EP0455005B1 - Alliage réfractaire pour organes de machine, basé sur l'aluminiure de titane dopé - Google Patents

Alliage réfractaire pour organes de machine, basé sur l'aluminiure de titane dopé Download PDF

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Publication number
EP0455005B1
EP0455005B1 EP91105503A EP91105503A EP0455005B1 EP 0455005 B1 EP0455005 B1 EP 0455005B1 EP 91105503 A EP91105503 A EP 91105503A EP 91105503 A EP91105503 A EP 91105503A EP 0455005 B1 EP0455005 B1 EP 0455005B1
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EP
European Patent Office
Prior art keywords
alloy
room temperature
melted
atom
mpa
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EP91105503A
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German (de)
English (en)
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EP0455005A1 (fr
Inventor
Mohamed Dr. Nazmy
Markus Staubli
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Alstom SA
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ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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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 invention relates to a high-temperature alloy for a mechanically highly stressed component of a thermal machine based on doped titanium aluminide.
  • Intermetallic compounds of titanium with aluminum have some interesting properties which make them appear attractive as construction materials in the medium and higher temperature range. Among other things, this includes their low density compared to superalloys, which only reaches approx. 1/2 of the value for Ni superalloys. Their technical usability in the present form stands in the way of their brittleness. The former can be improved by additives, whereby higher strength values are also achieved. As possible and in part already introduced intermetallic compounds, among others, nickel aluminides, nickel silicides and titanium aluminides are known as construction materials.
  • a heat-resistant alloy based on doped titanium aluminide is described in EP-A-0 363 598.
  • this alloy has 29 to 35 percent by weight Al, 0.5 to 20 percent by weight niobium, 0.1 to 1.8 percent by weight silicon and / or 0.3 to 5.5 percent by weight zirconium. From the strength curves It can be seen from FIG. 5 that this alloy has only an insignificantly greater strength than undoped titanium aluminide if, in the absence of zirconium, the niobium content is relatively high (e.g. alloys 30, 31) or the silicon content is relatively low (e.g. alloy 18) and in the absence of silicon, the zirconium content is relatively high.
  • This alloy generally has high strengths in the absence of zirconium with a silicon content between 0.97 and 1.36 percent by weight, corresponding to approximately 1.3 to 1.9 atom percent, and in the absence of silicon with relatively high zirconium contents. The ductility is then rather low.
  • US Pat. No. 3,203,794 discloses high-temperature alloys based on doped titanium aluminide. Ag, B, Be, C, Nb, Cr, Cu, Fe, In, Mn, N, Ni, O, Pb, Sn, Si, Ta, Te, W and Zr are provided as dopants. These dopants generally increase the hardness compared to the undoped titanium aluminide.
  • the invention is based on the object of creating an alloy based on doped titanium aluminide which, due to its high strength and hardness, also in the temperature range between 500 and 1000 ° C. and the best possible ductility Room temperature.
  • the alloy according to the invention has excellent strength and hardness properties. By alloying a not too high proportion of silicon, germanium or boron, an improved ductility is achieved compared to titanium aluminide, which contains predominantly high silicon contents or relatively high zirconium contents in the absence of silicon.
  • alloys 11, 28, 30 and 31 serve as comparison alloys.
  • the alloy compositions are as follows: alloy Components in at% Al Ge Si B Me Ti 11 48 - - - W rest 12th 48 0.5 - - W rest 13 48 - 0.5 - W rest 28 48 - - - Y rest 29 48 - - 0.5 Y rest 30th 48 2nd - - Zr rest 31 48 - - - Y rest 32 48 - - 0.5 Y rest 40 48 - - 0.5 W rest 41 48 - - 1 W rest
  • the bars were processed directly into pressure samples for short-term tests without subsequent heat treatment.
  • a further improvement of the mechanical properties through a suitable heat treatment is within the realm of possibility. There is also the possibility of improvement through directional solidification, for which the alloy is particularly suitable.
  • the melt was poured off as in Example 1, melted again under argon and cast into prisms of square cross section (7 mm ⁇ 7 mm ⁇ 80 mm). Test specimens for pressure, hardness and impact tests were produced from these prisms. The course of the mechanical properties corresponded approximately to that of the previous examples. The yield point ⁇ 0.2 at room temperature was 582 Mpa. The course over the temperature T is indicated in FIG. 5.
  • Alloy 1 (pure TiAl) is shown as the reference quantity.
  • the course over the temperature T is shown in Fig. 1.
  • Alloy 1 (pure TiAl) is to be given as the reference quantity. Heat treatment resulted in a further improvement in these values.
  • the yield point ⁇ 0.2 at room temperature was 578 MPa.
  • the course of the flow limit over the temperature T is plotted in FIG. 5.
  • the Vickers hardness HV at room temperature reached 350 units. Their course over the temperature T is recorded in Fig. 1.
  • the hardness-increasing effect of the combined W and Si additives compared to pure TiAl must be noted. In the present case, it averages 75%.
  • the yield point ⁇ 0.2 at room temperature was 572 MPa (Fig. 5).
  • the Vickers hardness HV reached the value of 347 units at room temperature (FIG. 1).
  • the yield point ⁇ 0.2 at room temperature was 550 MPa (Fig. 5).
  • the bars were processed directly into pressure samples for short-term tests without subsequent heat treatment.
  • the mechanical properties achieved were measured as a function of the test temperature.
  • a further improvement of the mechanical properties through a suitable heat treatment is within the realm of possibility. There is also the possibility of improvement by directional solidification, for which the alloy is particularly suitable.
  • the yield point ⁇ 0.2 at room temperature was 512 MPa (Fig. 6).
  • the Vickers hardness HV reached the value of 310 units at room temperature (FIG. 2).
  • the yield point ⁇ 0.2 at room temperature was 426 MPa (Fig. 6).
  • the yield point ⁇ 0.2 at room temperature reached 416 MPa (Fig. 7).
  • the Vickers hardness HV at room temperature corresponded to 252 units (Fig. 3).
  • the yield point ⁇ 0.2 at room temperature gave an average value of 488 MPa (Fig. 7).
  • the Vickers hardness HV at room temperature resulted in 296 units (FIG. 3).
  • the increase in hardness is associated with a more or less severe loss of ductility, which can, however, at least partially be compensated for by adding further elements which increase the toughness.
  • the addition of less than 0.5 at.% Of an element is usually hardly effective.
  • B generally has a strong toughness-increasing effect in combination with other strength-increasing elements. See Fig. 10.
  • the loss of ductility caused by alloying Y could be practically compensated for by adding only 0.5 at.% B. Additions higher than 1 at.% B are not necessary.
  • Ge looks similar to B but is much weaker. Additions of more than 2 at.% Ge in the presence of further elements are of little use. For further optimization of the properties there are polynary systems, in which an attempt is made to make up for the negative properties of individual additions by simultaneously alloying other elements.
  • the area of application of the modified titanium aluminides advantageously extends to temperatures between 600 ° C. and 1000 ° C.
  • the melt was poured into a cast blank of approximately 60 mm in diameter and approximately 80 mm in height. The blank was melted again under protective gas and also forced to solidify in the form of rods with a diameter of approximately 12 mm and a length of approximately 80 mm under protective gas.
  • the bars were processed directly into pressure samples for short-term tests without subsequent heat treatment.
  • a further improvement of the mechanical properties through a suitable heat treatment is within the realm of possibility. There is also the possibility of improvement through directional solidification, for which the alloy is particularly suitable.
  • the melt was poured off analogously to embodiment 61, melted again under argon and forced to solidify in the form of a rod.
  • the dimensions of the rods corresponded to the exemplary embodiment 61.
  • the rods were processed directly into pressure samples without subsequent heat treatment.
  • the values of the mechanical properties achieved as a function of the test temperature are shown in FIGS. 4 and 8. These values can be further improved by heat treatment.
  • the Vickers hardness HV at room temperature was 329 units.
  • the yield point ⁇ 0.2 at room temperature reached 543 MPa.
  • the strength and hardness increasing effect of the W additive is clearly visible.
  • the range of use of the modified tianaluminides advantageously extends to temperatures between 600 ° C. and 1000 ° C.

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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)
  • Luminescent Compositions (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)

Claims (1)

  1. Alliage réfractaire pour un organe soumis à de fortes sollicitations mécaniques d'une machine thermique à base de TiAl dopé, ayant la composition suivante:



            TixElyMezAl1-(x+y+z),



    El = B, Ge ou Si et Me signifiant Cr, Mn, Nb, Pd, Ta, W, Y, Zr, et avec:
    0,46 ≦ x ≦ 0,54
    0,001 ≦ y ≦ 0,015 pour El = Si et Me = W
    0,001 ≦ y ≦ 0,015 pour El = Ge et Me = Cr, Ta, W
    0 < y ≦ 0,02 pour El = Ge et Me = Pd, Y, Zr
    0,0001 ≦ y ≦ 0,01 pour El = B et Me = Cr, Mn, Nb, Y, W
    0,01 ≦ z ≦ 0,04 pour le cas où Me = élément individuel,
    0,01 < z ≦ 0,08 pour le cas où Me représente deux éléments individuels ou plus et
    0,46 ≦ (x+y+z) ≦ 0,54.
EP91105503A 1990-05-04 1991-04-08 Alliage réfractaire pour organes de machine, basé sur l'aluminiure de titane dopé Expired - Lifetime EP0455005B1 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
CH152390 1990-05-04
CH1524/90 1990-05-04
CH152490 1990-05-04
CH1523/90 1990-05-04
CH1616/90 1990-05-11
CH161690 1990-05-11

Publications (2)

Publication Number Publication Date
EP0455005A1 EP0455005A1 (fr) 1991-11-06
EP0455005B1 true EP0455005B1 (fr) 1995-09-13

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EP91105503A Expired - Lifetime EP0455005B1 (fr) 1990-05-04 1991-04-08 Alliage réfractaire pour organes de machine, basé sur l'aluminiure de titane dopé

Country Status (6)

Country Link
US (3) US5207982A (fr)
EP (1) EP0455005B1 (fr)
JP (1) JPH05230568A (fr)
AT (1) ATE127860T1 (fr)
DE (1) DE59106459D1 (fr)
RU (1) RU1839683C (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10054229B4 (de) 2000-11-02 2018-06-28 Ansaldo Energia Ip Uk Limited Hochtemperaturlegierung

Families Citing this family (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5098653A (en) * 1990-07-02 1992-03-24 General Electric Company Tantalum and chromium containing titanium aluminide rendered castable by boron inoculation
US5080860A (en) * 1990-07-02 1992-01-14 General Electric Company Niobium and chromium containing titanium aluminide rendered castable by boron inoculations
JP2678083B2 (ja) * 1990-08-28 1997-11-17 日産自動車株式会社 Ｔｉ―Ａｌ系軽量耐熱材料
US5131959A (en) * 1990-12-21 1992-07-21 General Electric Company Titanium aluminide containing chromium, tantalum, and boron
US5204058A (en) * 1990-12-21 1993-04-20 General Electric Company Thermomechanically processed structural elements of titanium aluminides containing chromium, niobium, and boron
US5354351A (en) * 1991-06-18 1994-10-11 Howmet Corporation Cr-bearing gamma titanium aluminides and method of making same
US5370839A (en) * 1991-07-05 1994-12-06 Nippon Steel Corporation Tial-based intermetallic compound alloys having superplasticity
US5264051A (en) * 1991-12-02 1993-11-23 General Electric Company Cast gamma titanium aluminum alloys modified by chromium, niobium, and silicon, and method of preparation
EP0545612B1 (fr) * 1991-12-02 1996-03-06 General Electric Company Alliages de gamma titane aluminium modifié par du chrome, du tantale et du bore
US5205875A (en) * 1991-12-02 1993-04-27 General Electric Company Wrought gamma titanium aluminide alloys modified by chromium, boron, and nionium
JP3320760B2 (ja) * 1991-12-06 2002-09-03 大陽工業株式会社 チタニウム・アルミニウム合金
US5228931A (en) * 1991-12-20 1993-07-20 General Electric Company Cast and hipped gamma titanium aluminum alloys modified by chromium, boron, and tantalum
DE4224867A1 (de) * 1992-07-28 1994-02-03 Abb Patent Gmbh Hochwarmfester Werkstoff
US5296056A (en) * 1992-10-26 1994-03-22 General Motors Corporation Titanium aluminide alloys
DE4301880A1 (de) * 1993-01-25 1994-07-28 Abb Research Ltd Verfahren zur Herstellung eines Werkstoffes auf der Basis einer dotierten intermetallischen Verbindung
US5350466A (en) * 1993-07-19 1994-09-27 Howmet Corporation Creep resistant titanium aluminide alloy
US5908516A (en) * 1996-08-28 1999-06-01 Nguyen-Dinh; Xuan Titanium Aluminide alloys containing Boron, Chromium, Silicon and Tungsten
DE19748874C2 (de) * 1996-11-09 2000-03-23 Max Planck Inst Eisenforschung Verwendung einer TiAl-Legierung
DE19756354B4 (de) 1997-12-18 2007-03-01 Alstom Schaufel und Verfahren zur Herstellung der Schaufel
US6425964B1 (en) * 1998-02-02 2002-07-30 Chrysalis Technologies Incorporated Creep resistant titanium aluminide alloys
EP1066415B1 (fr) * 1998-02-02 2002-07-24 Chrysalis Technologies, Incorporated Alliage d'aluminure de titane a deux phases
US6214133B1 (en) 1998-10-16 2001-04-10 Chrysalis Technologies, Incorporated Two phase titanium aluminide alloy
JP3915324B2 (ja) 1999-06-08 2007-05-16 石川島播磨重工業株式会社 チタンアルミナイド合金材料及びその鋳造品
DE19933633A1 (de) * 1999-07-17 2001-01-18 Abb Alstom Power Ch Ag Hochtemperaturlegierung
DE10049026A1 (de) * 2000-10-04 2002-04-11 Alstom Switzerland Ltd Hochtemperaturlegierung
US7060239B2 (en) * 2003-03-31 2006-06-13 Alstom Technology Ltd. Quasicrystalline alloys and their use as coatings
FR2868791B1 (fr) * 2004-04-07 2006-07-14 Onera (Off Nat Aerospatiale) Alliage titane-aluminium ductile a chaud
DE102010042889A1 (de) * 2010-10-25 2012-04-26 Manfred Renkel Turboladerbauteil
US8475943B2 (en) * 2011-07-08 2013-07-02 Kennametal Inc. Coated article having yttrium-containing coatings applied by physical vapor deposition and method for making the same
FR3006696B1 (fr) * 2013-06-11 2015-06-26 Centre Nat Rech Scient Procede de fabrication d'une piece en alliage en titane-aluminium
CN108884518A (zh) * 2016-04-20 2018-11-23 奥科宁克公司 铝、钛和锆的hcp材料及由其制成的产物
US20180230576A1 (en) * 2017-02-14 2018-08-16 General Electric Company Titanium aluminide alloys and turbine components
EP3974082A4 (fr) * 2019-05-23 2023-05-31 IHI Corporation Alliage de tial et son procédé de production
CN113528890B (zh) * 2020-04-16 2022-09-30 中国科学院金属研究所 一种高抗氧化、高塑性的变形TiAl基合金及其制备工艺
FR3121149B1 (fr) 2021-03-25 2023-04-21 Safran Alliage de fonderie intermétallique TiAl
EP4353855A1 (fr) * 2021-06-09 2024-04-17 IHI Corporation Alliage tial, poudre d'alliage tial, composant d'alliage tial et leur procédé de production

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3203794A (en) * 1957-04-15 1965-08-31 Crucible Steel Co America Titanium-high aluminum alloys
US4294615A (en) * 1979-07-25 1981-10-13 United Technologies Corporation Titanium alloys of the TiAl type
JPS63111152A (ja) * 1986-10-30 1988-05-16 Natl Res Inst For Metals Ｓｉを添加した金属間化合物ＴｉＡｌ基耐熱合金
US4849168A (en) * 1986-11-12 1989-07-18 Kawasaki Jukogyo Kabushiki Kaisha Ti-Al intermetallics containing boron for enhanced ductility
US4836983A (en) * 1987-12-28 1989-06-06 General Electric Company Silicon-modified titanium aluminum alloys and method of preparation
US4842819A (en) * 1987-12-28 1989-06-27 General Electric Company Chromium-modified titanium aluminum alloys and method of preparation
US4842820A (en) * 1987-12-28 1989-06-27 General Electric Company Boron-modified titanium aluminum alloys and method of preparation
US4842817A (en) * 1987-12-28 1989-06-27 General Electric Company Tantalum-modified titanium aluminum alloys and method of preparation
US4857268A (en) * 1987-12-28 1989-08-15 General Electric Company Method of making vanadium-modified titanium aluminum alloys
JP2569710B2 (ja) * 1988-04-04 1997-01-08 三菱マテリアル株式会社 常温靱性を有するＴｉ−Ａ▲ｌ▼系金属間化合物型鋳造合金
DE68917815T2 (de) * 1988-05-13 1995-01-05 Nippon Steel Corp Intermetallische Titan-Aluminium-Verbindung und Verfahren zu ihrer Herstellung.
JP2679109B2 (ja) * 1988-05-27 1997-11-19 住友金属工業株式会社 金属間化合物ＴｉＡ▲ｌ▼基軽量耐熱合金
US4983357A (en) * 1988-08-16 1991-01-08 Nkk Corporation Heat-resistant TiAl alloy excellent in room-temperature fracture toughness, high-temperature oxidation resistance and high-temperature strength
US4923534A (en) * 1988-10-03 1990-05-08 General Electric Company Tungsten-modified titanium aluminum alloys and method of preparation
US5045406A (en) * 1989-06-29 1991-09-03 General Electric Company Gamma titanium aluminum alloys modified by chromium and silicon and method of preparation
JP2510141B2 (ja) * 1989-08-18 1996-06-26 日産自動車株式会社 Ｔｉ―Ａｌ系軽量耐熱材料
JPH03111152A (ja) * 1989-09-26 1991-05-10 Takeda Giken:Kk 外周加工機
US5080860A (en) * 1990-07-02 1992-01-14 General Electric Company Niobium and chromium containing titanium aluminide rendered castable by boron inoculations
US5082506A (en) * 1990-09-26 1992-01-21 General Electric Company Process of forming niobium and boron containing titanium aluminide
US5082624A (en) * 1990-09-26 1992-01-21 General Electric Company Niobium containing titanium aluminide rendered castable by boron inoculations
US5131959A (en) * 1990-12-21 1992-07-21 General Electric Company Titanium aluminide containing chromium, tantalum, and boron

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10054229B4 (de) 2000-11-02 2018-06-28 Ansaldo Energia Ip Uk Limited Hochtemperaturlegierung

Also Published As

Publication number Publication date
US5207982A (en) 1993-05-04
ATE127860T1 (de) 1995-09-15
DE59106459D1 (de) 1995-10-19
EP0455005A1 (fr) 1991-11-06
US5342577A (en) 1994-08-30
RU1839683C (ru) 1993-12-30
US5286443A (en) 1994-02-15
JPH05230568A (ja) 1993-09-07

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