EP2227571A2 - 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 componentInfo
- Publication number
- EP2227571A2 EP2227571A2 EP08841961A EP08841961A EP2227571A2 EP 2227571 A2 EP2227571 A2 EP 2227571A2 EP 08841961 A EP08841961 A EP 08841961A EP 08841961 A EP08841961 A EP 08841961A EP 2227571 A2 EP2227571 A2 EP 2227571A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- phase
- gas turbine
- temperature
- turbine component
- material according
- 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
Links
- 239000000463 material Substances 0.000 title claims abstract description 41
- 238000004519 manufacturing process Methods 0.000 title claims description 12
- 239000010936 titanium Substances 0.000 claims abstract description 38
- 229910006281 γ-TiAl Inorganic materials 0.000 claims abstract description 17
- 239000000956 alloy Substances 0.000 claims abstract description 13
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 6
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000005242 forging Methods 0.000 claims description 21
- 238000000034 method Methods 0.000 claims description 13
- 239000011265 semifinished product Substances 0.000 claims description 11
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 4
- 229910052796 boron Inorganic materials 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 4
- 229910052750 molybdenum Inorganic materials 0.000 claims description 4
- 239000011733 molybdenum Substances 0.000 claims description 4
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 239000010703 silicon Substances 0.000 claims description 4
- 238000010438 heat treatment Methods 0.000 claims description 3
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 3
- 229910052758 niobium Inorganic materials 0.000 claims description 3
- 239000010955 niobium Substances 0.000 claims description 3
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims 2
- 239000000470 constituent Substances 0.000 claims 1
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 abstract description 3
- 229910021325 alpha 2-Ti3Al Inorganic materials 0.000 abstract 2
- 239000004411 aluminium Substances 0.000 abstract 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 239000007858 starting material Substances 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 229910010038 TiAl Inorganic materials 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 238000010275 isothermal forging Methods 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
-
- 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
Definitions
- the proportion of cubic body-centered ß / B2-Ti phase in the thermodynamic equilibrium of the material according to the invention is less than 5 vol .-% in the room temperature. In the area of the eutectoid temperature, the proportion of cubic body-centered ⁇ / B2-Ti phase is greater than 10% by volume.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Forging (AREA)
Abstract
Description
Werkstoff für ein Gasturbinenbauteil, Verfahren zur Herstellung eines Gasturbinenbauteils sowie Gasturbinenbauteil Material for a gas turbine component, method for producing a gas turbine component and gas turbine component
Die Erfindung betrifft einen Werkstoff für ein Gasturbinenbauteil nach dem Oberbegriff des Anspruchs 1. Des Weiteren betrifft die Erfindung ein Verfahren zur Herstellung eines Gasturbinenbauteils nach dem Oberbegriff des Anspruchs 9 sowie ein Gasturbinenbauteil nach dem Oberbegriff des Anspruchs 13.The invention relates to a material for a gas turbine component according to the preamble of claim 1. Furthermore, the invention relates to a method for producing a gas turbine component according to the preamble of claim 9 and a gas turbine component according to the preamble of claim 13.
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.
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, with the forging of such γ-TiAl base materials being used. 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 neuen Werkstoffs zur Herstellung von Gasturbinenbauteilen. Dieses Verfahren soll eine verbesserte Prozesssicherheit und Prozessstabilität unter reduzierten Herstellkosten gewährleisten.Thus, there is a need for an adaptive forging process using a new 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, einen neuartigen Werkstoff für ein Gasturbinenbauteil, ein neuartiges Verfahren zur Herstellung eines Gasturbinenbauteils sowie ein neuartiges Gasturbinenbauteil zu schaffen.On this basis, the present invention based on the problem of creating a novel material for a gas turbine component, a novel method for producing a gas turbine component and a novel gas turbine component.
Dieses Problem wird durch einen Werkstoff gemäß Anspruch 1 gelöst. Erfindungsgemäß weist derselbe a) im Bereich der Raumtemperatur die Phase ß/B2-Ti, die Phase Ot2-Ti3Al und die Phase γ-TiAl mit einem Anteil der ß/B2-Ti-Phase von maximal 5 Vol.-% auf; b) im Bereich der eutektoiden Temperatur die Phase ß/B2-Ti, die Phase Ci2-Ti3Al und die Phase γ-TiAl mit einem Anteil der ß-Ti-Phase von minimal 10 Vol.-% auf.This problem is solved by a material according to claim 1. According to the invention, the same a) in the region of room temperature, the phase ß / B2-Ti, the phase Ot 2 -Ti 3 Al and the phase γ-TiAl with a proportion of ß / B2-Ti phase of not more than 5 vol .-% ; b) in the eutectoid temperature the phase ß / B2-Ti, the phase Ci 2 -Ti 3 Al and the phase γ-TiAl with a proportion of ß-Ti phase of at least 10 vol .-% on.
Der erfindungsgemäße Werkstoff, bei welchem es sich um einen γ-TiAl-Basis Legierungswerkstoff handelt, erlaubt ein Schmieden innerhalb eines größeren Temperaturintervalls. Zum Schmieden kann als Vormaterial ein Gussmaterial verwendet werden, sodass auf teures Strangpressmaterial verzichtet werden kann.The material according to the invention, which is a γ-TiAl-based alloy material, allows forging within a larger temperature interval. Forging can be used as a starting material, a casting material, so that can be dispensed with expensive extruded material.
Das erfindungsgemäße Verfahren zur Herstellung eines Gasturbinenbauteils ist in Anspruch 9 und das erfindungsgemäße Gasturbinenbauteil ist in Anspruch 13 definiert. Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausfuhrungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:The inventive method for producing a gas turbine component is in claim 9 and the gas turbine component according to the invention is defined in claim 13. Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Exemplary embodiments of the invention will be explained in more detail with reference to the drawing, without being limited thereto. Showing:
Fig. 1 eine stark schematisierte Darstellung einer aus dem erfindungsgemäßen Werkstoff nach dem erfindungsgemäßen Verfahren hergestellten Schaufel einer Gasturbine.Fig. 1 is a highly schematic representation of a produced from the material according to the invention according to the invention blade of a gas turbine.
Die hier vorliegende Erfindung betrifft einen neuen Werkstoff für ein Gasturbinenbauteil, nämlich einen Werkstoff auf Basis einer Titan-Aluminium-Legierung. Der erfindungsgemäße Werkstoff umfasst sowohl im Bereich der Raumtemperatur als auch im Bereich der sogenannten eutektoiden Temperatur mehrere Phasen.The present invention relates to a new material for a gas turbine component, namely a material based on a titanium-aluminum alloy. The material according to the invention 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 erfindungsgemäße TiAl-Basis- Legierungswerkstoff die Phase ß/B2-Ti, die Phase (X2-Ti3Al und die Phase γ-TiAl auf, wobei der Anteil der ß/B2-Ti-Phase bei Raumtemperatur höchstens bzw. maximal 5 Vol.-% beträgt. Ln Bereich der eutektoiden Temperatur weist der erfindungsgemäße TiAl-Basis- Legierungswerkstoff die Phase ß/B2-Ti, die Phase Ct2-Ti3 Al und die Phase γ-TiAl auf, wobei der Anteil der ß/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 according to the invention has the phase β / B2-Ti, the phase (X 2 -Ti 3 Al and the phase γ-TiAl, wherein the proportion of ß / B2-Ti phase at room temperature In the region of the eutectoid temperature, the TiAl-based alloy material according to the invention has the phase β / B2-Ti, the phase Ct 2 -Ti 3 Al and the phase γ-TiAl, where the Proportion of ß / B2-Ti phase in the eutectoid temperature range is at least or minimum 10 vol .-%.
Bei dem erfindungsgemäßen 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 erfindungsgemäßen Werkstoffs liegt vorzugsweise zwischen Te-50K und Tα+100K, wobei Te die eutektoide Temperatur des Werkstoffs und Tα die Alpha-Transus-Temperatur des Werkstoffs ist.The material according to the invention is accordingly 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 according to the invention is preferably 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 Tem- peratur und der Raumtemperatur befinden sich die Phasen ß/B2-Ti, (X2Ti3Al 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 temperature and the room temperature are the phases ß / B2-Ti, (X 2 Ti 3 Al and γ-TiAl in the thermodynamic equilibrium.
Der Anteil der kubisch raumzentrierten ß/B2-Ti-Phase im thermodynamischen Gleichgewicht des erfindungsgemäßen Werkstoffs ist im Bereich der Raumtemperatur kleiner als 5 Vol.-%. Im Bereich der eutektoiden Temperatur ist der Anteil der kubisch raumzentrierten ß/B2-Ti-Phase größer als 10 Vol.-%.The proportion of cubic body-centered ß / B2-Ti phase in the thermodynamic equilibrium of the material according to the invention is less than 5 vol .-% in the room temperature. In the area of the eutectoid temperature, the proportion of cubic body-centered β / B2-Ti phase is greater than 10% by volume.
Der erfindungsgemäße γ-TiAl-Basis-Legierungswerkstoff weist neben Titan und Aluminium weiterhin Niob, Molybdän und/oder Mangan sowie Bor und/oder Kohlenstoff und / o- der Silizium auf.In addition to titanium and aluminum, the γ-TiAl-based alloy material according to the invention also contains niobium, molybdenum and / or manganese as well as boron and / or carbon and / or silicon.
Vorzugsweise weist der Titan- Aluminium-Basis-Legierungswerkstoff folgende Zusammensetzung auf:Preferably, the titanium-aluminum-base alloy material has the following composition:
- 42 bis 45 At.-% Aluminium, - 3 bis 8 At.-% Niob,42 to 45 at.% Aluminum, 3 to 8 at.% Niobium,
- 0,2 bis 3 At. -% Molybdän und/oder Mangan,- 0.2 to 3 at. % Molybdenum and / or manganese,
- 0,1 bis 1 At-% , bevorzugt 0,1 bis 0,5 At.-%, Bor und/oder Kohlenstoff und / oder Silizium,0.1 to 1 at%, preferably 0.1 to 0.5 at.%, Boron and / or carbon and / or silicon,
- im Rest Titan.- 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 erfindungsgemäßen Werkstoff bereitgestellt wird. Bei dem Halbzeug kann es sich um ein kostengünstiges, gegossenes Halbzeug handeln. Es kann auch vorgesehen sein, dass es sich bei dem Halbzeug um ein primär umgeformtes Bauteil handelt.For 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 according to the invention. The semi-finished product can be a cost-effective, cast semi-finished product. It can also be provided that the semifinished product is a primary formed component.
Anschließend wird im Sinne des erfindungsgemäßen Verfahrens das 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 m/s 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 semifinished product from the γ-TiAl-based alloy material according to the invention is formed by forging, namely at a forming temperature or forging temperature, the between T e -50K and T α + 100K. It is forged at a forming speed of at least 1 m / s. 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.If, as shown in FIG. 1, a blade 10 for a compressor of an aircraft engine is to be produced as a gas turbine component, the process according to the invention preferably proceeds in the area of an airfoil 11 to provide a coarser microstructure with high creep strength and in the area of a blade root 12 is forged for providing a finer microstructure with high ductility, preferably followed by a heat treatment to the simple forging and to the multiple forging.
Erfmdungsgemäße Gasturbinenbauteile sind mit Hilfe des erfindungsgemäßen Verfahrens aus dem erfindungsgemäßen Werkstoff gefertigt. Vorzugsweise handelt es sich bei den erfindungsgemäßen Gasturbinenbauteilen um Verdichterbauteile, so z. B. um Laufschaufeln eines Verdichters eines Flugtriebwerks, oder um Turbinenbauteile Gas turbine components according to the invention are manufactured from the material according to the invention 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
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PL08841961T PL2227571T3 (en) | 2007-10-27 | 2008-10-18 | Material for a gas turbine component, method for producing a gas turbine component and gas turbine component |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102007051499A DE102007051499A1 (en) | 2007-10-27 | 2007-10-27 | Material for a gas turbine component, method for producing a gas turbine component and gas turbine component |
| PCT/DE2008/001702 WO2009052792A2 (en) | 2007-10-27 | 2008-10-18 | Material for a gas turbine component, method for producing a gas turbine component and gas turbine component |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP2227571A2 true EP2227571A2 (en) | 2010-09-15 |
| EP2227571B1 EP2227571B1 (en) | 2015-09-02 |
Family
ID=40227637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP08841961.9A Not-in-force EP2227571B1 (en) | 2007-10-27 | 2008-10-18 | Material for a gas turbine component, method for producing a gas turbine component and gas turbine component |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US8888461B2 (en) |
| EP (1) | EP2227571B1 (en) |
| JP (1) | JP5926886B2 (en) |
| CA (1) | CA2703906C (en) |
| DE (1) | DE102007051499A1 (en) |
| ES (1) | ES2548243T3 (en) |
| PL (1) | PL2227571T3 (en) |
| WO (1) | WO2009052792A2 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AT509768B1 (en) * | 2010-05-12 | 2012-04-15 | Boehler Schmiedetechnik Gmbh & Co Kg | METHOD FOR PRODUCING A COMPONENT AND COMPONENTS FROM A TITANIUM ALUMINUM BASE ALLOY |
| 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 |
| ES2583756T3 (en) * | 2011-04-01 | 2016-09-22 | MTU Aero Engines AG | Blade arrangement for a turbomachine |
| DE102011110740B4 (en) * | 2011-08-11 | 2017-01-19 | MTU Aero Engines AG | Process for producing forged TiAl components |
| US20130084190A1 (en) * | 2011-09-30 | 2013-04-04 | General Electric Company | Titanium aluminide articles with improved surface finish and methods for their manufacture |
| EP2620517A1 (en) * | 2012-01-25 | 2013-07-31 | MTU Aero Engines GmbH | Heat-resistant TiAl alloy |
| ES2532582T3 (en) * | 2012-08-09 | 2015-03-30 | Mtu Aero Engines Gmbh | Method for manufacturing a TiAl blade crown segment for a gas turbine, as well as a corresponding blade crown segment |
| FR2997884B3 (en) * | 2012-11-09 | 2015-06-26 | Mecachrome France | METHOD AND DEVICE FOR MANUFACTURING TURBINE BLADES |
| EP2762684B1 (en) * | 2013-01-30 | 2021-03-03 | MTU Aero Engines AG | Seal mount made from titanium aluminide for a flow machine |
| EP2969319A4 (en) * | 2013-03-15 | 2016-11-09 | United Technologies Corp | METHOD FOR MANUFACTURING TITANIUM GAMMA ALUMINUM TURBINE COMPONENT |
| ES2747155T3 (en) | 2013-09-20 | 2020-03-10 | MTU Aero Engines AG | Creep resistant TiAl alloy |
| DE102013020460A1 (en) | 2013-12-06 | 2015-06-11 | Hanseatische Waren Handelsgesellschaft Mbh & Co. Kg | Process for the production of TiAl components |
| US10240608B2 (en) | 2014-02-05 | 2019-03-26 | Borgwarner Inc. | TiAl alloy, in particular for turbocharger applications, turbocharger component, turbocharger and method for producing the TiAl alloy |
| US9963977B2 (en) | 2014-09-29 | 2018-05-08 | United Technologies Corporation | Advanced gamma TiAl components |
| DE102015103422B3 (en) * | 2015-03-09 | 2016-07-14 | LEISTRITZ Turbinentechnik GmbH | Process for producing a heavy-duty component of an alpha + gamma titanium aluminide alloy for piston engines and gas turbines, in particular aircraft engines |
| 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 |
| RU2614294C1 (en) * | 2016-04-04 | 2017-03-24 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Рыбинский государственный авиационный технический университет имени П.А. Соловьева" | Method of blades forgings manufacturing from titanium alloys |
| EP3249064A1 (en) | 2016-05-23 | 2017-11-29 | MTU Aero Engines GmbH | Additive manufacture of high temperature components from tial |
| ES2891724T3 (en) | 2016-07-12 | 2022-01-31 | MTU Aero Engines AG | High temperature resistant TiAl alloy, method for manufacturing a corresponding TiAl alloy component and corresponding TiAl alloy component |
| 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 |
| CN112410698B (en) * | 2020-11-03 | 2021-11-02 | 中国航发北京航空材料研究院 | A method for controlling the uniformity of multi-layer structure of three-phase Ti2AlNb alloy |
| US20240043978A1 (en) | 2021-04-16 | 2024-02-08 | Kabushiki Kaisha Kobe Seiko Sho (Kobe Steel, Ltd.) | Tial alloy for forging, tial alloy material, and method for producing tial alloy material |
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| JP2546551B2 (en) * | 1991-01-31 | 1996-10-23 | 新日本製鐵株式会社 | γ and β two-phase TiAl-based intermetallic alloy and method for producing the same |
| JPH06116692A (en) * | 1992-10-05 | 1994-04-26 | Honda Motor Co Ltd | TiAl intermetallic compound excellent in high temperature strength and method for producing the same |
| DE19581384C2 (en) * | 1994-10-25 | 1999-03-11 | Mitsubishi Heavy Ind Ltd | Titanium-aluminum alloy based on an intermetallic compound |
| USH1659H (en) * | 1995-05-08 | 1997-07-01 | The United States Of America As Represented By The Secretary Of The Air Force | Method for heat treating titanium aluminide alloys |
| JP3388970B2 (en) * | 1995-12-26 | 2003-03-24 | 三菱重工業株式会社 | TiAl intermetallic compound based alloy |
| JP3492118B2 (en) * | 1996-10-28 | 2004-02-03 | 三菱重工業株式会社 | TiAl intermetallic compound based alloy |
| US6174387B1 (en) * | 1998-09-14 | 2001-01-16 | Alliedsignal, Inc. | Creep resistant gamma titanium aluminide alloy |
| DE102004056582B4 (en) * | 2004-11-23 | 2008-06-26 | Gkss-Forschungszentrum Geesthacht Gmbh | Alloy based on titanium aluminides |
-
2007
- 2007-10-27 DE DE102007051499A patent/DE102007051499A1/en not_active Withdrawn
-
2008
- 2008-10-18 JP JP2010530269A patent/JP5926886B2/en not_active Expired - Fee Related
- 2008-10-18 PL PL08841961T patent/PL2227571T3/en unknown
- 2008-10-18 ES ES08841961.9T patent/ES2548243T3/en active Active
- 2008-10-18 CA CA2703906A patent/CA2703906C/en active Active
- 2008-10-18 WO PCT/DE2008/001702 patent/WO2009052792A2/en not_active Ceased
- 2008-10-18 EP EP08841961.9A patent/EP2227571B1/en not_active Not-in-force
- 2008-10-18 US US12/739,929 patent/US8888461B2/en active Active
Non-Patent Citations (1)
| Title |
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| See references of WO2009052792A2 * |
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| WO2009052792A9 (en) | 2009-11-05 |
| WO2009052792A8 (en) | 2009-07-30 |
| CA2703906C (en) | 2016-07-19 |
| JP2011502213A (en) | 2011-01-20 |
| US20110189026A1 (en) | 2011-08-04 |
| CA2703906A1 (en) | 2009-04-30 |
| JP5926886B2 (en) | 2016-05-25 |
| DE102007051499A1 (en) | 2009-04-30 |
| PL2227571T3 (en) | 2016-02-29 |
| WO2009052792A3 (en) | 2009-09-03 |
| WO2009052792A2 (en) | 2009-04-30 |
| US8888461B2 (en) | 2014-11-18 |
| ES2548243T3 (en) | 2015-10-15 |
| EP2227571B1 (en) | 2015-09-02 |
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