WO2011090733A2 - Production of high strength titanium - Google Patents

Production of high strength titanium Download PDF

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Publication number
WO2011090733A2
WO2011090733A2 PCT/US2010/062284 US2010062284W WO2011090733A2 WO 2011090733 A2 WO2011090733 A2 WO 2011090733A2 US 2010062284 W US2010062284 W US 2010062284W WO 2011090733 A2 WO2011090733 A2 WO 2011090733A2
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WIPO (PCT)
Prior art keywords
titanium alloy
temperature
beta
alloy
ksi
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PCT/US2010/062284
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English (en)
French (fr)
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WO2011090733A3 (en
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David J. Bryan
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ATI Properties LLC
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ATI Properties LLC
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Priority to CN2010800607739A priority Critical patent/CN102712967A/zh
Priority to NZ600696A priority patent/NZ600696A/en
Priority to EP10803547.8A priority patent/EP2526215B1/en
Priority to PL10803547T priority patent/PL2526215T3/pl
Priority to KR1020127015595A priority patent/KR101827017B1/ko
Priority to JP2012550002A priority patent/JP5850859B2/ja
Priority to UAA201210024A priority patent/UA109892C2/ru
Priority to AU2010343097A priority patent/AU2010343097B2/en
Priority to BR112012016546-1A priority patent/BR112012016546B1/pt
Priority to RU2012136150/02A priority patent/RU2566113C2/ru
Priority to MX2012007178A priority patent/MX353903B/es
Priority to ES10803547T priority patent/ES2718104T3/es
Application filed by ATI Properties LLC filed Critical ATI Properties LLC
Priority to CA2784509A priority patent/CA2784509C/en
Publication of WO2011090733A2 publication Critical patent/WO2011090733A2/en
Publication of WO2011090733A3 publication Critical patent/WO2011090733A3/en
Priority to IL220372A priority patent/IL220372A/en
Priority to IN5891DEN2012 priority patent/IN2012DN05891A/en
Priority to ZA2012/05335A priority patent/ZA201205335B/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Definitions

  • the present disclosure is directed to methods for producing titanium alloys having high strength and high toughness.
  • the methods according to the present disclosure do not require the multi-step heat treatments used in certain existing titanium alloy production methods.
  • Titanium alloys typically exhibit a high strength-to-weight ratio, are corrosion resistant, and are resistant to creep at moderately high temperatures. For these reasons, titanium alloys are used in aerospace and aeronautic applications including, for example, critical structural parts such as landing gear members and engine frames. Titanium alloys also are used in jet engines for parts such as rotors, compressor blades, hydraulic system parts, and nacelles.
  • titanium undergoes an allotropic phase transformation at about 882°C. Below this temperature, titanium adopts a hexagonally close-packed crystal structure, referred to as the a phase. Above this temperature, titanium has a body centered cubic structure, referred to as the ⁇ phase. The temperature at which the transformation from the a phase to the ⁇ phase takes place is referred to as the beta transus temperature ( ⁇ ).
  • the beta transus temperature is affected by interstitial and substitutional elements and, therefore, is dependent upon impurities and, more importantly, alloying elements.
  • alloying elements are generally classified as a stabilizing elements or ⁇ stabilizing elements. Addition of a stabilizing elements ("a stabilizers") to titanium increases the beta transus temperature.
  • Aluminum for example, is a substitutional element for titanium and is an a stabilizer.
  • Interstitial alloying elements for titanium that are a stabilizers include, for example, oxygen, nitrogen, and carbon.
  • ⁇ stabilizing elements can be either ⁇ isomorphous elements or ⁇ eutectoid elements, depending on the resulting phase diagrams.
  • ⁇ isomorphous alloying elements for titanium are vanadium, molybdenum, and niobium.
  • ⁇ eutectoid alloying elements are chromium and iron. Additionally, 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.
  • FIG. 1 A depicts a schematic phase diagram showing the effect of adding an a stabilizer to titanium.
  • the beta phase field 12 lies above the beta transus temperature line 10 and is an area of the phase diagram where only ⁇ phase is present in the titanium alloy.
  • an alpha-beta phase field 14 lies below the beta transus temperature line 10 and represents an area on the phase diagram where both a phase and ⁇ phase ( ⁇ + ⁇ ) are present in the titanium alloy.
  • the alpha phase field 16 below the alpha-beta phase field 16, where only a phase is present in the titanium alloy.
  • FIG. 1 B depicts a schematic phase diagram showing the effect of adding an isomorphous ⁇ stabilizer to titanium. Higher concentrations of ⁇ stabilizers reduce the beta transus temperature, as is indicated by the negative slope of the beta transus temperature line 10. Above the beta transus temperature line 10 is the beta phase field 12. An alpha-beta phase field 14 and an alpha phase field 16 also are present in the schematic phase diagram of titanium with isomorphous ⁇ stabilizer in FIG. 1 B.
  • FIG. 1 C depicts a schematic phase diagram showing the effect of adding a eutectoid ⁇ stabilizer to titanium.
  • the phase diagram exhibits a beta phase field 12, a beta transus temperature line 10, an alpha-beta phase field 14, and an alpha phase field 16.
  • Titanium alloys are generally classified according to their chemical composition and their microstructure at room temperature.
  • Commercially pure (CP) titanium and titanium alloys that contain only a stabilizers such as aluminum are considered alpha alloys. These are predominantly single phase alloys consisting essentially of a phase.
  • CP titanium and other alpha alloys after being annealed below the beta transus temperature, generally contain about 2-5 percent by volume of ⁇ phase, which is typically stabilized by iron impurities in the alpha titanium alloy. The small volume of ⁇ phase is useful in the alloy for controlling the recrystallized a phase grain size.
  • Near-alpha titanium alloys have a small amount of ⁇ phase, usually less than 0 percent by volume, which results in increased room temperature tensile strength and increased creep resistance at use temperatures above 400°C, compared with the alpha alloys.
  • An exemplary near-alpha titanium alloy may contain about 1 weight percent molybdenum.
  • Alpha/beta ( ⁇ + ⁇ ) titanium alloys such as Ti-6AI-4V (Ti 6-4) alloy and Ti-6AI-2Sn-4Zr-2Mo (Ti 6-2-4-2) alloy, contain both alpha and beta phase and are widely used in the aerospace and aeronautics industries.
  • the microstructure and properties of alpha/beta alloys can be varied through heat treatments and
  • thermomechanical processing
  • Stable beta titanium alloys, metastable beta titanium alloys, and near beta titanium alloys contain substantially more ⁇ stabilizing elements than alpha/beta alloys.
  • Near-beta titanium alloys such as, for example, Ti-10V-2Fe-3AI alloy, contain amounts of ⁇ stabilizing elements sufficient to maintain an all- ⁇ phase structure when water quenched, but not when air quenched.
  • Metastable beta titanium alloys such as, for example, Ti-15Mo alloy, contain higher levels of ⁇ stabilizers and retain an all- ⁇ phase structure upon air cooling, but can be aged to precipitate a phase for strengthening.
  • Stable beta titanium alloys, such as, for example, Ti-30Mo alloy retain an all- ⁇ phase microstructure upon cooling, but cannot be aged to precipitate a phase.
  • the titanium alloy also may be heat treated at a third temperature above the beta transus temperature, or heat treating 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 to a second temperature below the beta transus temperature.
  • the titanium alloy also may be heat treated at a third
  • FIG. 2 A temperature-versus-time schematic plot of a typical prior art method for producing tough, high strength titanium alloys is shown in FIG. 2.
  • the method generally includes an elevated 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 prior 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 have the capability to conduct these steps. Accordingly, it would be advantageous to provide an improved process for increasing strength and/or toughness of titanium alloys.
  • 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-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 at or above a beta transus temperature of the titanium alloy.
  • the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beta transus temperature minus 20°F for a heat treatment time sufficient to produce a heat treated alloy having a fracture toughness (K
  • the titanium alloy may 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 a 25% reduction in area at a heat treatment temperature less than or equal to the beta transus temperature minus 20°F for a heat treatment time sufficient to produce a heat treated alloy having a fracture toughness (K
  • C fracture toughness
  • a non-limiting method for thermomechanically treating a titanium alloy includes working a titanium alloy in a working temperature range of 200°F (1 1 1°C) above the beta transus temperature of the titanium alloy to 400°F (222°C) below the beta transus temperature.
  • a working temperature range of 200°F (1 1 1°C) above the beta transus temperature of the titanium alloy to 400°F (222°C) below the beta transus temperature.
  • an equivalent plastic deformation of at least 25% reduction in area may occur in an alpha-beta phase field of the titanium alloy, and the titanium alloy is not heated above the beta transus
  • the alloy after working the titanium alloy, the alloy may be heat treated in a heat treatment temperature range between 1500°F (816°C) and 900°F (482°C) for a heat treatment time of between 0.5 and 24 hours.
  • the titanium alloy may be heat treated in a heat treatment temperature range between 1500°F (816°C) and 900°F (482°C) for a heat treatment time sufficient to produce a heat treated alloy having a fracture toughness (K
  • C fracture toughness
  • a non-limiting embodiment of a method for processing titanium alloys comprises working a titanium alloy in an alpha-beta phase field of the titanium alloy to provide an equivalent plastic deformation of at least a 25% reduction in area of the titanium alloy.
  • the titanium alloy is capable of retaining beta-phase at room temperature.
  • the titanium alloy after working the titanium alloy, the titanium alloy may be heat treated at a heat treatment temperature no greater than the beta transus temperature minus 20°F for a heat treatment time sufficient to provide the titanium alloy with an average ultimate tensile strength of at least 150 ksi and a K !c fracture toughness of at least 70 ksi-in /2 .
  • the heat treatment time is in the range of 0.5 hours to 24 hours.
  • Yet a further aspect of the present disclosure is directed to a titanium alloy that has been processed according to a method encompassed by the present disclosure.
  • One non-limiting embodiment is directed to a Ti-5AI-5V-5Mo-3Cr alloy that has been processed by a method according to the present disclosure including steps of plastically deforming and heat treating the titanium alloy, and wherein the heat treated alloy has a fracture toughness (K
  • Ti-5AI-5V-5Mo-3Cr alloy which also is known as Ti-5553 alloy or Ti 5-5-5-3 alloy, includes nominally 5 weight percent aluminum, 5 weight percent vanadium, 5 weight percent molybdenum, 3 weight percent chromium, and balance titanium and incidental impurities.
  • 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 at or above a beta transus temperature of the titanium alloy.
  • the titanium alloy is heat treated at a heat treatment temperature less than or equal to the beta transus temperature minus 20°F (1 1 .1 °C) for a heat treatment time sufficient to produce a heat treated alloy having a fracture toughness (K
  • C fracture toughness
  • YS yield strength
  • Yet another aspect according to the present disclosure is directed to an article adapted for use in at least one of an aeronautic application and an aerospace application and comprising a Ti-5AI-5V-5Mo-3Cr alloy that has been processed by a method including plastically deforming and heat treating the titanium alloy in a manner sufficient so that a fracture toughness (K
  • the titanium alloy may 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.
  • the titanium alloy After plastically deforming the titanium alloy at a temperature in the alpha-beta phase field, the titanium alloy is not heated to a temperature at or above a beta transus temperature of the titanium alloy.
  • the titanium alloy may be heat treated at a heat treatment temperature less than or equal to (i.e., no greater than) the beta transus temperature minus 20°F (1 1 .1 °C) for a heat treatment time sufficient to produce a heat treated alloy having a fracture toughness (K ic ) that is related to the yield strength (YS) of the heat treated alloy according to the equation K
  • FIG. 1 A is an example of a phase diagram for titanium alloyed with an alpha stabilizing element
  • FIG. 1 B is an example of a phase diagram for titanium alloyed with an isomorphous beta stabilizing element
  • FIG. 1 C is an example of a phase diagram for titanium alloyed with a eutectoid beta stabilizing element
  • FIG. 2 is a schematic representation of a prior art thermomechanical processing scheme for producing tough, high-strength titanium alloys
  • FIG. 3 is a time-temperature diagram of a non-limiting embodiment of a method according to the present disclosure comprising substantially all alpha-beta phase plastic deformation
  • FIG. 4 is a time-temperature diagram of another non-limiting embodiment
  • FIG. 5 is a graph of K
  • FIG. 6 is a graph of K
  • FIG. 7 A is a micrograph of a Ti 5-5-5-3 alloy in the longitudinal direction after rolling and heat treating at 1250°F (677°C) for 4 hours;
  • FIG. 7B is a micrograph of a Ti 5-5-5-3 alloy in the transverse direction after rolling and heat treating at 1250°F (677°C) for 4 hours.
  • Certain non-limiting embodiments according to the present disclosure are directed to thermomechanical methods for producing tough and high strength titanium alloys and that do not require the use of complicated, multi-step heat
  • thermomechanical methods disclosed herein include only a high temperature
  • thermomechanical processing within the present disclosure can be conducted at any facility that is reasonably well equipped to perform titanium thermomechanical heat treatment.
  • the embodiments contrast with conventional heat treatment practices for imparting high toughness and high strength to titanium alloys, practices commonly requiring sophisticated equipment for closely controlling alloy cooling rates.
  • one non-limiting method 20 for increasing the strength and toughness of a titanium alloy comprises plastically deforming 22 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 25% reduction in area.
  • the equivalent 25% plastic deformation in the alpha-beta phase field involves a final plastic deformation temperature 24 in the alpha-beta phase field.
  • final plastic deformation temperature is defined herein as the temperature of the titanium alloy at the conclusion of plastically deforming the titanium alloy and prior to aging the titanium alloy.
  • the titanium alloy is not heated above the beta transus temperature (T p ) of the titanium alloy during the method 20.
  • T p beta transus temperature
  • the titanium alloy is heat treated 26 at a temperature below the beta transus temperature for a time sufficient to impart high strength and high fracture toughness to the titanium alloy.
  • the heat treatment 26 may be conducted at a temperature at least 20°F below the beta transus temperature. In another non-limiting embodiment, the heat treatment 26 may be conducted at a temperature at least 50°F below the beta transus temperature.
  • the temperature of the heat treatment 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 above the final plastic deformation temperature, but less 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 the heat treatment 26 may vary. For example, a natural decrease in temperature of the titanium alloy workpiece occurs during plastic deformation is within the scope of embodiments disclosed herein. The schematic temperature - time plot of FIG.
  • FIG. 3 illustrates that certain embodiments of methods of heat treating titanium alloys to impart high strength and high toughness disclosed herein contrast with conventional heat treatment practices for imparting high strength and high toughness to titanium alloys.
  • conventional heat treatment practices typically require multi-step heat treatments and sophisticated equipment for closely controlling alloy cooling rates, and are therefore expensive and cannot be practiced at all heat treatment facilities.
  • 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 according to the present disclosure. Further, the heat treatment times and temperatures can be adjusted to obtain a specific desired balance of strength and fracture toughness for a particular alloy composition. In certain non-limiting embodiments disclosed herein, for example, by adjusting the heat treatment times and temperatures used to process a Ti-5AI-5V-5Mo-3Cr (Ti 5-5-5-3) alloy by a method according to the present disclosure, ultimate tensile strengths of 140 ksi to 180 ksi combined with fracture toughness levels of 60 ksi-in 1/2 K
  • plastic deformation is used herein to mean the inelastic distortion of a material under applied stress or stresses that strains the material beyond its elastic limit.
  • reduction in area is used herein to mean the difference between the cross-sectional area of a titanium alloy form prior to plastic deformation and the cross-sectional area of the titanium alloy form after plastic deformation, wherein the cross-section is taken at an equivalent location.
  • the titanium alloy form used in assessing reduction in area may be, but is not limited to, any of a billet, a bar, a plate, a rod, a coil, a sheet, a rolled shape, and an extruded shape.
  • An example of a reduction in area calculation for plastically deforming a 5 inch diameter round titanium alloy billet by rolling the billet to a 2.5 inch round titanium alloy bar follows.
  • the cross-sectional area of a 5 inch diameter round billet is ⁇ (pi) times the square of the radius, or approximately (3.1415) x (2.5 inch) 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 .
  • the ratio of the cross-section area of the starting billet to the bar after rolling is 4.91/ 19.625, or 25%.
  • the reduction in area is 100% - 25%, for a 75% reduction in area.
  • Equivalent plastic deformation is used herein to mean the inelastic distortion of a material under applied stresses that strain the material beyond its elastic limit. Equivalent plastic deformation may involve stresses that would result in the specified reduction in area obtained with uniaxial deformation, but occurs such that the dimensions of the alloy form after deformation are not substantially different than the dimensions of the alloy form prior to deformation.
  • multi-axis forging may be used to subject an upset forged titanium alloy billet to substantial plastic deformation, introducing dislocations into the alloy, but without substantially changing the final dimensions of the billet.
  • the equivalent plastic deformation is at least 25%, the actual reduction in area may by 5% or less.
  • the actual reduction in area may by 1 % or less.
  • Multi-axis forging is a technique known to a person having ordinary skill in the art and, therefore, is not further described herein.
  • a titanium alloy may be plastically deformed to an equivalent plastic deformation of greater than a 25% reduction in area and up to a 99% reduction in area.
  • the equivalent plastic deformation is greater than a 25% reduction in area
  • at least an equivalent plastic deformation of a 25% reduction in area in the alpha-beta phase field occurs at the end of the plastic deformation, and the titanium alloy is not heated above the beta transus temperature (T R ) of the titanium alloy after the plastic deformation.
  • plastically deforming the titanium alloy comprises plastically deforming the titanium alloy so that all of the equivalent plastic deformation occurs in the alpha-beta phase field.
  • FIG. 3 depicts a constant plastic deformation temperature in the alpha-beta phase field, it also is within the scope of embodiments herein that the equivalent plastic deformation of at least a 25% percent reduction in area in the alpha-beta phase field occurs at varying temperatures.
  • the titanium alloy may be worked in the alpha-beta phase field while the temperature of the alloy gradually decreases. It is also within the scope of
  • 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 400°F (222°C) below the beta transus temperature.
  • plastically deforming the titanium alloy in the alpha-beta phase region comprises plastically deforming the alloy in a plastic deformation temperature range of 400°F (222°C) below the beta transus temperature to 20°F (1 1 .1 °C) below the beta transus temperature.
  • plastically deforming the titanium alloy in the alpha-beta phase region comprises plastically deforming the alloy in a plastic deformation temperature range of 50°F (27.8°C) below the beta transus temperature to 400°F (222°C) below the beta transus temperature.
  • another non-limiting method 30 includes a feature referred to herein as "through beta transus” processing.
  • plastic deformation also referred to herein as “working” begins with the temperature of the titanium alloy at or above the beta transus temperature (T p ) of the titanium alloy.
  • plastic deformation 32 includes plastically deforming the titanium alloy from a temperature 34 that is at or above the beta transus temperature to a final plastic deformation temperature 24 that is in the alpha-beta phase field of the titanium alloy.
  • T p beta transus temperature
  • plastic deformation 32 includes plastically deforming the titanium alloy from a temperature 34 that is at or above the beta transus temperature to a final plastic deformation temperature 24 that is in the alpha-beta phase field of the titanium alloy.
  • FIG. 4 illustrates that non-limiting embodiments of methods of heat treating titanium alloys to impart high strength and high toughness disclosed herein contrast with conventional heat treatment practices for imparting high strength and high toughness to titanium alloys.
  • conventional heat treatment practices typically require multi-step heat treatments and sophisticated equipment for closely controlling alloy cooling rates, and are therefore expensive and cannot be practiced at all heat treatment facilities.
  • plastically deforming the titanium alloy in a through beta transus process comprises plastically deforming the titanium alloy in a temperature range of 200°F (1 1 1 °C) above the beta transus temperature of the titanium alloy to 400°F
  • 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 the plastic deformation in the alpha-beta phase field.
  • the titanium alloy can be plastically deformed by techniques including, but not limited to, forging, rotary forging, drop forging, multi-axis forging, bar rolling, plate rolling, and extruding, or by combinations of two or more of these techniques.
  • Plastic deformation can be accomplished by any suitable mill processing technique known now or hereinafter to a person having ordinary skill in the art, as long as the processing technique used is capable of plastically deforming the titanium alloy workpiece in the alpha-beta phase region to at least an equivalent of a 25% reduction in area.
  • the plastic deformation of the titanium alloy to at least an equivalent of a 25% reduction in area occurring in the alpha-beta phase region does not substantially change the final dimensions of the titanium alloy. This may be achieved by a technique such as, for example, multi-axis forging. In other words, multi-axis forging.
  • the plastic deformation comprises an actual reduction in area of a cross- section of the titanium alloy upon completion of the plastic deformation.
  • a person skilled in the art realizes that the reduction in area of a titanium alloy resulting from plastic deformation at least equivalent to a reduction in area of 25% could result, for example, in actually changing the referenced cross-sectional area of the titanium alloy, i.e., an actual reduction in area, anywhere from as little as 0% or 1 %, and up to 25%.
  • 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 furnace cooling, air cooling, water cooling, or any other suitable cooling technique known now or hereafter to a person having ordinary skill in the art.
  • An aspect of this disclosure is such that after hot working the titanium alloy according to embodiments disclosed herein, the titanium alloy is not heated to or above the beta transus temperature. Therefore, the step of heat treating does not occur at or above the beta transus temperature of the alloy.
  • heat treating comprises heating the titanium alloy at a temperature ("heat treatment temperature") in the range of 900°F (482°C) to 1500°F (816°C) for a time ("heat treatment time") in the range of 0.5 hours to 24 hours.
  • the heat treatment temperature may be above the final plastic deformation temperature, but less than the beta transus temperature of the alloy.
  • the heat treatment temperature (T h ) is less than or equal to the beta transus temperature minus 20°F (1 1 .1 °C), i.e., T h ⁇ ( ⁇ - 20°F).
  • the heat treatment temperature (T h ) is less than or equal to the beta transus temperature minus 50°F (27.8°C), i.e., T h ⁇ (Tp - 20°F).
  • a heat treatment temperature may be in a range from at least 900°F (482°C) to the beta transus temperature minus 20°F (1 1 .1°C), or in a range from at least 900°F (482°C) to the beta transus temperature minus 50°F (27.8°C). It is understood that heat treatment times may be longer than 24 hours, for example, when the thickness of the part requires long heating times.
  • Another non-limiting embodiment of a method according to the present disclosure comprises direct aging after plastically deforming the titanium alloy, wherein the titanium alloy is cooled or heated directly to the heat treatment temperature after plastically deforming the titanium alloy in the alpha-beta phase field. It is believed that in certain non-limiting embodiments of the present method in which the titanium alloy is cooled directly to the heat treatment temperature after plastic deformation, the rate of cooling will not significantly negatively affect the strength and toughness properties achieved by the heat treatment step.
  • the titanium alloy in non-limiting embodiments 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 may be directly heated to the heat treatment temperature after plastically deforming the titanium alloy in the alpha-beta phase field.
  • thermomechanical method include applying the process to a titanium alloy that is capable of retaining ⁇ phase at room temperature.
  • titanium alloys that may be advantageously processed by various embodiments of methods according to the present disclosure include beta titanium alloys, metastable beta titanium alloys, near- beta titanium alloys, alpha-beta titanium alloys, and near-alpha titanium alloys. It is contemplated that the methods disclosed herein may also increase the strength and toughness of alpha titanium alloys because, as discussed above, even CP titanium grades include small concentrations of ⁇ phase at room temperature.
  • the methods may be used to process titanium alloys that are capable of retaining ⁇ phase at room temperature, and that are capable of retaining or precipitating a phase after aging.
  • These alloys include, but are not limited to, the general categories of beta titanium alloys, alpha-beta titanium alloys, and alpha alloys comprising small volume percentages of ⁇ phase.
  • Non-limiting examples of titanium alloys that may be processed using embodiments of methods according to the present disclosure include: alpha/beta titanium alloys, such as, for example, Ti-6AI-4V alloy (UNS Numbers R56400 and R54601 ) and Ti-6AI-2Sn-4Zr-2Mo alloy (UNS Numbers R54620 and R54621 ); near-beta titanium alloys, such as, for example, Ti-10V-2Fe-3AI alloy (UNS R54610)); and metastable beta titanium alloys, such as, for example, Ti-15Mo alloy (UNS R58150) and Ti-5AI-5V-5Mo-3Cr alloy (UNS unassigned).
  • alpha/beta titanium alloys such as, for example, Ti-6AI-4V alloy (UNS Numbers R56400 and R54601 ) and Ti-6AI-2Sn-4Zr-2Mo alloy (UNS Numbers R54620 and R54621
  • near-beta titanium alloys such as, for example, Ti-10V
  • the titanium alloy may have an ultimate tensile strength in the range of 138 ksi to 179 ksi.
  • the ultimate tensile strength properties discussed herein may be measured according to the specification of ASTM E8 - 04, "Standard Test Methods for Tension Testing of Metallic Materials".
  • the titanium alloy may have an K
  • C fracture toughness values discussed herein may be measured according to the specification ASTM E399 - 08, "Standard Test Method for Linear-Elastic Plane-Strain Fracture Toughness K lc of Metallic Materials".
  • ASTM E399 - 08 Standard Test Method for Linear-Elastic Plane-Strain Fracture Toughness K lc of Metallic Materials.
  • the titanium alloy may have a yield strength in the range of 134 ksi to 170 ksi.
  • the titanium alloy may have a percent elongation in the range of 4.4% to 20.5%.
  • advantageous ranges of strength and fracture toughness for titanium alloys that can be achieved by practicing embodiments of methods according to the present disclosure include, but are not limited to, ultimate tensile strengths from 140 ksi to 180 ksi with fracture toughness ranging from about 40 ksi-in /2 K
  • advantageous ranges of strength and fracture toughness include ultimate tensile strengths of 160 ksi to 180 ksi with fracture toughness ranging from 40 ksi-in 1 2 K
  • Other advantageous ranges of strength and fracture toughness that can be achieved by practicing certain embodiments of methods according to the present disclosure include, but are not limited to: ultimate tensile strengths of 135 ksi to180 ksi with fracture toughness ranging from 55 ksi-in 1 2 K
  • the alloy after heat treating the titanium alloy, the alloy has an average ultimate tensile strength of at least 166 ksi, an average yield strength of at least 148 ksi, a percent elongation of at least 6%, and a Ki c fracture toughness of at least 65 ksi-in 1/2 .
  • Other non-limiting embodiments of methods according to the present disclosure provide a heat-treated titanium alloy having an ultimate tensile strength of at least 150 ksi and a Kic fracture toughness of at least 70 ksi-in 1/2 .
  • Still other non-limiting embodiments of methods according to the present disclosure provide a heat-treated titanium alloy having an ultimate tensile strength of at least 135 ksi and a fracture toughness of at least 55 ksi-in 1/2 .
  • thermomechanically treating a titanium alloy comprises working (i.e., plastically deforming) a titanium alloy in a temperature range of 200°F (1 1 1 °C) above a beta transus temperature of the titanium alloy to 400°F (222°C) below the beta transus temperature.
  • working i.e., plastically deforming
  • a titanium alloy in a temperature range of 200°F (1 1 1 °C) above a beta transus temperature of the titanium alloy to 400°F (222°C) below the beta transus temperature.
  • an equivalent plastic deformation of at least a 25% reduction in area occurs in an alpha-beta phase field of the titanium alloy.
  • the titanium alloy is not heated above the beta transus temperature.
  • the titanium alloy may be heat treated at a heat treatment temperature ranging between 900°F (482°C) and 1500°F (816°C) for a heat treatment time ranging between 0.5 and 24 hours.
  • working the titanium alloy provides an equivalent plastic deformation of greater than a 25% reduction in area and up to a 99% reduction in area, wherein an equivalent plastic deformation 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 the plastic deformation.
  • a non-limiting embodiment comprises working the titanium alloy in the alpha-beta phase field.
  • working comprises working the titanium alloy at a temperature at or above the beta transus temperature to a final working temperature in the alpha-beta field, wherein the working comprises an equivalent plastic deformation of a 25% reduction in area in the alpha-beta phase field of the titanium alloy and the titanium alloy is not heated above the beta transus temperature after the plastic deformation.
  • an alloy has mechanical properties that are "useful” for a particular application if toughness and strength of the alloy are at least as high as or are within a range that is required for the application. Mechanical properties for the following alloys that are useful for certain aerospace and aeronautical application were collected:
  • Ti-10V-2Fe-3-AI Ti 10-2-3; UNS R54610
  • Ti-5AI-5V-5Mo-3Cr Ti 5-5-5-3; UNS unassigned
  • Ti-6AI-2Sn-4Zr-2Mo alloy Ti 6-2-4-2; UNS Numbers R54620 and
  • embodiments of the method according to the present disclosure result in titanium alloys having yield strength and fracture toughness that are at least comparable to the same alloys if processed using relatively costly and procedurally complex prior art thermomechanical techniques.
  • Ti-5AI-5V-5Mo-3Cr Ti 5-5-5-3Cr (Ti 5-5-5-3) alloy, from ATI Allvac, Monroe, North Carolina, was rolled to 2.5 inch bar at a starting 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 a mean ingot chemistry of 5.02 weight percent aluminum, 4.87 weight percent vanadium, 0.41 weight percent 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, remainder titanium and incidental impurities.
  • the final working temperature was 1480°F (804.4°C), also in the alpha-beta phase field and no less than 400°F (222°C) below the beta transus temperature of the alloy.
  • the alloy was air cooled to room temperature. Samples of the cooled alloy were heat treated at several heat treatment temperatures for various heat treatment times. Mechanical properties of the heat treated alloy samples were measured in the
  • Typical targets for properties of Ti 5-5-5-3 alloy used in aerospace applications include an average ultimate tensile strength of at least 150 ksi and a minimum fracture toughness K
  • FIG. 7A is an optical micrograph (100x) in the longitudinal direction
  • FIG. 7B is an optical micrograph (100x) in the transverse direction of a representative prepared specimen.
  • the microstructure produced after rolling and heat treating at 1250°F (677°C) for 4 hours is a fine a phase dispersed in a ⁇ phase matrix.
  • a bar of Ti-15Mo alloy obtained from ATI Allvac was plastically deformed to a 75% reduction at a starting temperature of 1400°F (760.0°C), which is in the alpha-beta phase field.
  • the beta transus temperature of the Ti-15Mo alloy was about 1475°F (801 .7°C).
  • the final working temperature of the alloy was about 1200°F (648.9°C), which is no less than 400°F (222°C) below the alloy's beta transus
  • the Ti-15Mo bar was aged at 900°F (482.2°C) for 16 hours. After aging, the Ti-15Mo bar had ultimate tensile strengths ranging from 178-188 ksi, yield strengths ranging from 170-175 ksi, and K
  • a 5 inch round billet of Ti-5AI-5V-5Mo-3Cr (Ti 5-5-5-3) alloy is rolled to 2.5 inch bar at a starting 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 no less than 400°F (222°C) below the beta transus temperature of the alloy.
  • the reduction in diameter of the alloy corresponds to a 75% reduction in area.
  • the plastic deformation temperature cools during plastic deformation and passes through the beta transus temperature.
  • At least a 25% reduction of area occurs in the alpha-beta phase field as the alloy cools during plastic deformation. After the at least 25% reduction 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.

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MX2012007178A MX353903B (es) 2010-01-22 2010-12-29 Produccion de titanio de alta resistencia.
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PL10803547T PL2526215T3 (pl) 2010-01-22 2010-12-29 Wytwarzanie stopów tytanu o dużej wytrzymałości
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AU2010343097A AU2010343097B2 (en) 2010-01-22 2010-12-29 Production of high strength titanium alloys
BR112012016546-1A BR112012016546B1 (pt) 2010-01-22 2010-12-29 Métodos para aumentar a resistência e a tenacidade de uma liga de titânio, tratar termomecanicamente ligas de titânio e processar ligas de titânio
RU2012136150/02A RU2566113C2 (ru) 2010-01-22 2010-12-29 Получение высокопрочного титана
CN2010800607739A CN102712967A (zh) 2010-01-22 2010-12-29 高强度钛合金的制造
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