EP3067435B1 - Procede de production d'un composant tres resistant en alliage d'aluminure de titane alpha+gamma pour machines a piston et turbines a gaz, en particulier groupes motopropulseurs - Google Patents

Procede de production d'un composant tres resistant en alliage d'aluminure de titane alpha+gamma pour machines a piston et turbines a gaz, en particulier groupes motopropulseurs Download PDF

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Publication number
EP3067435B1
EP3067435B1 EP16153407.8A EP16153407A EP3067435B1 EP 3067435 B1 EP3067435 B1 EP 3067435B1 EP 16153407 A EP16153407 A EP 16153407A EP 3067435 B1 EP3067435 B1 EP 3067435B1
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Prior art keywords
process according
alloy
phase
forming
component
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EP16153407.8A
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German (de)
English (en)
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EP3067435B2 (fr
EP3067435A1 (fr
Inventor
Marianne Baumgärtner
Peter Janschek
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Leistritz Turbinentechnik GmbH
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Leistritz Turbinentechnik GmbH
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C21D1/30—Stress-relieving
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon

Claims (19)

  1. Procédé de fabrication d'un composant très résistant en un alliage d'aluminure de titane α+γ pour machines à piston et turbines à gaz, en particulier groupes motopropulseurs, caractérisé en ce qu'un alliage de TiAl de la composition suivante est utilisé en tant qu'alliage (en % atomique) :
    40 à 48 % d'Al,
    2 à 8 % de Nb,
    0,1 à 9 % d'au moins un élément stabilisant la phase β, choisi parmi Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
    0 à 0,5 % de B,
    le reste étant du Ti et des impuretés dues à la fusion, la déformation ayant lieu en une étape à partir d'une préforme ayant une distribution volumique variant le long de l'axe longitudinal, le composant étant déformé de manière isotherme avec une vitesse de déformation logarithmique de 0,01 à 0,5 1/s dans la zone de la phase β.
  2. Procédé selon la revendication 1, caractérisé en ce que seul Mo, V, Ta ou un mélange de ceux-ci est présent dans l'alliage en tant qu'élément stabilisant la phase β.
  3. Procédé selon la revendication 1 ou 2, caractérisé en ce que la teneur de l'élément stabilisant la phase β est de 0,1 à 2 %, notamment de 0,8 à 1,2 %.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce qu'un alliage de TiAl ayant la composition suivante est utilisé :
    41 à 47 % d'Al,
    1,5 à 7 % de Nb,
    0,2 à 8 % d'au moins un élément stabilisant la phase β, choisi parmi Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
    0 à 0,3 % de B,
    le reste étant du Ti et des impuretés dues à la fusion.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce qu'un alliage de TiAl ayant la composition suivante est utilisé :
    42 à 46 % d'Al,
    2 à 6,5 % de Nb,
    0,4 à 5 % d'au moins un élément stabilisant la phase β, choisi parmi Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
    0 à 0,2 % de B,
    le reste étant du Ti et des impuretés dues à la fusion.
  6. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce qu'un alliage ayant la composition suivante est utilisé :
    42,8 à 44,2 % d'Al,
    3,7 à 4,3 % de Nb,
    0,8 à 1,2 % de Mo,
    0,07 à 0,13 % de B,
    le reste étant du Ti et des impuretés dues à la fusion.
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la température de déformation dans la zone de la phase β est de 1 070 à 1 250 °C.
  8. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la préforme est fabriquée par coulage, moulage par injection de métal (MIM), des procédés additifs, notamment l'impression 3D, rechargement laser ou une combinaison de ceux-ci.
  9. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que des outils en un alliage de Mo sont utilisés pour la déformation.
  10. Procédé selon la revendication 9, caractérisé en ce que les outils sont protégés par une atmosphère inerte pendant le processus de déformation.
  11. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que les outils utilisés pour le façonnage sont chauffés activement, notamment par induction.
  12. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la préforme est chauffée dans un four, par induction ou par chauffage par résistance, avant la déformation.
  13. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la déformation est suivie par un traitement thermique du composant déformé.
  14. Procédé selon la revendication 13, caractérisé en ce que le traitement thermique comprend un recuit de recristallisation à une température de 1 230 à 1 270 °C.
  15. Procédé selon la revendication 14, caractérisé en ce que le temps de maintien pendant le recuit de recristallisation est de 50 à 100 minutes.
  16. Procédé selon la revendication 15, caractérisé en ce qu'après le recuit de recristallisation, le composant est refroidi à une température de 900 à 950 °C en 120 s ou plus rapidement.
  17. Procédé selon la revendication 16, caractérisé en ce que le composant est ensuite refroidi à température ambiante, puis porté à une température de stabilisation et de détente de 850 à 950 °C, ou en ce que le composant est maintenu sans refroidissement préalable à une température de stabilisation et de détente de 850 à 950 °C.
  18. Procédé selon la revendication 17, caractérisé en ce que le temps de maintien à la température de stabilisation et de détente est de 300 à 360 minutes.
  19. Procédé selon la revendication 17 ou 18, caractérisé en ce qu'un refroidissement du composant à une température inférieure à 300 °C à une vitesse de refroidissement de 0,5 à 2 K/min, notamment de 1,5 K/min, a ensuite lieu.
EP16153407.8A 2015-03-09 2016-01-29 Procede de production d'un composant tres resistant en alliage d'aluminure de titane alpha+gamma pour machines a piston et turbines a gaz, en particulier groupes motopropulseurs Active EP3067435B2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL16153407T PL3067435T5 (pl) 2015-03-09 2016-01-29 Sposób wytwarzania elementu konstrukcyjnego o wysokiej wytrzymałości ze stopu alfa+gamma-glinku tytanu do maszyn tłokowych i turbin gazowych, w szczególności do silników lotniczych

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102015103422.0A DE102015103422B3 (de) 2015-03-09 2015-03-09 Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke

Publications (3)

Publication Number Publication Date
EP3067435A1 EP3067435A1 (fr) 2016-09-14
EP3067435B1 true EP3067435B1 (fr) 2017-07-26
EP3067435B2 EP3067435B2 (fr) 2021-11-24

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EP16153407.8A Active EP3067435B2 (fr) 2015-03-09 2016-01-29 Procede de production d'un composant tres resistant en alliage d'aluminure de titane alpha+gamma pour machines a piston et turbines a gaz, en particulier groupes motopropulseurs

Country Status (5)

Country Link
US (1) US10196725B2 (fr)
EP (1) EP3067435B2 (fr)
JP (1) JP6200985B2 (fr)
DE (1) DE102015103422B3 (fr)
PL (1) PL3067435T5 (fr)

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DE102015103422B3 (de) 2015-03-09 2016-07-14 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
WO2018043187A1 (fr) 2016-09-02 2018-03-08 株式会社Ihi Alliage ti-al et son procédé de fabrication
KR101888049B1 (ko) * 2016-12-14 2018-08-13 안동대학교 산학협력단 파괴 인성 및 크리프 저항성이 향상된 Ti-Al-Nb-Fe계 합금의 제조방법
KR101890642B1 (ko) * 2016-12-14 2018-08-22 안동대학교 산학협력단 파괴 인성 및 크리프 저항성이 향상된 Ti-Al-Nb-V계 합금의 제조방법
EP3372700B1 (fr) 2017-03-10 2019-10-09 MTU Aero Engines GmbH Procédé de fabrication d'éléments structuraux en tial forgés
DE102017212082A1 (de) 2017-07-14 2019-01-17 MTU Aero Engines AG Schmieden bei hohen temperaturen, insbesondere von titanaluminiden
DE102018101194A1 (de) 2018-01-19 2019-07-25 Otto Fuchs - Kommanditgesellschaft - Verfahren zum Herstellen eines hoch belastbaren Bauteils aus einem zumindest zweiphasigen metallischen oder intermetallischen Werkstoff
DE102018202723A1 (de) * 2018-02-22 2019-08-22 MTU Aero Engines AG Verfahren zur herstellung eines bauteils aus einer gradierten tial - legierung und entsprechend hergestelltes bauteil
WO2019191450A1 (fr) * 2018-03-29 2019-10-03 Arconic Inc. Alliages d'aluminure de titane, produits en alliage d'aluminure de titane et leurs procédés de fabrication
DE102018209315A1 (de) 2018-06-12 2019-12-12 MTU Aero Engines AG Verfahren zur Herstellung eines Bauteils aus Gamma - TiAl und entsprechend hergestelltes Bauteil
EP3943627A4 (fr) * 2019-03-18 2022-11-16 IHI Corporation Matériau d'alliage d'aluminure de titane pour forgeage à chaud, procédé de forgeage pour matériau d'alliage d'aluminure de titane, et corps forgé
DE102020214700A1 (de) 2020-11-23 2022-05-25 MTU Aero Engines AG Verfahren zur herstellung eines bauteils aus einer tial – legierung und entsprechend hergestelltes bauteil
DE102021000614A1 (de) 2021-02-08 2022-08-11 Access E.V. Kokille zur rissfreien Herstellung eines Metallgegenstandes mit mindestens einem Hinterschnitt, insbesondere aus intermetallischen Legierungen wie TiAl, FeAl und anderen spröden oder rissanfälligen Werkstoffen, sowie ein entsprechendes Verfahren.
US20240043978A1 (en) * 2021-04-16 2024-02-08 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) Tial alloy for forging, tial alloy material, and method for producing tial alloy material
CN113355619B (zh) * 2021-06-04 2022-08-09 西安交通大学 一种阻止锆合金热机械加工开裂的热处理方法
US11807911B2 (en) * 2021-12-15 2023-11-07 Metal Industries Research & Development Centre Heat treatment method for titanium-aluminum intermetallic and heat treatment device therefor
CN115679231B (zh) * 2022-09-16 2024-03-19 中南大学 一种提高钛铝基合金高温强塑性的工艺

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DIETER ET AL.: "Handbook of Workability and Process Design", ASM INTERNATIONAL, ISBN: 0-87170-778-0, article GEORGE E DIETER: "Chapter 2 Bulk Workability of Metals", pages: 22 - 25, XP0055486181
G. SAUTHOFF, TITAN - ALUMINID - LEGIERUNGEN - EINE WERKSTOFF- GRUPPE MIT ZUKUNFT, FORSCHUNGSZENTRUM JÜLICH - PROJEKTTRÄGER JÜLICH PTJ, 2003, XP055486469, ISBN: 3-89336-318-1
HELMUT CLEMENS ET AL.: "Materials for Aircraft Engines", 7TH EUROPEAN WINTER SCHOOL ON NEUTRONS AND SYNCHROTRON RADIATION, 9 March 2011 (2011-03-09), pages 1 - 44, XP055486257, Retrieved from the Internet <URL:http://planner2011.unileoben.ac.at/fileadmin/shares/planner2011/docs/private/16-Clemens.pdf>
HUANG ZHAO-HUI ET AL.: "Isothermal forging of y-TiAI based alloys", TRANSF. NONFERROUS MET. SOC. CHINA, vol. 13, December 2003 (2003-12-01), pages 1325 - 1328, XP055486187
JACQUES TSCHOFFEN ET AL.: "Development of forging processes for TiAI engine components for aerospace and automotive components", INTERNATIONAL WORKSHOP ON GAMMA ALLOY TECHNOLOGY, 11 June 2013 (2013-06-11), Toulouse, France, pages 1 - 23, XP055486295
YANG FEI ET AL.: "Effect of Heat Treatment on Microstructure and Propertiesof as-Forged TiAI Alloy with beta Phase", RARE METAL MATERIALS AND ENGINEERING, vol. 40, no. 9, September 2011 (2011-09-01), pages 1505 - 1509, XP055486550
ZHANG H. ET AL.: "Process optimization for isothermal forging of TiAI Compressor blade by Numérical Simulation", 2ND INTERNATIONAL CONFÉRENCE ON COMPUTER ENGINEERING AND TECHNOLOGY, vol. 5, 16 April 2010 (2010-04-16), pages V5-412 - V5-415, XP031690316

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US10196725B2 (en) 2019-02-05
JP6200985B2 (ja) 2017-09-20
JP2016166418A (ja) 2016-09-15
US20160265096A1 (en) 2016-09-15
EP3067435B2 (fr) 2021-11-24
PL3067435T3 (pl) 2018-01-31
EP3067435A1 (fr) 2016-09-14
DE102015103422B3 (de) 2016-07-14

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