EP1052298A1 - Kriechbestängige Titanaluminid-Legierung des Gamma-Typs - Google Patents

Kriechbestängige Titanaluminid-Legierung des Gamma-Typs Download PDF

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Publication number
EP1052298A1
EP1052298A1 EP00109140A EP00109140A EP1052298A1 EP 1052298 A1 EP1052298 A1 EP 1052298A1 EP 00109140 A EP00109140 A EP 00109140A EP 00109140 A EP00109140 A EP 00109140A EP 1052298 A1 EP1052298 A1 EP 1052298A1
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EP
European Patent Office
Prior art keywords
weight
carbon
titanium aluminide
amount
composition
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Application number
EP00109140A
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English (en)
French (fr)
Inventor
Donald E. Larsen
Paul A. Mcquay
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Howmet Corp
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Howmet Research Corp
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Publication date
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Publication of EP1052298A1 publication Critical patent/EP1052298A1/de
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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 present invention relates to titanium aluminum alloys and, more particularly, to gamma and near gamma titanium aluminides having dramatically improved creep resistance at elevated temperature.
  • the '615 patent identifies V as an alloying element for improving low temperature ductility and Nb, Bi, and C as alloying elements for improving creep rupture resistance. If improved creep rupture life is desired, the alloy is forged and annealed at 1100 to 1200 degrees C followed by aging at 815 to 950 degrees C.
  • An object of the present invention is to provide a gamma and near gamma titanium aluminide with carbon content controlled in a range discovered to unexpectedly and significantly increase creep resistance at elevated temperature.
  • the present invention provides in one embodiment a gamma and near gamma titanium aluminide including a carbon concentration controlled in an amount of at least about 0.03 weight % C effective to surprisingly and unexpectedly increase high temperature creep resistance by approximately 10 times as compared to similar materials devoid of carbon.
  • the present invention provides in another embodiment a titanium aluminide composition
  • a titanium aluminide composition comprising titanium in the range of about 53 to about 64 weight % and aluminum in the range of about 29.5 to about 38 weight % wherein carbon is included and controlled in the composition in an amount of about 0.03 weight % to about 0.33 weight % to increase high temperature creep resistance.
  • a preferred titanium aluminide composition in accordance with the invention consists essentially of, in weight %, about 60.0% to about 63.5% Ti, about 29.5% to about 33.0% Al alloyed with one or more elements selected from Cr, Ga, Mo, Mn, Nb, Ni, Si, Zr, Ta, V and W each in amount of at least about 0.1 weight %, carbon controlled as described above and including strengthening dispersoids present in an amount of at least about 0.5 volume %.
  • a more preferred titanium aluminide composition in accordance with the invention consists essentially of, in weight %, about 31.5% to about 32.5% Al, about 4.0% to about 5.5% Nb, about 1.5% to about 3.0% Mn, about 0.2% to about 0.4% B, and about 0.04% to about 0.1% C and balance essentially Ti.
  • Another more preferred titanium aluminide composition in accordance with the invention consists essentially of, in weight %, about 29.8% to about 31.2% Al, about 4.0% to about 5.2% Nb, about 1.5% to about 3.0% Mn, about 0.25% to about 0.37% B, and about 0.04% to about 0.1% C and balance essentially Ti.
  • the composition can be investment cast, permanent mold cast, and vacuum die cast and heat treated alloy to provide a microstructure comprising predominantly gamma (TiAl) phase and a minor amount (e.g about 5 to about 20 volume %) of alpha-2 (Ti 3 Al) phase.
  • TiAl gamma
  • Ti 3 Al alpha-2
  • the present invention provides in one embodiment a titanium aluminide composition
  • a titanium aluminide composition comprising titanium in the range of about 53 to about 64 weight % and aluminum in the range of about 29.5 to about 38 weight % wherein carbon is included and controlled in the alloy composition in an amount of at least about 0.03 weight % C, preferably about 0.04 to about 0.33 weight % C, and more preferably about 0.04 to about 0.1 weight % C, to increase high temperature creep resistance by approximately 10 times as compared to similar composition devoid of carbon.
  • a preferred titanium aluminide composition in accordance with the invention consists essentially of, in weight %, about 60.0% to about 63.5% Ti, about 29.5% to about 33.0% Al alloyed with one or more alloying elements selected from Cr, Ga, Mo, Mn, Nb, Ni, Si, Zr, Ta, V and W each in amount of at least about 0.1 weight %, about 0.03% to 0.33% C, and including strengthening dispersoids present in an amount of at least about 0.5 volume %.
  • carbon-modified titanium aluminide alloy base compositions comprising 47 atomic % Al, 2 atomic % Mn, 2 atomic % Nb, and balance Ti with 0.8 volume % TiB 2 dispersoids was prepared as cylindrical specimen bars (dimensions of 5/8 inch diameter and length of 8 inches) by vacuum arc melting a master heat of the alloy composition that included 0.8 volume % TiB 2 dispersoids pursuant to US Patents 5 284 620 and 5 429 796, the teachings of which are incorporated herein by reference to this end.
  • Other melting techniques such as vacuum induction melting, induction skull melting, and plasma arc melting also can be used to melt the master heat.
  • the dispersoids can be provided in the master heat by adding an appropriate amount of a 95 weight % Al-5 weight % B alloy to the heat.
  • the master heat was melted at less than 20 microns atmosphere and then cast at a superheat of about 50 degrees F into an investment mold.
  • the carbon content of the specimen bars was controlled by melt addition of premeasured Al 4 C 3 to provide aim carbon concentrations of 0%, 0.04%, 0.07% and 0.11% (weight %) of the base alloy compositions for tensile and creep testing.
  • the composition having nominal carbon content of 0.006 weight % C was considered and designated the 47XD baseline composition.
  • Table 1 below sets forth the titanium aluminide compositions studied with the actual carbon concentrations set forth.
  • the as-cast microstructure of the specimen bars having the aforementioned carbon contents were similar and comprised a lamellar structure containing laths of gamma phase and alpha-2 phase present as a minor phase. Since carbon solubility in both the alpha-2 phase and gamma phase is fairly low (e.g. less than 0.1 atomic %), the carbon forms fine (less than 1 micron particle diameter) carbide precipitates throughout the as-cast microstructure primarily at the grain boundaries and lamellar interfaces.
  • Such carbide precipitates have been found to increase room and elevated temperature strength and creep resistance of the alloy in the as-hot isostatically pressed (HIP'ed) condition and as-heat treated.
  • test specimens for tensile testing and creep testing were machined from cast and HIP'ed specimen bars.
  • the tensile and creep test specimens were machined and tested in accordance with ASTM test standard E8.
  • the cast test specimens were hot isostatically pressed at 2300 degrees F and argon pressure of 20 ksi for 4 hours. Then, the test specimens were heat treated at 1800 degrees F for 50 hours in an argon atmosphere and allowed to furnace cool to ambient by furnace power shut-off.
  • the heat treated microstructure of the test specimens having the aforementioned carbon contents were similar with both lamellar and equiaxed grains and comprised predominantly gamma phase (TiAl) and a minor amount (e.g. 5 volume %) of alpha-2 phase.
  • the tensile strength increased with carbon content from 74 ksi for the 47XD baseline alloy up to 89 ksi for the 0.11 weight % C 47XD alloy.
  • a similar increase in strength was seen in the 650 degrees C tensile tests.
  • Room temperature ductility decreased with carbon content from 1.2% elongation for the 47XD baseline alloy to 0.3% elongation for the 0.11 weight % C XD47 alloy.
  • the room temperature ductility of the 47XD baseline alloy typically is in the range of 1.2 to 1.4% elongation.
  • Heat treated specimens were subjected to steady state creep testing in accordance with ASTM test standard E8 at 649 degrees C and test stress of 276 MPa and at 760 degrees C and 815 degrees C and test stress of 138 MPa, Figure 3. The time to reach 0.5% elongation was measured, Figure 3.
  • the titanium aluminide compositions of the invention can be produced by traditional ingot production methods, including, but not limited to, VAR (vacuum arc remelting) or PAM (plasma arc melting). Components can be produced from these alloys via a variety of methods including traditional cast, wrought, or powder metallurgy methods, with the preferred methods including investment casting, permanent mold casting, and vacuum die casting.
  • VAR vacuum arc remelting
  • PAM plasma arc melting

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00109140A 1999-05-10 2000-05-05 Kriechbestängige Titanaluminid-Legierung des Gamma-Typs Withdrawn EP1052298A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US30788299A 1999-05-10 1999-05-10
US307882 1999-05-10

Publications (1)

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EP1052298A1 true EP1052298A1 (de) 2000-11-15

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JP (1) JP2000345259A (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003074210A3 (de) * 2002-03-07 2004-04-29 Mtu Aero Engines Gmbh Verfahren und vorrichtung zur massgenauen feingussherstellung von bauteilen aus ne-metalllegierungen sowie ne-metalllegierungen zur durchführung des verfahrens
EP2657358A1 (de) * 2012-03-24 2013-10-30 General Electric Company Titanaluminidzusammensetzungen
CN103757571A (zh) * 2014-01-24 2014-04-30 中国科学院金属研究所 片层界面择优定向的γ-TiAl合金细小全片层组织制备方法
CN107604210A (zh) * 2017-11-23 2018-01-19 宁国市华成金研科技有限公司 一种耐高温钛合金板
CN111809080A (zh) * 2020-06-23 2020-10-23 中国科学院金属研究所 一种tc2合金薄壁挤压型材的制备方法
EP3943208A4 (de) * 2019-03-18 2022-11-09 IHI Corporation Titan-aluminid-legierungsmaterial zum warmschmieden und verfahren zum schmieden von titan-aluminid-legierungsmaterial

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015119927A1 (en) * 2014-02-05 2015-08-13 Borgwarner Inc. TiAl ALLOY, IN PARTICULAR FOR TURBOCHARGER APPLICATIONS, TURBOCHARGER COMPONENT, TURBOCHARGER AND METHOD FOR PRODUCING THE TiAl ALLOY

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4294615A (en) * 1979-07-25 1981-10-13 United Technologies Corporation Titanium alloys of the TiAl type
US4916028A (en) * 1989-07-28 1990-04-10 General Electric Company Gamma titanium aluminum alloys modified by carbon, chromium and niobium
US5429796A (en) * 1990-12-11 1995-07-04 Howmet Corporation TiAl intermetallic articles
JPH09176763A (ja) * 1995-12-26 1997-07-08 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4294615A (en) * 1979-07-25 1981-10-13 United Technologies Corporation Titanium alloys of the TiAl type
US4916028A (en) * 1989-07-28 1990-04-10 General Electric Company Gamma titanium aluminum alloys modified by carbon, chromium and niobium
US5429796A (en) * 1990-12-11 1995-07-04 Howmet Corporation TiAl intermetallic articles
JPH09176763A (ja) * 1995-12-26 1997-07-08 Mitsubishi Heavy Ind Ltd ＴｉＡｌ系金属間化合物基合金

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 1997, no. 11 28 November 1997 (1997-11-28) *

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003074210A3 (de) * 2002-03-07 2004-04-29 Mtu Aero Engines Gmbh Verfahren und vorrichtung zur massgenauen feingussherstellung von bauteilen aus ne-metalllegierungen sowie ne-metalllegierungen zur durchführung des verfahrens
EP2657358A1 (de) * 2012-03-24 2013-10-30 General Electric Company Titanaluminidzusammensetzungen
US10597756B2 (en) 2012-03-24 2020-03-24 General Electric Company Titanium aluminide intermetallic compositions
CN103757571A (zh) * 2014-01-24 2014-04-30 中国科学院金属研究所 片层界面择优定向的γ-TiAl合金细小全片层组织制备方法
CN107604210A (zh) * 2017-11-23 2018-01-19 宁国市华成金研科技有限公司 一种耐高温钛合金板
EP3943208A4 (de) * 2019-03-18 2022-11-09 IHI Corporation Titan-aluminid-legierungsmaterial zum warmschmieden und verfahren zum schmieden von titan-aluminid-legierungsmaterial
US12221683B2 (en) 2019-03-18 2025-02-11 Ihi Corporation Titanium aluminide alloy material for hot forging and forging method for titanium aluminide alloy material
CN111809080A (zh) * 2020-06-23 2020-10-23 中国科学院金属研究所 一种tc2合金薄壁挤压型材的制备方法
CN111809080B (zh) * 2020-06-23 2022-07-26 中国科学院金属研究所 一种tc2合金薄壁挤压型材的制备方法

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