巴西专利BR112012016546B1 METHODS FOR INCREASING RESISTANCE AND TENACITY OF A TITANIUM ALLOY, THERMOMECANICALLY TITANIUM ALLOY

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专利摘要:
high strength titanium production. Certain embodiments of a method for increasing the strength and toughness of a titanium alloy include plastically deforming a titanium alloy at a temperature in the alpha-beta phase field of the titanium alloy to an equivalent plastic deformation of at least a reduction of 25%. % in the area. After plastically deforming the titanium alloy in the alpha-beta phase camo, the titanium alloy is not heated to or above the titanium alloy beta transus temperature. after plastic deformation, the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beautiful transus minus 20Â ° f (11.1Â ° c).
公开号:BR112012016546B1
申请号:R112012016546-1
申请日:2010-12-29
公开日:2018-07-10
发明作者:J. Bryan David
申请人:Ati Properties Llc；
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(54) Title: METHODS FOR INCREASING THE RESISTANCE AND TENACITY OF A TITANIUM ALLOY, THERMOMECHANICALLY TREATING TITANIUM ALLOYS AND PROCESSING TITANIUM ALLOYS (51) Int.CI .: C22C 14/00; C22F 1/18 (30) Unionist Priority: 22/01/2010 US 12 / 691,952 (73) Holder (s): ATI PROPERTIES LLC (72) Inventor (s): DAVID J. BRYAN
1/25 “METHODS FOR INCREASING THE RESISTANCE AND TENACITY OF A TITANIUM ALLOY, THERMOMECHANICALLY TREATING TITANIUM ALLOYS AND PROCESSING TITANIUM ALLOYS”
Fundamentals of Technology
Technology Field [001] The present disclosure is directed to methods for the production of titanium alloys with high strength and high tenacity. The methods according to the present disclosure do not require multi-layer heat treatments used in certain methods of producing existing titanium alloys.
Description of Technology Basics [002] Titanium alloys typically exhibit a high strength to weight ratio, are resistant to corrosion, and are resistant to deformation at moderately high temperatures. For these reasons, titanium alloys are used in aerospace and aeronautical applications, including, for example, critical structural parts, such as landing gear members and engine frames. Titanium alloys are also used in jet engines for parts, such as rotors, compressor blades, hydraulic system parts and nacelles.
[003] Pure titanium undergoes an allotropic phase transformation at about 882 ° C. Below this temperature, titanium adopts a crystalline structure packaged close to the hexagonal shape, referred to as the α phase. Above this temperature, titanium has a centered body cubic structure, referred to as the β phase. The temperature at which the transformation from the α to the β phase occurs is referred to as the beta transus (Te) temperature. The beta transus temperature is affected by interstitial and substitutional elements and, therefore, is dependent on impurities and, more importantly, alloy elements.
[004] In titanium alloys, alloying elements are generally classified as stabilizing elements α or stabilizing elements β. The addition of α stabilizing elements (“α stabilizers”) to titanium increases the beta transus temperature. Aluminum, for example, is a replacement element for titanium and is a stabilizing α. The interstitial alloy elements for titanium that are α stabilizers include, for example, oxygen, nitrogen and carbon.
[005] The addition of β stabilization elements to titanium decreases the beta transus temperature. The β stabilization elements can be either isomorphic β elements or
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2/25 β eutetoid elements, depending on the resulting phase diagrams. Examples of isomorphic β alloy elements for titanium are vanadium, molybdenum and niobium. By bonding with sufficient concentrations of these isomorphic β alloy elements, it is possible to reduce the beta transus temperature to room temperature or below. Examples of β eutetoid alloy elements are chromium and iron. In addition, other elements, such as, for example, silicon, zirconium, and hafnium, are neutral in the sense that these elements have little effect on the beta transus temperature of titanium and titanium alloys.
[006] FIG. 1A represents a schematic phase diagram showing the effect of adding an α stabilizer to titanium. As the α stabilizer concentration increases, the beta transus temperature also increases, which is seen by the positive slope of the beta transus 10 temperature line. The beta 12 field is above the beta transus 10 temperature line. and it is an area of the phase diagram where only the β phase is present in the titanium alloy. In FIG. 1A, an alpha-beta phase 14 field is below the beta transus 10 temperature line and represents an area in the phase diagram, where both the α phase and the β phase (α + β) are present in the titanium alloy . Below the alpha-beta 14 field is the alpha 16 field, where only the α phase is present in the titanium alloy.
[007] FIG. 1B represents a schematic phase diagram showing the effect of adding an isomorphic β stabilizer to titanium. Higher concentrations of β stabilizers reduce the beta transus temperature, as indicated by the negative slope of the beta transus 10 temperature line. Above the beta transus 10 temperature line is the beta 12 phase field. and an alpha phase 16 field are also present in the titanium schematic phase diagram with the β isomorphic stabilizer in FIG. 1B.
[008] FIG. 1C represents a schematic phase diagram showing the effect of adding an eutetoid β stabilizer to titanium. The phase diagram shows a beta phase field 12, a beta transus temperature line 10, an alpha phase field 14, and an alpha phase field 16. In addition, there are two additional two phase fields in the phase diagram of the FIG. 1C, which contain both α and β phases together with the titanium reaction product and the alloy addition stabilization β (Z) eutetoid.
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3/25 [009] Titanium alloys are generally classified according to their chemical composition and microstructure at room temperature. Commercially pure titanium (CP) and titanium alloys that contain only α stabilizers, such as aluminum, are considered alpha alloys. These are predominantly single-phase alloys that consist essentially of the α phase. However, CP titanium and other alpha alloys, after being annealed below the beta transus temperature, generally contain about 2-5 percent by volume of β phase, which is typically stabilized by iron impurities in the alpha titanium alloy. The small volume of β phase is used in the alloy to control the grain size of the recrystallized α phase.
[0010] Titanium alloys close to alpha have a small amount of β phase, generally less than 10 percent by volume, which results in increased stress resistance at room temperature and increased resistance to deformation at use temperatures above 400 ° C, compared to alpha alloys. A titanium alloy close to exemplary alpha may contain about 1 weight percent molybdenum.
[0011] Titanium alpha / beta (α + β) alloys, such as Ti-6Al-4V alloy (Ti 6-4) and Ti6Al-2Sn-4Zr-2Mo alloy (Ti 6-2-4-2), contain both alpha and beta phases and are widely used in the aerospace and aeronautical industry. The microstructure and properties of alpha / beta alloys can be varied through heat treatments and thermomechanical processing.
[0012] Beta stable titanium alloys, metastable beta titanium alloys and near beta titanium alloys, collectively classified as “beta alloys”, contain substantially more β stabilizing elements than alpha / beta alloys. Titanium alloys close to beta, such as, for example, Ti-10V-2Fe-3AL alloy, contain sufficient amounts of β stabilization elements to maintain a β-phase structure as a whole when the water is cooled down sharply, but not when the air is suddenly cooled. Metastable beta titanium alloys, such as, for example, Ti-15Mo alloy, contain higher levels of β stabilizers and retain an all β phase structure by cooling in air, but can be aged to precipitate the α phase for resistance . Beta stable titanium alloys, such as, for example, Ti-30Mo alloy, retain an β-phase microstructure upon cooling, but cannot be aged to precipitate the α phase.
[0013] It is known that alpha / beta alloys are sensitive to cooling rates when cooled above the beta transus temperature. The precipitation of the α phase in grain boundaries
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4/25 during cooling reduces the toughness of these alloys. Currently, the production of titanium alloys with high strength and high toughness requires the use of a combination of high temperature strains, followed by a complicated multi-layer heat treatment that includes direct aging and carefully controlled heating rates. For example, US Patent Application Publication 2004/0250932 A1 discloses the formation of a titanium alloy that contains at least 5% molybdenum in a useful form at a first temperature above the beta transus temperature, or the heat treatment of a titanium alloy at a first temperature above the beta transus temperature followed by controlled cooling, at a rate of no more than 5 ° F (2.8 ° C) per minute for a second temperature below the beta transus temperature. The titanium alloy can also be heat treated at a third temperature.
[0014] A schematic graph of temperature versus time of a typical state of the art method for producing hard, high strength titanium alloys is shown in FIG. 2. The method generally includes a high temperature deformation step conducted below the beta transus temperature, and a heat treatment step, including heating above the beta transus temperature followed by controlled cooling. The state-of-the-art thermomechanical processing steps used to produce titanium alloys having both high strength and high toughness are expensive and, currently, only a limited number of manufacturers are able to perform these steps. Therefore, it would be advantageous to provide an improved process for increasing the strength and / or toughness of titanium alloys.
Summary [0015] In accordance with one aspect of the present disclosure, a non-limiting embodiment of a method for increasing the strength and toughness of a titanium alloy includes plastically deforming a titanium alloy at a temperature in the alpha phase field of the alloy of titanium for an equivalent plastic deformation of at least a 25% reduction in area. After plastically deforming the titanium alloy at a temperature in the alpha-beta phase field, the titanium alloy is not heated to a temperature equal to or above a beta transus temperature of the titanium alloy. Also according to the non-limiting modality, after plastically deforming the titanium alloy, the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beta transus temperature
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5/25 minus 20 ° F for a sufficient heat treatment time to produce a heat-treated alloy having a fracture toughness (Kic) that is related to yield strength (YS) according to the equation Kic s 173 - (0 , 9) YS. In another non-limiting modality, the titanium alloy can be heat treated after plastic deformation at a temperature in the alpha-beta phase field of the titanium alloy to an equivalent plastic deformation of at least 25% reduction in area at a temperature of heat treatment less than or equal to the beta transus temperature less than 20 ° F for a sufficient heat treatment time to produce a heat-treated alloy having a fracture toughness (Kic) that is related to yield strength (YS) according to the equation Kic s 217.6 - (0.9) YS.
[0016] In accordance with another aspect of the present disclosure, a non-limiting method for thermomechanically treating a titanium alloy includes working a titanium alloy in a working temperature range of 200 ° F (111 ^s C) above the beta temperature titanium alloy transus at 222 ° C below the beta transus temperature. In a non-limiting mode, at the completion of the work step, an equivalent plastic deformation of at least 25% reduction in area can occur in an alpha-beta phase field of the titanium alloy, and the titanium alloy is not heated above the beta transus temperature after the equivalent plastic deformation of at least 25% reduction in the alpha beta phase field area of the titanium alloy. According to a non-limiting modality, after working with the titanium alloy, the alloy can be heat treated in a heat treatment temperature range between 1500 ° F (816 ^o C) and 900 ° F (482 ^o C) for a time heat treatment of between 0.5 and 24 hours. The titanium alloy can be heat treated in a heat treatment temperature range between 1500 ° F (816 ^o C) and 900 ° F (482 ^o C) for a sufficient heat treatment time to produce a heat treated alloy having a toughness fracture (Kic) that is related to the yield strength (YS) of the heat-treated alloy according to the equation Kic s 173 - (0.9) YS or, in another non-limiting modality, according to the equation Kic s 217.6 - (0.9) YS.
[0017] According to yet another aspect of the present disclosure, a non-limiting embodiment of a method for processing titanium alloys comprises working a titanium alloy in an alpha beta field of the titanium alloy to provide an equivalent plastic deformation of at least a 25% reduction in area of the alloy of
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6/25 titanium. In a non-limiting modality of the method, the titanium alloy is able to retain the beta phase at room temperature. In a non-limiting modality, after working with the titanium alloy, the titanium alloy can be heat treated at a heat treatment temperature not higher than the beta transus temperature minus 20 ° F for a sufficient heat treatment time to supply the titanium alloy with an average final tensile strength of at least 150 ksi and a Kic fracture toughness of at least 70 ksi · in ^1/2 . In a non-limiting mode, the heat treatment time is in the range of 0.5 hour to 24 hours.
[0018] However, an additional aspect of the present disclosure is directed to a titanium alloy that has been processed according to a method encompassed by the present disclosure. A non-limiting modality is directed to a Ti-5Al-5V-5Mo-3CR alloy that has been processed by a method according to the present disclosure, including the steps of plastically deforming and heat treating the titanium alloy, and in which the heat-treated alloy has a fracture toughness (Kic) that is related to the yield strength (YS) of the heat-treated alloy according to the Kic equation s 217.6 - (0.9) YS. As is known in the art, Ti-5Al-5V-5Mo-3Cr alloy, which is also known as Ti-5553 alloy or Ti 5-5-5-3 alloy, nominally includes 5 weight percent aluminum, 5 percent percent by weight of vanadium, 5 percent by weight of molybdenum, 3 percent by weight of chromium and balance of titanium and accidental impurities. In a non-limiting embodiment, the titanium alloy is plastically deformed at a temperature in the alpha beta phase field of the titanium alloy to an equivalent plastic deformation of at least a 25% reduction in area. After plastically deforming the titanium alloy at a temperature in the alpha beta phase field, the titanium alloy is not heated to a temperature equal to or above a transus beta temperature of the titanium alloy. In addition, in a non-limiting modality, the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beta transus temperature minus 20 ° F (11.1 ° C) for a sufficient heat treatment time to produce a heat-treated alloy with a fracture toughness (Kic) that is related to the yield strength (YS) of the heat-treated alloy according to the Kic equation> 217.6 - (0.9) YS.
[0019] Yet another aspect according to the present disclosure is directed to an article adapted for use in at least one of an aeronautical application and an application
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Aerospace 7/25 and consisting of a Ti-5Al-5V-5Mo-3Cr alloy that has been processed by a method including plastically deforming and thermally treating the titanium alloy in a manner sufficient to have a fracture toughness (KIc) of the alloy heat treated is related to a yield strength (YS) of the heat treated alloy according to the equation Kic s 217.6 - (0.9) YS. In a non-limiting embodiment, the titanium alloy can be plastically deformed at a temperature in the alpha beta phase field of the titanium alloy to an equivalent plastic deformation of at least a 25% reduction in area. After plastically deforming the titanium alloy at a temperature in the alpha beta phase field, the titanium alloy is not heated to a temperature equal to or above a beta transus temperature of the titanium alloy. In a non-limiting modality, the titanium alloy can be heat treated at a heat treatment temperature less than or equal to (that is, not greater than) the beta transus temperature minus 20 ° F (11.1 ° C) for a sufficient heat treatment time to produce a heat-treated alloy having a fracture toughness (Kic) that is related to the yield strength (YS) of the heat-treated alloy according to the Kic equation> 217.6 - (0.9) YS.
Brief Description of the Drawings [0020] The characteristics and advantages of the methods described here can be better understood by reference to the accompanying drawings in which:
[0021] FIG. 1A is an example of a phase diagram for titanium alloy with an alpha stabilizing element;
[0022] FiG. 1B is an example of a phase diagram for titanium alloy with an isomorphic beta stabilizing element;
[0023] FiG. 1C is an example of a phase diagram for titanium alloy with a beta eutetoid stabilizing element;
[0024] FIG. 2 is a schematic representation of a state of the art thermomechanical processing scheme for the production of high-strength, hard titanium alloys;
[0025] FIG. 3 is a time-temperature diagram of a non-limiting embodiment of a method according to the present disclosure comprising substantially all of the alpha-beta phase plastic deformation;
[0026] FIG. 4 is a time-temperature diagram of another non-limiPetition 870170102430, from 12/27/2017, p. 20/50
8/25 of a method according to the present disclosure comprising plastic deformation “through beta transus”;
[0027] FIG. 5 is a graph of Kic fracture toughness versus yield strength for various heat-treated titanium alloys according to prior art processes;
[0028] FIG. 6 is a graph of Kic fracture toughness versus yield strength for titanium alloys that have been plastically deformed and heat treated according to non-limiting modalities of a method according to the present disclosure and comparison of these modalities with heat treated alloys according to state of the art processes;
[0029] FIG. 7A is a micrograph of a Ti 5-5-5-3 alloy in the longitudinal direction after rolling and heat treatment at 1250 ° F (677 ° C) for 4 hours, and [0030] FIG. 7B is a micrograph of a Ti 5-5-5-3 alloy in the transverse direction after rolling and heat treatment at 1250 ° F (677 ° C) for 4 hours.
[0031] The reader will appreciate the preceding details, as well as others, when considering the following detailed description of certain non-limiting modalities of methods in accordance with the present disclosure.
Detailed Description of Certain Non-limiting Modalities [0032] In this description of non-limiting modalities, except in the examples of operation or where otherwise indicated, all numbers expressing quantities or characteristics must be understood as being modified in all cases by the term “ about". Therefore, unless otherwise indicated, any numerical parameters contained in the description that follows are approximations that may vary depending on the desired properties that are sought in the methods for producing high strength, high tenacity titanium alloys according to present disclosure. 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 must at least be interpreted in terms of the number of significant figures reported and by the application of common rounding techniques.
[0033] Any patent, publication, or other disclosure material that is said to be incorporated, in whole or in part, by reference here is incorporated here only to the extent
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9/25 where the incorporated material does not conflict with existing definitions, statements, or other disclosure material set out in this disclosure. As such, and to the extent necessary, the disclosure as set forth 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 there is no conflict between the material and the existing disclosure material.
[0034] Certain non-limiting modalities in accordance with the present disclosure are directed to thermomechanical methods for the production of high-strength and hard titanium alloys that do not require the use of complicated, multi-layer heat treatments. Surprisingly, and in contrast to the complex thermomechanical processes presently and historically used with titanium alloys, certain non-limiting modalities of the thermomechanical methods disclosed here include only a high temperature deformation step followed by a one-step heat treatment to give titanium combinations of stress resistance, ductility and fracture toughness, required in certain aerospace and aeronautical materials. It is envisaged that the modalities of thermomechanical processing within the present disclosure can be conducted in any facility that is reasonably well equipped to perform the thermomechanical heat treatment of titanium. The modalities contrast with conventional heat treatment practices to provide high toughness and high strength for titanium alloys, practices that commonly require sophisticated equipment to closely control the alloy's cooling rates.
[0035] With reference to the schematic graph of temperature versus time of FIG. 3, a non-limiting method 20 according to the present disclosure for increasing the strength and toughness of a titanium alloy comprises plastically deforming a titanium alloy 22 at a temperature in the alpha-beta phase field of the titanium alloy to a deformation plastic equivalent of at least a 25% reduction in area. (See FIGS. 1A-1C and the above discussion regarding the alpha-beta phase field of a titanium alloy.) The equivalent 25% plastic strain in the alpha-beta field involves a final plastic strain temperature 24 at alpha-beta phase field. The term “temperaPetição 870170102430, of 12/27/2017, p. 22/50
10/25 final plastic deformation texture ”is defined here as the temperature of the titanium alloy at the completion of the plastic shape deformation of the titanium alloy and before the aging of the titanium alloy. As will be shown in FIG. 3, subsequent to plastic deformation 22, the titanium alloy is not heated above the beta transus temperature (Tp) of the titanium alloy during method 20. In certain non-limiting embodiments and as shown in FIG. 3 subsequent to plastic deformation at the final plastic deformation temperature 24, the titanium alloy is heat treated 26 at a temperature below the beta transus temperature for a time sufficient to provide high fracture strength and high toughness for the titanium alloy. In a non-limiting embodiment, heat treatment 26 can be conducted at a temperature of at least 20 ° F below the beta transus temperature. In another non-limiting embodiment, heat treatment 26 can be conducted at a temperature of at least 50 ° F below the beta transus temperature. In certain non-limiting embodiments, the heat treatment temperature 26 may be below the final plastic deformation temperature 24. In other non-limiting embodiments, not shown in FIG. 3, in order to further increase the fracture toughness of the titanium alloy, the temperature of the heat treatment may be higher than the final plastic deformation temperature, but lower than the beta transus temperature. It will be understood that, although FIG. 3 shows a constant temperature for the plastic deformation 22 and the heat treatment 26, in other non-limiting embodiments of a method according to the present disclosure the temperature of the plastic deformation 22 and / or heat treatment 26 can vary. For example, a natural decrease in the temperature of the titanium alloy workpiece that occurs during plastic deformation is within the scope of the modalities disclosed here. The schematic temperature-time graph of FIG. 3 illustrates that certain modalities of heat treatment methods for titanium alloys that confer high strength and high toughness disclosed here contrast with conventional heat treatment practices that provide high strength and high toughness for titanium alloys. For example, conventional heat treatment practices typically require multi-layer heat treatments and sophisticated equipment to closely control alloy cooling rates and are therefore expensive and cannot be practiced in all heat treatment facilities. The process modalities illustrated by FIG. 3, however, do not involve multiple heat treatment steps and can be conducted using heat treatment equipment
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Conventional 11/25.
[0036] Generally, the specific titanium alloy composition determines the combination of heat treatment time (s) and heat treatment temperature (s) that will impart the desired mechanical properties using methods in accordance with the present disclosure. In addition, heat treatment times and temperatures can be adjusted to achieve a specific desired balance of fracture toughness and strength by a particular alloy composition. In certain non-limiting modalities disclosed herein, for example, by adjusting the heat treatment times and temperatures used to process a Ti-5Al-5V-5Mo-3Cr (Ti 5-5-5-3) alloy by a method of According to the present disclosure, the final tensile strengths from 140 ksi to 180 ksi combined with fracture toughness levels from 60 ksi »in ^1/2 Kic to 100 ksi • in ^1/2 KIc have been achieved. When considering the present disclosure, those skilled in the art can, without undue effort, determine the particular combination (s) of heat treatment time and temperature that will confer the optimum strength and toughness properties for a particular titanium alloy for your intended application.
[0037] The term "plastic deformation" is used here to mean the inelastic distortion of a material through stress or applied stresses that stretch the material beyond its elastic limit.
[0038] The term "reduction in area" is used here to mean the difference between the cross-sectional area of a titanium alloy shape before plastic deformation and the cross-sectional area of the titanium alloy shape after plastic deformation , in which the cross section is taken at an equivalent location. The titanium alloy form used in the evaluation of the reduction in area can be, but is not limited to, any of an ingot, a bar, a plate, a rod, a coil, a sheet, a laminated form, and an extruded form .
[0039] An example of a reduction in the calculation of the area to plastically deform a 5-inch-diameter round titanium alloy ingot by rolling the ingot to a 2.5-inch round titanium alloy bar follows. The cross-sectional area of a 5-inch diameter round ingot is π (pi) times the square of the radius, or approximately (3.1415) x (2.5 inches) ² , or 19.625 in ² . The cross-sectional area of a 2.5-inch round bar is approximately (3.1415) x (1.25) ² , or 4.91 in ² .
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12/25
The ratio of the cross-sectional area of the starting ingot to the bar after rolling is 4.91 / 19.625, or 25%. The reduction in area is 100% - 25%, for a reduction of 75% in area.
[0040] The term "equivalent plastic deformation" is used here to mean the inelastic distortion of a material through applied stresses that stretch the material beyond its elastic limit. The equivalent plastic deformation may involve stresses that would result in the specified reduction in the area obtained with the uniaxial deformation, but it occurs in such a way that the dimensions of the alloy that form after the deformation are not substantially different from the dimensions of the alloy that form before the deformation. . For example, and without limitation, multi-axis forging can be used to subject a flat forged titanium alloy ingot to substantial plastic deformation, introducing shifts in the alloy, but without substantially changing the final dimensions of the ingot. In a non-limiting modality, in which the plastic deformation is equivalent to at least 25%, the real reduction in the area can be 5% or less. In a non-limiting modality, in which the equivalent plastic deformation is at least 25%, the real reduction in the area can be 1% or less. Multi-axis forging is a technique known to a person skilled in the art and is therefore not further described here.
[0041] In certain non-limiting modalities in accordance with the present disclosure, a titanium alloy can be plastically deformed to an equivalent plastic deformation of more than a 25% reduction in area and even a 99% reduction in area. In certain non-limiting modalities where the equivalent plastic strain is greater than a 25% reduction in area, at least one plastic strain equivalent to a 25% reduction in area in the alpha-beta field occurs at the end of the plastic strain, and the titanium alloy is not heated above the beta transus (Tp) temperature of the titanium alloy after plastic deformation.
[0042] In a non-limiting embodiment of a method according to the present disclosure, and as generally shown in FIG. 3, the plastic deformation of the titanium alloy comprises plastically deforming the titanium alloy so that all equivalent plastic deformation occurs in the alpha-beta phase field. Although FIG. 3 represents a constant plastic strain temperature in the alpha-beta phase field, it is also within the scope of the modalities of this invention that the equivalent plastic strain
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13/25 at least 25% percent reduction in area in the alpha-beta phase field occurs at varying temperatures. For example, the titanium alloy can be worked in the alpha-beta field, while the temperature of the alloy gradually decreases. It is also within the scope of the modalities here, to heat the titanium alloy during the equivalent plastic deformation of at least a 25% percent reduction in the area in the alpha-beta phase field in order to maintain a constant or almost constant temperature or to limit reduction in the temperature of the titanium alloy, provided that the titanium alloy is not heated to, or above, the beta transus temperature of the titanium alloy. In a non-limiting embodiment, plastically deforming the titanium alloy in the alpha-beta phase region comprises plastically deforming the alloy in a plastic deformation temperature range of just below the beta transus temperature, or about 18 ° F (10 ° C) ) below the beta transus temperature to 222 ° C below the beta transus temperature. In another non-limiting modality, plastically deforming the titanium alloy in the alpha-beta phase region comprises plastically deforming the alloy in a plastic deformation temperature range of 222 ° C below the transus beta temperature to 20 ° F (11.1 ° C) below the beta transus temperature. In yet another non-limiting modality, plastically deforming the titanium alloy in the region of the alphabetical phase comprises plastically deforming the metal alloy in a plastic deformation temperature range of 50 ° F (27.8 ° C) below the transus beta temperature at 222 ° C below the beta transus temperature.
[0043] With reference to the schematic graph of temperature versus time of FIG. 4, another non-limiting method 30 in accordance with the present disclosure includes a feature referred to here as processing “through beta transus In non-limiting modalities that include processing through beta transus, plastic deformation (also referred to here as“ work ”) starts with the temperature of the titanium alloy in, or above, the beta transus temperature (Τβ) of the titanium alloy. In addition, in processing through beta transus, plastic deformation 32 includes plastically deforming the titanium alloy from a temperature 34 which is at, or above, the beta transus temperature to a final plastic deformation temperature 24, which is at alpha-beta phase field of titanium alloy. Thus, the temperature of the titanium alloy passes “through” the beta transus temperature during plastic deformation 32. In addition, in processing through beta transus, the plastic deformation equivalent to at least a 25% reduction in area
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14/25 occurs in the alpha-beta phase field, and the titanium alloy is not heated to a temperature at, or above, the beta transus (Tp) temperature of the titanium alloy after plastically deforming the titanium alloy in the phase field alpha-beta. The schematic graph of temperature versus time in FIG. 4 illustrates that non-limiting modalities of heat treatment methods for titanium alloys to impart high strength and high toughness disclosed here contrast with conventional heat treatment practices to provide high strength and high toughness for titanium alloys. For example, conventional heat treatment practices typically require multi-layer heat treatments and sophisticated equipment to closely control alloy cooling rates and are therefore expensive and cannot be practiced in all heat treatment facilities. The modalities of the process illustrated by FIG. 4, however, do not involve multistage heat treatment and can be conducted using conventional heat treatment equipment.
[0044] In certain non-limiting modalities of a method according to the present disclosure, plastically deforming the titanium alloy in a process through beta transus comprises plastically deforming the titanium alloy in a temperature range of 200 ° F (111 ° C) above the beta transus temperature of the titanium alloy to 222 ° C below the beta transus temperature, passing through the beta transus temperature during plastic deformation. The inventor determined that this temperature range is effective as long as (i) a plastic deformation equivalent to at least a 25% reduction in area occurs in the alpha-beta phase field and (ii) the titanium alloy is not heated to a temperature at, or above, the beta transus temperature after plastic deformation in the alpha-beta phase field.
[0045] In embodiments in accordance with this disclosure, the titanium alloy can be plastically deformed by techniques including, but not limited to, forging, rotary forging, percussion forging, multi-axis forging, bar bearing, plate bearing, and extrusion or by combinations of two or more of these techniques. Plastic deformation can be performed by any suitable grinding processing technique known now or subsequently by a person skilled in the art, as long as the processing technique used is capable of plastically deforming the titanium alloy workpiece in the phase region alpha-beta by at least one equivalent of a 25% reduction in area.
[0046] As indicated above, in certain non-limiting modalities of a method
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15/25 according to the present disclosure, the plastic deformation of the titanium alloy to at least one equivalent of a 25% reduction in the area that occurs in the region of the alphabetical phase does not substantially alter the final dimensions of the titanium alloy. This can be achieved by a technique such as, for example, multi-axis forging. In other embodiments, the plastic deformation comprises a real reduction in the area of a cross section of the titanium alloy upon completion of the plastic deformation. A person skilled in the art recognizes that the reduction in the area of a titanium alloy resulting from plastic deformation at least equivalent to a reduction in the area of 25% could result, for example, in the actual alteration of the referred cross-sectional area of the titanium alloy , that is, a real reduction in the area, anywhere from as little as 0% or 1%, and up to 25%. In addition, since total plastic deformation can comprise plastic deformation equivalent to a reduction in area of up to 99%, the actual dimensions of the workpiece after plastic deformation equivalent to a reduction in area of up to 99% can produce a actual change in the referred cross-sectional area of the titanium alloy anywhere from as little as 0% or 1%, and up to 99%.
[0047] A non-limiting embodiment of a method according to the present disclosure comprises cooling the titanium alloy to room temperature after plastically deforming the titanium alloy and before heat treating the titanium alloy. Cooling can be achieved by cooling the oven, cooling the air, cooling water, or any other suitable cooling technique known now or thereafter by a person skilled in the art.
[0048] An aspect of the present disclosure is such that, after hot work of the titanium alloy according to the modalities disclosed here, the titanium alloy is not heated to, or above, the beta transus temperature. Therefore, the heat treatment step does not occur at, or above, the beta transus temperature of the alloy. In certain non-limiting modalities, heat treatment involves heating the titanium alloy to a temperature (“heat treatment temperature”) in the range of 900 ° F (482 ° C) to 1500 ° F (816 ° C) for a period of time (“Heat treatment time”) in the range of 0.5 hour to 24 hours. In other non-limiting modalities, in order to increase fracture toughness, the heat treatment temperature may be higher than the final plastic deformation temperature, but lower than the beta transus temperature of the alloy. In another non-limiting modality, the treatment temperaturePetition 870170102430, of 12/27/2017, p. 28/50
16/25 thermal (Th) is less than or equal to the beta transus temperature minus 20 ° F (11.1 ° C), that is, Th s (Tp - 20 ° F). In another non-limiting mode, the heat treatment temperature (Th) is less than or equal to the beta transus temperature minus 50 ° F (27.8 ° C), that is, Th s (Τβ - 50 ° F). In still other non-limiting embodiments, a heat treatment temperature can be in a range of at least 900 ° F (482 ° C) at the beta transus temperature minus 20 ° F (11.1 ° C), or in a hair range minus 900 ° F (482 ° C) at beta transus temperature minus 50 ° F (27.8 ° C). It is understood that the heat treatment times can be more than 24 hours, for example, when the thickness of the part requires long heating times.
[0049] Another non-limiting embodiment of a method according to the present disclosure comprises direct aging after plastically deforming the titanium alloy, in which the titanium alloy is cooled or heated directly to the heat treatment temperature after plastically deforming the alloy titanium in the alpha-beta phase field. It is believed that, in certain modalities, not limiting the present method in which the titanium alloy is cooled directly to the heat treatment temperature after plastic deformation, the cooling rate will not significantly negatively affect the strength and toughness properties achieved by the heat treatment step. In non-limiting modalities of the present method in which the titanium alloy is heat treated at a heat treatment temperature above the final plastic deformation temperature, but below the beta transus temperature, the titanium alloy can be directly heated to the heat treatment temperature after plastically deforming the titanium alloy in the alpha-beta phase field.
[0050] Certain non-limiting modalities of a thermomechanical method according to the present disclosure include the application of the process for a titanium alloy that is capable of retaining β phase at room temperature. As such, titanium alloys that can be advantageously processed by various modalities of the methods according to the present disclosure include beta titanium alloys, metastable beta titanium alloys, close beta beta titanium alloys, alpha beta beta titanium alloys and titanium near alpha. It is contemplated that the methods disclosed here can also increase the strength and toughness of alpha titanium alloys, because, as discussed above, even the CP titanium grades include small concentrations of β phase at room temperature.
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17/25 [0051] In other non-limiting modalities of methods according to the present disclosure, the methods can be used to process titanium alloys that are capable of retaining the β phase at room temperature, and that are capable of retaining or precipitate the α phase after aging. These alloys include, but are not limited to, general categories of beta titanium alloys, alpha-beta titanium alloys and alpha alloys comprising small percentages of β phase volume.
[0052] Non-limiting examples of titanium alloys that can be processed using the methods of the methods according to the present disclosure include: titanium alpha / beta alloys, such as, for example, the Ti-6Al-4V alloy (UNS numbers R56400 and R54601) and Ti-6Al-2Sn-4Zr-2Mo alloy (UNS numbers R54620 and R54621); titanium alloys close to beta, such as, for example, Ti-10V-2Fe-3Al (UNS R54610)); metastable beta titanium alloys, such as, for example, Ti-15Mo alloy (UNS R58150) and Ti-5Al-5V5Mo-3Cr alloy (UNS not assigned).
[0053] After the heat treatment of a titanium alloy in accordance with certain non-limiting modalities disclosed here, the titanium alloy can have a final stress resistance in the range of 138 ksi and 179 ksi. The final tensile strength properties discussed in this document can be measured according to the ASTM E804 specification “Standard Test Methods for Tension Testing of Matallic Materials”. In addition, after heat treatment of a titanium alloy in accordance with certain non-limiting methods in accordance with the present disclosure, the titanium alloy may have a Kic fracture toughness in the range of 59 Ksi • in ^1/2 a 100 ksi • in ^1/2 . The Kic fracture toughness values discussed here can be measured in accordance with the ASTM E399 - 08 specification, “Standard Test Method for Linear-Elastic Flat-Stretched K ic Fracture Tenacity in Metal Materials”. In addition, after the heat treatment of a titanium alloy in accordance with certain non-limiting modalities in the scope of the present disclosure, the titanium alloy may have a flow resistance in the range of 134 ksi and 170 ksi. In addition, after heat treatment of a titanium alloy in accordance with certain non-limiting modalities in the scope of this disclosure, the titanium alloy may have a percentage elongation in the range of 4.4% to 20.5%.
[0054] In general, advantageous bands of resistance and tenacity to fracture by titanium alloys that can be achieved by practicing the method modalities according to
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18/25 the present disclosure includes, but is not limited to, a final stress resistance of 140 ksi to 180 ksi with fracture toughness ranging from about 40 ksi • in ^1/2 Kic to 100 ksi • in ^1/2 Kic , or resistance to the final tension of 140 ksi to 160 Ksi with fracture toughness ranging from 60 ksi · in ^1/2 Kic to 80 ksi · in ^1/2 Kic. In yet other non-limiting modalities, the advantageous ranges of strength and fracture toughness include resistance to the final stress of 160 ksi to 180 ksi with fracture toughness ranging from 40 ksi · in ^1/2 Kic to 60 ksi · in ^1/2 Kic . Other advantageous ranges of fracture toughness and strength that can be achieved through practice certain modalities of methods in accordance with the present disclosure include, but are not limited to: final tensile strength from 135 ksi to 180 ksi with varying fracture toughness from 55 ksi · in ^1/2 Kic to 100 ksi · in ^1/2 Kc final tensile strengths ranging from 160 ksi to 180 ksi with fracture toughness ranging from 60 ksi · in ^1/2 Kic to 90 ksi · in ^{1 / 2} Kc and final tensile strengths ranging from 135 ksi to 160 ksi with fracture toughness values ranging from 85 ksi · in ^1/2 Kic to 95 ksi · in ^1/2 Kic.
[0055] In a non-limiting modality of a method according to the present disclosure, after heat treatment of the titanium alloy, the alloy has a final average stress resistance of at least 166 ksi, an average flow resistance of at least 148 ksi, a percentage elongation of at least 6%, and a Kic fracture toughness of at least 65 ksi · in ^1/2 . Other non-limiting modalities of methods according to the present disclosure provide a heat-treated titanium alloy having a tensile strength of at least 150 ksi and a Kic fracture toughness of at least 70 ksi · in ^1/2 . Still other non-limiting modalities of methods according to the present disclosure provide a heat-treated titanium alloy having a tensile strength of at least 135 ksi and a fracture toughness of at least 55 ksi · in ^1/2 .
[0056] A non-limiting method according to the present disclosure for thermomechanically treating a titanium alloy comprises working (i.e., plastically deforming) a titanium alloy in a temperature range of 200 ° F (111 ° C) above a beta transus temperature of the titanium alloy to 222 ° C below the beta transus temperature. During the final portion of the work step, an equivalent plastic deformation of at least a 25% reduction in area occurs in an alpha-beta phase field of the titanium alloy. After the work step, the titanium alloy is not heated above the beta transus temperature. In non-limiting modalities, after the work step the titanium alloy can be
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19/25 heat treated at a heat treatment temperature ranging from 900 ° F (482 ° C) to 1500 ° F (816 ° C) for a heat treatment time ranging from 0.5 to 24 hours.
[0057] In certain non-limiting modalities in accordance with this disclosure, the work of the titanium alloy provides an equivalent plastic deformation greater than a reduction of 25% in area and even a reduction of 99% in area, in which a plastic deformation equivalent of at least 25% occurs in the alpha-beta phase region of the titanium alloy of the working step and the titanium alloy is not heated above the beta transus temperature after plastic deformation. A non-limiting modality involves working the titanium alloy in the alpha-beta phase field. In other non-limiting modalities, the work comprises working the titanium alloy at a temperature equal to or above the beta transus temperature until a final working temperature in the alpha-beta field, where the work comprises a plastic deformation equivalent to a reduction of 25 % in the area in the alpha-beta phase field of the titanium alloy and the titanium alloy is not heated above the beta transus temperature after plastic deformation.
[0058] In order to determine the thermomechanical properties of titanium alloys that are useful for certain aerospace and aeronautical applications, mechanical test data from titanium alloys that have been processed according to state of the art practices in ATI Allvac and data collected from the technical literature were collected. As used here, an alloy has mechanical properties that are "useful" for a particular application, if the alloy's toughness and strength are at least as high or within a range that is required for the application. The mechanical properties for the following alloys that are useful for certain aerospace and aeronautical applications have been collected: Ti-10V-2Fe3-Al (Ti 10-2-3; UNS R54610), Ti-5Al-5V-5Mo-3Cr (Ti 5 -5-5-3; UNS not assigned), Ti6Al-2Sn-4Zr-2Mo alloy (Ti 6-2-4-2; UNS numbers R54620 and R54621), Ti-6Al-4V (Ti 6-4; UNS numbers R56400 and R54601), Ti-6Al-2Sn-4Zr-6Mo (Ti 6-2-4-6; UNS R56260), Ti-6Al-2Sn-2Zr2Cr-2Mo-0.25Si (Ti 6-22-22; AMS 4898), and Ti-3Al-8V-6Cr-4Zr-4Mo (Ti 3-8-6-4-4; AMS 4939, 4957, 4958). The composition of each of these alloys is reported in the literature and is well known. Typical chemical composition ranges, in percentage by weight, of exemplary non-limiting titanium alloys that are amenable to the methods described here are shown in Table 1. It is understood that the alloys shown in Table 1 are only examples
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20/25 non-limiting alloys that may have increased strength and toughness when processed according to the modalities described here, and that other titanium alloys, recognized by a qualified practitioner now or hereafter, are also within the scope of the modalities here disclosed.
Table 1 (% by weight) Ti 10-2-3 Ti-5-5-3 Ti 6-2-42 Ti 6-4 Ti 6-2-46 Ti 6-2222 Ti 3-8-64-4 Ti-15MO Al 2.6-3.4 4.0-6.3 5.5-6.5 5.5-6.75 5.5-6.5 5.5-6.5 3.0-4.0 V 9.0-11.0 4.5-5.9 3.5-4.5 7.5-8.5 Mo4.5-5.9 1.80-2.20 5.50-6.50 1.5-2.5 3.5-4.5 14.00-16.00 Cr 2.0-3.6 1.5-2.5 5.5-6.5 Cr +Mo 4.0-5.0 Zr 0.01-0.08 3.60-4.40 3.50-4.50 1.5-2.5 3.5-4.5 Sn 1.80-2.20 1.75-2.25 1.5-2.5 Si 0.2-0.3 Ç 0.05max 0.01-0.25 0.05max 0.1 max 0.04max 0.05max 0.05max 0.10max N 0.05max 0.05max 0.05max 0.04max 0.04max 0.05max O 0.13max 0.03-0.25 0.15max 0.20max 0.15max 0.14max 0.14 H 0.015max 0.0125max 0.015max 0.0125max 0.01max 0.020max 0.015max Faith 1.6-2.2 0.2-0.8 0.25max 0.40max 0.15max 0.3 max 0.1 max You rem rem rem rem rem rem rem rem
[0059] The useful combinations of fracture toughness and yield strength exhibited by the above-mentioned alloys when processed using the procedurally complex and costly thermomechanical processes of the art are shown graphically in FIG. 5. It is seen in FIG. 5, that a lower limit of the graph region, including useful combinations of fracture toughness and yield strength, can be approximated by the line y = -0.9x + 173, where “y” is fracture toughness Kic in ksi units
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21/25 • in ^1/2 and “x” is the yield strength (YS) in ksi units. The data presented in Examples 1 and 3 (see also FIG. 6) presented here below demonstrate that the modalities of a method of processing titanium alloys according to the present disclosure, including plastically deforming and heat treating the alloys as described herein, result in combinations of Kic fracture toughness and yield strength that are comparable to those obtained using process processing techniques that are procedurally complex and relatively expensive. In other words, with reference to FIG. 5, based on the results obtained by carrying out certain modalities of a method in accordance with the present disclosure, a titanium alloy exhibiting fracture toughness and flow resistance according to Equation (1) can be obtained.
Kic> - (0.9) YS + 173 (1) [0060] It is still seen in FIG. 5, that an upper limit of the graph region including useful combinations of fracture toughness and yield strength can be approximated by the line y = -0.9x + 217.6, where “y” is the Kic fracture toughness in units of ksi · in ^1/2 and “x” is the yield strength (YS) in units of ksi. Therefore, based on the results obtained by carrying out modalities of a method in accordance with the present disclosure, the present method can be used to produce a titanium alloy exhibiting fracture toughness and flow resistance within the limited region in FIG. 5, which can be described according to equation (2).
217.6 - (0.9) YS> Kic> 173 - (0.9) YS (2) [0061] In accordance with a non-limiting aspect of the present disclosure, modalities of the method according to the present disclosure, including steps plastic deformation and heat treatment results in titanium alloys with yield strength and fracture toughness that are at least comparable to the same alloys if transformed using relatively expensive and procedurally complex thermomechanical techniques.
[0062] Furthermore, as shown by the data presented in Example 1 and Tables 1 and 2 hereinafter, processing of the titanium alloy Ti-5Al-5V-5Mo-3Cr by a method according to the present disclosure resulted in a titanium alloy showing mechanical properties superior to those obtained by processing the state of the thermomechanical technique. See FIG. 6. In other words, with reference to the limited region shown in
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22/25
FIGS. 5 and 6 including the combinations of yield strength and fracture toughness achieved by state-of-the-art thermomechanical processing, certain embodiments of a method in accordance with the present disclosure produce titanium alloys in which fracture toughness and yield strength are related according to equation (3).
Kic> 217.6 - (0.9) YS (3) [0063] The examples that follow are intended to describe additional non-limiting modalities, without restricting the scope of the present invention. Those skilled in the art will appreciate that variations of the Examples are possible within the scope of the invention, which is defined only by the claims.
Example 1 [0064] A 5-inch round ingot of Ti-5Al-5V-5Mo-3Cr (Ti 5-5-5-3) alloy, from ATI Allvac, Monroe, North Carolina, was laminated to a 2-bar , 5 inches at an initial temperature of about 1450 ° F (787.8 ° C), in the alpha-beta phase field. The beta transus temperature of the Ti 5-5-5-3 alloy was about 1530 ° F (832 ° C). The Ti 5-5-5-3 alloy had an average ingot chemistry of 5.02 percent by weight of aluminum, 4.87 percent by weight of vanadium, 0.41 percent by weight of iron, 4.90 weight percent molybdenum, 2.85 weight percent chromium, 0.12 weight percent oxygen, 0.09 weight percent zirconium, 0.03 weight percent silicon, remaining titanium and accidental impurities. The final working temperature was 1480 ° F (804.4 ° C), also in the alpha-beta phase field and not less than 222 ° C below the beta transus temperature of the alloy. The reduction in the alloy diameter corresponded to a 75% reduction in the area of the alloy in the alpha-beta phase field. After rolling, the alloy was cooled in air to room temperature. The samples of the cooled alloy were heat treated at various heat treatment temperatures for various heat treatment times. The mechanical properties of the heat-treated alloy samples were measured in the longitudinal (L) and transverse (T) directions. The heat treatment times and heat treatment temperatures used for the various test samples, and the fracture toughness (Kic) and stress test results for the samples in the longitudinal direction are shown in Table 2.
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Table 2 - Longitudinal Properties and Heat Treatment Conditions At the. TemperatureTreatmentthermal (° F / ° C) Time toTreatmentThermal(hours) Resistance toFinal tension (ksi) Resistance toflow(ksi) Percent ofStretching Kic (ksi-in ^1/2 ) 1 1200/649 2 178.7 170.15 11.5 65.55 2 1200/649 4 180.45 170.35 11 59.4 3 1200/649 6 174.45 165.4 12.5 62.1 4 1250/677 4 168.2 157.45 14.5 79.4 5 1300/704 2 155.8 147 16 87.75 6 1300/704 6 153 143.7 17 87.75 7 1350/732 4 145.05 137.95 20 95.55 8 1400/760 2 140.25 134.8 20 99.25 9 1400/760 6 137.95 133.6 20.5 98.2
[0065] Heat treatment times, heat treatment temperatures, and stress test results measured in the transverse direction for the samples are shown in Table 3.
Table 3 - Transversal Properties and Heat Treatment Conditions At the. TemperatureHeat treatment(° F / ° C) Treatment TimeThermal(hours) Resistance toFinal Tension(ksi) Resistance toflow(ksi) Percent ofstretching 1 1200/649 2 193.25 182.8 4.4 2 1200/649 4 188.65 179.25 4.5 3 1200/649 6 186.35 174.85 6.5 4 1250/677 4 174.6 163.3 4.5 5 1300/704 2 169.15 157.35 6.5 6 1300/704 6 162.65 151.85 7 7 1350/732 4 147.7 135.25 9 8 1400/760 2 143.65 131.6 12 9 1400/760 6 147 133.7 15
[0066] Typical targets for Ti 5-5-5-3 alloy properties used in aerospace applications include an average final stress resistance of at least 150 ksi and a minimum fracture toughness Kic value of at least 70 ksi • in ^1/2 . According to Example 1, these target mechanical properties were obtained by the heat treatment time and temperature combinations listed in Table 2 for samples 4-6.
Example 2 [0067] Specimens from Sample No. 4 of Example 1 were sectioned at approximately the midpoint of each specimen and Krolls were recorded for examination of the microscopePetition 870170102430, of 12/27/2017, p. 36/50
24/25 structure resulting from laminate and heat treatment. FIG. 7A is an optical micrograph (100x) in the longitudinal direction and FIG. 7B is an optical micrograph (100x) in the transverse direction of a prepared representative specimen. The microstructure produced after rolling and heat treatment at 1250 ° F (677 ° C) for 4 hours is a fine α phase dispersed in a β phase matrix.
Example 3 [0068] A Ti-15Mo alloy bar obtained from ATI Allvac has been plastically deformed to a 75% reduction at a starting temperature of 1400 ° F (760.0 ° C), which is in the phase field alpha-beta. The beta transus temperature of the Ti-15Mo alloy was about 1475 ° (801.7 ° C). The final working temperature of the alloy was about 1200 ° F (648.9 ° C), which is no less than 222 ° C below the alloy's beta-trans temperature. After work, the Ti-15Mo bar was aged at 900 ° F (482.2 ° C) for 16 hours. After aging, the Ti-15Mo bar had final tensile strengths ranging from 178-188 ksi, yield strengths ranging from 170-175 ksi and Kic fracture toughness values of approximately 30 ksi · in ^1/2 .
Example 4 [0069] A 5-inch round ingot of Ti-5Al-5V-5Mo-3Cr alloy (Ti 5-5-5-3) is laminated to 2.5-inch bars at an initial temperature of about 1650 ° F (889 ° C), in the beta phase field. The beta transus temperature of the Ti 5-5-5-3 alloy is about 1530 ° F (832 ° C). The final working temperature is 1330 ° F (721 ° C), which is in the alpha-beta phase field and not less than 222 ° C below the beta transus temperature of the alloy. The reduction in alloy diameter corresponds to a 75% reduction in area. The plastic deformation temperature cools during the plastic deformation and passes through the beta transus temperature. At least a 25% reduction in area occurs in the alpha-beta phase field as the alloy cools down during plastic deformation. After a reduction of at least 25% in the alpha-beta phase field the alloy is not heated above the beta transus temperature. After rolling, the alloy was air cooled to room temperature. The alloys are aged at 1300 ° F (704 ° C) for 2 hours.
[0070] This disclosure was written with reference to several exemplary, illustrative, and not limiting modalities. However, it will be recognized by persons skilled in the art that various substitutions, modifications or combinations of any of the
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Disclosed modalities (or portions thereof) can be made without departing from the scope of the invention as defined only by the claims. Thus, it is contemplated and understood that the present disclosure includes additional modalities not expressly established here. Such modalities can be obtained, for example, by combining and / or modifying any of the steps, ingredients, constituents, components, elements, characteristics, aspects described, and the like, of the modalities described herein. Thus, this disclosure is not limited by the description of the various exemplary, illustrative, and not limiting modalities, but only by the claims. In this way, the claimant reserves the right to change claims during processing to add features as otherwise described here.
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权利要求:
Claims (22)
[1]
1. Method for increasing the strength and toughness of a titanium alloy CHARACTERIZED by the fact that it comprises:
plastically deform a titanium alloy at a temperature in an alpha-beta phase field of the titanium alloy to an equivalent plastic deformation of at least a 25% reduction in area, where the plastic deformation of at least a 25% reduction in the area occurs in a plastic deformation temperature range of 10 ° C below a beta transus temperature of the titanium alloy to 222 ° C below the beta transus temperature of the titanium alloy, and in which after plastically deforming the titanium alloy to a temperature in the alpha-beta phase field the titanium alloy is not heated to a temperature at or above the beta transus temperature of the titanium alloy, and heat treatment of the titanium alloy, where the heat treatment of the titanium alloy consists of a one-stage heat treatment at a heat treatment temperature less than or equal to the beta transus temperature minus 11.1 ° C for a heat treatment time in the range of 0.5 hour to 24 hours to pro produce a heat-treated alloy in which a fracture toughness (Kic) of the heat-treated alloy is related to a yield strength (YS) of the heat-treated alloy according to the equation: Kic> 173 (0.9) YS, where Kic is in the ksi.in ^1/2 unit and YS is in the ksi unit.
[2]
2. Method, according to claim 1, CHARACTERIZED by the fact that the fracture toughness (Kic) of the heat-treated alloy is related to the yield strength (YS) of the heat-treated alloy according to the equation:
217.6 - (0.9) YS>Kic> 173 - (0.9) YS, where Kic is in the ksi.in ^1/2 unit and YS is in the ksi unit.
[3]
3. Method, according to claim 1, CHARACTERIZED by the fact that the fracture toughness (Kic) of the heat-treated alloy is related to the yield strength (YS) of the heat-treated alloy according to the equation: Kic> 217 , 6 - (0.9) YS, where Kic is in the ksi.in ^1/2 unit and YS is in the ksi unit.
[4]
4. Method, according to claim 1, CHARACTERIZED by the fact that the equivalent plastic deformation of at least a 25% reduction in area occurs in a plastic deformation temperature range of 11.1 ° C below the beta transus temperature up to 222 ° C below the beta transus temperature.
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[5]
5. Method according to claim 1, CHARACTERIZED by the fact that it further comprises plastically deforming the titanium alloy at a temperature equal to or above the beta transus temperature and through the beta transus temperature before plastically deforming the titanium alloy to a temperature in the alpha-beta phase field.
[6]
6. Method according to claim 1, CHARACTERIZED by the fact that the heat treatment of the titanium alloy comprises heating the titanium alloy to a temperature of heat treatment in the range of 482 ° C to the beta transus temperature minus 11.1 ° Ç.
[7]
7. Method according to claim 1, CHARACTERIZED by the fact that plastically deforming the titanium alloy comprises at least one of forging, rotary forging, percussion forging, multi-axis forging, bar lamination, plate lamination and extrusion of titanium alloy.
[8]
8. Method, according to claim 1, CHARACTERIZED by the fact that the titanium alloy is a titanium alloy that is capable of retaining the beta phase at room temperature.
[9]
9. Method, according to claim 8, CHARACTERIZED by the fact that the titanium alloy is Ti-5Al-5V-5Mo-3Cr alloy.
[10]
10. Method according to claim 8, CHARACTERIZED by the fact that the titanium alloy is Ti-15Mo.
[11]
11. Method, according to claim 1, CHARACTERIZED by the fact that after the heat treatment of the titanium alloy, the titanium alloy has a final stress resistance in the range of 951 MPa to 1234 MPa.
[12]
12. Method, according to claim 1, CHARACTERIZED by the fact that after the heat treatment of the titanium alloy, the titanium alloy has an elongation percentage in the range of 4.4% to 20.5%.
[13]
13. Method, according to claim 1, CHARACTERIZED by the fact that after the heat treatment of the titanium alloy, the titanium alloy has a final average stress resistance of at least 1145 MPa, an average flow resistance of at least 1020 MPa, a percentage elongation of at least 6%, and a Kic fracture toughness of at least 71.4 MPa.m ^1/2 .
[14]
14. Method for thermomechanically treating a titanium alloy CHARACTERIZED by the fact that it comprises:
to work a titanium alloy in a working temperature range of 111 ° C
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3/4 above a beta transus temperature of the titanium alloy up to 222 ° C below the beta transus temperature of the titanium alloy, where at least a 25% reduction in the area of the titanium alloy occurs in an alpha- beta of titanium alloy; and wherein the titanium alloy is not heated above the beta transus temperature after at least a 25% reduction in the area of the titanium alloy in the alpha-beta phase field of the titanium alloy; and heat treating the titanium alloy, where the heat treatment of the titanium alloy consists of a one-step heat treatment at a heat treatment temperature in a heat treatment temperature range between 482 ° C and the beta transus temperature minus 11 , 1 ° C for a heat treatment time in the range of 0.5 hour to 24 hours to produce a heat-treated alloy having a fracture toughness (Kic) that is related to the yield strength (YS) of the heat-treated alloy accordingly with the equation: Kic s 173 - (0.9) YS, where Kic is in the unit of ksi.in ^1/2 and YS is in the unit of ksi.
[15]
15. Method, according to claim 14, CHARACTERIZED by the fact that the titanium alloy work provides an equivalent plastic deformation in the range of more than a 25% reduction in area to a 99% reduction in area.
[16]
16. Method, according to claim 14, CHARACTERIZED by the fact that the work of the titanium alloy comprises working the titanium alloy of a temperature at, or above, the beta transus temperature, in the alpha-beta field and up to a temperature final work in the alpha-beta field.
[17]
17. Method, according to claim 14, CHARACTERIZED by the fact that it further comprises, after working the titanium alloy, cooling the titanium alloy to the heat treatment temperature within the heat treatment temperature range.
[18]
18. Method, according to claim 14, CHARACTERIZED by the fact that the titanium alloy is a titanium alloy that is capable of retaining the beta phase at room temperature.
[19]
19. Method, according to claim 14, CHARACTERIZED by the fact that after the heat treatment of the titanium alloy, the titanium alloy has an average final stress resistance of at least 1145 MPa, an average flow resistance of at least 1020 MPa, a Kic fracture toughness of at least 71.4 MPa.m ^1/2 , and an elongation percentage of at least 6%.
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[20]
20. Method, according to claim 14, CHARACTERIZED by the fact that the fracture toughness (Kic) of the heat-treated alloy is related to the yield strength (YS) of the heat-treated alloy according to the equation: 217.6 - (0.9) YS>Kic> 173 - (0.9) YS, where Kic is in the ksi.in unit ^{1 /} and YS is in the ksi unit.
[21]
21. Method, according to claim 14, CHARACTERIZED by the fact that the fracture toughness (Kic) of the heat-treated alloy is related to the yield strength (YS) of the heat-treated alloy according to the equation: Kic> 217 , 6 (0.9) YS, where Kic is in the ksi.in unit ^/ and YS is in the ksi unit.
[22]
22. Method for processing titanium alloys CHARACTERIZED by the fact that it comprises:
working a titanium alloy in an alpha-beta phase field of the titanium alloy to provide at least an equivalent 25% reduction in area of the titanium alloy, where the titanium alloy is able to retain the beta phase at room temperature ; and where the equivalent 25% reduction in area of the titanium alloy occurs in a plastic deformation temperature range of 10 ° C below the beta transus temperature of the titanium alloy to 222 ° C below the beta transus temperature of the titanium alloy , and heat treat the titanium alloy, where the heat treatment of the titanium alloy consists of a one-step heat treatment at a heat treatment temperature not higher than the beta transus temperature minus 11.1 ° C for a treatment time thermal in the range of 0.5 hour to 24 hours to provide the titanium alloy with an average final tensile strength of at least 1034 MPa and a Kic fracture toughness of at least 76.9 MPa.m ^1/2 .
Petition 870180040386, of 5/15/2018, p. 12/12
1/7

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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) |

2017-10-03| B07A| Technical examination (opinion): publication of technical examination (opinion)|

2018-02-14| B06A| Notification to applicant to reply to the report for non-patentability or inadequacy of the application according art. 36 industrial patent law|

2018-06-19| B09A| Decision: intention to grant|

2018-07-10| B16A| Patent or certificate of addition of invention granted|

优先权:

申请号 | 申请日 | 专利标题

US12/691,952|US10053758B2|2010-01-22|2010-01-22|Production of high strength titanium|

US12/691,952|2010-01-22|

PCT/US2010/062284|WO2011090733A2|2010-01-22|2010-12-29|Production of high strength titanium|

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