EP1359231A1 - Nickel-based superalloy - Google Patents
Nickel-based superalloy Download PDFInfo
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- EP1359231A1 EP1359231A1 EP03100776A EP03100776A EP1359231A1 EP 1359231 A1 EP1359231 A1 EP 1359231A1 EP 03100776 A EP03100776 A EP 03100776A EP 03100776 A EP03100776 A EP 03100776A EP 1359231 A1 EP1359231 A1 EP 1359231A1
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- 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%
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- the invention relates to the field of materials technology. It concerns a nickel-base superalloy, in particular for the production of Single crystal components (SX alloy) or components with directed solidified structure (DS alloy), such as blades for Gas turbines.
- SX alloy Single crystal components
- DS alloy directed solidified structure
- the inventive alloy is also for Conventionally cast components can be used.
- Such nickel-base superalloys are known. Single-crystal components from these alloys have at high temperatures very good material resistance. As a result, z. B. the inlet temperature of Gas turbines are increased, whereby the efficiency of the gas turbine increases.
- Nickel-based superalloys for single-crystal components as found in US 4,643,782, EP 0 208 645 and US 5,270,123, are included solid solution strengthening alloying elements, for example Re, W, Mo, Co, Cr, and ⁇ '-phase-forming elements, such as Al, Ta, and Ti.
- the Content of high-melting alloying elements (W, Mo, Re) in the Basic matrix (austenitic ⁇ -phase) increases continuously with increase the stress temperature of the alloy.
- To contain z. B. usual Nickel-based superalloys for single crystals 6-8% W, up to 6% Re and up to 2% Mo (in% by weight).
- the in the above-mentioned publications alloys disclosed have high creep resistance, good LCF (Low cycle fatigue fatigue) and HCF (high fatigue fatigue) Load cycle number) properties as well as a high oxidation resistance.
- Another problem of the known nickel-base superalloys is that the castability of large components, eg. B. at Gas turbine blades with a length of more than 80 mm, to be desired leaves.
- the casting of a perfect, relatively large directionally solidified Single-crystal component of a nickel-base superalloy is extreme difficult because most of these components have errors, e.g. B. Kleinwinkelkornskynskyn, "Frecklen" (these are defects due to a Chain of rectified grains with a high content of eutectic), equiaxial scattering margins, microporosities u. a.
- Grain boundaries are areas of high local disorder of the crystal lattice since In these areas, the neighboring grains collide and thus one certain disorientation exists between the crystal lattices. ever the greater the disorientation, the greater the disorder, d. H. more greater is the number of dislocations in the grain boundaries that are necessary are, so that the two grains fit together.
- the aim of the invention is to avoid the disadvantages mentioned.
- a nickel-based superalloy which have improved castability and higher Oxidation resistance compared to known nickel-base superalloys having.
- this alloy z For example for large gas turbine single crystal components with a length of> 80 mm be suitable.
- the nickel-based superalloy according to the invention is characterized by the following chemical composition (data in% by weight): 7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-750 ppm C 50-400 ppm B
- the advantages of the invention are that the alloy is very good is pourable and over the previously known state of the art improved oxidation resistance at high temperatures.
- the alloy has the following composition: 7.7-8.3 Cr 5.0-5.25 Co 2.0-2.1 Mo 7.8-8.3 W 5.8-6.1 Ta 4.9-5.1 Al 1.3-1.4 Ti 0.11-0.15 Si 0.11-0.15 Hf 200-300 ppm C 50-100 ppm B
- This alloy is ideally suited for the production of large single-crystal components, For example, blades for gas turbines.
- Nickel-based superalloys having the chemical composition given in Table 1 were investigated (in% by weight): Chemical composition of the investigated alloys VL1 (CMSX-11B) VL2 (CMSX-6) VL3 (CMSX-2) VL4 (René N5) L1 Ni rest rest rest rest rest Cr 12.4 9.7 7.9 7.12 7.7 Co 5.7 5.0 4.6 7.4 5.1 Not a word 0.5 3.0 0.6 1.4 2.0 W 5.1 - 8.0 4.9 7.8 Ta 5.18 2.0 6.0 6.5 5.84 al 3:59 4.81 5:58 6:07 5.0 Ti 4.18 4.71 0.99 00:03 1.4 Hf 00:04 00:05 - 00:17 00:12 C - - - 00:02 B - - - - 0005 Si - - - - 00:12 Nb 0.1 - - - - re - - - 2.84 -
- Alloy L1 is a nickel base superalloy for single crystal components, their composition under the claim of present invention falls.
- the alloys VL1, VL2, VL3 and VL4 comparative alloys under the designations CMSX-11B, CMSX-6, CMSX-2 and René N5 known prior art are. They differ, inter alia. from the alloy according to the invention all in that they are not alloyed with C, B and Si.
- FIGS. 1 to 5 a quasi-isothermal oxidation diagram is shown in each case for the comparative alloys VL1 to VL4 (FIGS. 1 to 4) and the alloy L1 according to the invention (FIG. 5).
- the specific mass change ⁇ m / A data in mg / cm 2 ) at temperatures of 800 ° C., 950 ° C., 1050 ° C. and 1100 ° C. in the range from 0 to 1000 h is shown for the alloys mentioned. Comparing the curves, the superiority of the alloy according to the invention is particularly evident in the case of the high temperatures (1000 ° C.) and the long removal times.
- nickel-base superalloys with higher C and B contents (max. 750 ppm C and max. 400 ppm B) selected according to claim 1 of the invention.
- the components produced from it can also be conventional to water.
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Abstract
Description
Die Erfindung bezieht sich auf das Gebiet der Werkstofftechnik. Sie betrifft eine Nickel-Basis-Superlegierung, insbesondere zur Herstellung von Einkristall-Komponenten (SX-Legierung) oder Komponenten mit gerichtet erstarrtem Gefüge (DS-Legierung), wie beispielsweise Schaufeln für Gasturbinen. Die erfindungsgemässe Legierung ist aber auch für konventionell gegossene Komponenten einsetzbar.The invention relates to the field of materials technology. It concerns a nickel-base superalloy, in particular for the production of Single crystal components (SX alloy) or components with directed solidified structure (DS alloy), such as blades for Gas turbines. The inventive alloy is also for Conventionally cast components can be used.
Derartige Nickel-Basis-Superlegierungen sind bekannt. Einkristall-Komponenten aus diesen Legierungen weisen bei hohen Temperaturen eine sehr gute Materialfestigkeit auf. Dadurch kann z. B. die Einlasstemperatur von Gasturbinen erhöht werden, wodurch die Effizienz der Gasturbine steigt. Such nickel-base superalloys are known. Single-crystal components from these alloys have at high temperatures very good material resistance. As a result, z. B. the inlet temperature of Gas turbines are increased, whereby the efficiency of the gas turbine increases.
Nickel-Basis-Superlegierungen für Einkristall-Komponenten, wie sie aus US
4,643,782, EP 0 208 645 und US 5,270,123 bekannt sind, enthalten dazu
mischkristallverfestigende Legierungselemente, beispielsweise Re, W, Mo,
Co, Cr, sowie γ'-Phasen bildende Elemente, beispielsweise Al, Ta, und Ti. Der
Gehalt an hochschmelzenden Legierungselementen (W, Mo, Re) in der
Grundmatrix (austenitische γ-Phase) nimmt kontinuierlich zu mit der Zunahme
der Beanspruchungstemperatur der Legierung. So enthalten z. B. übliche
Nickel-Basis-Superlegierungen für Einkristalle 6-8 % W, bis zu 6 % Re und bis
zu 2 % Mo (Angaben in Gew.- %). Die in den oben genannten Druckschriften
offenbarten Legierungen weisen eine hohe Kriechfestigkeit, gute LCF
(Ermüdung bei niedriger Lastspielzahl)- und HCF(Ermüdung bei hoher
Lastspielzahl)-Eigenschaften sowie einen hohen Oxidationswiderstand auf.Nickel-based superalloys for single-crystal components as found in US
4,643,782,
Diese bekannten Legierungen wurden für Flugzeugturbinen entwickelt und deshalb optimiert auf den Kurz- und Mittelzeiteinsatz, d.h. die Beanspruchungsdauer wird auf bis zu 20 000 Stunden ausgelegt. Im Gegensatz dazu müssen industrielle Gasturbinen-Komponenten auf eine Beanspruchungsdauer von bis zu 75 000 Stunden ausgelegt werden.These known alloys have been developed for aircraft turbines and therefore optimized for short and medium time use, i. the Stress duration is designed for up to 20,000 hours. in the In contrast, industrial gas turbine components have to go to one Stress duration of up to 75 000 hours are designed.
Nach einer Beanspruchungsdauer von 300 Stunden zeigt z. B. die Legierung CMSX-4 aus US 4,643,782 beim versuchsweisen Einsatz in einer Gasturbine bei einer Temperatur oberhalb von 1000 °C eine starke Vergröberung der γ'-Phase, die nachteilig mit einer Erhöhung der Kriechgeschwindigkeit der Legierung einhergeht.After a period of use of 300 hours z. As the alloy CMSX-4 from US 4,643,782 when used experimentally in a gas turbine at a temperature above 1000 ° C a strong coarsening of the γ'-phase, the disadvantageous with an increase in the creeping speed of Alloy goes along.
Es ist somit erforderlich, die Oxidationsbeständigkeit der bekannten Legierungen bei sehr hohen Temperaturen zu verbessern.It is thus necessary, the oxidation resistance of the known To improve alloys at very high temperatures.
Ein weiteres Problem der bekannten Nickel-Basis-Superlegierungen, beispielsweise der aus US 5,435,861 bekannten Legierungen, besteht darin, dass die Giessbarkeit bei grossen Komponenten, z. B. bei Gasturbinenschaufeln mit einer Länge von mehr als 80 mm, zu wünschen übrig lässt. Das Giessen einer perfekten, relativ grossen gerichtet erstarrten Einkristall-Komponente aus einer Nickel-Basis-Superlegierung ist extrem schwierig, weil die meisten dieser Komponenten Fehler aufweisen, z. B. Kleinwinkelkorngrenzen, "Frecklen" (das sind Fehlstellen bedingt durch eine Kette von gleichgerichteten Körnern mit einem hohem Gehalt an Eutektikum), äquiaxiale Streugrenzen, Mikroporositäten u. a. Diese Fehler schwächen die Komponenten bei hohen Temperaturen, so dass die gewünschte Lebensdauer bzw. die Betriebstemperatur der Turbine nicht erreicht werden. Da aber eine perfekt gegossene Einkristall-Komponente extrem teuer ist, tendiert die Industrie dazu, so viele Defekte wie möglich zuzulassen ohne dass die Lebensdauer oder die Betriebstemperatur beeinträchtigt werden.Another problem of the known nickel-base superalloys, for example, the alloys known from US 5,435,861, is that the castability of large components, eg. B. at Gas turbine blades with a length of more than 80 mm, to be desired leaves. The casting of a perfect, relatively large directionally solidified Single-crystal component of a nickel-base superalloy is extreme difficult because most of these components have errors, e.g. B. Kleinwinkelkorngrenzen, "Frecklen" (these are defects due to a Chain of rectified grains with a high content of eutectic), equiaxial scattering margins, microporosities u. a. These mistakes weaken the Components at high temperatures, leaving the desired Lifespan or the operating temperature of the turbine can not be achieved. But since a perfectly cast single crystal component is extremely expensive, The industry tends to allow as many defects as possible without that the service life or the operating temperature are impaired.
Einer der häufigsten Fehler sind Korngrenzen, welche besonders schädlich für die Hochtemperatureigenschaften der Einkristall-Artikel sind. Während Kleinwinkelkorngrenzen bei kleinen Bauteilen vergleichsweise nur einen geringen Einfluss auf die Eigenschaften haben, sind sie in Bezug auf die Giessbarkeit und das Oxidationsverhalten bei hohen Temperaturen bei grossen SX- oder DS-Bauteilen von hoher Relevanz.One of the most common mistakes are grain boundaries, which are especially harmful for the high temperature properties of single crystal articles. While Kleinwinkelkorngrenzen for small components comparatively only one have little impact on the properties, they are in terms of the Castability and the oxidation behavior at high temperatures large SX or DS components of high relevance.
Korngrenzen sind Gebiete hoher örtlicher Fehlordnung des Kristallgitters, da in diesen Gebieten die Nachbarkörner zusammenstossen und somit eine bestimmte Desorientierung zwischen den Kristallgittern vorhanden ist. Je grösser die Desorientierung ist, desto grösser ist die Fehlordnung, d. h. desto grösser ist die Anzahl der Versetzungen in den Korngrenzen, die notwendig sind, damit die beiden Körner zusammenpassen. Diese Fehlordnung steht in direktem Zusammenhang zum Verhalten des Materials bei hohen Temperaturen. Sie schwächt das Material, wenn sich die Temperatur über die äquikohäsive Temperatur (= 0,5 x Schmelzpunkt in K) erhöht.Grain boundaries are areas of high local disorder of the crystal lattice since In these areas, the neighboring grains collide and thus one certain disorientation exists between the crystal lattices. ever the greater the disorientation, the greater the disorder, d. H. more greater is the number of dislocations in the grain boundaries that are necessary are, so that the two grains fit together. This disorder is in direct relation to the behavior of the material at high Temperatures. It weakens the material when the temperature over the Equally cohesive temperature (= 0.5 x melting point in K) increased.
Aus GB 2 234 521 A ist dieser Effekt bekannt. So sinkt bei einer
konventionellen Nickel-Basis-Einkristall-Legierung beispielsweise bei einer
Prüftemperatur von 871 °C die Bruchfestigkeit extrem ab, wenn die
Desorientierung der Körner grösser als 6° ist. Dies wurde auch bei Einkristall-Komponenten
mit gerichtet erstarrtem Gefüge festgestellt, so dass allgemein
die Ansicht vertreten wurde, Desorientierungen grösser als 6° nicht
zuzulassen.From
Aus der genannten GB 2 234 521 A ist auch bekannt, dass durch die
Anreicherung von Nickel-Basis-Superlegierungen mit Bor oder Kohlenstoff bei
einer gerichteten Erstarrung Gefüge erzeugt werden, welche eine äquiaxiale
oder prismatische Kornstruktur aufweisen. Kohlenstoff und Bor festigen die
Korngrenzen, da C und B die Ausscheidung von Karbiden und Boriden an
den Korngrenzen verursachen, welche bei hohen Temperaturen stabil sind.
Ausserdem verringert die Anwesenheit dieser Elemente in den und entlang
der Korngrenzen den Diffusionsprozess, der eine Hauptursache der
Korngrenzenschwäche ist. Es ist daher möglich, die Desorientierungen auf
10° bis 12° zu erhöhen und trotzdem gute Eigenschaften des Materials bei
hohen Temperaturen zu erzielen. Insbesondere bei grossen
Einkristallkomponenten aus Nickel-Basis-Superlegierungen beeinflussen
diese Kleinwinkelkorngrenzen aber negativ die Eigenschaften.From the
Ziel der Erfindung ist es, die genannten Nachteile zu vermeiden. Der Erfindung liegt die Aufgabe zu Grunde, eine Nickel-Basis-Superlegierung zu entwickeln, welche eine verbesserte Giessbarkeit und einen höheren Oxidationswiderstand im Vergleich zu bekannten Nickel-Basis-Superlegierungen aufweist. Ausserdem soll diese Legierung z. B. besonders für grosse Gasturbinen-Einkristallkomponenten mit einer Länge von > 80 mm geeignet sein.The aim of the invention is to avoid the disadvantages mentioned. Of the Invention is based on the object, a nickel-based superalloy which have improved castability and higher Oxidation resistance compared to known nickel-base superalloys having. In addition, this alloy z. For example for large gas turbine single crystal components with a length of> 80 mm be suitable.
Erfindungsgemäss wird diese Aufgabe dadurch gelöst, dass die
erfindungsgemässe Nickel-Basis-Superlegierung durch folgende chemische
Zusammensetzung (Angaben in Gew.- %) gekennzeichnet ist:
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-750 ppm C
50-400 ppm BAccording to the invention, this object is achieved in that the nickel-based superalloy according to the invention is characterized by the following chemical composition (data in% by weight):
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-750 ppm C
50-400 ppm B
Rest Nickel und herstellungsbedingte Verunreinigungen.Remaining nickel and manufacturing-related impurities.
Die Vorteile der Erfindung bestehen darin, dass die Legierung sehr gut giessbar ist und gegenüber dem bisher bekannten Stand der Technik einen verbesserten Oxidationswiderstand bei hohen Temperaturen aufweist.The advantages of the invention are that the alloy is very good is pourable and over the previously known state of the art improved oxidation resistance at high temperatures.
Von besonderem Vorteil ist, wenn die Legierung folgende Zusammensetzung
aufweist:
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-300 ppm C
50-100 ppm BIt is particularly advantageous if the alloy has the following composition:
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-300 ppm C
50-100 ppm B
Rest Nickel und herstellungsbedingte Verunreinigungen. Diese Legierung ist hervorragend geeignet zur Herstellung von grossen Einkristall-Komponenten, beispielsweise Schaufeln für Gasturbinen. Remaining nickel and manufacturing-related impurities. This alloy is ideally suited for the production of large single-crystal components, For example, blades for gas turbines.
In den Zeichnungen ist ein Ausführungsbeispiel der Erfindung anhand von quasi-isothermischen Oxidationsdiagrammen dargestellt. Es zeigen:
- Fig. 1
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL1;
- Fig. 2
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL2;
- Fig. 3
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL3;
- Fig. 4
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die Vergleichslegierung VL4 und
- Fig. 5
- die Abhängigkeit der spezifischen Massenänderung von der Temperatur und Zeit für die erfindungsgemässe Legierung L1.
- Fig. 1
- the dependence of the specific mass change on the temperature and time for the comparative alloy VL1;
- Fig. 2
- the dependence of the specific mass change on the temperature and time for the reference alloy VL2;
- Fig. 3
- the dependence of the specific mass change on the temperature and time for the reference alloy VL3;
- Fig. 4
- the dependence of the specific mass change on the temperature and time for the comparative alloy VL4 and
- Fig. 5
- the dependence of the specific mass change on the temperature and time for the inventive alloy L1.
Nachfolgend wird die Erfindung anhand eines Ausführungsbeispieles und der Fig. 1 bis 5 näher erläutert.Hereinafter, the invention with reference to an embodiment and the Fig. 1 to 5 explained in more detail.
Es wurden Nickel-Basis-Superlegierungen mit der in Tabelle 1 angegebenen
chemischen Zusammensetzung untersucht (Angaben in Gew.- %):
Die Legierung L1 ist eine Nickel-Basis-Superlegierung für Einkristall-Komponenten, deren Zusammensetzung unter den Patentanspruch der vorliegenden Erfindung fällt. Im Gegensatz dazu sind die Legierungen VL1, VL2, VL3 und VL4 Vergleichslegierungen, die unter den Bezeichnungen CMSX-11B, CMSX-6, CMSX-2 und René N5 bekannter Stand der Technik sind. Sie unterscheiden sich u.a. von der erfindungsgemässen Legierung vor allem darin, dass sie nicht mit C, B und Si legiert sind.Alloy L1 is a nickel base superalloy for single crystal components, their composition under the claim of present invention falls. In contrast, the alloys VL1, VL2, VL3 and VL4 comparative alloys under the designations CMSX-11B, CMSX-6, CMSX-2 and René N5 known prior art are. They differ, inter alia. from the alloy according to the invention all in that they are not alloyed with C, B and Si.
Kohlenstoff und Bor festigen die Korngrenzen, insbesondere auch die in <001>-Richtung bei SX- bzw. DS-Gasturbinenschaufeln aus Nickel-Basis-Superlegierungen auftretenden Kleinwinkelkorngrenzen, da diese Elemente die Ausscheidung von Karbiden und Boriden an den Korngrenzen verursachen, welche bei hohen Temperaturen stabil sind. Ausserdem verringert die Anwesenheit dieser Elemente in den und entlang der Korngrenzen den Diffusionsprozess, der eine Hauptursache der Korngrenzenschwäche ist. Dadurch wird die Giessbarkeit langer Einkristall-Komponenten, beispielsweise Gasturbinenschaufeln mit einer Länge von ca. 200 bis 230 mm, erheblich verbessert.Carbon and boron strengthen the grain boundaries, especially those in <001> direction for SX or DS gas turbine blades made of nickel-base superalloys occurring small angle grain boundaries, as these elements the precipitation of carbides and borides at the grain boundaries which are stable at high temperatures. Moreover reduces the presence of these elements in and along the Grain boundaries the diffusion process, which is a major cause of Grain boundary weakness is. This results in the castability of long single crystal components, For example, gas turbine blades with a length of approx. 200 to 230 mm, significantly improved.
Durch die Zugabe von 0.11 bis 0.15 Gew.-% Si, vor allem in Kombination mit Hf in etwa gleicher Grössenordnung, wird eine wesentliche Verbesserung des Oxidationswiderstandes bei hohen Temperaturen gegenüber bisher bekannten Nickel-Basis-Superlegierungen erzielt. Dies wird in den Fig. 1 bis 5 verdeutlicht, in welchen jeweils für die Vergleichslegierungen VL1 bis VL4 (Fig. 1 bis 4) und die erfindungsgemässe Legierung L1 (Fig. 5) ein quasiisothermisches Oxidationsdiagramm abgebildet ist. Für die genannten Legierungen ist jeweils die spezifische Masseveränderung Δm/A (Angaben in mg/cm2) bei Temperaturen von 800 °C, 950 °C, 1050 °C und 1100 °C im Bereich von 0 bis 1000 h dargestellt. Vergleicht man die Kurvenverläufe, so zeigt sich insbesondere bei den hohen Temperaturen (1000 °C) und den langen Auslagerungszeiten die Überlegenheit der erfindungsgemässen Legierung.The addition of 0.11 to 0.15 wt .-% Si, especially in combination with Hf in about the same order of magnitude, a significant improvement in the oxidation resistance at high temperatures compared to previously known nickel-based superalloys is achieved. This is illustrated in FIGS. 1 to 5, in which a quasi-isothermal oxidation diagram is shown in each case for the comparative alloys VL1 to VL4 (FIGS. 1 to 4) and the alloy L1 according to the invention (FIG. 5). The specific mass change Δm / A (data in mg / cm 2 ) at temperatures of 800 ° C., 950 ° C., 1050 ° C. and 1100 ° C. in the range from 0 to 1000 h is shown for the alloys mentioned. Comparing the curves, the superiority of the alloy according to the invention is particularly evident in the case of the high temperatures (1000 ° C.) and the long removal times.
Werden Nickel-Basis-Superlegierungen mit höheren C- und B-Gehalten (max.
750 ppm C und max. 400 ppm B) gemäss Anspruch 1 der Erfindung gewählt,
so lassen sich die daraus hergestellten Komponenten auch konventionell
giessen.Are nickel-base superalloys with higher C and B contents (max.
750 ppm C and max. 400 ppm B) selected according to
Claims (3)
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-750 ppm C
50-400 ppm B
Rest Nickel und herstellungsbedingte Verunreinigungen.Nickel-based superalloy characterized by the following chemical composition (in% by weight):
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-750 ppm C
50-400 ppm B
Remaining nickel and manufacturing-related impurities.
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-300 ppm C
50-100 ppm B
Rest Nickel und herstellungsbedingte Verunreinigungen.Nickel-based superalloy according to claim 1, in particular for the production of single-crystal components, characterized by the following chemical composition (in% by weight):
7.7-8.3 Cr
5.0-5.25 Co
2.0-2.1 Mo
7.8-8.3 W
5.8-6.1 Ta
4.9-5.1 Al
1.3-1.4 Ti
0.11-0.15 Si
0.11-0.15 Hf
200-300 ppm C
50-100 ppm B
Remaining nickel and manufacturing-related impurities.
7.7 Cr
5.1 Co
2.0 Mo
7.8 W
5.8 Ta
5.0 Al
1.4 Ti
0.12 Si
0.12 Hf
200 ppm C
50 ppm B
Rest Nickel und herstellungsbedingte Verunreinigungen.Nickel-based superalloy according to claim 2 characterized by the following chemical composition (in% by weight):
7.7 Cr
5.1 Co
2.0 Mo
7.8 W
5.8 Ta
5.0 al
1.4 Ti
0.12 Si
0.12 Hf
200 ppm C
50 ppm B
Remaining nickel and manufacturing-related impurities.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH7452002 | 2002-04-30 | ||
| CH00745/02A CH695497A5 (en) | 2002-04-30 | 2002-04-30 | Nickel-base superalloy. |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1359231A1 true EP1359231A1 (en) | 2003-11-05 |
| EP1359231B1 EP1359231B1 (en) | 2005-10-19 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP03100776A Expired - Fee Related EP1359231B1 (en) | 2002-04-30 | 2003-03-26 | Nickel-based superalloy |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US6740292B2 (en) |
| EP (1) | EP1359231B1 (en) |
| JP (1) | JP4326830B2 (en) |
| AT (1) | ATE307219T1 (en) |
| CH (1) | CH695497A5 (en) |
| DE (1) | DE50301388D1 (en) |
| ES (1) | ES2250826T3 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006053826A2 (en) * | 2004-11-18 | 2006-05-26 | Alstom Technology Ltd | Nickel-based superalloy |
| CH699205A1 (en) * | 2008-07-25 | 2010-01-29 | Alstom Technology Ltd | Protective tubes for thermocouples. |
| WO2011003804A1 (en) * | 2009-07-09 | 2011-01-13 | Alstom Technology Ltd. | Nickel-based superalloy |
| EP2354261A1 (en) * | 2010-02-05 | 2011-08-10 | Alstom Technology Ltd | Nickel-Basis-Superalloy with improved degradation behaviour |
| EP2949768A1 (en) | 2014-05-28 | 2015-12-02 | Alstom Technology Ltd | Gamma prime precipitation strengthened nickel-base superalloy for use in powder based additive manufacturing process |
| US10752978B2 (en) | 2016-09-13 | 2020-08-25 | Rolls-Royce Plc | Nickel-base superalloy and use thereof |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE528807C2 (en) * | 2004-12-23 | 2007-02-20 | Siemens Ag | Component of a superalloy containing palladium for use in a high temperature environment and use of palladium for resistance to hydrogen embrittlement |
| US20060182649A1 (en) * | 2005-02-16 | 2006-08-17 | Siemens Westinghouse Power Corp. | High strength oxidation resistant superalloy with enhanced coating compatibility |
| US20060219329A1 (en) * | 2005-03-29 | 2006-10-05 | Honeywell International, Inc. | Repair nickel-based superalloy and methods for refurbishment of gas turbine components |
| ES2444407T3 (en) * | 2006-09-07 | 2014-02-24 | Alstom Technology Ltd | Procedure for heat treatment of nickel-based super-alloys |
| JP5439822B2 (en) * | 2009-01-15 | 2014-03-12 | 独立行政法人物質・材料研究機構 | Ni-based single crystal superalloy |
| US20100254822A1 (en) * | 2009-03-24 | 2010-10-07 | Brian Thomas Hazel | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
| US20110076179A1 (en) * | 2009-03-24 | 2011-03-31 | O'hara Kevin Swayne | Super oxidation and cyclic damage resistant nickel-base superalloy and articles formed therefrom |
| US8449262B2 (en) * | 2009-12-08 | 2013-05-28 | Honeywell International Inc. | Nickel-based superalloys, turbine blades, and methods of improving or repairing turbine engine components |
| WO2013167513A1 (en) | 2012-05-07 | 2013-11-14 | Alstom Technology Ltd | Method for manufacturing of components made of single crystal (sx) or directionally solidified (ds) superalloys |
| US20160214350A1 (en) | 2012-08-20 | 2016-07-28 | Pratt & Whitney Canada Corp. | Oxidation-Resistant Coated Superalloy |
| JP6267890B2 (en) * | 2013-08-07 | 2018-01-24 | 三菱日立パワーシステムズ株式会社 | Ni-base cast superalloy and casting made of the Ni-base cast superalloy |
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| GB2105748A (en) * | 1981-09-14 | 1983-03-30 | United Technologies Corp | Minor element additions to single crystals for improved oxidation resistance |
| US4885216A (en) * | 1987-04-03 | 1989-12-05 | Avco Corporation | High strength nickel base single crystal alloys |
| GB2234521A (en) * | 1986-03-27 | 1991-02-06 | Gen Electric | Nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries |
| US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
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| US4461659A (en) * | 1980-01-17 | 1984-07-24 | Cannon-Muskegon Corporation | High ductility nickel alloy directional casting of parts for high temperature and stress operation |
| FR2557598B1 (en) * | 1983-12-29 | 1986-11-28 | Armines | SINGLE CRYSTAL ALLOY WITH NICKEL-BASED MATRIX |
| US4643782A (en) | 1984-03-19 | 1987-02-17 | Cannon Muskegon Corporation | Single crystal alloy technology |
| US4677035A (en) * | 1984-12-06 | 1987-06-30 | Avco Corp. | High strength nickel base single crystal alloys |
| US4719080A (en) | 1985-06-10 | 1988-01-12 | United Technologies Corporation | Advanced high strength single crystal superalloy compositions |
| US5270123A (en) | 1992-03-05 | 1993-12-14 | General Electric Company | Nickel-base superalloy and article with high temperature strength and improved stability |
| DE69701900T2 (en) * | 1996-02-09 | 2000-12-07 | Hitachi Ltd | High-strength nickel-based superalloy for directionally solidified castings |
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2002
- 2002-04-30 CH CH00745/02A patent/CH695497A5/en not_active IP Right Cessation
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2003
- 2003-03-26 EP EP03100776A patent/EP1359231B1/en not_active Expired - Fee Related
- 2003-03-26 AT AT03100776T patent/ATE307219T1/en active
- 2003-03-26 DE DE50301388T patent/DE50301388D1/en not_active Expired - Lifetime
- 2003-03-26 ES ES03100776T patent/ES2250826T3/en not_active Expired - Lifetime
- 2003-03-28 US US10/400,415 patent/US6740292B2/en not_active Expired - Lifetime
- 2003-04-23 JP JP2003118858A patent/JP4326830B2/en not_active Expired - Fee Related
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| GB2105748A (en) * | 1981-09-14 | 1983-03-30 | United Technologies Corp | Minor element additions to single crystals for improved oxidation resistance |
| GB2234521A (en) * | 1986-03-27 | 1991-02-06 | Gen Electric | Nickel-base superalloys for producing single crystal articles having improved tolerance to low angle grain boundaries |
| US4885216A (en) * | 1987-04-03 | 1989-12-05 | Avco Corporation | High strength nickel base single crystal alloys |
| US5435861A (en) * | 1992-02-05 | 1995-07-25 | Office National D'etudes Et De Recherches Aerospatiales | Nickel-based monocrystalline superalloy with improved oxidation resistance and method of production |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006053826A2 (en) * | 2004-11-18 | 2006-05-26 | Alstom Technology Ltd | Nickel-based superalloy |
| WO2006053826A3 (en) * | 2004-11-18 | 2007-05-31 | Alstom Technology Ltd | Nickel-based superalloy |
| CH699205A1 (en) * | 2008-07-25 | 2010-01-29 | Alstom Technology Ltd | Protective tubes for thermocouples. |
| WO2011003804A1 (en) * | 2009-07-09 | 2011-01-13 | Alstom Technology Ltd. | Nickel-based superalloy |
| CH701415A1 (en) * | 2009-07-09 | 2011-01-14 | Alstom Technology Ltd | Nickel-base superalloy. |
| US9017605B2 (en) | 2009-07-09 | 2015-04-28 | Alstom Technology Ltd. | Nickel-based superalloy |
| EP2354261A1 (en) * | 2010-02-05 | 2011-08-10 | Alstom Technology Ltd | Nickel-Basis-Superalloy with improved degradation behaviour |
| CH702642A1 (en) * | 2010-02-05 | 2011-08-15 | Alstom Technology Ltd | Nickel-base superalloy with improved degradation. |
| EP2949768A1 (en) | 2014-05-28 | 2015-12-02 | Alstom Technology Ltd | Gamma prime precipitation strengthened nickel-base superalloy for use in powder based additive manufacturing process |
| US10752978B2 (en) | 2016-09-13 | 2020-08-25 | Rolls-Royce Plc | Nickel-base superalloy and use thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CH695497A5 (en) | 2006-06-15 |
| ES2250826T3 (en) | 2006-04-16 |
| DE50301388D1 (en) | 2006-03-02 |
| JP2004027361A (en) | 2004-01-29 |
| US20040005238A1 (en) | 2004-01-08 |
| EP1359231B1 (en) | 2005-10-19 |
| JP4326830B2 (en) | 2009-09-09 |
| US6740292B2 (en) | 2004-05-25 |
| ATE307219T1 (en) | 2005-11-15 |
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