EP2742162B1 - Procédé de fabrication des composants en tial forgés - Google Patents

Procédé de fabrication des composants en tial forgés Download PDF

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Publication number
EP2742162B1
EP2742162B1 EP12762523.4A EP12762523A EP2742162B1 EP 2742162 B1 EP2742162 B1 EP 2742162B1 EP 12762523 A EP12762523 A EP 12762523A EP 2742162 B1 EP2742162 B1 EP 2742162B1
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EP
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Prior art keywords
phase
temperature
tial
heat
percent
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EP12762523.4A
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German (de)
English (en)
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EP2742162A1 (fr
Inventor
Dietmar Helm
Falko Heutling
Ulrike Habel
Wilfried Smarsly
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MTU Aero Engines AG
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MTU Aero Engines 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
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • 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
    • 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 forged components from a TiAl alloy, in particular components for gas turbines, preferably aircraft turbines and in particular turbine blades for low-pressure turbines. Moreover, the present invention relates to corresponding components.
  • titanium aluminides Due to their low specific weight and their mechanical properties, components of titanium aluminides are of interest for use in gas turbines, in particular aircraft turbines. However, for titanium aluminide materials, the microstructures must be precisely adjusted to achieve the desired mechanical properties.
  • a method for producing forged components from a Ti-43Al-4Nb-lMo-0.1B alloy is known from " Microstructural and Tensile Ductility of a Ti-43Al-4Nb-1Mo-0.1B Alloy "- Laura, M. Droessler et al, Mater.Res.Soc.Symp.Proc, vol 1128, 2009 Materials research Society, pages 121-126 , known.
  • the components are subjected to a two-stage heat treatment after forging, wherein the first stage of the heat treatment provides recrystallization annealing below the ⁇ / ⁇ transformation temperature for a period of 50 to 100 minutes ,
  • the annealing at a temperature below the ⁇ / ⁇ transformation temperature at which ⁇ -titanium is converted into ⁇ -TiAl in accordance with the phase diagram for the TiAl alloy used may take place as close as possible to the ⁇ / ⁇ transformation temperature, with a temperature of 15 ° C, in particular 10 ° C, below the ⁇ / ⁇ - conversion temperature should not fall below.
  • the recrystallization annealing may preferably be carried out for 60 to 90 minutes, especially 70 to 80 minutes.
  • the first stage of the heat treatment with the recrystallization annealing is followed by a second stage of the heat treatment with stabilizing annealing in the temperature range of 800 ° C to 950 ° C for 5 to 7 hours.
  • the stabilization annealing can be carried out in particular in the temperature range from 825 ° C. to 925 ° C., preferably from 850 ° C. to 900 ° C., with a holding time of from 345 minutes to 375 minutes.
  • the cooling in the recrystallization annealing can be carried out by air cooling, wherein in the temperature range between 1300 ° C and 900 ° C, the cooling rate ⁇ 3 ° C per second should be to set a fine-lamellar microstructure of ⁇ 2 -Ti 3 Al and ⁇ -TiAl in the corresponding ⁇ 2 - and ⁇ -phase, which ensures the required mechanical properties.
  • the cooling in the second heat treatment stage, so the stabilization annealing, can be done with correspondingly lower cooling rates in the oven.
  • the heat treatment steps are carried out as accurately as possible at the corresponding selected temperature.
  • an increasingly precise adjustment of the temperature and holding the components at the appropriate temperatures associated with increasing effort so that a compromise must be found for an economically meaningful processing.
  • a temperature adjustment with a deviation in the range of 5 ° C to 10 ° C up and down from the target temperature has been found to be advantageous.
  • the selected target temperature for the heat treatment steps of the present invention can be set and maintained in a corresponding temperature window of 5 ° C to 10 ° C deviation from the target temperature up and down.
  • titanium-titanium aluminide alloys alloyed with niobium and molybdenum can be used in particular.
  • Such alloys are also referred to as TNM alloys.
  • an alloy of 42 to 45 atomic percent aluminum, 3 to 5 atomic percent niobium and 0.5 to 1.5 atomic percent molybdenum is used.
  • the aluminum content may be selected in the range of 42.8 to 44.2 atomic percent aluminum, while 3.7 to 4.3 atomic percent of niobium and 0.8 to 1.2 atomic percent of molybdenum may be alloyed.
  • the alloy may be alloyed with boron in the range of 0.05 to 0.15 atomic percent boron, more preferably 0.07 to 0.13 atomic percent boron.
  • the alloy may include unavoidable impurities such as carbon, oxygen, nitrogen, hydrogen, chromium, silicon, iron, copper, nickel and yttrium, the content of which is ⁇ 0.05% by weight of chromium, ⁇ 0.05% by weight of silicon, ⁇ 0.08 wt% oxygen, ⁇ 0.02 wt% carbon, ⁇ 0.015 wt% nitrogen, ⁇ 0.005 wt% hydrogen, ⁇ 0.06 wt% iron, ⁇ 0.15 wt% copper, ⁇ 0.02 wt% nickel, and ⁇ 0.001 wt% yttrium , Further constituents may be contained individually in the range of 0 to 0.05 percent by weight or in total from 0 to 0.2 percent by weight.
  • unavoidable impurities such as carbon, oxygen, nitrogen, hydrogen, chromium, silicon, iron, copper, nickel and yttrium, the content of which is ⁇ 0.05% by weight of chromium, ⁇ 0.05% by weight of silicon
  • the forging of the corresponding components can be carried out by drop forging in the ⁇ - ⁇ - ⁇ -temperature range, which can be used as a starting material for forging cast and / or hot isostatically pressed blanks.
  • the blanks themselves can be produced by melting in vacuo or inert gas with self-consumable electrodes or in the cooled crucible by means of plasma arc melting, wherein a single or multiple remelting of the alloy can be performed.
  • the remelting may be by vacuum induction melting or vacuum arc remelting (VIM vacuum induction melting), and the cast material may be hot isostatically pressed using temperatures ⁇ 200 ° C at a pressure ⁇ 190 MPa and a holding time ⁇ 4 hours can.
  • a component made of a TiAl alloy in particular a component of a gas turbine, preferably an aircraft turbine, which is produced in particular according to the above-described method, is provided, which has a triplex structure with a globulitic ⁇ -TiAl phase, a B2-TiAl Phase (cubic body-centered phase) and a lamellar ⁇ 2 -Ti 3 Al and ⁇ -TiAl phase is constructed.
  • the proportion of the ⁇ -phase is in this case 2 to 20 percent by volume, the proportion of the B2 phase 1 to 20 percent by volume and the proportion of the ⁇ -phase together with the B2 phase 5 to 25 percent by volume.
  • the proportion of the ⁇ -phase 5 to 15 volume percent and the proportion of B2 phase 3 to 15 volume percent and the proportion of the two phases together amount to 8 to 20 volume percent.
  • the size of the ⁇ -phase or the ⁇ -grains may be set so that a circumscribed circle has a diameter ⁇ 40 ⁇ m. The same applies to the B2 phase or B2 grains.
  • the lamellar microstructure areas of ⁇ 2 and ⁇ phase have a size in which the equivalent area of a circle has a diameter of ⁇ 100 ⁇ m.
  • the aspect ratio of the lamellar ⁇ 2 and ⁇ phase ie the ratio of the length to the width of the lamellae, can be ⁇ 3: 1.
  • the structure may additionally have borides.
  • the thus molten material was hot isostatically compacted at a temperature of> 1200 ° C and a pressure of greater than 190 MPa for a holding time of more than 4 hours, and then forged in a die forging at a temperature in the ⁇ - ⁇ - ⁇ phase region , Subsequently, a heat treatment was carried out with recrystallization annealing below the ⁇ / ⁇ transformation temperature for 75 minutes with air cooling at a cooling rate of more than 3 ° C per second. Subsequently, the corresponding component was subjected to stabilization annealing at 920 ° C. for 6 hours and then cooled in the oven.
  • Such a component such as a turbine blade for a low-pressure turbine in an aircraft engine, has a triplex structure according to the invention with corresponding proportions of ⁇ phase, B2 phase and lamellar ⁇ 2 and ⁇ phase.
  • a yield strength (0.2% proof strength Rp 0.2 ) of more than 670 MPa and a tensile strength R m of more than 840 MPa for a total elongation (elastic and plastic elongation to breakage) ) A dead higher than 1.7%.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Procédé de fabrication de composants forgés en un alliage TiAl, notamment d'aubes de turbine, dans lequel les composants sont forgés et soumis à un traitement thermique en deux étapes après le forgeage, dans lequel la première étape du traitement thermique comprend un recuit de recristallisation pendant 50 à 100 minutes à une température inférieure à la température de transition γ/α, à savoir dans la plage de température entre 1300 °C et 900 °C, en particulier une température de refroidissement de recristallisation entre 1200 °C et 1300 °C, et la seconde étape du traitement thermique comprend un recuit de stabilisation dans la plage de température de 800 °C à 950 °C pendant 5 à 7 heures, et dans lequel un alliage TiAl avec 42 à 45 % d'atomes d'aluminium, 3 à 5 % d'atomes de niobium et 0,5 à 1,5 % d'atomes de molybdène est utilisé, caractérisé en ce que la vitesse de refroidissement lors de la première étape de traitement thermique est supérieure ou égale à 3 °C/s, afin d'obtenir une structure lamellaire fine en α2-Ti3Al et en γ-TiAl dans une phase correspondante α2 et γ.
  2. Procédé selon la revendication 1,
    caractérisé en ce que
    le recuit de recristallisation est effectué pendant 60 à 90 minutes, en particulier 70 à 80 minutes, et/ou le recuit de stabilisation est effectué dans la plage de température de 825 °C à 925 °C, en particulier 850 °C à 900 °C et/ou pendant 345 à 375 minutes.
  3. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que
    la température, pendant le traitement thermique, est réglée avec une précision de 5 °C à 10 °C de déviation par rapport à la température souhaitée vers le haut et vers le bas et maintenue.
  4. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que,
    lors du recuit de recristallisation, la température ne descend pas sous une température inférieure de 15 °C, en particulier de 10 °C, à la température de transition γ/α.
  5. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que
    un alliage avec 0,05 à 0,15 % d'atomes de bore est utilisé.
  6. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que
    le composant est fabriqué par un estampage dans la plage de température α-γ-β.
  7. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que
    des ébauches coulées ou soumises à une compression isostatique à chaud sont utilisées en tant que matériau brut pour le forgeage.
  8. Procédé selon l'une des revendications précédentes,
    caractérisé en ce que
    le composant présente une structure en triple hélice après la seconde étape de traitement thermique, avec une phase γ-TiAl globulaire, une phase B2-TiAl et une phase α2-Ti3Al et γ-TiAl lamellaire.
  9. Procédé selon la revendication 8,
    caractérisé en ce que
    la proportion de la phase γ atteint 2 à 20 pour cent en volume, la proportion de la phase B2 atteint 1 à 20 pour cent en volume et la proportion de la phase γ conjointement avec la phase B2 atteint 5 à 25 pour cent en volume.
EP12762523.4A 2011-08-11 2012-08-09 Procédé de fabrication des composants en tial forgés Active EP2742162B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011110740.5A DE102011110740B4 (de) 2011-08-11 2011-08-11 Verfahren zur Herstellung geschmiedeter TiAl-Bauteile
PCT/DE2012/000804 WO2013020548A1 (fr) 2011-08-11 2012-08-09 Composants en tial forgés et procédé de fabrication de ceux-ci

Publications (2)

Publication Number Publication Date
EP2742162A1 EP2742162A1 (fr) 2014-06-18
EP2742162B1 true EP2742162B1 (fr) 2015-10-07

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ID=46924179

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EP12762523.4A Active EP2742162B1 (fr) 2011-08-11 2012-08-09 Procédé de fabrication des composants en tial forgés

Country Status (5)

Country Link
US (1) US20140202601A1 (fr)
EP (1) EP2742162B1 (fr)
DE (1) DE102011110740B4 (fr)
ES (1) ES2553439T3 (fr)
WO (1) WO2013020548A1 (fr)

Families Citing this family (13)

* 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
DE102013020460A1 (de) * 2013-12-06 2015-06-11 Hanseatische Waren Handelsgesellschaft Mbh & Co. Kg Verfahren zur Herstellung von TiAl-Bauteilen
CN103993248B (zh) * 2014-06-20 2016-12-07 南昌航空大学 使tc21合金两相区超塑性变形后获得网篮组织的热处理工艺
CN104264012A (zh) * 2014-09-30 2015-01-07 西北有色金属研究院 一种含钼高铌β型γ-TiAl合金铸锭及其制备方法
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
CN105220096B (zh) * 2015-11-04 2017-03-08 哈尔滨工业大学 一种改善传统铸造γ‑TiAl合金力学性能的多步循环热处理方法
US20180010468A1 (en) * 2016-07-07 2018-01-11 United Technologies Corporation Enhanced temperature capability gamma titanium aluminum alloys
US20180010213A1 (en) * 2016-07-07 2018-01-11 United Technologies Corporation Enhance ductility of gamma titanium aluminum alloys by reducing interstitial contents
CN109312427B (zh) * 2016-09-02 2020-12-15 株式会社Ihi TiAl合金及其制造方法
DE102016224386A1 (de) * 2016-12-07 2018-06-07 MTU Aero Engines AG Verfahren zum herstellen einer schaufel für eine strömungsmaschine
ES2753242T3 (es) 2017-03-10 2020-04-07 MTU Aero Engines AG Procedimiento para fabricar componentes de TiAl forjados
DE102017212082A1 (de) 2017-07-14 2019-01-17 MTU Aero Engines AG Schmieden bei hohen temperaturen, insbesondere von titanaluminiden
CN109500331B (zh) * 2018-11-02 2020-03-17 湖南金天钛业科技有限公司 Tc25钛合金大规格棒材加工方法

Family Cites Families (6)

* 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
DE19756354B4 (de) * 1997-12-18 2007-03-01 Alstom Schaufel und Verfahren zur Herstellung der Schaufel
AT2881U1 (de) * 1998-06-08 1999-06-25 Plansee Ag Verfahren zur herstellung eines tellerventiles aus gamma-tial-basislegierungen
DE102007051499A1 (de) * 2007-10-27 2009-04-30 Mtu Aero Engines Gmbh Werkstoff für ein Gasturbinenbauteil, Verfahren zur Herstellung eines Gasturbinenbauteils sowie Gasturbinenbauteil
DE102007060587B4 (de) * 2007-12-13 2013-01-31 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Titanaluminidlegierungen
US8876992B2 (en) * 2010-08-30 2014-11-04 United Technologies Corporation Process and system for fabricating gamma TiAl turbine engine components

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
HELMUT CLEMENS ET AL.: "Design of Novel beta-Solidifying TiAl Alloys with Adjustable beta/B2-Phase Fraction and Excellent Hot-Workability", ADVANCED ENGINEERING MATERIALS, vol. 10, no. 8, 2008, Weinheim, pages 707 - 713, XP002612341
LAURA DROESSLER ET AL.: "Microstructure and Tensile Ductility of a Ti-43Al-4Nb-1 Mo-0.1 B Alloy", MATER.RES.SOC.SYMP.PROC., vol. 1128, 2009, pages 121 - 126, XP009165478
LIMEI CHA ET AL.: "nanometer-scaled Imellar microstructures in Ti-45Al-7.5Nb-(0;0.5)C alloys and their influence on hardness", INTERMETALLICS, vol. 16, no. 7, July 2008 (2008-07-01), pages 868 - 875, XP022733484
MANFRED PETERS ET AL., TITAN- UND TITANLEGIERUNGEN, September 2002 (2002-09-01), Weinheim, pages 369 - 405, XP055298667, ISBN: 3-527-30539-4

Also Published As

Publication number Publication date
WO2013020548A8 (fr) 2013-07-18
WO2013020548A1 (fr) 2013-02-14
DE102011110740A1 (de) 2013-02-14
US20140202601A1 (en) 2014-07-24
ES2553439T3 (es) 2015-12-09
DE102011110740B4 (de) 2017-01-19
EP2742162A1 (fr) 2014-06-18

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