EP0274631A1 - Process for increasing the room temperature ductility of an oxide dispersion hardened nickel base superalloy article having a coarse columnar grain structure directionally oriented along the length - Google Patents
Process for increasing the room temperature ductility of an oxide dispersion hardened nickel base superalloy article having a coarse columnar grain structure directionally oriented along the length Download PDFInfo
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- EP0274631A1 EP0274631A1 EP87117524A EP87117524A EP0274631A1 EP 0274631 A1 EP0274631 A1 EP 0274631A1 EP 87117524 A EP87117524 A EP 87117524A EP 87117524 A EP87117524 A EP 87117524A EP 0274631 A1 EP0274631 A1 EP 0274631A1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
- C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
- C22C32/0026—Matrix based on Ni, Co, Cr or alloys thereof
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/10—Alloys containing non-metals
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
Definitions
- the invention relates to the improvement of the mechanical properties of oxide dispersion-hardened nickel-based superalloys with overall optimal properties with regard to high-temperature strength, long-term stability and ductility.
- it relates to a method for increasing the ductility of a workpiece made of an oxide dispersion-hardened nickel-base superalloy in coarse, longitudinally shaped, columnar crystallites at room temperature, the workpiece being produced by powder metallurgy, extruded or forged or hot-isostatically pressed and then zone-annealed.
- Oxide dispersion-hardened nickel-based superalloys are characterized by high heat resistance, in particular creep resistance and fatigue strength at the highest working temperatures. In lower temperature ranges, especially at room temperatures, however, these alloys are comparatively brittle and also have a low shear strength compared to conventional high-temperature alloys. This complicates their use as blade material in gas turbine construction, since a rotor blade is usually exposed to very different complex thermal and mechanical stresses in terms of time and location.
- the blade root usually a kind of "fir tree construction" for anchoring in the rotor body, is always subjected to tensile, compressive and shear stresses and is therefore particularly at risk.
- the material to be used must therefore have a certain minimum ductility and shear strength.
- the invention is based on the object of specifying a method for improving the ductility of a workpiece consisting of a coarse-grained oxide dispersion-hardened nickel-based superalloy which can be carried out easily and does not impair the other material properties, particularly in the high temperature range.
- the process is said to increase the comparatively low ductility in the transverse direction of the longitudinal stem crystallites appreciably. This should be accompanied by an increase in shear strength.
- the majority of the commercially used oxide-hardened nickel-based superalloys contain, apart from the dispersoids, the well-known ⁇ phase in finely divided deposits. It could be shown that the ductility, especially in the low temperature range (eg at room temperature), is essentially dependent on the amount, shape and distribution of this ⁇ phase. It is therefore a matter of bringing this phase into a suitable form or in solution in the matrix, which is according to the invention according to with the help of the above-mentioned heat treatment and targeted cooling of the workpiece.
- the creep limit and fatigue strength are not adversely affected by the at least partial dissolution of the ⁇ in phase in the matrix in view of the highest operating temperature of the alloy.
- the figure shows:
- T1 is the maximum permissible solution temperature for the ⁇ phase in the ⁇ matrix, which is determined by the melting point of the deep-melting phase of the superalloy. In order to prevent melting of this phase with certainty, T 1 must still be around 10 ° C below the lowest melting point (solidus point) of the alloy.
- T2 is the minimum required solution annealing temperature for the ⁇ phase in the ⁇ matrix. It is assumed that after a finite period of time that is in operation, the entire mass of the ⁇ phase has changed to a solid solution in the ⁇ matrix (ie after a few hours). a is the upper limit of the temperature profile of the slow cooling of the workpiece, which is given by practical operating conditions.
- Curve 1 relates to the temperature profile of the heat treatment of the material MA 6000 according to Example 1, curve 2 to that of MA 6000 according to Example 2.
- the temperature curve according to curve 3 relates to a workpiece of the alloy according to example 3.
- a prismatic sample 180 mm long, 50 mm wide and 12 mm thick was machined from an oxide dispersion-hardened nickel-based alloy with the trade name MA 6000 (INCO).
- the raw material had undergone the following thermomechanical and thermal treatments at the manufacturer: - hot extrusion - hot rolling - Zone annealing on elongated coarse grain at 1270 ° C - Annealing at 1230 ° C / 1/2 h, air cooling - Annealing at 955 ° C / 2 h, air cooling - Annealing at 845 ° C / 24 h, air cooling
- the mechanical properties of the material in the form of elongated crystallites in the delivery state were determined as follows (long-term values at room temperature Transverse direction of the crystallites): - yield strength (0.2%) 1095 MPa - tensile strength 1187 MPa - elongation 2.48%
- the workpiece was then subjected to a heat treatment as follows: - Warming up to 1180 ° C under an argon atmosphere - Solution annealing at 1180 ° C for 2 1/2 hours - Cool down to 640 ° C at a rate of 0.5 ° C / min - Cool down to room temperature in air
- the raw material had undergone the following thermomechanical and thermal treatments at the manufacturer: - hot extrusion - Zone annealing on elongated coarse grain at 1270 ° C
- the mechanical properties of the material in the form of elongated crystallites in the delivery state were determined as follows (values at room temperature): In the longitudinal direction of the crystallites: - yield strength (0.2%) 1186 MPa - tensile strength 1210 MPa - elongation 1.37% In the transverse direction of the crystallites: - yield strength (0.2%) 1228 MPa - tensile strength 1232 MPa - elongation 0.33%
- the workpiece was then subjected to a heat treatment as follows: - Warming up to 1260 ° C under an argon atmosphere - Solution annealing at 1260 ° C for 1 h - Cool down to 600 ° C at a rate of 0.5 ° C / min - Cool down to room temperature in air
- a prismatic sample 120 mm long, 40 mm wide and 10 mm thick was machined from an oxide dispersion-hardened nickel-based alloy.
- the raw material had undergone the following thermomechanical and thermal treatments at the manufacturer: - hot extrusion - Zone annealing on elongated coarse grain at 1260 ° C - Annealing at 1230 ° C / 1/2 h, air cooling - Annealing at 955 ° C / 2 h, air cooling - Annealing at 845 ° C / 24 h, air cooling
- the mechanical properties of the material in the form of elongated crystallites as delivered were determined as follows (values at room temperature in the transverse direction of the crystallites): - yield strength (0.2%) 1316 MPa - tensile strength 1348 MPa - elongation 0.41%
- the workpiece was then subjected to a heat treatment as follows: - Warming up to 1260 ° C under an argon atmosphere - Solution annealing at 1260 ° C for 1 h - Cool down to 700 ° C at a rate of 0.4 ° C / min - Cool down to room temperature in air
- the solution annealing temperature for this type of oxide dispersion hardened nickel-based superalloys can be selected within the limits of T2 (1160 ° C) and T1 (1280 ° C). Depending on the workpiece and operational requirements, the solution annealing time is preferably between 1/2 h and 5 h.
- the cooling rate during the cooling process after solution annealing can be selected within the limits of 5 ° C / min and 0.1 ° C / min. Approx. 0.5 ° C / min are preferred.
- the lower temperature T3 up to which the heat treatment is to be carried out at a defined cooling rate can be chosen freely between the limits of 500 and 700 ° C.
Abstract
Verfahren zur Erhöhung der Duktilität eines in groben längsgerichteten stengelförmigen Kristalliten vorliegenden Werkstücks aus einer oxyddispersionsgehärteten Nickelbasis-Superlegierung bei Raumtemperatur, indem das zuvor zonengeglühte Werkstück unter Argonatmosphäre während 1/2 h bis 5 h einer Lösungsglühung im Temperaturbereich zwischen 1160 und 1280 °C und anschliessend einer gezielten Abkühlung mit einer Geschwindigkeit von 0,1 °C/min bis 5 °C/min bis auf eine Temperatur von 500 bis 700 °C unterworfen wird. Daraufhin wird das Werkstück an Luft bis auf Raumtemperatur abgekühlt. Bevorzugte gezielte Abkühlungsgeschwindigkeit: ca. 0,5 °C/min.Process for increasing the ductility of a workpiece made of an oxide dispersion-hardened nickel-base superalloy in coarse, longitudinally shaped, columnar crystallites at room temperature by subjecting the previously zone-annealed workpiece to an annealing solution in the temperature range between 1160 and 1280 ° C for 1/2 h to 5 h and then one targeted cooling at a rate of 0.1 ° C / min to 5 ° C / min to a temperature of 500 to 700 ° C is subjected. The workpiece is then cooled in air to room temperature. Preferred targeted cooling rate: approx. 0.5 ° C / min.
Description
Oxyddispersionsgehärtete Superlegierungen auf der Basis von Nickel, welche dank ihrer hervorragenden mechanischen Eigenschaften be hohen Temperaturen beim Bau thermischer Maschinen Verwendung finden. Bevorzugte Verwendung als Schaufelwerkstoff für Gasturbinen.Oxide dispersion hardened superalloys based on nickel, which thanks to their excellent mechanical properties are used at high temperatures in the construction of thermal machines. Preferred use as a blade material for gas turbines.
Die Erfindung bezieht sich auf die Verbesserung der mechanischen Eigenschaften von oxyddispersionsgehärteten Nickelbasis-Superlegierungen mit insgesamt optimalen Eigenschaften bezüglich Hochtemperaturfestigkeit, Langzeitstabilität und Duktilität.The invention relates to the improvement of the mechanical properties of oxide dispersion-hardened nickel-based superalloys with overall optimal properties with regard to high-temperature strength, long-term stability and ductility.
Insbesondere betrifft sie ein Verfahren zur Erhöhung der Duktilität eines in groben längsgerichteten stengelförmigen Kristalliten vorliegenden Werkstücks aus einer oxyddisperionsgehärteten Nickelbasis-Superlegierung bei Raumtemperatur, wobei das Werkstück pulvermetallurgisch hergestellt, stranggepresst oder geschmiedet oder heiss-isostatisch gepresst und anschliessend zonengeglüht wird.In particular, it relates to a method for increasing the ductility of a workpiece made of an oxide dispersion-hardened nickel-base superalloy in coarse, longitudinally shaped, columnar crystallites at room temperature, the workpiece being produced by powder metallurgy, extruded or forged or hot-isostatically pressed and then zone-annealed.
Zum Stand der Technik wird folgende Literatur zitiert:
- G.H. Gessinger, Powder Metallurgy of Superalloys, Butterworths, London, 1984
- R.F. Singer and E. Arzt, To be published in: Conf. Proc. "High Temperature Materials for Gas Turbines", Liège, Belgium, Oktober 1986
- J.S. Benjamin, Metall. Trans. 1970, 1, 2943 - 2951
- M.Y. Nazmy and R.F. Singer, Effect of inclusions on tensile ductility of a nickel-base oxide dispersion strengthened superalloy, Scripta Metallurgica, Vol. 19, pp. 829-832, 1985, Pergamon Press Ldt.
- T.K. Glasgow, "Longitudinal Shear Behaviour of Several Oxide Dispersion Strengthened Alloys", NASA TM-78973 (1978).The following literature is cited on the prior art:
- GH Gessinger, Powder Metallurgy of Superalloys, Butterworths, London, 1984
- RF Singer and E. Arzt, To be published in: Conf. Proc. "High Temperature Materials for Gas Turbines", Liège, Belgium, October 1986
- JS Benjamin, metal. Trans. 1970, 1, 2943-2951
- MY Nazmy and RF Singer, Effect of inclusions on tensile ductility of a nickel-base oxide dispersion strengthened superalloy, Scripta Metallurgica, Vol. 19, pp. 829-832, 1985, Pergamon Press Ldt.
- TK Glasgow, "Longitudinal Shear Behavior of Several Oxide Dispersion Strengthened Alloys", NASA TM-78973 (1978).
Oxyddispersionsgehärtete Nickelbasis-Superlegierungen zeichnen sich durch hohe Warmfestigkeit, insbesondere Kriechfestigkeit und Ermüdungsfestigkeit bei höchsten Arbeitstemperaturen aus. In tieferen Temperaturbereichen, insbesondere bei Raumtemperaturen sind jedoch diese Legierungen vergleichsweise spröde und haben ausserdem im Vergleich zu konventionellen Hochtemperaturlegierungen eine geringe Scherfestigkeit. Dies erschwert ihre Verwendung als Schaufelmaterial im Gasturbinenbau, da eine Rotorschaufel in der Regel zeitlich und örtlich sehr verschiedenen komplexen thermischen und mechanischen Beanspruchungen ausgesetzt ist. Insbesondere der Schaufelfuss, meist eine Art "Tannenbaumkonstruktion" zwecks Verankerung im Rotorkörper ist stets Zug-, Druck- und Schubspannungen unterworfen und demzufolge besonders gefährdet. Ausserdem sollte er Deformationen übernehmen können, um sich den Betriebs bedingungen anpassen zu können. Der zu verwendende Werkstoff muss daher eine bestimmte minimale Duktilität und Scherfestigkeit aufweisen.Oxide dispersion-hardened nickel-based superalloys are characterized by high heat resistance, in particular creep resistance and fatigue strength at the highest working temperatures. In lower temperature ranges, especially at room temperatures, however, these alloys are comparatively brittle and also have a low shear strength compared to conventional high-temperature alloys. This complicates their use as blade material in gas turbine construction, since a rotor blade is usually exposed to very different complex thermal and mechanical stresses in terms of time and location. In particular, the blade root, usually a kind of "fir tree construction" for anchoring in the rotor body, is always subjected to tensile, compressive and shear stresses and is therefore particularly at risk. In addition, he should be able to take deformations to the operating to be able to adapt conditions. The material to be used must therefore have a certain minimum ductility and shear strength.
Es besteht daher ein Bedürfnis, die obigen Mängel weitgehend zu beseitigen und Wege zur Verbesserung des Werkstoffverhaltens im Betrieb aufzuzeigen.There is therefore a need to largely remedy the above deficiencies and to show ways of improving the material behavior in operation.
Der Erfindung liegt die Aufgabe zugrunde, ein Verfahren zur Verbesserung der Duktilität eines aus einer grobkörnigen oxyddispersionsgehärteten Nickelbasis-Superlegierung bestehenden Werkstücks anzugeben, das sich einfach durchführen lässt und den übrigen Werkstoffeigenschaften, insbesondere im Hochtemperaturbereich keinen Abbruch tut. Das Verfahren soll insbesondere die vergleichweise geringe Duktilität in der Querrichtung der längsgerichteten Stengelkristallite nahmhaft erhöhen. Damit einher soll eine Erhöhung der Scherfestigkeit erreicht werden.The invention is based on the object of specifying a method for improving the ductility of a workpiece consisting of a coarse-grained oxide dispersion-hardened nickel-based superalloy which can be carried out easily and does not impair the other material properties, particularly in the high temperature range. In particular, the process is said to increase the comparatively low ductility in the transverse direction of the longitudinal stem crystallites appreciably. This should be accompanied by an increase in shear strength.
Diese Aufgabe wird dadurch gelöst, dass im eingangs erwähnten Vefahren das Werkstück nach dem Zonenglühen unter Argonatmosphäre während 1/2 bis 5 h einer Lösungsglühung bei einer Temperatur zwischen 1160 und 1280 °C unterworfen und anschliessend mit einer Geschwindigkeit zwischen 0,1 °C/min und 5 °C/min bis auf eine Temperatur von 500 bis 700 °C abgekühlt und daraufhin in Luft bis auf Raumtemperatur abgekühlt wird.This object is achieved in that in the process mentioned at the outset, after the zone annealing under an argon atmosphere, the workpiece is subjected to solution annealing for 1/2 to 5 hours at a temperature between 1160 and 1280 ° C. and then at a speed between 0.1 ° C./min and 5 ° C / min cooled to a temperature of 500 to 700 ° C and then cooled in air to room temperature.
Der Grossteil der komerziell verwendeten oxyddispersionsgehärteten Nickelbasis-Superlegierungen enthält ausser den Dispersoiden die bekannte γʹ-Phase in feinverteilten Auscheidungen. Es konnte gezeigt werden, dass die Duktilität insbesondere im tiefen Temperaturbereich (z.B. bei Raumtemperatur) wesentlich von der Menge, Form und Verteilung dieser γʹ-Phase abhängig ist. Es handelt sich also darum, diese Phase in eine geeignete Form bzw. in der Matrix in Lösung zu bringen, was erfindungs gemäss mit Hilfe der oben genannten Wärmebehandlung und gezielter Abkühlung des Werkstücks geschieht. Da die Hochtemperatureigenschaften der oxyddispersionsgehärteten Legierungen hauptsächlich durch die Dispersoide bestimmt sind, werden Kriechgrenze und Ermüdungsfestigkeit durch die mindestens teilweise Lösung der γʹ-Phase in der Matrix in Anbetracht der höchsten Einsatztemperatur der Legierung nicht nachteilig beeinflusst.The majority of the commercially used oxide-hardened nickel-based superalloys contain, apart from the dispersoids, the well-known γʹ phase in finely divided deposits. It could be shown that the ductility, especially in the low temperature range (eg at room temperature), is essentially dependent on the amount, shape and distribution of this γʹ phase. It is therefore a matter of bringing this phase into a suitable form or in solution in the matrix, which is according to the invention according to with the help of the above-mentioned heat treatment and targeted cooling of the workpiece. Since the high-temperature properties of the oxide dispersion-hardened alloys are mainly determined by the dispersoids, the creep limit and fatigue strength are not adversely affected by the at least partial dissolution of the γ in phase in the matrix in view of the highest operating temperature of the alloy.
Die Erfindung wird anhand der durch eine Figur näher erläuterten Ausführungsbeispiele beschrieben:The invention is described on the basis of the exemplary embodiments explained in more detail by a figure:
Dabei zeigt die Figur:The figure shows:
Ein Diagramn des Temperaturverlaufs in Funktion der Zeit bei der Durchführung des Verfahrens. T₁ ist die höchstzulässige Lösungstemperatur für die γʹ-Phase in der γ-Matrix, welche durch den Schmelzpunkt der tiefstschmelzenden Phase der Superlegierung bestimmt wird. Um mit Sicherheit ein Anschmelzen dieser Phase zu verhindern, muss T₁ noch um einen Wert von ca. 10 °C unter dem tiefsten Schmelzpunkt (Soliduspunkt) der Legierung 1egen. T₂ ist die mindest notwendige Lösungsglühtemperatur für die γʹ-Phase in der γʹ-Matrix. Dabei wird angenommen, dass nach einer endlichen Zeit, welche im Betrieb vert,retbar ist (d.h. nach eingen Stunden) die gesamte Masse der γʹ-Phase in feste Lösung in der γ-Matrix übergegangen ist. a ist die obere Grenze des Temperaturverlaufs der langsamen Abkühlung des Werkstücks, die durch praktische Betriebsbedingungen gegeben ist. Eine noch langsamere Abkühlung wäre unwirtschaftlich und ist nicht notwendig. b ist die untere Grenze des Temperaturverlaufs der langsamen Abkühlung des Werkstücks. Eine schnellere Abkühlung ist nicht zulässig, da sich dabei zumindest ein Teil der in Lösung befindlichen γʹ-Phase wieder ausscheiden würde. Kurve 1 bezieht sich auf den Temperaturverlauf der Wärmebehand ung des Werkstoffs MA 6000 gemäss Beispiel 1, Kurve 2 auf denjenigen von MA 6000 gemäss Beispiel 2. Der Temperaturverlauf nach Kurve 3 bezieht sich auf ein Werkstück der Legierung gemäss Beispiel 3.A diagram of the temperature curve as a function of time when carrying out the method. T₁ is the maximum permissible solution temperature for the γʹ phase in the γ matrix, which is determined by the melting point of the deep-melting phase of the superalloy. In order to prevent melting of this phase with certainty,
Siehe Kurve 1 der Figur!See
Aus einer oxyddispersionsgehärteten Nickelbasislegierung mit dem Handelsnamen MA 6000 (INCO) wurde eine prismatische Probe von 180 mm Länge, 50 mm Breite und 12 mm Dicke herausgearbeitet. Der Werkstoff hatte die nachfolgende Zusammensetzung:
Cr = 15 Gew.-%
W = 4,0 Gew.-%
Mo = 2,0 Gew.-%
Al = 4,5 Gew.-%
Ti = 2,5 Gew.-%
Ta = 2,0 Gew.-%
C = 0,05 Gew.-%
B = 0,01 Gew.-%
Zr = 0,15 Gew.-%
Y₂O₃ = 1,1 Gew.-%
Ni = Rest
A prismatic sample 180 mm long, 50 mm wide and 12 mm thick was machined from an oxide dispersion-hardened nickel-based alloy with the trade name MA 6000 (INCO). The material had the following composition:
Cr = 15% by weight
W = 4.0% by weight
Mo = 2.0% by weight
Al = 4.5% by weight
Ti = 2.5% by weight
Ta = 2.0% by weight
C = 0.05% by weight
B = 0.01% by weight
Zr = 0.15% by weight
Y₂O₃ = 1.1% by weight
Ni = rest
Das Ausgangsmaterial hatte beim Hersteller folgende thermomechanischen und thermischen Behandlungen durchgemacht:
- Warmstrangpressen
- Warmwalzen
- Zonenglühen auf längliches Grobkorn bei 1270 °C
- Glühen bei 1230 °C/1/2 h, Luftabkühlung
- Glühen bei 955 °C/2 h, Luftabkühlung
- Glühen bei 845 °C/24 h, Luftabkühlung
The raw material had undergone the following thermomechanical and thermal treatments at the manufacturer:
- hot extrusion
- hot rolling
- Zone annealing on elongated coarse grain at 1270 ° C
- Annealing at 1230 ° C / 1/2 h, air cooling
- Annealing at 955 ° C / 2 h, air cooling
- Annealing at 845 ° C / 24 h, air cooling
Die mechanischen Eigenschaften des in Form von langgestreckten Kristalliten vorliegenden Materials im Anlieferungszustand wurden wie folgt bestimmt (Werte bei Raumtemperatur in langer Querrichtung der Kristallite):
- Streckgrenze (0,2 %) 1095 MPa
- Zugfestigkeit 1187 MPa
- Dehnung 2,48 %
The mechanical properties of the material in the form of elongated crystallites in the delivery state were determined as follows (long-term values at room temperature Transverse direction of the crystallites):
- yield strength (0.2%) 1095 MPa
- tensile strength 1187 MPa
- elongation 2.48%
Das Werkstück wurde nun einer Wärmebehandlung wie folgt unterworfen:
- Erwärmen unter Argonatmosphäre bis auf 1180 °C
- Lösungsglühen bei 1180 °C während 2 1/2 h
- Abkühlen bis auf 640 °C mit einer Geschwindigkeit von 0,5 °C/min
- Abkühlen bis auf Raumtemperatur an Luft
The workpiece was then subjected to a heat treatment as follows:
- Warming up to 1180 ° C under an argon atmosphere
- Solution annealing at 1180 ° C for 2 1/2 hours
- Cool down to 640 ° C at a rate of 0.5 ° C / min
- Cool down to room temperature in air
Nach dieser Behandlung stellten sich die mechanischen Eigenschaften wie folgt (Werte bei Raumtepmeratur in langer Querrichtung der Kristallite):
- Streckgrenze (0,2 %) 930 MPa
- Zugfestigkeit 1147 MPa
- Dehnung 4,30 %
After this treatment, the mechanical properties were as follows (values for room temperature in the long transverse direction of the crystallites):
- yield strength (0.2%) 930 MPa
- tensile strength 1147 MPa
- elongation 4.30%
Siehe Kurve 2 der Figur!See
Aus der Nickelbasislegierung MA 6000 mit der Zusammensetzung gemäss Beispiel 1 wurde eine Gasturbinenschaufel mit folgenden Massen des Schaufelblattes (Tragflügelprofil) herausgearbeitet:
Höhe = 160 mm
Breite = 40 mm
max. Dicke = 8 mm
Profilhöhe = 13 mm
A gas turbine blade with the following dimensions of the airfoil (airfoil profile) was machined from the nickel-based alloy MA 6000 with the composition according to Example 1:
Height = 160 mm
Width = 40 mm
Max. Thickness = 8 mm
Profile height = 13 mm
Das Ausgangsmaterial hatte beim Hersteller folgende thermomechanischen und thermischen Behandlungen durchgemacht:
- Warmstrangpressen
- Zonenglühen auf längliches Grobkorn bei 1270 °C
The raw material had undergone the following thermomechanical and thermal treatments at the manufacturer:
- hot extrusion
- Zone annealing on elongated coarse grain at 1270 ° C
Die mechanischen Eigenschaften des in Form von langgestreckten Kristalliten vorliegenden Materials im Anlieferungszustand wurden wie folgt bestimmt (Werte bei Raumtemperatur):
In Längsrichtung der Kristallite:
- Streckgrenze (0,2 %) 1186 MPa
- Zugfestigkeit 1210 MPa
- Dehnung 1,37 %
In Querrichtung der Kristallite:
- Streckgrenze (0,2 %) 1228 MPa
- Zugfestigkeit 1232 MPa
- Dehnung 0,33 %
The mechanical properties of the material in the form of elongated crystallites in the delivery state were determined as follows (values at room temperature):
In the longitudinal direction of the crystallites:
- yield strength (0.2%) 1186 MPa
- tensile strength 1210 MPa
- elongation 1.37%
In the transverse direction of the crystallites:
- yield strength (0.2%) 1228 MPa
- tensile strength 1232 MPa
- elongation 0.33%
Das Werkstück wurde nun einer Wärmebehandlung wie folgt unterworfen:
- Erwärmen unter Argonatmosphäre bis auf 1260 °C
- Lösungsglühen bei 1260 °C während 1 h
- Abkühlen bis auf 600 °C mit einer Geschwindigkeit von 0,5 °C/min
- Abkühlen bis auf Raumtemperatur an Luft
The workpiece was then subjected to a heat treatment as follows:
- Warming up to 1260 ° C under an argon atmosphere
- Solution annealing at 1260 ° C for 1 h
- Cool down to 600 ° C at a rate of 0.5 ° C / min
- Cool down to room temperature in air
Nach dieser Behandlung stellten sich die mechanischen Eigenschaften wie folgt (Werte bei Raumtemperatur):
In Längsrichtung der Kristallite:
- Streckgrenze (0,2 %) 1028 MPa
- Zugfestigkeit 1200 MPa
- Dehnung 5,37 %
In Querrichtung der Kristallite:
- Streckgrenze (0,2 %) 1038 MPa
- Zugfestigkeit 1165 MPa
- Dehnung 1,97 %
After this treatment, the mechanical properties were as follows (values at room temperature):
In the longitudinal direction of the crystallites:
- yield strength (0.2%) 1028 MPa
-
- elongation 5.37%
In the transverse direction of the crystallites:
- yield strength (0.2%) 1038 MPa
- tensile strength 1165 MPa
- elongation 1.97%
Aus einer oxyddispersionsgehärteten Nickelbasislegierung wurde eine prismatische Probe von 120 mm Länge, 40 mm Breite und 10 mm Dicke herausgearbeitet. Der Werkstoff hatte die nachfolgende Zusammensetzung:
Cr = 19,6 Gew.-%
W = 3,6 Gew.-%
Mo = 2,0 Gew.-%
Al = 6,0 Gew.-%
Fe = 1,4 Gew.-%
C = 0,04 Gew.-%
B = 0,017 Gew.-%
Zr = 0,12 Gew.-%
Y₂O₃ = 1,1 Gew.-%
Ni = Rest
A prismatic sample 120 mm long, 40 mm wide and 10 mm thick was machined from an oxide dispersion-hardened nickel-based alloy. The material had the following composition:
Cr = 19.6% by weight
W = 3.6% by weight
Mo = 2.0% by weight
Al = 6.0% by weight
Fe = 1.4% by weight
C = 0.04% by weight
B = 0.017% by weight
Zr = 0.12% by weight
Y₂O₃ = 1.1% by weight
Ni = rest
Das Ausgangsmaterial hatte beim Hersteller folgende thermomechanischen und thermischen Behandlungen durchgemacht:
- Warmstrangpressen
- Zonenglühen auf längliches Grobkorn bei 1260 °C
- Glühen bei 1230 °C/1/2 h, Luftabkühlung
- Glühen bei 955 °C/2 h, Luftabkühlung
- Glühen bei 845 °C/24 h, Luftabkühlung
The raw material had undergone the following thermomechanical and thermal treatments at the manufacturer:
- hot extrusion
- Zone annealing on elongated coarse grain at 1260 ° C
- Annealing at 1230 ° C / 1/2 h, air cooling
- Annealing at 955 ° C / 2 h, air cooling
- Annealing at 845 ° C / 24 h, air cooling
Die mechanischen Eigenschaften des in Form von langgestreckten Kristalliten vorliegenden Materials im Anlieferungszustand wurden wie folgt bestimmt (Werte bei Raumtemperatur in Querrichtung der Kristallite):
- Streckgrenze (0,2 %) 1316 MPa
- Zugfestigkeit 1348 MPa
- Dehnung 0,41 %
The mechanical properties of the material in the form of elongated crystallites as delivered were determined as follows (values at room temperature in the transverse direction of the crystallites):
- yield strength (0.2%) 1316 MPa
- tensile strength 1348 MPa
- elongation 0.41%
Das Werkstück wurde nun einer Wärmebehandlung wie folgt unterzogen:
- Erwärmen unter Argonatmosphäre bis auf 1260 °C
- Lösungsglühen bei 1260 °C während 1 h
- Abkühlen bis auf 700 °C mit einer Geschwindigkeit von 0,4 °C/min
- Abkühlen bis auf Raumtemperatur an Luft
The workpiece was then subjected to a heat treatment as follows:
- Warming up to 1260 ° C under an argon atmosphere
- Solution annealing at 1260 ° C for 1 h
- Cool down to 700 ° C at a rate of 0.4 ° C / min
- Cool down to room temperature in air
Nach dieser Behandlung stellten sich die mechanischen Eigenschaften wie folgt (Werte bei Raumtemperatur in Querrichtung der Kristallite):
- Streckgrenze (0,2 %) 1095 MPa
- Zugfestigkeit 1221 MPa
- Dehnung 1,29 %
After this treatment, the mechanical properties were as follows (values at room temperature in the transverse direction of the crystallites):
- yield strength (0.2%) 1095 MPa
- tensile strength 1221 MPa
- elongation 1.29%
Die Erfindung ist nicht auf die Ausführungsbeispiele beschränkt. Die Lösungsglühtemperatur für diese Art oxyddispersionsgehärtete Nickelbasis-Superlegierungen kann innerhalb der Grenzen von T₂ (1160 °C) und T₁ (1280 °C) gewählt werden. Die Zeitdauer der Lösungsglühung liegt je nach Werkstück und betrieblichen Erfordernissen vorzugsweise zwischen 1/2 h und 5 h. Die Abkühlungsgeschwindigkeit während des Abkühlungsprozesses nach der Lösungsglühung kann innerhalb der Grenzen von 5 °C/min und 0,1 °C/min gewählt werden. Bevorzugt werden ca. 0,5 °C/min. Die untere Temperatur T₃, bis zu welcher die Wärmebehandlung mit definierter Abkühlungsgeschwindigkeit durchgeführt werden soll, kann frei zwischen den Grenzen von 500 und 700 °C gewählt werden.The invention is not restricted to the exemplary embodiments. The solution annealing temperature for this type of oxide dispersion hardened nickel-based superalloys can be selected within the limits of T₂ (1160 ° C) and T₁ (1280 ° C). Depending on the workpiece and operational requirements, the solution annealing time is preferably between 1/2 h and 5 h. The cooling rate during the cooling process after solution annealing can be selected within the limits of 5 ° C / min and 0.1 ° C / min. Approx. 0.5 ° C / min are preferred. The lower temperature T₃ up to which the heat treatment is to be carried out at a defined cooling rate can be chosen freely between the limits of 500 and 700 ° C.
Aus den Beispielen geht hervor, dass die im Zugversuch bei Raumtemperatur festgestellte Dehnung am fertigen Werkstück in der Längsrichtung der Stengelkristallite bis ca. auf das Doppelte, in der langen Querrichtung durchschnittlich bis auf das Fünffache gesteigert werden konnte. Weitere Versuche zeigten, dass damit auch eine namhafte Steigerung der Duktilität verbunden ist.The examples show that the elongation of the finished workpiece in the tensile test at room temperature in the longitudinal direction of the stem crystallites could be increased by approximately twice and in the long transverse direction on average by up to five times. Further tests showed that this also involves a notable increase in ductility.
Claims (4)
Cr = 15 Gew.-%
W = 4,0 Gew.-%
Mo = 2,0 Gew.-%
Al = 4,5 Gew.-%
Ti = 2,5 Gew.-%
Ta = 2,0 Gew.-%
C = 0,05 Gew.-%
B = 0,01 Gew.-%
Zr = 0,15 Gew.-%
Y₂O₃ = 1,1 Gew.-%
Ni = Rest
besteht, und dass das Werkstück unter Argonatmosphäre während 1 h einer Lösungsglühung bei einer Temperatur von 1260 °C unterworfen und anschliessend mit einer Geschwindigkeit von 0,5 °C/min bis auf eine Temperatur von 500 bis 700 °C abgekühlt und daraufhin in Luft bis auf Raumtemperatur abgekühlt wird.2. The method according to claim 1, characterized in that the workpiece made of a material of the following composition
Cr = 15% by weight
W = 4.0% by weight
Mo = 2.0% by weight
Al = 4.5% by weight
Ti = 2.5% by weight
Ta = 2.0% by weight
C = 0.05% by weight
B = 0.01% by weight
Zr = 0.15% by weight
Y₂O₃ = 1.1% by weight
Ni = rest
and that the workpiece is under an argon atmosphere for 1 hour solution annealing at a temperature of 1260 ° C subjected and then cooled at a rate of 0.5 ° C / min to a temperature of 500 to 700 ° C and then cooled in air to room temperature.
Cr = 15 Gew.-%
W = 4,0 Gew.-%
Mo = 2,0 Gew.-%
Al = 4,5 Gew.-%
Ti = 2,5 Gew.-%
Ta = 2,0 Gew.-%
C = 0,05 Gew.-%
B = 0,01 Gew.-%
Zr = 0,15 Gew.-%
Y₂O₃ = 1,1 Gew.-%
Ni = Rest
besteht, und dass das Werkstück unter Argonatmosphäre während 2 1/2 h einer Lösungsglühung bei einer Temperatur von 1180 °C unterworfen und anschliessend mit einer Geschwindigkeit von 0,5 °C/min bis auf eine Temperatur von 500 bis 700 °C abgekühlt und daraufhin in Luft bis auf Raumtemperatur abgekühlt wird.3. The method according to claim 1, characterized in that the workpiece made of a material of the following composition
Cr = 15% by weight
W = 4.0% by weight
Mo = 2.0% by weight
Al = 4.5% by weight
Ti = 2.5% by weight
Ta = 2.0% by weight
C = 0.05% by weight
B = 0.01% by weight
Zr = 0.15% by weight
Y₂O₃ = 1.1% by weight
Ni = rest
and that the workpiece is subjected to solution annealing under an argon atmosphere for 2 1/2 hours at a temperature of 1180 ° C. and then cooled at a speed of 0.5 ° C./min to a temperature of 500 to 700 ° C. and then is cooled in air to room temperature.
Cr = 19,6 Gew.-%
W = 3,6 Gew.-%
Mo = 2,0 Gew.-%
Al = 6,0 Gew.-%
Fe = 1,4 Gew.-%
C = 0,04 Gew.-%
B = 0,017 Gew.-%
Zr = 0,12 Gew.-%
Y₂O₃ = 1,1 Gew.-%
Ni = Rest
besteht, und dass das Werkstück unter Argonatmosphäre während 1 h einer Lösungsglühung bei einer Temperatur von 1260 °C unterworfen und anschliessend mit einer Geschwindigkeit von 0,4 °C/min bis auf eine Temperatur von 500 bis 700 °C abgekühlt und daraufhin in Luft bis auf Raumtemperatur abgekühlt wird.4. The method according to claim 1, characterized in that the workpiece made of a material of the following composition
Cr = 19.6% by weight
W = 3.6% by weight
Mo = 2.0% by weight
Al = 6.0% by weight
Fe = 1.4% by weight
C = 0.04% by weight
B = 0.017% by weight
Zr = 0.12% by weight
Y₂O₃ = 1.1% by weight
Ni = rest
and that the workpiece is subjected to solution annealing at an temperature of 1260 ° C for 1 h under an argon atmosphere and then cooled to a temperature of 500 to 700 ° C at a speed of 0.4 ° C / min and then in air until is cooled to room temperature.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH5111/86 | 1986-12-19 | ||
| CH5111/86A CH671583A5 (en) | 1986-12-19 | 1986-12-19 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0274631A1 true EP0274631A1 (en) | 1988-07-20 |
| EP0274631B1 EP0274631B1 (en) | 1991-03-06 |
Family
ID=4288113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP87117524A Expired - Lifetime EP0274631B1 (en) | 1986-12-19 | 1987-11-27 | Process for increasing the room temperature ductility of an oxide dispersion hardened nickel base superalloy article having a coarse columnar grain structure directionally oriented along the length |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US4795507A (en) |
| EP (1) | EP0274631B1 (en) |
| JP (1) | JPS63162846A (en) |
| CH (1) | CH671583A5 (en) |
| DE (1) | DE3768464D1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0398121A1 (en) * | 1989-05-16 | 1990-11-22 | Asea Brown Boveri Ag | Process for producing coarse columnar grains directionally oriented along their length in an oxide dispersion hardened nickel base superalloy |
| EP0442545A1 (en) * | 1990-02-14 | 1991-08-21 | PM HOCHTEMPERATUR-METALL GmbH | Process for producing heat treated profiles and bodies |
| EP0456119A1 (en) * | 1990-05-07 | 1991-11-13 | PM HOCHTEMPERATUR-METALL GmbH | Nickel-base superalloy |
| EP0761826A2 (en) * | 1995-08-28 | 1997-03-12 | PLANSEE Aktiengesellschaft | Method for manufacturing seamless pipes |
| EP0767252A1 (en) * | 1995-10-02 | 1997-04-09 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
| EP3421621B1 (en) | 2017-06-28 | 2021-01-06 | United Technologies Corporation | Method for heat treating components |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| ATE123076T1 (en) * | 1990-03-20 | 1995-06-15 | Asea Brown Boveri | METHOD FOR PRODUCING LONGITUDINALLY DIRECTED COARSE-GRAINED STEM CRYSTALS IN A WORKPIECE CONSISTING OF AN OXIDE DISPERSION HARDENED NICKEL-BASED SUPER ALLOY. |
| KR100250810B1 (en) * | 1997-09-05 | 2000-04-01 | 이종훈 | Annealing process of ni-base alloy for corrosion resistance improvement |
| CA2287116C (en) * | 1999-10-25 | 2003-02-18 | Mitsubishi Heavy Industries, Ltd. | Process for the heat treatment of a ni-base heat-resisting alloy |
| EP2205771B1 (en) | 2007-10-25 | 2019-04-03 | GKN Aerospace Sweden AB | Method, nickel base alloy and component |
| KR101007582B1 (en) * | 2008-06-16 | 2011-01-12 | 한국기계연구원 | Method of heat treatment of Ni based superalloy for wave type grain-boundary and Ni based superalloy the same |
| CH705750A1 (en) * | 2011-10-31 | 2013-05-15 | Alstom Technology Ltd | A process for the production of components or portions, which consist of a high-temperature superalloy. |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB943141A (en) * | 1961-01-24 | 1963-11-27 | Rolls Royce | Method of heat treating nickel alloys |
| US3746581A (en) * | 1972-01-31 | 1973-07-17 | Nat Nickel Co Inc | Zone annealing in dispersion strengthened materials |
| US3871928A (en) * | 1973-08-13 | 1975-03-18 | Int Nickel Co | Heat treatment of nickel alloys |
| EP0045984A1 (en) * | 1980-08-08 | 1982-02-17 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Process for manufacturing an article from a heat-resisting alloy |
| EP0194683A1 (en) * | 1985-03-13 | 1986-09-17 | Inco Alloys International, Inc. | Nickel-chromium alloys having a dispersed phase |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH554972A (en) * | 1972-01-05 | 1974-10-15 | ||
| JPS512548B2 (en) * | 1972-10-09 | 1976-01-27 | ||
| CH580197B5 (en) * | 1973-10-18 | 1976-09-30 | Ciba Geigy Ag | |
| CH963874A4 (en) * | 1974-07-12 | 1977-04-29 | ||
| FR2451270A1 (en) * | 1979-03-12 | 1980-10-10 | Sublistatic Holding Sa | NOVEL AUXILIARY DRY THERMO-PRINTING MEDIA, PREPARATION METHODS THEREOF AND INKS FOR PRINTING SUCH MEDIA |
| US4518442A (en) * | 1981-11-27 | 1985-05-21 | United Technologies Corporation | Method of producing columnar crystal superalloy material with controlled orientation and product |
| EP0115092B1 (en) * | 1983-02-01 | 1987-08-12 | BBC Brown Boveri AG | Structural element with a high corrosion and oxidation resistance made from a dispersion-hardened superalloy, and process for its manufacture |
| US4502896A (en) * | 1984-04-04 | 1985-03-05 | Raychem Corporation | Method of processing beta-phase nickel/titanium-base alloys and articles produced therefrom |
-
1986
- 1986-12-19 CH CH5111/86A patent/CH671583A5/de not_active IP Right Cessation
-
1987
- 1987-11-27 DE DE8787117524T patent/DE3768464D1/en not_active Expired - Fee Related
- 1987-11-27 EP EP87117524A patent/EP0274631B1/en not_active Expired - Lifetime
- 1987-12-10 US US07/131,361 patent/US4795507A/en not_active Expired - Fee Related
- 1987-12-14 JP JP62314335A patent/JPS63162846A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB943141A (en) * | 1961-01-24 | 1963-11-27 | Rolls Royce | Method of heat treating nickel alloys |
| US3746581A (en) * | 1972-01-31 | 1973-07-17 | Nat Nickel Co Inc | Zone annealing in dispersion strengthened materials |
| US3871928A (en) * | 1973-08-13 | 1975-03-18 | Int Nickel Co | Heat treatment of nickel alloys |
| EP0045984A1 (en) * | 1980-08-08 | 1982-02-17 | BBC Aktiengesellschaft Brown, Boveri & Cie. | Process for manufacturing an article from a heat-resisting alloy |
| EP0194683A1 (en) * | 1985-03-13 | 1986-09-17 | Inco Alloys International, Inc. | Nickel-chromium alloys having a dispersed phase |
Non-Patent Citations (1)
| Title |
|---|
| POWDER METALLURGY, Nr. 4, 1981, Seiten 191-195, The Metals Society, US; R.C. BENN et al.: "Scale-up thermomechanical processing of MA 6000E" * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0398121A1 (en) * | 1989-05-16 | 1990-11-22 | Asea Brown Boveri Ag | Process for producing coarse columnar grains directionally oriented along their length in an oxide dispersion hardened nickel base superalloy |
| EP0442545A1 (en) * | 1990-02-14 | 1991-08-21 | PM HOCHTEMPERATUR-METALL GmbH | Process for producing heat treated profiles and bodies |
| EP0456119A1 (en) * | 1990-05-07 | 1991-11-13 | PM HOCHTEMPERATUR-METALL GmbH | Nickel-base superalloy |
| EP0761826A2 (en) * | 1995-08-28 | 1997-03-12 | PLANSEE Aktiengesellschaft | Method for manufacturing seamless pipes |
| EP0761826A3 (en) * | 1995-08-28 | 1998-10-28 | PLANSEE Aktiengesellschaft | Method for manufacturing seamless pipes |
| EP0767252A1 (en) * | 1995-10-02 | 1997-04-09 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
| US5725692A (en) * | 1995-10-02 | 1998-03-10 | United Technologies Corporation | Nickel base superalloy articles with improved resistance to crack propagation |
| US5788785A (en) * | 1995-10-02 | 1998-08-04 | United Technology Corporation | Method for making a nickel base alloy having improved resistance to hydrogen embittlement |
| KR100391737B1 (en) * | 1995-10-02 | 2003-10-17 | 유나이티드 테크놀로지스 코포레이션 | Nickel-based superalloy products with improved crack propagation resistance |
| EP3421621B1 (en) | 2017-06-28 | 2021-01-06 | United Technologies Corporation | Method for heat treating components |
Also Published As
| Publication number | Publication date |
|---|---|
| EP0274631B1 (en) | 1991-03-06 |
| CH671583A5 (en) | 1989-09-15 |
| DE3768464D1 (en) | 1991-04-11 |
| US4795507A (en) | 1989-01-03 |
| JPS63162846A (en) | 1988-07-06 |
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