EP3067435B2 - 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
EP3067435B2
EP3067435B2 EP16153407.8A EP16153407A EP3067435B2 EP 3067435 B2 EP3067435 B2 EP 3067435B2 EP 16153407 A EP16153407 A EP 16153407A EP 3067435 B2 EP3067435 B2 EP 3067435B2
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EP
European Patent Office
Prior art keywords
process according
forming
component
temperature
heat treatment
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EP16153407.8A
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German (de)
English (en)
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EP3067435B1 (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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Priority to PL16153407T priority Critical patent/PL3067435T5/pl
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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

Definitions

  • the invention relates to a method for producing a highly resilient component from an ⁇ + ⁇ -titanium aluminide alloy for piston engines and gas turbines, in particular aircraft engines.
  • TiAl-based alloys belong to the group of intermetallic materials that have been developed for applications in the area of the operating temperatures of superalloys. Due to its low density of around 4 g / cm 3 , this material offers considerable potential for weight savings and for reducing the loads on moving components, e.g. blades and disks of gas turbines or components of piston engines, at temperatures of up to approx. 700 ° C. State of the art is the investment casting of z. B. Turbine blades for aircraft engines. For applications with higher loads such as B. in high-speed turbines for novel geared turbofan aircraft engines, the properties of the cast structure are no longer sufficient.
  • TiAl alloys can be increased to the required values through thermomechanical treatment by means of plastic deformation with a defined degree of deformation and subsequent heat treatment.
  • thermomechanical treatment due to their high deformation resistance, TiAl alloys cannot be forged conventionally.
  • the forming processes must therefore be carried out at high temperatures in the area of the ⁇ + ⁇ or ⁇ -phase area in a protective atmosphere at low forming speeds. In order to achieve the desired final geometry of the forged part, several successive forging steps are usually necessary.
  • FIG DE 101 50 674 B4 An example of such a method for producing heavy-duty components from ⁇ + ⁇ -TiAl alloys is shown in FIG DE 101 50 674 B4 known.
  • the components are manufactured by encapsulating TiAI blanks with a globular structure through isothermal primary deformation in the ⁇ + ⁇ phase range in the temperature range of 1000 - 1340 ° C or in the ⁇ phase range in the temperature range of 1340 - 1360 ° C are deformed by forging or extrusion, after which the preforms are formed by forging into a component of a given contour by at least one isothermal secondary forming process with simultaneous dynamic recrystallization in the ⁇ + ⁇ or ⁇ phase range in the temperature range of 1000 - 1340 ° C, after which the component is solution annealed to adjust the microstructure in the ⁇ -phase area and then rapidly cooled.
  • a two-stage process is used here, including primary forming in the ⁇ + ⁇ or ⁇ phase range, followed by
  • the invention is thus based on the object of specifying a method for producing a highly stressed component from an ⁇ + ⁇ -titanium aluminide alloy, which is easier to implement in comparison to previously known methods.
  • a method according to claim 1 is used to solve this problem.
  • the method according to the invention is characterized by a one-stage, isothermal forming process of the component in the ⁇ -phase range at a slow forming speed, a specific TiAl alloy being used that makes it possible to stabilize the component in the ⁇ -phase range so that the forming takes place there can.
  • the alloy contains a corresponding proportion of the element Mo, which stabilizes the ⁇ -phase.
  • the method according to the invention particularly advantageously permits a single-stage deformation, the component being completely forged after the end of the deformation.
  • the content of the element Mo stabilizing the ⁇ -phase is 0.8-1.2%.
  • Mo has a particularly high stabilizing property, so its content can be kept relatively low.
  • the forming temperature in the ⁇ -phase range is 1070-1250 ° C, with the forming being carried out isothermally as described, i.e. the forming tools are kept at the forming temperature in order not to leave the required narrow temperature window.
  • the logarithmic forming speed is 10 -3 s -1 to 10 -1 s -1 .
  • the preform used has a volume distribution that varies over the longitudinal axis, i.e. a predetermined three-dimensional basic shape is already given, from which the finished component is forged by the one-step forming according to the invention.
  • This preform is preferably produced by casting, metal injection molding (MIM) or additive processes (3D printing, laser deposition welding, etc.) or a combination of the options mentioned.
  • tools made of a highly heat-resistant material are preferably used, preferably made of a Mo alloy.
  • the tools are expediently protected against oxidation by an inert atmosphere during the forming process.
  • they are preferably actively heated, for example inductively or by resistance heating.
  • the preform is also heated before the forming process, for example in a furnace, inductively or by resistance heating.
  • the deformation is preferably followed by a heat treatment of the deformed component in order to set the required properties and to convert the ⁇ -phase favorable for the deformation into a fine-lamellar ⁇ + ⁇ structure by means of a suitable heat treatment.
  • the heat treatment can include recrystallization annealing at a temperature of 1230-1270 ° C.
  • the holding time during the recrystallization annealing is preferably 50-100 minutes.
  • the recrystallization annealing takes place in the range of the ⁇ / ⁇ conversion temperature. If, as also provided according to the invention, after the recrystallization annealing, the component is cooled to a temperature of 900-950 ° C. in 120 s or faster, then small lamellar spacings of the ⁇ + ⁇ phase are formed.
  • a second heat treatment step in which the component is first cooled to room temperature and then heated to a stabilization or relaxation temperature of 850-950 ° C.
  • the temperature of 900 - 950 ° C which is quickly reached after the recrystallization annealing, can be changed directly to the stabilization and relaxation temperature of 850 - 950 ° C as described above.
  • the preferred holding time at the stabilization and relaxation temperature is preferably 300-360 min.
  • the component temperature is preferably reduced to a temperature below 300 ° C. at a defined cooling rate.
  • the cooling rate is preferably 0.5-2 K / min, that is, the cooling takes place relatively slowly, which serves to stabilize and relax the structure.
  • the cooling rate is preferably 1.5 K / min.
  • the respective cooling can take place in a liquid, e.g. in oil, or in air or an inert gas.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Child & Adolescent Psychology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
  • Forging (AREA)

Claims (13)

  1. Procédé de fabrication d'un composant très résistant à partir d'un alliage d'aluminure de titane α+γ pour des machines à piston et des turbines à gaz, en particulier des groupes motopropulseurs, caractérisé en ce qu'un alliage de TiAl de la composition suivante est utilisé en tant qu'alliage (en % atomique) :
    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,
    et à partir d'un reste comprenant 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 et la température de déformation étant de 1070 à 1250 °C.
  2. Procédé selon la revendication 1, caractérisé en ce que la préforme est fabriquée par coulage, par moulage par injection de métal (MIM), par des procédés additifs, en particulier par impression 3D, par rechargement laser ou une combinaison de ceux-ci.
  3. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que des outils composés d'un alliage de Mo sont utilisés pour la déformation.
  4. Procédé selon la revendication 3, caractérisé en ce que les outils sont protégés par une atmosphère inerte pendant le processus de déformation.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que les outils utilisés pour la déformation sont chauffés activement, en particulier par induction.
  6. 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.
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la déformation est suivie par un traitement thermique du composant déformé.
  8. Procédé selon la revendication 7, caractérisé en ce que le traitement thermique comprend un recuit de recristallisation à une température de 1 230 à 1 270 °C.
  9. Procédé selon la revendication 8, caractérisé en ce que le temps de maintien pendant le recuit de recristallisation est de 50 à 100 minutes.
  10. Procédé selon la revendication 9, 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.
  11. Procédé selon la revendication 10, caractérisé en ce que le composant est ensuite refroidi à température ambiante, puis chauffé 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.
  12. Procédé selon la revendication 11, caractérisé en ce que le temps de maintien à la température de stabilisation et de détente est de 300 à 360 minutes.
  13. Procédé selon la revendication 11 ou 12, 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, en particulier 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 EP3067435B1 (fr) 2017-07-26
EP3067435B2 true EP3067435B2 (fr) 2021-11-24

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Country Status (5)

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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
EP3508594B8 (fr) * 2016-09-02 2021-06-16 IHI Corporation 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
WO2020189215A1 (fr) * 2019-03-18 2020-09-24 株式会社Ihi 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.
EP4299776A1 (fr) * 2021-04-16 2024-01-03 Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) Alliage tial pour forgeage, matériau à base d'alliage tial et procédé de production d'un matériau d'alliage tial
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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US20160265096A1 (en) 2016-09-15
EP3067435B1 (fr) 2017-07-26
US10196725B2 (en) 2019-02-05
PL3067435T5 (pl) 2022-03-14
EP3067435A1 (fr) 2016-09-14
JP2016166418A (ja) 2016-09-15
PL3067435T3 (pl) 2018-01-31
DE102015103422B3 (de) 2016-07-14
JP6200985B2 (ja) 2017-09-20

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