EP2227571B1 - Material for a gas turbine component, method for producing a gas turbine component and gas turbine component - Google Patents

Material for a gas turbine component, method for producing a gas turbine component and gas turbine component Download PDF

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EP2227571B1
EP2227571B1 EP08841961.9A EP08841961A EP2227571B1 EP 2227571 B1 EP2227571 B1 EP 2227571B1 EP 08841961 A EP08841961 A EP 08841961A EP 2227571 B1 EP2227571 B1 EP 2227571B1
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Prior art keywords
phase
gas turbine
turbine component
temperature
forging
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German (de)
French (fr)
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EP2227571A2 (en
Inventor
Wilfried Smarsly
Helmut Clemens
Volker Guether
Sascha Kremmer
Andreas Otto
Harald Chladil
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Montanuniversitaet Leoben
Voestalpine Boehler Aerospace GmbH and Co KG
GFE Metalle und Materialien GmbH
MTU Aero Engines GmbH
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Montanuniversitaet Leoben
Voestalpine Boehler Aerospace GmbH and Co KG
GFE Metalle und Materialien GmbH
MTU Aero Engines GmbH
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Priority to DE102007051499A priority Critical patent/DE102007051499A1/en
Application filed by Montanuniversitaet Leoben, Voestalpine Boehler Aerospace GmbH and Co KG, GFE Metalle und Materialien GmbH, MTU Aero Engines GmbH filed Critical Montanuniversitaet Leoben
Priority to PCT/DE2008/001702 priority patent/WO2009052792A2/en
Publication of EP2227571A2 publication Critical patent/EP2227571A2/en
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    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22CALLOYS
    • C22C14/00Alloys based on titanium
    • CCHEMISTRY; METALLURGY
    • C22METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22FCHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/16Changing 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
    • C22F1/18High-melting or refractory metals or alloys based thereon
    • C22F1/183High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon

Description

  • Die Erfindung betrifft ein Verfahren zur Herstellung eines Gasturbinenbauteils nach dem Oberbegriff des Anspruchs 1 sowie ein Gasturbinenbauteil nach Anspruch 4.The invention relates to a method for producing a gas turbine component according to the preamble of claim 1 and to a gas turbine component according to claim 4.
  • Moderne Gasturbinen, insbesondere Flugtriebwerke, müssen höchsten Ansprüchen im Hinblick auf Zuverlässigkeit, Gewicht, Leistung, Wirtschaftlichkeit und Lebensdauer gerecht werden. In den letzten Jahrzehnten wurden insbesondere auf dem zivilen Sektor Flugtriebwerke entwickelt, die den obigen Anforderungen voll gerecht werden und ein hohes Maß an technischer Perfektion erreicht haben. Bei der Entwicklung von Flugtriebwerken spielt unter anderem die Werkstoffauswahl, die Suche nach neuen, geeigneten Werkstoffen sowie die Suche nach neuen Fertigungsverfahren eine entscheidende Rolle.Modern gas turbines, in particular aircraft engines, must meet the highest demands in terms of reliability, weight, performance, economy and service life. In recent decades, aircraft engines have been developed, particularly in the civil sector, which fully meet the above requirements and have achieved a high degree of technical perfection. Among other things, the selection of materials, the search for new, suitable materials and the search for new production processes play a crucial role in the development of aircraft engines.
  • Die wichtigsten, heutzutage für Flugtriebwerke oder sonstige Gasturbinen verwendeten Werkstoffe sind Titanlegierungen, Nickellegierungen (auch Superlegierungen genannt) und hochfeste Stähle. Die hochfesten Stähle werden für Wellenteile, Getriebeteile, Verdichtergehäuse und Turbinengehäuse verwendet. Titanlegierungen sind typische Werkstoffe für Verdichterteile. Nickellegierungen sind für die heißen Teile des Flugtriebwerks geeignet.The most important materials used today for aircraft engines or other gas turbines are titanium alloys, nickel alloys (also called superalloys) and high-strength steels. The high strength steels are used for shaft parts, gear parts, compressor casings and turbine casings. Titanium alloys are typical materials for compressor parts. Nickel alloys are suitable for the hot parts of the aircraft engine.
  • Als Fertigungsverfahren für Gasturbinenbauteile aus Titanlegierungen, Nickellegierung oder sonstigen Legierungen sind aus dem Stand der Technik in erster Linie das Feingießen sowie Schmieden bekannt. Alle hochbeanspruchten Gasturbinenbauteile, wie zum Beispiel Bauteile für einen Verdichter, sind Schmiedeteile. Bauteile für eine Turbine werden hingegen in der Regel als Feingussteile ausgeführt.As a manufacturing method for gas turbine components made of titanium alloys, nickel alloy or other alloys are known from the prior art primarily investment casting and forging. All highly stressed gas turbine components, such as components for a compressor, are forgings. Components for a turbine, however, are usually designed as precision castings.
  • Die DE 10 2004 056 582 A1 offenbart eine Titan-Aluminium-Basis-Legierung mit den Bestandteilen Aluminium, Niob, Molybdän, Bor und Kohlenstoff. Dieser Druckschrift sind allerdings keine Hinweise über Mikrostrukturen des Werkstoffs im Bereich der Raumtemperatur bzw. der eutektoiden Temperatur entnehmbar. Es sind lediglich Hinweise auf das grundsätzliche Vorhandensein einer α2-, γ- und β-Phase enthalten.The DE 10 2004 056 582 A1 discloses a titanium-aluminum base alloy with the components aluminum, niobium, molybdenum, boron and carbon. However, this document gives no information about microstructures of the material in the range of the room temperature or the eutectoid temperature can be removed. There are only indications of the basic presence of α 2 , γ and β phase included.
  • Der Fachartikel von Imayev, R. M. et. al. "Alloy design concepts for refined gamma titanium aluminide based alloys", Intermetallics, 15 (4), 451-460 CODEN: IERME5; ISSN: 0966-9795, 29. Januar 2007 (2007-01-29), XP005924292 offenbart einen Titan-Aluminium-Basis-Legierungswerkstoff mit 44 at% Aluminium, 5 at% Niob, 1 at% Molybdän, 0,2 at% Bor und 0,3 at% Kohlenstoff, Rest Titan. Angaben über den Volumenanteil einer βB2-Ti-Phase Bei Raumtemperatur bzw. bei der eutektoiden Temperatur sind dieser Druckschrift nicht entnehmbar.The article from Imayev, RM et. al. "Alloy design concepts for refined gamma titanium aluminide based alloys", Intermetallics, 15 (4), 451-460 CODEN: IERME5; ISSN: 0966-9795, January 29, 2007 (2007-01-29 ), EP005924292 discloses a titanium-aluminum base alloy material comprising 44 at% aluminum, 5 at% niobium, 1 at% molybdenum, 0.2 at% boron and 0.3 at% carbon, balance titanium. Information on the volume fraction of a βB2-Ti phase At room temperature or at the eutectoid temperature of this document are not removable.
  • Die EP 0 592 189 A1 offenbart einen Werkstoff umfassend zumindest Titan und Aluminium, der sowohl im Bereich der Raumtemperatur als auch im Bereich der eutektoiden Temperatur die Phase βB2, die Phase α2 und die Phase γ mit einem Anteil der βB2-Phase von weniger als 5 Vol.-% aufweist.The EP 0 592 189 A1 discloses a material comprising at least titanium and aluminum which, both in the region of the room temperature and in the region of the eutectoid temperature, has the phase βB2, the phase α 2 and the phase γ with a fraction of the βB 2 phase of less than 5% by volume ,
  • Auch der Fachartikel von Kobayashi, Satoru et. al.: "Microstructure control using betatitanium phase for wrought gamma TiAl based alloys" Gamma Titanium Aluminides 2003, proceedings of [a] symposium held during the TMS annual meeting, San Diego, CA, United States, Mar. 2-6, 2003, 165-175. Editor(s): Kim, Young-Won; Clemens, Helmut; Rosenberger, Andrew H. Publisher: Minerals, Meta, 2003, XP009110846 offenbart eine Titan-Aluminium-Legierung mit einem Anteil der Phase βB2 von weniger als 5 Vol.-% im Bereich der eutektoiden Temperatur.Also the article by Kobayashi, Satoru et. al.: "Microstructure control using betatitanium phase for wrought gamma TiAl based alloys" Gamma Titanium Aluminides 2003, proceedings of [a] held during the TMS annual meeting, San Diego, CA, United States, Mar. 2-6, 2003, 165-175. Editor (s): Kim, Young-Won; Clemens, Helmut; Rosenberger, Andrew H. Publisher: Minerals, Meta, 2003 , XP009110846 discloses a titanium-aluminum alloy with a portion of the phase βB2 of less than 5% by volume in the eutectoid temperature range.
  • Aus der Praxis ist es bereits bekannt, Gasturbinenbauteile aus Titan-Aluminium-Basis-Legierungswerkstoffen zu fertigen. Dabei kommen insbesondere γ-TiAl-Basis-Legierungswerkstoffe zum Einsatz, wobei das Schmieden solcher γ-TiAl-Basis-Legierungswerkstoffe problematisch ist. Schmiedeteile aus solchen Werkstoffen müssen nach der Praxis durch isothermes Schmieden oder Hot-Die-Schmieden von vorgeformten, wie z. B. stranggepressten, Halbzeugen hergestellt werden. Das isotherme Schmieden sowie das Hot-Die-Schmieden erfordert quasi isotherm-stranggepresstes Vormaterial, wodurch sich hohe Herstellkosten ergeben.From practice, it is already known to manufacture gas turbine components made of titanium-aluminum-based alloy materials. In particular, γ-TiAl-based alloy materials are used, whereby the forging of such γ-TiAl-based alloy materials is problematic. Forged parts of such materials must be prepared in practice by isothermal forging or hot die forging of preformed, such. B. extruded, semi-finished products are produced. The isothermal forging and the hot die forging requires quasi-isothermal extruded starting material, resulting in high production costs.
  • Es besteht daher ein Bedarf für ein adaptives Schmiedeverfahren unter Verwendung eines Titan-Aluminium-Basis-Legierungswerkstoffes zur Herstellung von Gasturbinenbauteilen. Dieses Verfahren soll eine verbesserte Prozesssicherheit und Prozessstabilität unter reduzierten Herstellkosten gewährleisten.Therefore, there is a need for an adaptive forging process using a titanium-aluminum-base alloy material to make gas turbine components. This process is intended to ensure improved process reliability and process stability with reduced production costs.
  • Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Herstellung eines Gasturbinenbauteils sowie ein neuartiges Gasturbinenbauteil zu schaffen.On this basis, the present invention based on the problem to provide a novel method for producing a gas turbine component and a novel gas turbine component.
  • Dieses Problem wird durch ein Verfahren gemäß Anspruch 1 gelöst. Erfindungsgemäß sind folgende Schritte vorgesehen:
  1. a) Bereitstellen eines gegossenen Halbzeugs aus einem Titan-Aluminium-Basis-Legierungswerkstoff, umfassend zumindest Titan und Aluminium, wobei derselbe im Bereich der Raumtemperatur die Phase β/B2-Ti, die Phase α2-Ti3Al und die Phase γ-TiAl mit einem Anteil der β/B2-Ti-Phase von maximal 5 Vol.-%; im Bereich der eutektoiden Temperatur die Phase β/B2-Ti, die Phase α2-Ti3Al und die Phase γ-TiAl mit einem Anteil der β-Ti-Phase von minimal 10 Vol.-% sowie folgende Zusammensetzung aufweist
    • 42 bis 45 At.-% Aluminium,
    • 3 bis 8 At.-% Niob,
    • 0,2 bis 3 At.-% Molybdän und/oder Mangan,
    • 0,1 bis 1 At.-% Bor und/oder Kohlenstoff und / oder Silizium
    • im Rest Titan, sowie
  2. b) Schmieden des Halbzeugs aus dem Werkstoff zum Bauteil bei einer Umformtemperatur zwischen Te-50K und Tα+100K, wobei Te die eutektoide Temperatur des Werkstoffs und Tα die Alpha-Transus-Temperatur des Werkstoffs ist.
This problem is solved by a method according to claim 1. According to the invention the following steps are provided:
  1. a) providing a cast semi-finished product of a titanium-aluminum-base alloy material comprising at least titanium and aluminum, wherein the same in the region of room temperature, the phase β / B2-Ti, the phase α 2 -Ti 3 Al and the phase γ-TiAl with a proportion of the β / B2-Ti phase of not more than 5% by volume; in the region of the eutectoid temperature, the phase β / B2-Ti, the phase α 2 -Ti 3 Al and the phase γ-TiAl with a proportion of the β-Ti phase of at least 10 vol .-% and having the following composition
    • 42 to 45 at.% Aluminum,
    • 3 to 8 at.% Niobium,
    • 0.2 to 3 at.% Molybdenum and / or manganese,
    • 0.1 to 1 at.% Boron and / or carbon and / or silicon
    • in the rest of titanium, as well
  2. b) forging the semifinished product from the material to the component at a forming temperature between T e -50K and T α + 100K, where T e is the eutectoid temperature of the material and T α is the alpha transus temperature of the material.
  • Der verwendete Werkstoff, bei welchem es sich um einen γ-TiAl-Basis Legierungswerkstoff handelt, erlaubt ein Schmieden innerhalb eines größeren Temperaturintervalls. Zum Schmieden wird als Vormaterial ein Gussmaterial verwendet, sodass auf teures Strangpressmaterial verzichtet werden kann.The material used, which is a γ-TiAl based alloy material, allows forging within a wider temperature range. Forging is used as a starting material, a casting material, so that expensive extruded material can be dispensed with.
  • Das erfindungsgemäße Gasturbinenbauteil ist in Anspruch 4 definiert.The gas turbine component according to the invention is defined in claim 4.
  • Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:
  • Fig. 1
    eine stark schematisierte Darstellung einer aus einem Titan-Aluminium-Basis-Legierungswerkstoff nach dem erfindungsgemäßen Verfahren hergestellten Schaufel einer Gasturbine.
    Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
    Fig. 1
    a highly schematic representation of a produced from a titanium-aluminum-based alloy material according to the inventive blade of a gas turbine.
  • Die hier vorliegende Erfindung setzt einen Werkstoff auf Basis einer Titan-Aluminium-Legierung ein. Der Werkstoff umfasst sowohl im Bereich der Raumtemperatur als auch im Bereich der sogenannten eutektoiden Temperatur mehrere Phasen.The present invention uses a material based on a titanium-aluminum alloy. The material comprises several phases both in the region of the room temperature and in the region of the so-called eutectoid temperature.
  • Im Bereich der Raumtemperatur weist der TiAl-Basis-Legierungswerkstoff die Phase βB2-Ti, die Phase α2-Ti3Al und die Phase γ-TiAl auf, wobei der Anteil der β/B2-Ti-Phase bei Raumtemperatur höchstens bzw. maximal 5 Vol.-% beträgt. Im Bereich der eutektoiden Temperatur weist der erfindungsgemäße TiAI-Basis-Legierungswerkstoff die Phase βB2-Ti, die Phase α2-Ti3Al und die Phase γ-TiAl auf, wobei der Anteil der β/B2-Ti-Phase im Bereich der eutektoiden Temperatur mindestens bzw. minimal 10 Vol.-% beträgt.In the region of room temperature, the TiAl-based alloy material has the phase βB2-Ti, the phase α 2 -Ti 3 Al and the phase γ-TiAl, wherein the proportion of β / B2-Ti phase at room temperature at most or maximum 5% by volume. In the field of eutectoid temperature, the TiAl based alloy material of the invention on the phase βB2-Ti, the phase of α2-Ti 3 Al and the phase γ-TiAl, the proportion of the β / B2-Ti phase in the range of eutectoid temperature at least or minimum 10 vol .-% is.
  • Bei dem Werkstoff handelt es sich demnach um einen γ-TiAl-Basis-Legierungswerkstoff. Derselbe kann mit konventionellen Schmiedeverfahren umgeformt werden, und zwar mit einer Schmiedetemperatur innerhalb eines relativ großen Temperaturintervalls. Die Schmiedetemperatur des Werkstoffs liegt zwischen Te-50K und Tα+100K, wobei Te die eutektoide Temperatur des Werkstoffs und Tα die Alpha-Transus-Temperatur des Werkstoffs ist.The material is therefore a γ-TiAl-based alloy material. It can be reshaped by conventional forging techniques with a forging temperature within a relatively large temperature interval. The forging temperature of the material is between T e -50K and T α + 100K, where T e is the eutectoid temperature of the material and T α is the alpha transus temperature of the material.
  • Wenn die Schmiedetemperatur bzw. Umformtemperatur unter Tα liegt, sowie im Bereich der Schmiedetemperatur bzw. Umformtemperatur sowie im Bereich der eutektoiden Temperatur und der Raumtemperatur befinden sich die Phasen β/B2-Ti, α2Ti3Al und γ-TiAl im thermodynamischen Gleichgewicht.If the forging temperature or forming temperature is below T α , as well as in the area of the forging temperature or forming temperature and in the area of the eutectoid temperature and the room temperature are the phases β / B2-Ti, α 2 Ti 3 Al and γ-TiAl in the thermodynamic equilibrium.
  • Der Anteil der kubisch raumzentrierten βB2-Ti-Phase im thermodynamischen Gleichgewicht des verwendeten Werkstoffs ist im Bereich der Raumtemperatur kleiner als 5 Vol.-%. Im Bereich der eutektoiden Temperatur ist der Anteil der kubisch raumzentrierten βB2-Ti-Phase größer als 10 Vol.-%.The proportion of cubic body-centered βB2-Ti phase in the thermodynamic equilibrium of the material used is less than 5% by volume in the room temperature range. In the area of the eutectoid temperature, the proportion of cubic body-centered βB2-Ti phase is greater than 10% by volume.
  • Der verwendete γ-TiAl-Basis-Legierungswerkstoff weist neben Titan und Aluminium weiterhin Niob, Molybdän und/oder Mangan sowie Bor und/oder Kohlenstoff und / oder Silizium auf.In addition to titanium and aluminum, the γ-TiAl-based alloy material used also contains niobium, molybdenum and / or manganese, and also boron and / or carbon and / or silicon.
  • Der Titan-Aluminium-Basis-Legierungswerkstoff weist folgende Zusammensetzung auf:
    • 42 bis 45 At.-% Aluminium,
    • 3 bis 8 At.-% Niob,
    • 0,2 bis 3 At.-% Molybdän und/oder Mangan,
    • 0,1 bis 1 At.-% , bevorzugt 0,1 bis 0,5 At.-%, Bor und/oder Kohlenstoff und / oder Silizium,
    • im Rest Titan.
    The titanium-aluminum-based alloy material has the following composition:
    • 42 to 45 at.% Aluminum,
    • 3 to 8 at.% Niobium,
    • 0.2 to 3 at.% Molybdenum and / or manganese,
    • 0.1 to 1 at.%, Preferably 0.1 to 0.5 at.%, Boron and / or carbon and / or silicon,
    • in the rest of titanium.
  • Zur Herstellung eines Gasturbinenbauteils aus dem erfindungsgemäßen Werkstoff wird im Sinne des erfindungsgemäßen Verfahrens so vorgegangen, dass zuerst ein Halbzeug bzw. Vormaterial aus dem Werkstoff bereitgestellt wird. Bei dem Halbzeug handelt es sich um ein kostengünstiges, gegossenes HalbzeugFor the production of a gas turbine component from the material according to the invention, the procedure according to the invention is such that first of all a semifinished product or starting material is provided from the material. The semifinished product is a low-cost, cast semi-finished product
  • Anschließend wird im Sinne des erfindungsgemäßen Verfahrens das gegossene Halbzeug aus dem erfindungsgemäßen γ-TiAl-Basis-Legierungswerkstoff durch Schmieden umgeformt, nämlich bei einer Umformtemperatur bzw. Schmiedetemperatur, die zwischen Te-50K und Tα+100K liegt. Dabei wird mit einer Umformgeschwindigkeit von mindestens 1 s- 1 geschmiedet. In zu bevorzugender Weiterbildung wird das Halbzeug dabei vor dem Schmieden wärmedämmend beschichtet.Subsequently, in the context of the method according to the invention, the cast semifinished product from the γ-TiAl base alloy material according to the invention is formed by forging, namely at a forming temperature or forging temperature which is between T e -50K and T α + 100K. This is done with a forming speed of at least 1 s - 1 forged. In a preferred development, the semifinished product is thermally coated before forging.
  • Im Anschluss an das Schmieden erfolgt vorzugsweise eine Wärmebehandlung des herzustellenden Bauteils.After forging, preferably a heat treatment of the component to be produced takes place.
  • Dann, wenn gemäß Fig. 1 als Gasturbinenbauteil eine Laufschaufel 10 für einen Verdichter eines Flugtriebwerks hergestellt werden soll, wird beim erfindungsgemäßen Verfahren vorzugsweise so vorgegangen, dass im Bereich eines Schaufelblatts 11 zur Bereitstellung einer gröberen Mikrostruktur mit hoher Kriechfestigkeit einfach geschmiedet und im Bereich eines Schaufelfußes 12 zur Bereitstellung einer feineren Mikrostruktur mit hoher Duktilität mehrfach geschmiedet wird, wobei sich an das einfache Schmieden sowie an das mehrfache Schmieden vorzugsweise eine Wärmebehandlung anschließt.Then, if according to Fig. 1 When a turbine blade 10 for a compressor of an aircraft engine is to be produced as a gas turbine component, in the method according to the invention, the procedure is preferably that in the region of a blade 11 to provide a coarser microstructure with high creep strength simply forged and in the region of a blade root 12 to provide a finer microstructure with high ductility is forged several times, with the simple forging and the multiple forging preferably followed by a heat treatment.
  • Erfindungsgemäße Gasturbinenbauteile sind mit Hilfe des erfindungsgemäßen Verfahrens aus dem angegebenen Werkstoff gefertigt. Vorzugsweise handelt es sich bei den erfindungsgemäßen Gasturbinenbauteilen um Verdichterbauteile, so z. B. um Laufschaufeln eines Verdichters eines Flugtriebwerks, oder um TurbinenbauteileGas turbine components according to the invention are manufactured from the specified material with the aid of the method according to the invention. Preferably, the gas turbine components according to the invention to compressor components, such. As to blades of a compressor of an aircraft engine, or turbine components
  • Claims (5)

    1. Method for producing a gas turbine component, the method comprising the following steps:
      a) providing a cast semi-finished product made of a titanium aluminium base alloy material, the material comprising at least titanium and aluminium, wherein
      - in the range of room temperature, said material contains the β/B2-Ti phase, the α2-Ti3Al phase and the γ-TiAl phase, with a proportion of the β/B2-Ti phase amounting to no more than 5 vol%,
      - in the range of the eutectoid temperature, said material contains the β/B2-Ti phase, the α2-Ti3Al phase and the γ-TiAl phase, with a proportion of the β/B2-Ti phase amounting to at least 10 vol%, and
      - the material has the following composition:
      -- 42 to 45 at% of aluminium,
      -- 3 to 8 at% of niobium,
      -- 0.2 to 3 at% of molybdenum and/or manganese,
      -- 0.1 to 1 at% of boron and/or carbon and/or silicon
      -- a rest of titanium, and
      b) forging the semi-finished product made of said material to obtain the component at a forming temperature of between Te-50K and Ta+100K, with Te being the eutectoid temperature of the material and Ta being the alpha transus temperature of the material.
    2. Method according to claim 1,
      characterised in that
      forging is carried out at a forming speed of at least 1s-1.
    3. Method according to claim 1 or 2,
      characterised in that
      a heat treatment is carried out after forging.
    4. Gas turbine component, produced by a method according to one or more of claims 1 to 3.
    5. Gas turbine component according to claim 4,
      characterised in that
      said gas turbine component is a blade which is single-forged in the region of a blade vane to provide a coarser microstructure having a high creep resistance, and which is multi-forged in the region of a blade root to provide a finer microstructure having a high ductility.
    EP08841961.9A 2007-10-27 2008-10-18 Material for a gas turbine component, method for producing a gas turbine component and gas turbine component Active EP2227571B1 (en)

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    JP (1) JP5926886B2 (en)
    CA (1) CA2703906C (en)
    DE (1) DE102007051499A1 (en)
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    US8876992B2 (en) * 2010-08-30 2014-11-04 United Technologies Corporation Process and system for fabricating gamma TiAl turbine engine components
    WO2012041276A2 (en) * 2010-09-22 2012-04-05 Mtu Aero Engines Gmbh Heat-resistant tial alloy
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    US8888461B2 (en) 2014-11-18

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