EP0362661B1 - Gegossenes aus stengelförmigen Kristallen bestehendes hohles Werkstück auf Nickel basierender Legierung sowie die Legierung und Wärmebehandlung für dessen Herstellung - Google Patents
Gegossenes aus stengelförmigen Kristallen bestehendes hohles Werkstück auf Nickel basierender Legierung sowie die Legierung und Wärmebehandlung für dessen Herstellung Download PDFInfo
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- EP0362661B1 EP0362661B1 EP89117666A EP89117666A EP0362661B1 EP 0362661 B1 EP0362661 B1 EP 0362661B1 EP 89117666 A EP89117666 A EP 89117666A EP 89117666 A EP89117666 A EP 89117666A EP 0362661 B1 EP0362661 B1 EP 0362661B1
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- 229910045601 alloy Inorganic materials 0.000 title claims description 65
- 239000000956 alloy Substances 0.000 title claims description 65
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims description 36
- 238000010438 heat treatment Methods 0.000 title claims description 34
- 229910052759 nickel Inorganic materials 0.000 title claims description 15
- 230000032683 aging Effects 0.000 claims description 23
- 230000003647 oxidation Effects 0.000 claims description 17
- 238000007254 oxidation reaction Methods 0.000 claims description 17
- 238000005266 casting Methods 0.000 claims description 14
- 239000010936 titanium Substances 0.000 claims description 12
- 238000001816 cooling Methods 0.000 claims description 11
- 239000011651 chromium Substances 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 9
- 229910052735 hafnium Inorganic materials 0.000 claims description 8
- 229910000601 superalloy Inorganic materials 0.000 claims description 8
- 229910052720 vanadium Inorganic materials 0.000 claims description 8
- 239000012535 impurity Substances 0.000 claims description 7
- 229910052726 zirconium Inorganic materials 0.000 claims description 7
- 230000001590 oxidative effect Effects 0.000 claims description 6
- 229910052721 tungsten Inorganic materials 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 5
- 229910052796 boron Inorganic materials 0.000 claims description 5
- 230000005496 eutectics Effects 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims description 5
- 229910052702 rhenium Inorganic materials 0.000 claims description 5
- 229910052715 tantalum Inorganic materials 0.000 claims description 5
- 229910052719 titanium Inorganic materials 0.000 claims description 5
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 238000005495 investment casting Methods 0.000 claims description 4
- 238000007711 solidification Methods 0.000 claims description 4
- 230000008023 solidification Effects 0.000 claims description 4
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000010941 cobalt Substances 0.000 claims description 2
- 229910017052 cobalt Inorganic materials 0.000 claims description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims description 2
- 210000001787 dendrite Anatomy 0.000 claims description 2
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims description 2
- 239000011733 molybdenum Substances 0.000 claims description 2
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 claims description 2
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 2
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 2
- 239000010937 tungsten Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims 1
- 230000035882 stress Effects 0.000 description 27
- 239000008186 active pharmaceutical agent Substances 0.000 description 13
- 238000005336 cracking Methods 0.000 description 6
- 239000013078 crystal Substances 0.000 description 6
- 238000011156 evaluation Methods 0.000 description 6
- 229910052751 metal Inorganic materials 0.000 description 6
- 239000002184 metal Substances 0.000 description 6
- 230000000750 progressive effect Effects 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 239000007789 gas Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 238000007792 addition Methods 0.000 description 3
- 230000007797 corrosion Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000011282 treatment Methods 0.000 description 2
- 229910000951 Aluminide Inorganic materials 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000001307 helium Substances 0.000 description 1
- 229910052734 helium Inorganic materials 0.000 description 1
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 230000009257 reactivity Effects 0.000 description 1
- 238000010583 slow cooling Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
Images
Classifications
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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%
-
- 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
- This invention relates to cast directionally solidified columnar grain nickel base alloy articles and, more particularly, to such an article of outstanding elevated temperature surface stability as represented by oxidation resistance, particularly in thin walled hollow articles, and to the alloy and neat treatment for making such article.
- such structures have been generated by the well known precision casting techniques of solidifying a molten metal directionally (directional solidification) to cause the solidifying crystals or grains to be elongated. If only one grain is allowed to grow in the article during solidification, for example, through choking out others or using a seed crystal, an article of a single crystal and substantially no grain boundaries results.
- the grain boundaries in such an article are substantially all longitudinal grain boundaries, it is important in an article casting that longitudinal mechanical properties, such as stress rupture life and ductility, be very good, along with good transverse mechanical properties and good alloy surface stability. With this property balance in the article, the article alloy must be capable of being cast and directionally solidified in complex shapes and generally with complex internal cavities and relatively thin walls without cracking. So called “thin-wall” hollow castings have presented difficult quality problems to article casters using the well known "lost wax" type of precision casting methods with alloys designed for improved properties: though the alloy properties are good and within desired limits, thin wall castings, for example with a wall less than about 0.889mm (0.035 inch) thick, generally cracked during multicolumnar grain directional solidification.
- the present invention provides a nickel base superalloy consisting of in weight percent 0.12% carbon, 1.5% hafnium, 12% cobalt, 6.35% tantalum, 6.8% chromium, 1.5% molybdenum, 4.9% tungsten, 6.15% aluminum, 2.8% rhenium, 0.015% boron, the substantial absence of zirconium, the substantial absence of titanium, the substantial absence of vanadium and the balance of nickel and incidental impurities.
- Articles may be formed from the above alloy and are characterized by outstanding elevated temperature surface stability for a directionally solidified article, resulting from an alloy specification enhanced, in one form, by heat treatment and by an improved combination and balance between longitudinal and transverse stress rupture properties.
- the article has at least one internal cavity and includes an integral cast wall substantially free of a major crack, the wall having a thickness of less than about 0.889mm (0.035 inch).
- Such heat treatment comprises a combination of at least three progressive heating steps including a solutioning step, a preliminary, first aging step and a second aging step, to improve stress rupture properties of the article.
- the present invention also provides a method of heat treating a cast nickel base alloy article made of an alloy consisting of, in weight percent, 0.1-0.15 C, 0.3-2 Hf, 11-14 Co, 5-9 Ta, less than 0.05 Zr, no more than 1 of V, no more than 1 of Ti, 5-10 Cr, 0.5-3 Mo, 4-7 W, 5-7 Al, 1.5-4 Re, 0.005-0.03 B, up to 1.5 Nb, up to 0.5 Y and the balance Ni and incidental impurities comprising the steps of :
- the solutioning temperature is in the range of 1246-1293°C (2275-2360°F) and the heating time is at least about 30 minutes.
- the drawing is a graphical comparison of oxidation resistance of the alloy associated with the present invention with other alloys.
- the nickel base alloy of the present invention is particularly characterized by the relatively high C content in combination with a relatively large amount of Hf and additions of Co and Ta. This, along with the intentional control and limitation of the elements V, Zr and Ti, enabled the total alloy to have, for a DS structure, outstanding oxidation resistance and the good DS castability and resistance to grain boundary and fatigue cracking to the point at which thin walls of less than 0.889mm (0.035 inch) can be DS cast with elongated grains substantially crack free.
- Other elements in the alloy contributing to its unique mechanical properties and surface stability, in a nickel base, are Cr, Mo, W, Al, Re and B.
- the resultant article with an unusual, unique combination of mechanical properties and surface stability, is particularly useful in making hollow, air cooled, high temperature operating components such as blading members (blades and vanes) of the type used in the strenuous environment of the turbine section of gas turbine engines.
- blading members blades and vanes
- the crack free condition of thin walls associated with internal cooling passages is essential to safe, efficient engine operation.
- a selection of nickel base superalloys sometimes used or designed for use in gas turbine engine turbine components is presented in the following Table II along with a form of the particular alloy associated with the present invention.
- the alloy identified as Rene' N5, designed for use in making single crystal alloy articles, is described in US-A-5100484 and GB-A-2235697; the alloy identified as Rene' 150, designed for use as a DS columnar grain article, is described in the U.S. Patent 4,169,742. Also included in Table II are the castability ratings of such alloys.
- the data of Table III show primarily the benefit and criticality of including Co at a level greater than 7.5 wt% (for example about 10 wt %) up to about 12 wt%, in combination with Hf in the range of about 0.3 - 1.6 wt%.
- the alloy modification of Rene' N5 alloy had reduced longitudinal stress rupture strength due to dilution of the hardening elements from the addition of more Co to the Rene' N5 alloy base chemistry of Table II above, at a C level of about 0.05 wt%.
- vanadium can detract from the surface stability, i.e., hot corrosion and oxidation resistance; Zr can increase crackability; and Ti can seriously reduce oxidation resistance. Therefore, these elements have been controlled and limited to the ranges in weight percent of less than 1 V, 0.05 Zr and 1.5 Ti, preferably less than 0.1V, 0.03 Zr and 0.02 Ti. While yttrium is helpful in improving oxidation resistance, it can cause grain boundary weakening; thus, it is limited to amounts less than 0.1% in the alloys of the invention. Cr is included primarily for its contribution to oxidation and hot corrosion resistance; Mo, W and Re primarily for matrix strengthening and B to enhance grain boundary strength.
- Rene' 150 alloys as Rene' 150 were very good and within the acceptable range for thin wall castings, their surface stabilities were unacceptable for certain high temperature applications under strenuous environments.
- a comparison of the elevated temperature surface stability of Rene' 150 alloy and the alloy of the present invention has shown that during 100 hours exposure to Mach 1 air, Rene' 150 alloy at 1135°C (2075°F) lost 1.27-1.65mm (50-65 mils) of metal per specimen side, whereas the alloy of the present invention, in the form shown in Table II, at a higher temperature of 1177°C (2150°F) and a longer exposure time of 150 hours lost only 0.038mm (1.5 mils) per specimen side, i.e. less than about 0.127mm (5 mils) per side according to this invention.
- Rene' 150 alloy at 1135°C (2075°F) in Mach 1 airflow lost 1.016mm (40 mils) per specimen side after 82 hours.
- MA754 alloy One nickel base alloy considered to have outstanding elevated temperature oxidation resistance is MA754 alloy, identified in Table II. Such alloy is a wrought rather than cast alloy but is included here for further comparison with the oxidation resistance of the present invention. After exposure of a specimen of MA 754 at Mach 1 airflow and 1177°C (2150°F) loss of 0.254mm (10 mils) per specimen side occurred after 140 hours exposure. Confirming the outstanding elevated temperature oxidation resistance of the present invention were tests conducted on specimens from a 1361 kg (3000 pound) heat of the alloy of the present invention.
- an important characteristic of the present invention is its improved longitudinal stress rupture strength and improved balance between longitudinal and transverse stress rupture properties along with the outstanding surface stability discussed above. It exhibits, in a DS columnar grain article, the good stress rupture strength of Rene' 150 alloy and outstanding oxidation resistance of the single crystal article of the Rene' N5 composition in Table II above.
- Table IV compares certain stress rupture properties: TABLE IV LONGITUDINAL STRESS RUPTURE DATA (uncoated, 0.160 diameter bars) TEMP °C (°F) STRESS MPa (ksi) ALLOY/RUPTURE LIFE (hours) INVENTION(DS) RENE' 150(DS) RENE' N4(a) 982 (1800) 276 (40) 40 - 70 40 - 70 60 871 (1600) 552 (80) 45 - 100 50 - 90 65 (a) Single crystal, diffusion aluminide coated.
- the transverse stress rupture strength at 982°C (1800°F) and 221 MPa (32,000 psi)(32 ksi) nominally was in the range of about 80 - 120 hours, as shown in Table V below.
- a preferred form of the heat treatment of the present invention includes an additional progressive combination of aging steps: a primary, first aging to improve ductility and transverse stress rupture properties, and two additional aging treatments at temperatures consecutively lower than that of the primary age to further optimize the gamma prime precipitate.
- the heat treatments identified as A, B, C and D, summarize the heating steps, first with a solution temperature in the range of 1260°C-1279°C (2300-2335°F) for 2 hours. This is followed by a progressive combination and series of aging steps identified in a manner widely used and understood in the metallurgical art.
- the solution and aging steps were conducted in a non-oxidizing atmosphere: vacuum, argon or helium. Cooling below 649°C (1200°F) conducted between aging steps, need not be conducted in such an atmosphere.
- heat treatment D involving a unique relatively slow cooling step from the first aging to the temperature at which the second aging temperature was to be conducted, resulted in the best combination of properties.
- a substantially full solutioning step is included. This is in contrast with the partial solutioning commonly used with such DS articles made from alloys from Table II such as Rene' 150, certain properties of which are affected detrimentally by a full solution heat treatment.
- solutioning of at least about 90% of the gamma - gamma prime eutectic and coarse secondary gamma prime and with less than about 4%incipient melting is important because the stress rupture life is increased with increased solutioning of the gamma prime eutectic and coarse secondary gamma prime.
- Table VI compares amount of solutioning and stress rupture life for the alloy associated with the present invention. TABLE VI Effect of Solutioning on Stress Rupture Life % Unsolutioned 982°C (1800°F) Stress Rupture Life 20 x 10 - 15 2x 0 - 5 3x
- cooling for example to a temperature in the range of 1107-1135°C (2025-2075°F) be at a rate of at least 56°C (100°F) per minute.
- cooling for example to a temperature in the range of 1107-1135°C (2025-2075°F) be at a rate of at least 56°C (100°F) per minute.
- more rapid cooling rates have a beneficial effect on properties such as stress rupture strength.
- the heat treatment of the present invention is further characterized by a progressive combination of aging stops after solutioning
- the first or primary age is conducted in a temperature range of 1107-1135°C (2025-2075°F) in a non-oxidizing atmosphere, for example for about 1 - 10 hours, to improve ductility and stress rupture strength of the article.
- cooling for example to the range of 1066-1093°C (1950-2000°F) be at a rate of about 42°C (75°F) per hour prior to further cooling.
- a second aging step at a temperature lower than the first aging, for example in the range of 1066-1093°C (1950-2000°F) for about 4-12 hours, generally about 4-8 hours, enables growth of the gamma prime to improve ductility, As can be seen from the data of Table V, this unique progressive combination of heating steps results in a structure of improved mechanical properties and enables heat treatment of castings having thin walls without detrimental affect on such walls.
- a final aging step generally is beneficial, for example, in the range of 885-913°C (1625-1675°F) for about 2-10 hours, typically about 4-8 hours.
- the heat treatment of the present invention in connection with the DS cast article utilizing the alloy associated with this invention maximizes longitudinal stress rupture strength while retaining acceptable transverse strength and ductility. This is due, at least in part, to the increased solutioning of the gamma prime at a relatively higher temperature, Introduction of a primary or first aging in the range of 1107-1135°C (2025-2075°F) followed by a relatively slow cool (for example, about 1 hour) to a temperature in the range of 1066-1093°C (1950-2000°F) before further cooling resulted in a further improvement in longitudinal stress rupture life coupled with improved transverse stress rupture properties.
- the combination of alloy selection, casting practice, and heat treatment, according to the present invention enables provision of an improved DS columnar grain article including a thin wall of less than about 0.889mm (0.035 inch) substantially free of cracks.
- the grain boundaries and primary dendritic orientation is approximately straight and parallel.
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Claims (10)
- Superlegierung auf Nickelbasis, bestehend aus, in Gew.-%, 0,12% Kohlenstoff, 1,5% Hafnium, 12% Cobalt, 6,35% Tantal, 6,8% Chrom, 1,5% Molybdän, 4,9% Wolfram, 6,15% Aluminium, 2,8% Rhenium, 0,015% Brom, wobei Zirkonium, Titan und Vanadium im wesentlichen abwesend und der Rest Nickel und übliche Verunreinigungen sind.
- Gegenstand aus der Legierung nach Anspruch 1 mit einem inneren Hohlraum innerhalb einer äußeren Gegenstandsoberfläche, wobei der Hohlraum eine integral gegossene Wand einschließt, die im wesentlichen frei von Rissen ist und eine Dicke von weniger als etwa 0,889 mm (0,035 inch) hat.
- Gegenstand nach Anspruch 2, worin der innere Hohlraum von der äußeren Oberfläche durch eine Gegenstandswand über eine Dicke von weniger als etwa 0,889 mm (0,035 inch) getrennt ist.
- Gußteil nach Anspruch 2 in Form einer Turbinenschaufel mit einer radialen Mittellinie und mit einem Flügel mit einer Vorderkante und einer rückwärtigen Kante, bei dem:
die Korngrenzenorientierung und die Orientierung der primären Dentriten etwa gerade und parallel ist und
jedes austretende Korn, das die Vorder- oder rückwärtige Kante des Flügels schneidet, mit dieser Kante einen Winkel von nicht mehr als 15° bildet und alle anderen Korngrenzen und primären Dentriten innerhalb von 15° der radialen Mittellinie liegen. - Gegenstand nach Anspruch 1, der ein Flügel einer Gasturbine ist.
- Verfahren zum Wärmebehandeln eines Gußteiles aus einer Nickellegierung, hergestellt aus einer Legierung, bestehend aus, in Gew.-%, 0,1-0,15 C, 0,3-2 Hf, 11-14 Co, 5-9 Ta, weniger als 0,05 Zr, nicht mehr als 1 V, nicht mehr als 1 Ti, 5-10 Cr, 0,5-3 Mo, 4-7 W, 5-7 Al, 1,5-4 Re, 0,005-0,03 B, bis zu 1,5 Nb, bis zu 0,5 Y, der Rest sind Nickel und übliche Verunreinigungen, umfassend die Stufen:(a) Erhitzen bei einer Lösungstemperatur in einer nicht oxidierenden Atmosphäre für eine Zeit, die zur Lösung von mindestens 90% des Gamma-Gamma'-Eutektikums und grober sekundärer Gamma' genügt, und daß nicht mehr als etwa 4% beginnendes Schmelzen auftritt und dann Abkühlen in der Atmosphäre auf eine Temperatur im Bereich von 1107-1135°C (2025°-2075°F);(b) Erhitzen auf eine erste Alterungstemperatur im Bereich von 1107-1135°C (2025°-2075°F) in einer nicht oxidierenden Atmosphäre für 1-10 Stunden und dann Abkühlen in der Atmosphäre auf eine Temperatur im Bereich von 1066 bis 1093°C (1950°-2000°F) und(c) Erhitzen auf eine zweite Alterungstemperatur, die geringer als die erste Alterungstemperatur ist und im Bereich von 1066-1093°C (1950°-2000°F) liegt, für 4-12 Stunden.
- Verfahren nach Anspruch 6, bei dem die Lösungstemperatur im Bereich von 1246-1293°C (2275°-2360°F) liegt, und die Erhitzungszeit mindestens etwa 30 Minuten beträgt.
- Verfahren nach Anspruch 6 oder 7, das eine dritte Alterungsstufe des(d) Erhitzens auf eine Temperatur von 885-913°C (1625°-1675°F) für 2-10 Stunden einschließt.
- Verfahren zum Herstellen eines Gußteiles mit stengelförmigen Körnern aus Superlegierung auf Nickelbasis mit hervorragender Oxidationsbeständigkeit bei erhöhter Temperatur, wobei das Teil einen inneren Hohlraum mit einer integralen Gußwand einer Dicke von weniger als etwa 0,889 mm (0,035 inch) einschließt, umfassend die Stufen:(a) Präzisionsgießen des Teiles aus einer Legierung, bestehend aus, in Gew.-%, 0,1-0,15 C, 0,3-2 Hf, 11-14 Co, 5-9 Ta, weniger als 0,05 Zr, nicht mehr als 1 V, nicht mehr als 1 Ti, 5-10 Cr, 0,5-3 Mo, 4-7 W, 5-7 Al, 1,5-4 Re, 0,005-0,03 B, bis zu 1,5 Nb, bis zu 0,5 Y, der Rest sind Nickel und übliche Verunreinigungen, wobei die Gußwand integral mit dem durch gerichtete Erstarrung erhaltenen Gußkörper mit einer Vielzahl stengelförmiger Körner ist und(b) Wärmebehandeln des Gußteiles gemäß Anspruch 6.
- Verfahren zum Herstellen einer gegossenen Gasturbinenschaufel mit Stengelkorn aus Superlegierung auf Nickelbasis mit ausgezeichneter Oxidationsbeständigkeit bei erhöhter Temperatur, wobei der Gegenstand mindestens einen inneren Hohlraum aufweist, der eine integrale Gußwand einer Dicke von weniger als etwa 0,889 mm (0,035 inch) einschließt, umfassend die Stufen:(a) Schaffen einer Superlegierung, bestehend aus, in Gew.-%, 0,1-0,14 C, 1,2-1,7 Hf, 11,7-12,3 Co, 6,2-6,5 Ta, bis zu 0,1 V, bis zu 0,03 Zr, 6,6-7 Cr, 1,3-1,7 Mo, 4,7-5,1 W, nicht mehr als 0,02 Ti, 6-6,3 Al, 2,6-3 Re, 0,01-0,02 B, bis zu 0,1 Nb, bis zu 0,2 Y und der Rest sind Ni und übliche Verunreinigungen;(b) Präzisionsgießen der Superlegierung zur Schaffung eines Gegenstandes mit mindestens einem inneren Hohlraum, der eine integrale Gußwand einer Dicke von weniger als etwa 0,889 mm (0,035 inch) einschließt und(c) Wärmebehandeln des Gußteiles gemäß Anspruch 7.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US25310988A | 1988-10-03 | 1988-10-03 | |
US253109 | 1999-02-19 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0362661A1 EP0362661A1 (de) | 1990-04-11 |
EP0362661B1 true EP0362661B1 (de) | 1995-03-08 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP89117666A Expired - Lifetime EP0362661B1 (de) | 1988-10-03 | 1989-09-25 | Gegossenes aus stengelförmigen Kristallen bestehendes hohles Werkstück auf Nickel basierender Legierung sowie die Legierung und Wärmebehandlung für dessen Herstellung |
Country Status (8)
Country | Link |
---|---|
EP (1) | EP0362661B1 (de) |
JP (1) | JP3148211B2 (de) |
AU (1) | AU630623B2 (de) |
DE (1) | DE68921530T2 (de) |
ES (1) | ES2070155T3 (de) |
GR (1) | GR3015341T3 (de) |
IL (1) | IL91793A (de) |
NO (1) | NO175875C (de) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5316866A (en) * | 1991-09-09 | 1994-05-31 | General Electric Company | Strengthened protective coatings for superalloys |
US5443789A (en) * | 1992-09-14 | 1995-08-22 | Cannon-Muskegon Corporation | Low yttrium, high temperature alloy |
US5783318A (en) * | 1994-06-22 | 1998-07-21 | United Technologies Corporation | Repaired nickel based superalloy |
JP2905473B1 (ja) * | 1998-03-02 | 1999-06-14 | 科学技術庁金属材料技術研究所長 | Ni基一方向凝固合金の製造方法 |
EP1053804A1 (de) * | 1999-05-20 | 2000-11-22 | Asea Brown Boveri AG | Kernstütze |
KR20040008381A (ko) * | 2002-07-18 | 2004-01-31 | 한국기계연구원 | 고온크립특성이 향상된 단결정 초내열합금 |
JP4449337B2 (ja) * | 2003-05-09 | 2010-04-14 | 株式会社日立製作所 | 高耐酸化性Ni基超合金鋳造物及びガスタービン部品 |
JP4885530B2 (ja) | 2005-12-09 | 2012-02-29 | 株式会社日立製作所 | 高強度高延性Ni基超合金と、それを用いた部材及び製造方法 |
EP1900839B1 (de) | 2006-09-07 | 2013-11-06 | Alstom Technology Ltd | Verfahren zur Wärmebehandlung von Nickel-Basis-Superlegierungen |
US20100135846A1 (en) * | 2008-12-01 | 2010-06-03 | United Technologies Corporation | Lower cost high strength single crystal superalloys with reduced re and ru content |
EP2876176B1 (de) | 2013-11-25 | 2017-06-21 | Mitsubishi Hitachi Power Systems, Ltd. | Ni-basiertes Gießen von Superlegierungen und gegossener Gegenstand daraus |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1417474A (en) * | 1973-09-06 | 1975-12-10 | Int Nickel Ltd | Heat-treatment of nickel-chromium-cobalt base alloys |
US4169742A (en) * | 1976-12-16 | 1979-10-02 | General Electric Company | Cast nickel-base alloy article |
DE2741271A1 (de) * | 1976-12-16 | 1978-06-22 | Gen Electric | Superlegierung auf nickelbasis sowie gusskoerper daraus |
GB1562082A (en) * | 1977-10-17 | 1980-03-05 | Gen Electric | Nickel-base olloys |
DE3162552D1 (en) * | 1980-01-17 | 1984-04-19 | Cannon Muskegon Corp | Nickel base alloy and turbine engine blade cast therefrom |
US4643782A (en) * | 1984-03-19 | 1987-02-17 | Cannon Muskegon Corporation | Single crystal alloy technology |
FR2578554B1 (fr) * | 1985-03-06 | 1987-05-22 | Snecma | Alliage monocristallin a matrice a base de nickel |
CA1315572C (en) * | 1986-05-13 | 1993-04-06 | Xuan Nguyen-Dinh | Phase stable single crystal materials |
-
1989
- 1989-09-22 AU AU41700/89A patent/AU630623B2/en not_active Ceased
- 1989-09-25 ES ES89117666T patent/ES2070155T3/es not_active Expired - Lifetime
- 1989-09-25 DE DE68921530T patent/DE68921530T2/de not_active Expired - Fee Related
- 1989-09-25 EP EP89117666A patent/EP0362661B1/de not_active Expired - Lifetime
- 1989-09-27 IL IL9179389A patent/IL91793A/en not_active IP Right Cessation
- 1989-10-02 NO NO893913A patent/NO175875C/no unknown
- 1989-10-03 JP JP25718889A patent/JP3148211B2/ja not_active Expired - Fee Related
-
1995
- 1995-03-09 GR GR940403923T patent/GR3015341T3/el unknown
Also Published As
Publication number | Publication date |
---|---|
NO893913D0 (no) | 1989-10-02 |
IL91793A (en) | 1994-07-31 |
DE68921530D1 (de) | 1995-04-13 |
IL91793A0 (en) | 1990-06-10 |
ES2070155T3 (es) | 1995-06-01 |
NO175875B (de) | 1994-09-12 |
JPH02153037A (ja) | 1990-06-12 |
EP0362661A1 (de) | 1990-04-11 |
NO893913L (no) | 1990-04-04 |
DE68921530T2 (de) | 1995-10-26 |
AU4170089A (en) | 1990-04-05 |
NO175875C (no) | 1994-12-21 |
JP3148211B2 (ja) | 2001-03-19 |
AU630623B2 (en) | 1992-11-05 |
GR3015341T3 (en) | 1995-06-30 |
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