US20130014865A1 - Method of Making High Strength-High Stiffness Beta Titanium Alloy - Google Patents
Method of Making High Strength-High Stiffness Beta Titanium Alloy Download PDFInfo
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- US20130014865A1 US20130014865A1 US13/181,732 US201113181732A US2013014865A1 US 20130014865 A1 US20130014865 A1 US 20130014865A1 US 201113181732 A US201113181732 A US 201113181732A US 2013014865 A1 US2013014865 A1 US 2013014865A1
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- alloy
- titanium alloy
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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
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/045—Alloys based on refractory metals
- C22C1/0458—Alloys based on titanium, zirconium or hafnium
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
- C22C1/1036—Alloys containing non-metals starting from a melt
- C22C1/1042—Alloys containing non-metals starting from a melt by atomising
-
- 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
-
- 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/05—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys of the Al-Si-Mg type, i.e. containing silicon and magnesium in approximately equal proportions
-
- 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
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
Definitions
- the present invention relates to a method of improving mechanical properties of beta titanium alloys, and more specifically, a method of increasing strength and stiffness of Ti-5Al-5Mo-5V-3Cr (Ti-5553) alloy without debit in ductility.
- Beta titanium alloys offer improved performance via higher specific strength (strength normalized with density) which enables weight reduction. These alloys find applications in the aerospace industry, e.g., for the structure, landing gear assemblies, and helicopter rotor systems. 1 In these applications, titanium alloys replace steels such as high strength low alloy steel and 4340M steel, providing weight savings along with reduced maintenance due to superior corrosion resistance.
- Ti-5553 (all compositions expressed in weight percent) has recently gained an increasing interest as an alternative to the more established alloy Ti-10V-2Fe-3Cr.
- Ti-5553 alloy offers improved processibility, ability to heat treat in section sizes up to 6 inches and more favorable combination of strength-ductility-toughness.
- Typical target properties of Ti-5553 in the heat treated condition are ultimate tensile strength of 180 ksi, tensile elongation of 5%, and tensile elastic modulus of 16.2 Msi. Improvements in strength and stiffness of beta titanium alloys would offer improved performance and provide further weight reduction benefit.
- titanium boride (TiB) precipitates are incorporated into a beta titanium alloy such as Ti-5553, the alloy is then subjected to process steps of homogenization, hot work, and final heat treatment to achieve improvements in mechanical properties compared to the baseline alloy.
- the boron is introduced into the titanium alloy composition to produce TiB precipitates by a suitable method, such as a pre-alloyed powder metallurgy technique.
- the method of the present invention may be used to increase mechanical properties of Ti-5553 alloy produced via a gas atomized pre-alloyed powder approach.
- FIG. 1 is a flowchart for making high strength-high stiffness Ti-5553 alloy via a pre-alloyed powder metal approach in accordance with the present invention.
- FIG. 2 is a graph of tensile yield strength (TYS), ultimate tensile strength (UTS), and tensile elongation (TE) of enhanced Ti-5553 alloy subjected to different homogenization temperatures and without homogenization. All the samples were final heat treated by solution treating at 1500° F. for 1 hour followed by aging at 1100° F. for 6 hours.
- TLS tensile yield strength
- UTS ultimate tensile strength
- TE tensile elongation
- a new and improved method of increasing mechanical properties of multi-component beta titanium alloys such as Ti-5553 is described hereinafter.
- boron into the titanium alloy composition to produce TiB precipitates can be accomplished by several different methods, such as casting, cast-and-wrought processing, powder metallurgy techniques such as gas atomization and blended elemental approach.
- Homogenization heat treatment above the beta transus temperature produces equilibrium microstructure that possesses good strength-elongation combination.
- Conventional hot metalworking operations such as forging, rolling, and extrusion below the beta transus temperature can be used to produce fine-grained microstructure.
- Final heat treatment comprising solution treatment to precipitate a desired volume fraction of coarse alpha plates followed by ageing to precipitate fine alpha platelets, both conducted below the beta transus temperature, provides the desired strength-elongation combination in the final product.
- Solution treatment in general is well known to those skilled in the art. 2 2 “Titanium”, G. Lutjering and J. C. Williams, Second Edition, Springer, 2007, page 289.
- the present approach has been practiced by a gas atomization powder metallurgy process flowchart as shown in FIG. 1 .
- the boron is added to the molten titanium alloy and the liquid melt is inert gas atomized to obtain titanium alloy powder.
- Each powder particle contains needle-shaped TiB precipitates distributed uniformly and in random orientations.
- Titanium alloy powder is consolidated using a conventional technique such as hot isostatic pressing (HIP) at, e.g., 1475° F. and 15 ksi for 3 hours to obtain fully dense powder compact.
- the beta transus temperature of the alloy is determined as 1580° F.
- the powder compact is homogenized in the temperature range 1900-2200° F. to force out supersaturated boron from the titanium lattice and produce equilibrium microstructure.
- the heat treated compact then is subjected to a metalworking operation such as forging, rolling, or extrusion below the beta transus temperature.
- a Ti-5553-1B article produced by extrusion of a 3′′ diameter powder compact into a bar of 0.75′′ diameter at 1500° F. and a ram speed of 120 inch/min is characterized as an example.
- Extruded bar was heat treated below the beta transus temperature using a combination of solution treatment at 1500° F. for 1 hour and gas furnace cooled to room temperature at a cooling rate of about 200° F./minute, plus ageing treatment at 1100° F. for 6 hours and air cooled to room temperature.
- the tensile strength was higher by up to 50 ksi, or a 28% improvement compared to the typical strength of Ti-5553 [Ref. 2] 3 .
- the tensile modulus of Ti-5553-1B was 19 Msi compared to 16.2 Msi for the baseline Ti-5553, which corresponds to a 17% increase. 3 [Ref. 2]: J. C. Fanning, Properties of TIMETAL 555, Journal of Materials Engineering and Performance, Volume 14(6), 2005, pp. 788-791.
Abstract
Description
- 1. Field of the Invention
- The present invention relates to a method of improving mechanical properties of beta titanium alloys, and more specifically, a method of increasing strength and stiffness of Ti-5Al-5Mo-5V-3Cr (Ti-5553) alloy without debit in ductility.
- 2. Description of the Background Art
- Beta titanium alloys offer improved performance via higher specific strength (strength normalized with density) which enables weight reduction. These alloys find applications in the aerospace industry, e.g., for the structure, landing gear assemblies, and helicopter rotor systems.1 In these applications, titanium alloys replace steels such as high strength low alloy steel and 4340M steel, providing weight savings along with reduced maintenance due to superior corrosion resistance. The alloy Ti-5Al-5Mo-5V-3Cr 1[Ref. 1]: R. R. Boyer and R. D. Briggs. The Use of Beta Titanium Alloys in the Aerospace Industry, Journal of Materials, Engineering and Performance, Volume 14(6), 2005, pp. 681-685.](Ti-5553) (all compositions expressed in weight percent) has recently gained an increasing interest as an alternative to the more established alloy Ti-10V-2Fe-3Cr. Ti-5553 alloy offers improved processibility, ability to heat treat in section sizes up to 6 inches and more favorable combination of strength-ductility-toughness. Typical target properties of Ti-5553 in the heat treated condition are ultimate tensile strength of 180 ksi, tensile elongation of 5%, and tensile elastic modulus of 16.2 Msi. Improvements in strength and stiffness of beta titanium alloys would offer improved performance and provide further weight reduction benefit.
- There is a need, therefore, for a new and improved method of increasing the mechanical properties of beta titanium alloys without debits in tensile elongation. The method of present invention meets this need.
- In accordance with the new and improved method of present invention, titanium boride (TiB) precipitates are incorporated into a beta titanium alloy such as Ti-5553, the alloy is then subjected to process steps of homogenization, hot work, and final heat treatment to achieve improvements in mechanical properties compared to the baseline alloy. The boron is introduced into the titanium alloy composition to produce TiB precipitates by a suitable method, such as a pre-alloyed powder metallurgy technique. As an illustrative example, the method of the present invention may be used to increase mechanical properties of Ti-5553 alloy produced via a gas atomized pre-alloyed powder approach.
-
FIG. 1 is a flowchart for making high strength-high stiffness Ti-5553 alloy via a pre-alloyed powder metal approach in accordance with the present invention; and -
FIG. 2 is a graph of tensile yield strength (TYS), ultimate tensile strength (UTS), and tensile elongation (TE) of enhanced Ti-5553 alloy subjected to different homogenization temperatures and without homogenization. All the samples were final heat treated by solution treating at 1500° F. for 1 hour followed by aging at 1100° F. for 6 hours. - A new and improved method of increasing mechanical properties of multi-component beta titanium alloys such as Ti-5553 is described hereinafter.
- The method described in this disclosure encompasses four critical elements:
-
- 1. Incorporation of TiB precipitates into beta titanium alloy matrix;
- 2. Homogenization heat treatment above the beta transus temperature;
- 3. Hot work below the beta transus temperature; and
- 4. Final heat treatment below the beta transus temperature
- Introduction of boron into the titanium alloy composition to produce TiB precipitates can be accomplished by several different methods, such as casting, cast-and-wrought processing, powder metallurgy techniques such as gas atomization and blended elemental approach. Homogenization heat treatment above the beta transus temperature (temperature at which alpha to beta phase transformation is complete) produces equilibrium microstructure that possesses good strength-elongation combination. Conventional hot metalworking operations such as forging, rolling, and extrusion below the beta transus temperature can be used to produce fine-grained microstructure. Final heat treatment comprising solution treatment to precipitate a desired volume fraction of coarse alpha plates followed by ageing to precipitate fine alpha platelets, both conducted below the beta transus temperature, provides the desired strength-elongation combination in the final product. Solution treatment in general is well known to those skilled in the art.2 2“Titanium”, G. Lutjering and J. C. Williams, Second Edition, Springer, 2007, page 289.
- The present approach has been practiced by a gas atomization powder metallurgy process flowchart as shown in
FIG. 1 . The boron is added to the molten titanium alloy and the liquid melt is inert gas atomized to obtain titanium alloy powder. Each powder particle contains needle-shaped TiB precipitates distributed uniformly and in random orientations. Titanium alloy powder is consolidated using a conventional technique such as hot isostatic pressing (HIP) at, e.g., 1475° F. and 15 ksi for 3 hours to obtain fully dense powder compact. The beta transus temperature of the alloy is determined as 1580° F. The powder compact is homogenized in the temperature range 1900-2200° F. to force out supersaturated boron from the titanium lattice and produce equilibrium microstructure. The heat treated compact then is subjected to a metalworking operation such as forging, rolling, or extrusion below the beta transus temperature. A Ti-5553-1B article produced by extrusion of a 3″ diameter powder compact into a bar of 0.75″ diameter at 1500° F. and a ram speed of 120 inch/min is characterized as an example. Extruded bar was heat treated below the beta transus temperature using a combination of solution treatment at 1500° F. for 1 hour and gas furnace cooled to room temperature at a cooling rate of about 200° F./minute, plus ageing treatment at 1100° F. for 6 hours and air cooled to room temperature. - By a series of experiments, for a given boron enhancement content, it has been determined that homogenization and ageing are critical steps for achieving improved mechanical property combinations in accordance with the method of the present invention. The influence of homogenization heat treat on room temperature tensile properties of extruded Ti-5553-1B is shown in
FIG. 2 . The hot work temperature (1500° F.), solution treatment (1500° F./1 hour), and ageing (1100° F./6 hours) were kept constant in this study. The alloy without homogenization exhibited high strength (230 ksi ultimate tensile strength) but the tensile elongation was poor (2%). Homogenization in the temperature range 1900-2200° F. for 2-4 hours prior to hot work significantly improved the tensile elongation (8% or higher) while maintaining high tensile strength. The tensile strength was higher by up to 50 ksi, or a 28% improvement compared to the typical strength of Ti-5553 [Ref. 2]3. The tensile modulus of Ti-5553-1B was 19 Msi compared to 16.2 Msi for the baseline Ti-5553, which corresponds to a 17% increase. 3[Ref. 2]: J. C. Fanning, Properties of TIMETAL 555, Journal of Materials Engineering and Performance, Volume 14(6), 2005, pp. 788-791. - The influence of ageing treatment on room temperature tensile properties of extruded Ti-5553-1B for different homogenization temperatures is demonstrated in Table 1 hereinafter. The hot work temperature (1500° F.), solution treatment (1500° F./1 hour), and ageing time (6 hours) were kept constant in this study. Upon ageing, tensile strength increased by 50-60 ksi, tensile modulus increased by 4-5 Msi without debit in tensile elongation compared to the no post heat treat condition. By a suitable choice of homogenization temperature and ageing temperature, optimum strength-modulus-ductility combinations can be achieved as shown in Table 1.
-
TABLE 1 Tensile properties of Ti-5553-1B alloy homogenized at different temperatures and tested without and with final heat treatment of solution treatment plus ageing. Solution treatment of 1500° F. for 1 hour was used. THomogenization TAgeing TYS UTS TE RA TM ° F. ° F. ksi ksi % % Msi 1900 None 160 169 9 18 14.5 1100 214 230 9 13 19.0 2000 None 152 159 9 25 14 1100 211 226 9 16 19.1 2200 None 151 158 5 27 13.3 1100 206 221 8 12 18.7 (TYS: Tensile Yield Strength, UTS: Ultimate Tensile Strength, TE: Tensile Elongation, RA: Reduction of Area, TM: Tensile Modulus). - While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims (16)
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US13/181,732 US20130014865A1 (en) | 2011-07-13 | 2011-07-13 | Method of Making High Strength-High Stiffness Beta Titanium Alloy |
CN2012102118615A CN102953024A (en) | 2011-07-13 | 2012-06-25 | Method of making high strength-high stiffness beta titanium alloy |
EP12173618A EP2546370A1 (en) | 2011-07-13 | 2012-06-26 | Method of making high strength-high stiffness beta titanium alloy |
KR1020120075100A KR20130009639A (en) | 2011-07-13 | 2012-07-10 | Method of making high strength-high stiffness beta titanium alloy |
JP2012156365A JP2013019054A (en) | 2011-07-13 | 2012-07-12 | Method of making high strength-high stiffness beta titanium alloy |
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US13/181,732 US20130014865A1 (en) | 2011-07-13 | 2011-07-13 | Method of Making High Strength-High Stiffness Beta Titanium Alloy |
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EP (1) | EP2546370A1 (en) |
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CN (1) | CN102953024A (en) |
Cited By (4)
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US20170286158A1 (en) * | 2014-09-19 | 2017-10-05 | Hewlett Packard Enterprise Development Lp | Migration Of Virtual Machines |
WO2017185079A1 (en) * | 2016-04-22 | 2017-10-26 | Arconic Inc. | Improved methods for finishing extruded titanium products |
CN112226646A (en) * | 2020-09-29 | 2021-01-15 | 中国科学院金属研究所 | Antibacterial equiaxial nanocrystalline Ti-Cu rod and wire and preparation method thereof |
CN114540603A (en) * | 2022-02-23 | 2022-05-27 | 无锡宏达重工股份有限公司 | Manufacturing process of blowout preventer shell forging |
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CN104454389A (en) * | 2014-12-20 | 2015-03-25 | 常熟市强盛电力设备有限责任公司 | Direct-driven rotor for wind driven generator |
CN104454390A (en) * | 2014-12-20 | 2015-03-25 | 常熟市强盛电力设备有限责任公司 | Wind turbine generator unit cabin base |
JP2019073760A (en) * | 2017-10-13 | 2019-05-16 | 株式会社日立製作所 | Titanium-based alloy member, method for manufacturing titanium-based alloy member, and product manufactured using titanium-based alloy member |
CN108796264B (en) * | 2018-06-28 | 2020-06-09 | 北京理工大学 | Preparation method of TiB whisker reinforced titanium-based composite material in oriented arrangement |
CN108977689B (en) * | 2018-07-20 | 2020-11-06 | 北京理工大学 | Metastable beta titanium alloy plate and processing method thereof |
CN111534772A (en) * | 2020-05-27 | 2020-08-14 | 西部超导材料科技股份有限公司 | Preparation method of TC4 titanium alloy finished bar with short process and low cost |
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CN101080504B (en) * | 2003-12-11 | 2012-10-17 | 俄亥俄州大学 | Titanium alloy microstructural refinement method and high temperature, high strain rate superplastic forming of titanium alloys |
US7879286B2 (en) * | 2006-06-07 | 2011-02-01 | Miracle Daniel B | Method of producing high strength, high stiffness and high ductility titanium alloys |
FR2940319B1 (en) * | 2008-12-24 | 2011-11-25 | Aubert & Duval Sa | PROCESS FOR THERMALLY PROCESSING A TITANIUM ALLOY, AND PIECE THUS OBTAINED |
-
2011
- 2011-07-13 US US13/181,732 patent/US20130014865A1/en not_active Abandoned
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2012
- 2012-06-25 CN CN2012102118615A patent/CN102953024A/en active Pending
- 2012-06-26 EP EP12173618A patent/EP2546370A1/en not_active Withdrawn
- 2012-07-10 KR KR1020120075100A patent/KR20130009639A/en not_active Application Discontinuation
- 2012-07-12 JP JP2012156365A patent/JP2013019054A/en active Pending
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
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US20170286158A1 (en) * | 2014-09-19 | 2017-10-05 | Hewlett Packard Enterprise Development Lp | Migration Of Virtual Machines |
WO2017185079A1 (en) * | 2016-04-22 | 2017-10-26 | Arconic Inc. | Improved methods for finishing extruded titanium products |
CN109072390A (en) * | 2016-04-22 | 2018-12-21 | 奥科宁克公司 | The improved method of titanium products for finishing through squeezing out |
CN112226646A (en) * | 2020-09-29 | 2021-01-15 | 中国科学院金属研究所 | Antibacterial equiaxial nanocrystalline Ti-Cu rod and wire and preparation method thereof |
CN114540603A (en) * | 2022-02-23 | 2022-05-27 | 无锡宏达重工股份有限公司 | Manufacturing process of blowout preventer shell forging |
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EP2546370A1 (en) | 2013-01-16 |
KR20130009639A (en) | 2013-01-23 |
CN102953024A (en) | 2013-03-06 |
JP2013019054A (en) | 2013-01-31 |
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