EP1783235B1 - Titanium-based alloy - Google Patents
Titanium-based alloy Download PDFInfo
- Publication number
- EP1783235B1 EP1783235B1 EP05772406A EP05772406A EP1783235B1 EP 1783235 B1 EP1783235 B1 EP 1783235B1 EP 05772406 A EP05772406 A EP 05772406A EP 05772406 A EP05772406 A EP 05772406A EP 1783235 B1 EP1783235 B1 EP 1783235B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- titanium
- molybdenum
- vanadium
- aluminum
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- 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
- C22C1/02—Making non-ferrous alloys by melting
-
- 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 invention relates to the field of metallurgy and particularly to the field of development of state-of-the-art titanium alloys used for making high-strength and high-workable articles including large articles, i.e. alloys of high versatility.
- Titanium alloys are widely used as aerospace materials, e.g. in airplanes and rockets since the alloys possess tough mechanical properties and are comparatively light.
- Ti6A14V alloy B.A. Kalachyov, I.S. Polkin and V.D. Talalayev. Titanium Alloys of Different countries. Reference Book. Moscow: VILS, 2000, p. 58-59 ) - [1].
- This alloy was developed in 1950s in the USA. It is characterized by medium strength of 850 up to 1000 MPa and high workability. It is a good material to work by forming: forging, die forging, and extruding. It is widely used in aeronautical and aerospace engineering, shipbuilding, automotive industry, etc., as well as in manufacturing fasteners for various applications. This alloy is good to work by all types of welding including diffusion bonding.
- Ti6A14V alloy has insufficient versatility. It is difficult to make rolled sheet products, foil, and tubes thereof since the alloy possesses relatively high resistance to deformation, which in case that the deformation temperature becomes below 800°C leads to the generation of defects such as cracks and shortens the life of working tools or necessitates costly tools.
- a pseudo- ⁇ -titanium alloy Grade 9 (Ti-3Al-2,5V), which is highly capable of cold working (see [1], p. 44, 45).
- the strength of this alloy is intermediate between that of Ti-6Al-4V alloy and titanium (600-800 MPa).
- This alloy is used as cold-worked and stress annealed; it is characterized by high corrosion resistance in various media including sea water.
- This alloy is used in making tubes for hydraulics and fuel systems of airplanes, rockets, and submarines.
- the most close analogue of the invented alloy is ⁇ + ⁇ -titanium alloy consisting of 3.0-5.0 Al; 2.1-3.7 V; 0.85-3.15 Mo; 0.85-3.15 Fe; 0.06-0.2 O 2 , and inevitable impurities (Japanese application No. 3007214 B2, filed Feb. 7, 2000 ) - prior art.
- a titanium base alloy consisting of Aluminum, Vanadium, Molybdenum, Iron, and Oxygen in the following ratio, wt.%: Aluminum 3.5-4.4 Vanadium 2.0-4.0 Molybdenum 0.1-0.8 Iron max 0.4 Oxygen max 0.25 Ti balance
- Aluminum is a ⁇ -stabilizer for the ⁇ + ⁇ -titanium alloys, which contributes to the increase of mechanical strength.
- Aluminum content is below 3.5%, sufficient strength aimed in this invention cannot be obtained, whereas in case that Aluminum content exceeds 4.4%, the hot deformation resistance is increased and ductility at lower temperatures is deteriorated, which leads to the lowering of productivity.
- Vanadium is added to titanium as a ⁇ -stabilizer for the ⁇ + ⁇ -titanitun alloys, which contributes to the increase of mechanical strength without forming brittle intermetallic compounds with titanium. Presence of Vanadium in the alloy impedes formation of ⁇ 2 -superstructure in ⁇ -phase as ⁇ -phase stabilizes, and contributes to the increase of both strength and ductility. In case that Vanadium content is below 2%, sufficient strength aimed in this invention cannot be obtained, whereas in case that Vanadium content exceeds 4.0%, the superplastic elongation is decreased by exceedingly lowering of the beta transus. Vanadium content within the range of 2.0-4.0% in this alloy has the merit in which the scrap of the most used Ti6A14V can be utilized.
- Molybdenum is added to titanium as a ⁇ -stabilizer for the ⁇ + ⁇ -titanium alloys. In case that Molybdenum is added within the range of 0.1-0.8% this contributes to its full dissolution in ⁇ -phase, which enables to obtain the sufficient strength properties without deteriorating plastic properties. In case that Molybdenum content exceeds 0.8% this contributes to the increase of the specific weight of the alloy due to the fact that Molybdenum is a heavy metal and the plastic properties of the alloy are deteriorated. In case that Molybdenum content is below 0.1%, Molybdenum does not contribute to the alloy properties in full.
- Iron added to the alloy up to 0.4% contributes to increase of the volume ratio of ⁇ -phase decreasing resistance to deformation in hot working of this alloy which leads to evading of the generation of such defects as cracking. In case that Iron content exceeds 0.4%, this generates a segregation phase with beta-flecks in melting and solidifying of the alloy, which leads to heterogeneity of mechanical properties, especially ductility.
- Oxygen contributes to the enhancement of mechanical strength by constituting a solid solution mainly in ⁇ -phase. In case that Oxygen content exceeds 0.25%, the alloy ductility may be deteriorated.
- the alloy may contain up to 0.1% of carbon and up to 0.05% of nitrogen as inevitable impurities; the total quantity of impurities shall not exceed 0.16%.
- Bars with the diameter of 50 mm were made of each ingot by hot working. Part of the bars was heat treated by annealing at 750°C, soaking for 1 hour and cooling in the air. The mechanical properties at room temperature were evaluated on the bars heat treated and on those not heat treated. The evaluation results are given in Table 2. In addition, the mechanical properties of ⁇ -upset workpieces were evaluated, which were heat treated at 710°C, soaked for 3 hours and cooled in air. The results of mechanical test of workpieces upset in ⁇ + ⁇ and ⁇ -field are given in Table 2.
- the invented alloy is highly versatile, economically beneficial and has lower cost due to the fact that scrap of widely known alloys, such as Ti6Al4V, can be used for its production.
- This alloy possesses required and sufficient mechanical properties and can be utilized for making a wide range of products, such as large forgings and die forgings, thin sheets and foil, by working in both ⁇ + ⁇ -field and ⁇ -field.
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- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Forging (AREA)
- Materials For Medical Uses (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
- The invention relates to the field of metallurgy and particularly to the field of development of state-of-the-art titanium alloys used for making high-strength and high-workable articles including large articles, i.e. alloys of high versatility.
- Titanium alloys are widely used as aerospace materials, e.g. in airplanes and rockets since the alloys possess tough mechanical properties and are comparatively light.
- Known is the most widely used titanium alloy, Ti6A14V alloy (B.A. Kalachyov, I.S. Polkin and V.D. Talalayev. Titanium Alloys of Different Countries. Reference Book. Moscow: VILS, 2000, p. 58-59) - [1]. This alloy was developed in 1950s in the USA. It is characterized by medium strength of 850 up to 1000 MPa and high workability. It is a good material to work by forming: forging, die forging, and extruding. It is widely used in aeronautical and aerospace engineering, shipbuilding, automotive industry, etc., as well as in manufacturing fasteners for various applications. This alloy is good to work by all types of welding including diffusion bonding.
- The disadvantage of Ti6A14V alloy is its insufficient versatility. It is difficult to make rolled sheet products, foil, and tubes thereof since the alloy possesses relatively high resistance to deformation, which in case that the deformation temperature becomes below 800°C leads to the generation of defects such as cracks and shortens the life of working tools or necessitates costly tools.
- Known is a pseudo-α-titanium alloy Grade 9 (Ti-3Al-2,5V), which is highly capable of cold working (see [1], p. 44, 45). The strength of this alloy is intermediate between that of Ti-6Al-4V alloy and titanium (600-800 MPa). This alloy is used as cold-worked and stress annealed; it is characterized by high corrosion resistance in various media including sea water. This alloy is used in making tubes for hydraulics and fuel systems of airplanes, rockets, and submarines.
- The disadvantage of this alloy is also its low versatility since it requires stress relieving in making large structural parts thereof. Therefore, articles have to be annealed which reduces strength of Grade 9 alloy down to 400-500 MPa.
- The most close analogue of the invented alloy is α+β-titanium alloy consisting of 3.0-5.0 Al; 2.1-3.7 V; 0.85-3.15 Mo; 0.85-3.15 Fe; 0.06-0.2 O2, and inevitable impurities (Japanese application No.
3007214 B2, filed Feb. 7, 2000 - The disadvantage of this alloy is that it is rich in Fe and Mo and, therefore, is prone to segregation process. In order to reduce possibility of segregational heterogeneity it is required to use a special ingot melting technology, then carry out rolling and forging at a small deformation rate in order to exclude decoration of "beta-flecks", which decreases the productivity.
- It is an object of the invention to provide a versatile titanium alloy which requires the least manufacturing costs and is capable of making a wide product mix thereof, such as large forgings and die forgings, as well as rolled sheet products and foil having sufficient strength and plastic properties and structure.
- According to the invention an optimum mix of α- and β-stabilizing alloying elements in a semi-finished product is provided.
- According to the invention a titanium base alloy is provided consisting of Aluminum, Vanadium, Molybdenum, Iron, and Oxygen in the following ratio, wt.%:
Aluminum 3.5-4.4 Vanadium 2.0-4.0 Molybdenum 0.1-0.8 Iron max 0.4 Oxygen max 0.25 Ti balance - High strength and ductility combined in the invented alloy is achieved through targeted selection and experimental evaluation of the alloying ranges. The content of α- stabilizers (Aluminum, Oxygen) and β-stabilizers (Vanadium, Molybdenum, and Iron) was determined so as to meet a goal objective.
- Aluminum is a α-stabilizer for the α +β-titanium alloys, which contributes to the increase of mechanical strength. However in case that Aluminum content is below 3.5%, sufficient strength aimed in this invention cannot be obtained, whereas in case that Aluminum content exceeds 4.4%, the hot deformation resistance is increased and ductility at lower temperatures is deteriorated, which leads to the lowering of productivity.
- Vanadium is added to titanium as a β-stabilizer for the α +β-titanitun alloys, which contributes to the increase of mechanical strength without forming brittle intermetallic compounds with titanium. Presence of Vanadium in the alloy impedes formation of α2-superstructure in α-phase as β-phase stabilizes, and contributes to the increase of both strength and ductility. In case that Vanadium content is below 2%, sufficient strength aimed in this invention cannot be obtained, whereas in case that Vanadium content exceeds 4.0%, the superplastic elongation is decreased by exceedingly lowering of the beta transus. Vanadium content within the range of 2.0-4.0% in this alloy has the merit in which the scrap of the most used Ti6A14V can be utilized.
- Molybdenum is added to titanium as a β-stabilizer for the α +β-titanium alloys. In case that Molybdenum is added within the range of 0.1-0.8% this contributes to its full dissolution in α-phase, which enables to obtain the sufficient strength properties without deteriorating plastic properties. In case that Molybdenum content exceeds 0.8% this contributes to the increase of the specific weight of the alloy due to the fact that Molybdenum is a heavy metal and the plastic properties of the alloy are deteriorated. In case that Molybdenum content is below 0.1%, Molybdenum does not contribute to the alloy properties in full.
- Iron added to the alloy up to 0.4% contributes to increase of the volume ratio of β-phase decreasing resistance to deformation in hot working of this alloy which leads to evading of the generation of such defects as cracking. In case that Iron content exceeds 0.4%, this generates a segregation phase with beta-flecks in melting and solidifying of the alloy, which leads to heterogeneity of mechanical properties, especially ductility.
- Oxygen contributes to the enhancement of mechanical strength by constituting a solid solution mainly in α-phase. In case that Oxygen content exceeds 0.25%, the alloy ductility may be deteriorated.
- The alloy may contain up to 0.1% of carbon and up to 0.05% of nitrogen as inevitable impurities; the total quantity of impurities shall not exceed 0.16%.
- To evaluate the properties of the claimed alloy ingots were melted by the method of double vacuum arc remelt, having the following chemical composition (Table 1).
Table 1 Alloy Chemical Composition, wt.% Al V Mo Fe O 1 3.9 2.2 0.2 0.13 0.17 2 4.3 2.8 0.3 0.24 0.23 3 4.3 3.3 0.6 0.32 0.20 Table 2 Alloy Heat Treatment Mechanical Properties σB, MPa σ0.2, MPa δ, % ψ, % 1 W/o annealing 810 735 15.2 38.2 750°C 1 hour, air 780 693 13.2 32.0 2 W/o annealing 960 840 14.2 33.1 750°C 1 hour, air 920 845 13.6 32.5 3 α+β 710°C 3 hours, air 900 835 15 33.0 β 710°C 3 hours, air 870 800 14 28.0 - Bars with the diameter of 50 mm were made of each ingot by hot working. Part of the bars was heat treated by annealing at 750°C, soaking for 1 hour and cooling in the air. The mechanical properties at room temperature were evaluated on the bars heat treated and on those not heat treated. The evaluation results are given in Table 2. In addition, the mechanical properties of β-upset workpieces were evaluated, which were heat treated at 710°C, soaked for 3 hours and cooled in air. The results of mechanical test of workpieces upset in α+β and β-field are given in Table 2.
- In comparison with the known alloys the invented alloy is highly versatile, economically beneficial and has lower cost due to the fact that scrap of widely known alloys, such as Ti6Al4V, can be used for its production. This alloy possesses required and sufficient mechanical properties and can be utilized for making a wide range of products, such as large forgings and die forgings, thin sheets and foil, by working in both α+β-field and β-field.
Claims (1)
- A titanium base alloy consisting of Aluminum, Vanadium, Molybdenum, Iron, and Oxygen in the following ratio, wt.%:
Aluminum 3.5-4.4 Vanadium 2.0-4.0 Molybdenum 0.1-0.8 Iron max 0.4 Oxygen max 0.25 Titanium balance
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2004123500/02A RU2269584C1 (en) | 2004-07-30 | 2004-07-30 | Titanium-base alloy |
PCT/RU2005/000381 WO2006014124A1 (en) | 2004-07-30 | 2005-07-14 | Titanium-based alloy |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1783235A1 EP1783235A1 (en) | 2007-05-09 |
EP1783235A4 EP1783235A4 (en) | 2008-02-13 |
EP1783235B1 true EP1783235B1 (en) | 2009-01-07 |
Family
ID=35787368
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05772406A Not-in-force EP1783235B1 (en) | 2004-07-30 | 2005-07-14 | Titanium-based alloy |
Country Status (8)
Country | Link |
---|---|
US (1) | US20080181809A1 (en) |
EP (1) | EP1783235B1 (en) |
AT (1) | ATE420217T1 (en) |
DE (1) | DE602005012284D1 (en) |
DK (1) | DK1783235T3 (en) |
ES (1) | ES2320684T3 (en) |
RU (1) | RU2269584C1 (en) |
WO (1) | WO2006014124A1 (en) |
Families Citing this family (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2211873C2 (en) * | 2001-11-22 | 2003-09-10 | ОАО Верхнесалдинское металлургическое производственное объединение | METASTABLE β-TITANIUM ALLOY |
US20040221929A1 (en) | 2003-05-09 | 2004-11-11 | Hebda John J. | Processing of titanium-aluminum-vanadium alloys and products made thereby |
US7837812B2 (en) | 2004-05-21 | 2010-11-23 | Ati Properties, Inc. | Metastable beta-titanium alloys and methods of processing the same by direct aging |
CN101543948B (en) * | 2008-03-28 | 2011-06-08 | 北京有色金属研究总院 | Processing technology of Ti5Mo5V2Cr3Al alloy |
DE102009050603B3 (en) * | 2009-10-24 | 2011-04-14 | Gfe Metalle Und Materialien Gmbh | Process for producing a β-γ-TiAl base alloy |
RU2425164C1 (en) * | 2010-01-20 | 2011-07-27 | Открытое Акционерное Общество "Корпорация Всмпо-Ависма" | Secondary titanium alloy and procedure for its fabrication |
US10053758B2 (en) | 2010-01-22 | 2018-08-21 | Ati Properties Llc | Production of high strength titanium |
US9255316B2 (en) | 2010-07-19 | 2016-02-09 | Ati Properties, Inc. | Processing of α+β titanium alloys |
US9631261B2 (en) | 2010-08-05 | 2017-04-25 | Titanium Metals Corporation | Low-cost alpha-beta titanium alloy with good ballistic and mechanical properties |
US9206497B2 (en) | 2010-09-15 | 2015-12-08 | Ati Properties, Inc. | Methods for processing titanium alloys |
US8613818B2 (en) | 2010-09-15 | 2013-12-24 | Ati Properties, Inc. | Processing routes for titanium and titanium alloys |
US10513755B2 (en) * | 2010-09-23 | 2019-12-24 | Ati Properties Llc | High strength alpha/beta titanium alloy fasteners and fastener stock |
RU2463365C2 (en) * | 2010-09-27 | 2012-10-10 | Открытое Акционерное Общество "Корпорация Всмпо-Ависма" | METHOD TO PRODUCE INGOT OF PSEUDO β-TITANIUM ALLOY, CONTAINING (4,0-6,0)%Al, (4,5-6,0)% Mo, (4,5-6,0)% V, (2,0-3,6)%Cr, (0,2-0,5)% Fe, (0,1-2,0)%Zr |
US8652400B2 (en) | 2011-06-01 | 2014-02-18 | Ati Properties, Inc. | Thermo-mechanical processing of nickel-base alloys |
CN102586639A (en) * | 2012-03-16 | 2012-07-18 | 广州有色金属研究院 | Method for preparing titanium alloy through high-speed pressing formation |
US9869003B2 (en) | 2013-02-26 | 2018-01-16 | Ati Properties Llc | Methods for processing alloys |
US9192981B2 (en) | 2013-03-11 | 2015-11-24 | Ati Properties, Inc. | Thermomechanical processing of high strength non-magnetic corrosion resistant material |
US9777361B2 (en) | 2013-03-15 | 2017-10-03 | Ati Properties Llc | Thermomechanical processing of alpha-beta titanium alloys |
US11111552B2 (en) | 2013-11-12 | 2021-09-07 | Ati Properties Llc | Methods for processing metal alloys |
US9956629B2 (en) * | 2014-07-10 | 2018-05-01 | The Boeing Company | Titanium alloy for fastener applications |
JP6392179B2 (en) * | 2014-09-04 | 2018-09-19 | 株式会社神戸製鋼所 | Method for deoxidizing Ti-Al alloy |
US10094003B2 (en) | 2015-01-12 | 2018-10-09 | Ati Properties Llc | Titanium alloy |
US10502252B2 (en) | 2015-11-23 | 2019-12-10 | Ati Properties Llc | Processing of alpha-beta titanium alloys |
JP7022698B2 (en) * | 2016-04-25 | 2022-02-18 | ハウメット エアロスペース インコーポレイテッド | BCC materials of titanium, aluminum, vanadium, and iron and products made from them |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2754204A (en) * | 1954-12-31 | 1956-07-10 | Rem Cru Titanium Inc | Titanium base alloys |
US2868640A (en) * | 1955-01-11 | 1959-01-13 | British Non Ferrous Metals Res | Titanium alloys |
US2819958A (en) * | 1955-08-16 | 1958-01-14 | Mallory Sharon Titanium Corp | Titanium base alloys |
US2893864A (en) * | 1958-02-04 | 1959-07-07 | Harris Geoffrey Thomas | Titanium base alloys |
JPS5839902B2 (en) * | 1976-04-28 | 1983-09-02 | 三菱重工業株式会社 | Titanium alloy with high internal friction |
RU2039111C1 (en) * | 1992-07-14 | 1995-07-09 | Научно-производственное объединение "Композит" | Titanium alloy |
US5358686A (en) * | 1993-02-17 | 1994-10-25 | Parris Warren M | Titanium alloy containing Al, V, Mo, Fe, and oxygen for plate applications |
US5332545A (en) * | 1993-03-30 | 1994-07-26 | Rmi Titanium Company | Method of making low cost Ti-6A1-4V ballistic alloy |
JP2988246B2 (en) * | 1994-03-23 | 1999-12-13 | 日本鋼管株式会社 | Method for producing (α + β) type titanium alloy superplastic formed member |
RU2259413C2 (en) * | 2001-02-28 | 2005-08-27 | ДжФЕ СТИЛ КОРПОРЕЙШН | Brick made out of a titanium alloy and a method of its production |
US6786985B2 (en) * | 2002-05-09 | 2004-09-07 | Titanium Metals Corp. | Alpha-beta Ti-Ai-V-Mo-Fe alloy |
-
2004
- 2004-07-30 RU RU2004123500/02A patent/RU2269584C1/en active
-
2005
- 2005-07-14 WO PCT/RU2005/000381 patent/WO2006014124A1/en active Application Filing
- 2005-07-14 AT AT05772406T patent/ATE420217T1/en active
- 2005-07-14 ES ES05772406T patent/ES2320684T3/en active Active
- 2005-07-14 US US11/630,428 patent/US20080181809A1/en not_active Abandoned
- 2005-07-14 DE DE602005012284T patent/DE602005012284D1/en active Active
- 2005-07-14 DK DK05772406T patent/DK1783235T3/en active
- 2005-07-14 EP EP05772406A patent/EP1783235B1/en not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
WO2006014124A1 (en) | 2006-02-09 |
ATE420217T1 (en) | 2009-01-15 |
DK1783235T3 (en) | 2009-03-16 |
ES2320684T3 (en) | 2009-05-27 |
EP1783235A1 (en) | 2007-05-09 |
US20080181809A1 (en) | 2008-07-31 |
DE602005012284D1 (en) | 2009-02-26 |
EP1783235A4 (en) | 2008-02-13 |
RU2269584C1 (en) | 2006-02-10 |
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