EP2546370A1 - Procédé de production d'un alliage de titane bêta à rigidité et résistance élevée - Google Patents

Procédé de production d'un alliage de titane bêta à rigidité et résistance élevée Download PDF

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Publication number
EP2546370A1
EP2546370A1 EP12173618A EP12173618A EP2546370A1 EP 2546370 A1 EP2546370 A1 EP 2546370A1 EP 12173618 A EP12173618 A EP 12173618A EP 12173618 A EP12173618 A EP 12173618A EP 2546370 A1 EP2546370 A1 EP 2546370A1
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EP
European Patent Office
Prior art keywords
alloy
titanium alloy
beta
temperature
beta transus
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.)
Withdrawn
Application number
EP12173618A
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German (de)
English (en)
Inventor
William M. Hanusiak
Seshacharyulu Tamirisakandala
Robert Lewis Grabow
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
FMW Composite Systems Inc
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FMW Composite Systems Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by FMW Composite Systems Inc filed Critical FMW Composite Systems Inc
Publication of EP2546370A1 publication Critical patent/EP2546370A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • 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, as described in 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 . 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 The alloy Ti-5Al-5Mo-5V-3Cr (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.
  • a new and improved method of increasing mechanical properties of multicomponent 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, as described in " 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 Figure 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 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, as described in " J.C. Fanning", Properties of TIMETAL 555, Journal of Materials Engineering and Performance, Volume 14(6), 2005, pp. 788-791 .
  • 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.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Forging (AREA)
  • Manufacture Of Metal Powder And Suspensions Thereof (AREA)
EP12173618A 2011-07-13 2012-06-26 Procédé de production d'un alliage de titane bêta à rigidité et résistance élevée Withdrawn EP2546370A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/181,732 US20130014865A1 (en) 2011-07-13 2011-07-13 Method of Making High Strength-High Stiffness Beta Titanium Alloy

Publications (1)

Publication Number Publication Date
EP2546370A1 true EP2546370A1 (fr) 2013-01-16

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EP12173618A Withdrawn EP2546370A1 (fr) 2011-07-13 2012-06-26 Procédé de production d'un alliage de titane bêta à rigidité et résistance élevée

Country Status (5)

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US (1) US20130014865A1 (fr)
EP (1) EP2546370A1 (fr)
JP (1) JP2013019054A (fr)
KR (1) KR20130009639A (fr)
CN (1) CN102953024A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104454389A (zh) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 风力发电机用直驱转子
CN104454390A (zh) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 风力发电机组机舱座

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105471744B (zh) * 2014-09-19 2018-10-09 新华三技术有限公司 一种虚拟机迁移方法和装置
US20170306467A1 (en) * 2016-04-22 2017-10-26 Arconic Inc. Methods for finishing extruded titanium products
JP2019073760A (ja) * 2017-10-13 2019-05-16 株式会社日立製作所 チタン基合金部材、該チタン基合金部材の製造方法、及び該チタン基合金部材を用いた製造物
CN108796264B (zh) * 2018-06-28 2020-06-09 北京理工大学 一种定向排布TiB晶须增强钛基复合材料的制备方法
CN108977689B (zh) * 2018-07-20 2020-11-06 北京理工大学 一种亚稳β钛合金板材及其加工方法
CN111534772A (zh) * 2020-05-27 2020-08-14 西部超导材料科技股份有限公司 一种短流程低成本tc4类钛合金成品棒材的制备方法
CN112226646B (zh) * 2020-09-29 2022-02-15 中国科学院金属研究所 一种抗菌等轴纳米晶Ti-Cu棒、丝材及其制备方法
CN114540603A (zh) * 2022-02-23 2022-05-27 无锡宏达重工股份有限公司 防喷器壳体锻件制作工艺

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005060631A2 (fr) * 2003-12-11 2005-07-07 Ohio University Procede d'affinage microstructurel d'alliage de titane et formation superplastique a vitesse de deformation elevee et haute temperature d'alliages de titane
WO2007142837A1 (fr) * 2006-06-07 2007-12-13 Fmw Composite Systems, Inc. Procédé de fabrication d'alliages de titane de grande résistance, de grande rigidité et de grande ductilité
US20100180991A1 (en) * 2008-12-24 2010-07-22 Aubert & Duval Titanium alloy heat treatment process, and part thus obtained

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005060631A2 (fr) * 2003-12-11 2005-07-07 Ohio University Procede d'affinage microstructurel d'alliage de titane et formation superplastique a vitesse de deformation elevee et haute temperature d'alliages de titane
WO2007142837A1 (fr) * 2006-06-07 2007-12-13 Fmw Composite Systems, Inc. Procédé de fabrication d'alliages de titane de grande résistance, de grande rigidité et de grande ductilité
US20100180991A1 (en) * 2008-12-24 2010-07-22 Aubert & Duval Titanium alloy heat treatment process, and part thus obtained

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
G. LUTJERING; J.C. WILLIAMS: "Titanium", 2007, SPRINGER, pages: 289
J.C. FANNING: "Properties of TIMETAL 555", JOURNAL OF MATERIALS ENGINEERING AND PERFORMANCE, vol. 14, no. 6, 2005, pages 788 - 791
R.R. BOYER; R.D. BRIGGS: "The Use of Beta Titanium Alloys in the Aerospace Industry", JOURNAL OF MATERIALS, ENGINEERING AND PERFORMANCE, vol. 14, no. 6, 2005, pages 681 - 685, XP002531684, DOI: doi:10.1361/105994905X75448

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104454389A (zh) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 风力发电机用直驱转子
CN104454390A (zh) * 2014-12-20 2015-03-25 常熟市强盛电力设备有限责任公司 风力发电机组机舱座

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Publication number Publication date
KR20130009639A (ko) 2013-01-23
CN102953024A (zh) 2013-03-06
US20130014865A1 (en) 2013-01-17
JP2013019054A (ja) 2013-01-31

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