EP0455005A1 - 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
EP0455005A1
EP0455005A1 EP91105503A EP91105503A EP0455005A1 EP 0455005 A1 EP0455005 A1 EP 0455005A1 EP 91105503 A EP91105503 A EP 91105503A EP 91105503 A EP91105503 A EP 91105503A EP 0455005 A1 EP0455005 A1 EP 0455005A1
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EP
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Prior art keywords
alloy
room temperature
melted
temperature
yield point
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Granted
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EP91105503A
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German (de)
English (en)
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EP0455005B1 (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

  • High-temperature alloys for thermal machines based on intermetallic compounds which are suitable for directional solidification and complement the conventional nickel-based superalloys.
  • the invention relates to the further development and improvement of the alloys based on an intermetallic compound of the titanium aluminide TiAl type with further additives which increase strength, toughness and ductility.
  • the invention relates to a high-temperature alloy for machine components based on doped TiAl.
  • 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 is only approx. 1/2 of the value for Ni superalloys reached. However, 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, inter alia nickel aluminides, nickel silicides and titanium aluminides are known as construction materials.
  • EP-A1-0 365 598 shows a high-temperature alloy based on TiAl with additions of Si and Nb
  • EP-A1-0 405 134 suggests a high-temperature alloy based on TiAl with additions of Si and Cr.
  • the invention is based on the object of specifying a light alloy with adequate oxidation and corrosion resistance at high temperatures and at the same time high heat resistance and sufficient toughness in the temperature range from 500 to 1000 ° C., which is good for directed Solidification is suitable and essentially consists of a high-melting intermetallic compound.
  • FIG. 7 relates to a graphic representation of the yield point ⁇ 0.2 as a function of the temperature of alloys 21-27 and of comparative alloys 1 and 2.
  • FIGS. 9, 10 and 11 each relate to graphic representations of the influence of metal additives (Me, W) on the mechanical properties of alloys based on the intermetallic compound titanium aluminide at room temperature.
  • metal additives Mo, W
  • the influence of tungsten and yttrium content on the Vickers hardness is HV (kg / mm2) and for alloys 11, 12, 13, 31, 32 and 40 the influence of the tungsten or xttrium content on the elongation at break ⁇ (%) each at room temperature.
  • the alloy 11 serves as the basis.
  • the alloy compositions are as follows:
  • the individual elements with a purity of 99.99% served as the starting materials.
  • the melt was poured into a cast blank of approximately 50 mm in diameter and approximately 70 mm in height.
  • the blank was melted again under protective gas and also forced under solidification to solidify in the form of rods with a diameter of approximately 9 mm and a length of approximately 70 mm.
  • 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 realms of possibility. There is also the possibility of improvement by directional solidification, for which the alloy is particularly suitable.
  • the melt was poured off analogously to embodiment 1, melted again under argon and forced to solidify in the form of a rod.
  • the dimensions of the rods corresponded to embodiment 1.
  • the rods were processed directly into pressure samples without subsequent heat treatment.
  • the mechanical properties as a function of the test temperature thus approximately corresponded to those of Example 1. These values can be further improved by heat treatment.
  • the melt was poured off analogously to 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 mechanical properties corresponded approximately to those of the previous examples. Heat treatment resulted in a further improvement in these values.
  • the melt was poured off analogously to 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 a reference. The Vickers hardness HV at room temperature averaged 322 units. 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 further improved 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 Vickers hardness HV at room temperature averaged 333 units (Fig. 1).
  • the yield point ⁇ 0.2 at room temperature reached 495 MPa (Fig. 5).
  • the Vickers hardness HV at room temperature averaged 300 units (FIG. 1).
  • the yield point ⁇ 0.2 at room temperature was 489 MPa. Their course over the temperature T is similar to that of alloy 8.
  • the Vickers hardness HV at room temperature was 296 units. It had a profile similar to alloy 8 over temperature.
  • the yield point ⁇ 0.2 was approx. 478 MPa.
  • the course over the temperature lies approximately in the middle between the corresponding courses of alloys 8 and 9.
  • the Vickers hardness HV was 290 units at room temperature. Their temperature profile lies approximately in the middle between the corresponding temperature profiles of alloys 8 and 9.
  • the yield point ⁇ was 0.2 388 MPa at room temperature. Their course over the temperature T practically coincides with that of the alloy 2. The Vickers hardness HV at room temperature reached 235 units. The corresponding course over T practically coincides with that of alloy 2.
  • the yield point ⁇ 0.2 at room temperature was measured at 449 MPa. Their course over the temperature T is just below that of the alloy 9. The Vickers hardness HV at room temperature gave a value of 272 units. The temperature profile is just below that of alloy 9.
  • the yield point ⁇ 0.2 at room temperature gave an average value of 522 MPa. Their temperature profile is just below that of alloy 3. The Vickers hardness HV at room temperature was 316 units. The corresponding course over the temperature T is just below that of the alloy 3.
  • the individual elements with a purity of 99.99% served as the starting materials.
  • 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 under solidification to solidify in the form of rods with a diameter of approximately 8 mm and a length of approximately 80 mm.
  • 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 realms of possibility. There is also the possibility of improvement by directional solidification, for which the alloy is particularly suitable.
  • the melt was poured off analogously to embodiment 34, melted again under argon and forced to solidify in the form of a rod.
  • the dimensions of the rods corresponded to embodiment 34.
  • the rods were processed directly into pressure samples without subsequent heat treatment.
  • the mechanical properties as a function of the test temperature thus achieved corresponded approximately to those of Example 34. These values can be further improved by heat treatment.
  • Example 34 The melt was poured off as in Example 34, melted again under argon and cast into prisms of square cross section (8 mm ⁇ 8 mm ⁇ 100 mm). Test specimens for pressure, hardness and impact tests were produced from these prisms. The mechanical properties corresponded approximately to those of the previous examples. Heat treatment further improved these values.
  • the yield point ⁇ 0.2 at room temperature was 650 MPa (Fig. 6).
  • the Vickers hardness HV at room temperature averaged 394 units (FIG. 2).
  • the hardness-increasing effect of the Y addition compared to pure TiAl is remarkable and is almost 100%.
  • the yield point ⁇ 0.2 at room temperature was 482 MPa (Fig. 6).
  • the Vickers hardness HV at room temperature reached the value of 292 units (Fig. 2).
  • 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 Vickers hardness HV at room temperature averaged 258 units (Fig. 2).
  • the yield point ⁇ 0.2 at room temperature was 439 MPa (Fig. 6).
  • the Vickers hardness HV at room temperature reached an average of 266 units (FIG. 2).
  • the yield point ⁇ 0.2 at room temperature reached 512 MPa (Fig. 6).
  • the Vickers hardness HV at room temperature averaged 310 units (FIG. 2).
  • the hardness-increasing effect of the Zr addition compared to alloy 1 (pure TiAl) is therefore approx. 55%.
  • the yield point ⁇ 0.2 at room temperature was 513 MPa (Fig. 7).
  • the Vickers hardness HV at room temperature was 311 units (FIG. 3).
  • 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 was measured at 498 MPa (Fig. 7).
  • the Vickers hardness HV at room temperature gave a value of 302 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 was 296 units (FIG. 3).
  • the increase in hardness is associated with a more or less severe loss of ductility, which can, however, be at least partially 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 considerably 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 individual elements with a purity of 99.99% served as the starting materials.
  • 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 under solidification to solidify in the form of rods with a diameter of approximately 12 mm and a length of approximately 80 mm.
  • 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 realms of possibility. There is also the possibility of improvement by 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 Vickers hardness at room temperature was 342 units (Fig. 4).
  • the yield point ⁇ 0.2 at room temperature was 565 MPa (Fig. 8).
  • the mechanical properties are hardly changed by the further addition of boron up to 1 atom%. Therefore, this value is also a justified upper limit for the boron content of the alloy.
  • the area of application 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)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Luminescent Compositions (AREA)
  • Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
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
CH1524/90 1990-05-04
CH152490 1990-05-04
CH1523/90 1990-05-04
CH152390 1990-05-04
CH161690 1990-05-11
CH1616/90 1990-05-11

Publications (2)

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

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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 (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2663956A1 (fr) * 1990-07-02 1992-01-03 Gen Electric Composition moulable et element structural contenant du titane de l'aluminium, du chrome, du tantale et du bore.
FR2663957A1 (fr) * 1990-07-02 1992-01-03 Gen Electric Composition moulable et element structural contenant du titane, de l'aluminium, du chrome, du niobium et du bore.
FR2670805A1 (fr) * 1990-12-21 1992-06-26 Gen Electric Procede de formation d'aluminiure de titane contenant du chrome, du tantale et du bore.
FR2670804A1 (fr) * 1990-12-21 1992-06-26 Gen Electric Procede de formation d'aluminiures de titane contenant du chrome, du niobium et du bore.
US5196162A (en) * 1990-08-28 1993-03-23 Nissan Motor Co., Ltd. Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si
US5205875A (en) * 1991-12-02 1993-04-27 General Electric Company Wrought gamma titanium aluminide alloys modified by chromium, boron, and nionium
US5205876A (en) * 1991-12-06 1993-04-27 Taiyo Kogyo Co., Ltd. Alloyed titanium aluminide having lamillar microstructure
EP0545614A1 (fr) * 1991-12-02 1993-06-09 General Electric Company Alliages titane-aluminium du type gamma, modifiés par addition de chrome, niobium et silicium
EP0545612A1 (fr) * 1991-12-02 1993-06-09 General Electric Company Alliages de gamma titane aluminium modifié par du chrome, du tantale et du bore
EP0550165A1 (fr) * 1991-12-20 1993-07-07 General Electric Company Alliages de gamma titane aluminium
EP0581204A1 (fr) * 1992-07-28 1994-02-02 ABBPATENT GmbH Matériau résistant aux températures élevées
US5296056A (en) * 1992-10-26 1994-03-22 General Motors Corporation Titanium aluminide alloys
DE19756354A1 (de) * 1997-12-18 1999-06-24 Asea Brown Boveri Schaufel und Verfahren zur Herstellung der Schaufel
DE19748874C2 (de) * 1996-11-09 2000-03-23 Max Planck Inst Eisenforschung Verwendung einer TiAl-Legierung
DE19933633A1 (de) * 1999-07-17 2001-01-18 Abb Alstom Power Ch Ag Hochtemperaturlegierung
EP1195445A1 (fr) * 2000-10-04 2002-04-10 Alstom (Switzerland) Ltd Alliage du type aluminure de titane contenant du bore, du silicium et du tungstène
DE102010042889A1 (de) * 2010-10-25 2012-04-26 Manfred Renkel Turboladerbauteil
FR3006696A1 (fr) * 2013-06-11 2014-12-12 Centre Nat Rech Scient Procede de fabrication d'une piece en alliage en titane-aluminium

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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
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
US6214133B1 (en) 1998-10-16 2001-04-10 Chrysalis Technologies, Incorporated Two phase titanium aluminide alloy
JP4664500B2 (ja) * 1998-02-02 2011-04-06 フィリップ モーリス ユーエスエー インコーポレイテッド ２相チタン・アルミニド合金
US6425964B1 (en) * 1998-02-02 2002-07-30 Chrysalis Technologies Incorporated Creep resistant titanium aluminide alloys
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
DE10054229B4 (de) 2000-11-02 2018-06-28 Ansaldo Energia Ip Uk Limited 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
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
CA3017247A1 (fr) * 2016-04-20 2017-10-26 Arconic Inc. Materiaux hcp constitues d'aluminium, de titane et de zirconium et produits fabriques a partir de ces materiaux
US20180230576A1 (en) * 2017-02-14 2018-08-16 General Electric Company Titanium aluminide alloys and turbine components
WO2020235201A1 (fr) * 2019-05-23 2020-11-26 株式会社Ihi 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

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EP0405134A1 (fr) * 1989-06-29 1991-01-02 General Electric Company Alliages titane-aluminium du type gamma, modifiés par addition de chrome et silicium, et procédé de préparation
EP0413524A1 (fr) * 1989-08-18 1991-02-20 Nissan Motor Company Limited Matériau léger résistant aux températures élevées, à base de titane-aluminium

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US3203794A (en) * 1957-04-15 1965-08-31 Crucible Steel Co America Titanium-high aluminum alloys
EP0363598A1 (fr) * 1988-08-16 1990-04-18 Nkk Corporation Alliage réfractaire titane-aluminium présentant une haute ténacité à la température ambiante et une bonne résistance à l'oxydation ainsi qu'une haute résistance mécanique aux températures élevées
EP0405134A1 (fr) * 1989-06-29 1991-01-02 General Electric Company Alliages titane-aluminium du type gamma, modifiés par addition de chrome et silicium, et procédé de préparation
EP0413524A1 (fr) * 1989-08-18 1991-02-20 Nissan Motor Company Limited Matériau léger résistant aux températures élevées, à base de titane-aluminium

Cited By (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2663956A1 (fr) * 1990-07-02 1992-01-03 Gen Electric Composition moulable et element structural contenant du titane de l'aluminium, du chrome, du tantale et du bore.
FR2663957A1 (fr) * 1990-07-02 1992-01-03 Gen Electric Composition moulable et element structural contenant du titane, de l'aluminium, du chrome, du niobium et du bore.
US5196162A (en) * 1990-08-28 1993-03-23 Nissan Motor Co., Ltd. Ti-Al type lightweight heat-resistant materials containing Nb, Cr and Si
FR2670805A1 (fr) * 1990-12-21 1992-06-26 Gen Electric Procede de formation d'aluminiure de titane contenant du chrome, du tantale et du bore.
FR2670804A1 (fr) * 1990-12-21 1992-06-26 Gen Electric Procede de formation d'aluminiures de titane contenant du chrome, du niobium et du bore.
EP0545612A1 (fr) * 1991-12-02 1993-06-09 General Electric Company Alliages de gamma titane aluminium modifié par du chrome, du tantale et du bore
EP0545613A1 (fr) * 1991-12-02 1993-06-09 General Electric Company Alliages forgés de gamma titane aluminium modifié par du chrome, du bore et du niobium
EP0545614A1 (fr) * 1991-12-02 1993-06-09 General Electric Company Alliages titane-aluminium du type gamma, modifiés par addition de chrome, niobium et silicium
US5324367A (en) * 1991-12-02 1994-06-28 General Electric Company Cast and forged gamma titanium aluminum alloys modified by boron, chromium, and tantalum
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
US5205875A (en) * 1991-12-02 1993-04-27 General Electric Company Wrought gamma titanium aluminide alloys modified by chromium, boron, and nionium
US5205876A (en) * 1991-12-06 1993-04-27 Taiyo Kogyo Co., Ltd. Alloyed titanium aluminide having lamillar microstructure
EP0545518A1 (fr) * 1991-12-06 1993-06-09 Taiyo Kogyo Co. Ltd., Alliage titane-aluminium
EP0550165A1 (fr) * 1991-12-20 1993-07-07 General Electric Company Alliages de gamma titane aluminium
US5228931A (en) * 1991-12-20 1993-07-20 General Electric Company Cast and hipped gamma titanium aluminum alloys modified by chromium, boron, and tantalum
EP0581204A1 (fr) * 1992-07-28 1994-02-02 ABBPATENT GmbH Matériau résistant aux températures élevées
US5393356A (en) * 1992-07-28 1995-02-28 Abb Patent Gmbh High temperature-resistant material based on gamma titanium aluminide
US5296056A (en) * 1992-10-26 1994-03-22 General Motors Corporation Titanium aluminide alloys
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
US6521059B1 (en) 1997-12-18 2003-02-18 Alstom Blade and method for producing the blade
DE19756354A1 (de) * 1997-12-18 1999-06-24 Asea Brown Boveri Schaufel und Verfahren zur Herstellung der Schaufel
DE19933633A1 (de) * 1999-07-17 2001-01-18 Abb Alstom Power Ch Ag Hochtemperaturlegierung
GB2354257A (en) * 1999-07-17 2001-03-21 Abb Alstom Power Ch Ag A high temperature titanium-aluminium alloy
EP1195445A1 (fr) * 2000-10-04 2002-04-10 Alstom (Switzerland) Ltd Alliage du type aluminure de titane contenant du bore, du silicium et du tungstène
US6676897B2 (en) 2000-10-04 2004-01-13 Alstom (Switzerland) Ltd High-temperature alloy
DE102010042889A1 (de) * 2010-10-25 2012-04-26 Manfred Renkel Turboladerbauteil
FR3006696A1 (fr) * 2013-06-11 2014-12-12 Centre Nat Rech Scient Procede de fabrication d'une piece en alliage en titane-aluminium
WO2014199082A1 (fr) * 2013-06-11 2014-12-18 Centre National De La Recherche Scientifique - Cnrs - Procédé de fabrication d'une pièce en alliage en titane-aluminium
CN105451915A (zh) * 2013-06-11 2016-03-30 国家科学研究中心 钛铝合金工件制造工艺
CN105451915B (zh) * 2013-06-11 2018-01-02 国家科学研究中心 钛铝合金工件制造工艺

Also Published As

Publication number Publication date
RU1839683C (ru) 1993-12-30
DE59106459D1 (de) 1995-10-19
EP0455005B1 (fr) 1995-09-13
US5342577A (en) 1994-08-30
ATE127860T1 (de) 1995-09-15
US5207982A (en) 1993-05-04
JPH05230568A (ja) 1993-09-07
US5286443A (en) 1994-02-15

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