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EP3067435A1 - Method for producing a heavy-duty component made of an alpha+gamma titanium aluminide alloy for piston engines and gas turbines, in particular jet engines - Google Patents

Method for producing a heavy-duty component made of an alpha+gamma titanium aluminide alloy for piston engines and gas turbines, in particular jet engines Download PDF

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Publication number
EP3067435A1
EP3067435A1 EP16153407.8A EP16153407A EP3067435A1 EP 3067435 A1 EP3067435 A1 EP 3067435A1 EP 16153407 A EP16153407 A EP 16153407A EP 3067435 A1 EP3067435 A1 EP 3067435A1
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Prior art keywords
alloy
component
temperature
phase
forming
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EP16153407.8A
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German (de)
French (fr)
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EP3067435B1 (en
EP3067435B2 (en
Inventor
Marianne Baumgärtner
Peter Janschek
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Leistritz Turbinentechnik GmbH
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Leistritz Turbinentechnik 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
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/26—Methods of annealing
    • C21D1/30—Stress-relieving
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
    • 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
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • 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
    • C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
    • 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

Definitions

  • the invention relates to a method for producing a heavy-duty component of an ⁇ + ⁇ -titanium aluminide alloy for reciprocating engines and gas turbines, in particular aircraft engines.
  • TiAl-based alloys belong to the group of intermetallic materials which have been developed for applications in the field of application temperatures of superalloys. Due to its low density of about 4 g / cm 3 , this material offers considerable potential for saving weight and reducing the loads on moving components, eg blades and disks of gas turbines or components of piston engines, at temperatures up to approx. 700 ° C. State of the art is the investment casting of z. B. turbine blades for aircraft engines. For applications with higher load such. As in high-speed turbines for novel geared turbofan aircraft engines, the properties of the cast structure are no longer sufficient.
  • thermomechanical treatment by means of plastic forming with a defined degree of deformation and subsequent heat treatment, the static and dynamic properties of TiAl alloys can be increased to the required values.
  • TiAl alloys are not conventionally forgeable because of their high resistance to deformation. Therefore, the forming processes at high temperatures in the region of the ⁇ + ⁇ or ⁇ -phase region must be carried out in a protective atmosphere at low forming speeds. In order to achieve the desired final geometry of the forging part id usually several consecutive forging steps are required.
  • the invention is thus the task of specifying a method for producing a highly loaded component of an ⁇ + ⁇ -Titanaluminid-alloy, which is easier to implement compared to previously known methods.
  • the inventive method is characterized by a single-stage, isothermal forming process of the component in the ⁇ -phase region at slow forming speed, wherein a specific TiAl alloy is used, which makes it possible to stabilize the component in the ⁇ -phase region, so that there is the forming can.
  • the alloy contains a corresponding proportion of at least one ⁇ -phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe or Si, although mixtures thereof can also be used.
  • ⁇ -phase stabilizing elements Mo, V or Ta are used, which can be used individually or as a mixture.
  • the content of the ⁇ -phase stabilizing element is preferably 0.1-2%, in particular 0.8-1.2%. This in particular when Mo, V and / or Ta are used, since they have a particularly high stabilizing property and therefore their content can be kept relatively low.
  • the forming temperature in the ⁇ -phase range is preferably 1070-1250 ° C., wherein as described, the deformation takes place isothermally, that is, that the forming tools are kept at the forming temperature so as not to leave the required narrow temperature window.
  • the logarithmic deformation rate is 10 -3 s -1 to 10 -1 s -1 .
  • the preform used has a volume distribution which varies over the longitudinal axis, ie that a given three-dimensional basic shape is already given, from which the finished component is forged by the single-stage forming according to the invention.
  • This preform is preferably produced by casting, metal injection molding (MIM) or additive processes (3D printing, laser deposition welding, etc.) or a combination of the abovementioned possibilities.
  • forming tools are preferably used from a highly heat-resistant material, preferably from a Mo alloy.
  • the tools are protected during the forming process by an inert atmosphere against oxidation.
  • they are preferably actively heated, for example inductively or by resistance heating.
  • the preform is heated before the forming process, for example in an oven, inductively or by resistance heating.
  • the deformation is followed by a heat treatment of the formed component in order to set the required performance properties and to convert the ⁇ -phase, which is favorable for the transformation, into a fine-lamellar ⁇ + ⁇ -structure by means of a suitable heat treatment.
  • the heat treatment may comprise a recrystallization annealing at a temperature of 1230-1270 ° C.
  • the holding time during the recrystallization annealing is preferably 50-100 min.
  • the recrystallization annealing takes place in the region of the ⁇ / ⁇ transformation temperature. If, as is further provided according to the invention, after the recrystallization annealing, the component is cooled to a temperature of 900-950 ° C. in 120 s or faster, small ⁇ finite pitches of the ⁇ + ⁇ phase occur.
  • a second heat treatment step follows, in which the component is first cooled to room temperature and then heated to a stabilizing or relaxation temperature of 850-950 ° C.
  • the stabilization and relaxation temperature of 850 ° -950 ° C. can also be gone directly from the temperature of 900-950 ° C. which has been reached rapidly after the recrystallization annealing as described above.
  • the preferred holding time at the stabilizing and relaxing temperature, regardless of how it is achieved, is preferably 300-360 min.
  • the component temperature is preferably reduced to a temperature below 300 ° C. with a defined cooling rate.
  • the cooling rate is preferably 0.5-2 K / min, that is, the cooling is relatively slow, which serves to stabilize and relax the structure.
  • the cooling rate is preferably 1.5 K / min.
  • the respective cooling may take place in a liquid, e.g. in oil, or in air or in an inert gas.
  • the invention further relates to a component of an ⁇ + ⁇ -titanium aluminide alloy, in particular for a piston engine, an aircraft engine or a gas turbine, which is produced in a method of the type described.
  • a component may for example be a blade or a disk of a gas turbine or the like.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Child & Adolescent Psychology (AREA)
  • Health & Medical Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
  • Forging (AREA)

Abstract

Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer ±+³-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke, dadurch gekennzeichnet, dass als Legierung eine TiAl-Legierung folgender Zusammensetzung verwendet wird (in Atom%): 40-48% Al, 2-8% Nb, 0,1-9% wenigstens eines die ²-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0-0,5% B, sowie einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen, wobei die Umformung einstufig ausgehend von einer Vorform mit über die Längsachse variierender Volumenverteilung erfolgt, wobei das Bauteil im ²-Phasenbereich isotherm mit einer logarithmischen Umformgeschwindigkeit von 0,01 - 0,5 1/s umgeformt wird.Method for producing a high-strength component from a ± + 3 titanium aluminide alloy for reciprocating engines and gas turbines, in particular aircraft engines, characterized in that the alloy used is a TiAl alloy of the following composition (in atom%): 40-48% Al, 2-8% Nb, 0.1-9% of at least one ²-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0-0.5% B, and a remainder of Ti and impurities caused by melting, wherein the transformation takes place in one stage starting from a preform having a volume distribution varying over the longitudinal axis, the component being isothermally transformed in the ²-phase region with a logarithmic deformation rate of 0.01-0.5 1 / s ,

Description

Die Erfindung betrifft ein Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer α+γ-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke.The invention relates to a method for producing a heavy-duty component of an α + γ-titanium aluminide alloy for reciprocating engines and gas turbines, in particular aircraft engines.

Legierungen auf TiAl-Basis gehören zur Gruppe der intermetallischen Werkstoffe, die für Anwendungen im Bereich der Einsatztemperaturen der Superlegierungen entwickelt wurden. Aufgrund ihrer geringen Dichte von etwa 4 g/cm3 bietet dieser Werkstoff ein erhebliches Potenzial zur Gewichtseinsparung sowie zur Reduzierung der Belastungen bewegter Bauteile, z.B. Schaufeln und Scheiben von Gasturbinen oder Bauteile von Kolbenmotoren, bei Temperaturen bis ca. 700 °C. Stand der Technik ist das Feingießen von z. B. Turbinenschaufeln für Flugtriebwerke. Für Anwendungen mit größerer Belastung wie z. B. in schnell laufenden Turbinen für neuartige Getriebefan-Flugtriebwerke sind die Eigenschaften des Gussgefüges nicht mehr ausreichend. Durch thermomechanische Behandlung mittels plastischer Umformung mit definiertem Umformgrad und nachfolgender Wärmebehandlung lassen sich die statischen und dynamischen Eigenschaften von TiAI-Legierungen auf die geforderten Werte steigern. Allerdings sind TiAI-Legierungen wegen ihres hohen Umformwiderstands nicht konventionell schmiedbar. Daher müssen die Umformprozesse bei hohen Temperaturen im Bereich des α+γ- oder α-Phasengebiets in schützender Atmosphäre bei niedrigen Umformgeschwindigkeiten durchgeführt werden. Zum Erreichen der gewünschten Endgeometrie des Schmiedeteils sind dabei i. d. Regel mehrere aufeinander folgende Schmiedeschritte erforderlich.TiAl-based alloys belong to the group of intermetallic materials which have been developed for applications in the field of application temperatures of superalloys. Due to its low density of about 4 g / cm 3 , this material offers considerable potential for saving weight and reducing the loads on moving components, eg blades and disks of gas turbines or components of piston engines, at temperatures up to approx. 700 ° C. State of the art is the investment casting of z. B. turbine blades for aircraft engines. For applications with higher load such. As in high-speed turbines for novel geared turbofan aircraft engines, the properties of the cast structure are no longer sufficient. By thermomechanical treatment by means of plastic forming with a defined degree of deformation and subsequent heat treatment, the static and dynamic properties of TiAl alloys can be increased to the required values. However, TiAl alloys are not conventionally forgeable because of their high resistance to deformation. Therefore, the forming processes at high temperatures in the region of the α + γ or α-phase region must be carried out in a protective atmosphere at low forming speeds. In order to achieve the desired final geometry of the forging part id usually several consecutive forging steps are required.

Ein Beispiel eines solchen Verfahrens zur Herstellung hochbelastbarer Bauteile aus α+γ-TiAl-Legierungen ist aus DE 101 50 674 B4 bekannt. Bei diesem Verfahren werden die Bauteile, insbesondere für Flugtriebwerke oder stationäre Gasturbinen, dadurch hergestellt, dass gekapselte TiAI-Rohlinge globularen Gefüges durch isotherme Primärumformung im α+γ-Phasengebiet im Temperaturbereich von 1000 - 1340 °C oder im α-Phasengebiet im Temperaturbereich von 1340 - 1360 °C durch Schmieden oder Strangpressen verformt werden, wonach die Vorformlinge durch mindestens einen isothermen Sekundärumformprozess unter gleichzeitiger dynamischer Rekristallisation im α+γ- oder α-Phasengebiet im Temperaturbereich von 1000 - 1340 °C durch Schmieden zum Bauteil vorgegebener Kontur ausgeformt werden, wonach das Bauteil zur Einstellung des Mikrogefüges im α-Phasengebiet lösungsgelüht und anschließend schnell abgekühlt wird. Hier kommt also ein zweistufiger Prozess zum Einsatz, umfassend die Primärumformung im α+γ- oder α-Phasengebiet, gefolgt von der Sekundärumformung unter gleichzeitiger Rekristallisation. Ein solcher zweistufiger Prozess ist jedoch äußerst aufwendig.An example of such a method for producing high-strength components made of α + γ-TiAl alloys is out DE 101 50 674 B4 known. In this method, the components, in particular for aircraft engines or stationary gas turbines, prepared by encapsulated TiAI blanks of globular microstructure by isothermal primary deformation in the α + γ phase region in Temperature range of 1000 - 1340 ° C or in the α-phase region in the temperature range of 1340 - 1360 ° C deformed by forging or extrusion, after which the preforms by at least one isothermal secondary forming process with simultaneous dynamic recrystallization in the α + γ or α-phase region in the temperature range 1000-1340 ° C are formed by forging to the component predetermined contour, after which the component for setting the microstructure in the α-phase region solution-annealed and then cooled rapidly. Here, therefore, a two-step process is used, comprising the primary transformation in the α + γ or α-phase region, followed by the secondary transformation with simultaneous recrystallization. However, such a two-step process is extremely expensive.

Der Erfindung liegt damit die Aufgabenstellung zugrunde, ein Verfahren zur Herstellung eines hochbelasteten Bauteils aus einer α+γ-Titanaluminid-Legierung anzugeben, das im Vergleich zu bisher bekannten Verfahren einfacher zu realisieren ist.The invention is thus the task of specifying a method for producing a highly loaded component of an α + γ-Titanaluminid-alloy, which is easier to implement compared to previously known methods.

Zur Lösung dieses Problems dient erfindungsgemäß ein Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer α+γ-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke, das sich dadurch auszeichnet, dass als Legierung eine TiAI-Legierung folgender Zusammensetzung verwendet wird (in Atom%):

  • 40 - 48 % Al,
  • 2-8%Nb,
  • 0,1 - 9 % wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0,5 % B,
sowie einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen, wobei die Umformung einstufig ausgehend von einer Vorform mit über die Längsachse variierender Volumenverteilung erfolgt, wobei das Bauteil im β-Phasenbereich isotherm mit einer logarithmischen Umformgeschwindigkeit von 0,01 - 0,5 1/s umgeformt wird.To solve this problem, the invention provides a method for producing a high-strength component of an α + γ-Titanaluminid-alloy for reciprocating engines and gas turbines, in particular aircraft engines, which is characterized in that as alloy a TiAl alloy of the following composition is used (in atomic% ):
  • 40 - 48% Al,
  • 2-8% Nb,
  • 0.1-9% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0.5% B,
and a remainder of Ti and impurities caused by melting, wherein the transformation takes place in one stage starting from a preform with a volume distribution varying over the longitudinal axis, the component being isothermally transformed in the β-phase range with a logarithmic deformation rate of 0.01-0.5 1 / s ,

Das erfindungsgemäße Verfahren zeichnet sich durch einen einstufigen, isothermen Umformvorgang des Bauteils im β-Phasenbereich bei langsamer Umformgeschwindigkeit aus, wobei eine spezifische TiAI-Legierung verwendet wird, die es ermöglicht, das Bauteil im β-Phasenbereich zu stabilisieren, so dass dort die Umformung erfolgen kann. Zu diesem Zweck enthält die Legierung einen entsprechenden Anteil wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe oder Si, wobei auch Mischungen davon verwendet werden können. Während der langsamen Umformung mit einer logarithmischen Umformgeschwindigkeit von 0,01 - 0,5 1/s bei hoher Temperatur werden die in der kubisch-raumzentrierten β-Phase existenten 12 Gleitebenen aktiviert und eine dynamische Rekristallisation angestoßen. Durch stetig weiter zugeführte Umformenergie wird diese über den gesamten Umformweg aufrechterhalten. Hierbei entsteht bei niedrigerer Fließspannung ein feinkörniges Mikrogefüge. Dagegen ist bei einer Umformung im α+γ- oder α-Phasengebiet, wie in DE 101 50 674 A1 beschrieben, aufgrund der hexagonalen Phasenstruktur nur eine Gleitebene existent, was die Zweistufigkeit des Umformvorgangs erfordert. Demgegenüber lässt das erfindungsgemäße Verfahren mit besonderem Vorteil eine einstufige Umformung zu, wobei das Bauteil nach Beendigung der Umformung fertig geschmiedet ist.The inventive method is characterized by a single-stage, isothermal forming process of the component in the β-phase region at slow forming speed, wherein a specific TiAl alloy is used, which makes it possible to stabilize the component in the β-phase region, so that there is the forming can. For this purpose, the alloy contains a corresponding proportion of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe or Si, although mixtures thereof can also be used. During the slow forming process with a logarithmic deformation rate of 0.01 - 0.5 1 / s at high temperature, the 12 slip planes existing in the cubic body-centered β-phase are activated and dynamic recrystallization initiated. By constantly further supplied forming energy, this is maintained over the entire Umformweg. This results in a fine-grained microstructure at lower yield stress. In contrast, in a transformation in the α + γ or α-phase region, as in DE 101 50 674 A1 described, due to the hexagonal phase structure only one slip plane exist, which requires the two-stage of the forming process. In contrast, the method according to the invention is particularly advantageous for single-stage forming, the component being finished forged after completion of the forming.

Besonders bevorzugt werden als die β-Phase stabilisierende Elemente Mo, V oder Ta verwendet, die einzeln oder als Mischung eingesetzt werden können.Particularly preferred as the β-phase stabilizing elements Mo, V or Ta are used, which can be used individually or as a mixture.

Bevorzugt beträgt der Gehalt des die β-Phase stabilisierenden Elements 0,1 - 2 %, insbesondere 0,8 - 1,2 %. Dies insbesondere, wenn Mo, V und/oder Ta verwendet werden, da diese eine besonders hohe stabilisierende Eigenschaft besitzen und daher deren Gehalt relativ niedrig gehalten werden kann.The content of the β-phase stabilizing element is preferably 0.1-2%, in particular 0.8-1.2%. This in particular when Mo, V and / or Ta are used, since they have a particularly high stabilizing property and therefore their content can be kept relatively low.

Bevorzugt wird eine Legierung folgender Zusammensetzung verwendet:

  • 41 - 47 % Al,
  • 1,5-7 % Nb,
  • 0,2 - 8 % wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0,3 % B,
und einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen.Preferably, an alloy of the following composition is used:
  • 41 - 47% Al,
  • 1.5-7% Nb,
  • 0.2-8% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0.3% B,
and a balance of Ti and impurities caused by melting.

In weiterer Konkretisierung wird bevorzugt eine Legierung folgender Zusammensetzung verwendet:

  • 42 - 46 % Al,
  • 2 - 6,5 % Nb,
  • 0,4 - 5 % wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0,2 % B,
und einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen.In further concretization, an alloy of the following composition is preferably used:
  • 42 - 46% Al,
  • 2 - 6.5% Nb,
  • 0.4-5% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si,
  • 0 - 0.2% B,
and a balance of Ti and impurities caused by melting.

Besonders bevorzugt wird eine Legierung folgender Zusammensetzung verwendet:

  • 42,8 - 44,2 % Al,
  • 3,7 - 4,3 % Nb,
  • 0,8 - 1,2 % Mo,
  • 0,07 - 0,13 % B,
sowie einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen.An alloy of the following composition is particularly preferably used:
  • 42.8 - 44.2% Al,
  • 3.7 - 4.3% Nb,
  • 0.8-1.2% Mo,
  • 0.07 - 0.13% B,
and a balance of Ti and impurities caused by melting.

Die Umformtemperatur im β-Phasenbereich beträgt bevorzugt 1070 - 1250°C, wobei wie beschrieben die Umformung isotherm erfolgt, das heißt, dass die Umformwerkzeuge auf der Umformtemperatur gehalten sind, um das geforderte enge Temperaturfenster nicht zu verlassen. Die logarithmische Umformgeschwindigkeit beträgt 10-3 s-1 bis 10-1 s-1.The forming temperature in the β-phase range is preferably 1070-1250 ° C., wherein as described, the deformation takes place isothermally, that is, that the forming tools are kept at the forming temperature so as not to leave the required narrow temperature window. The logarithmic deformation rate is 10 -3 s -1 to 10 -1 s -1 .

Die verwendete Vorform weist eine über die Längsachse variierende Volumenverteilung auf, d.h. dass bereits eine vorgegebene dreidimensionale Grundform gegeben ist, aus der durch die erfindungsgemäße einstufige Umformung das fertige Bauteil geschmiedet wird. Diese Vorform wird bevorzugt durch Gießen, Metallformspritzen (MIM) oder additive Verfahren (3D-Druck, Laserauftragsschweißen, etc.) oder eine Kombination der genannten Möglichkeiten hergestellt.The preform used has a volume distribution which varies over the longitudinal axis, ie that a given three-dimensional basic shape is already given, from which the finished component is forged by the single-stage forming according to the invention. This preform is preferably produced by casting, metal injection molding (MIM) or additive processes (3D printing, laser deposition welding, etc.) or a combination of the abovementioned possibilities.

Zur Umformung werden bevorzugt Werkzeuge aus einem höchst-warmfesten Werkstoff verwendet, bevorzugt aus einer Mo-Legierung. Zweckmäßigerweise werden die Werkzeuge während des Umformvorgangs durch eine inerte Atmosphäre gegen Oxidation geschützt. Um die Werkzeuge auf der Umformtemperatur zu halten werden sie bevorzugt aktiv beheizt, beispielsweise induktiv oder durch Widerstandsheizung.For forming tools are preferably used from a highly heat-resistant material, preferably from a Mo alloy. Advantageously, the tools are protected during the forming process by an inert atmosphere against oxidation. In order to keep the tools at the forming temperature, they are preferably actively heated, for example inductively or by resistance heating.

Auch die Vorform wird vor dem Umformvorgang erwärmt, beispielsweise in einem Ofen, induktiv oder durch Widerstandsbeheizung.The preform is heated before the forming process, for example in an oven, inductively or by resistance heating.

Bevorzugt folgt der Umformung eine Wärmebehandlung des umgeformten Bauteils, um die geforderten Gebrauchseigenschaften einzustellen und hierfür die für die Umformung günstige β-Phase durch eine geeignete Wärmebehandlung in ein feinlamellares α+γ-Gefüge umzuwandeln. Hierzu kann die Wärmebehandlung eine Rekristallisationsglühung bei einer Temperatur von 1230 - 1270°C umfassen. Die Haltezeit während der Rekristallisationsglühung beträgt bevorzugt 50 - 100 min. Die Rekristallisationsglühung erfolgt im Bereich der γ/α-Umwandlungstemperatur. Wird, wie erfindungsgemäß ferner vorgesehen, nach der Rekristallisationsglühung das Bauteil auf eine Temperatur von 900 - 950°C in 120 s oder schneller abgekühlt, so kommt es zur Bildung kleiner Lamellenabstände der α+γ-Phase.Preferably, the deformation is followed by a heat treatment of the formed component in order to set the required performance properties and to convert the β-phase, which is favorable for the transformation, into a fine-lamellar α + γ-structure by means of a suitable heat treatment. For this purpose, the heat treatment may comprise a recrystallization annealing at a temperature of 1230-1270 ° C. The holding time during the recrystallization annealing is preferably 50-100 min. The recrystallization annealing takes place in the region of the γ / α transformation temperature. If, as is further provided according to the invention, after the recrystallization annealing, the component is cooled to a temperature of 900-950 ° C. in 120 s or faster, small α finite pitches of the α + γ phase occur.

Bevorzugt schließt sich ein zweiter Wärmebehandlungsschritt an, in dem das Bauteil zunächst auf Raumtemperatur abgekühlt und anschließend auf eine Stabilisierungs- oder Entspannungstemperatur von 850 - 950°C erwärmt wird. Alternativ kann auch direkt von der nach der Rekristallisationsglühung schnell erreichten Temperatur von 900 - 950 °C wie zuvor beschrieben auf die Stabilisierungs- und Entspannungstemperatur von 850 - 950°C gegangen werden. Die bevorzugte Haltezeit auf der Stabilisierungs- und Entspannungstemperatur, unabhängig davon, wie diese erreicht wird, beträgt bevorzugt 300 - 360 min.Preferably, a second heat treatment step follows, in which the component is first cooled to room temperature and then heated to a stabilizing or relaxation temperature of 850-950 ° C. Alternatively, the stabilization and relaxation temperature of 850 ° -950 ° C. can also be gone directly from the temperature of 900-950 ° C. which has been reached rapidly after the recrystallization annealing as described above. The preferred holding time at the stabilizing and relaxing temperature, regardless of how it is achieved, is preferably 300-360 min.

Nach Ablauf der Haltezeit wird bevorzugt mit einer definierten Abkühlrate die Bauteiltemperatur auf eine Temperatur unterhalb 300°C reduziert. Die Abkühlrate beträgt bevorzugt 0,5 - 2 K/min, das heißt, die Abkühlung erfolgt relativ langsam, was zur Stabilisierung und Entspannung des Gefüges dient. Bevorzugt beträgt die Abkühlrate 1,5 K/min.After the holding time has expired, the component temperature is preferably reduced to a temperature below 300 ° C. with a defined cooling rate. The cooling rate is preferably 0.5-2 K / min, that is, the cooling is relatively slow, which serves to stabilize and relax the structure. The cooling rate is preferably 1.5 K / min.

Die jeweilige Abkühlung kann in einer Flüssigkeit, z.B. in Öl, oder in Luft oder einem Inertgas erfolgen.The respective cooling may take place in a liquid, e.g. in oil, or in air or in an inert gas.

Neben dem erfindungsgemäßen Verfahren betrifft die Erfindung ferner ein Bauteil aus einer α+γ-Titanaluminid-Legierung, insbesondere für eine Kolbenmaschine, ein Flugtriebwerk oder eine Gasturbine, das in einem Verfahren der beschriebenen Art hergestellt ist. Ein solches Bauteil kann beispielsweise eine Schaufel oder eine Scheibe einer Gasturbine oder ähnliches sein.In addition to the method according to the invention, the invention further relates to a component of an α + γ-titanium aluminide alloy, in particular for a piston engine, an aircraft engine or a gas turbine, which is produced in a method of the type described. Such a component may for example be a blade or a disk of a gas turbine or the like.

Claims (20)

Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer α+γ-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke, dadurch gekennzeichnet, dass als Legierung eine TiAI-Legierung folgender Zusammensetzung verwendet wird (in Atom%): 40-48% Al, 2-8% Nb, 0,1-9% wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0-0,5% B, sowie einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen, wobei die Umformung einstufig ausgehend von einer Vorform mit über die Längsachse variierender Volumenverteilung erfolgt, wobei das Bauteil im β-Phasenbereich isotherm mit einer logarithmischen Umformgeschwindigkeit von 0,01 - 0,5 1/s umgeformt wird.Method for producing a high-strength component from an α + γ-titanium aluminide alloy for reciprocating engines and gas turbines, in particular aircraft engines, characterized in that the alloy used is a TiAl alloy of the following composition (in atom%): 40-48% Al, 2-8% Nb, 0.1-9% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0-0.5% B, and a remainder of Ti and impurities caused by melting, wherein the transformation takes place in one stage starting from a preform with a volume distribution varying over the longitudinal axis, the component being isothermally transformed in the β-phase range with a logarithmic deformation rate of 0.01-0.5 1 / s , Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass als die β-Phase stabilisierende Element nur Mo, V, Ta oder eine Mischung davon in der Legierung vorliegt.A method according to claim 1, characterized in that as the β-phase stabilizing element is present only Mo, V, Ta or a mixture thereof in the alloy. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Gehalt des die β-Phase stabilisierenden Elements 0,1 - 2 %, insbesondere 0,8 - 1,2% beträgt.A method according to claim 1 or 2, characterized in that the content of the β-phase stabilizing element is 0.1 - 2%, in particular 0.8 - 1.2%. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass eine TiAI-Legierung folgender Zusammensetzung verwendet wird: 41 - 47 % Al, 1,5-7 % Nb, 0,2 - 8 % wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0 - 0,3 % B, und einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen.Method according to one of the preceding claims, characterized in that a TiAl alloy of the following composition is used: 41 - 47% Al, 1.5-7% Nb, 0.2-8% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0 - 0.3% B, and a balance of Ti and impurities caused by melting. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass eine TiAI-Legierung folgender Zusammensetzung verwendet wird: 42 - 46 % Al, 2 - 6,5 % Nb, 0,4 - 5 % wenigstens eines die β-Phase stabilisierenden Elements, gewählt aus Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0 - 0,2 % B, und einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen. Method according to one of the preceding claims, characterized in that a TiAl alloy of the following composition is used: 42 - 46% Al, 2 - 6.5% Nb, 0.4-5% of at least one β-phase stabilizing element selected from Mo, V, Ta, Cr, Mn, Ni, Cu, Fe, Si, 0 - 0.2% B, and a balance of Ti and impurities caused by melting. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass eine Legierung folgender Zusammensetzung verwendet wird: 42,8-44,2% Al, 3,7-4,3% Nb, 0,8-1,2% Mo, 0,07-0,13% B, sowie einem Rest aus Ti und erschmelzungsbedingten Verunreinigungen.Method according to one of the preceding claims, characterized in that an alloy of the following composition is used: 42.8-44.2% Al, 3.7-4.3% Nb, 0.8-1.2% Mo, 0.07-0.13% B, and a balance of Ti and impurities caused by melting. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Umformtemperatur im β-Phasenbereich 1070-1250°C beträgt.Method according to one of the preceding claims, characterized in that the forming temperature in the β-phase region is 1070-1250 ° C. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Vorform durch Gießen, Metallformspritzen (MIM), additive Verfahren, insbesondere 3D-Druck, Laserauftragsschweißen, oder eine Kombination davon hergestellt wird.Method according to one of the preceding claims, characterized in that the preform is produced by casting, metal injection molding (MIM), additive processes, in particular 3D printing, laser deposition welding, or a combination thereof. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass zur Umformung Werkzeuge aus einem höchst-warmfesten Werkstoff, insbesondere aus einer Mo-Legierung verwendet werden.Method according to one of the preceding claims, characterized in that for forming tools from a highly heat-resistant Material, in particular be used from a Mo alloy. Verfahren nach Anspruch 9, dadurch gekennzeichnet, dass die Werkzeuge während des Umformvorgangs durch eine inerte Atmosphäre geschützt sind.A method according to claim 9, characterized in that the tools are protected during the forming process by an inert atmosphere. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die zur Umformung verwendeten Werkzeuge aktiv, insbesondere induktiv beheizt werden.Method according to one of the preceding claims, characterized in that the tools used for forming are actively, in particular inductively heated. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Vorform in einem Ofen, induktiv oder durch Widerstandsbeheizung vor der Umformung erwärmt wird.Method according to one of the preceding claims, characterized in that the preform is heated in an oven, inductively or by resistance heating before forming. Verfahren nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass der Umformung eine Wärmebehandlung des umgeformten Bauteils folgt.Method according to one of the preceding claims, characterized in that the deformation follows a heat treatment of the formed component. Verfahren nach Anspruch 13, dadurch gekennzeichnet, dass die Wärmebehandlung eine Rekristallisationsglühung bei einer Temperatur von 1230-1270°C umfasst.A method according to claim 13, characterized in that the heat treatment comprises a recrystallization annealing at a temperature of 1230-1270 ° C. Verfahren nach Anspruch 14, dadurch gekennzeichnet, dass die Haltezeit während der Rekristallisationsglühung 50-100 min beträgt.A method according to claim 14, characterized in that the holding time during the recrystallization annealing is 50-100 min. Verfahren nach Anspruch 15, dadurch gekennzeichnet, dass nach der Rekristallisationsglühung das Bauteil auf eine Temperatur von 900-950°C in 120s oder schneller abgekühlt wird.A method according to claim 15, characterized in that after the recrystallization annealing, the component is cooled to a temperature of 900-950 ° C in 120 seconds or faster. Verfahren nach Anspruch 16, dadurch gekennzeichnet, dass das Bauteil anschließend auf Raumtemperatur abgekühlt wird und anschließend auf eine Stabilisierungs- und Entspannungstemperatur von 850-950°C erwärmt wird, oder dass das Bauteil ohne vorherige Abkühlung auf einer Stabilisierungs- und Entspannungstemperatur von 850-950°C gehalten wird.A method according to claim 16, characterized in that the component is then cooled to room temperature and then heated to a stabilizing and relaxation temperature of 850-950 ° C. or that the component is maintained at a stabilizing and relaxation temperature of 850-950 ° C without cooling previously. Verfahren nach Anspruch 17, dadurch gekennzeichnet, dass die Haltezeit auf der Stabilisierungs- und Entspannungstemperatur 300-360min beträgt.A method according to claim 17, characterized in that the holding time at the stabilizing and relaxation temperature is 300-360min. Verfahren nach Anspruch 17 oder 18, dadurch gekennzeichnet, dass anschließend eine Abkühlung des Bauteils auf eine Temperatur unter 300°C mit einer Abkühlrate von 0,5-2 K/min, insbesondere 1,5 K/min erfolgt.A method according to claim 17 or 18, characterized in that then takes place a cooling of the component to a temperature below 300 ° C at a cooling rate of 0.5-2 K / min, in particular 1.5 K / min. Bauteil aus einer α+γ-Titanaluminid-Legierung, insbesondere für eine Kolbenmaschine, ein Flugtriebwerk oder eine Gasturbine, hergestellt nach dem Verfahren nach einem der vorangehenden Ansprüche.Component of an α + γ-titanium aluminide alloy, in particular for a piston engine, an aircraft engine or a gas turbine, produced by the method according to one of the preceding claims.
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