US3619184A - Balanced titanium alloy - Google Patents

Balanced titanium alloy Download PDF

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Publication number
US3619184A
US3619184A US713214A US3619184DA US3619184A US 3619184 A US3619184 A US 3619184A US 713214 A US713214 A US 713214A US 3619184D A US3619184D A US 3619184DA US 3619184 A US3619184 A US 3619184A
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percent
creep
alloy
molybdenum
zirconium
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US713214A
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Howard B Bomberger Jr
Stanley R Seagle
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RMI Co
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RMI Co
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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

Definitions

  • the natural crystallographic grouping of titanium and its alloys involves three categories divided according to the predominant phase or phases in their microstructure. These groups are alpha, beta and mixed alpha and beta phases.
  • the alpha phase which is characterized by a hexagonal, close-packed crystallographic structure is stable from room temperature to approximately l,620 F.
  • the beta phase of pure titanium has a body-centered cubic structure and is stable from approximately l,620 F. to the melting point of about 3,035 F.-
  • the hexagonal, close-packed allotrope of titanium i.e. the alpha phase
  • the hexagonal, close-packed allotrope of titanium i.e. the alpha phase
  • Solid solution strengthening of the alpha phase by the addition of aluminum, tin and zirconium has resulted in alloys with still better resistance to creep defonnation.
  • further improvements by the addition of such alpha stabilizers is restricted due to poor thermal stability of compositions containing too great a quantity of such elements as manifested by lower ductility after creep exposure.
  • the present invention provides a balanced titanium alloy composition which possesses improved creep strength without undue sacrifice of thermal stability or ductility after creep exposure.
  • a titanium alloy consisting essentially of4.0 to 7.8 percent aluminum, up to I20 percent tin, at least 0.3 percent zirconium, traces to 0.5 percent silicon and at least one stabilizer from the group consisting of molybdenum, columbium, tantalum, vanadium and tungsten, the quantity of aluminum, tin and zirconium complying with the equation:
  • a preferred alloy in accordance with the invention contains 4.0 to 7.0 percent aluminum, 0.3 to 7.0 percent zirconium, 2.0 to 8.0 percent tin, 0.1 to 0.35 percent silicon and 0.1 to 1.2 percent of at least one stabilizer from the group consisting of molybdenum, columbium, tantalum, vanadium and tungsten.
  • Optimum properties have been found to be associated with a composition within the melting range 4.7 to 5.3 percent aluminum, 5.5 to 6.5 percent tin, 0.5 to 2.5 percent zirconium, 0.4 to 1.1 percent molybdenum, 0.2 to 0.3 percent silicon, more specifically having the nominal composition of 5.0 percent aluminum, 6.0 percent tin, 2.0 percent zirconium, 0.8 percent molybdenum and 0.25 percent silicon.
  • alloys in accordance with the invention contain 4.0 to 7.8 percent aluminum. if the upper aluminum limit is exceeded, the alloy becomes thermally unstable; similarly, a minimum of 4.0 percent aluminum is necessary to achieve acceptable mechanical properties. Zirconium has been found to enhance the creepstrengthening efi'ect of silicon and at least 0.3 percent zirconium is necessary for this purpose.
  • Zirconium-containing alloys result in the formation of a complex compound of titanium, zirconium and silicon instead of normal titanium silicide which would form in the absence of zirconium. Some silicon is, of course, necessary for creep strengthening. However, amounts in excess of 0.5 percent are avoided to avoid ductility problems. Tin may act as a replacement for aluminum, at least in part, and is desirable, but not absolutely necessary, since it further assists in assuring thermal stability. However, over l2.0 percent tin increases the tendency toward thermal instability.
  • a critically controlled quantity of at least one stabilizer from the group consisting of molybdenum, columbium, tantalum, vanadium and tungsten is necessary in balancing the alpha-stabilizing components to assure additional high-temperature strength while imparting thermal stability which is particularly beneficial for alloys processed or heat treated above the beta transus.
  • a discovery in accordance with the invention is that the addition of the stabilizers must not exceed the alpha-solubility limit for the particular stabilizer. If the alphasolubility is exceeded, some beta phase may form that would result in a significant less of strength which may be accompanied by a loss of high-temperature stability as well.
  • Alloy No. 4 possesses good tensile ductility after creep exposure while Alloy No. 3 is brittle.
  • the amounts of molybdenum and silicon added to the alloy are important in optimizing the creep strength with post creep tensile ductility.
  • the creep strength of Alloy No. in table 1 compared with Alloy Nos. 2 and 3 indicates that the combination of beta stabilizers plus silicon, e.g. molybdenum plus silicon, even at lower silicon contents, is superior.
  • the influence of the stabilizers, in this case molybdenum is shown by comparing Alloy No. 3 with Alloy Nos. 4, 6 and 7 7 in table 1.
  • the slight addition of 0.4 percent molybdenum is sufficient to impart improved creep strength. With 0.8 percent molybdenum, the excellent creep strength is still maintained.
  • zirconium in the alloy system in accordance with the invention is shown in the examples in table lV. With zirconium, higher creep resistance is obtained. The zirconium addition results in the formation of a complex (TiZr) Si compound which benefits creep resistance. Thus, a complex (TiZr) Si compound which benefits creep resistance.
  • optimum creep strength is achieved by beta processing or heat treatment, and in this connection, the balanced composition of the invention is a particular advance over present commercially available materials.
  • optimum yield strength in titanium alloys of the type described is developed by processing, e.g. heat treating, in such a manner so as to avoid the formation of a transformed beta structure.
  • a typical process to develop optimum yield strength involves (1) working to an end temperature below the beta transus temperature or (2) working to an end temperature below the beta transus temperature plus a heat treatment below that temperature.
  • M0 molybdenum content or molybdenum equivalency of other stabilizers, i.e. columbium, tantalum, vanadium and tungsten.
  • Molybdenum equivalency is expressed by the equation:
  • Creep and stability according to the equations A and B above are determined by testing specimens at 950 F, under with respect to aluminum and tin on creep strength and thermal stability.
  • the graph is related to a base composition of Ti- XAl-YSn-2Zr-0.8Mo-0.25Si based upon an instability threshold of less than 8 where the aluminum, tin and zirconium, ie the alpha stabilizers, are related by the equation:
  • the sloping line represents the tin content for different aluminum levels at which the loss of ductility is disproportionately greater with increase in creep strength, that is, the point at which the equations discussed above are no longer applicable.
  • a titanium-base alloy consisting essentially of about 4.7 to 5.3 percent aluminum, 5.5 to 6.5 percent tin, 0.5 to 2.5 percent zirconium, 0.4 to 1.1 percent molybdenum, 0.2 to 0.3 percent silicon, and the balance titanium and incidental impurities, said alloy being characterized by improved creep strength without undue sacrifice of thermal stability or ductility after creep exposure.
  • a titanium alloy In accordance with claim 1 containing 5.0 percent aluminum, 6.0 percent tin, 2.0 percent zirconium, 0.8 percent molybdenum and 0.25 percent silicon.
  • a titanium alloy in accordance with claim 1 additionally containing 0.53 to 1.33 percent vanadium.
  • a titanium alloy in accordance with claim I additionally containing 0.8 to 2.0 percent tungsten t a a t UNITED STATES PATENT OFFIGE CERTIFICATE OF CORRECTION Patent No. 3,619,184 Dated November 9, 1971 Inventor(s) Howard B. Bomberqer, Jr, et a1 It is certified that error appears in the above-identified patent and that: said Letters Patent are hereby corrected as shown below:

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Compounds Of Heavy Metals (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
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US713214A 1968-03-14 1968-03-14 Balanced titanium alloy Expired - Lifetime US3619184A (en)

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DE (1) DE1913142A1 (enrdf_load_stackoverflow)
FR (1) FR2003910A1 (enrdf_load_stackoverflow)
GB (1) GB1264891A (enrdf_load_stackoverflow)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3833363A (en) * 1972-04-05 1974-09-03 Rmi Co Titanium-base alloy and method of improving creep properties
DE2620311A1 (de) * 1975-05-07 1976-11-18 Imp Metal Ind Kynoch Ltd Titanlegierung
US4229216A (en) * 1979-02-22 1980-10-21 Rockwell International Corporation Titanium base alloy
US4606886A (en) * 1983-12-10 1986-08-19 Imi Titanium Limited Titanium-base alloy
US4738822A (en) * 1986-10-31 1988-04-19 Titanium Metals Corporation Of America (Timet) Titanium alloy for elevated temperature applications
EP0611831A1 (en) * 1993-02-17 1994-08-24 Warren M. Parris Titanium alloy for plate applications
US6531091B2 (en) * 2000-02-16 2003-03-11 Kobe Steel, Ltd. Muffler made of a titanium alloy
US20110097501A1 (en) * 2004-03-22 2011-04-28 Lanxide Technology Company Methods for extracting titanium metal and useful alloys from titanium oxides
CN103014412A (zh) * 2011-09-27 2013-04-03 什邡市明日宇航工业股份有限公司 一种复合耐热钛合金
CN103014413A (zh) * 2011-09-27 2013-04-03 什邡市明日宇航工业股份有限公司 一种复合强化耐热钛合金
JP2014058740A (ja) * 2012-07-19 2014-04-03 Rti Internat Metals Inc 高温において良好な耐酸化性と高い強度を有するチタン合金
US20140295988A1 (en) * 2013-04-01 2014-10-02 Acushnet Company Golf club head with improved striking face
US10041150B2 (en) 2015-05-04 2018-08-07 Titanium Metals Corporation Beta titanium alloy sheet for elevated temperature applications
US11421303B2 (en) 2017-10-23 2022-08-23 Howmet Aerospace Inc. Titanium alloy products and methods of making the same

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2893864A (en) * 1958-02-04 1959-07-07 Harris Geoffrey Thomas Titanium base alloys
US3049425A (en) * 1958-11-14 1962-08-14 Ici Ltd Alloys
US3061427A (en) * 1960-04-28 1962-10-30 Titanium Metals Corp Alloy of titanium
GB944954A (en) * 1959-10-31 1963-12-18 Jessop William & Sons Ltd Improvements in or relating to titanium alloys
GB1049210A (en) * 1963-10-17 1966-11-23 Continental Titanium Metals Co Titanium base alloys
FR1477221A (fr) * 1966-04-25 1967-04-14 Birmingham Small Arms Co Ltd Alliages à base de titane
FR1486765A (fr) * 1965-07-14 1967-06-30 Imp Metal Ind Kynoch Ltd Alliage à base de titane
US3333995A (en) * 1963-12-05 1967-08-01 Titanium Metals Corp Processing titanium alloy sheet products
GB1079416A (en) * 1965-07-14 1967-08-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys
US3343951A (en) * 1963-10-17 1967-09-26 Titanium Metals Corp Titanium base alloy
US3378368A (en) * 1965-01-04 1968-04-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2893864A (en) * 1958-02-04 1959-07-07 Harris Geoffrey Thomas Titanium base alloys
US3049425A (en) * 1958-11-14 1962-08-14 Ici Ltd Alloys
US3105759A (en) * 1958-11-14 1963-10-01 Ici Ltd Titanium-base alloys
GB944954A (en) * 1959-10-31 1963-12-18 Jessop William & Sons Ltd Improvements in or relating to titanium alloys
US3061427A (en) * 1960-04-28 1962-10-30 Titanium Metals Corp Alloy of titanium
GB1049210A (en) * 1963-10-17 1966-11-23 Continental Titanium Metals Co Titanium base alloys
US3343951A (en) * 1963-10-17 1967-09-26 Titanium Metals Corp Titanium base alloy
US3333995A (en) * 1963-12-05 1967-08-01 Titanium Metals Corp Processing titanium alloy sheet products
US3378368A (en) * 1965-01-04 1968-04-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys
FR1486765A (fr) * 1965-07-14 1967-06-30 Imp Metal Ind Kynoch Ltd Alliage à base de titane
GB1079416A (en) * 1965-07-14 1967-08-16 Imp Metal Ind Kynoch Ltd Titanium-base alloys
FR1477221A (fr) * 1966-04-25 1967-04-14 Birmingham Small Arms Co Ltd Alliages à base de titane

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3833363A (en) * 1972-04-05 1974-09-03 Rmi Co Titanium-base alloy and method of improving creep properties
USRE29946E (en) * 1972-04-05 1979-03-27 Rmi Company Titanium-base alloy and method of improving creep properties
DE2620311A1 (de) * 1975-05-07 1976-11-18 Imp Metal Ind Kynoch Ltd Titanlegierung
US4087292A (en) * 1975-05-07 1978-05-02 Imperial Metal Industries (Kynoch) Limited Titanium base alloy
US4229216A (en) * 1979-02-22 1980-10-21 Rockwell International Corporation Titanium base alloy
US4606886A (en) * 1983-12-10 1986-08-19 Imi Titanium Limited Titanium-base alloy
US4738822A (en) * 1986-10-31 1988-04-19 Titanium Metals Corporation Of America (Timet) Titanium alloy for elevated temperature applications
EP0611831A1 (en) * 1993-02-17 1994-08-24 Warren M. Parris Titanium alloy for plate applications
US5358686A (en) * 1993-02-17 1994-10-25 Parris Warren M Titanium alloy containing Al, V, Mo, Fe, and oxygen for plate applications
US6531091B2 (en) * 2000-02-16 2003-03-11 Kobe Steel, Ltd. Muffler made of a titanium alloy
US20110097501A1 (en) * 2004-03-22 2011-04-28 Lanxide Technology Company Methods for extracting titanium metal and useful alloys from titanium oxides
CN103014412A (zh) * 2011-09-27 2013-04-03 什邡市明日宇航工业股份有限公司 一种复合耐热钛合金
CN103014413A (zh) * 2011-09-27 2013-04-03 什邡市明日宇航工业股份有限公司 一种复合强化耐热钛合金
JP2014058740A (ja) * 2012-07-19 2014-04-03 Rti Internat Metals Inc 高温において良好な耐酸化性と高い強度を有するチタン合金
US20150192031A1 (en) * 2012-07-19 2015-07-09 Rti International Metals, Inc. Titanium alloy having good oxidation resistance and high strength at elevated temperatures
US9957836B2 (en) * 2012-07-19 2018-05-01 Rti International Metals, Inc. Titanium alloy having good oxidation resistance and high strength at elevated temperatures
US20140295988A1 (en) * 2013-04-01 2014-10-02 Acushnet Company Golf club head with improved striking face
US20150360093A1 (en) * 2013-04-01 2015-12-17 Acushnet Company Golf club head with improved performance
US9433835B2 (en) * 2013-04-01 2016-09-06 Acushnet Company Golf club head with improved striking face
US9700766B2 (en) * 2013-04-01 2017-07-11 Acushnet Company Golf club head with improved striking face
US10041150B2 (en) 2015-05-04 2018-08-07 Titanium Metals Corporation Beta titanium alloy sheet for elevated temperature applications
US11421303B2 (en) 2017-10-23 2022-08-23 Howmet Aerospace Inc. Titanium alloy products and methods of making the same

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DE1913142A1 (de) 1969-10-16
GB1264891A (enrdf_load_stackoverflow) 1972-02-23
FR2003910A1 (enrdf_load_stackoverflow) 1969-11-14

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