EP2807281B1 - 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 Download PDFInfo
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- EP2807281B1 EP2807281B1 EP13705380.7A EP13705380A EP2807281B1 EP 2807281 B1 EP2807281 B1 EP 2807281B1 EP 13705380 A EP13705380 A EP 13705380A EP 2807281 B1 EP2807281 B1 EP 2807281B1
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- component
- tial
- heat treatment
- temperature
- forging
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- 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
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
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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
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- 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
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- 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
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- 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
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- 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
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- 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 is then subjected to a heat treatment.
- the present invention relates to a correspondingly manufactured component.
- a method according to the features of the preamble of claim 1 is for example from EP 2 386 663 A1 known.
- TiAl alloys the main components of which 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 resistance. In addition, they have a low specific weight, so that the use of titanium aluminides or TiAl alloys is suitable as in high-temperature applications, for example in flow machines, in particular gas turbines or aircraft engines.
- TNM alloys By adding certain alloy components, such as niobium and molybdenum, the property profile of the TiAl alloys can be further optimized.
- Such alloys with a niobium and molybdenum content are also referred to as so-called TNM alloys,
- alloys are used in aircraft engines, for example, as guide vanes or rotor blades and are brought into the appropriate component shape by forging.
- isothermal forging can be used here with subsequent heat treatment to adjust the structure and the property profile.
- blisk artificial word for blade and disk
- one-piece blade and disk units so-called blisk (artificial word for blade and disk) can also be produced.
- due to differences in the chemical composition across the component there may be a different phase composition within a component made of a TiAl material during manufacture, which results in an uneven distribution of the property profile in the component, resulting in corresponding fluctuations in the properties
- Such components can no longer be used across the component if they are outside the specified specification for the component. This leads to high reject rates.
- the present invention it is proposed to carry out at least one first heat treatment after forging in a component made of a TiAl alloy, i.e. an alloy in which the alloy components with the highest proportion of the alloy composition are titanium and aluminum, after forging, in which at least In one process step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and is then cooled.
- a component made of a TiAl alloy i.e. an alloy in which the alloy components with the highest proportion of the alloy composition are titanium and aluminum
- This first heat treatment is referred to as homogenization annealing, as it homogenizes the material composition over the component and dissolves existing concentration points.
- the cooling rate can be between 1 ° C / s and 5 ° C / s.
- the component is heated in a second heat treatment above the solvus line of ⁇ -TiAl.
- a second heat treatment the ⁇ -TiAl contained in the structure is at least partially converted into another solid phase, such as ⁇ -TiAl, so that a desired or adapted phase composition is made possible in the TiAl alloy and in particular depending on the chemical composition of the
- the heat treatment can be specially tailored to the specific chemical composition and its distribution in the component.
- the component is rapidly cooled above the solvus line of the ⁇ -TiAl in order to largely freeze the phase composition set at the heat treatment temperature. Rapid cooling is achieved by quenching in water or oil or by air cooling with a fan.
- the cooling can take place so quickly that a conversion of the ⁇ -TiAl additionally formed during the second heat treatment into a lamellar structure of ⁇ -TiAl and ⁇ -TiAl is avoided.
- the second heat treatment can be carried out at a temperature at which it is avoided to get into a single-phase phase field of the TiAl phase diagram, such as the ⁇ -TiAl phase field, in order to reduce the risk of coarse grain growth occurring during a heat treatment in a single-phase phase field prevent.
- the second heat treatment can be carried out for a period of time which ensures sufficient conversion of the ⁇ -TiAl into another phase, in particular ⁇ -TiAl, so that the desired phase composition can be achieved.
- the temperature in the second heat treatment above the ⁇ -TiAl solvus line can be 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 to be chosen.
- the method is used for components made of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 - 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 remainder aluminum and unavoidable impurities.
- Such an alloy has a phase composition with corresponding proportions of ⁇ -TiAl which makes the use of the method according to the invention particularly advantageous.
- a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours can also be carried out in order to stabilize the material structure in the component (stabilization annealing).
- components of a turbomachine can be produced, in particular a gas turbine or an aircraft engine, such as in particular rotor blades, guide vanes, or turbine blisks, which have a variably adjustable property profile based on an adapted phase composition.
- the attached drawing in the single figure shows a so-called TNM phase diagram for a material in which the present invention can be implemented.
- a material for a component produced according to the invention has a composition in the range from 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 atom% boron with the remainder aluminum and unavoidable impurities.
- a corresponding component can, for example, be isothermally forged until it has the raw contour of the component to be finally produced.
- the material of the component is homogenized by a first heat treatment at, for example, 1150 ° C for 8 hours.
- the component is then annealed in a second heat treatment at a temperature of, for example, 1290 ° C (i.e. above the Solvus line (1)) for a predetermined period of time in order to bring about a partial conversion of the ⁇ -TiAl to ⁇ -TiAl, so that ⁇ -TiAl and ⁇ -TiAl are present next to each other in the structure.
- the temperature treatment can be carried out until a sufficient amount of ⁇ -TiAl has been converted into ⁇ -TiAl for the desired phase composition.
- the component is then quickly cooled, for example by quenching in water (10min) or in oil or by cooling with a fan. This fan cooling takes place in an oven, the temperature being reduced to 850 ° C. and held for 6 hours.
- the ⁇ - and ⁇ -TiAl structure set at the temperature of the second heat treatment i.e. at a temperature of 1290 ° C.
- the heat treatment temperature 1290 ° C, it is also avoided that the ⁇ -TiAl is completely converted into ⁇ -TiAl, which would lead to the risk of coarse grain growth with a corresponding temperature treatment.
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- 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)
Description
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. Ein Verfahren gemäß den Merkmalen des Oberbegriffs von Anspruch 1 ist zum Beispiel aus der
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 Titanaluminide bzw. von TiAl-Legierungenwie bei Hochtemperaturanwendungen, beispielsweise bei Strömungsmaschinen, insbesondere Gasturbinen oder Flugtriebwerken, geeignet ist.TiAl alloys, the main components of which 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 resistance. In addition, they have a low specific weight, so that the use of titanium aluminides or TiAl alloys is suitable as in high-temperature applications, for example in flow machines, in particular gas turbines or aircraft engines.
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 alloy components, such as niobium and molybdenum, the property profile of the TiAl alloys can be further optimized. Such alloys with a 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. Allerdings kann es bei der Herstellung auf Grund von Unterschieden in der chemischen Zusammensetzung über das Bauteil hinweg zu einer unterschiedlichen Phasenzusammensetzung innerhalb 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.These alloys are used in aircraft engines, for example, as guide vanes or rotor blades and are brought into the appropriate component shape by forging. In particular, isothermal forging can be used here with subsequent heat treatment to adjust the structure and the property profile. In this way, one-piece blade and disk units, so-called blisk (artificial word for blade and disk) can also be produced. However, due to differences in the chemical composition across the component, there may be a different phase composition within a component made of a TiAl material during manufacture, which results in an uneven distribution of the property profile in the component, resulting in corresponding fluctuations in the properties Such components can no longer be used across the component if they are outside the specified specification for the component. This leads to high reject rates.
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 the object of the present invention to provide a method for producing components from a TiAl alloy via a forging production route, in which the problems of the prior art, in particular with regard to inhomogeneous properties of the component, are eliminated, and in particular a component made from a TiAl -Alloy can be produced in a simple manner with a desired profile of properties, in particular the specific chemical composition and its scatter in the component can be addressed.
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 11. 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 11. Advantageous configurations are the subject matter 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 to carry out at least one first heat treatment after forging in a component made of a TiAl alloy, i.e. an alloy in which the alloy components with the highest proportion of the alloy composition are titanium and aluminum, after forging, in which at least In one process step, the component is at a temperature between 1100 ° C and 1200 ° C for 6 to 10 hours and is then cooled.
Durch die vorhergehenden Herstellungsschritte erfährt das TiAl-Material eine teilweise Entrnischung. 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 1°C/s und 5°C/s betragen.As a result of the previous manufacturing steps, the TiAl material is partially cleared. This first heat treatment is referred to as homogenization annealing, as it homogenizes the material composition over the component and dissolves existing concentration points. 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. α-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 y - 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 above the solvus line of γ-TiAl. Through such a second heat treatment, the γ-TiAl contained in the structure is at least partially converted into another solid phase, such as α-TiAl, so that a desired or adapted phase composition is made possible in the TiAl alloy and in particular depending on the chemical composition of the By varying the phase composition of the component, it is possible to set optimal mechanical properties, in particular with regard to the overall elongation and creep resistance. The heat treatment can be specially tailored to the specific chemical composition and its distribution in the component. Compared to the previous procedure, in which heat treatment was also carried out after forging to recover the structure, however, if the component is removed from storage at a temperature above the solvus line of the y - TiAl in the corresponding phase diagram, there is a change in the Phase composition, which enables a variable setting of the mechanical properties of the component. This second heat treatment is known as recrystallization annealing.
Erfindungsgemäß wird das Bauteil nach der zweiten Wärmebehandlung über der Solvus-Linie des γ-TiAl schnell abgekühlt, um die bei der Wärmebehandlungstemperatur eingestellte Phasenzusammensetzung weitgehend einzufrieren. Eine schnelle Abkühlung erfolgt durch Abschrecken in Wasser oder Öl oder durch Luftkühlung mit einem Gebläse.According to the invention, after the second heat treatment, the component is rapidly cooled above the solvus line of the γ-TiAl in order to largely freeze the phase composition set at the heat treatment temperature. Rapid cooling is achieved by quenching in water or oil or by air cooling with a fan.
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 the α-TiAl additionally formed during 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.In addition, the second heat treatment can be carried out at a temperature at which it is avoided to get into a single-phase phase field of the TiAl phase diagram, such as the α-TiAl phase field, in order to reduce the risk of coarse grain growth occurring during a heat treatment in a single-phase phase field prevent.
Die zweite Wärmebehandlung kann für eine Zeitdauer durchgeführt werden, die eine ausreichende Umwandlung des γ - TiAl in eine andere Phase, insbesondere α - TiAl, gewährleistet, so dass die gewünschte Phasenzusammensetzung erreicht werden kann.The second heat treatment can be carried out for a period of time which ensures sufficient conversion of the γ-TiAl into another phase, in particular α-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 above the γ-TiAl solvus line can be 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 to be chosen.
Das Verfahren wird für Bauteile eingesetzt, 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 is used for components made of a TiAl alloy with 42 to 45 at.% Titanium, in particular 42.5 - 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 remainder aluminum and unavoidable impurities. Such an alloy has a phase composition with corresponding proportions of γ-TiAl which makes the use of the method according to the invention particularly advantageous.
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 Materialgefüge im Bauteil zu stabilisieren (Stabilisierungsglühen).In a preferred embodiment, a third heat treatment in the temperature range from 800 ° C. to 950 ° C. for 5 to 7 hours can also be carried out in order to stabilize the material structure 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.With a corresponding method, components of a turbomachine can be produced, in particular a gas turbine or an aircraft engine, such as in particular rotor blades, guide vanes, or turbine blisks, which have a variably adjustable property profile based on an adapted phase composition.
Die beigefügte Zeichnung in der einzigen Figur zeigt ein sogenanntes TNM-Phasendiagramm für einen Werkstoff, bei dem die vorliegende Erfindung verwirklicht werden kann.The attached drawing in the single figure shows a so-called TNM phase diagram for a material in which the present invention can be implemented.
Ein Werkstoff für ein erfindungsgemäß hergestelltes Bauteil weist 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 auf. 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 has a composition in the range from 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 atom% boron with the remainder aluminum and unavoidable impurities. A corresponding component can, for example, be isothermally forged until it has the raw contour of the component to be finally 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 wird in einer zweiten Wärmebehandlung dann bei einer Temperatur von beispielsweise 1290°C (also oberhalb der Solvus-Linie(1)) für eine vorbestimmte Zeitdauer geglüht, um eine teilweise Umwandlung des γ-TiAls in α-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 α-TiAl umgewandelt worden ist.The component is then annealed in a second heat treatment at a temperature of, for example, 1290 ° C (i.e. above the Solvus line (1)) for a predetermined period of time in order to bring about a partial conversion of the γ-TiAl to α-TiAl, so that α -TiAl and γ-TiAl are present next to each other in the structure. The temperature treatment can be carried out until a sufficient amount of γ-TiAl has been converted into 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. Dadurch wird das bei der Temperatur der zweiten Wärmebehandlung, also bei einer Temperatur von 1290°C, eingestellte α- 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.The component is then quickly cooled, for example by quenching in water (10min) or in oil or by cooling with a fan. This fan cooling takes place in an oven, the temperature being reduced to 850 ° C. and held for 6 hours. As a result, the α- and γ-TiAl structure set at the temperature of the second heat treatment, i.e. at a temperature of 1290 ° C., is largely frozen and a conversion of the α-phase into α / γ-lamellae is avoided. By choosing the heat treatment temperature of 1290 ° C, it is also avoided 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.
Claims (12)
- A method for producing a component from a TiAl alloy with 42 to 45 at% Ti, 3.5 to 4.5 at% Nb, 0.75 to 1.5 at% Mo, 0.05 to 0.15 at% B, and the remainder aluminum and unavoidable impurities, wherein the component is formed by forging, in particular isothermal forging, and then subjected to at least one heat treatment, the temperature of a first heat treatment being between 1100 and 1200°C and being maintained for 6 to 10 hours, whereupon the component is cooled, characterized in that, in a second heat treatment, the component is heated to a temperature above the solvus line (1) of γ-TiAl, and after the second heat treatment above the solvus line (1), the component is rapidly cooled by quenching in water or oil or by air cooling with a fan.
- The method according to claim 1, characterized in that the cooling rate after the first heat treatment is between 1 °C/s and 5°C/s.
- The method according to claim 1 or 2, characterized in that the component is cooled so quickly after the second heat treatment that a conversion of the α-TiAl into a lamellar structure of α-TiAl and γ-TiAl is suppressed.
- The method according to one of the preceding claims, characterized in that the temperature above the solvus line (1) is maintained until a desired phase composition of α-TiAl and γ-TiAl is reached.
- The method according to one of the preceding claims, characterized in that the temperature for the second heat treatment is selected from 20°C to 50°C, in particular 25°C to 35°C, preferably approximately 30°C above the solvus line.
- The method according to one of the preceding claims, characterized in that the component is made of a TiAl alloy with 42.5 to 44.5 at% Ti, 4 to 4.2 at% Nb, 0.9 to 1.2 at% Mo, 0.1 to 0.12 at% B, and the remainder aluminum and unavoidable impurities.
- The method according to one of the preceding claims, characterized in that the component is formed by isothermal forging.
- The method according to one of the preceding claims, characterized in that the component is formed by investment casting and subsequent hot isostatic pressing.
- The method according to one of the preceding claims, characterized in that the method comprises a third heat treatment for stabilization in the temperature range from 800°C to 950°C for 5 to 7 hours.
- The method according to one of the preceding claims, characterized in that the temperature during at least one heat treatment is adjusted up and down and maintained with a precision of a 5°C to 10°C deviation from the targettemperature.
- A component that has been produced using the method according to one of the preceding claims.
- The component according to claim 11, characterized in that it is a component of a turbomachine, in particular a gas turbine or an aircraft engine, in particular a rotor blade, guide vane, or turbine blisk.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102012201082.3A DE102012201082B4 (en) | 2012-01-25 | 2012-01-25 | Method for producing forged components from a TiAl alloy and correspondingly manufactured component |
| PCT/DE2013/000037 WO2013110260A1 (en) | 2012-01-25 | 2013-01-19 | Method for producing forged components from a tial alloy and component produced thereby |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP2807281A1 EP2807281A1 (en) | 2014-12-03 |
| EP2807281B1 true EP2807281B1 (en) | 2021-06-02 |
Family
ID=47747265
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP13705380.7A Active EP2807281B1 (en) | 2012-01-25 | 2013-01-19 | Method for producing forged components from a tial alloy and component produced thereby |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10107112B2 (en) |
| EP (1) | EP2807281B1 (en) |
| DE (1) | DE102012201082B4 (en) |
| ES (1) | ES2877557T3 (en) |
| WO (1) | WO2013110260A1 (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2851445B1 (en) * | 2013-09-20 | 2019-09-04 | MTU Aero Engines GmbH | Creep-resistant TiAl alloy |
| EP3050998B1 (en) * | 2015-01-28 | 2019-03-27 | MTU Aero Engines GmbH | Component with protective layer and method for producing the same |
| 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 |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2386663A1 (en) * | 2010-05-12 | 2011-11-16 | Böhler Schmiedetechnik GmbH & Co KG | Method for producing a component and component from a gamma-titanium-aluminium base alloy |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5558729A (en) | 1995-01-27 | 1996-09-24 | The United States Of America As Represented By The Secretary Of The Air Force | Method to produce gamma titanium aluminide articles having improved properties |
| GB9714391D0 (en) | 1997-07-05 | 1997-09-10 | Univ Birmingham | Titanium aluminide alloys |
| DE19756354B4 (en) | 1997-12-18 | 2007-03-01 | Alstom | Shovel and method of making the blade |
| AU2002221859A1 (en) | 2000-12-15 | 2002-06-24 | Rolls-Royce Deutschland Ltd And Co Kg | Method for producing components with a high load capacity from tial alloys |
| AT508323B1 (en) | 2009-06-05 | 2012-04-15 | Boehler Schmiedetechnik Gmbh & Co Kg | METHOD FOR PRODUCING A FORGING PIECE FROM A GAMMA TITANIUM ALUMINUM BASE ALLOY |
-
2012
- 2012-01-25 DE DE102012201082.3A patent/DE102012201082B4/en not_active Expired - Fee Related
-
2013
- 2013-01-19 ES ES13705380T patent/ES2877557T3/en active Active
- 2013-01-19 EP EP13705380.7A patent/EP2807281B1/en active Active
- 2013-01-19 US US14/374,260 patent/US10107112B2/en active Active
- 2013-01-19 WO PCT/DE2013/000037 patent/WO2013110260A1/en not_active Ceased
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2386663A1 (en) * | 2010-05-12 | 2011-11-16 | Böhler Schmiedetechnik GmbH & Co KG | Method for producing a component and component from a gamma-titanium-aluminium base alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2013110260A1 (en) | 2013-08-01 |
| DE102012201082A1 (en) | 2013-07-25 |
| US20140369822A1 (en) | 2014-12-18 |
| EP2807281A1 (en) | 2014-12-03 |
| DE102012201082B4 (en) | 2017-01-26 |
| US10107112B2 (en) | 2018-10-23 |
| ES2877557T3 (en) | 2021-11-17 |
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