EP2386663A1 - Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane - Google Patents

Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane Download PDF

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Publication number
EP2386663A1
EP2386663A1 EP11450055A EP11450055A EP2386663A1 EP 2386663 A1 EP2386663 A1 EP 2386663A1 EP 11450055 A EP11450055 A EP 11450055A EP 11450055 A EP11450055 A EP 11450055A EP 2386663 A1 EP2386663 A1 EP 2386663A1
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EP
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Prior art keywords
globular
volume fraction
particle size
gamma
mpa
Prior art date
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EP11450055A
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German (de)
English (en)
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EP2386663B1 (fr
Inventor
Helmut Clemens
Wilfried Wallgram
Martin Schloffer
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Voestalpine Boehler Aerospace GmbH and Co KG
MTU Aero Engines AG
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Voestalpine Boehler Aerospace GmbH and Co KG
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    • 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
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/045—Alloys based on refractory metals
    • C22C1/0458—Alloys based on titanium, zirconium or hafnium
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps

Definitions

  • the invention relates to a method for producing a component from a titanium-aluminum base alloy.
  • the invention relates to a component made of a titanium-aluminum base alloy, produced with dimensions close to the final dimensions.
  • Titanium-aluminum base alloys generally have high strength, low density, and good corrosion resistance, and are preferably used as components in gas turbines and aircraft engines.
  • Alloys having a composition of: aluminum 40 at.% To 50 at.%, Niobium 3 at.% To 10 at.%, Molybdenum to 4 at.%, And optionally the elements manganese, are suitable for the above fields of application. Boron, silicon, carbon, oxygen and nitrogen in low concentrations as well as titanium as the remainder of interest.
  • a schematic diagram ( Fig. 1 ) shows microstructures as a function of the temperature and the aluminum concentration with temperature range information used by the person skilled in the art.
  • Prepared the components can be by casting an ingot or powder by H schreib- I sostatisches- P ests (HIPing) of alloyed metal powder as well as by casting an ingot and optionally HIPing thereof followed by extrusion molding and each with a subsequent forging of the ingot or intermediate to a Component, which is subsequently subjected to heat treatments.
  • HIPing H prolongation- I sostatisches- P ests
  • Titanium-aluminum materials have only a narrow temperature window for a hot forming, although through the alloying elements niobium and molybdenum can be extended, nevertheless, there are limitations with respect to the deformation or forging of the parts. It is known, by slow, isothermal deformation, familiar to those skilled in the art as Isothermschmieden to produce a component at least partially by chipless shaping, but this is associated with great expense.
  • a component produced by the above technologies will usually not have a homogeneous microstructure because, on the one hand, a low and unequal recrystallization potential of the slowly isothermally deformed material is given, and / or, on the other hand, a time-consuming diffusion of the atoms of the elements niobium and / or molybdenum are important for a deformability of a material, align themselves with the forming structure and thus can adversely affect the structure.
  • a homogenization of the microstructure and thus achieving isotropic, mechanical properties of the material by time-consuming annealing treatments is in principle possible, but requires a lot of effort.
  • components made of a titanium-aluminum base alloy are required, which have direction-independent, homogeneous, mechanical properties, the ductility, strength and creep resistance of the material are balanced even at high operating temperatures at a high level.
  • the present invention has the object to provide a method by which a component having a homogeneous, fine and uniform microstructure can be produced, which component in balanced form, a ductility, strength and creep resistance of the material in all directions substantially the same has desired, high level and can be economically produced with dimensions close to final dimensions.
  • the invention further aims at a component which, in the case of a targeted phase shaping of the microstructure, has the desired mechanical properties, in particular the yield strength R p0 . 2 and strength R m and total elongation A t in Tensile test at room temperature and at a temperature of 700 ° C, having.
  • a melt or powder metallurgy produced material requires only compaction by hot isostatic pressing thereof, after which the blank is heated in a second step at an elevated temperature compared to isothermal forging and, as found, advantageously improved hot workability of the material -Massivumformung at a speed greater than 0.4 mm / sec and a compression ratio ⁇ of greater than 0.3 is subjected.
  • This rapid massive forming of the blank can, surprisingly for the expert, be carried out at elevated temperature with high forming speed, according to the invention a high minimum deformation and subsequent cooling with high cooling rate for a high, initially frozen Recrystallization potential in the structure are required.
  • This recrystallization potential or stored energy resulting from the rapid deformation, which is also formed from the driving force from the chemical phase imbalance, in a third step causes the alloy to undergo a transformation in the region of the eutectoid temperature of the alloy extremely finely-tuned microstructure of the phases GAMMA, BETA 0, ALPHA 2 with ordered at room temperature atomic structure with certain phase proportions, which microstructure serves as a favorable fine-grain starting structure for a subsequent, achievable by heat treatment (s), provided with regard to desired properties of the material structure formation ,
  • the starting material has a chemical composition of at.%: al 42 to 44.5 optionally Nb 3.5 to 4.5 Not a word 0.5 to 1.5 Mn to 2.2 B 12:05 to 0.2 Si 0001 to 12:01 C 0001 to 1.0 O 0001 to 0.1 N 0.0001 to 12:02 Titanium and impurities as rest having.
  • the supersaturated ALPHA 2 grains and a fine but non-optimized microstructural shape give low material ductility and toughness at high strength values.
  • Improved mechanical properties of the material can be achieved by means of a narrowed chemical composition, but the property profile is oriented only to specific uses.
  • a choice of annealing time at a post-anneal close to the alpha transus temperature (T ⁇ ) can be made with a view to setting desired phase amounts and grain sizes.
  • the ⁇ -phase is generally reduced as the annealing time increases.
  • the structural phases After a thermal treatment in the Alpha-Transus area and a forced Cooling, the structural phases essentially have a disordered atomic structure.
  • the supersaturated ALPHA 2 grains are converted into a lamellar ALPHA 2 / GAMMA structure without any significant change in grain size.
  • a lamellar structure in the formerly supersaturated structural grains greatly improves the creep resistance of the material at high temperatures of around 700 ° C in the temperature range.
  • This created with high efficiency of manufacturing component has a fine, globular, homogeneous microstructure with the same property profile in all directions of the material, which is advantageously used for a variety of applications.
  • Fig. 1 schematically the microstructures of titanium-aluminum base alloys are shown as a function of the temperature and the aluminum concentration. Furthermore, the temperature data used by the expert can be seen.
  • the in the Fig. 2 to Fig. 5 The microstructures shown are from a test series with an alloy Ti, 43.2 at.% Al, 4 at.% Nb, 1 at.% Mo, 0.1 at.% B.
  • micrographs were taken at 200X magnification on the scanning electron microscope in electron backscatter contrast.
  • a typical directed deformation texture shows as components directed GAMMA-BETA 0 -ALPHA 2 grains.
  • Fig. 3 shows the structure of the deformed part after a heat treatment in the region of the eutectioden temperature (T eu ) in the present case at 1150 ° C, followed by a cooling.
  • the microstructure consisted of globular ALPHA 2 grains with a particle size (measured as the diameter of the smallest circumscribed circle) of 3.2 ⁇ m ⁇ 1.9 ⁇ m with a volume fraction of approximately 25% from globular BETA 0 grains with a particle size of 3.7 ⁇ m ⁇ 2.1 ⁇ m with a volume fraction of about 26% and globular GAMMA grains with a grain size of 5.7 ⁇ m ⁇ 2.4 ⁇ m with a volume fraction of 49%.
  • Fig. 4 is the structure of the deformed and subsequently annealed at 1150 ° C and cooled part after a subsequent annealing in the range of the alpha transus temperature (T ⁇ ) in the given case at a temperature of 1240 ° C and a cooling of this to 700 ° C in 5 min and further cooling in air.
  • T ⁇ alpha transus temperature
  • microstructural constituents were: ALPHA 2 granules with a particle size of 11.0 ⁇ m ⁇ 5.8 ⁇ m with a volume fraction of 73%, globular BETA 0 grains with a particle size of 4.5 ⁇ m ⁇ 2.6 ⁇ m with a volume fraction of 11% and globular GAMMA grains with a grain size of 4.2 ⁇ m ⁇ 2.2 ⁇ m with a volume fraction of 16%.
  • Fig. 5 shows the structure of the deformed part after a fine grain annealing in the eutectoid temperature range (T eu ), a high temperature annealing in ( ⁇ + ⁇ + ⁇ ) phase space or an alpha transus annealing (T ⁇ ) at 1240 ° C and a forced cooling followed by Stabilization annealing in a given case at 875 ° C with subsequent slow cooling at a rate of 2 ° C / min.
  • T eu eutectoid temperature range
  • T ⁇ + ⁇ + ⁇ phase space
  • T ⁇ alpha transus annealing
  • microstructure of the microstructure and the property profile of the material can be adjusted by varying the annealing temperature and / or the annealing time.
  • the structure consisted of globular ALPHA 2 / GAMMA grains with a lamellar ⁇ / ⁇ structure with a grain size of 7.1 ⁇ m ⁇ 3.8 ⁇ m with a volume fraction of 64% from globular BETA 0 grains with a grain size of 2.3 ⁇ m ⁇ 2.2 ⁇ m with a volume fraction of 13% and of globular GAMMA phases with a grain size of 2.7 ⁇ m ⁇ 2.1 ⁇ m with a volume fraction of 23%.
  • a value A p of less than 0.65% was determined in the creep test (ASTME139 or EN2005-5) at a test voltage in the sample of 250 MPa and a stress duration of 100 hours.

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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)
  • Powder Metallurgy (AREA)
EP11450055.6A 2010-05-12 2011-04-26 Procédé de fabrication d'un composant et composants constitués d'un alliage à base d'aluminium-titane Active EP2386663B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ATA802/2010A AT509768B1 (de) 2010-05-12 2010-05-12 Verfahren zur herstellung eines bauteiles und bauteile aus einer titan-aluminium-basislegierung

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EP2386663A1 true EP2386663A1 (fr) 2011-11-16
EP2386663B1 EP2386663B1 (fr) 2017-08-02

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Country Link
US (1) US8864918B2 (fr)
EP (1) EP2386663B1 (fr)
JP (2) JP2011236503A (fr)
AT (1) AT509768B1 (fr)
CA (1) CA2739964C (fr)
ES (1) ES2644256T3 (fr)
IL (1) IL212821A (fr)

Cited By (10)

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WO2013110260A1 (fr) * 2012-01-25 2013-08-01 Mtu Aero Engines Gmbh Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé
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
WO2015081922A1 (fr) 2013-12-06 2015-06-11 Hanseatische Waren Handelsgesellschaft Mbh & Co. Kg Procédé de fabrication de pièces en tial
CN105051236A (zh) * 2013-02-22 2015-11-11 纳米钢公司 新类别的温成形先进高强度钢
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
EP3249064A1 (fr) * 2016-05-23 2017-11-29 MTU Aero Engines GmbH Fabrication additive de composants haute temperature en tial
EP3372700A1 (fr) 2017-03-10 2018-09-12 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
CN111020347A (zh) * 2019-12-30 2020-04-17 广州航海学院 一种高致密复相合金材料及其制备方法
EP3901295A4 (fr) * 2018-12-21 2022-08-17 National Institute for Materials Science Alliage à base de tial forgé à chaud, procédé de production d'un tel alliage et utilisations d'un tel alliage

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US9981349B2 (en) * 2013-05-31 2018-05-29 Arconic Inc. Titanium welding wire, ultrasonically inspectable welds and parts formed therefrom, and associated methods
US9651524B2 (en) * 2013-05-31 2017-05-16 Rti International Metals, Inc. Method of ultrasonic inspection of as-cast titanium alloy articles
EP2851445B1 (fr) 2013-09-20 2019-09-04 MTU Aero Engines GmbH Alliage TiAl résistant au fluage
JP6230885B2 (ja) * 2013-11-22 2017-11-15 東邦チタニウム株式会社 α＋β型チタン合金および同合金の製造方法
DE112015000354T9 (de) * 2014-02-05 2017-01-05 Borgwarner Inc. TiAl-Legierung insbesondere für Turboladeranwendungen, Turboladerkomponente, Turbolader und Verfahren zur Herstellung der TiAl-Legierung
CN103898428B (zh) * 2014-03-14 2015-10-28 西北工业大学 近α钛合金混合组织中片状α的重复退火球化方法
JP2018504282A (ja) * 2014-11-05 2018-02-15 アールティーアイ・インターナショナル・メタルズ，インコーポレイテッド Ｔｉ溶接ワイヤ、該溶接ワイヤから得られた超音波検査可能な溶接部及び溶接品、並びに関連する方法
CN104480347B (zh) * 2014-12-17 2017-03-29 南京理工大学 一种TiAl基合金及其热处理工艺
DE102014226805A1 (de) * 2014-12-22 2016-06-23 Robert Bosch Gmbh Turbinenrad und Verfahren zu seiner Herstellung
JP6884994B2 (ja) * 2015-09-07 2021-06-09 セイコーエプソン株式会社 チタン焼結体および装飾品
US20170067137A1 (en) * 2015-09-07 2017-03-09 Seiko Epson Corporation Titanium sintered body and ornament
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
HUE037106T2 (hu) * 2016-04-14 2018-08-28 Element 22 GmbH Eljárás alkatrészeknek titánból vagy titánötvözetekbõl való porkohászati gyártására
US20180010213A1 (en) * 2016-07-07 2018-01-11 United Technologies Corporation Enhance ductility of gamma titanium aluminum alloys by reducing interstitial contents
US20180010468A1 (en) * 2016-07-07 2018-01-11 United Technologies Corporation Enhanced temperature capability gamma titanium aluminum alloys
CN106363021B (zh) * 2016-08-30 2018-08-10 西部超导材料科技股份有限公司 一种1500MPa级钛合金棒材的轧制方法
JP6911651B2 (ja) * 2017-08-31 2021-07-28 セイコーエプソン株式会社 チタン焼結体、装飾品および時計
DE102018209315A1 (de) * 2018-06-12 2019-12-12 MTU Aero Engines AG Verfahren zur Herstellung eines Bauteils aus Gamma - TiAl und entsprechend hergestelltes Bauteil
SK288792B6 (sk) * 2018-07-12 2020-11-03 Ustav Materialov A Mech Strojov Sav Spôsob kontrolovaného legovania intermetalických zliatin γ-TiAl uhlíkom v priebehu vákuového indukčného tavenia v grafitových téglikoch
CN109207892B (zh) * 2018-11-05 2020-08-25 贵州大学 一种变形双相钛合金的组织控制工艺
CN110643842B (zh) * 2019-09-30 2021-12-14 西安欧中材料科技有限公司 一种镍基高温合金电极棒的制备方法
WO2023276067A1 (fr) * 2021-06-30 2023-01-05 住友電工ハードメタル株式会社 Outil de coupe
CN113502412B (zh) * 2021-07-03 2022-05-13 西北工业大学 一种可抑制有序ω相生成的TiAl合金及其制备方法

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Cited By (20)

* Cited by examiner, † Cited by third party
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WO2013110260A1 (fr) * 2012-01-25 2013-08-01 Mtu Aero Engines Gmbh Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé
EP2807281A1 (fr) * 2012-01-25 2014-12-03 MTU Aero Engines GmbH Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé
US10107112B2 (en) 2012-01-25 2018-10-23 MTU Aero Engines AG Method for producing forged components from a TiAl alloy and component produced thereby
EP2807281B1 (fr) * 2012-01-25 2021-06-02 MTU Aero Engines GmbH Procédé de fabrication de pièces forgées dans un alliage tial et pièce forgée fabriquée par ce procédé
DE102012201082B4 (de) * 2012-01-25 2017-01-26 MTU Aero Engines AG Verfahren zur Herstellung geschmiedeter Bauteile aus einer TiAl-Legierung und entsprechend hergestelltes Bauteil
CN105051236A (zh) * 2013-02-22 2015-11-11 纳米钢公司 新类别的温成形先进高强度钢
WO2015081922A1 (fr) 2013-12-06 2015-06-11 Hanseatische Waren Handelsgesellschaft Mbh & Co. Kg Procédé de fabrication de pièces en tial
DE102013020460A1 (de) 2013-12-06 2015-06-11 Hanseatische Waren Handelsgesellschaft Mbh & Co. Kg Verfahren zur Herstellung von TiAl-Bauteilen
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
EP3067435B1 (fr) 2015-03-09 2017-07-26 LEISTRITZ Turbinentechnik GmbH 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
EP3067435A1 (fr) * 2015-03-09 2016-09-14 LEISTRITZ Turbinentechnik GmbH 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
US10196725B2 (en) 2015-03-09 2019-02-05 LEISTRITZ Turbinentechnik GmbH Method for the production of a highly stressable component from an α+γ-titanium aluminide alloy for reciprocating-piston engines and gas turbines, especially aircraft engines
EP3249064A1 (fr) * 2016-05-23 2017-11-29 MTU Aero Engines GmbH Fabrication additive de composants haute temperature en tial
US10544485B2 (en) 2016-05-23 2020-01-28 MTU Aero Engines AG Additive manufacturing of high-temperature components from TiAl
US10737314B2 (en) 2017-03-10 2020-08-11 MTU Aero Engines AG Method for producing forged TiAl components
EP3372700A1 (fr) 2017-03-10 2018-09-12 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
EP3901295A4 (fr) * 2018-12-21 2022-08-17 National Institute for Materials Science Alliage à base de tial forgé à chaud, procédé de production d'un tel alliage et utilisations d'un tel alliage
CN111020347A (zh) * 2019-12-30 2020-04-17 广州航海学院 一种高致密复相合金材料及其制备方法

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AT509768A1 (de) 2011-11-15
EP2386663B1 (fr) 2017-08-02
US20110277891A1 (en) 2011-11-17
JP2017122279A (ja) 2017-07-13
AT509768B1 (de) 2012-04-15
JP6576379B2 (ja) 2019-09-18
US8864918B2 (en) 2014-10-21
IL212821A (en) 2014-11-30
CA2739964C (fr) 2014-02-18
JP2011236503A (ja) 2011-11-24
IL212821A0 (en) 2011-07-31
CA2739964A1 (fr) 2011-11-12

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