EP2807281A1 - Method for producing forged components from a tial alloy and component produced thereby - Google Patents

Method for producing forged components from a tial alloy and component produced thereby

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Publication number
EP2807281A1
EP2807281A1 EP13705380.7A EP13705380A EP2807281A1 EP 2807281 A1 EP2807281 A1 EP 2807281A1 EP 13705380 A EP13705380 A EP 13705380A EP 2807281 A1 EP2807281 A1 EP 2807281A1
Authority
EP
European Patent Office
Prior art keywords
component
tial
heat treatment
temperature
solvus line
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
EP13705380.7A
Other languages
German (de)
French (fr)
Other versions
EP2807281B1 (en
Inventor
Wilfried Smarsly
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2807281A1 publication Critical patent/EP2807281A1/en
Application granted granted Critical
Publication of EP2807281B1 publication Critical patent/EP2807281B1/en
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/25—Manufacture essentially without removing material by forging
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/40—Heat treatment
    • F05D2230/41—Hardening; Annealing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl

Definitions

  • the present invention relates to a method for producing a component from a TiAl alloy, in which the component is formed by forging, in particular by isothermal forging and subsequently subjected to a heat treatment. Moreover, the present invention relates to a correspondingly manufactured component.
  • TiAl alloys whose main constituents are titanium and aluminum are characterized by the fact that they have a high strength due to the formation of intermetallic phases, such as ⁇ -TiAl, which have a high proportion of covalent bonding forces within the metallic bond, with sufficient ductility. especially high-temperature strength. In addition, they have a low specific weight, so that the use of Titanalumi- nide or TiAl alloys as in high-temperature applications, for example in turbomachines, especially gas turbines or aircraft engines, is suitable.
  • the property profile of the TiAl alloys can be further optimized.
  • Such alloys with niobium and molybdenum content are also referred to as so-called TNM alloys.
  • alloys are used in aircraft engines, for example, as guide or moving blades and are brought by forging in the appropriate component form.
  • isothermal forging can be used with subsequent heat treatment for adjusting the microstructure and the property profile.
  • blisk art word for blade and disk
  • a forged component made of a TiAl alloy ie an alloy in which the alloying constituents with the highest proportion of the alloy composition are titanium and aluminum, at least one first heat treatment after forging, in which at least in one step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and then cooled.
  • the TiAl material undergoes partial segregation.
  • This first heat treatment is referred to as homogenization annealing, as it does the material composition is homogenized over the component and existing concentration point are dissolved.
  • the cooling rate can be between 1 ° C / s and 5 ° C / s.
  • the component is heated in a second heat treatment over the solvus line of ⁇ -TiAl.
  • a second heat treatment in the microstructure, the contained ⁇ -TiAl is at least partially converted to another solid phase, such as e.g. a TiAl converted, so that a desired or adapted phase composition in the TiAl alloy is made possible and in particular depending on the chemical composition of the component by varying the phase composition adjustment of optimum mechanical properties, in particular with respect to the total elongation and creep resistance is possible.
  • the heat treatment can be tailored specifically to the specific chemical composition and its scattering in the component.
  • the component may be rapidly cooled after the second heat treatment above the solvus line of the ⁇ -TiAl to substantially freeze the phase composition set at the heat treatment temperature.
  • Quick cooling can be done, for example, by quenching in water or oil, or by air cooling with a blower.
  • the cooling can take place so quickly that a conversion of ⁇ -TiAl additionally formed in the second heat treatment into a lamellar structure of ⁇ -TiAl and ⁇ -TiAl is avoided.
  • the second heat treatment may be performed at a temperature that avoids entering a single-phase phase field of the TiAl phase diagram, such as the ⁇ -TiAl phase field, by the risk of coarse grain growth associated with heat treatment in a single-phase phase field prevention.
  • the second heat treatment can be carried out for a period of time which ensures sufficient conversion of the ⁇ -TiAl to another phase, in particular a-TiAl, so that the desired phase composition can be achieved.
  • the temperature in the second heat treatment over the ⁇ -TiAl solvus line can at a temperature of 20 ° C to 50 ° C, in particular 25 ° C to 35 ° C, preferably about 30 ° C above the ⁇ -TiAl solvus Line can be selected.
  • the method can be used in particular for components which consist of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 to 54.5 at.% Titanium, 3.5 to 4.5 at.%. Niobium, in particular 4.0 to 4.2 at.% Niobium, 0.75 to 1.5 at.% Molybdenum, in particular 0.9 to 1.2 at.% Molybdenum, and 0.05 to 0, 15 at.% Boron, in particular 0.1 to 0.12 at.% Boron, and the balance aluminum and unavoidable impurities.
  • a phase composition with corresponding proportions of the ⁇ -TiAl is present, which makes the use of the method according to the invention particularly advantageous.
  • the second heat treatment may be carried out at a temperature below the solvus line ⁇ -TiAl, the temperature being in particular between 12 ° C and 18 ° C below the solvus line.
  • a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours may additionally be carried out in order to stabilize the material charge in the component (stabilization annealing).
  • a turbomachine in particular a gas turbine or an aircraft engine, in particular blades, vanes, or turbine blades, which have a variably adjustable property profile due to an adapted phase composition.
  • a material for a component produced according to the invention can be, for example, a composition in the range of 42 to 45 at.% Titanium, 3.5 to 4.5 at.% Niobium, 0.75 to 1.5 at.% Molybdenum, and 0.05 to 0.15 at.% Boron with balance aluminum and unavoidable impurities.
  • a corresponding component can for example be forged isothermally until it has the rough contour of the final component to be produced.
  • the material of the component is homogenized by a first heat treatment at, for example, 1150 ° C for 8 hours.
  • the component may then be annealed in a first first alternative of a second heat treatment then at a temperature of, for example, 1290 ° C (ie, above the solvus line (l)) for a predetermined period of time to permit partial conversion of the ⁇ -TiAl to ⁇ -TiAl cause ⁇ -TiAl and ⁇ -TiAl to coexist in the microstructure.
  • the temperature treatment can be carried out until a sufficient amount of ⁇ -TiAl has been converted to ⁇ -TiAl for the desired phase composition.
  • the component is cooled rapidly, for example by quenching in water (10 min) or in oil or by cooling with a blower. This fan cooling takes place in an oven, the temperature is lowered to 850 ° C and held for 6 hours.
  • the ⁇ and ⁇ -TiAl microstructure set at the temperature of the second heat treatment are largely frozen and a conversion of the ⁇ phase into ⁇ / ⁇ fins is avoided.
  • the choice of the heat treatment temperature of 1290 ° C also avoids that the ⁇ -TiAl is completely converted into ⁇ -TiAl, which would lead to the risk of coarse grain growth with a corresponding temperature treatment.
  • the component is heated below the solvus line (1). For example, the component is heated at 1235 ° C for one hour, then cooled the component (with water, oil or Ofenkkühlung). During the oven cooling, the temperature is lowered to 850 ° C and held for 6 hours.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Forging (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200°C and is maintained for 6 to 10 hours and then the component is cooled.

Description

Verfahren zur Herstellung geschmiedeter Bauteile aus einer TiAl-Legierung und entsprechend hergestelltes Bauteil  Method for producing forged components from a TiAl alloy and correspondingly manufactured component
HINTERGRUND DER ERFINDUNG BACKGROUND OF THE INVENTION
GEBIET DER ERFINDUNG FIELD OF THE INVENTION
Die vorliegende Erfindung betrifft ein Verfahren zur Herstellung eines Bauteils aus einer TiAl- Legierung, bei welchem das Bauteil durch Schmieden, insbesondere durch isothermes Schmieden geformt und nachfolgend einer Wärmebehandlung unterzogen wird. Darüber hinaus betrifft die vorliegende Erfindung ein entsprechend hergestelltes Bauteil. The present invention relates to a method for producing a component from a TiAl alloy, in which the component is formed by forging, in particular by isothermal forging and subsequently subjected to a heat treatment. Moreover, the present invention relates to a correspondingly manufactured component.
STAND DER TECHNIK STATE OF THE ART
TiAl-Legierungen, deren Hauptbestandteile Titan und Aluminium sind, zeichnen sich dadurch aus, dass sie durch Ausbildung von intermetallischen Phasen, wie beispielsweise γ-TiAl, die einen hohen Anteil kovalenter Bindungskräfte innerhalb der metallischen Bindung aufweisen, bei ausreichender Duktilität über eine hohe Festigkeit, insbesondere Hochtemperaturfestigkeit, verfügen. Zudem besitzen sie ein geringes spezifisches Gewicht, sodass der Einsatz der Titanalumi- nide bzw. von TiAl-Legierungenwie bei Hochtemperaturanwendungen, beispielsweise bei Strömungsmaschinen, insbesondere Gasturbinen oder Flugtriebwerken, geeignet ist. TiAl alloys whose main constituents are titanium and aluminum are characterized by the fact that they have a high strength due to the formation of intermetallic phases, such as γ-TiAl, which have a high proportion of covalent bonding forces within the metallic bond, with sufficient ductility. especially high-temperature strength. In addition, they have a low specific weight, so that the use of Titanalumi- nide or TiAl alloys as in high-temperature applications, for example in turbomachines, especially gas turbines or aircraft engines, is suitable.
Durch Zugabe bestimmter Legierungsbestandteile, wie beispielsweise Niob und Molybdän, können das Eigenschaftsprofil der TiAl-Legierungen weiter optimiert werden. Derartige Legierungen mit Niob- und Molybdän-Anteil werden auch als sogenannte TNM-Legierungen bezeichnet. By adding certain alloying constituents, such as niobium and molybdenum, the property profile of the TiAl alloys can be further optimized. Such alloys with niobium and molybdenum content are also referred to as so-called TNM alloys.
Diese Legierungen werden in Flugtriebwerken beispielsweise als Leit- oder Laufschaufeln eingesetzt und werden durch Schmieden in die entsprechende Bauteilform gebracht. Insbesondere kann hier isothermes Schmieden mit nachfolgendender Wärmebehandlung zur Einstellung des Gefüges und des Eigenschaftsprofils eingesetzt werden. Auf diese Weise lassen sich auch einstückige Schaufel-Scheiben-Einheiten, sogenannte blisk (Kunstwort für blade and disk) herstellen. These alloys are used in aircraft engines, for example, as guide or moving blades and are brought by forging in the appropriate component form. In particular, here isothermal forging can be used with subsequent heat treatment for adjusting the microstructure and the property profile. In this way, one-piece blade-disc units, so-called blisk (art word for blade and disk) can be produced.
Allerdings kann es bei der Herstellung auf Grund von Unterschieden in der chemischen Zusammensetzung über das Bauteil hinweg zu einer unterschiedlichen Phasenzusammensetzung inner- halb eines Bauteils aus einem TiAl- Werkstoff kommen, was eine ungleichmäßige Verteilung des Eigenschaftsprofils im Bauteil zur Folge hat, sodass aufgrund entsprechender Schwankungen der Eigenschaften über das Bauteil hinweg derartige Bauteile nicht mehr einsetzbar sind, wenn sie außerhalb der vorgegebenen Spezifikation für das Bauteil liegen. Dadurch kommt es zu hohen Ausschussraten. However, due to differences in the chemical composition across the component, during manufacture it may result in a different phase composition within the component. come half of a component of a TiAl material, which has an uneven distribution of the property profile in the component result, so that due to corresponding variations in the properties of the component such components are no longer applicable, if they are outside the specified specification for the component. This leads to high reject rates.
OFFENBARUNG DER ERFINDUNG DISCLOSURE OF THE INVENTION
AUFGABE DER ERFINDUNG OBJECT OF THE INVENTION
Es ist deshalb Aufgabe der vorliegenden Erfindung, ein Verfahren zur Herstellung von Bauteilen aus einer TiAl-Legierung über eine schmiedetechnische Herstellungsroute anzugeben, bei denen die Probleme des Standes der Technik insbesondere im Hinblick auf inhomogene Eigenschaften des Bauteils behoben werden und insbesondere ein Bauteil aus einer TiAl-Legierung in einfacher Weise mit einem gewünschten Eigenschaftsprofil hergestellt werden kann, wobei vor allem auf die spezifische chemische Zusammensetzung und deren Streuung im Bauteil eingegangen werden kann. It is therefore an object of the present invention to provide a method for producing components made of a TiAl alloy via a forging production route, in which the problems of the prior art, in particular with respect to inhomogeneous properties of the component are resolved and in particular a component of a TiAl Alloy can be prepared in a simple manner with a desired property profile, which can be addressed in particular on the specific chemical composition and their scattering in the component.
TECHNISCHE LÖSUNG TECHNICAL SOLUTION
Diese Aufgabe wird gelöst durch ein Verfahren zur Herstellung eines Bauteils mit den Merkmalen des Anspruchs 1 sowie durch ein Bauteil mit den Merkmalen des Anspruchs 14. Vorteilhafte Ausgestaltungen sind Gegenstand der abhängigen Ansprüche. This object is achieved by a method for producing a component having the features of claim 1 and by a component having the features of claim 14. Advantageous embodiments are the subject of the dependent claims.
Gemäß der vorliegenden Erfindung wird vorgeschlagen, bei einem schmiedetechnisch hergestellten Bauteil aus einer TiAl-Legierung, also einer Legierung, bei der die Legierungsbestandteile mit dem höchsten Anteil an der Legierungszusammensetzung Titan und Aluminium sind, nach dem Schmieden mindestens eine erste Wärmebehandlung vorzunehmen, bei der zumindest in einem Verfahrensschritt das Bauteil auf eine Temperatur zwischen 1100°C und 1200°C für 6 bis 10 Stunden liegt und anschließend abgekühlt wird. According to the present invention, it is proposed that in a forged component made of a TiAl alloy, ie an alloy in which the alloying constituents with the highest proportion of the alloy composition are titanium and aluminum, at least one first heat treatment after forging, in which at least in one step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and then cooled.
Durch die vorhergenden Herstellungsschritte erfährt das TiAl-Material eine teilweise Entmischung. Diese erste Wärmebehandlung wird als Homogenisierungsglühen bezeichnet, da damit die Materialzusammensetzung über das Bauteil homogenisiert wird und bestehende Konzentrationsstelle aufgelöst werden. Dabei kann die Abkühlrate zwischen l°C/s und 5°C/s betragen. Through the previous manufacturing steps, the TiAl material undergoes partial segregation. This first heat treatment is referred to as homogenization annealing, as it does the material composition is homogenized over the component and existing concentration point are dissolved. The cooling rate can be between 1 ° C / s and 5 ° C / s.
In einer bevorzugten ersten Ausführungsform wird das Bauteil in einer zweiten Wärmebehandlung über der Solvus-Linie von γ-TiAl erwärmt. Durch eine derartige zweiten Wärmebehandlung wird im Gefüge das enthaltene γ-TiAl zumindest teilweise in eine andere feste Phase, wie z.B. a- TiAl umgewandelt, sodass eine gewünschte bzw. angepasste Phasenzusammensetzung in der TiAl-Legierung ermöglicht wird und insbesondere abhängig von der chemischen Zusammensetzung des Bauteils durch Variation der Phasenzusammensetzung eine Einstellung optimaler mechanischer Eigenschaften, insbesondere hinsichtlich der Gesamtdehnung und der Kriechfestigkeit möglich wird. Die Wärmebehandlung kann hierbei speziell auf die spezifische chemische Zusammensetzung und deren Streuung im Bauteil abgestimmt werden. Im Vergleich zur bisherigen Vorgehensweise, bei der zwar nach dem Schmieden ebenfalls eine Wärmebehandlung zur Erholung des Gefüges durchgeführt worden ist, kommt es jedoch bei einer Auslagerung des Bauteils bei einer Temperatur oberhalb der Solvus-Linie des γ - TiAl im entsprechenden Phasendiagramm zu einer Änderung der Phasenzusammensetzung, welche eine variable Einstellung der mechanischen Eigenschaften des Bauteils ermöglicht. Diese zweite Wärmebehandlung bezeichnet man als Rekristallisationsglühen. In a preferred first embodiment, the component is heated in a second heat treatment over the solvus line of γ-TiAl. By such a second heat treatment, in the microstructure, the contained γ-TiAl is at least partially converted to another solid phase, such as e.g. a TiAl converted, so that a desired or adapted phase composition in the TiAl alloy is made possible and in particular depending on the chemical composition of the component by varying the phase composition adjustment of optimum mechanical properties, in particular with respect to the total elongation and creep resistance is possible. The heat treatment can be tailored specifically to the specific chemical composition and its scattering in the component. Compared to the previous procedure, in which although a heat treatment for the recovery of the microstructure has also been carried out after forging, when the component is removed at a temperature above the solvus line of the γ-TiAl in the corresponding phase diagram, there is a change in the Phase composition, which allows a variable adjustment of the mechanical properties of the component. This second heat treatment is called recrystallization annealing.
Das Bauteil kann nach der zweiten Wärmebehandlung über der Solvus-Linie des γ-TiAl schnell abgekühlt werden, um die bei der Wärmebehandlungstemperatur eingestellte Phasenzusammensetzung weitgehend einzufrieren. Eine schnelle Abkühlung kann beispielsweise durch Abschrecken in Wasser oder Öl oder durch Luftkühlung mit einem Gebläse erfolgen. The component may be rapidly cooled after the second heat treatment above the solvus line of the γ-TiAl to substantially freeze the phase composition set at the heat treatment temperature. Quick cooling can be done, for example, by quenching in water or oil, or by air cooling with a blower.
Die Abkühlung kann so schnell erfolgen, dass eine Umwandlung von bei der zweiten Wärmebehandlung zusätzlich gebildetem α-TiAl in eine Lamellenstruktur aus α-TiAl und γ-TiAl vermieden wird. The cooling can take place so quickly that a conversion of α-TiAl additionally formed in the second heat treatment into a lamellar structure of α-TiAl and γ-TiAl is avoided.
Darüber hinaus kann die zweiten Wärmebehandlung bei einer Temperatur durchgeführt werden, bei der vermieden wird, in ein einphasiges Phasenfeld des TiAl-Phasendiagramms zu gelangen, wie beispielsweise das α-TiAl Phasenfeld, um die bei einer Wärmebehandlung in einem einphasigen Phasenfeld auftretende Gefahr des Grobkornwachstums zu unterbinden. Die zweite Wärmebehandlung kann für eine Zeitdauer durchgeführt werden, die eine ausreichende Umwandlung des γ-TiAl in eine andere Phase, insbesondere a-TiAl, gewährleistet, so dass die gewünschte Phasenzusammensetzung erreicht werden kann. Moreover, the second heat treatment may be performed at a temperature that avoids entering a single-phase phase field of the TiAl phase diagram, such as the α-TiAl phase field, by the risk of coarse grain growth associated with heat treatment in a single-phase phase field prevention. The second heat treatment can be carried out for a period of time which ensures sufficient conversion of the γ-TiAl to another phase, in particular a-TiAl, so that the desired phase composition can be achieved.
Die Temperatur bei der zweiten Wärmebehandlung über der γ-TiAl-Solvus-Linie kann bei einer Temperatur von 20°C bis 50°C, insbesondere 25°C bis 35°C, vorzugsweise ca. 30°C über der γ- TiAl-Solvus-Linie gewählt werden. The temperature in the second heat treatment over the γ-TiAl solvus line can at a temperature of 20 ° C to 50 ° C, in particular 25 ° C to 35 ° C, preferably about 30 ° C above the γ-TiAl solvus Line can be selected.
Das Verfahren kann insbesondere für Bauteile eingesetzt werden, die aus einer TiAl-Legierung mit 42 bis 45 At.-% Titan, insbesondere 42,5 - 54,5 At.-% Titan, 3,5 bis 4,5 At.-% Niob, insbesondere 4,0 bis 4,2 At.-% Niob, 0,75 bis 1,5 At.-% Molybdän, insbesondere 0,9 bis 1,2 At.-% Molybdän, und 0,05 bis 0,15 At.-% Bor, insbesondere 0,1 bis 0,12 At.-% Bor, sowie dem Rest Aluminium und unvermeidbaren Verunreinigungen bestehen. Bei einer derartigen Legierung liegt eine Phasenzusammensetzung mit entsprechenden Anteilen des γ-TiAl vor, die den Einsatz des erfindungsgemäßen Verfahrens besonders vorteilhaft macht. The method can be used in particular for components which consist of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 to 54.5 at.% Titanium, 3.5 to 4.5 at.%. Niobium, in particular 4.0 to 4.2 at.% Niobium, 0.75 to 1.5 at.% Molybdenum, in particular 0.9 to 1.2 at.% Molybdenum, and 0.05 to 0, 15 at.% Boron, in particular 0.1 to 0.12 at.% Boron, and the balance aluminum and unavoidable impurities. In such an alloy, a phase composition with corresponding proportions of the γ-TiAl is present, which makes the use of the method according to the invention particularly advantageous.
Aiterativ zur oben erwähnten zweiten Wärmebehandlung kann in der zweiten bevorzugten Aus- fuhrungsform die zweite Wärmehandlung bei einer Temperatur unterhalb der Solvus-Linie γ- TiAl durchgeführt werden, wobei die Temperatur insbesondere zwischen 12°C und 18°C unterhalb der Solvus-Linie liegt. As an alternative to the above-mentioned second heat treatment, in the second preferred embodiment, the second heat treatment may be carried out at a temperature below the solvus line γ-TiAl, the temperature being in particular between 12 ° C and 18 ° C below the solvus line.
In einer bevorzugten Ausführungsform kann zusätzlich eine dritte Wärmebehandlung im Temperaturbereich von 800°C bis 950°C für 5 bis 7 Stunden durchgeführt werden, um das Materialge- f ge im Bauteil zu stabilisieren (Stablisierungsglühen). In a preferred embodiment, a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours may additionally be carried out in order to stabilize the material charge in the component (stabilization annealing).
Mit einem entsprechenden Verfahren können Bauteile einer Strömungsmaschine hergestellt werden, insbesondere einer Gasturbine oder eines Flugtriebwerks, wie insbesondere Laufschaufeln, Leitschaufeln, oder Turbinenbliske, die ein variabel einstellbares Eigenschaftsprofil aufgrund einer angepassten Phasenzusammensetzung aufweisen. KURZBESCHREIBUNG DER FIGUR With a corresponding method components of a turbomachine can be produced, in particular a gas turbine or an aircraft engine, in particular blades, vanes, or turbine blades, which have a variably adjustable property profile due to an adapted phase composition. BRIEF DESCRIPTION OF THE FIGURE
Die beigefügte Zeichnung in der einzigen Figur zeigt ein sogenanntes TNM-Phasendiagramm für einen Werkstoff, bei dem die vorliegende Erfindung verwirklicht werden kann. The accompanying drawing in the single figure shows a so-called TNM phase diagram for a material in which the present invention can be realized.
AUSFÜHRUNGSBEISPIEL Embodiment
Ein Werkstoff für ein erfindungsgemäß hergestelltes Bauteil kann beispielsweise eine Zusammensetzung im Bereich von 42 bis 45 At.-% Titan, 3,5 bis 4,5 At.-% Niob, 0,75 bis 1,5 At.-% Molybdän, sowie 0,05 bis 0,15 At.-% Bor mit Rest Aluminium und unvermeidbaren Verunreinigungen aufweisen. Ein entsprechendes Bauteil kann beispielsweise isotherm geschmiedet werden, bis es die Rohkontur des endgültig herzustellenden Bauteils aufweist. A material for a component produced according to the invention can be, for example, a composition in the range of 42 to 45 at.% Titanium, 3.5 to 4.5 at.% Niobium, 0.75 to 1.5 at.% Molybdenum, and 0.05 to 0.15 at.% Boron with balance aluminum and unavoidable impurities. A corresponding component can for example be forged isothermally until it has the rough contour of the final component to be produced.
Als erstes wird das Material des Bauteils durch eine erste Wärmebehandlung bei bspw. 1150°C für 8 Stunden homogenisiert. First, the material of the component is homogenized by a first heat treatment at, for example, 1150 ° C for 8 hours.
Das Bauteil kann in ersten ersten Alternative einer zweiten Wärmebehandlung dann bei einer Temperatur von beispielsweise 1290°C (also oberhalb der Solvus-Linie(l)) für eine vorbestimmte Zeitdauer geglüht werden, um eine teilweise Umwandlung des γ-TiAls in a-TiAl zu bewirken, sodass α-TiAl und γ-TiAl nebeneinander im Gefüge vorliegen. Die Temperaturbehandlung kann dabei solange durchgeführt werden, bis für die gewünschte Phasenzusammensetzung eine ausreichende Menge an γ-TiAl in a-TiAl umgewandelt worden ist. The component may then be annealed in a first first alternative of a second heat treatment then at a temperature of, for example, 1290 ° C (ie, above the solvus line (l)) for a predetermined period of time to permit partial conversion of the γ-TiAl to α-TiAl cause α-TiAl and γ-TiAl to coexist in the microstructure. The temperature treatment can be carried out until a sufficient amount of γ-TiAl has been converted to α-TiAl for the desired phase composition.
Danach wird das Bauteil schnell abgekühlt, beispielsweise durch Abschrecken in Wasser (10min) oder in Öl oder durch Abkühlung mit einem Gebläse. Diese Gebläseabkühlung erfolgt in einem Ofen, wobei die Temperatur auf 850°C gesenkt und für 6 Stunden gehalten wird. Thereafter, the component is cooled rapidly, for example by quenching in water (10 min) or in oil or by cooling with a blower. This fan cooling takes place in an oven, the temperature is lowered to 850 ° C and held for 6 hours.
Dadurch wird das bei der Temperatur der zweiten Wärmebehandlung, also bei einer Temperatur von 1290°C, eingestellte a- und γ-TiAl- Gefüge weitgehend eingefroren und eine Umwandlung der α-Phase in α/γ-Lamellen vermieden. Durch die Wahl der Wärmebehandlungstemperatur in Höhe von 1290°C wird zudem vermieden, dass das γ-TiAl vollständig in α-TiAl umgewandelt wird, was bei einer entsprechenden Temperaturbehandlung zu der Gefahr des Grobkornwachstums führen würde. In einer zweiten Alternative für die zweite Wärmebehandlung wird das Bauteil unterhalb der Solvus-Linie (1) erwärmt. Beispielsweise wird das Bauteil bei 1235°C für eine Stunde erwärmt, anschließend das Bauteil abgekühlt (mit Wasser, Öl oder Ofenabkühlung). Bei der Ofenabkühlung wird die Temperatur auf 850°C gesenkt und für 6 Stunden gehalten. As a result, the α and γ-TiAl microstructure set at the temperature of the second heat treatment, that is to say at a temperature of 1290 ° C., are largely frozen and a conversion of the α phase into α / γ fins is avoided. The choice of the heat treatment temperature of 1290 ° C also avoids that the γ-TiAl is completely converted into α-TiAl, which would lead to the risk of coarse grain growth with a corresponding temperature treatment. In a second alternative for the second heat treatment, the component is heated below the solvus line (1). For example, the component is heated at 1235 ° C for one hour, then cooled the component (with water, oil or Ofenkkühlung). During the oven cooling, the temperature is lowered to 850 ° C and held for 6 hours.
Obwohl die vorliegende Erfindung anhand des Ausführungsbeispiels detailliert beschrieben worden ist, ist für einen Fachmann klar, dass Abwandlungen in der Weise möglich sind, dass einzelne Merkmale weggelassen, oder andersartige Kombinationen von Merkmalen realisiert werden können, ohne dass der Schutzbereich der Ansprüche verlassen wird. Insbesondere schließt die Offenbarung der vorliegenden Erfindung sämtliche Kombinationen der vorgestellten Einzelmerkmale mit ein. Although the present invention has been described in detail with reference to the exemplary embodiment, it is clear to a person skilled in the art that modifications can be made in such a way that individual features can be omitted or other types of combinations of features can be realized without departing from the scope of the claims. In particular, the disclosure of the present invention includes all combinations of the featured individual features.

Claims

Patentansprüche claims
1. Verfahren zur Herstellung eines Bauteils aus einer TiAl - Legierung, bei welchem das Bauteil durch Schmieden, insbesondere isothermes Schmieden geformt und nachfolgend mindestens einer Wärmebehandlung unterzogen wird, dadurch gekennzeichnet, dass A method for producing a component from a TiAl alloy, in which the component is formed by forging, in particular isothermal forging and subsequently subjected to at least one heat treatment, characterized in that
bei einer ersten Wärmebehandlung die Temperatur zwischen 1100 und 1200°C liegt und für 6 bis 10 Stunden gehalten wird und anschließend das Bauteil abgekühlt wird.  in a first heat treatment, the temperature is between 1100 and 1200 ° C and is held for 6 to 10 hours and then the component is cooled.
2. Verfahren nach Anspruch 1, 2. The method according to claim 1,
dadurch gekennzeichnet, dass  characterized in that
die Abkühlrate zwischen l°C/s und 5°C/s liegt.  the cooling rate is between 1 ° C / s and 5 ° C / s.
3. Verfahren nach einem der vorhergehenden Ansprüche, 3. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
bei einer zweiten Wärmebehandlung das Bauteil auf eine Temperatur über der Solvus - Linie (1) von γ - TiAl erwärmt wird.  in a second heat treatment, the component is heated to a temperature above the solvus line (1) of γ - TiAl.
4. Verfahren nach mindestens einem der obigen Ansprüche, 4. The method according to at least one of the above claims,
dadurch gekennzeichnet, dass  characterized in that
das Bauteil nach der zweiten Wärmebehandlung über der Solvus-Linie (1) durch Abschrecken in Wasser oder Öl oder durch Luftkühlung mit einem Gebläse schnell abgekühlt wird.  After the second heat treatment, the component is rapidly cooled above the Solvus line (1) by quenching in water or oil or by air cooling with a blower.
5. Verfahren nach Anspruch 1 oder 2, 5. The method according to claim 1 or 2,
dadurch gekennzeichnet, dass  characterized in that
das Bauteil nach der zweiten Wärmebehandlung so schnell abgekühlt wird, dass eine Umwandlung des α - TiAl in eine Lamellenstruktur aus α - TiAl und γ - TiAl unterdrückt wird.  After the second heat treatment, the component is cooled down so rapidly that a conversion of the α - TiAl into a lamellar structure of α - TiAl and γ - TiAl is suppressed.
6. Verfahren nach einem der vorhergehenden Ansprüche, 6. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
die Temperatur oberhalb der Solvus - Linie (1) so lange gehalten wird, bis eine gewünschte Phasenzusammensetzung aus α - TiAl und γ - TiAl erreicht ist.  the temperature above the Solvus line (1) is maintained until a desired phase composition of α - TiAl and γ - TiAl is reached.
7. Verfahren nach einem der vorhergehenden Ansprüche, 7. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass die Temperatur bei der zweiten Wärmebehandlung 20°C bis 50°C, insbesondere 25°C bis 35°C, vorzugsweise ca. 30°C über der Solvus - Linie gewählt wird. characterized in that the temperature in the second heat treatment is selected to be 20 ° C to 50 ° C, especially 25 ° C to 35 ° C, preferably about 30 ° C above the solvus line.
8. Verfahren nach Anspruch 1 , 8. The method according to claim 1,
dadurch gekennzeichnet, dass  characterized in that
die zweite Wärmebehandlung bei einer Temperatur unterhalb der Solvus-Linie (1) γ - TiAl - Phasenfeldes durchgeführt wird, wobei die Temperatur insbesondere bei 12 bis 18°C unterhalb der Solvus-Linie (1) liegt.  the second heat treatment is carried out at a temperature below the solvus line (1) γ-TiAl phase field, wherein the temperature is in particular at 12 to 18 ° C below the solvus line (1).
9. Verfahren nach einem der vorhergehenden Ansprüche, 9. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
das Bauteil aus einer TiAl - Legierung mit 42 bis 45 At.-% Ti, insbesondere 42,5 bis 44,5 At.-% Ti, 3,5 bis 4,5 At.-% Nb, insbesondere 4 bis 4,2 At.-% Nb, 0,75 bis 1,5 At.-% Mo, insbesondere 0,9 bis 1,2 At.-% Mo und 0,05 bis 0,15 At.-% B, insbesondere 0,1 bis 0,12 At.-% B und Rest Aluminium und unvermeidbare Verunreinigungen gebildet wird.  the component consists of a TiAl alloy with 42 to 45 at.% Ti, in particular 42.5 to 44.5 at.% of Ti, 3.5 to 4.5 at.% Nb, in particular 4 to 4.2 At% Nb, 0.75-1.5 at% Mo, especially 0.9-1.2 at% Mo, and 0.05-0.15 at% B, especially 0.1 to 0.12 at.% B and balance aluminum and unavoidable impurities is formed.
10. Verfahren nach einem der vorhergehenden Ansprüche, 10. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
die Formung des Bauteils durch isothermes Schmieden erfolgt.  the formation of the component is carried out by isothermal forging.
11. Verfahren nach einem der vorhergehenden Ansprüche, 11. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
die Formung des Bauteils durch Feingießen und nachfolgend heiß-isostatisches Pressen erfolgt.  the formation of the component by investment casting and subsequent hot isostatic pressing takes place.
12. Verfahren nach einem der vorhergehenden Ansprüche, 12. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
das Verfahren eine dritte Wärmebehandlung zur Stabilisierung im Temperaturbereich von 800°C bis 950°C für 5 bis 7 Stunden umfasst.  the process comprises a third heat treatment for stabilization in the temperature range of 800 ° C to 950 ° C for 5 to 7 hours.
13. Verfahren nach einem der vorhergehenden Ansprüche, 13. The method according to any one of the preceding claims,
dadurch gekennzeichnet, dass die Temperatur bei mindestens einer Wärmebehandlung mit einer Genauigkeit von 5°C bis 10°C Abweichung von der Solltemperatur nach oben und unten eingestellt und gehalten wird. characterized in that the temperature is set and maintained at at least one heat treatment with an accuracy of 5 ° C to 10 ° C deviation from the target temperature up and down.
14. Bauteil, das mit dem Verfahren nach einem der vorhergehenden Ansprüche hergestellt den ist. 14. A component manufactured by the method according to any one of the preceding claims is the.
Bauteil nach Anspruch 12, Component according to claim 12,
dadurch gekennzeichnet, dass  characterized in that
es ein Bauteil einer Strömungsmaschine, insbesondere einer Gasturbine oder eines ] triebwerks ist, insbesondere eine Laufschaufel, Leitschaufel oder Turbinenblisk ist.  it is a component of a turbomachine, in particular a gas turbine or an engine, in particular a blade, guide vane or turbine blisk.
EP13705380.7A 2012-01-25 2013-01-19 Method for producing forged components from a tial alloy and component produced thereby Active EP2807281B1 (en)

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EP2851445B1 (en) 2013-09-20 2019-09-04 MTU Aero Engines GmbH Creep-resistant TiAl alloy
ES2719706T3 (en) * 2015-01-28 2019-07-12 MTU Aero Engines AG Component element with protective layer and procedure for manufacturing it
DE102015115683A1 (en) * 2015-09-17 2017-03-23 LEISTRITZ Turbinentechnik GmbH A method for producing an alpha + gamma titanium aluminide alloy preform for producing a heavy duty component for reciprocating engines and gas turbines, in particular aircraft engines
EP3239468A1 (en) 2016-04-27 2017-11-01 MTU Aero Engines GmbH Method for producing a rotor blade for a fluid flow engine
EP3238863A1 (en) 2016-04-27 2017-11-01 MTU Aero Engines GmbH Method for producing a rotor blade for a fluid flow engine
EP3326746A1 (en) * 2016-11-25 2018-05-30 Helmholtz-Zentrum Geesthacht Zentrum für Material- und Küstenforschung GmbH Method for joining and/or repairing substrates of titanium aluminide alloys
DE102018209881A1 (en) * 2018-06-19 2019-12-19 MTU Aero Engines AG Process for producing a forged component from a TiAl alloy
US11807911B2 (en) * 2021-12-15 2023-11-07 Metal Industries Research & Development Centre Heat treatment method for titanium-aluminum intermetallic and heat treatment device therefor

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