alloys. processes for forming an article of a <244> + <225> titanium alloy are disclosed. <244> + <225> titanium alloy includes, by weight, 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 <244> + <225> titanium alloy is cold worked at a temperature in the ambient temperature range of 500 <198> f and then aged in a temperature in the range of 700 <198> to 1200 <198> f.
公开号:BR112013001367B1
申请号:R112013001367-2
申请日:2011-06-27
公开日:2019-04-16
发明作者:David J.Bryan
申请人:Ati Properties Llc；
IPC主号:

专利说明:

[001] The present disclosure is directed to processes for producing high strength alpha / beta (α + β) titanium alloys and to products produced by the disclosed processes.
BACKGROUND [002] Titanium and titanium-based alloys are used in a variety of applications due to the relatively high strength, low density and good corrosion resistance of these materials. For example, titanium and titanium-based alloys are used extensively in the aerospace industry due to the high strength to weight ratio of materials and corrosion resistance. A group of titanium alloys known to be widely used in a variety of applications are the alpha / beta (α + β) Ti-6Al-4V alloys comprising a nominal composition of 6 percent aluminum, 4 percent vanadium less than 0.20 percent oxygen and titanium, by weight.
[003] Ti-6Al-4V alloys are one of the most common titanium-based materials, estimated to account for 50% of the total titanium-based materials market. Ti-6Al-4V alloys are used in several applications that benefit from the combination of high strength alloys at low to moderate temperatures, light weight, and corrosion resistance. For example, Ti-6Al-4V alloys are used to produce aircraft engine components, aircraft structural components, fasteners, high-performance automotive components, components for medical devices, sports equipment, components for marine applications and components for chemical processing.
[004] Ti-6Al-4V alloy laminated products are generally used in a mill annealed condition or in a solution treated and aged condition (STA). Rolled Ti6AI-4V alloy products of relatively high strength
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2/31 lower can be supplied in a mill annealed condition. As used here, the "mill annealed condition" refers to the condition of a titanium alloy after a "mill annealing" heat treatment in which a workpiece is annealed at an elevated temperature (eg 1200-1500 ° F / 649816 ° C) for approximately 1-8 hours and cooled in still air. A heat treatment of annealing in a plant is carried out after a workpiece has been heat-worked in the α + β phase field. Ti-6Al-4V alloys in a mill annealed condition have a minimum specified ultimate tensile strength of 130 ksi (896 MPa) and a minimum specified strain resistance of 120 ksi (827 MPa) at room temperature. See, for example, Aerospace Material Specifications (AMS) 4928 and 6931A, which are incorporated by reference here.
[005] To increase the resistance of Ti-6Al-4V alloys, the materials are generally subjected to a STA heat treatment. STA heat treatments are generally performed after a workpiece is heat-worked in the α + β phase field. STA refers to heat treatment of a workpiece at an elevated temperature below the temperature of β-transus (for example, 17251775 ° F / 940-968 ° C) for a relatively short time (for example, approximately 1 hour) and then quickly cool the workpiece abruptly with water or an equivalent medium. The sharply cooled workpiece is aged at a high temperature (eg 900-1200 ° F / 482649 ° C) for approximately 4-8 hours and cooled in still air. Ti-6Al-4V alloys in a STA condition have a minimum specified ultimate tensile strength of 150-165 ksi (1034-1138 MPa) and a minimum specified strain resistance of 140-155 ksi (965-1069 MPa), in room temperature, depending on diameter or thickness dimension of the article processed by STA. See, for example, AMS 4965 and AMS 6930A, which is incorporated by reference here.
[006] However, there are several limitations to using heat treatments from
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3/31
STA to obtain high strength in Ti-6Al-4V alloys. for example, the material's inherent physical properties and the requirement for rapid rapid cooling during STA processing limit the sizes and dimensions of articles that can achieve high strength, and may exhibit relatively large thermal stresses, internal stresses, warping and dimensional distortion. This disclosure is directed to methods for processing certain α + β titanium alloys to provide mechanical properties that are comparable or superior to the properties of Ti-6Al-4V alloys in an STA condition, but which do not suffer from STA processing limitations.
SUMMARY [007] The modalities disclosed here are directed to processes for forming an article of a titanium alloy α + β. The processes comprise cold working of the α + β titanium alloy at a temperature in the ambient temperature range at 500 ° F (260 ° C) and after the cold working stage, aging of the α + β titanium alloy at a temperature in the 700 ° F to 1200 ° F (371-649 ° C) range. the titanium alloy α + β comprises, in weight percentages, from 2.90% to 5.00% aluminum, from 2.00% to 3.00% vanadium, from 0.40% to 2.00% iron, 0.10% to 0.30% oxygen, incidental impurities and titanium.
[008] It is understood that the invention disclosed and described here is not limited to the modalities disclosed in this Summary.
BRIEF DESCRIPTION OF THE DRAWINGS [009] The characteristics of several non-limiting modalities disclosed and described here can be better understood by reference to the attached figures, in which:
[010] Figure 1 is a graph of average final tensile strength and average deformation strength versus cold work quantified as percentage reductions in area (% RA) for α + β titanium alloy bars cold drawn in a conPetition 870180138493, of 10/05/2018, p. 25/75
4/31 as stretched;
[011] Figure 2 is a graph of average ductility quantified as a percentage of tensile elongation for cold-drawn α + β titanium alloy bars in a stretched condition;
[012] Figure 3 is a graph of final tensile strength and deformation resistance versus elongation percentage for α + β titanium alloy bars after being cold worked and directly aged according to the process modalities revealed here;
[013] Figure 4 is a graph of average final tensile strength and average deformation resistance versus average elongation for α + β titanium alloy bars after being cold worked and directly aged according to the process modalities revealed here;
[014] Figure 5 is a graph of average final tensile strength and average deformation resistance versus aging temperatures for α + β titanium alloy bars cold worked up to 20% reduction in area and aged for 1 hour or 8 hours in temperature;
[015] Figure 6 is a graph of average final tensile strength and average deformation resistance versus aging temperature for α + β titanium alloy bars cold worked up to 30% reduction in area and aged for 1 hour or 8 hours in temperature;
[016] Figure 7 is a graph of average final tensile strength and average deformation resistance versus aging temperature for cold worked α + β titanium alloy bars up to 40% reduction in area and aged for 1 hour or 8 hours in temperature;
[017] Figure 8 is a graph of average elongation versus aging temperature for α + β titanium alloy bars cold worked at 20% reduction in area and aged for 1 hour or 8 hours in temperature;
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5/31 [018] Figure 9 is a graph of average elongation versus aging temperature for α + β titanium alloy bars cold worked at 30% reduction in area and aged for 1 hour or 8 hours in temperature;
[019] Figure 10 is a graph of average elongation versus aging temperature for titanium alloy bars α + β at 40% reductions in area and aged for 1 hour or 8 hours in temperature;
[020] Figure 11 is a graph of average final tensile strength and average yield strength versus aging time for α + β titanium alloy bars cold worked at 20% reductions in area and aged at 850 ° F ( 454 ° C) or 1100 ° F (593 ° C); and [021] Figure 12 is a graph of average elongation versus aging time for α + β titanium alloy bars cold worked at 20% reduction in area and aged at 850 ° F (454 ° C) or 1100 ° F (593 ° C).
[022] The reader will recognize the above details, as well as others, after considering the following detailed description of various non-limiting modalities in accordance with the present disclosure. The reader can also understand additional details after implementing or using the modalities described here.
DETAILED DESCRIPTION OF NON-LIMITING MODALITIES [023] It should be understood that the descriptions of the revealed modalities have been simplified to illustrate only those characteristics and aspects that are relevant to a clear understanding of the revealed modalities, while eliminating, for clarity purposes, other characteristics and aspects . People of ordinary skill in the art, after considering this description of the revealed modalities, will recognize that other aspects and characteristics may be desirable in a specific implementation or application of the revealed modalities. However, how such aspects and characteristics can be readily determined and implemented by people with common technical knowledge after considering this
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6/31 description of the revealed modalities, and are therefore not necessary for a complete understanding of the revealed modalities, a description of such aspects, characteristics and the like is not provided here. As such, it should be understood that the description set out here is merely exemplary and illustrative of the disclosed modalities and is not intended to limit the scope of the invention defined by the claims.
[024] In the present disclosure, which is not otherwise indicated, all numerical parameters must be understood as being prefaced and modified in all cases by the term "approximately", in which the numerical parameters have the characteristic of inherent variability in the techniques of underlying measurement used to determine the numerical value of the parameter. At a minimum and not as an attempt to limit the application of the doctrine of equivalents to the scope of the claims, each numerical parameter described in the present description should at least be interpreted in light of the number of significant digits reported and by applying common rounding techniques.
[025] In addition, any numeric range recited here is intended to include all sub-ranges included within the recited range. For example, a “1 to 10” range is intended to include all sub-ranges between (and including) the minimum recited value of 1 and the maximum recited value of 10, that is, having a minimum value equal to or greater than 1 and a maximum value equal to or less than 10. Any maximum numerical limitation recited here is intended to include all the lowest numerical limitations included therein and any minimum numerical limitation recited here is intended to include all high numerical limitations in the same. Accordingly, the Claimant reserves the right to change this disclosure, including the claims, to expressly recite any sub-band included within the ranges expressly recited here. All of these tracks are intended to be inherently disclosed here so that the change to expressly recite any such sub-tracks would be in compliance with the requirements of 35 U.S.C. § 112, firstPetition 870180138493, of 10/05/2018, p. 28/75
7/31 ro paragraph, and 35 U.S.C. § 132 (a).
[026] The grammatical articles "one", "one" and "o, a" as used here, are intended to include "at least one" or "one or more", unless otherwise indicated. Thus, articles are used here to refer to one or more of one (that is, “at least one”) of the article's grammatical objects. As an example, a “component” means one or more components, and therefore, possibly more than one component is considered and can be used or used in an implementation of the described modalities.
[027] Any patent, publication or other disclosure material that is said to be incorporated by reference here in its entirety unless otherwise indicated, but only to the extent that the incorporated material does not conflict with existing definitions , statements, or other disclosure material exposed in that disclosure. As such, and to the extent necessary, the disclosure expressed as outlined herein replaces any conflicting material incorporated herein by reference. Any material or portion thereof that is said to be incorporated by reference here, but which conflicts with existing definitions, statements or other disclosure material set forth herein, is only incorporated to the extent that no conflict arises between that material incorporated and the existing development material. The applicant reserves the right to change the present disclosure to expressly mention any matter, or portion thereof, incorporated by reference here.
[028] The present disclosure includes descriptions of various modalities. It should be understood that the various modalities described here are exemplary, illustrative and not limiting. Thus, the present disclosure is not limited by the description of the various exemplary, illustrative and non-limiting modalities. Instead, the invention is defined by the claims, which can be changed to mention some aspects or features expressly or inherently described in
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8/31 or otherwise expressly or inherently supported by the present disclosure. In addition, the applicant reserves the right to change the claims to affirmatively waive aspects or characteristics that may be present in the prior art. Therefore, any such changes would comply with the requirements of 35 U.S.C. § 112, first paragraph, and 35 U.S.C. § 132 (a). the various embodiments disclosed and described here may comprise, consist of, or consist essentially of aspects and characteristics as described in a variety of ways here.
[029] The various modalities disclosed here are directed to thermomechanical processes to form an article of an α + β titanium alloy having a different chemical composition than Ti-6Al-4V alloys. In various modalities, the titanium alloy α + β comprises in percentages by weight, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, from 0.20 to 0.30 of oxygen, incidental impurities and titanium. Such α + β titanium alloys (which are referred to here as “Kosaka alloys”) are described in the US NO patent. 5,980,655 DE Kosaka, which is incorporated by reference here. The nominal commercial composition of Kosaka alloys includes, in weight percentages, 4.00 aluminum, 2.50 vanadium, 1.50 iron, 0.25 oxygen, incidental impurities, and titanium, and can be mentioned as alloy Ti-4Al-2.5V-1.5Fe-0.25O.
[030] US patent no. 5,980,655 (the '655 patent') describes the use of α + β thermomechanical processing to form Kosaka alloy ingot plates. Kosaka alloys were developed as a lower cost alternative to Ti-6Al-4V alloys for ballistic shielding plate applications. The α + β thermomechanical processing described in the ‘655 patent includes:
(a) Form an ingot having a Kosaka alloy composition;
(b) Forging β the ingot at a temperature above the Btransus temperature of the alloy (for example, at a temperature above 1900 ° F (1038 ° C)) to form an intermediate plate;
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9/31 (c) Forging α + β the intermediate plate at a temperature below the β-transus temperature of the alloy, but in the α + β phase field, for example, at a temperature of 1500-1775 ° F (815- 968 ° C);
(d) Lamination α + β to plate to final plate thickness at a temperature below the β-transus temperature of the alloy, but in the α + β phase field, for example, at a temperature of 1500-1775 ° F ( 815-968 ° C); and (e) Annealing at a plant at a temperature of 1300-1500 ° F (704-815 ° C).
[031] The plates formed according to the processes disclosed in the '655 patent showed ballistic properties comparable or superior to Ti6Al-4V plates. however, the plates formed according to the processes disclosed in the ‘655 patent showed lower tensile strengths at room temperature than the high strengths obtained by Ti-6Al-4V alloys after STA processing.
[032] Ti-6Al-4V alloys in a STA condition can have a final tensile strength of approximately 160-177 ksi (1103-1220 MPa) and a deformation resistance of approximately 150-164 ksi (1034-1131 MPa) at room temperature. However, due to certain physical properties of Ti-6Al-4V, such as relatively low thermal conductivity, the final tensile strength and deformation resistance that can be obtained with Ti-6Al-4V alloys through processing depends on the size of the alloy article of Ti-6Al-4V being subjected to STA processing. In this respect, the relatively low thermal conductivity of Ti-6Al-4V alloys limits the diameter / thickness of articles that can be fully hardened / reinforced using STA processing because internal portions of thick section and large diameter alloy articles do not cool in a sufficient rate during sudden cooling to form the raw alpha phase (phase α '). Thus, the STA processing of Ti-6Al-4V alloys of thick section or large diameter produces an article having a case reinforced by precipitation surrounding a
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10/31 relatively weaker core without the same level of precipitation boost, which can significantly decrease the overall strength of the article. For example, the strength of Ti-6Al-4V alloy articles begins to decrease for articles having small dimensions (for example, diameters or thicknesses) greater than approximately 0.5 inch (1.27 cm), and processing and STA do not provides no benefit to Ti-6Al-4V alloy articles having small dimensions greater than approximately 3 inches (7.62 cm).
[033] The size dependence of the tensile strength of Ti-6Al-4V alloys in a STA condition is evident in decreasing strength minima corresponding to increasing article sizes for material specifications, such as AMS 6930A, in which the minima of Higher strength for Ti6Al-4V alloys in a STA condition corresponds to articles having a diameter or thickness less than 0.5 inch (1.27 cm). For example, AMS 6930A specifies a minimum final tensile strength of 165 ksi (1138 MPa) and a minimum deformation resistance of 155 ksi (1069 MPa) for Ti-6Al-4V alloy articles in a STA condition and having a diameter or thickness less than 0.5 inch (1.27 cm).
[034] In addition, STA processing can induce relatively large thermal and internal stresses and cause warping of titanium alloy articles during the sudden cooling step. Despite its limitations, STA processing is the standard method for obtaining high strength in Ti-6Al-4V alloys because Ti-6Al-4V alloys are not generally cold-deformable and therefore cannot be effectively cold-worked to increase strength . Without wishing to be limited by theory, the lack of cold deformability / work capacity is generally believed to be attributable to a phenomenon of sliding band formation in Ti-6Al-4V alloys.
[035] The alpha phase (α-phase) of Ti-6Al-4V alloys precipitates Ti3Al particles (alphaPetition 870180138493, from 05/10/2018, page 32/75
11/31 two). These alpha-two (a ₂ ) coherent precipitates increase the strength of the alloys, but as the coherent precipitates are sheared by mobile displacements during plastic deformation, the precipitates result in the formation of flat sliding bands, accentuated in the microstructure of the alloys. In addition, Ti-6Al-4V alloy crystals have been shown to form localized short-range areas of oxygen and aluminum atoms, that is, localized deviations from a homogeneous distribution of oxygen and aluminum atoms in the crystal structure. These localized areas of decreased entropy have been shown to promote the formation of accentuated flat sliding bands in the microstructure of Ti-6Al-4V alloys. the presence of these microstructural and thermodynamic aspects in Ti-6Al-4V alloys can cause the tangle of slip displacements or otherwise prevent the displacements from slipping during deformation. When this occurs, landslide is located in accentuated flat regions in the alloy mentioned as sliding bands. Sliding strips cause a loss of ductility, crack nucleation, and crack propagation, which leads to the failure of Ti-6Al-4V alloys during cold working.
[036] Consequently, Ti-6Al-4V alloys are generically worked (for example, forged, laminated, drawn and the like) at elevated temperatures, generally above the solvus temperature at ₂ ° C. Ti-6Al-4V alloys cannot be effectively cold worked to increase strength due to the high incidence of cracking (ie workpiece failure) during cold deformation. However, it has been unexpectedly discovered that Kosaka alloys have a substantial degree of cold deformability / workability, as described in US patent application publication 2004/0221929, which is incorporated by reference here.
[037] It has been determined that Kosaka alloys do not have a sliding band formation during cold working and, therefore, significantly show mePetition 870180138493, of 10/05/2018, p. 33/75
12/31 crack us during cold work than Ti-6Al-4V alloy. not wishing to be limited by theory, it is believed that the lack of sliding band formation in Kosaka alloys can be attributed to a minimization of aluminum and short-range oxygen. In addition, phase 02 stability is low in Kosaka alloys in relation to Ti-6Al-4V for example, as demonstrated by equilibrium models for a2 phase solvus temperature (1305 ^o F / 707 ° C for Ti -6Al-4V (max. 0.15% oxygen) and 1062 ° F / 572 ° C for Ti-4Al-2.5V-1.5Fe-0.25O, determined using Pandat software, CompuTherm LLC, Madison, Wisconsin, USA) . As a result, Kosaka alloys can be cold worked to obtain high strength and retain a workable level of ductility. In addition, it has been found that Kosaka alloys can be cold worked and aged to obtain increased strength and increased ductility compared to cold working alone. As such, Kosaka alloys can achieve strength and ductility comparable or superior to those of Ti-6Al-4V alloys in an STA condition, but without the need for, and STA processing limitations.
[038] In general, "cold working" refers to working an alloy at a temperature below that at which the material flow stress is significantly decreased. As used here with respect to the disclosed processes, “cold work”, “cold work”, “cold work” and similar terms, or “cold used in connection with a specific work technique or training, refer to work or the characteristics of having been working, as the case may be, at a temperature no higher than approximately 500 ° F (260 ° C). thus, for example, a drawing operation performed on a Kosaka alloy workpiece at a temperature in the ambient temperature range at 500 ° F (260 ° C) is considered here to be cold working. In addition, the terms “work”, “training” and “deformation” are generally used interchangeably here, as are the terms “work capacity”, “training capacity”, “deformation capacityPetition 870180138493, from 05 / 10/2018, p. 34/75
13/31 tion ”and similar terms. It will be understood that the meaning applied to "cold working", "cold working", "cold forming" and similar terms, with respect to this application does not intend and does not limit the meaning of those terms in other contexts or in relation to other inventions.
[039] In various modalities, the processes disclosed here may comprise cold working an α + β titanium alloy at a temperature in the ambient temperature range up to 500 ° F (260 ° C). After cold working operation, the α + β titanium alloy can be aged at a temperature in the range of 700 ° F to 1200 ° F (371-649 ° C).
[040] When a mechanical operation, such as a cold drawn pass, is described here as being conducted, performed or similar, at a specified temperature or within a specified temperature range, the mechanical operation is performed in a workpiece that is at the specified temperature or within the specified temperature range at the beginning of the mechanical operation. During the course of a mechanical operation, the temperature of a workpiece can vary from the initial temperature of the workpiece at the beginning of the mechanical operation. For example, the temperature of a workpiece may increase due to adiabatic heating or decrease due to conductive, convective and / or radioactive cooling during a work operation. The magnitude and direction of temperature variation from the initial temperature at the beginning of the mechanical operation can depend on several parameters, such as, for example, the level of work performed on the workpiece, the stress rate at which the work is performed, the initial temperature of the workpiece at the beginning of the mechanical operation, and the temperature of the surrounding environment.
[041] When a thermal operation such as an aging heat treatment is described here as being conducted at a specified temperature and for a specified period of time or within a specified temperature range 870180138493, from 10/05/2018, pg. 35/75
14/31 each and time range, the operation is carried out for the specified time while keeping the workpiece at temperature. The time periods described here for thermal operations such as aging heat treatments do not include heating and cooling times, which may depend, for example, on the size and shape of the workpiece.
[042] In various modalities, an α + β titanium alloy can be cold worked at a temperature in the ambient temperature range up to 500 ° F (260 ° C), or any sub-range in it, such as, for example, room temperature up to 450 ° F (232 ° C), room temperature up to 400 ° F (204 ° C), room temperature up to 350 ° F (177 ° C), room temperature up to 300 ° F (149 ° C), room temperature up to 250 ° F (121 ° C), room temperature up to 200 ° F (93 ° C), or room temperature up to 150 ° F (65 ° C). in various modalities, a titanium alloy α + β is cold worked at room temperature.
[043] In various embodiments, cold working of an α + β titanium alloy can be performed using forming techniques including, but not necessarily limited to, drawing, deep drawing, rolling, roll forming, forging, extrusion, reduction cold, oscillation, flow rotation, shear wiring, hydroforming, bulging formation, stamping, impact extrusion, explosive formation, rubber formation, back extrusion, drilling, spinning, stretch forming, pressure bending, electromagnetic forming, course, coinage, and combinations of any of them. In terms of the processes disclosed here, these forming techniques transmit cold work to an α + β titanium alloy when carried out at temperatures no higher than 500 ° F (260 ° C).
[044] In several modalities, a titanium alloy α + β can be cold worked at 20% to 60% reduction in area. For example, a α + β titanium alloy workpiece, such as an ingot, a billet, a bar, a rod, a tube, a plate, or a plate, can be plastically deformed, for example,
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15/31 in a cold drawing, cold rolling, cold extruding, or cold forging operation, so that a cross-sectional area of the workpiece is reduced by a percentage in the range of 20% to 60%. For cylindrical workpieces, such as round ingots, billets, bars, rods, and tubes, the reduction in area is measured for the circular or annular cross section of the workpiece, which is generally perpendicular to the direction of movement of the workpiece. workpiece through a stretch die, an extrusion die or similar. Similarly, the reduction in area of laminated workpieces is measured by the cross section of the workpiece which is generally perpendicular to the direction of movement of the workpiece through the rollers of a laminating apparatus or the like.
[045] In several modalities, a titanium alloy α + β can be cold worked to a reduction of 20% to 60% in area, or any sub-band in it, such as, for example, 30% to 60%, 40% to 60%, 50% to 60%, 20% to 50%, 20% to 40%, 20% to 30%, 30% to 50%, 30% to 40%, or 40% to 50%. An α + β titanium alloy can be cold worked to a 20% to 60% reduction in area with no observable edge crack or other surface crack. Cold work can be carried out without any intermediate stress relief annealing. In this way, various modalities of the processes disclosed here can achieve reductions in areas up to 60% without any annealing of intermediate stress relief between sequential cold work operations, such as, for example, two or more passes through a cold drawing apparatus.
[046] In several modalities, a cold working operation can comprise at least two deformation cycles, in which each deformation cycle comprises cold working an α + β titanium alloy with at least a 10% reduction in area. In various embodiments, a cold working operation can comprise at least two deformation cycles, with each deformation cycle
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16/31 includes cold working a titanium alloy α + β at least 20% reduction in area. At least two deformation cycles can achieve area reductions of up to 60% without any intermediate stress relief annealing.
[047] For example, in a cold drawing operation, a bar can be cold drawn in a first pass of drawing at room temperature to a reduction greater than 20% in area. The cold drawn bar greater than 20% can then be cold drawn in a second drawing pass at room temperature to a second reduction in area greater than 20%. The two cold-drawn passes can be carried out without any intermediate strain relief annealing between the two passes. In this way, an α + β titanium alloy can be cold worked using at least two deformation cycles to obtain larger overall reductions in area. In a given implementation of a cold work operation, the forces required for cold deformation of an α + β titanium alloy will depend on parameters including, for example, the size and shape of the workpiece, the resistance to deformation of the material alloy, the extent of deformation (eg reduction in area), and the specific cold working technique.
[048] In several modalities, after a cold working operation, a cold worked α + β titanium alloy can be aged at a temperature in the range of 700 ° F to 1200 ° F (371-649 ° C), or any sub-band in it, such as, for example, 800 ° F to 1150 ° F, 850 ° F to 1150 ° F, 800 ° F to 1100 ° F, or 850 ° F to 1100 ° F (i.e., 427- 621 ° C, 454-621 ° C, 427-593 ° C, or 454-593 ° C). heat treatment of aging can be carried out for a temperature and for a time sufficient to provide a specified combination of mechanical properties, such as, for example, a specified final tensile strength, a specified creep resistance, and / or a specified elongation . In various modalities, an aging heat treatment can be carried out for up to 50 hours in temperatuPetição 870180138493, of 05/10/2018, pg. 38/75
17/31 ra, for example. In various modalities, an aging heat treatment can be carried out for 0.5 to 10 hours in temperature, or any sub-band in it, such as, for example, 1 to 8 hours in temperature. Heat treatment of aging can be carried out in a temperature-controlled oven, such as an open air gas oven.
[049] In various modalities, the processes disclosed here may also comprise a hot work operation carried out before the cold work operation. A hot work operation can be carried out in the α + β phase field. For example, a hot work operation can be performed at a temperature in the range of 300 ° F to 25 ° F (167-15 ° C) below the βtransus temperature of the α + β titanium alloy. Generally, Kosaka alloys have a β-transus temperature of approximately 1765 ° F to 1800 ° F (963-982 ° C). In various modalities, a titanium alloy α + β can be hot worked at a temperature in the range of 1500 ° F to 1775 ° F (815-968 ° C), or any sub-fixed in it, such as, for example, 1600 ° F to 1775 ° F, 1600 ° F to 1750 ° F, or 1600 ° F to 1700 ° F (i.e., 871-968 ° C, 871-954 ° C, or 871-927 ° C).
[050] In embodiments comprising a hot work operation prior to the cold work operation, the processes disclosed here may further comprise an optional strain relief or annealing heat treatment between the heat work operation and the work operation cold. An α + β titanium alloy can be annealed at a temperature in the range of 1200 ° F to 1500 ° F (649815 ° C), or any sub-band in it, such as, for example, 1200 ° F to 1400 ° F or 1250 ° F to 1300 ° F (i.e., 649-760 ° C or 677-704 ° C).
[051] In various modalities, the processes disclosed here may comprise an optional hot work operation carried out in the β-phase field before a hot work operation carried out in the α + β phase field. For example, a titanium alloy ingot can be hot work in the phase field. Petition 870180138493, 10/05/2018, pg. 39/75
18/31 β to form an intermediate article. The intermediate article can be hot worked in the α + β phase field to develop an α + β phase microstructure. After hot work, the intermediate article can be annealed in strain relief and then cold worked at a temperature in the ambient temperature range at 500 ° F (260 ° C). the cold-worked article can be aged at a temperature in the range of 700 ° F to 1200 ° F (371-649 ° C). Optional hot work in the β phase field is performed at a temperature above the β-transus temperature of the alloy, for example, at a temperature in the range 1800 ° F to 2300 ° F (982-1260 ° C), or any sub-band therein, such as, for example, 1900 ° F to 2300 ° F or 1900 ° F to 2100 ° F (i.e., 1038-1260 ° C or 1038-1149 ° C).
[052] In several modalities, the processes disclosed here can be characterized by the formation of an α + β titanium alloy article having a final tensile strength in the range of 155 ksi to 200 ksi (1069-1379 MPa) and an elongation in range of 8% to 20% at room temperature. In addition, in several modalities, the processes disclosed here can be characterized by the formation of a titanium alloy article α + β having a final tensile strength in the range of 160 ksi to 180 ksi (1103-1241 MPa) and an elongation in range of 8% to 20% at room temperature. In addition, in various modalities, the processes disclosed here can be characterized by the formation of an α + β titanium alloy article having a final tensile strength in the range of 165 ksi to 180 ksi (1138-1241 MPa) and an elongation in range of 8% to 17% at room temperature.
[053] In various modalities, the processes disclosed here can be characterized by the formation of a titanium alloy article α + β having a resistance to deformation in the range of 140 to 165 ksi (965-1138 MPa) and an elongation in the range of 8 to 20% at room temperature. In addition, in several modalities, the processes disclosed here can be characterized by the formation of an α + β titanium alloy article having a resistance to deformation in the range of 155 ksi to 165 ksi
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19/31 (1069-1138 MPa) and an elongation in the range of 8% to 15% at room temperature.
[054] In several modalities, the processes disclosed here can be characterized by the formation of an α + β titanium alloy article having a final tensile strength in any sub-range subsumed in 155 ksi to 200 ksi (1069-1379 MPa) , a resistance to deformation in any sub-band subsumed in 140 ksi to 165 ksi (965-1138 MPa), and an elongation in any sub-band subsumed in 8% to 20%, at room temperature.
[055] In various modalities, the processes disclosed here can be characterized by the formation of a titanium alloy article α + β having a final tensile strength greater than 155 ksi, a resistance to deformation greater than 140 ksi, and a elongation greater than 8% at room temperature. An α + β titanium alloy article formed according to various modalities may have a final tensile strength greater than 166 ksi, greater than 175 ksi, greater than 185 ksi, or greater than 195 ksi at room temperature. A formation of α + β titanium alloy article according to various modalities can have a deformation resistance greater than 145 ksi, greater than 155 ksi or greater than 160 ksi, at room temperature. A formation of α + β titanium alloy article according to various modalities may have an elongation greater than 8%, greater than 10%, greater than 12%, greater than 14%, greater than 16%, or greater than 18% at room temperature.
[056] In various modalities, the processes disclosed here can be characterized by the formation of an α + β titanium alloy article having a final tensile strength, a resistance to deformation, and an elongation at room temperature, which are at least as large as a final tensile strength, a resistance to deformation, and an elongation at room temperature of an otherwise identical article consisting of a Ti-6AIU-4V alloy in a treated conditionPetition 870180138493, of 10/05/2018, pg . 41/75
20/31 da in solution and aged (STA).
[057] In various embodiments, the processes disclosed here can be used to thermomechanically process α + β titanium alloys comprising, consisting of or consisting essentially of weight percentages, from 2.90% to 5.00% aluminum, of 2.00% to 3.00% vanadium, 0.40% to 2.00% iron, 0.10% to 0.30% oxygen, incidental elements, and titanium.
[058] The concentration of aluminum in α + β titanium alloys thermomechanically processed according to the processes disclosed here can vary from 2.90 to 5.00 percent by weight, or any sub-band in it, such as, for example, 3.00% to 5.00%, 3.50% to 4.50%, 3.70% to 4.30%, 3.75% to 4.25%, or 3.90% to 4.50%. The concentration of vanadium in α + β titanium alloys processed thermomechanically according to the processes disclosed here can vary from 2.00 to 3.00 weight percent, or any sub-band in it, such as 2, 20% to 3.00%, 2.20% to 2.80%, or 2.30% to 2.70%. The concentration of iron in the thermomechanically processed α + β titanium alloys disclosed here can vary from 0.40 to 2.00 weight percent, or any sub-band in it, such as 0.50% to 2 , 00%, 1.00% to 2.00%, 1.20% to 1.80%, or 1.30% to 1.70%. The oxygen concentration in the thermomechanically processed α + β titanium alloys according to the processes disclosed here can vary from 0.10 to 0.30 percent by weight, or any sub-band in it, such as 0 , 15% to 0.30%, 0.10% to 0.20%, 0.10% to 0.15%, 0.18% to 0.28%, 0.20% to 0.30%, 0 , 22% to 0.28%, 0.24% to 0.30%, or 0.23% to 0.27%.
[059] In various embodiments, the processes disclosed here can be used to thermomechanically process an α + β titanium alloy comprising, consisting of, or consisting essentially of the nominal composition of 4.00 weight percent aluminum, 2.50 per percent by weight of vanadium, 1.50 percent by weight of iron and 0.25 percent by weight of oxygen, titanium, and incidental impurities
Petition 870180138493, of 10/05/2018, p. 42/75
21/31 (Ti-4Al-2.5V-1.5Fe-0.25O). an α + β titanium alloy having the nominal composition Ti4Al-2.5V-1.5Fe-0.25O is commercially available as an ATI 425® alloy from Allegheny Technologies Incorporated.
[060] In various embodiments, the processes disclosed here can be used to thermomechanically process α + β titanium alloys comprising, consisting of, or consisting essentially of titanium, aluminum, vanadium, iron, oxygen, incidental impurities, and less than 0 , 50 weight percent of any other intentional alloying elements. In various embodiments, the processes disclosed herein can be used to thermomechanically process α + β titanium alloys comprising, consisting of, or consisting essentially of titanium, aluminum, vanadium, iron, oxygen and less than 0.50 weight percent of any other elements including intentional alloying elements and incidental impurities. In various modalities the maximum level of total elements (incidental impurities and / or intentional alloying additions) other than titanium, aluminum, vanadium, iron and oxygen, can be 0.40 percent by weight, 0.30 percent in weight, 0.25 percent by weight, 0.20 percent by weight or 0.10 percent by weight.
[061] In various embodiments, α + β titanium alloys processed as described here may comprise, consist essentially of or consist of a composition according to AMS 6946A, section 3.1, which is incorporated by reference here, and which specifies the composition provided in table 1 (percentages by weight).
Table 1
Element Minimum Maximum Aluminum 3.50 4.50 Vanadium 2.00 3.00 iron 1.20 1.80 oxygen 0.20 0.30 Carbon - 0.08 Nitrogen - 0.03 Hydrogen - 0.015 other elements (each) - 0.10
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22/31
other elements (total) - 1 0.30 Titanium remaining
[062] In several embodiments, α + β titanium alloys processed as described here can include several different elements of titanium, aluminum, vanadium, iron and oxygen. For example, such other elements, and their percentages by weight, may include, but are not necessarily limited to, one or more of the following: (a) chromium, 0.10% maximum, generally 0.0001% to 0.05 %, or up to approximately 0.03%; (b) nickel, 0.10% maximum, generally from 0.001% to 0.05% or up to approximately 0.02%; (c) molybdenum, 0.10% maximum; (d) zirconium, 0.10% maximum; (e) tin, 0.10% maximum; (f) carbon, 0.10% maximum, generally from 0.005% to 0.03% or up to approximately 0.01%; and / or (g) nitrogen, 0.10% maximum, generally from 0.001% to 0.02%, or up to approximately 0.01%.
[063] The processes disclosed here can be used to form articles such as, for example, ingots, bars, rods, wires, tubes, pipes, plates, plates, structural elements, fasteners, rivets, and the like. In various modalities, the processes disclosed here produce articles having a final tensile strength in the range of 155 ksi to 200 ksi (1069-1379 MPa), a resistance to deformation in the range of 140 ksi to 165 ksi (965-1138 MPa) and an elongation in the range of 8% to 20% at room temperature, and having a minimum dimension (for example, diameter or thickness) greater than 0.5 inch, greater than 1.0 inch, greater than 2.0 inches , greater than 3.0 inches, greater than 4.0 inches, greater than 5.0 inches, or greater than 10.0 inches (that is, greater than 1.27 cm, 2.54 cm, 5.08 cm, 7.62 cm, 10.16 cm, 12.70 cm, or 24.50 cm).
[064] In addition, one of the several process modalities advantages disclosed here is that high strength α + β titanium alloy articles can be formed without a size limitation, which is an inherent limitation of STA processing. As a result, the processes revealed here can produce articles having a final tensile strength greater than 165 ksi (1138 MPa), a repetition 870180138493, from 10/05/2018, pg. 44/75
23/31 resistance to deformation greater than 155 ksi (1069 MPa), and an elongation greater than 8%, at room temperature, without inherent limitation on the maximum value of the small dimension (for example, diameter or thickness) of the article. Therefore, the maximum size limitation is only triggered by the size limitations of the cold work equipment used to perform cold work according to the modalities disclosed here. In contrast, STA processing places an inherent limit on the maximum value of the small dimension of an article that can achieve high strength, for example, a maximum of 0.5 inch (1.27 cm) for Ti-6Al-4V articles showing at least 165 ksi (1138 MPa) of ultimate tensile strength and at least 155 ksi (1069 MPa) of resistance to deformation at room temperature. See AMS 6930A.
[065] In addition, the processes disclosed here can produce articles of α + β titanium alloy having high strength with low or zero thermal stresses and better dimensional tolerances than high strength articles produced using STA processing. Cold drawing and direct aging according to the processes disclosed here do not transmit problematic internal thermal stresses, do not cause warping of articles and do not cause dimensional distortion of articles which is known to occur with STA processing of α + β titanium alloy articles.
[066] The process disclosed here can also be used to form articles of titanium alloy α + β having mechanical properties comprised in a wide range depending on the level of cold work and the time / temperature of the aging treatment. In various modalities, final tensile strength can vary from approximately 155 ksi to more than 180 ksi (approximately 1069 MPa to more than 1241 MPa), deformation resistance can vary from approximately 140 ksi to approximately 163 ksi (965-1124 MPa), and elongation can vary from approximately 8% to more than 19%. Different mechanical properties can
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24/31 be obtained through different combinations of cold work and aging treatment. In various modalities, higher levels of cold work (eg reductions) can correlate with higher strength and lower ductility, while higher aging temperatures can correlate with lower strength and higher ductility. In this way, cold working and aging cycles can be specified according to the modalities revealed here to obtain controlled and reproducible levels of resistance and ductility in α + β titanium alloy articles. This allows the production of α + β titanium alloy articles having moldable mechanical properties.
[067] The illustrative and non-limiting examples that follow are intended to further describe various non-limiting modalities without restricting the scope of the modalities. Those of ordinary skill in the art will recognize that variations of the Examples are possible within the scope of the invention as defined by the claims.
EXAMPLES
Example 1 [068] Cylindrical ingots 5.0 inches in diameter from two different matches having an average chemical composition shown in table 2 (exclusive of incidental impurities) were hot rolled in the α + β phase field at a temperature of 1600 ° F (871 ° C) to form 1.0 inch diameter round bars.
Table 2
Match Al V Faith O N Ç You X 4.36 2.48 1.28 0.272 0.005 0.010 remaining Y 4.10 2.31 1.62 0.187 0.004 0.007 remaining
[069] The 1.0 inch round bars were annealed at a temperature of 1275 ° F for one hour and air-cooled to room temperature. The annealed bars were cold worked at room temperature using stretching operations to reduce the diameters of the bars. The amount of cold work
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25/31 performed on the bars during cold drawing operations was quantified as the percentages of reductions in the area in circular cross section for the round bars during cold drawing. The percentages of cold work obtained were 20%, 30%, or 40% of reductions in area (RA). Stretching operations were performed using a single stretch pass for 20% reductions in area and two stretch passes for 30% and 40% reductions in area, without intermediate annealing.
[070] Final tensile strength (UTS), deformation resistance (YS) and elongation (%) were measured at room temperature for each cold drawn bar (20%, 30% and 40% RA) and for bars with 1 inch in diameter that were not cold drawn (0% RA). The mediated results are shown in table 3 and figures 1 and 2.
Table 3
Heat Cold drawing (% RA) UTS(ksi) YS (ksi) Stretching(%) X 0 144.7 132.1 18.1 20 176.3 156.0 9.5 30 183.5 168.4 8.2 40 188.2 166.2 7.7 Y 0 145.5 130.9 17.7 20 173.0 156.3 9.7 30 181.0 163.9 7.0 40 182.8 151.0 8.3
[071] The ultimate tensile strength has generally increased with increasing levels of cold work, while stretching has generally decreased with increasing levels of cold work up to approximately 20-30% of cold work. Cold-worked alloys at 30% and 40% retained approximately 8% elongation with final tensile strengths greater than 180 ksi and approaching 190 ksi. Cold-worked alloys at 30% and 40% also showed resistance to deformation in the range of 150 ksi to 170 ksi.
Example 2 [072] Cylindrical ingots 5 inches in diameter having the composition
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26/31 Starting X average chemistry shown in table 1 (β-transus temperature 1790 ° F) were thermomechanically processed as described in example 1 to form round bars having cold work percentages of 20%, 30% or 40% of reductions in area. After cold stretching, the bars were directly aged using one of the aging cycles shown in table 4, followed by cold air to room temperature.
Table 4
Aging temperature ( ^o F) Aging time (hour) 850 1.00 850 8.00 925 4.50 975 2.75 975 4.50 975 6.25 1100 1.00 1100 8.00
[073] Final tensile strength, resistance to deformation and elongation were measured at room temperature for each cold drawn and aged bar. The raw data are shown in figure 3 and the mediated data are shown in figure 4 and table 5.
Table 5
Stretchcold(%FROG) Aging temperature ( ^o F) Time toaging(hour) UTS (ksi) YS (ksi) Stretching (%) 20 850 1.00 170.4 156.2 14.0
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27/31
Stretchcold Temperatureaging Time toaging UTS (ksi) YS (ksi) Stretching (%) (%FROG) ment ( ^the F) (hour) 30 850 1.00 174.6 158.5 13.5 40 850 1.00 180.6 162.7 12.9 20 850 8.00 168.7 153.4 13.7 30 850 8.00 175.2 158.5 12.6 40 850 8.00 179.5 161.0 11.5 20 925 4.50 163.4 148.0 15.2 30 925 4.50 168.8 152.3 14.0 40 925 4.50 174.5 156.5 13.7 20 975 2.75 161.7 146.4 14.8 30 975 2.75 167.4 155.8 15.5 40 975 2.75 173.0 155.1 13.0 20 975 4.50 160.9 145.5 14.4 30 975 4.50 169.3 149.9 13.2 40 975 4.50 174.4 153.9 12.9 20 975 6.25 163.5 144.9 14.7 30 975 6.25 172.7 150.3 12.9 40 975 6.25 171.0 153.4 12.9 20 1100 1.00 155.7 140.6 18.3 30 1100 1.00 163.0 146.5 15.2 40 1100 1.00 165.0 147.8 15.2 20 1100 8.00 156.8 141.8 18.0 30 1100 8.00 162.1 146.1 17.2 40 1100 8.00 162.1 145.7 17.8
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28/31 [074] Cold drawn and aged alloys showed a range of mechanical properties depending on the level of cold work and temperature / time cycle of the aging treatment. The final tensile strength ranged from approximately 155 ksi to more than 180 ksi. Deformation resistance ranged from approximately 140 ksi to approximately 163 ksi. The elongation ranged from approximately 11% to more than 19%. Therefore, different mechanical properties can be obtained through different combinations of cold work level and aging treatment.
[075] Higher levels of cold work generally correlated with higher strength and lower ductility. Higher aging temperatures generally correlated with lower resistance. This is shown in figures 5, 6 and 7, which are graphs of resistance (average UTS and average YS) versus temperature for cold work percentages of 20%, 30% and 40% of reductions in area, respectively. Higher aging temperatures generally correlated with higher ductility. This is shown in Figures 8, 9 and 10, which are graphs of average elongation versus temperature for percentages of cold work of 20%, 30% and 40% reductions in area, respectively. The duration of the aging treatment does not appear to have a significant effect on the mechanical properties as illustrated in figures 11 and 12, which are graphs of resistance and elongation, respectively, versus time for percentage of cold work of 20% reduction in area.
Example 3 [076] Cold drawn round bars having the starting X chemical composition shown in table 1, 0.75 inch diameters and processed as described in examples 1 and 2 at 40% area reductions during a drawing operation were double shear tested in accordance with NASM 1312-13 (Aerospace Industries Association, February 1, 2003, incorporated as
Petition 870180138493, of 10/05/2018, p. 50/75
29/31 reference here). The double shear test provides an assessment of the applicability of this combination of alloy chemistry and thermomechanical processing for the production of high strength fastener material. A first set of round bars was tested in the stretched condition and a second set of round bars was tested after being aged at 850 ° F for 1 hour and cooled in air at room temperature (850/1 / AC). The results of resistance to double shear are presented in table 5 together with average values for final tensile strength, resistance to deformation and elongation. For comparative purposes, the minimum specified values for these mechanical properties for Ti-6Al-4V fastening material are also shown in table 6.
Table 6
Condition Size Cold drawing (% RA) UTS(ksi) YS(ksi) Stretching(%) Double shear strength (ksi) howstretched 0.75 40 188.2 166.2 7.7 100.6 102 850/1 / AC 0.75 40 180.6 162.7 12.9 103.2 102.4 Ti-6-4target 0.75 AT 165 155 10 102
[077] Cold drawn and aged alloys showed mechanical properties higher than the minimum specified values for Ti-6Al-4V fastener material applications. As such, the processes revealed here can offer a
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30/31 more efficient alternative to the production of Ti-6Al-4V articles using STA processing.
[078] α + β titanium alloys from cold working and aging comprising, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 of iron, 0.10 to 0.30 of oxygen, and titanium, according to the various modalities disclosed here, produce alloy articles having mechanical properties that exceed the minimum specified mechanical properties of Ti-6Al-4V alloys for various applications, including, for example, aerospace applications in general and fastener applications. As noted above, Ti-6Al-4V alloys require STA processing to obtain the necessary strength required for critical applications, such as aerospace applications. As such, high strength Ti-6Al-4V alloys are limited by the size of the articles due to the material's inherent physical properties and the requirement for sudden cooling during STA processing. In contrast, cold-worked and aged high-strength α + β titanium alloys, as described here, are not limited in terms of article size and dimensions. In addition, cold-worked and aged high-strength α + β titanium alloys, as described here, do not experience large internal and thermal stresses or warpage, which may be characteristic of Ti-6Al-4V alloy articles of more section thick during STA processing.
[079] The revelation was written with reference to several exemplary, illustrative and non-limiting modalities. However, it will be recognized by people having common knowledge in the art that various substitutions, modifications or combinations of any of the disclosed modalities (or portions thereof) can be made without departing from the scope of the invention. Thus, it is considered and understood that the present disclosure covers additional modalities not expressly exposed here. Such modalities can be obtained, for example, by combining, modifying or reorganizing any of the revealed steps, components, elePetição 870180138493, of 10/05/2018, p. 52/75
31/31 ments, resources, aspects, characteristics, limitations, and similar, of the modalities described here. In this regard, the claimant reserves the right to change the claims during execution to add aspects as described in various ways here.

权利要求:
Claims (25)
[1]
1. Process to form an α + β titanium alloy article, FEATURED by the fact that it comprises:
cold working an α + β titanium alloy at a temperature in the ambient temperature range up to 260 ° C (500 ° F); and age directly the α + β titanium alloy at a temperature in the range of 371 ° C to 649 ° C (700 ° F to 1200 ° F) after cold working;
the titanium alloy α + β comprising, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, from 0, 10 to 0.30 of oxygen, titanium and incidental impurities, in which cold work and aging form an article of titanium alloy α + β with a final tensile strength in the range of 1069 MPa to 1379 MPa (155 ksi at 200 ksi) and an elongation in the range of 8% to 20%, at room temperature.
[2]
2. Process, according to claim 1, CHARACTERIZED by the fact that cold working and aging form a titanium alloy article α + β having a final tensile strength in the range of 1138 MPa to 1241 MPa (165 ksi to 180 ksi) and an elongation in the range of 8% to 17% at room temperature.
[3]
3. Process, according to claim 1, CHARACTERIZED by the fact that cold working and aging form a titanium alloy article α + β having a resistance to deformation in the range of 965 MPa to 1138 MPa (140 ksi to 165 ksi ) and an elongation in the range of 8% to 20% at room temperature.
[4]
4. Process, according to claim 1, CHARACTERIZED by the fact that cold working and aging form a titanium alloy article α + β having a resistance to deformation in the range of 1069 MPa to 1138 MPa (155 ksi to 165 ksi ) and an elongation in the range of 8% to 15% at room temperature.
[5]
5. Process, according to claim 1, CHARACTERIZED by the fact that cold work and aging form an α + β titanium alloy article
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2/4 having a final tensile strength, a resistance to deformation and an elongation at room temperature, which are at least as great as a final tensile strength, a resistance to deformation and an elongation at room temperature of an article otherwise identical consisting of a Ti-6Al-4V alloy in a solution treated and aged condition.
[6]
6. Process, according to claim 1, CHARACTERIZED because it comprises cold working the α + β titanium alloy until a reduction of 20% to 60% in area.
[7]
7. Process, according to claim 1, CHARACTERIZED because it comprises cold working the α + β titanium alloy until a reduction of 20% to 40% in area.
[8]
8. Process, according to claim 1, CHARACTERIZED by the fact that cold working of the α + β titanium alloy comprises at least two deformation cycles, in which each cycle comprises cold working the titanium alloy α + β up to at least minus 10% reduction in area.
[9]
9. Process according to claim 1, CHARACTERIZED by the fact that the cold working of the α + β titanium alloy comprises at least two deformation cycles, in which each cycle comprises cold working the α + β titanium alloy up to at least minus 20% reduction in area.
[10]
10. Process according to claim 1, CHARACTERIZED because it comprises cold working the titanium alloy α + β at a temperature in the range of room temperature up to 204 ° C (400 ° F).
[11]
11. Process according to claim 1, CHARACTERIZED because it comprises cold working the titanium alloy α + β at room temperature.
[12]
12. Process according to claim 1, CHARACTERIZED by comprising aging the titanium alloy α + β at a temperature in the range of 427 ° C to 593 ° C (800 ° F to 1150 ° F) after cold working.
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3/4
[13]
13. Process according to claim 1, characterized by aging the titanium alloy α + β at a temperature in the range of 454 ° C to 593 ° C (850 ° F to 1100 ° F) after cold working.
[14]
14. Process, according to claim 1, CHARACTERIZED for comprising aging the titanium alloy α + β for up to 50 hours.
[15]
15. Process, according to claim 14, CHARACTERIZED by comprising aging the titanium alloy α + β for 0.5 to 10 hours.
[16]
16. Process, according to claim 1, CHARACTERIZED because it also includes hot working the titanium alloy α + β at a temperature in the range of 137 ° C to 14 ° C (300 ° F to 25 ° F) below the temperature β-transus of the titanium alloy α + β, where hot work is carried out before cold work.
[17]
17. Process, according to claim 16, CHARACTERIZED by further comprising annealing the α + β titanium alloy at a temperature in the range of 649 ° C to 816 ° C (1200 ° F to 1500 ° F) where the annealing is carried out between hot work and cold work.
[18]
18. Process according to claim 16, CHARACTERIZED because it comprises hot working the α + β titanium alloy at a temperature in the range of 816 ° C to 968 ° C (1500 ° F to 1775 ° F).
[19]
19. Process, according to claim 1, CHARACTERIZED by the fact that the titanium alloy α + β consists of, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium , 0.40 to 2.00 iron, 0.10 to 0.30 oxygen, incidental impurities, and titanium.
[20]
20. Process, according to claim 1, CHARACTERIZED by the fact that the titanium alloy α + β consists essentially of, in weight percentages, from 3.50 to 4.50 aluminum, from 2.00 to 3.00 aluminum vanadium, from 1.00 to 2.00 iron, from 0.10 to 0.30 oxygen and titanium.
[21]
21. Process, according to claim 1, CHARACTERIZED by the
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4/4 the fact that the α + β titanium alloy consists essentially of, in weight percentages, from 3.70 to 4.30 aluminum, from 2.20 to 2.80 vanadium, from 1.20 to 1.80 of iron, from 0.22 to 0.28 of oxygen and titanium.
[22]
22. Process, according to claim 1, CHARACTERIZED by the fact that cold working of the α + β titanium alloy comprises cold working for at least one operation selected from the group consisting of rolling, forging, extrusion, cold reduction, oscillation and stretching.
[23]
23. Process, according to claim 1, CHARACTERIZED by the fact that cold working of the α + β titanium alloy comprises cold drawing the α + β titanium alloy.
[24]
24. Process, according to claim 1, CHARACTERIZED by the fact that aging is carried out directly after cold work.
[25]
25. Process for forming an α + β titanium alloy article, CHARACTERIZED by the fact that it comprises:
cold working the α + β titanium alloy at a temperature in the ambient temperature range up to 260 ° C (500 ° F); and age directly the α + β titanium alloy at a temperature in the range of 371 ° C to 649 ° C (700 ° F to 1200 ° F) after cold working;
where the process does not include a hot treatment between cold working and aging;
the titanium alloy α + β comprising, in weight percentages, from 2.90 to 5.00 aluminum, from 2.00 to 3.00 vanadium, from 0.40 to 2.00 iron, from 0, 10 to 0.30 of oxygen, titanium and incidental impurities, and cold working and aging form an α + β titanium alloy article with a final tensile strength in the range of 1069 MPa to 1379 MPa (155 ksi to 200 ksi) and an elongation in the range of 8% to 20% at room temperature.

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US10144999B2|2018-12-04|

EP2596143A1|2013-05-29|

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TW201224162A|2012-06-16|

引用文献:

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

US2974076A|1954-06-10|1961-03-07|Crucible Steel Co America|Mixed phase, alpha-beta titanium alloys and method for making same|

GB847103A|1956-08-20|1960-09-07|Copperweld Steel Co|A method of making a bimetallic billet|

US3025905A|1957-02-07|1962-03-20|North American Aviation Inc|Method for precision forming|

US3015292A|1957-05-13|1962-01-02|Northrop Corp|Heated draw die|

US2932886A|1957-05-28|1960-04-19|Lukens Steel Co|Production of clad steel plates by the 2-ply method|

US2857269A|1957-07-11|1958-10-21|Crucible Steel Co America|Titanium base alloy and method of processing same|

US2893864A|1958-02-04|1959-07-07|Harris Geoffrey Thomas|Titanium base alloys|

US3060564A|1958-07-14|1962-10-30|North American Aviation Inc|Titanium forming method and means|

US3082083A|1960-12-02|1963-03-19|Armco Steel Corp|Alloy of stainless steel and articles|

US3117471A|1962-07-17|1964-01-14|Kenneth L O'connell|Method and means for making twist drills|

US3313138A|1964-03-24|1967-04-11|Crucible Steel Co America|Method of forging titanium alloy billets|

US3379522A|1966-06-20|1968-04-23|Titanium Metals Corp|Dispersoid titanium and titaniumbase alloys|

US3436277A|1966-07-08|1969-04-01|Reactive Metals Inc|Method of processing metastable beta titanium alloy|

DE1558632C3|1966-07-14|1980-08-07|Sps Technologies, Inc., Jenkintown, Pa. |Application of deformation hardening to particularly nickel-rich cobalt-nickel-chromium-molybdenum alloys|

US3489617A|1967-04-11|1970-01-13|Titanium Metals Corp|Method for refining the beta grain size of alpha and alpha-beta titanium base alloys|

US3469975A|1967-05-03|1969-09-30|Reactive Metals Inc|Method of handling crevice-corrosion inducing halide solutions|

US3605477A|1968-02-02|1971-09-20|Arne H Carlson|Precision forming of titanium alloys and the like by use of induction heating|

US4094708A|1968-02-16|1978-06-13|Imperial Metal Industries Limited|Titanium-base alloys|

US3615378A|1968-10-02|1971-10-26|Reactive Metals Inc|Metastable beta titanium-base alloy|

US3584487A|1969-01-16|1971-06-15|Arne H Carlson|Precision forming of titanium alloys and the like by use of induction heating|

US3635068A|1969-05-07|1972-01-18|Iit Res Inst|Hot forming of titanium and titanium alloys|

US3649259A|1969-06-02|1972-03-14|Wyman Gordon Co|Titanium alloy|

GB1501622A|1972-02-16|1978-02-22|Int Harvester Co|Metal shaping processes|

US3676225A|1970-06-25|1972-07-11|United Aircraft Corp|Thermomechanical processing of intermediate service temperature nickel-base superalloys|

US3686041A|1971-02-17|1972-08-22|Gen Electric|Method of producing titanium alloys having an ultrafine grain size and product produced thereby|

DE2148519A1|1971-09-29|1973-04-05|Ottensener Eisenwerk Gmbh|METHOD AND DEVICE FOR HEATING AND BOARDING RUBBES|

DE2204343C3|1972-01-31|1975-04-17|Ottensener Eisenwerk Gmbh, 2000 Hamburg|Device for heating the edge zone of a circular blank rotating around the central normal axis|

US3802877A|1972-04-18|1974-04-09|Titanium Metals Corp|High strength titanium alloys|

JPS5025418A|1973-03-02|1975-03-18|

FR2237435A5|1973-07-10|1975-02-07|Aerospatiale|

JPS5339183B2|1974-07-22|1978-10-19|

SU534518A1|1974-10-03|1976-11-05|Предприятие П/Я В-2652|The method of thermomechanical processing of alloys based on titanium|

US4098623A|1975-08-01|1978-07-04|Hitachi, Ltd.|Method for heat treatment of titanium alloy|

FR2341384B3|1976-02-23|1979-09-21|Little Inc A|

US4053330A|1976-04-19|1977-10-11|United Technologies Corporation|Method for improving fatigue properties of titanium alloy articles|

US4138141A|1977-02-23|1979-02-06|General Signal Corporation|Force absorbing device and force transmission device|

US4120187A|1977-05-24|1978-10-17|General Dynamics Corporation|Forming curved segments from metal plates|

SU631234A1|1977-06-01|1978-11-05|Karpushin Viktor N|Method of straightening sheets of high-strength alloys|

US4163380A|1977-10-11|1979-08-07|Lockheed Corporation|Forming of preconsolidated metal matrix composites|

US4197643A|1978-03-14|1980-04-15|University Of Connecticut|Orthodontic appliance of titanium alloy|

US4309226A|1978-10-10|1982-01-05|Chen Charlie C|Process for preparation of near-alpha titanium alloys|

US4229216A|1979-02-22|1980-10-21|Rockwell International Corporation|Titanium base alloy|

JPS6039744B2|1979-02-23|1985-09-07|Mitsubishi Metal Corp|

CA1194346A|1981-04-17|1985-10-01|Edward F. Clatworthy|Corrosion resistant high strength nickel-base alloy|

US4639281A|1982-02-19|1987-01-27|Mcdonnell Douglas Corporation|Advanced titanium composite|

SU1088397A1|1982-06-01|1991-02-15|Предприятие П/Я А-1186|Method of thermal straightening of articles of titanium alloys|

EP0109350B1|1982-11-10|1991-10-16|Mitsubishi Jukogyo Kabushiki Kaisha|Nickel-chromium alloy|

US4473125A|1982-11-17|1984-09-25|Fansteel Inc.|Insert for drill bits and drill stabilizers|

FR2545104B1|1983-04-26|1987-08-28|Nacam|METHOD OF LOCALIZED ANNEALING BY HEATING BY INDICATING A SHEET OF SHEET AND A HEAT TREATMENT STATION FOR IMPLEMENTING SAME|

RU1131234C|1983-06-09|1994-10-30|ВНИИ авиационных материалов|Titanium-base alloy|

US4510788A|1983-06-21|1985-04-16|Trw Inc.|Method of forging a workpiece|

SU1135798A1|1983-07-27|1985-01-23|Московский Ордена Октябрьской Революции И Ордена Трудового Красного Знамени Институт Стали И Сплавов|Method for treating billets of titanium alloys|

JPH0232640Y2|1983-09-01|1990-09-04|

US4543132A|1983-10-31|1985-09-24|United Technologies Corporation|Processing for titanium alloys|

JPS6157390B2|1983-11-04|1986-12-06|Mitsubishi Metal Corp|

US4554028A|1983-12-13|1985-11-19|Carpenter Technology Corporation|Large warm worked, alloy article|

FR2557145B1|1983-12-21|1986-05-23|Snecma|THERMOMECHANICAL TREATMENT PROCESS FOR SUPERALLOYS TO OBTAIN STRUCTURES WITH HIGH MECHANICAL CHARACTERISTICS|

US4482398A|1984-01-27|1984-11-13|The United States Of America As Represented By The Secretary Of The Air Force|Method for refining microstructures of cast titanium articles|

DE3405805A1|1984-02-17|1985-08-22|Siemens AG, 1000 Berlin und 8000 München|PROTECTIVE TUBE ARRANGEMENT FOR FIBERGLASS|

US4631092A|1984-10-18|1986-12-23|The Garrett Corporation|Method for heat treating cast titanium articles to improve their mechanical properties|

GB8429892D0|1984-11-27|1985-01-03|Sonat Subsea Services Uk Ltd|Cleaning pipes|

US4690716A|1985-02-13|1987-09-01|Westinghouse Electric Corp.|Process for forming seamless tubing of zirconium or titanium alloys from welded precursors|

JPH0588304B2|1985-03-25|1993-12-21|Hitachi Metals Ltd|

AT381658B|1985-06-25|1986-11-10|Ver Edelstahlwerke Ag|METHOD FOR PRODUCING AMAGNETIC DRILL STRING PARTS|

US4668290A|1985-08-13|1987-05-26|Pfizer Hospital Products Group Inc.|Dispersion strengthened cobalt-chromium-molybdenum alloy produced by gas atomization|

US4714468A|1985-08-13|1987-12-22|Pfizer Hospital Products Group Inc.|Prosthesis formed from dispersion strengthened cobalt-chromium-molybdenum alloy produced by gas atomization|

US4639231A|1985-09-23|1987-01-27|The Singer Company|Retainer for electrically fired getter|

EP0235075B1|1986-01-20|1992-05-06|Mitsubishi Jukogyo Kabushiki Kaisha|Ni-based alloy and method for preparing same|

JPH0524980B2|1986-03-28|1993-04-09|Sumitomo Metal Ind|

DE3622433A1|1986-07-03|1988-01-21|Deutsche Forsch Luft Raumfahrt|METHOD FOR IMPROVING THE STATIC AND DYNAMIC MECHANICAL PROPERTIES OF + SS) TIT ALLOYS|

US4799975A|1986-10-07|1989-01-24|Nippon Kokan Kabushiki Kaisha|Method for producing beta type titanium alloy materials having excellent strength and elongation|

FR2614040B1|1987-04-16|1989-06-30|Cezus Co Europ Zirconium|PROCESS FOR THE MANUFACTURE OF A PART IN A TITANIUM ALLOY AND A PART OBTAINED|

US4808249A|1988-05-06|1989-02-28|The United States Of America As Represented By The Secretary Of The Air Force|Method for making an integral titanium alloy article having at least two distinct microstructural regions|

US4851055A|1988-05-06|1989-07-25|The United States Of America As Represented By The Secretary Of The Air Force|Method of making titanium alloy articles having distinct microstructural regions corresponding to high creep and fatigue resistance|

US4888973A|1988-09-06|1989-12-26|Murdock, Inc.|Heater for superplastic forming of metals|

US4857269A|1988-09-09|1989-08-15|Pfizer Hospital Products Group Inc.|High strength, low modulus, ductile, biopcompatible titanium alloy|

CA2004548C|1988-12-05|1996-12-31|Kenji Aihara|Metallic material having ultra-fine grain structure and method for its manufacture|

US4957567A|1988-12-13|1990-09-18|General Electric Company|Fatigue crack growth resistant nickel-base article and alloy and method for making|

US5173134A|1988-12-14|1992-12-22|Aluminum Company Of America|Processing alpha-beta titanium alloys by beta as well as alpha plus beta forging|

US4975125A|1988-12-14|1990-12-04|Aluminum Company Of America|Titanium alpha-beta alloy fabricated material and process for preparation|

US4943412A|1989-05-01|1990-07-24|Timet|High strength alpha-beta titanium-base alloy|

US4980127A|1989-05-01|1990-12-25|Titanium Metals Corporation Of America |Oxidation resistant titanium-base alloy|

US5366598A|1989-06-30|1994-11-22|Eltech Systems Corporation|Method of using a metal substrate of improved surface morphology|

US5256369A|1989-07-10|1993-10-26|Nkk Corporation|Titanium base alloy for excellent formability and method of making thereof and method of superplastic forming thereof|

US5074907A|1989-08-16|1991-12-24|General Electric Company|Method for developing enhanced texture in titanium alloys, and articles made thereby|

JP2536673B2|1989-08-29|1996-09-18|日本鋼管株式会社|Heat treatment method for titanium alloy material for cold working|

US5041262A|1989-10-06|1991-08-20|General Electric Company|Method of modifying multicomponent titanium alloys and alloy produced|

US5026520A|1989-10-23|1991-06-25|Cooper Industries, Inc.|Fine grain titanium forgings and a method for their production|

US5169597A|1989-12-21|1992-12-08|Davidson James A|Biocompatible low modulus titanium alloy for medical implants|

KR920004946B1|1989-12-30|1992-06-22|포항종합제철 주식회사|Making process for the austenite stainless steel|

US5244517A|1990-03-20|1993-09-14|Daido Tokushuko Kabushiki Kaisha|Manufacturing titanium alloy component by beta forming|

US5032189A|1990-03-26|1991-07-16|The United States Of America As Represented By The Secretary Of The Air Force|Method for refining the microstructure of beta processed ingot metallurgy titanium alloy articles|

US5094812A|1990-04-12|1992-03-10|Carpenter Technology Corporation|Austenitic, non-magnetic, stainless steel alloy|

JP2841766B2|1990-07-13|1998-12-24|住友金属工業株式会社|Manufacturing method of corrosion resistant titanium alloy welded pipe|

JP2968822B2|1990-07-17|1999-11-02|株式会社神戸製鋼所|Manufacturing method of high strength and high ductility β-type Ti alloy material|

KR920004946A|1990-08-29|1992-03-28|한태희|VGA input / output port access circuit|

EP0479212B1|1990-10-01|1995-03-01|Sumitomo Metal Industries, Ltd.|Method for improving machinability of titanium and titanium alloys and free-cutting titanium alloys|

EP0484931B1|1990-11-09|1998-01-14|Kabushiki Kaisha Toyota Chuo Kenkyusho|Sintered powdered titanium alloy and method for producing the same|

RU2003417C1|1990-12-14|1993-11-30|Всероссийский институт легких сплавов|Method of making forged semifinished products of cast ti-al alloys|

FR2675818B1|1991-04-25|1993-07-16|Saint Gobain Isover|ALLOY FOR FIBERGLASS CENTRIFUGAL.|

FR2676460B1|1991-05-14|1993-07-23|Cezus Co Europ Zirconium|PROCESS FOR THE MANUFACTURE OF A TITANIUM ALLOY PIECE INCLUDING A MODIFIED HOT CORROYING AND A PIECE OBTAINED.|

US5219521A|1991-07-29|1993-06-15|Titanium Metals Corporation|Alpha-beta titanium-base alloy and method for processing thereof|

US5360496A|1991-08-26|1994-11-01|Aluminum Company Of America|Nickel base alloy forged parts|

US5374323A|1991-08-26|1994-12-20|Aluminum Company Of America|Nickel base alloy forged parts|

DE4228528A1|1991-08-29|1993-03-04|Okuma Machinery Works Ltd|METHOD AND DEVICE FOR METAL SHEET PROCESSING|

JP2606023B2|1991-09-02|1997-04-30|日本鋼管株式会社|Method for producing high strength and high toughness α + β type titanium alloy|

CN1028375C|1991-09-06|1995-05-10|中国科学院金属研究所|Process for producing titanium-nickel alloy foil and sheet material|

GB9121147D0|1991-10-04|1991-11-13|Ici Plc|Method for producing clad metal plate|

US5162159A|1991-11-14|1992-11-10|The Standard Oil Company|Metal alloy coated reinforcements for use in metal matrix composites|

US5201967A|1991-12-11|1993-04-13|Rmi Titanium Company|Method for improving aging response and uniformity in beta-titanium alloys|

JP3532565B2|1991-12-31|2004-05-31|ミネソタマイニングアンドマニュファクチャリングカンパニー|Removable low melt viscosity acrylic pressure sensitive adhesive|

US5226981A|1992-01-28|1993-07-13|Sandvik Special Metals, Corp.|Method of manufacturing corrosion resistant tubing from welded stock of titanium or titanium base alloy|

US5399212A|1992-04-23|1995-03-21|Aluminum Company Of America|High strength titanium-aluminum alloy having improved fatigue crack growth resistance|

JP2669261B2|1992-04-23|1997-10-27|三菱電機株式会社|Forming rail manufacturing equipment|

US5277718A|1992-06-18|1994-01-11|General Electric Company|Titanium article having improved response to ultrasonic inspection, and method therefor|

KR0148414B1|1992-07-16|1998-11-02|다나카 미노루|Titanium alloy bar suitable for producing engine valve|

JP3839493B2|1992-11-09|2006-11-01|日本発条株式会社|Method for producing member made of Ti-Al intermetallic compound|

US5310522A|1992-12-07|1994-05-10|Carondelet Foundry Company|Heat and corrosion resistant iron-nickel-chromium alloy|

US5358686A|1993-02-17|1994-10-25|Parris Warren M|Titanium alloy containing Al, V, Mo, Fe, and oxygen for plate applications|

US5332545A|1993-03-30|1994-07-26|Rmi Titanium Company|Method of making low cost Ti-6A1-4V ballistic alloy|

US5483480A|1993-07-22|1996-01-09|Kawasaki Steel Corporation|Method of using associative memories and an associative memory|

FR2711674B1|1993-10-21|1996-01-12|Creusot Loire|Austenitic stainless steel with high characteristics having great structural stability and uses.|

FR2712307B1|1993-11-10|1996-09-27|United Technologies Corp|Articles made of super-alloy with high mechanical and cracking resistance and their manufacturing process.|

JP3083225B2|1993-12-01|2000-09-04|オリエント時計株式会社|Manufacturing method of titanium alloy decorative article and watch exterior part|

JP2988246B2|1994-03-23|1999-12-13|日本鋼管株式会社|Method for producing type titanium alloy superplastic formed member|

JP2877013B2|1994-05-25|1999-03-31|株式会社神戸製鋼所|Surface-treated metal member having excellent wear resistance and method for producing the same|

US5442847A|1994-05-31|1995-08-22|Rockwell International Corporation|Method for thermomechanical processing of ingot metallurgy near gamma titanium aluminides to refine grain size and optimize mechanical properties|

US5472526A|1994-09-30|1995-12-05|General Electric Company|Method for heat treating Ti/Al-base alloys|

AU705336B2|1994-10-14|1999-05-20|Osteonics Corp.|Low modulus, biocompatible titanium base alloys for medical devices|

US5698050A|1994-11-15|1997-12-16|Rockwell International Corporation|Method for processing-microstructure-property optimization of α-β beta titanium alloys to obtain simultaneous improvements in mechanical properties and fracture resistance|

US5759484A|1994-11-29|1998-06-02|Director General Of The Technical Research And Developent Institute, Japan Defense Agency|High strength and high ductility titanium alloy|

JP3319195B2|1994-12-05|2002-08-26|日本鋼管株式会社|Toughening method of α + β type titanium alloy|

US5547523A|1995-01-03|1996-08-20|General Electric Company|Retained strain forging of ni-base superalloys|

US6059904A|1995-04-27|2000-05-09|General Electric Company|Isothermal and high retained strain forging of Ni-base superalloys|

US5600989A|1995-06-14|1997-02-11|Segal; Vladimir|Method of and apparatus for processing tungsten heavy alloys for kinetic energy penetrators|

US6127044A|1995-09-13|2000-10-03|Kabushiki Kaisha Toshiba|Method for producing titanium alloy turbine blades and titanium alloy turbine blades|

JP3445991B2|1995-11-14|2003-09-16|Ｊｆｅスチール株式会社|Method for producing α + β type titanium alloy material having small in-plane anisotropy|

US5649280A|1996-01-02|1997-07-15|General Electric Company|Method for controlling grain size in Ni-base superalloys|

JP3873313B2|1996-01-09|2007-01-24|住友金属工業株式会社|Method for producing high-strength titanium alloy|

US5759305A|1996-02-07|1998-06-02|General Electric Company|Grain size control in nickel base superalloys|

US5861070A|1996-02-27|1999-01-19|Oregon Metallurgical Corporation|Titanium-aluminum-vanadium alloys and products made using such alloys|

JP3838445B2|1996-03-15|2006-10-25|本田技研工業株式会社|Titanium alloy brake rotor and method of manufacturing the same|

EP0834586B1|1996-03-29|2002-09-04|Kabushiki Kaisha Kobe Seiko Sho|High strength titanium alloy, product made therefrom and method for producing the same|

DE19743802C2|1996-10-07|2000-09-14|Benteler Werke Ag|Method for producing a metallic molded component|

RU2134308C1|1996-10-18|1999-08-10|Институт проблем сверхпластичности металлов РАН|Method of treatment of titanium alloys|

IT1286276B1|1996-10-24|1998-07-08|Univ Bologna|METHOD FOR THE TOTAL OR PARTIAL REMOVAL OF PESTICIDES AND / OR PHYTOPHARMACEUTICALS FROM FOOD LIQUIDS AND NOT THROUGH THE USE OF DERIVATIVES OF THE|

US6310300B1|1996-11-08|2001-10-30|International Business Machines Corporation|Fluorine-free barrier layer between conductor and insulator for degradation prevention|

WO1998022629A2|1996-11-22|1998-05-28|Dongjian Li|A new class of beta titanium-based alloys with high strength and good ductility|

US5897830A|1996-12-06|1999-04-27|Dynamet Technology|P/M titanium composite casting|

US5795413A|1996-12-24|1998-08-18|General Electric Company|Dual-property alpha-beta titanium alloy forgings|

JP3959766B2|1996-12-27|2007-08-15|大同特殊鋼株式会社|Treatment method of Ti alloy with excellent heat resistance|

FR2760469B1|1997-03-05|1999-10-22|Onera |TITANIUM ALUMINUM FOR USE AT HIGH TEMPERATURES|

US5954724A|1997-03-27|1999-09-21|Davidson; James A.|Titanium molybdenum hafnium alloys for medical implants and devices|

US5980655A|1997-04-10|1999-11-09|Oremet-Wah Chang|Titanium-aluminum-vanadium alloys and products made therefrom|

US6071360A|1997-06-09|2000-06-06|The Boeing Company|Controlled strain rate forming of thick titanium plate|

ES2130077B1|1997-06-26|2000-01-16|Catarain Arregui Esteban|AUTOMATIC NATURAL JUICE SUPPLY MACHINE.|

US6569270B2|1997-07-11|2003-05-27|Honeywell International Inc.|Process for producing a metal article|

US6044685A|1997-08-29|2000-04-04|Wyman Gordon|Closed-die forging process and rotationally incremental forging press|

NO312446B1|1997-09-24|2002-05-13|Mitsubishi Heavy Ind Ltd|Automatic plate bending system with high frequency induction heating|

US20050047952A1|1997-11-05|2005-03-03|Allvac Ltd.|Non-magnetic corrosion resistant high strength steels|

FR2772790B1|1997-12-18|2000-02-04|Snecma|TITANIUM-BASED INTERMETALLIC ALLOYS OF THE Ti2AlNb TYPE WITH HIGH ELASTICITY LIMIT AND HIGH RESISTANCE TO CREEP|

EP0970764B1|1998-01-29|2009-03-18|Amino Corporation|Apparatus for dieless forming plate materials|

EP1062374A4|1998-03-05|2004-12-22|Memry Corp|Pseudoelastic beta titanium alloy and uses therefor|

KR19990074014A|1998-03-05|1999-10-05|신종계|Surface processing automation device of hull shell|

US6032508A|1998-04-24|2000-03-07|Msp Industries Corporation|Apparatus and method for near net warm forging of complex parts from axi-symmetrical workpieces|

US20010041148A1|1998-05-26|2001-11-15|Kabushiki Kaisha Kobe Seiko Sho|Alpha + beta type titanium alloy, process for producing titanium alloy, process for coil rolling, and process for producing cold-rolled coil of titanium alloy|

CA2272730C|1998-05-26|2004-07-27|Kabushiki Kaisha Kobe Seiko Sho|.alpha. + .beta. type titanium alloy, a titanium alloy strip, coil-rolling process of titanium alloy, and process for producing a cold-rolled titanium alloy strip|

JP3452798B2|1998-05-28|2003-09-29|株式会社神戸製鋼所|High-strength β-type Ti alloy|

US6632304B2|1998-05-28|2003-10-14|Kabushiki Kaisha Kobe Seiko Sho|Titanium alloy and production thereof|

JP3417844B2|1998-05-28|2003-06-16|株式会社神戸製鋼所|Manufacturing method of high-strength Ti alloy with excellent workability|

FR2779155B1|1998-05-28|2004-10-29|Kobe Steel Ltd|TITANIUM ALLOY AND ITS PREPARATION|

JP2000153372A|1998-11-19|2000-06-06|Nkk Corp|Manufacture of copper of copper alloy clad steel plate having excellent working property|

US6334912B1|1998-12-31|2002-01-01|General Electric Company|Thermomechanical method for producing superalloys with increased strength and thermal stability|

US6409852B1|1999-01-07|2002-06-25|Jiin-Huey Chern|Biocompatible low modulus titanium alloy for medical implant|

US6143241A|1999-02-09|2000-11-07|Chrysalis Technologies, Incorporated|Method of manufacturing metallic products such as sheet by cold working and flash annealing|

US6187045B1|1999-02-10|2001-02-13|Thomas K. Fehring|Enhanced biocompatible implants and alloys|

JP3681095B2|1999-02-16|2005-08-10|株式会社クボタ|Bending tube for heat exchange with internal protrusion|

JP3268639B2|1999-04-09|2002-03-25|独立行政法人産業技術総合研究所|Strong processing equipment, strong processing method and metal material to be processed|

RU2150528C1|1999-04-20|2000-06-10|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy|

US6558273B2|1999-06-08|2003-05-06|K. K. Endo Seisakusho|Method for manufacturing a golf club|

JP2001071037A|1999-09-03|2001-03-21|Matsushita Electric Ind Co Ltd|Press working method for magnesium alloy and press working device|

US6402859B1|1999-09-10|2002-06-11|Terumo Corporation|β-titanium alloy wire, method for its production and medical instruments made by said β-titanium alloy wire|

JP4562830B2|1999-09-10|2010-10-13|トクセン工業株式会社|Manufacturing method of β titanium alloy fine wire|

US7024897B2|1999-09-24|2006-04-11|Hot Metal Gas Forming Intellectual Property, Inc.|Method of forming a tubular blank into a structural component and die therefor|

RU2172359C1|1999-11-25|2001-08-20|Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов|Titanium-base alloy and product made thereof|

US6387197B1|2000-01-11|2002-05-14|General Electric Company|Titanium processing methods for ultrasonic noise reduction|

RU2156828C1|2000-02-29|2000-09-27|Воробьев Игорь Андреевич|METHOD FOR MAKING ROD TYPE ARTICLES WITH HEAD FROM DOUBLE-PHASE TITANIUM ALLOYS|

US6332935B1|2000-03-24|2001-12-25|General Electric Company|Processing of titanium-alloy billet for improved ultrasonic inspectability|

US6399215B1|2000-03-28|2002-06-04|The Regents Of The University Of California|Ultrafine-grained titanium for medical implants|

JP2001343472A|2000-03-31|2001-12-14|Seiko Epson Corp|Manufacturing method for watch outer package component, watch outer package component and watch|

JP3753608B2|2000-04-17|2006-03-08|株式会社日立製作所|Sequential molding method and apparatus|

US6532786B1|2000-04-19|2003-03-18|D-J Engineering, Inc.|Numerically controlled forming method|

US6197129B1|2000-05-04|2001-03-06|The United States Of America As Represented By The United States Department Of Energy|Method for producing ultrafine-grained materials using repetitive corrugation and straightening|

JP2001348635A|2000-06-05|2001-12-18|Nikkin Material:Kk|Titanium alloy excellent in cold workability and work hardening|

US6484387B1|2000-06-07|2002-11-26|L. H. Carbide Corporation|Progressive stamping die assembly having transversely movable die station and method of manufacturing a stack of laminae therewith|

AT408889B|2000-06-30|2002-03-25|Schoeller Bleckmann Oilfield T|CORROSION-RESISTANT MATERIAL|

RU2169204C1|2000-07-19|2001-06-20|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy and method of thermal treatment of large-size semiproducts from said alloy|

RU2169782C1|2000-07-19|2001-06-27|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy and method of thermal treatment of large-size semiproducts from said alloy|

UA40862A|2000-08-15|2001-08-15|Інститут Металофізики Національної Академії Наук України|process of thermal and mechanical treatment of high-strength beta-titanium alloys|

US6877349B2|2000-08-17|2005-04-12|Industrial Origami, Llc|Method for precision bending of sheet of materials, slit sheets fabrication process|

JP2002069591A|2000-09-01|2002-03-08|Nkk Corp|High corrosion resistant stainless steel|

UA38805A|2000-10-16|2001-05-15|Інститут Металофізики Національної Академії Наук України|alloy based on titanium|

US6946039B1|2000-11-02|2005-09-20|Honeywell International Inc.|Physical vapor deposition targets, and methods of fabricating metallic materials|

JP2002146497A|2000-11-08|2002-05-22|Daido Steel Co Ltd|METHOD FOR MANUFACTURING Ni-BASED ALLOY|

US6384388B1|2000-11-17|2002-05-07|Meritor Suspension Systems Company|Method of enhancing the bending process of a stabilizer bar|

JP3742558B2|2000-12-19|2006-02-08|新日本製鐵株式会社|Unidirectionally rolled titanium plate with high ductility and small in-plane material anisotropy and method for producing the same|

EP1382695A4|2001-02-28|2004-08-11|Jfe Steel Corp|Titanium alloy bar and method for production thereof|

EP1375690B1|2001-03-26|2006-03-15|Kabushiki Kaisha Toyota Chuo Kenkyusho|High strength titanium alloy and method for production thereof|

US6539765B2|2001-03-28|2003-04-01|Gary Gates|Rotary forging and quenching apparatus and method|

US6536110B2|2001-04-17|2003-03-25|United Technologies Corporation|Integrally bladed rotor airfoil fabrication and repair techniques|

US6576068B2|2001-04-24|2003-06-10|Ati Properties, Inc.|Method of producing stainless steels having improved corrosion resistance|

JP4031992B2|2001-04-27|2008-01-09|リサーチインスティチュートオブインダストリアルサイエンスアンドテクノロジー|High manganese duplex stainless steel with excellent hot workability and method for producing the same|

RU2203974C2|2001-05-07|2003-05-10|ОАО Верхнесалдинское металлургическое производственное объединение|Titanium-based alloy|

DE10128199B4|2001-06-11|2007-07-12|Benteler Automobiltechnik Gmbh|Device for forming metal sheets|

RU2197555C1|2001-07-11|2003-01-27|Общество с ограниченной ответственностью Научно-производственное предприятие "Велес"|Method of manufacturing rod parts with heads from titanium alloys|

JP3934372B2|2001-08-15|2007-06-20|株式会社神戸製鋼所|High strength and low Young's modulus β-type Ti alloy and method for producing the same|

JP2003074566A|2001-08-31|2003-03-12|Nsk Ltd|Rolling device|

CN1159472C|2001-09-04|2004-07-28|北京航空材料研究院|Titanium alloy quasi-beta forging process|

US6663501B2|2001-12-07|2003-12-16|Charlie C. Chen|Macro-fiber process for manufacturing a face for a metal wood golf club|

CN1602369A|2001-12-14|2005-03-30|Ati资产公司|Method for processing beta titanium alloys|

JP3777130B2|2002-02-19|2006-05-24|本田技研工業株式会社|Sequential molding equipment|

FR2836640B1|2002-03-01|2004-09-10|Snecma Moteurs|THIN PRODUCTS OF TITANIUM BETA OR QUASI BETA ALLOYS MANUFACTURING BY FORGING|

JP2003285126A|2002-03-25|2003-10-07|Toyota Motor Corp|Warm plastic working method|

RU2217260C1|2002-04-04|2003-11-27|ОАО Верхнесалдинское металлургическое производственное объединение|METHOD FOR MAKING INTERMEDIATE BLANKS OF α AND α TITANIUM ALLOYS|

US6786985B2|2002-05-09|2004-09-07|Titanium Metals Corp.|Alpha-beta Ti-Ai-V-Mo-Fe alloy|

JP2003334633A|2002-05-16|2003-11-25|Daido Steel Co Ltd|Manufacturing method for stepped shaft-like article|

US7410610B2|2002-06-14|2008-08-12|General Electric Company|Method for producing a titanium metallic composition having titanium boride particles dispersed therein|

US6918974B2|2002-08-26|2005-07-19|General Electric Company|Processing of alpha-beta titanium alloy workpieces for good ultrasonic inspectability|

JP4257581B2|2002-09-20|2009-04-22|株式会社豊田中央研究所|Titanium alloy and manufacturing method thereof|

AU2003299073A1|2002-09-30|2004-04-19|Zenji Horita|Method of working metal, metal body obtained by the method and metal-containing ceramic body obtained by the method|

JP2004131761A|2002-10-08|2004-04-30|Jfe Steel Kk|Method for producing fastener material made of titanium alloy|

US6932877B2|2002-10-31|2005-08-23|General Electric Company|Quasi-isothermal forging of a nickel-base superalloy|

FI115830B|2002-11-01|2005-07-29|Metso Powdermet Oy|Process for the manufacture of multi-material components and multi-material components|

US7008491B2|2002-11-12|2006-03-07|General Electric Company|Method for fabricating an article of an alpha-beta titanium alloy by forging|

AU2003295609A1|2002-11-15|2004-06-15|University Of Utah|Integral titanium boride coatings on titanium surfaces and associated methods|

US20040099350A1|2002-11-21|2004-05-27|Mantione John V.|Titanium alloys, methods of forming the same, and articles formed therefrom|

RU2321674C2|2002-12-26|2008-04-10|Дженерал Электрик Компани|Method for producing homogenous fine-grain titanium material |

US7010950B2|2003-01-17|2006-03-14|Visteon Global Technologies, Inc.|Suspension component having localized material strengthening|

DE10303458A1|2003-01-29|2004-08-19|Amino Corp., Fujinomiya|Shaping method for thin metal sheet, involves finishing rough forming body to product shape using tool that moves three-dimensionally with mold punch as mold surface sandwiching sheet thickness while mold punch is kept under pushed state|

RU2234998C1|2003-01-30|2004-08-27|Антонов Александр Игоревич|Method for making hollow cylindrical elongated blank |

WO2004083477A1|2003-03-20|2004-09-30|Sumitomo Metal Industries, Ltd.|High-strength stainless steel, container and hardware made of such steel|

JP4209233B2|2003-03-28|2009-01-14|株式会社日立製作所|Sequential molding machine|

JP3838216B2|2003-04-25|2006-10-25|住友金属工業株式会社|Austenitic stainless steel|

US20040221929A1|2003-05-09|2004-11-11|Hebda John J.|Processing of titanium-aluminum-vanadium alloys and products made thereby|

JP4041774B2|2003-06-05|2008-01-30|住友金属工業株式会社|Method for producing β-type titanium alloy material|

US7785429B2|2003-06-10|2010-08-31|The Boeing Company|Tough, high-strength titanium alloys; methods of heat treating titanium alloys|

US7073559B2|2003-07-02|2006-07-11|Ati Properties, Inc.|Method for producing metal fibers|

DE10355670B4|2003-11-28|2005-12-08|Infineon Technologies Ag|Method for driving a switch in a power factor correction circuit and drive circuit|

AT412727B|2003-12-03|2005-06-27|Boehler Edelstahl|CORROSION RESISTANT, AUSTENITIC STEEL ALLOY|

US8128764B2|2003-12-11|2012-03-06|Miracle Daniel B|Titanium alloy microstructural refinement method and high temperature, high strain rate superplastic forming of titanium alloys|

US7038426B2|2003-12-16|2006-05-02|The Boeing Company|Method for prolonging the life of lithium ion batteries|

US20050145310A1|2003-12-24|2005-07-07|General Electric Company|Method for producing homogeneous fine grain titanium materials suitable for ultrasonic inspection|

JP2005281855A|2004-03-04|2005-10-13|Daido Steel Co Ltd|Heat-resistant austenitic stainless steel and production process thereof|

US7837812B2|2004-05-21|2010-11-23|Ati Properties, Inc.|Metastable beta-titanium alloys and methods of processing the same by direct aging|

US7449075B2|2004-06-28|2008-11-11|General Electric Company|Method for producing a beta-processed alpha-beta titanium-alloy article|

RU2269584C1|2004-07-30|2006-02-10|Открытое Акционерное Общество "Корпорация Всмпо-Ависма"|Titanium-base alloy|

US20060045789A1|2004-09-02|2006-03-02|Coastcast Corporation|High strength low cost titanium and method for making same|

US7096596B2|2004-09-21|2006-08-29|Alltrade Tools Llc|Tape measure device|

US7601232B2|2004-10-01|2009-10-13|Dynamic Flowform Corp.|α-β titanium alloy tubes and methods of flowforming the same|

US7360387B2|2005-01-31|2008-04-22|Showa Denko K.K.|Upsetting method and upsetting apparatus|

US20060243356A1|2005-02-02|2006-11-02|Yuusuke Oikawa|Austenite-type stainless steel hot-rolling steel material with excellent corrosion resistance, proof-stress, and low-temperature toughness and production method thereof|

JP5208354B2|2005-04-11|2013-06-12|新日鐵住金株式会社|Austenitic stainless steel|

RU2288967C1|2005-04-15|2006-12-10|Закрытое акционерное общество ПКФ "Проммет-спецсталь"|Corrosion-resisting alloy and article made of its|

US7984635B2|2005-04-22|2011-07-26|K.U. Leuven Research & Development|Asymmetric incremental sheet forming system|

RU2283889C1|2005-05-16|2006-09-20|ОАО "Корпорация ВСМПО-АВИСМА"|Titanium base alloy|

JP4787548B2|2005-06-07|2011-10-05|株式会社アミノ|Thin plate forming method and apparatus|

DE102005027259B4|2005-06-13|2012-09-27|Daimler Ag|Process for the production of metallic components by semi-hot forming|

KR100677465B1|2005-08-10|2007-02-07|이영화|Linear Induction Heating Coil Tool for Plate Bending|

US7531054B2|2005-08-24|2009-05-12|Ati Properties, Inc.|Nickel alloy and method including direct aging|

US8337750B2|2005-09-13|2012-12-25|Ati Properties, Inc.|Titanium alloys including increased oxygen content and exhibiting improved mechanical properties|

JP4915202B2|2005-11-03|2012-04-11|大同特殊鋼株式会社|High nitrogen austenitic stainless steel|

US7669452B2|2005-11-04|2010-03-02|Cyril Bath Company|Titanium stretch forming apparatus and method|

JP2009521660A|2005-12-21|2009-06-04|エクソンモービルリサーチアンドエンジニアリングカンパニー|Corrosion resistant material for suppressing fouling, heat transfer device having improved corrosion resistance and fouling resistance, and method for suppressing fouling|

US7611592B2|2006-02-23|2009-11-03|Ati Properties, Inc.|Methods of beta processing titanium alloys|

JP5050199B2|2006-03-30|2012-10-17|国立大学法人電気通信大学|Magnesium alloy material manufacturing method and apparatus, and magnesium alloy material|

US20090165903A1|2006-04-03|2009-07-02|Hiromi Miura|Material Having Ultrafine Grained Structure and Method of Fabricating Thereof|

KR100740715B1|2006-06-02|2007-07-18|경상대학교산학협력단|Ti-ni alloy-ni sulfide element for combined current collector-electrode|

US7879286B2|2006-06-07|2011-02-01|Miracle Daniel B|Method of producing high strength, high stiffness and high ductility titanium alloys|

JP5187713B2|2006-06-09|2013-04-24|国立大学法人電気通信大学|Metal material refinement processing method|

US20080000554A1|2006-06-23|2008-01-03|Jorgensen Forge Corporation|Austenitic paramagnetic corrosion resistant material|

WO2008017257A1|2006-08-02|2008-02-14|Hangzhou Huitong Driving Chain Co., Ltd.|A bended link plate and the method to making thereof|

US20080103543A1|2006-10-31|2008-05-01|Medtronic, Inc.|Implantable medical device with titanium alloy housing|

JP2008200730A|2007-02-21|2008-09-04|Daido Steel Co Ltd|METHOD FOR MANUFACTURING Ni-BASED HEAT-RESISTANT ALLOY|

CN101294264A|2007-04-24|2008-10-29|宝山钢铁股份有限公司|Process for manufacturing type alpha+beta titanium alloy rod bar for rotor impeller vane|

US20080300552A1|2007-06-01|2008-12-04|Cichocki Frank R|Thermal forming of refractory alloy surgical needles|

CN100567534C|2007-06-19|2009-12-09|中国科学院金属研究所|The hot-work of the high-temperature titanium alloy of a kind of high heat-intensity, high thermal stability and heat treating method|

US20090000706A1|2007-06-28|2009-01-01|General Electric Company|Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys|

DE102007039998B4|2007-08-23|2014-05-22|Benteler Defense Gmbh & Co. Kg|Armor for a vehicle|

RU2364660C1|2007-11-26|2009-08-20|Владимир Валентинович Латыш|Method of manufacturing ufg sections from titanium alloys|

JP2009138218A|2007-12-05|2009-06-25|Nissan Motor Co Ltd|Titanium alloy member and method for manufacturing titanium alloy member|

CN100547105C|2007-12-10|2009-10-07|巨龙钢管有限公司|A kind of X80 steel bend pipe and bending technique thereof|

RU2461641C2|2007-12-20|2012-09-20|ЭйТиАй ПРОПЕРТИЗ, ИНК.|Austenitic stainless steel with low content of nickel and including stabilising elements|

KR100977801B1|2007-12-26|2010-08-25|주식회사 포스코|Titanium alloy with exellent hardness and ductility and method thereof|

US8075714B2|2008-01-22|2011-12-13|Caterpillar Inc.|Localized induction heating for residual stress optimization|

RU2368695C1|2008-01-30|2009-09-27|Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" |Method of product's receiving made of high-alloy heat-resistant nickel alloy|

DE102008014559A1|2008-03-15|2009-09-17|Elringklinger Ag|Process for partially forming a sheet metal layer of a flat gasket produced from a spring steel sheet and device for carrying out this process|

JP4433230B2|2008-05-22|2010-03-17|住友金属工業株式会社|High-strength Ni-base alloy tube for nuclear power and its manufacturing method|

JP2009299110A|2008-06-11|2009-12-24|Kobe Steel Ltd|HIGH-STRENGTH alpha-beta TYPE TITANIUM ALLOY SUPERIOR IN INTERMITTENT MACHINABILITY|

JP5299610B2|2008-06-12|2013-09-25|大同特殊鋼株式会社|Method for producing Ni-Cr-Fe ternary alloy material|

RU2392348C2|2008-08-20|2010-06-20|Федеральное Государственное Унитарное Предприятие "Центральный Научно-Исследовательский Институт Конструкционных Материалов "Прометей" |Corrosion-proof high-strength non-magnetic steel and method of thermal deformation processing of such steel|

JP5315888B2|2008-09-22|2013-10-16|Ｊｆｅスチール株式会社|α-β type titanium alloy and method for melting the same|

CN101684530A|2008-09-28|2010-03-31|杭正奎|Ultra high-temperature resistant nickel-chrome alloy and manufacturing method thereof|

RU2378410C1|2008-10-01|2010-01-10|Открытое акционерное общество "Корпорация ВСПМО-АВИСМА"|Manufacturing method of plates from duplex titanium alloys|

US8408039B2|2008-10-07|2013-04-02|Northwestern University|Microforming method and apparatus|

RU2383654C1|2008-10-22|2010-03-10|Государственное образовательное учреждение высшего профессионального образования "Уфимский государственный авиационный технический университет"|Nano-structural technically pure titanium for bio-medicine and method of producing wire out of it|

US8430075B2|2008-12-16|2013-04-30|L.E. Jones Company|Superaustenitic stainless steel and method of making and use thereof|

RU2393936C1|2009-03-25|2010-07-10|Владимир Алексеевич Шундалов|Method of producing ultra-fine-grain billets from metals and alloys|

US8578748B2|2009-04-08|2013-11-12|The Boeing Company|Reducing force needed to form a shape from a sheet metal|

US8316687B2|2009-08-12|2012-11-27|The Boeing Company|Method for making a tool used to manufacture composite parts|

CN101637789B|2009-08-18|2011-06-08|西安航天博诚新材料有限公司|Resistance heat tension straightening device and straightening method thereof|

JP2011121118A|2009-11-11|2011-06-23|Univ Of Electro-Communications|Method and equipment for multidirectional forging of difficult-to-work metallic material, and metallic material|

WO2011062231A1|2009-11-19|2011-05-26|独立行政法人物質・材料研究機構|Heat-resistant superalloy|

RU2425164C1|2010-01-20|2011-07-27|Открытое Акционерное Общество "Корпорация Всмпо-Ависма"|Secondary titanium alloy and procedure for its fabrication|

US10053758B2|2010-01-22|2018-08-21|Ati Properties Llc|Production of high strength titanium|

DE102010009185A1|2010-02-24|2011-11-17|Benteler Automobiltechnik Gmbh|Sheet metal component is made of steel armor and is formed as profile component with bend, where profile component is manufactured from armored steel plate by hot forming in single-piece manner|

CN102933331B|2010-05-17|2015-08-26|麦格纳国际公司|For the method and apparatus formed the material with low ductility|

CA2706215C|2010-05-31|2017-07-04|Corrosion Service Company Limited|Method and apparatus for providing electrochemical corrosion protection|

US9255316B2|2010-07-19|2016-02-09|Ati Properties, Inc.|Processing of α+β titanium alloys|

US8499605B2|2010-07-28|2013-08-06|Ati Properties, Inc.|Hot stretch straightening of high strength α/β processed titanium|

US9206497B2|2010-09-15|2015-12-08|Ati Properties, Inc.|Methods for processing titanium alloys|

US8613818B2|2010-09-15|2013-12-24|Ati Properties, Inc.|Processing routes for titanium and titanium alloys|

US20120067100A1|2010-09-20|2012-03-22|Ati Properties, Inc.|Elevated Temperature Forming Methods for Metallic Materials|

US20120076611A1|2010-09-23|2012-03-29|Ati Properties, Inc.|High Strength Alpha/Beta Titanium Alloy Fasteners and Fastener Stock|

US10513755B2|2010-09-23|2019-12-24|Ati Properties Llc|High strength alpha/beta titanium alloy fasteners and fastener stock|

US20120076686A1|2010-09-23|2012-03-29|Ati Properties, Inc.|High strength alpha/beta titanium alloy|

RU2441089C1|2010-12-30|2012-01-27|Юрий Васильевич Кузнецов|ANTIRUST ALLOY BASED ON Fe-Cr-Ni, ARTICLE THEREFROM AND METHOD OF PRODUCING SAID ARTICLE|

JP2012140690A|2011-01-06|2012-07-26|Sanyo Special Steel Co Ltd|Method of manufacturing two-phase stainless steel excellent in toughness and corrosion resistance|

CN103492099B|2011-04-25|2015-09-09|日立金属株式会社|The manufacture method of ladder forged material|

US9732408B2|2011-04-29|2017-08-15|Aktiebolaget Skf|Heat-treatment of an alloy for a bearing component|

US8679269B2|2011-05-05|2014-03-25|General Electric Company|Method of controlling grain size in forged precipitation-strengthened alloys and components formed thereby|

CN102212716B|2011-05-06|2013-03-27|中国航空工业集团公司北京航空材料研究院|Low-cost alpha and beta-type titanium alloy|

US8652400B2|2011-06-01|2014-02-18|Ati Properties, Inc.|Thermo-mechanical processing of nickel-base alloys|

US9034247B2|2011-06-09|2015-05-19|General Electric Company|Alumina-forming cobalt-nickel base alloy and method of making an article therefrom|

ES2620310T3|2011-06-17|2017-06-28|Titanium Metals Corporation|Method for manufacturing alpha-beta alloy plates from Ti-Al-V-Mo-Fe|

US20130133793A1|2011-11-30|2013-05-30|Ati Properties, Inc.|Nickel-base alloy heat treatments, nickel-base alloys, and articles including nickel-base alloys|

US9347121B2|2011-12-20|2016-05-24|Ati Properties, Inc.|High strength, corrosion resistant austenitic alloys|

US9869003B2|2013-02-26|2018-01-16|Ati Properties Llc|Methods for processing alloys|

US9192981B2|2013-03-11|2015-11-24|Ati Properties, Inc.|Thermomechanical processing of high strength non-magnetic corrosion resistant material|

US9050647B2|2013-03-15|2015-06-09|Ati Properties, Inc.|Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys|

US9777361B2|2013-03-15|2017-10-03|Ati Properties Llc|Thermomechanical processing of alpha-beta titanium alloys|

JP6171762B2|2013-09-10|2017-08-02|大同特殊鋼株式会社|Method of forging Ni-base heat-resistant alloy|

US11111552B2|2013-11-12|2021-09-07|Ati Properties Llc|Methods for processing metal alloys|

US10094003B2|2015-01-12|2018-10-09|Ati Properties Llc|Titanium alloy|

US10502252B2|2015-11-23|2019-12-10|Ati Properties Llc|Processing of alpha-beta titanium alloys|US20040221929A1|2003-05-09|2004-11-11|Hebda John J.|Processing of titanium-aluminum-vanadium alloys and products made thereby|

US7837812B2|2004-05-21|2010-11-23|Ati Properties, Inc.|Metastable beta-titanium alloys and methods of processing the same by direct aging|

US10053758B2|2010-01-22|2018-08-21|Ati Properties Llc|Production of high strength titanium|

US9255316B2|2010-07-19|2016-02-09|Ati Properties, Inc.|Processing of α+β titanium alloys|

US8783078B2|2010-07-27|2014-07-22|Ford Global Technologies, Llc|Method to improve geometrical accuracy of an incrementally formed workpiece|

US8499605B2|2010-07-28|2013-08-06|Ati Properties, Inc.|Hot stretch straightening of high strength α/β processed titanium|

US8613818B2|2010-09-15|2013-12-24|Ati Properties, Inc.|Processing routes for titanium and titanium alloys|

US9206497B2|2010-09-15|2015-12-08|Ati Properties, Inc.|Methods for processing titanium alloys|

US20120076686A1|2010-09-23|2012-03-29|Ati Properties, Inc.|High strength alpha/beta titanium alloy|

US10513755B2|2010-09-23|2019-12-24|Ati Properties Llc|High strength alpha/beta titanium alloy fasteners and fastener stock|

US8652400B2|2011-06-01|2014-02-18|Ati Properties, Inc.|Thermo-mechanical processing of nickel-base alloys|

US20150119166A1|2012-05-09|2015-04-30|Acushnet Company|Variable thickness golf club head and method of manufacturing the same|

US9869003B2|2013-02-26|2018-01-16|Ati Properties Llc|Methods for processing alloys|

US9192981B2|2013-03-11|2015-11-24|Ati Properties, Inc.|Thermomechanical processing of high strength non-magnetic corrosion resistant material|

US9050647B2|2013-03-15|2015-06-09|Ati Properties, Inc.|Split-pass open-die forging for hard-to-forge, strain-path sensitive titanium-base and nickel-base alloys|

US9777361B2|2013-03-15|2017-10-03|Ati Properties Llc|Thermomechanical processing of alpha-beta titanium alloys|

RU2549804C1|2013-09-26|2015-04-27|Открытое Акционерное Общество "Корпорация Всмпо-Ависма"|Method to manufacture armoured sheets from -titanium alloy and items from it|

US11111552B2|2013-11-12|2021-09-07|Ati Properties Llc|Methods for processing metal alloys|

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法律状态:
2017-05-23| B25D| Requested change of name of applicant approved|Owner name: ATI PROPERTIES LLC (US) |

2018-07-10| B07A| Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]|

2019-02-05| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

2019-04-16| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 27/06/2011, OBSERVADAS AS CONDICOES LEGAIS. (CO) 20 (VINTE) ANOS CONTADOS A PARTIR DE 27/06/2011, OBSERVADAS AS CONDICOES LEGAIS |

优先权:

申请号 | 申请日 | 专利标题

US12/838.674|2010-07-19|

US12/838,674|US9255316B2|2010-07-19|2010-07-19|Processing of α+β titanium alloys|

PCT/US2011/041934|WO2012012102A1|2010-07-19|2011-06-27|Processing of alpha/beta titanium alloys|

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