EP3067435B2 - 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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EP3067435B2
EP3067435B2 EP16153407.8A EP16153407A EP3067435B2 EP 3067435 B2 EP3067435 B2 EP 3067435B2 EP 16153407 A EP16153407 A EP 16153407A EP 3067435 B2 EP3067435 B2 EP 3067435B2
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process according
forming
component
temperature
heat treatment
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German (de)
French (fr)
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EP3067435A1 (en
EP3067435B1 (en
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Marianne Baumgärtner
Peter Janschek
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Leistritz Turbinentechnik GmbH
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Leistritz Turbinentechnik GmbH
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    • 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 highly resilient component from an ⁇ + ⁇ -titanium aluminide alloy for piston engines and gas turbines, in particular aircraft engines.
  • TiAl-based alloys belong to the group of intermetallic materials that have been developed for applications in the area of the operating temperatures of superalloys. Due to its low density of around 4 g / cm 3 , this material offers considerable potential for weight savings and for reducing the loads on moving components, e.g. blades and disks of gas turbines or components of piston engines, at temperatures of 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 loads such as B. in high-speed turbines for novel geared turbofan aircraft engines, the properties of the cast structure are no longer sufficient.
  • TiAl alloys can be increased to the required values through thermomechanical treatment by means of plastic deformation with a defined degree of deformation and subsequent heat treatment.
  • thermomechanical treatment due to their high deformation resistance, TiAl alloys cannot be forged conventionally.
  • the forming processes must therefore be carried out at high temperatures in the area of the ⁇ + ⁇ or ⁇ -phase area in a protective atmosphere at low forming speeds. In order to achieve the desired final geometry of the forged part, several successive forging steps are usually necessary.
  • FIG DE 101 50 674 B4 An example of such a method for producing heavy-duty components from ⁇ + ⁇ -TiAl alloys is shown in FIG DE 101 50 674 B4 known.
  • the components are manufactured by encapsulating TiAI blanks with a globular structure through isothermal primary deformation in the ⁇ + ⁇ phase range in the temperature range of 1000 - 1340 ° C or in the ⁇ phase range in the temperature range of 1340 - 1360 ° C are deformed by forging or extrusion, after which the preforms are formed by forging into a component of a given contour by at least one isothermal secondary forming process with simultaneous dynamic recrystallization in the ⁇ + ⁇ or ⁇ phase range in the temperature range of 1000 - 1340 ° C, after which the component is solution annealed to adjust the microstructure in the ⁇ -phase area and then rapidly cooled.
  • a two-stage process is used here, including primary forming in the ⁇ + ⁇ or ⁇ phase range, followed by
  • the invention is thus based on the object of specifying a method for producing a highly stressed component from an ⁇ + ⁇ -titanium aluminide alloy, which is easier to implement in comparison to previously known methods.
  • a method according to claim 1 is used to solve this problem.
  • the method according to the invention is characterized by a one-stage, isothermal forming process of the component in the ⁇ -phase range at a slow forming speed, a specific TiAl alloy being used that makes it possible to stabilize the component in the ⁇ -phase range so that the forming takes place there can.
  • the alloy contains a corresponding proportion of the element Mo, which stabilizes the ⁇ -phase.
  • the method according to the invention particularly advantageously permits a single-stage deformation, the component being completely forged after the end of the deformation.
  • the content of the element Mo stabilizing the ⁇ -phase is 0.8-1.2%.
  • Mo has a particularly high stabilizing property, so its content can be kept relatively low.
  • the forming temperature in the ⁇ -phase range is 1070-1250 ° C, with the forming being carried out isothermally as described, i.e. the forming tools are kept at the forming temperature in order not to leave the required narrow temperature window.
  • the logarithmic forming speed is 10 -3 s -1 to 10 -1 s -1 .
  • the preform used has a volume distribution that varies over the longitudinal axis, i.e. a predetermined three-dimensional basic shape is already given, from which the finished component is forged by the one-step 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 options mentioned.
  • tools made of a highly heat-resistant material are preferably used, preferably made of a Mo alloy.
  • the tools are expediently protected against oxidation by an inert atmosphere during the forming process.
  • they are preferably actively heated, for example inductively or by resistance heating.
  • the preform is also heated before the forming process, for example in a furnace, inductively or by resistance heating.
  • the deformation is preferably followed by a heat treatment of the deformed component in order to set the required properties and to convert the ⁇ -phase favorable for the deformation into a fine-lamellar ⁇ + ⁇ structure by means of a suitable heat treatment.
  • the heat treatment can include recrystallization annealing at a temperature of 1230-1270 ° C.
  • the holding time during the recrystallization annealing is preferably 50-100 minutes.
  • the recrystallization annealing takes place in the range of the ⁇ / ⁇ conversion temperature. If, as also 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, then small lamellar spacings of the ⁇ + ⁇ phase are formed.
  • a second heat treatment step in which the component is first cooled to room temperature and then heated to a stabilization or relaxation temperature of 850-950 ° C.
  • the temperature of 900 - 950 ° C which is quickly reached after the recrystallization annealing, can be changed directly to the stabilization and relaxation temperature of 850 - 950 ° C as described above.
  • the preferred holding time at the stabilization and relaxation temperature is preferably 300-360 min.
  • the component temperature is preferably reduced to a temperature below 300 ° C. at a defined cooling rate.
  • the cooling rate is preferably 0.5-2 K / min, that is, the cooling takes place relatively slowly, which serves to stabilize and relax the structure.
  • the cooling rate is preferably 1.5 K / min.
  • the respective cooling can take place in a liquid, e.g. in oil, or in air or an inert gas.

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 highly resilient component from an α + γ-titanium aluminide alloy for piston 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 that have been developed for applications in the area of the operating temperatures of superalloys. Due to its low density of around 4 g / cm 3 , this material offers considerable potential for weight savings and for reducing the loads on moving components, e.g. blades and disks of gas turbines or components of piston engines, at temperatures of 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 loads such as B. in high-speed turbines for novel geared turbofan aircraft engines, the properties of the cast structure are no longer sufficient. The static and dynamic properties of TiAl alloys can be increased to the required values through thermomechanical treatment by means of plastic deformation with a defined degree of deformation and subsequent heat treatment. However, due to their high deformation resistance, TiAl alloys cannot be forged conventionally. The forming processes must therefore be carried out at high temperatures in the area of the α + γ or α-phase area in a protective atmosphere at low forming speeds. In order to achieve the desired final geometry of the forged part, several successive forging steps are usually necessary.

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 heavy-duty components from α + γ-TiAl alloys is shown in FIG DE 101 50 674 B4 known. In this process, the components, especially for aircraft engines or stationary gas turbines, are manufactured by encapsulating TiAI blanks with a globular structure through isothermal primary deformation in the α + γ phase range in the temperature range of 1000 - 1340 ° C or in the α phase range in the temperature range of 1340 - 1360 ° C are deformed by forging or extrusion, after which the preforms are formed by forging into a component of a given contour by at least one isothermal secondary forming process with simultaneous dynamic recrystallization in the α + γ or α phase range in the temperature range of 1000 - 1340 ° C, after which the component is solution annealed to adjust the microstructure in the α-phase area and then rapidly cooled. A two-stage process is used here, including primary forming in the α + γ or α phase range, followed by secondary forming with simultaneous recrystallization. However, such a two-stage process is extremely complex.

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 based on the object of specifying a method for producing a highly stressed component from an α + γ-titanium aluminide alloy, which is easier to implement in comparison to previously known methods.

Zur Lösung dieses Problems dient erfindungsgemäss ein Verfahren gemäss Patentanspruch 1.According to the invention, a method according to claim 1 is used to solve this problem.

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 des die β-Phase stabilisierenden Elements Mo. 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 method according to the invention is characterized by a one-stage, isothermal forming process of the component in the β-phase range at a slow forming speed, a specific TiAl alloy being used that makes it possible to stabilize the component in the β-phase range so that the forming takes place there can. For this purpose, the alloy contains a corresponding proportion of the element Mo, which stabilizes the β-phase. During the slow deformation with a logarithmic deformation rate of 0.01-0.5 1 / s at high temperature, the body-centered cubic β-phase 12 existing slip planes activated and dynamic recrystallization initiated. This is maintained over the entire forming path by continuously supplied further forming energy. This creates a fine-grain microstructure at a lower flow stress. On the other hand, in the case of a deformation in the α + γ or α phase region, as in DE 101 50 674 A1 described, due to the hexagonal phase structure, there is only one slip plane, which requires the two-stage forming process. In contrast, the method according to the invention particularly advantageously permits a single-stage deformation, the component being completely forged after the end of the deformation.

Erfindungsgemäss beträgt der Gehalt des die β-Phase stabilisierenden Elements Mo 0,8 - 1,2 %. Mobesitzt eine besonders hohe stabilisierende Eigenschaft, daher kann dessen Gehalt relativ niedrig gehalten werden.According to the invention, the content of the element Mo stabilizing the β-phase is 0.8-1.2%. Mo has a particularly high stabilizing property, so its content can be kept relatively low.

Die Umformtemperatur im β-Phasenbereich beträgt 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 1070-1250 ° C, with the forming being carried out isothermally as described, i.e. the forming tools are kept at the forming temperature in order not to leave the required narrow temperature window. The logarithmic forming speed 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 that varies over the longitudinal axis, i.e. a predetermined three-dimensional basic shape is already given, from which the finished component is forged by the one-step 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 options mentioned.

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 made of a highly heat-resistant material are preferably used, preferably made of a Mo alloy. The tools are expediently protected against oxidation by an inert atmosphere during the forming process. 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 also heated before the forming process, for example in a furnace, 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.The deformation is preferably followed by a heat treatment of the deformed component in order to set the required properties and to convert the β-phase favorable for the deformation into a fine-lamellar α + γ structure by means of a suitable heat treatment. For this purpose, the heat treatment can include recrystallization annealing at a temperature of 1230-1270 ° C. The holding time during the recrystallization annealing is preferably 50-100 minutes. The recrystallization annealing takes place in the range of the γ / α conversion temperature. If, as also 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, then small lamellar spacings of the α + γ phase are formed.

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.This is preferably followed by a second heat treatment step in which the component is first cooled to room temperature and then heated to a stabilization or relaxation temperature of 850-950 ° C. Alternatively, the temperature of 900 - 950 ° C, which is quickly reached after the recrystallization annealing, can be changed directly to the stabilization and relaxation temperature of 850 - 950 ° C as described above. The preferred holding time at the stabilization and relaxation temperature, regardless of how this 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 elapsed, the component temperature is preferably reduced to a temperature below 300 ° C. at a defined cooling rate. The cooling rate is preferably 0.5-2 K / min, that is, the cooling takes place relatively slowly, 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 can take place in a liquid, e.g. in oil, or in air or an inert gas.

Claims (13)

  1. Process for producing a highly stressable component composed of a α+γ-titanium aluminide alloy for piston engines and gas turbines, in particular aircraft engines, characterized in that a TiAl alloy having the following composition (in atom%) :
    42.8-44.2% of Al,
    3.7-4.3% of Nb,
    0.8-1.2% of Mo
    0.07-1.3% of B,
    and a balance of Ti and melting-related impurities is used as alloy, where forming is carried out in a single stage proceeding from a preform having a volume distribution which varies over the longitudinal axis, wherein the component is formed isothermally in the β phase region with a logarithmic strain rate of 0.01-0.5 1/s and the forming temperature is 1070-1250°C.
  2. Process according to Claim 1, characterized in that the preform is produced by casting, metal injection moulding (MIM), additive processes, in particular 3D printing, laser build-up welding or a combination thereof.
  3. Process according to either of the preceding claims, characterized in that tools made of an Mo alloy are used for forming.
  4. Process according to Claim 3, characterized in that the tools are protected by an inert atmosphere during the forming operation.
  5. Process according to any of the preceding claims, characterized in that the tools used for forming are actively, in particular inductively, heated.
  6. Process according to any of the preceding claims, characterized in that the preform is heated in a furnace, inductively or by resistance heating, before forming.
  7. Process according to any of the preceding claims, characterized in that forming is followed by a heat treatment of the formed component.
  8. Process according to Claim 7, characterized in that the heat treatment comprises a recrystallization heat treatment at a temperature of 1230-1270°C.
  9. Process according to Claim 8, characterized in that the hold time during the recrystallization heat treatment is 50-100 minutes.
  10. Process according to Claim 9, characterized in that the component is cooled to a temperature of 900-950°C in 120 s or less after the recrystallization heat treatment.
  11. Process according to Claim 10, characterized in that the component is subsequently cooled to room temperature and is subsequently heated to a stabilization and relaxation temperature of 850-950°C or in that the component is, without prior cooling, maintained at a stabilization and relaxation temperature of 850-950°C.
  12. Process according to Claim 11, characterized in that the hold time at the stabilization and relaxation temperature is 300-360 minutes.
  13. Process according to Claim 11 or 12, characterized in that the component is subsequently cooled to a temperature below 300°C at a cooling rate of 0.5-2 K/min, in particular 1.5 K/min.
EP16153407.8A 2015-03-09 2016-01-29 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 Active EP3067435B2 (en)

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US10196725B2 (en) 2019-02-05
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JP2016166418A (en) 2016-09-15
US20160265096A1 (en) 2016-09-15
PL3067435T3 (en) 2018-01-31
EP3067435A1 (en) 2016-09-14
DE102015103422B3 (en) 2016-07-14
EP3067435B1 (en) 2017-07-26

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