EP2788518B1 - Rhenium free or low rhenium nickel base superalloy - Google Patents

Rhenium free or low rhenium nickel base superalloy Download PDF

Info

Publication number
EP2788518B1
EP2788518B1 EP12787636.5A EP12787636A EP2788518B1 EP 2788518 B1 EP2788518 B1 EP 2788518B1 EP 12787636 A EP12787636 A EP 12787636A EP 2788518 B1 EP2788518 B1 EP 2788518B1
Authority
EP
European Patent Office
Prior art keywords
content
rhenium
weight
nickel
tungsten
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.)
Not-in-force
Application number
EP12787636.5A
Other languages
German (de)
French (fr)
Other versions
EP2788518A1 (en
Inventor
Robert F. Singer
Ernst Affeldt
Michael Weiss
Thomas GÖHLER
Ralf RETTIG
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2788518A1 publication Critical patent/EP2788518A1/en
Application granted granted Critical
Publication of EP2788518B1 publication Critical patent/EP2788518B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • 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
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
    • 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
    • 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
    • F05D2300/175—Superalloys
    • 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
    • F05D2300/177—Ni - Si alloys

Definitions

  • the present invention relates to a nickel-base superalloy with little or no rhenium content.
  • nickel-based superalloys are used, which can be used as single crystals or as directionally solidified alloys. These alloys have high strength due to their alloying components due to solid solution and / or precipitation or particle hardening.
  • nickel-based superalloys are optimized so that the particle hardening is maintained by the excretion of so-called ⁇ '-phases even at high temperatures and long periods of use.
  • nickel base superalloys such as CMSX-4, PWA-1484 or René N5.
  • Such alloys all contain a rhenium content of more than 3% by weight.
  • a nickel-base superalloy for gas turbine components which, in addition to nickel, contain chromium with a content of 7-9% by weight, titanium with a content of 0.5-1.5% by weight, molybdenum with a content of 5-7% by weight. 7% by weight, tungsten containing 0-1% by weight, tantalum containing 4-5% by weight, aluminum containing 5.5-5.6% by weight, cobalt containing 8-12% by weight, boron containing 0.01-0.02% by weight, zirconium containing 0.02-0.1% by weight, containing carbon from 0.05-0.15% by weight, hafnium at a level of 0-1.5% by weight.
  • nickel-base superalloy for gas turbine components which in addition to nickel molybdenum at a content of 2.0 wt .-%, tungsten with a content of 5.0 wt .-%, tantalum with a content of 6.3 wt .-% , Rhenium at a level of 2.0% by weight, aluminum at a level of 5.5% by weight, titanium at a level of 1.5% by weight, chromium at a level of 5.0% by weight. % and cobalt with a content of 10.0% by weight.
  • a nickel-based superalloy is proposed, the aluminum with a content of 4 to 6 wt .-%, cobalt with a content of 8 to 10 wt .-%, chromium containing 5 to 8 wt % Molybdenum, containing from 2 to 5.5% by weight, tantalum containing from 4 to 6% by weight, rhenium containing from 0 to 1.5% by weight, titanium having a content of Content of 3 to 5.5 wt .-% and tungsten with a content of 3.5 to 6 wt .-% and the balance nickel and unavoidable impurities.
  • the nickel-based superalloy may have an aluminum content of 4.5 to 5.5% by weight, a cobalt content of 8.5 to 9.5% by weight, a chromium content of 6 to 7, 5 wt .-%, a molybdenum content of 2 to 4 wt -%, a tantalum content from 4 to 5.5% by weight, a rhenium content of 0 to 1% by weight, a titanium content of 3.5 to 5.5% by weight and a tungsten content of 4 to 5, 5 wt .-% have.
  • the rest is again formed by nickel and unavoidable impurities.
  • a nickel base superalloy comprising aluminum at a content of 4.5 to 5.5% by weight, cobalt at a content of 8.5 to 9.5% by weight, chromium with a content of 6 to 7.5% by weight, tantalum with a content of 6 to 8% by weight, rhenium with a content of 0 to 2% by weight, titanium with a content of 1.5 to 3 Wt .-% and tungsten with a content of 6 to 8 wt .-% and the remainder comprises nickel and unavoidable impurities.
  • Such alloys can be used in various forms, for example as a directionally solidified alloy or as single crystals for components in gas turbines and in particular aircraft engines.
  • the alloys for turbine blades and in particular blades of low-pressure turbines can be used.
  • the present invention can be realized in particular by alloys having the following compositions: Elemental proportion [wt .-%], balance nickel Short-Bez. al Co Cr Not a word re Ta Ti W Alloy 1 5 9 7 2.5 1 5 4.25 4.5 Alloy 2 5 9 6.5 3.5 1 5 3.75 4.5 Alloy 3 5 9 6.5 3.5 0 4.5 4.5 5 Alloy 4 5 9 6.5 0 2 6 1.5 8th Alloy 5 5 9 6.5 0 1.5 7 2 7 Alloy 6 5 9 6.5 0 1 8th 3 6
  • the alloys 4 to 6 are better castable or heat treatable compared to the alloys 1 to 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

HINTERGRUND DER ERFINDUNGBACKGROUND OF THE INVENTION GEBIET DER ERFINDUNGFIELD OF THE INVENTION

Die vorliegende Erfindung betrifft eine Nickel-Basis-Superlegierung mit geringem oder keinem Rheniumgehalt.The present invention relates to a nickel-base superalloy with little or no rhenium content.

STAND DER TECHNIKSTATE OF THE ART

In Gasturbinen, wie stationären Gastturbinen zur Stromerzeugung oder Flugtriebwerken, herrschen harte Einsatzbedingungen für die eingesetzten Werkstoffe, da die Werkstoffe, insbesondere für die Laufschaufeln hohen mechanischen Belastungen und zugleich hohen Temperaturen ausgesetzt sind, sodass neben hohen Festigkeiten eine ausreichend große Phasenstabilität sowie Kriech- und Oxidationsbeständigkeit des Werkstoffs erforderlich ist.In gas turbines, such as stationary gas turbines for power generation or aircraft engines, there are harsh operating conditions for the materials used, since the materials, in particular for the blades high mechanical loads and high temperatures are exposed at the same time so high strength in addition to sufficiently high phase stability and creep and oxidation resistance of the material is required.

Um diesen Anforderungen gerecht zu werden, werden beispielsweise Nickel-Basis-Superlegierungen eingesetzt, die als Einkristalle oder als gerichtet erstarrte Legierungen zum Einsatz kommen können. Diese Legierungen weisen durch ihre Legierungsbestandteile aufgrund der Mischkristall- und/oder Ausscheidungs- oder Teilchenhärtung eine hohe Festigkeit auf. Darüber hinaus sind derartige Nickel-Basis-Superlegierungen dahingehend optimiert, dass die Teilchenhärtung durch die Ausscheidung von sogenannten γ'-Phasen auch bei hohen Temperaturen und langen Einsatzzeiten erhalten bleibt.To meet these requirements, for example, nickel-based superalloys are used, which can be used as single crystals or as directionally solidified alloys. These alloys have high strength due to their alloying components due to solid solution and / or precipitation or particle hardening. In addition, such nickel-based superalloys are optimized so that the particle hardening is maintained by the excretion of so-called γ'-phases even at high temperatures and long periods of use.

Als Beispiele für derartige Legierungen können Nickel-Basis-Superlegierungen, wie CMSX-4, PWA-1484 oder René N5 genannt werden. Derartige Legierungen enthalten alle einen Rheniumanteil von mehr als 3 Gew.-%.As examples of such alloys may be mentioned nickel base superalloys such as CMSX-4, PWA-1484 or René N5. Such alloys all contain a rhenium content of more than 3% by weight.

Durch den hohen Rheniumanteil sind jedoch die Materialkosten sehr hoch, sodass es bereits Überlegungen gegeben hat, Nickel-Basis-Superlegierungen zu entwickeln, die einen geringen oder gar keinen Rheniumanteil aufweisen. Beispiele hierfür sind in der EP 2 305 848 A1 , EP 2 218 798 A2 , WO 2009/032578 und WO 2009/032579 beschrieben.Due to the high rhenium content, however, the material costs are very high, so that it has already been considered to develop nickel-base superalloys that have little or no rhenium content. Examples are in the EP 2 305 848 A1 . EP 2 218 798 A2 . WO 2009/032578 and WO 2009/032579 described.

Aus der US 6 054 096 A ist eine Nickelbasis-Superlegierung für Gasturbinenbauteile bekannt, welche neben Nickel Kobalt mit einem Gehalt von 10,0 Gew.-%, Chrom mit einem Gehalt von 5,2 Gew.-%, Molybdän mit einem Gehalt von 2,04 Gew.-%, Wolfram mit einem Gehalt von 7.0 Gew.-%, Tantal mit einem Gehalt von 5,1 Gew.-%, Aluminium mit einem Gehalt von 5,6 Gew.-%, daneben Hafnium mit einem Gehalt von 0.1 Gew.-% und Vanadin mit einem Gehalt von 0,4 Gew.-°/o, sowie Titan mit einem Gehalt von 1,52 Gew.-% umfasst.From the US 6 054 096 A discloses a nickel base superalloy for gas turbine components which, in addition to nickel, contains cobalt containing 10.0% by weight, chromium containing 5.2% by weight, molybdenum containing 2.04% by weight. Tungsten with a content of 7.0% by weight, tantalum with a content of 5.1% by weight, aluminum with a content of 5.6% by weight, besides hafnium with a content of 0.1% by weight and Vanadin with a content of 0.4% by weight, and titanium with a content of 1.52 wt .-% comprises.

Aus der EP 2 333 121 A ist zudem eine Nickelbasis-Superlegierung für Gasturbinenbauteile bekannt, welche neben Nickel Chrom mit einem Gehalt von 7-9 Gew.-%, Titan mit einem Gehalt von 0,5-1,5 Gew.-%, Molybdän mit einem Gehalt von 5-7 Gew.-%, Wolfram mit einem Gehalt von 0-1 Gew.-%, Tantal mit einem Gehalt von 4-5 Gew.-%, Aluminium mit einem Gehalt von 5,5-5,6 Gew.-%, Kobalt mit einem Gehalt von 8-12 Gew.-%, Bor mit einem Gehalt von 0,01-0,02 Gew.-%, Zirkonium mit einem Gehalt von 0,02-0,1 Gew.-%, Kohlenstoff mit einem Gehalt von 0,05-0,15 Gew.-%, Hafnium mit einem Gehalt von 0-1,5 Gew.-% umfasst.From the EP 2 333 121 A In addition, a nickel-base superalloy is known for gas turbine components which, in addition to nickel, contain chromium with a content of 7-9% by weight, titanium with a content of 0.5-1.5% by weight, molybdenum with a content of 5-7% by weight. 7% by weight, tungsten containing 0-1% by weight, tantalum containing 4-5% by weight, aluminum containing 5.5-5.6% by weight, cobalt containing 8-12% by weight, boron containing 0.01-0.02% by weight, zirconium containing 0.02-0.1% by weight, containing carbon from 0.05-0.15% by weight, hafnium at a level of 0-1.5% by weight.

Ferner ist aus der EP 0 150 917 A2 ist eine Nickelbasis-Superlegierung für Gasturbinenbauteile bekannt, welche neben Nickel Molybdän mit einem Gehalt von 2,0 Gew.-%, Wolfram mit einem Gehalt von 5,0 Gew.-%, Tantal mit einem Gehalt von 6,3 Gew.-%, Rhenium mit einem Gehalt von 2,0 Gew.-%, Aluminium mit einem Gehalt von 5,5 Gew.-%, Titan mit einem Gehalt von 1,5 Gew.-%, Chrom mit einem Gehalt von 5,0 Gew.-% und Kobalt mit einem Geahlt von 10,0 Gew.-% umfasst.Furthermore, from the EP 0 150 917 A2 is a nickel-base superalloy for gas turbine components is known, which in addition to nickel molybdenum at a content of 2.0 wt .-%, tungsten with a content of 5.0 wt .-%, tantalum with a content of 6.3 wt .-% , Rhenium at a level of 2.0% by weight, aluminum at a level of 5.5% by weight, titanium at a level of 1.5% by weight, chromium at a level of 5.0% by weight. % and cobalt with a content of 10.0% by weight.

OFFENBARUNG DER ERFINDUNGDISCLOSURE OF THE INVENTION AUFGABE DER ERFINDUNGOBJECT OF THE INVENTION

Obwohl im Stand der Technik bereits Nickel-Basis-Superlegierungen mit geringem oder gar keinem Rheniumanteil beschrieben sind, besteht weiterhin ein Bedarf an Rhenium-freien bzw. Rhenium-reduzierten Nickel-Basis-Superlegierungen, bei denen das Eigenschaftsprofil weiter optimiert ist. Insbesondere besteht ein Bedarf dahingehend, eine Legierung bereitzustellen, die auch bei hohen Temperaturen einen großen Volumenanteil an Ausscheidungen aufweist, um auch bei hohen Einsatztemperaturen die notwendige Festigkeit und insbesondere Kriechfestigkeit aufzuweisen.Although nickel-based superalloys with little or no rhenium content have already been described in the prior art, there continues to be a need for rhenium-free or rhenium-reduced nickel-based superalloys in which the property profile is further optimized. In particular, there is a need to provide an alloy having a high volume fraction of precipitates even at high temperatures even at high operating temperatures to have the necessary strength and especially creep resistance.

TECHNISCHE LÖSUNGTECHNICAL SOLUTION

Diese Aufgabe wird gelöst durch eine Nickel-Basis-Superlegierung gemäß dem Anspruch 1 sowie durch eine Nickel-Basis-Superlegierung gemäß dem Anspruch 3 . Vorteilhafte Ausgestaltungen sind Gegenstand der abhängigen Ansprüche.This object is achieved by a nickel-based superalloy according to claim 1 and by a nickel-based superalloy according to claim 3. Advantageous embodiments are the subject of the dependent claims.

Gemäß der vorliegenden Erfindung wird somit eine Nickel-Basis-Superlegierung vorgeschlagen, die Aluminium mit einem Gehalt von 4 bis 6 Gew.-%, Kobalt mit einem Gehalt von 8 bis 10 Gew.-%, Chrom mit einem Gehalt von 5 bis 8 Gew.-%, Molybdän mit einem Gehalt von 2 bis 5,5 Gew.-%, Tantal mit einem Gehalt von 4 bis 6 Gew,-%, Rhenium mit einem Gehalt von 0 bis 1,5 Gew.-%, Titan mit einem Gehalt von 3 bis 5,5 Gew.-% und Wolfram mit einem Gehalt von 3,5 bis 6 Gew.-% sowie dem Rest Nickel und unvermeidbare Verunreinigungen umfasst.According to the present invention, therefore, a nickel-based superalloy is proposed, the aluminum with a content of 4 to 6 wt .-%, cobalt with a content of 8 to 10 wt .-%, chromium containing 5 to 8 wt % Molybdenum, containing from 2 to 5.5% by weight, tantalum containing from 4 to 6% by weight, rhenium containing from 0 to 1.5% by weight, titanium having a content of Content of 3 to 5.5 wt .-% and tungsten with a content of 3.5 to 6 wt .-% and the balance nickel and unavoidable impurities.

Nach einer weiteren Ausführungsform kann die Nickel-Basis-Superlegierung einen AluminiumGehalt von 4,5 bis 5,5 Gew.-%, einen Kobalt-Gehalt von 8,5 bis 9,5 Gew.-%, einen ChromGehalt von 6 bis 7,5 Gew.-%, einen Molybdän-Gehalt von 2 bis 4 Gew,-%, einen Tantal-Gehalt von 4 bis 5,5 Gew.-%, einen Rhenium-Gehalt von 0 bis 1 Gew.-%, einen Titan-Gehalt von 3,5 bis 5,5 Gew.-% und einen Wolfram-Gehalt von 4 bis 5,5 Gew.-% aufweisen. Der Rest wird wiederum durch Nickel und unvermeidbare Verunreinigungen gebildet.According to a further embodiment, the nickel-based superalloy may have an aluminum content of 4.5 to 5.5% by weight, a cobalt content of 8.5 to 9.5% by weight, a chromium content of 6 to 7, 5 wt .-%, a molybdenum content of 2 to 4 wt -%, a tantalum content from 4 to 5.5% by weight, a rhenium content of 0 to 1% by weight, a titanium content of 3.5 to 5.5% by weight and a tungsten content of 4 to 5, 5 wt .-% have. The rest is again formed by nickel and unavoidable impurities.

Gemäß der vorliegenden Erfindung wird außerdem eine Nickel-Basis-Superlegierung vorgeschlagen, die Aluminium mit einem Gehalt von 4,5 bis 5,5 Gew.-%, Kobalt mit einem Gehalt von 8,5 bis 9,5 Gew.-%, Chrom mit einem Gehalt von 6 bis 7,5 Gew.-%, Tantal mit einem Gehalt von 6 bis 8 Gew.-%, Rhenium mit einem Gehalt von 0 bis 2 Gew.-%, Titan mit einem Gehalt von 1,5 bis 3 Gew.-% und Wolfram mit einem Gehalt von 6 bis 8 Gew.-% sowie dem Rest Nickel und unvermeidbare Verunreinigungen umfasst.According to the present invention, there is also proposed a nickel base superalloy comprising aluminum at a content of 4.5 to 5.5% by weight, cobalt at a content of 8.5 to 9.5% by weight, chromium with a content of 6 to 7.5% by weight, tantalum with a content of 6 to 8% by weight, rhenium with a content of 0 to 2% by weight, titanium with a content of 1.5 to 3 Wt .-% and tungsten with a content of 6 to 8 wt .-% and the remainder comprises nickel and unavoidable impurities.

Derartige Legierungen können in unterschiedlichen Formen, beispielsweise als gerichtet erstarrte Legierung oder als Einkristalle für Bauteile in Gasturbinen und insbesondere Flugtriebwerken eingesetzt werden. Insbesondere können die Legierungen für Turbinenschaufeln und insbesondere Laufschaufeln von Niederdruckturbinen Verwendung finden.Such alloys can be used in various forms, for example as a directionally solidified alloy or as single crystals for components in gas turbines and in particular aircraft engines. In particular, the alloys for turbine blades and in particular blades of low-pressure turbines can be used.

AUSFÜHRUNGSBEISPIELEEMBODIMENTS

Die vorliegende Erfindung kann insbesondere durch Legierungen verwirklicht werden, die folgende Zusammensetzungen aufweist: Elementanteil [Gew.-%], Rest Nickel Kurz-Bez. Al Co Cr Mo Re Ta Ti W Legierung 1 5 9 7 2,5 1 5 4,25 4,5 Legierung 2 5 9 6,5 3,5 1 5 3,75 4,5 Legierung 3 5 9 6,5 3,5 0 4,5 4,5 5 Legierung 4 5 9 6,5 0 2 6 1,5 8 Legierung 5 5 9 6,5 0 1,5 7 2 7 Legierung 6 5 9 6,5 0 1 8 3 6 The present invention can be realized in particular by alloys having the following compositions: Elemental proportion [wt .-%], balance nickel Short-Bez. al Co Cr Not a word re Ta Ti W Alloy 1 5 9 7 2.5 1 5 4.25 4.5 Alloy 2 5 9 6.5 3.5 1 5 3.75 4.5 Alloy 3 5 9 6.5 3.5 0 4.5 4.5 5 Alloy 4 5 9 6.5 0 2 6 1.5 8th Alloy 5 5 9 6.5 0 1.5 7 2 7 Alloy 6 5 9 6.5 0 1 8th 3 6

Mit derartigen Legierungen wird erreicht, dass auch bei hohen Temperaturen, also z.B. Temperaturen im Einsatzbereich von Niederdruckturbinen eines Flugtriebwerk, ein hoher Ausscheidungsanteil vorliegt, sodass die Festigkeit und insbesondere Kriechfestigkeit erhöht ist. Gleichzeitig ist auch bei tiefen Temperaturen ein hoher Ausscheidungsanteil gegeben, sodass auch hier entsprechende Festigkeitswerte erreicht werden.With such alloys it is achieved that even at high temperatures, for example, temperatures in the field of application of low-pressure turbines of an aircraft engine, a high precipitation fraction is present, so that the strength and in particular creep resistance is increased. simultaneously Even at low temperatures, a high degree of precipitation is given, so that here, too, corresponding strength values are achieved.

Mit den vorgestellten Legierungen kann insbesondere erreicht werden, dass die Verteilungsverhältnisse von Wolfram und Molybdän zwischen den Ausscheidungen und der Matrix-Phase verbessert werden, was die Reduzierung des Rhenium-Anteils ermöglicht. Dadurch wird nicht nur erreicht, dass sich die Werkstoffkosten reduzieren, sondern auch die Dichte der Legierung wird reduziert, was für Bauteile im Flugtriebwerksbau von erheblicher Bedeutung ist, da das Triebwerksgewicht reduziert und der Wirkungsgrad erhöht werden kann.In particular, it can be achieved with the alloys presented that the distribution ratios of tungsten and molybdenum between the precipitates and the matrix phase are improved, which enables the reduction of the rhenium fraction. Not only does this reduce the cost of materials, it also reduces the density of the alloy, which is of considerable importance to aeroengine components because engine weight can be reduced and efficiency increased.

Die Legierungen 4 bis 6 sind im Vergleich zu den Legierungen 1 bis 3 besser gieß- bzw. wärmebehandelbar.The alloys 4 to 6 are better castable or heat treatable compared to the alloys 1 to 3.

Obwohl die vorliegende Erfindung anhand der Ausführungsbeispiele beschrieben ist, ist für den Fachmann klar, dass die Erfindung nicht auf diese Ausführungsbeispiele beschränkt ist, sondern lediglich durch den Umfang des Schutzbereichs der beigefügten Ansprüche beschränkt ist.Although the present invention has been described with reference to the embodiments, it will be understood by those skilled in the art that the invention is not limited to these embodiments, but is limited only by the scope of the scope of the appended claims.

Claims (4)

  1. A nickel-based superalloy comprising aluminum with a content of 4 to 6 wt%, cobalt with a content of 8 to 10 wt%, chromium with a content of 5 to 8 wt%, molybdenum with a content of 2 to 5.5 wt%, tantalum with a content of 4 to 6 wt%, rhenium with a content of 0 to 1.5 wt%, titanium with a content of 3 to 5.5 wt%, and tungsten with a content of 3.5 to 6 wt%, and the remainder nickel and unavoidable impurities.
  2. The nickel-based superalloy according to claim 1,
    characterized in that
    the alloy comprises aluminum with a content of 4.5 to 5.5 wt%, cobalt with a content of 8.5 to 9.5 wt%, chromium with a content of 6 to 7.5 wt%, molybdenum with a content of 2 to 4 wt%, tantalum with a content of 4 to 5.5 wt%, rhenium with a content of 0 to 1 wt%, titanium with a content of 3.5 to 5 wt%, and tungsten with a content of 4 to 5.5 wt%, and the remainder nickel and unavoidable impurities.
  3. A nickel-based superalloy comprising aluminum with a content of 4.5 to 5.5 wt%, cobalt with a content of 8.5 to 9.5 wt%, chromium with a content of 6 to 7.5 wt%, tantalum with a content of 6 to 8 wt%, rhenium with a content of 0 to 2 wt%, titanium with a content of 1.5 to 3 wt%, and tungsten with a content of 6 to 8 wt%, and the remainder nickel and unavoidable impurities.
  4. A component of a gas turbine, in particular an aircraft engine, preferably turbine blades for a low-pressure turbine, produced with an alloy according to any one of the preceding claims.
EP12787636.5A 2011-12-07 2012-10-17 Rhenium free or low rhenium nickel base superalloy Not-in-force EP2788518B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011120388 2011-12-07
PCT/DE2012/001009 WO2013083101A1 (en) 2011-12-07 2012-10-17 Rhenium-free or rhenium-reduced nickel-base superalloy

Publications (2)

Publication Number Publication Date
EP2788518A1 EP2788518A1 (en) 2014-10-15
EP2788518B1 true EP2788518B1 (en) 2018-04-25

Family

ID=47191456

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12787636.5A Not-in-force EP2788518B1 (en) 2011-12-07 2012-10-17 Rhenium free or low rhenium nickel base superalloy

Country Status (4)

Country Link
US (1) US9850765B2 (en)
EP (1) EP2788518B1 (en)
ES (1) ES2670877T3 (en)
WO (1) WO2013083101A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927336A1 (en) * 2014-04-04 2015-10-07 MTU Aero Engines GmbH Nickel base alloy with optimised matrix properties
ES2682362T3 (en) 2015-05-05 2018-09-20 MTU Aero Engines AG Super-alloy of rhenium-free nickel with low density
DE102016203724A1 (en) * 2016-03-08 2017-09-14 Siemens Aktiengesellschaft SX-nickel alloy with improved TMF properties, raw material and component

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6054096A (en) * 1982-12-27 2000-04-25 United Technologies Corporation Stable heat treatable nickel superalloy single crystal articles and compositions
US4765850A (en) * 1984-01-10 1988-08-23 Allied-Signal Inc. Single crystal nickel-base super alloy
WO1997038144A1 (en) * 1996-04-10 1997-10-16 The Penn State Research Foundation Improved superalloys with improved oxidation resistance and weldability
WO1999031365A1 (en) * 1997-12-15 1999-06-24 Hitachi, Ltd. Gas turbine for power generation, and combined power generation system
US20130230405A1 (en) 2007-08-31 2013-09-05 Kevin Swayne O'Hara Nickel base superalloy compositions being substantially free of rhenium and superalloy articles
US8876989B2 (en) 2007-08-31 2014-11-04 General Electric Company Low rhenium nickel base superalloy compositions and superalloy articles
US20090185944A1 (en) * 2008-01-21 2009-07-23 Honeywell International, Inc. Superalloy compositions with improved oxidation performance and gas turbine components made therefrom
US20100135846A1 (en) 2008-12-01 2010-06-03 United Technologies Corporation Lower cost high strength single crystal superalloys with reduced re and ru content
US20100254822A1 (en) * 2009-03-24 2010-10-07 Brian Thomas Hazel Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom
JP5558050B2 (en) * 2009-08-25 2014-07-23 株式会社日立製作所 Nickel-base superalloy for unidirectional solidification with excellent strength and oxidation resistance
US20110076180A1 (en) 2009-09-30 2011-03-31 General Electric Company Nickel-Based Superalloys and Articles
US9138963B2 (en) * 2009-12-14 2015-09-22 United Technologies Corporation Low sulfur nickel base substrate alloy and overlay coating system
US9108266B2 (en) * 2011-04-19 2015-08-18 General Electric Company Welded component, a welded gas turbine component, and a process of welding a component

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
WO2013083101A1 (en) 2013-06-13
EP2788518A1 (en) 2014-10-15
ES2670877T3 (en) 2018-06-01
US20140356183A1 (en) 2014-12-04
US9850765B2 (en) 2017-12-26

Similar Documents

Publication Publication Date Title
DE3030962A1 (en) SINGLE AND POLYCRYSTALLINE ALLOY ON NICKEL OR COBALT BASE.
EP3175008B1 (en) Cobalt based alloy
EP2163656B1 (en) High-temperature-resistant cobalt-base superalloy
WO2018083065A1 (en) Superalloy without titanium, powder, method and component
DE102019213990A1 (en) Nickel-based alloy for additive manufacturing, process and product
EP2788518B1 (en) Rhenium free or low rhenium nickel base superalloy
WO2017118547A1 (en) Gamma, gamma'-cobalt-based alloys for additive manufacturing methods or soldering, welding, powder and component
EP2196550B1 (en) High temperature and oxidation resistant material on the basis of NiAl
DE3503110C2 (en)
EP3091095B1 (en) Low density rhenium-free nickel base superalloy
EP3133178B1 (en) Optimized nickel based superalloy
EP2725110B1 (en) Creep resistant rhenium-free nickel based superalloy
WO2019233692A1 (en) Y, y' hardened cobalt-nickel base alloy, powder, component, and method
EP1223229B1 (en) Nickel based alloy for casting single crystal components
WO2012041276A2 (en) Heat-resistant tial alloy
EP0760869A1 (en) Nickel-aluminium intermetallic basis alloy
WO2019233693A1 (en) Y, y' hardened cobalt-nickel base alloy, powder, component, and method
EP2832872A2 (en) Highly temperature resistant lightweight construction alloy made of NiAl
EP4291408A1 (en) Alloy, powder, method and component
EP2876177B1 (en) Material from laves phase and ferritic fe-al phase
WO2023094116A1 (en) Cobalt-based alloy having a high proportion of aluminum, powder, method and components
EP4288575A1 (en) Alloy, powder, method and component
EP4126425A1 (en) Nickel-based alloy, powder, method and component
EP4208304A1 (en) Alloy, powder, ductile gamma' adhesion promoter layer and component

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140422

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20161013

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MTU AERO ENGINES AG

INTG Intention to grant announced

Effective date: 20180115

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 992999

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180515

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502012012604

Country of ref document: DE

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2670877

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20180601

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180425

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 7

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180725

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180725

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180726

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180827

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502012012604

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20190128

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181017

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181031

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181017

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 992999

Country of ref document: AT

Kind code of ref document: T

Effective date: 20181017

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20181017

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20121017

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180425

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180825

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20201117

Year of fee payment: 9

Ref country code: FR

Payment date: 20201020

Year of fee payment: 9

Ref country code: GB

Payment date: 20201022

Year of fee payment: 9

Ref country code: DE

Payment date: 20201022

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502012012604

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20211017

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211017

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220503

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211031

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20230215

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20211018