EP1577409B1 - Alliage a base de titane - Google Patents

Alliage a base de titane Download PDF

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Publication number
EP1577409B1
EP1577409B1 EP03811968A EP03811968A EP1577409B1 EP 1577409 B1 EP1577409 B1 EP 1577409B1 EP 03811968 A EP03811968 A EP 03811968A EP 03811968 A EP03811968 A EP 03811968A EP 1577409 B1 EP1577409 B1 EP 1577409B1
Authority
EP
European Patent Office
Prior art keywords
alloy
mass
titanium
strength
iron
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.)
Expired - Lifetime
Application number
EP03811968A
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German (de)
English (en)
Other versions
EP1577409A1 (fr
EP1577409A4 (fr
Inventor
Vladislav Valentinovich Tetyukhin
Jury Ivanovich Zakharov
Igor Vasilievich Levin
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.)
VSMPO Avisma Corp PSC
Original Assignee
VSMPO Avisma Corp PSC
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Publication date
Application filed by VSMPO Avisma Corp PSC filed Critical VSMPO Avisma Corp PSC
Publication of EP1577409A1 publication Critical patent/EP1577409A1/fr
Publication of EP1577409A4 publication Critical patent/EP1577409A4/fr
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Publication of EP1577409B1 publication Critical patent/EP1577409B1/fr
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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

Definitions

  • the invention relates to the metallurgical one, and more particularly to creation of the modem titanium alloys used for making high-strength and high-tech items, including the large-sized ones, i.e. alloys having a broad range of applications.
  • titanium alloys One of the known titanium alloys is the alloy containing, in % by weight: aluminum 2-6, molybdenum 6-9, vanadium 1-3, chromium 0,5-2,0, iron 0-1,5, titanium - balance (Inventor's Certificate USSR No. 180351, Class C22C 14/00, published 1966).
  • This alloy was proposed for making die-forgings and forgings for the highly loaded structural parts.
  • the significant drawback is its tendency to forming the high density inclusions when melting ingots due to the high content of the refractory element molybdenum (> 6%). The presence of such inclusions in the high-loaded parts leads to destruction of such parts when being in service.
  • the other known titanium alloy containing % by weight: 4,0-6,3 Al; 4,0-5,0 V; 1,5-2,5 Mo; 0,8-1,4 Cr; 0,4-0,8 Fe; 0,01-0,08 Zr; 0,01-0,25 C; 0,03-0,25 O; balance - titanium (Inventor's Certificate USSR No. 555161, Class C22C 14/00, published 1977).
  • This alloy has the high strength properties, fine ductility, not disposed to forming the high density inclusions.
  • the drawback of this alloy is the impossibility of cold die-forging, caused by insufficient level of the index of the process plasticity as age, such as the degree of cold upsetting(less than 60%).
  • the closest to the claimed invention from the technical point is the alloy with the base of titanium, containing % by weight: 2,2-3,8 Al; 4,5-5,9 V; 4,5-5,9 Mo; 2,0-3,6 Cr; 0,2-0,8 Fe; 0,01-0,08 Zr; 0,01-0,25 C; 0,03-0,25 O; Ti - balance (RF Patent No. 2150528, Class C22C 14/00, published 2000) - prototype.
  • Alloy has the high level of plasticity as quenched, in this case they achieve the degree of cold upsetting ⁇ 75%.
  • the known alloy has the insufficiently high level of the working temperatures, this limits the scope of its application as a structural material for making parts, used at increased temperatures.
  • This invention aims at creation of the titanium alloy with the increased heat-resistance, which ensures the possibility of making the heavy large-sized parts with the high level of the strength and plastic properties, used at increased temperatures.
  • the technical result is achieved due to the fact that in the alloy with the base of titanium, containing aluminum, vanadium, molybdenum, chromium, iron, zirconium, carbon, oxygen, according to the invention, the components are taken in the following ratio, weight %: Aluminum 2,2 - 3,8 Vanadium 4,5 - 5,9 Molybdenum 4,5 - 5,9 Chromium 2,0 - 3,6 Zirconium 0,1 - 0,4 Iron 0,01 - 0,18 Carbon 0,01 - 0,25 Oxygen 0,03 - 0,25 Titanium balance
  • the combination of high strength and plasticity of the proposed alloy is achieved as a result of the task-oriented choice and experimental evaluation of the alloying ranges.
  • Content of the ⁇ - stabilizing elements (aluminum, oxygen, carbon) and ⁇ -stabilizers (molybdenum, vanadium, chromium, iron) is chosen as required and sufficient for achievement of the set target.
  • the proposed alloy ensures the possibility to effectively regulate the strength level of the alloy as aged within the wide ranges.
  • Balancing aluminum and chromium content in the claimed alloy ensures high alloy ability for cold die forging (fine rolling to bar) and possibility of alloy strengthening by the thermal techniques obtaining the high level of the strength and plastic properties.
  • the content of V and Mo is set as ⁇ 4,5%.
  • V and Mo content is accepted 5,9% max due to the hazard of significant growth of segregation non-uniformity and occurrence of defects when using the hard master alloys.
  • Amount of zirconium in the alloy from 0,1 to 0,4% ensures increase of the tensile strength without lowering of the metal processibility during hot (not increases the flow stress) and cold (not decreases the plasticity resource) deformation. In this case stabilizing the ⁇ -phase, zirconium increases creep resistance and high-temperature strength.
  • Ranges of alloying with zirconium and iron are selected on the base of experimental evaluation of the alloy mechanical properties in the proposed composition range. Content of zirconium from 0,1 to 0,4% and iron to 0,18% ensures the increase of the ultimate strength of the alloy in the as quenched and aged condition.
  • the proposed combination of the components of the alloy and their % ratio in complex ensures the possibility of the alloy deformation in the greater temperature range and obtaining parts by cold die forging.
  • Test results show that the declared items (bars with dia 50 mm) from titanium-base alloy have the high processing plasticity level as quenched, in this case they achieve the degree of cold upsetting > 75% in combination with high strength obtained as a result of the subsequent ageing ( ⁇ B > 1500 Mpa).
  • the claimed alloy has the higher range of the working temperatures (10-15°C higher than the alloy - prototype has), this gives the possibility to use it not only when making the bolt heads through cold heading, in cold threading, in production of coil springs, and for making large semis up to 60mm in section, with the high level of strength and plastic properties, used at increased temperatures.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)
  • Forging (AREA)
  • Manufacture And Refinement Of Metals (AREA)
  • Materials For Medical Uses (AREA)
  • Springs (AREA)

Claims (1)

  1. Alliage à base de titane, contenant de l'aluminium, du vanadium, du molybdène, du chrome, du fer, du zirconium, du carbone, de l'oxygène, qui se distingue par le fait que les composants de l'alliage sont pris dans les rapports suivants, en pourcentage du poids : aluminium 2,2 à 3,8 vanadium 4,5 à 5,9 molybdène 4,5 à 5,9 chrome 2,0 à 3,6 zirconium 0,1 à 0,4 fer 0,01 à 0,18 carbone 0,01 à 0,25 oxygène 0,03 à 0,25 titane reste.
EP03811968A 2002-11-25 2003-08-21 Alliage a base de titane Expired - Lifetime EP1577409B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
RU2002131488 2002-11-25
RU2002131488/02A RU2228966C1 (ru) 2002-11-25 2002-11-25 Сплав на основе титана
PCT/RU2003/000378 WO2004048627A1 (fr) 2002-11-25 2003-08-21 Alliage a base de titane

Publications (3)

Publication Number Publication Date
EP1577409A1 EP1577409A1 (fr) 2005-09-21
EP1577409A4 EP1577409A4 (fr) 2006-08-16
EP1577409B1 true EP1577409B1 (fr) 2007-11-21

Family

ID=32390762

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03811968A Expired - Lifetime EP1577409B1 (fr) 2002-11-25 2003-08-21 Alliage a base de titane

Country Status (9)

Country Link
US (1) US20060115374A1 (fr)
EP (1) EP1577409B1 (fr)
AU (1) AU2003261684A1 (fr)
DE (1) DE60317708T2 (fr)
DK (1) DK1577409T3 (fr)
ES (1) ES2293095T3 (fr)
HK (1) HK1079826B (fr)
RU (1) RU2228966C1 (fr)
WO (1) WO2004048627A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SG11201808763QA (en) * 2016-04-25 2018-11-29 Arconic Inc Bcc materials of titanium, aluminum, vanadium, and iron, and products made therefrom

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU555161A1 (ru) * 1975-02-14 1977-04-25 Ордена Ленина Предприятие П/Я Р-6209 Сплав на основе титана
US4943412A (en) * 1989-05-01 1990-07-24 Timet High strength alpha-beta titanium-base alloy
US5980655A (en) * 1997-04-10 1999-11-09 Oremet-Wah Chang Titanium-aluminum-vanadium alloys and products made therefrom
RU2150528C1 (ru) * 1999-04-20 2000-06-10 ОАО Верхнесалдинское металлургическое производственное объединение Сплав на основе титана
RU2169204C1 (ru) * 2000-07-19 2001-06-20 ОАО Верхнесалдинское металлургическое производственное объединение Сплав на основе титана и способ термической обработки крупногабаритных полуфабрикатов из этого сплава
RU2192493C2 (ru) * 2000-12-19 2002-11-10 Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов Сплав на основе титана и изделие, выполненное из него

Also Published As

Publication number Publication date
EP1577409A1 (fr) 2005-09-21
WO2004048627A1 (fr) 2004-06-10
DK1577409T3 (da) 2008-02-18
HK1079826A1 (en) 2006-04-13
DE60317708D1 (de) 2008-01-03
ES2293095T3 (es) 2008-03-16
DE60317708T2 (de) 2008-10-30
US20060115374A1 (en) 2006-06-01
HK1079826B (zh) 2008-05-02
EP1577409A4 (fr) 2006-08-16
RU2228966C1 (ru) 2004-05-20
AU2003261684A1 (en) 2004-06-18

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