EP2807281B1 - Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé - Google Patents

Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé Download PDF

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Publication number
EP2807281B1
EP2807281B1 EP13705380.7A EP13705380A EP2807281B1 EP 2807281 B1 EP2807281 B1 EP 2807281B1 EP 13705380 A EP13705380 A EP 13705380A EP 2807281 B1 EP2807281 B1 EP 2807281B1
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European Patent Office
Prior art keywords
component
tial
heat treatment
temperature
forging
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EP13705380.7A
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German (de)
English (en)
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EP2807281A1 (fr
Inventor
Wilfried Smarsly
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F05D2230/41—Hardening; Annealing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the present invention relates to a method for producing a component from a TiAl alloy, in which the component is formed by forging, in particular by isothermal forging, and is then subjected to a heat treatment.
  • the present invention relates to a correspondingly manufactured component.
  • a method according to the features of the preamble of claim 1 is for example from EP 2 386 663 A1 known.
  • TiAl alloys the main components of which are titanium and aluminum, are characterized by the fact that they have a high strength due to the formation of intermetallic phases, such as ⁇ -TiAl, which have a high proportion of covalent bonding forces within the metallic bond, with sufficient ductility, especially high temperature resistance. In addition, they have a low specific weight, so that the use of titanium aluminides or TiAl alloys is suitable as in high-temperature applications, for example in flow machines, in particular gas turbines or aircraft engines.
  • TNM alloys By adding certain alloy components, such as niobium and molybdenum, the property profile of the TiAl alloys can be further optimized.
  • Such alloys with a niobium and molybdenum content are also referred to as so-called TNM alloys,
  • alloys are used in aircraft engines, for example, as guide vanes or rotor blades and are brought into the appropriate component shape by forging.
  • isothermal forging can be used here with subsequent heat treatment to adjust the structure and the property profile.
  • blisk artificial word for blade and disk
  • one-piece blade and disk units so-called blisk (artificial word for blade and disk) can also be produced.
  • due to differences in the chemical composition across the component there may be a different phase composition within a component made of a TiAl material during manufacture, which results in an uneven distribution of the property profile in the component, resulting in corresponding fluctuations in the properties
  • Such components can no longer be used across the component if they are outside the specified specification for the component. This leads to high reject rates.
  • the present invention it is proposed to carry out at least one first heat treatment after forging in a component made of a TiAl alloy, i.e. an alloy in which the alloy components with the highest proportion of the alloy composition are titanium and aluminum, after forging, in which at least In one process step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and is then cooled.
  • a component made of a TiAl alloy i.e. an alloy in which the alloy components with the highest proportion of the alloy composition are titanium and aluminum
  • This first heat treatment is referred to as homogenization annealing, as it homogenizes the material composition over the component and dissolves existing concentration points.
  • the cooling rate can be between 1 ° C / s and 5 ° C / s.
  • the component is heated in a second heat treatment above the solvus line of ⁇ -TiAl.
  • a second heat treatment the ⁇ -TiAl contained in the structure is at least partially converted into another solid phase, such as ⁇ -TiAl, so that a desired or adapted phase composition is made possible in the TiAl alloy and in particular depending on the chemical composition of the
  • the heat treatment can be specially tailored to the specific chemical composition and its distribution in the component.
  • the component is rapidly cooled above the solvus line of the ⁇ -TiAl in order to largely freeze the phase composition set at the heat treatment temperature. Rapid cooling is achieved by quenching in water or oil or by air cooling with a fan.
  • the cooling can take place so quickly that a conversion of the ⁇ -TiAl additionally formed during the second heat treatment into a lamellar structure of ⁇ -TiAl and ⁇ -TiAl is avoided.
  • the second heat treatment can be carried out at a temperature at which it is avoided to get into a single-phase phase field of the TiAl phase diagram, such as the ⁇ -TiAl phase field, in order to reduce the risk of coarse grain growth occurring during a heat treatment in a single-phase phase field prevent.
  • the second heat treatment can be carried out for a period of time which ensures sufficient conversion of the ⁇ -TiAl into another phase, in particular ⁇ -TiAl, so that the desired phase composition can be achieved.
  • the temperature in the second heat treatment above the ⁇ -TiAl solvus line can be at a temperature of 20 ° C. to 50 ° C., in particular 25 ° C. to 35 ° C., preferably about 30 ° C. above the ⁇ -TiAl solvus - Line to be chosen.
  • the method is used for components made of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 - 54.5 at.% Titanium, 3.5 to 4.5 at.% Niobium, in particular 4.0 to 4.2 at% niobium, 0.75 to 1.5 at% molybdenum, in particular 0.9 to 1.2 at% molybdenum, and 0.05 to 0.15 at .-% boron, in particular 0.1 to 0.12 at .-% boron, and the remainder aluminum and unavoidable impurities.
  • Such an alloy has a phase composition with corresponding proportions of ⁇ -TiAl which makes the use of the method according to the invention particularly advantageous.
  • a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours can also be carried out in order to stabilize the material structure in the component (stabilization annealing).
  • components of a turbomachine can be produced, in particular a gas turbine or an aircraft engine, such as in particular rotor blades, guide vanes, or turbine blisks, which have a variably adjustable property profile based on an adapted phase composition.
  • the attached drawing in the single figure shows a so-called TNM phase diagram for a material in which the present invention can be implemented.
  • a material for a component produced according to the invention has a composition in the range from 42 to 45 at.% Titanium, 3.5 to 4.5 at.% Niobium, 0.75 to 1.5 at.% Molybdenum, and 0 .05 to 0.15 atom% boron with the remainder aluminum and unavoidable impurities.
  • a corresponding component can, for example, be isothermally forged until it has the raw contour of the component to be finally produced.
  • the material of the component is homogenized by a first heat treatment at, for example, 1150 ° C for 8 hours.
  • the component is then annealed in a second heat treatment at a temperature of, for example, 1290 ° C (i.e. above the Solvus line (1)) for a predetermined period of time in order to bring about a partial conversion of the ⁇ -TiAl to ⁇ -TiAl, so that ⁇ -TiAl and ⁇ -TiAl are present next to each other in the structure.
  • the temperature treatment can be carried out until a sufficient amount of ⁇ -TiAl has been converted into ⁇ -TiAl for the desired phase composition.
  • the component is then quickly cooled, for example by quenching in water (10min) or in oil or by cooling with a fan. This fan cooling takes place in an oven, the temperature being reduced to 850 ° C. and held for 6 hours.
  • the ⁇ - and ⁇ -TiAl structure set at the temperature of the second heat treatment i.e. at a temperature of 1290 ° C.
  • the heat treatment temperature 1290 ° C, it is also avoided that the ⁇ -TiAl is completely converted into ⁇ -TiAl, which would lead to the risk of coarse grain growth with a corresponding temperature treatment.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • General Engineering & Computer Science (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (12)

  1. Procédé de fabrication d'un composant à partir d'un alliage TiAl comportant 42 à 45 % en atome de Ti, 3,5 à 4,5 % en atome de Nb, 0,75 à 1,5 % en atome de Mo, 0,05 à 0,15 % en atome de B et le reste d'aluminium et d'impuretés inévitables, selon lequel le composant est formé par forgeage, en particulier forgeage isotherme, et est ensuite soumis à au moins un traitement thermique, dans lequel lors d'un premier traitement thermique, la température est comprise entre 1 100 et 1 200 °C et est maintenue pendant 6 à 10 heures, et le composant est par la suite refroidi, caractérisé en ce que lors d'un deuxième traitement thermique, le composant est chauffé à une température supérieure à la ligne Solvus (1) de γ - TiAl et le composant, après le deuxième traitement thermique au-dessus de la ligne Solvus (1), est rapidement refroidi par trempe dans de l'eau ou de l'huile ou par refroidissement par air au moyen d'un ventilateur.
  2. Procédé selon la revendication 1, caractérisé en ce que la vitesse de refroidissement après le premier traitement thermique est comprise entre 1 °C/s et 5 °C/s.
  3. Procédé selon la revendication 1 ou 2, caractériséen ce que le composant est refroidi si rapidement après le deuxième traitement thermique qu'une conversion de l'a - TiAl en une structure lamellaire constituée de α-TiAl et de γ-TiAl est empêchée.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la température supérieure à la ligne Solvus (1) est maintenue jusqu'à ce qu'une composition de phase souhaitée constituée de α - TiAl et de γ - TiAl est atteinte.
  5. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la température lors du deuxième traitement thermique est choisie de façon à être supérieure à la ligne Solvus de 20 °C à 50 °C, en particulier de 25 °C à 35 °C, de préférence d'environ 30 °C.
  6. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le composant est formé d'un alliage TiAl comportant 42,5 à 44,5 % en atome de Ti, 4 à 4,2 % en atome de Nb, 0,9 à 1,2 % en atome de Mo, 0,1 à 0,12 % en atome de B et le reste d'aluminium et d'impuretés inévitables.
  7. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le formage du composant est effectué par forgeage isotherme.
  8. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le formage du composant est effectué par moulage de précision et ensuite par pressage isostatique à chaud.
  9. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le procédé comprend un troisième traitement thermique destiné à la stabilisation dans la plage de température comprise entre 800 °C et 950 °C pendant 5 à 7 heures.
  10. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la température lors de l'au moins un traitement thermique est réglée vers le haut et vers le bas avec une précision de 5 °C à 10 °C d'écart par rapport à la température de consigne.
  11. Composant, lequel est fabriqué au moyen d'un procédé selon l'une quelconque des revendications précédentes.
  12. Composant selon la revendication 11, caractérisé en ce que il s'agit d'un composant d'une turbomachine, en particulier d'une turbine à gaz ou d'un moteur d'aéronef, en particulier une aube mobile, une aube directrice ou une aube intégrée de turbine.
EP13705380.7A 2012-01-25 2013-01-19 Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé Active EP2807281B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012201082.3A DE102012201082B4 (de) 2012-01-25 2012-01-25 Verfahren zur Herstellung geschmiedeter Bauteile aus einer TiAl-Legierung und entsprechend hergestelltes Bauteil
PCT/DE2013/000037 WO2013110260A1 (fr) 2012-01-25 2013-01-19 Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé

Publications (2)

Publication Number Publication Date
EP2807281A1 EP2807281A1 (fr) 2014-12-03
EP2807281B1 true EP2807281B1 (fr) 2021-06-02

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EP13705380.7A Active EP2807281B1 (fr) 2012-01-25 2013-01-19 Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé

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US (1) US10107112B2 (fr)
EP (1) EP2807281B1 (fr)
DE (1) DE102012201082B4 (fr)
ES (1) ES2877557T3 (fr)
WO (1) WO2013110260A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2747155T3 (es) 2013-09-20 2020-03-10 MTU Aero Engines AG Aleación de TiAl resistente a la fluencia
ES2719706T3 (es) * 2015-01-28 2019-07-12 MTU Aero Engines AG Elemento componente con capa protectora y procedimiento para fabricar el mismo
DE102015115683A1 (de) * 2015-09-17 2017-03-23 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung einer Vorform aus einer Alpha+Gamma-Titanaluminid-Legierung zur Herstellung eines hochbelastbaren Bauteils für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
EP3238863A1 (fr) 2016-04-27 2017-11-01 MTU Aero Engines GmbH Procédé de fabrication d'une aube de turbomachine
EP3239468A1 (fr) 2016-04-27 2017-11-01 MTU Aero Engines GmbH Procédé de fabrication d'une aube de turbomachine
EP3326746A1 (fr) * 2016-11-25 2018-05-30 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Procédé pour assembler et/ou réparer des substrats d'alliages d'aluminure de titane
DE102018209881A1 (de) * 2018-06-19 2019-12-19 MTU Aero Engines AG Verfahren zur Herstellung eines geschmiedeten Bauteils aus einer TiAl-Legierung
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

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2386663A1 (fr) * 2010-05-12 2011-11-16 Böhler Schmiedetechnik GmbH & Co KG Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5558729A (en) 1995-01-27 1996-09-24 The United States Of America As Represented By The Secretary Of The Air Force Method to produce gamma titanium aluminide articles having improved properties
GB9714391D0 (en) 1997-07-05 1997-09-10 Univ Birmingham Titanium aluminide alloys
DE19756354B4 (de) 1997-12-18 2007-03-01 Alstom Schaufel und Verfahren zur Herstellung der Schaufel
WO2002048420A2 (fr) 2000-12-15 2002-06-20 Thyssenkrupp Automotive Ag Procede de fabrication de composants en alliages tial a capacite de charge elevee
AT508323B1 (de) 2009-06-05 2012-04-15 Boehler Schmiedetechnik Gmbh & Co Kg Verfahren zur herstellung eines schmiedestückes aus einer gamma-titan-aluminium-basislegierung

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2386663A1 (fr) * 2010-05-12 2011-11-16 Böhler Schmiedetechnik GmbH & Co KG Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane

Also Published As

Publication number Publication date
US10107112B2 (en) 2018-10-23
EP2807281A1 (fr) 2014-12-03
ES2877557T3 (es) 2021-11-17
DE102012201082B4 (de) 2017-01-26
DE102012201082A1 (de) 2013-07-25
US20140369822A1 (en) 2014-12-18
WO2013110260A1 (fr) 2013-08-01

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