EP2851445A1 - Alliage TiAl résistant au fluage - Google Patents

Alliage TiAl résistant au fluage Download PDF

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Publication number
EP2851445A1
EP2851445A1 EP13185280.8A EP13185280A EP2851445A1 EP 2851445 A1 EP2851445 A1 EP 2851445A1 EP 13185280 A EP13185280 A EP 13185280A EP 2851445 A1 EP2851445 A1 EP 2851445A1
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EP
European Patent Office
Prior art keywords
tial
alloy
annealing
temperature
tial alloy
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
EP13185280.8A
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German (de)
English (en)
Other versions
EP2851445B1 (fr
Inventor
Wilfried Dr. Smarsly
Helmut Prof. Dr. Clemens
Emanuel Schwaighofer
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MTU Aero Engines AG
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MTU Aero Engines AG
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Publication date
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Priority to ES13185280T priority Critical patent/ES2747155T3/es
Priority to EP13185280.8A priority patent/EP2851445B1/fr
Priority to US14/481,295 priority patent/US9994934B2/en
Publication of EP2851445A1 publication Critical patent/EP2851445A1/fr
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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
    • 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
    • C22F1/16—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
    • 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
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium

Definitions

  • the present invention relates to a TiAl alloy which, in addition to titanium and aluminum, comprises niobium and molybdenum and / or manganese and is referred to in the art as TNM alloy.
  • TiAl alloys based on the ⁇ -TiAl intermetallic phase are predestined for applications in turbomachines, such as stationary gas turbines and aircraft engines, due to their low specific weight and high strength due to the ordered intermetallic phase.
  • turbomachines such as stationary gas turbines and aircraft engines
  • the ordered intermetallic phase For example, describes the US 2011/0189026 A1 a TiAl - based alloy for the manufacture of gas turbine components.
  • the alloy described therein is a so-called TNM alloy which, in addition to 42 to 45 at.% Aluminum, contains 3 to 8 at.% Niobium and 0.2 to 3 at.% Molybdenum and / or manganese. In addition, 0.1 to 1 at.% Boron and / or carbon and / or silicon may be included. The remainder of the alloy is formed by titanium.
  • Such alloys which in particular have 43.5 at.% Aluminum, 4 at.% Niobium, 1 at.% Molybdenum and 0.1 percent boron with the remainder of titanium, are suitable for use at operating temperatures of 750 ° C. to 780 ° C suitable.
  • TNM alloys is complexly composed of several phases and comprises ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o / B2 - titanium.
  • Another alloy with a structure of ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ - phase is in US 2011/0277891 A1 described.
  • This alloy has 42 to 44.5 at.% Aluminum, 3.5 to 4.5 at.% Niobium, 0.5 to 1.5 percent molybdenum, up to 2.2 at.% Manganese, 0.05 to 0 , 2 at.% Boron, 0.001 to 0.01 at.% Silicon, 0.001 to 1.0 at.% Carbon, 0.001 to 0.1 at.% Oxygen, 0.0001 to about 0.002 at.% Nitrogen and the balance titanium and impurities on.
  • TNM alloys are limited to temperatures below 800 ° C, since prolonged use at higher temperatures insufficient creep resistance is observed, which has an insufficient life for use in turbomachinery, such as stationary gas turbine or aircraft engines result ,
  • the present invention makes it possible to improve the known TNM alloys in their creep resistance and thus to increase the possible use temperatures.
  • the known composition of the TNM alloys it is proposed to limit the aluminum content to a maximum of 43 at.%.
  • the combined and targeted reduction of the aluminum content and the simultaneous provision of certain proportions of carbon and silicon can significantly improve the creep resistance of a corresponding TiAl alloy and thus increase the operating temperature in the range of 800 to 850 ° C.
  • the chemical composition of a corresponding alloy can not exceed 43 at.% Aluminum, 3 to 8 at.% Niobium, 0.2 at.% To 3 at.% Molybdenum and / or manganese, 0.05 at.% To 0.5 % boron, 0.1 at.% to 0.5 at.% carbon, 0.1 at.% to 0.5 at.% silicon, and the balance titanium and unavoidable impurities.
  • the TiAl alloy may be at most 43 at.% Aluminum, 3.5 at.% To 4.5 at.% Niobium, 0.8 at.% To 1.2 at.% Molybdenum and / or manganese, 0.05 % to 0.15 at.% boron, 0.2 at.% to 0.4 at.% carbon, 0.2 at.% to 0.4 at.% silicon and the balance titanium and unavoidable impurities.
  • a TiAl alloy has proved to be advantageous which contains 43 at.% Aluminum, 4 at.% Niobium, 1 at.% Molybdenum, 0.1 at.% Boron, 0.3 at.% Carbon, 0.3 at. % Silicon and the rest titanium and unavoidable impurities.
  • the specified values are not absolute values, but represent target values, from which within the limits of the technical feasibility can be deviated, which are thus adjustable according to the accepted rules of technology in a certain accuracy range.
  • Such an alloy has a microstructure at room or operating temperatures which has the phases ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o / B2 - titanium, the B2 or ⁇ o phase being an ordered variant of the ⁇ - Titans represents.
  • a corresponding component with a TiAl alloy according to the invention can be produced by casting with or without subsequent cold and / or hot working.
  • a common method for producing corresponding components of turbomachines, such as turbine blades, is to cast a blank and then hot-form it by forging.
  • a suitably prepared intermediate may be subjected to a heat treatment according to the present invention comprising annealing at a temperature between 800 ° C and 900 ° C for 4 to 8 hours. Such stabilization annealing can be used to optimize the desired microstructure of a TNM alloy for improved creep resistance.
  • the annealing may take place at a temperature of or around 850 ° C for 6 hours.
  • the corresponding component can be cooled rapidly, for example to ambient atmosphere or by flowing with a cooling gas.
  • the heat treatment may include, in addition to the above-described annealing, additional heat treatment steps that take place before annealing.
  • the heat treatment can be configured in two stages with an aging upstream of the annealing.
  • the use of the terms outsourcing and annealing here does not indicate fundamentally different process mechanisms, but merely serves to distinguish the heat treatment stages.
  • thermomechanical treatments it is possible to carry out further thermal and / or thermomechanical treatments before or after the heat treatment described here.
  • the heat treatment described herein should be the final heat treatment.
  • the aging as the first stage of a two-stage heat treatment may take place at a temperature of 950 ° C to 1300 ° C for 0.1 hour to 2 hours.
  • the aging can take place at a temperature of 950 ° C to 1050 ° C or 1200 ° C to 1300 ° C for a period of 0.25 hours to 1 hour.
  • a TiAl alloy with the presented composition and a component made of a corresponding TiAl alloy, which has been subjected in particular to the presented production method with the heat treatment according to the invention, can advantageously be used for components of turbomachines, such as, for example, blades of a turbomachine.
  • the components can be used at temperatures up to 850 ° C, in particular in the operating temperature range from 800 ° C to 830 ° C, wherein operating temperature here means that the corresponding temperature occurs permanently during operation or the temperature can occur as a peak temperature in the short term during operation ,
  • the attached figure shows a microstructure of a typical structure of a material according to the invention.
  • a blade of an aircraft engine can be produced by first casting the above-mentioned TNM alloy and hot isostatically pressing.
  • the fine - grained and supersaturated TNM alloy is subjected to a two - stage heat treatment.
  • a targeted ⁇ - lamella width is set for the first removal in order to optimize the creep properties ("short-time annealing").
  • phase fractions are set close to the thermodynamic equilibrium (“long-term annealing”).
  • the heat treatment process for the microstructure with a particularly good creep resistance takes place, for example, with an aging at 1000 ° C. for 15 minutes with a subsequent rapid cooling and annealing at 850 ° C. for 6 hours and likewise rapid cooling.
  • the first removal results in the formation of a cellular reaction phase (ZR) starting from the boundaries of the ⁇ 2 -Ti 3 Al / ⁇ -TiAl colonies, which occurs in different amounts depending on the aging temperature and duration and represents a transformation structure.
  • ZR cellular reaction phase
  • the driving force for the cellular reaction and the corresponding formation of the cellular reaction phase comes to a standstill because of the larger lamellar spacing.
  • the described method results in combination with the selected material with less effort compared to the previous methods to significantly improved mechanical properties. Avoiding high-temperature annealing prevents the risk of grain growth.
  • a correspondingly produced component such as, for example, a blade of an aircraft engine, has improved creep resistance compared to previously known TiAl alloys and in particular TNM alloys.
  • FIGURE A characteristic structure of a component according to the invention produced according to the invention of a TiAl alloy according to the invention is shown in the appended FIGURE.
  • This microstructure is a nearly lamellar microstructure with small amounts of ⁇ o - phase in the order of ⁇ 5 vol.% (NL ⁇ ).
  • the ⁇ o - titanium phase can be linear or globular. Within the ⁇ o phase are lenticular ⁇ - TiAl precipitates.
  • the structure consists with up to 98 vol.% Mainly of globular ⁇ 2 - Ti 3 Al / ⁇ - TiAl colonies with a maximum size of ⁇ 10 - 20 ⁇ m and an average width of the ⁇ - TiAl lamellae of the order of 50 - 150 nm. In general, there are no globular ⁇ - grains, which can lead to a reduction of the creep resistance from a volume fraction of about> 5%.
  • the volume fraction of cellular reaction phase (ZR) is less than 10 vol.%.
  • the microstructure of a corresponding component may comprise about 70 to 80 vol.%, In particular about 75 vol.% ⁇ -TiAl, 20 to 25 vol.%, In particular about 23 vol.% ⁇ 2 -Ti 3 Al and 1 to 3 vol.%, in particular about 2 vol.% ⁇ o - Ti.
  • the carbon is mainly present in solution.
  • Small proportions of H carbides and silicides, in particular of less than 3% by volume in total, preferably less than 1% by volume, and of cellular reaction phase (ZR) may additionally be present in the microstructure, the microstructural constituents being of course 100% by volume. and wherein the cellular reaction phase is assigned to the proportions of ⁇ - TiAl and ⁇ 2 - Ti 3 Al.
  • the microstructural fractions of ⁇ - TiAl, ⁇ 2 - Ti 3 Al and ⁇ o - Ti hardly change, ie the microstructure remains stable, but the creep under conditions of use leads to the precipitation of very fine carbides within the ⁇ -TiAl phase, eg in the form of P-Ti 3 AlC, which contribute to the hindrance of dislocation creep and thus to an increase in creep resistance.
  • the finest silicide precipitates ( ⁇ - Ti 5 Si 3 ) at the ⁇ 2 - Ti 3 Al / ⁇ - TiAl interfaces improve the microstructure stability. Residues of coarser silicides can be contained in the microstructure depending on the choice of the forming and heat treatment parameters.
  • the fine-grained NLSS microstructure is characterized by high high-temperature strength, creep resistance and microstructure stability with significantly improved damage tolerance below the brittle-ductile transition temperature due to the small size and globular formation of ⁇ 2 -Ti 3 Al / ⁇ -TiAl colonies.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13185280.8A 2013-09-20 2013-09-20 Alliage TiAl résistant au fluage Not-in-force EP2851445B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES13185280T ES2747155T3 (es) 2013-09-20 2013-09-20 Aleación de TiAl resistente a la fluencia
EP13185280.8A EP2851445B1 (fr) 2013-09-20 2013-09-20 Alliage TiAl résistant au fluage
US14/481,295 US9994934B2 (en) 2013-09-20 2014-09-09 Creep-resistant TiA1 alloy

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13185280.8A EP2851445B1 (fr) 2013-09-20 2013-09-20 Alliage TiAl résistant au fluage

Publications (2)

Publication Number Publication Date
EP2851445A1 true EP2851445A1 (fr) 2015-03-25
EP2851445B1 EP2851445B1 (fr) 2019-09-04

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104878452A (zh) * 2015-05-13 2015-09-02 南京理工大学 一种高温高强TiAl-Nb单晶及其制备方法
EP3266889A1 (fr) * 2016-07-07 2018-01-10 United Technologies Corporation Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles
EP3266888A1 (fr) * 2016-07-07 2018-01-10 United Technologies Corporation Capacité de température améliorée d'alliages d'aluminium de titane gamma
EP3269838A1 (fr) * 2016-07-12 2018-01-17 MTU Aero Engines GmbH Alliage tial thermostable et procédé de production associé et composant constitué d'un alliage tial correspondant
CN110512116A (zh) * 2019-09-09 2019-11-29 中国航发北京航空材料研究院 一种多组元高合金化高Nb-TiAl金属间化合物

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3012410B1 (fr) * 2014-09-29 2023-05-10 Raytheon Technologies Corporation Composants de tial gamma avancé
CN112620488A (zh) * 2020-12-16 2021-04-09 西部超导材料科技股份有限公司 一种Ti3Al层状复合板及其制备方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110189026A1 (en) 2007-10-27 2011-08-04 Mtu Aero Engines Gmbh Material for a gas turbine component, method for producing a gas turbine component and gas turbine component
US20110219912A1 (en) * 2009-10-24 2011-09-15 Dipl-Ing Matthias Achtermann METHOD FOR THE PRODUCTION OF A Ãβ-y-TiAL BASE ALLOY
US20110277891A1 (en) 2010-05-12 2011-11-17 Boehler Schmiedetechnik Gmbh & Co Kg Method for producing a component and components of a titanium-aluminum base alloy
EP2423340A1 (fr) * 2010-08-30 2012-02-29 United Technologies Corporation Procédé et système pour fabriquer des composants de moteur à turbine en TiAl gamma
WO2012041276A2 (fr) * 2010-09-22 2012-04-05 Mtu Aero Engines Gmbh Alliage tial résistant à la chaleur
WO2013020548A1 (fr) * 2011-08-11 2013-02-14 Mtu Aereo Engines Gmbh Composants en tial forgés et procédé de fabrication de ceux-ci
EP2620517A1 (fr) * 2012-01-25 2013-07-31 MTU Aero Engines GmbH Alliage TiAl thermostable
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

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5350466A (en) * 1993-07-19 1994-09-27 Howmet Corporation Creep resistant titanium aluminide alloy

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110189026A1 (en) 2007-10-27 2011-08-04 Mtu Aero Engines Gmbh Material for a gas turbine component, method for producing a gas turbine component and gas turbine component
US20110219912A1 (en) * 2009-10-24 2011-09-15 Dipl-Ing Matthias Achtermann METHOD FOR THE PRODUCTION OF A Ãβ-y-TiAL BASE ALLOY
US20110277891A1 (en) 2010-05-12 2011-11-17 Boehler Schmiedetechnik Gmbh & Co Kg Method for producing a component and components of a titanium-aluminum base alloy
EP2423340A1 (fr) * 2010-08-30 2012-02-29 United Technologies Corporation Procédé et système pour fabriquer des composants de moteur à turbine en TiAl gamma
WO2012041276A2 (fr) * 2010-09-22 2012-04-05 Mtu Aero Engines Gmbh Alliage tial résistant à la chaleur
WO2013020548A1 (fr) * 2011-08-11 2013-02-14 Mtu Aereo Engines Gmbh Composants en tial forgés et procédé de fabrication de ceux-ci
EP2620517A1 (fr) * 2012-01-25 2013-07-31 MTU Aero Engines GmbH Alliage TiAl thermostable
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

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
CLEMENS H ET AL: "In and ex situ investigations of the beta-phase in a Nb and Mo containing gamma-TiAl based alloy", INTERMETALLICS, ELSEVIER SCIENCE PUBLISHERS B.V, GB, vol. 16, no. 6, June 2008 (2008-06-01), pages 827 - 833, XP022691290, ISSN: 0966-9795, [retrieved on 20080513], DOI: 10.1016/J.INTERMET.2008.03.008 *
GUETHER VOLKER ET AL: "Microstructure and corresponding tensile properties of as-cast, . beta .-solidifying, . gamma .-TiAl based TNM alloys", GAMMA, TITANIUM, ALUMINIDES, PROCEEDINGS OF A SYMPOSIUM, XX, XX, 9 March 2008 (2008-03-09), pages 249 - 256, XP009110850 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104878452A (zh) * 2015-05-13 2015-09-02 南京理工大学 一种高温高强TiAl-Nb单晶及其制备方法
EP3266889A1 (fr) * 2016-07-07 2018-01-10 United Technologies Corporation Amélioration de la ductilité d'alliages de titane aluminium gamma par réduction de teneurs interstitielles
EP3266888A1 (fr) * 2016-07-07 2018-01-10 United Technologies Corporation Capacité de température améliorée d'alliages d'aluminium de titane gamma
EP3269838A1 (fr) * 2016-07-12 2018-01-17 MTU Aero Engines GmbH Alliage tial thermostable et procédé de production associé et composant constitué d'un alliage tial correspondant
US10590520B2 (en) 2016-07-12 2020-03-17 MTU Aero Engines AG High temperature resistant TiAl alloy, production method therefor and component made therefrom
CN110512116A (zh) * 2019-09-09 2019-11-29 中国航发北京航空材料研究院 一种多组元高合金化高Nb-TiAl金属间化合物
CN110512116B (zh) * 2019-09-09 2021-03-26 中国航发北京航空材料研究院 一种多组元高合金化高Nb-TiAl金属间化合物

Also Published As

Publication number Publication date
US20150086414A1 (en) 2015-03-26
US9994934B2 (en) 2018-06-12
EP2851445B1 (fr) 2019-09-04
ES2747155T3 (es) 2020-03-10

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