EP2807281A1 - 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

Info

Publication number
EP2807281A1
EP2807281A1 EP13705380.7A EP13705380A EP2807281A1 EP 2807281 A1 EP2807281 A1 EP 2807281A1 EP 13705380 A EP13705380 A EP 13705380A EP 2807281 A1 EP2807281 A1 EP 2807281A1
Authority
EP
European Patent Office
Prior art keywords
component
tial
heat treatment
temperature
solvus line
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP13705380.7A
Other languages
German (de)
English (en)
Other versions
EP2807281B1 (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
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2807281A1 publication Critical patent/EP2807281A1/fr
Application granted granted Critical
Publication of EP2807281B1 publication Critical patent/EP2807281B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 subsequently subjected to a heat treatment. Moreover, the present invention relates to a correspondingly manufactured component.
  • TiAl alloys whose main constituents 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 strength. In addition, they have a low specific weight, so that the use of Titanalumi- nide or TiAl alloys as in high-temperature applications, for example in turbomachines, especially gas turbines or aircraft engines, is suitable.
  • the property profile of the TiAl alloys can be further optimized.
  • Such alloys with niobium and molybdenum content are also referred to as so-called TNM alloys.
  • alloys are used in aircraft engines, for example, as guide or moving blades and are brought by forging in the appropriate component form.
  • isothermal forging can be used with subsequent heat treatment for adjusting the microstructure and the property profile.
  • blisk art word for blade and disk
  • a forged component made of a TiAl alloy ie an alloy in which the alloying constituents with the highest proportion of the alloy composition are titanium and aluminum, at least one first heat treatment after forging, in which at least in one step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and then cooled.
  • the TiAl material undergoes partial segregation.
  • This first heat treatment is referred to as homogenization annealing, as it does the material composition is homogenized over the component and existing concentration point are dissolved.
  • the cooling rate can be between 1 ° C / s and 5 ° C / s.
  • the component is heated in a second heat treatment over the solvus line of ⁇ -TiAl.
  • a second heat treatment in the microstructure, the contained ⁇ -TiAl is at least partially converted to another solid phase, such as e.g. a TiAl converted, so that a desired or adapted phase composition in the TiAl alloy is made possible and in particular depending on the chemical composition of the component by varying the phase composition adjustment of optimum mechanical properties, in particular with respect to the total elongation and creep resistance is possible.
  • the heat treatment can be tailored specifically to the specific chemical composition and its scattering in the component.
  • the component may be rapidly cooled after the second heat treatment above the solvus line of the ⁇ -TiAl to substantially freeze the phase composition set at the heat treatment temperature.
  • Quick cooling can be done, for example, by quenching in water or oil, or by air cooling with a blower.
  • the cooling can take place so quickly that a conversion of ⁇ -TiAl additionally formed in the second heat treatment into a lamellar structure of ⁇ -TiAl and ⁇ -TiAl is avoided.
  • the second heat treatment may be performed at a temperature that avoids entering a single-phase phase field of the TiAl phase diagram, such as the ⁇ -TiAl phase field, by the risk of coarse grain growth associated with heat treatment in a single-phase phase field prevention.
  • the second heat treatment can be carried out for a period of time which ensures sufficient conversion of the ⁇ -TiAl to another phase, in particular a-TiAl, so that the desired phase composition can be achieved.
  • the temperature in the second heat treatment over the ⁇ -TiAl solvus line can 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 can be selected.
  • the method can be used in particular for components which consist of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 to 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 balance aluminum and unavoidable impurities.
  • a phase composition with corresponding proportions of the ⁇ -TiAl is present, which makes the use of the method according to the invention particularly advantageous.
  • the second heat treatment may be carried out at a temperature below the solvus line ⁇ -TiAl, the temperature being in particular between 12 ° C and 18 ° C below the solvus line.
  • a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours may additionally be carried out in order to stabilize the material charge in the component (stabilization annealing).
  • a turbomachine in particular a gas turbine or an aircraft engine, in particular blades, vanes, or turbine blades, which have a variably adjustable property profile due to an adapted phase composition.
  • a material for a component produced according to the invention can be, for example, a composition in the range of 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 at.% Boron with balance aluminum and unavoidable impurities.
  • a corresponding component can for example be forged isothermally until it has the rough contour of the final component to be produced.
  • the material of the component is homogenized by a first heat treatment at, for example, 1150 ° C for 8 hours.
  • the component may then be annealed in a first first alternative of a second heat treatment then at a temperature of, for example, 1290 ° C (ie, above the solvus line (l)) for a predetermined period of time to permit partial conversion of the ⁇ -TiAl to ⁇ -TiAl cause ⁇ -TiAl and ⁇ -TiAl to coexist in the microstructure.
  • the temperature treatment can be carried out until a sufficient amount of ⁇ -TiAl has been converted to ⁇ -TiAl for the desired phase composition.
  • the component is cooled rapidly, for example by quenching in water (10 min) or in oil or by cooling with a blower. This fan cooling takes place in an oven, the temperature is lowered to 850 ° C and held for 6 hours.
  • the ⁇ and ⁇ -TiAl microstructure set at the temperature of the second heat treatment are largely frozen and a conversion of the ⁇ phase into ⁇ / ⁇ fins is avoided.
  • the choice of the heat treatment temperature of 1290 ° C also avoids that the ⁇ -TiAl is completely converted into ⁇ -TiAl, which would lead to the risk of coarse grain growth with a corresponding temperature treatment.
  • the component is heated below the solvus line (1). For example, the component is heated at 1235 ° C for one hour, then cooled the component (with water, oil or Ofenkkühlung). During the oven cooling, the temperature is lowered to 850 ° C and held for 6 hours.

Landscapes

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

Abstract

La présente invention concerne un procédé de fabrication d'une pièce dans un alliage TiAl, selon lequel la pièce est façonnée par forgeage, en particulier forgeage isotherme, puis soumise à au moins un traitement thermique, la température lors du premier traitement thermique étant comprise entre 1100 et 1200 °C et maintenue pendant 6 à 10 heures, et la pièce étant ensuite refroidie.
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 true EP2807281A1 (fr) 2014-12-03
EP2807281B1 EP2807281B1 (fr) 2021-06-02

Family

ID=47747265

Family Applications (1)

Application Number Title Priority Date Filing Date
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

Country Status (5)

Country Link
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
EP2851445B1 (fr) 2013-09-20 2019-09-04 MTU Aero Engines GmbH Alliage TiAl résistant au fluage
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
EP3239468A1 (fr) 2016-04-27 2017-11-01 MTU Aero Engines GmbH Procédé de fabrication d'une aube de turbomachine
EP3238863A1 (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
EP1341945B1 (fr) * 2000-12-15 2008-01-09 Leistritz Aktiengesellschaft 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2013110260A1 *

Also Published As

Publication number Publication date
US20140369822A1 (en) 2014-12-18
WO2013110260A1 (fr) 2013-08-01
DE102012201082A1 (de) 2013-07-25
DE102012201082B4 (de) 2017-01-26
EP2807281B1 (fr) 2021-06-02
ES2877557T3 (es) 2021-11-17
US10107112B2 (en) 2018-10-23

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