EP0683239B1 - Oxidationsbeständige Superlegierung auf Nickelbasis - Google Patents

Oxidationsbeständige Superlegierung auf Nickelbasis Download PDF

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Publication number
EP0683239B1
EP0683239B1 EP94303644A EP94303644A EP0683239B1 EP 0683239 B1 EP0683239 B1 EP 0683239B1 EP 94303644 A EP94303644 A EP 94303644A EP 94303644 A EP94303644 A EP 94303644A EP 0683239 B1 EP0683239 B1 EP 0683239B1
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Prior art keywords
weight percent
superalloy
nickel
weight
alloy
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Expired - Lifetime
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EP94303644A
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English (en)
French (fr)
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EP0683239A1 (de
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William J. Gostic
Paul P. Norris Jr.
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RTX Corp
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United Technologies Corp
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Priority to DE1994616110 priority Critical patent/DE69416110T2/de
Priority to EP94303644A priority patent/EP0683239B1/de
Priority to JP12211394A priority patent/JP3474634B2/ja
Publication of EP0683239A1 publication Critical patent/EP0683239A1/de
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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
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • 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%

Definitions

  • the present invention relates to nickel superalloys and methods for making nickel superalloys having high oxidation resistance and containing controlled amounts of boron and zirconium.
  • Such nickel superalloys are suitable for use in articles requiring good strength and superior oxidation resistance at high temperatures, including jet engine combustors, nozzles, and low turbine components.
  • a variety of nickel based superalloys are known in the art.
  • Superalloys are those alloys which maintain high strength at high temperatures. Examples of nickel based superalloys can be found in U.S. Patent Nos. 3,322,534 (Shaw et al.), 3,526,499 (Quigg et al.), 3,653,987 (Boesch), 3,667,938 (Boesch), 3,832,167 (Shaw et al.), and 4,719,080 (Duhl et al.).
  • nickel based superalloys include B1900+Hf and Mar-M 247, the nominal compositions of which are, in weight percent, B-l900+HF Mar-M-247 Nickel Balance Balance Chromium 8.0 8.4 Cobalt 10.0 10.0 Carbon 0.11 0.15 Titanium 1.0 1.1 Aluminum 6.0 5.5 Molybdenum 6.0 0.65 Tungsten - 10.0 Boron 0.015 0.015 Hafnium 1.15 1.4 Tantalum 4.25 3.1 Zirconium 0.08 0.055 Due to their ability to maintain good mechanical strength at high temperatures, these alloys are especially useful as a material for making components of jet engines.
  • Boron is typically added in the range of 0.010 to 0.020 weight percent to conventionally cast superalloys for the enhancement of grain boundary strength and ductility.
  • Zirconium is typically added in the range of 0.03 to 0.13 weight percent for further grain boundary property enhancement.
  • Yttrium can be added to nickel superalloys to enhance their oxidation resistance.
  • US-A-3526499 discloses a nickel base superalloy with 0.01-0. 5 weight percent zirconium and 0.005-0.200 weight percent boron.
  • JP-A-6041664 discloses a heat-resistant nickel superalloy with a maximum of 0.5 weight percent zirconium and a maximum of 0.01 weight percent boron.
  • SU-A-360389 discloses a nickel cathode alloy containing 0.05-0.5 weight percent zirconium and 0.005-0.2 weight percent boron.
  • the nickel superalloys of the prior art which demonstrate excellent oxidation resistance at high temperature are too brittle.
  • nickel superalloys which have excellent oxidation resistance at high temperatures while at the same time possessing good ductility.
  • turbine components in jet engines which have good strength and excellent oxidation resistance within the temperature range of 760°C (1400°F) to 1038°C (1900°F).
  • a polycrystalline nickel-based superalloy comprising 0.25 to 0.40 weight percent zirconium, 0.004 to 0.010 weight percent boron, 5.0 to 8.0 weight percent aluminium, 5.0 to 12.0 weight percent chromium, 0.75 to 2.0 weight percent hafnium, 0 to 10.0 weight percent cobalt; and optionally further comprising the following elements in the following weight percent ranges: 0 to 12 weight percent tungsten, 0 to 12 weight percent molybdenum, 0 to 12 weight percent tantalum, 0 to 2 weight percent titanium, 0 to 2 weight percent niobium, and 0.06 to 0.20 weight percent carbon; and optionally comprising the following additive materials containing from zero up to the maximum percent by weight indicated amounts: manganese (0.20), phosphorus (0.015) sulfur (0.015), silicon (0.10), iron (0.25), bismuth (0.00005, 0.5ppm), lead (0.0002, 2ppm), selenium (0.0001, lppm
  • the alloys of the present invention have demonstrated excellent oxidation resistance up to 1093°C (2000°F), and in preferable instances up to 1204°C (2200°F).
  • the nickel superalloys of the present invention have demonstrated good strength within the temperature range of 760°C (1400°F) to 1038°C (1900°F).
  • the excellent oxidation resistance of the superalloys of the present invention make them suitable for use in high temperature applications such as in a jet engine combustor, nozzle and low turbine components.
  • the superalloys of the present invention contain between 5.0 and 8.0 weight percent aluminum in order to form an effective barrier layer which impedes oxidation of the superalloy. Having zirconium present in the superalloy promotes formation of the alumina barrier layer.
  • Burner rig oxidation testing revealed the detrimental effect of boron on high temperature (1093°C-1204°C (2000-2200°F)) oxidation resistance. Removing boron from the nickel superalloy solved the oxidation problem, but the resulting alloy had unacceptable ductility. Adding low levels of boron (0.002 to 0.010 weight percent) provided acceptable oxidation behavior, but ductility was marginal at best. The addition of yttrium also presented embrittlement problems due to the formation of surface oxide particles during casting, which result from the reaction between yttrium and the casting ceramics. Through further experimentation, it was discovered that the combination of zirconium and boron at the levels designated in this specification can greatly enhance the oxidation resistance of conventionally cast nickel superalloys, while maintaining grain boundary properties and avoiding inclusion formation during casting.
  • the nickel superalloy of the present invention includes and has been found to work when elements are added in the following weight percentages: Element Percentage Chromium 5.0 - 12.0 Hafnium 0.75 - 2.0 Cobalt O - 10.0
  • alloy elements can be added for alloy strengthening: Element Percentage Tungsten 0 - 12 Molybdenum 0 - 12 Tantalum 0 - 12 Titanium 0 - 2 Columbium (Niobium) 0 - 2 Carbon 0.06 - 0.20
  • the elements manganese, phosphorus, sulfur, silicon, iron, bismuth, lead, selenium, tellurium, and thallium are preferably controlled to low levels in order to prevent degradation to the properties of the superalloy.
  • the superalloy is comprised of the following elements given in weight percentages: Element Percentage min max Carbon 0.08 0.13 Chromium 9.50 10.50 Molybdenum 1.75 2.25 Tungsten 3.00 3.40 Aluminum 6.50 6.70 Tantalum 3.90 4.30 Hafnium 1.05 1.25 Boron 0.004 0.010 zirconium 0.25 0.35 Nickel remainder
  • the superalloy of the present invention may contain additive materials, such as the following, up to the indicated percent by weight maximum amounts: manganese (0.20), phosphorus (0.015), sulfur (0.015), silicon (0.10), iron (0.25), bismuth (0.00005, 0.5 ppm), lead (0.0002, 2 ppm), selenium (0.0001, 1 ppm), tellurium (0.00005, 0.5 ppm), and thallium (0.00005, 0.5 ppm).
  • additive materials such as the following, up to the indicated percent by weight maximum amounts: manganese (0.20), phosphorus (0.015), sulfur (0.015), silicon (0.10), iron (0.25), bismuth (0.00005, 0.5 ppm), lead (0.0002, 2 ppm), selenium (0.0001, 1 ppm), tellurium (0.00005, 0.5 ppm), and thallium (0.00005, 0.5 ppm).
  • articles are fabricated by taking an ingot of the requisite composition, which has been cast from a single furnace charge under vacuum, and vacuum remelting and recasting using investment casting procedures that are conventionally used for nickel based alloys.
  • Conventional investment casting procedures for superalloys, procedures for forming ingots of superalloys, and other general information regarding superalloys can be found in Superalloys II , Sims et al., eds., John Wiley & Sons, New York, 1987.
  • alloying elements in their commercially pure form are added to the master heat during ingot formation.
  • the alloying elements contain less than maximum ("max") specified amounts of the following additive materials set forth above: Mn, P, S, Si, Fe, Ti, Cb (Nb), Bi, Pb, Se, Te, and T1.
  • a nickel superalloy was made having the composition shown in Table I.
  • the invention showed superior ductility compared to a compositionally similar nickel alloy whose boron and zirconium content falls outside the critical range defined in the present invention as demonstrated below in Table II.
  • superalloys of the present invention have a mean tensile elongation of three ASTM E 8 tests at 649°C (1200°F) exceeding 3.0%. In a preferred embodiment, mean tensile elongation of three ASTM E 8 tests at 649°F (1200°F) exceeds 5.0%.
  • Burner rig oxidation testing demonstrated that the alloy of the present invention had superior oxidation resistance compared to the conventional nickel superalloys Bl900+HF and Mar-M-247 (see Table I and Figures 1 and 2). After 70 cycles of 1204°C (2200°F) burner rig oxidation, the alloy of this invention lost only about 2% of its weight, as compared to 55% for B1900+HF and 75% for Mar-M-247.
  • a liquid fuel burner is controlled by fuel pressure to maintain the temperature of interest.
  • the specimens are typically cylindrical rods (12mm (0.47") diameter x 82.5mm (3.25") long in this case). Individual specimens can be tested. Multiple specimens are tested in a rotating spindle. Specimen weight and diameter are measured at intervals during the test to monitor the loss of material via oxide spallation. Oxidation rate is proportional to weight loss (greater weight corresponds to greater oxidation rate).
  • a second method of testing oxidation resistance can also be used to characterize the nickel superalloys of the present invention.
  • coupons of a superalloy are suspended from a wire and placed into a furnace maintained at 1149°C +/- 14°C (2100 0 F +/- 25 0 F), while exposed to ambient air.
  • alloy samples are 12.7 x 19mm +/- 3mm (0.50 X 0.75 in. +/-0.12 in.) by 1.02mm +/- 0.25mm (0.040 in. +/- 0.010-in.). Prior to the initial insertion into the furnace, corners and edges on the sample are rounded. Samples are heated in cycles of 24 +/- 4 hours.
  • a nickel superalloy component of the present invention is heated to 1079 ⁇ 14°C (1975 ⁇ 25°F) in air for 4 hours and air cooled at a minimum of 22°C/min (40°F/min). The component is then heated to 871 ⁇ 14°C (1600 ⁇ 25°F) for 16 hours and then air cooled at a minimum of 22°C/min (40°F/min). This heat treatment serves to improve the tensile and creep properties of the superalloy component.
  • the polycrystalline nickel superalloy of the present invention is equiaxed; in another embodiment, the polycrystalline nickel superalloy of the present invention is columnar.
  • the nickel superalloy of the present invention which is shown in Table I has been successfully used as a component of a float wall combustor.

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

Claims (15)

  1. Polykristalline Superlegierung auf Nickelbasis aufweisend 0,25 bis 0,40 Gewichtsprozent Zirconium, 0,004 bis 0,010 Gewichtsprozent Bor, 5,0 bis 8,0 Gewichtsprozent Aluminium, 5,0 bis 12,0 Gewichtsprozent Chrom, 0,75 bis 2,0 Gewichtsprozent Hafnium, 0 bis 10,0 Gewichtsprozent Cobalt; und gewünschtenfalls außerdem die folgenden Elemente in den folgenden Gewichtsprozentbereichen aufweisend: 0 bis 12 Gewichtsprozent Wolfram, 0 bis 12 Gewichtsprozent Molybdän, 0 bis 12 Gewichtsprozent Tantal, 0 bis 2 Gewichtsprozent Titan, 0 bis 2 Gewichtsprozent Niobium und 0,06 bis 0,20 Gewichtsprozent Kohlenstoff; und gewünschtenfalls die folgenden Zusatzmaterialien aufweisend, die von Null bis zu den angegebenen Maximalgewichtsprozentmengen enthalten: Mangan (0,20), Phosphor (0,015), Schwefel (0,015), Silicium (0,10), Eisen (0,25), Bismut (0,00005, 0,5 ppm), Blei (0,0002, 2 ppm), Selen (0,0001, 1 ppm), Tellur (0,00005, 0,5 ppm) und Thallium (0,00005, 0,5 ppm); wobei der Rest der Superlegierung Nickel ist.
  2. Legierung nach Anspruch 1, bei der die Körner achsengleich sind.
  3. Legierung nach Anspruch 1, bei der die Körner säulenförmig sind.
  4. Legierung nach Anspruch 1, 2 oder 3, bei der, nachdem sie scharfen oxidierenden Bedingungen ausgesetzt wurde, an der Oberfläche der Legierung eine Aluminiumoxid-Schicht ausgebildet ist, die in der Lage ist, die Oxidationsrate der Superlegierung zu verringern.
  5. Legierung nach irgendeinem vorangehenden Anspruch, bei der Mangan, Phosphor, Schwefel, Silicium, Eisen, Bismut, Blei, Selen, Tellur und Thallium in Anteilen anwesend sind, die ausreichend niedrig sind, um eine wesentliche Verringerung der Duktilität der Superlegierung, wie sie durch die Zugdehnung der Superlegierung gemessen wird, zu verringern.
  6. Legierung nach irgendeinem vorangehenden Anspruch, bei der die Legierung 0,007 oder weniger Gewichtsprozent Bor enthält.
  7. Legierung nach irgendeinem vorangehenden Anspruch, die Elemente in den folgenden Gewichtsprozentsätzen aufweist: Element Prozentsatz min max Kohlenstoff 0,08 0,13 Chrom 9,50 10,50 Molybdän 1,75 2,25 Wolfram 3,00 3,40 Aluminium 6,50 6,70 Tantal 3,90 4,30 Hafnium 1,05 1,25 Bor 0,004 0,010 Zirconium 0,25 0,35 Nickel Rest.
  8. Superlegierung nach irgendeinem vorangehenden Anspruch, bei der die mittlere Zugdehnung von drei ASTM E 8-Tests bei 649°C (1200°F) 3,0% überschreitet, und der Gewichtsverlust durch 300 Stunden langes Testen einer Probe der Superlegierung mit den Abmessungen 12,7 x 19 mm +/- 3 mm (0,50 x 0,75 in. +/- 0,12 in.) auf 1,02 mm +/- 0,25 mm (0,040 in. +/- 0,010 in.) bei 1149°C (2100°F) unter zyklischen Bedingungen von 24 +/- 4 Stunden in Umgebungsluft 10% des Ausgangsprobengewichts nicht überschreitet.
  9. Superlegierung nach irgendeinem vorangehenden Anspruch, bei der die mittlere Zugdehnung von drei ASTM E 8-Tests bei 649°C (1200°F) 5,0% überschreitet, und der Gewichtsverlust durch 300 Stunden langes Testen einer Probe der Superlegierung mit den Abmessungen 12,7 x 19 mm +/- 3 mm (0,50 x 0,75 in. +/- 0,12 in.) auf 1,02 mm +/- 0,25 mm (0,040 in. +/- 0,010 in.) bei 1149°C (2100°F) unter zyklischen Bedingungen von 24 +/- 4 Stunden in Umgebungsluft 5,0% des Ausgangsprobengewichts nicht überschreitet.
  10. Strahltriebwerksbauteil aufweisend die Nickel-Superlegierung nach irgendeinem vorangehenden Anspruch.
  11. Bauteil nach Anspruch 10, das ausgewählt ist aus der Gruppe, die besteht aus Brennraum-, Düsen- und Niederturbinen-Bauteilen.
  12. Verfahren zur Herstellung einer polykristallinen Nickel-Superlegierung mit hoher Oxidationsbeständigkeit, aufweisend den Schritt des Inkorporierens von 0,25 bis 0,40 Gewichtsprozent Zirconium, 0,004 bis 0,010 Gewichtsprozent Bor, 5,0 bis 8,0 Gewichtsprozent Aluminium, 5,0 bis 12,0 Gewichtsprozent Chrom, 0,75 bis 2,0 Gewichtsprozent Hafnium, 0 bis 10,0 Gewichtsprozent Cobalt; und gewünschtenfalls außerdem die folgenden Elemente in den folgenden Gewichtsprozentbereichen aufweisend: 0 bis 12 Gewichtsprozent Wolfram, 0 bis 12 Gewichtsprozent Molybdän, 0 bis 12 Gewichtsprozent Tantal, 0 bis 2 Gewichtsprozent Titan, 0 bis 2 Gewichtsprozent Niobium und 0,06 bis 0,20 Gewichtsprozent Kohlenstoff; und gewünschtenfalls die folgenden Zusatzmaterialien aufweisend, die von Null bis zu den angegebenen Maximalgewichtsprozentmengen enthalten: Mangan (0,20), Phosphor (0,015), Schwefel (0,015), Silicium (0,10), Eisen (0,25), Bismut (0,00005, 0,5 ppm), Blei (0,0002, 2 ppm), Selen (0,0001, lppm), Tellur (0,00005, 0,5 ppm) und Thallium (0,00005, 0,5 ppm); wobei der Rest der Superlegierung Nickel ist.
  13. Verfahren zur Herstellung von Strahltriebwerksbauteilen, aufweisend den Schritt des Gießens einer Nickel-Superlegierung, wobei die Superlegierung 0,25 bis 0,40 Gewichtsprozent Zirconium, 0,004 bis 0,010 Gewichtsprozent Bor, 5,0 bis 8,0 Gewichtsprozent Aluminium, 5,0 bis 12,0 Gewichtsprozent Chrom, 0,75 bis 2,0 Gewichtsprozent Hafnium, 0 bis 10,0 Gewichtsprozent Cobalt aufweist; und gewünschtenfalls außerdem die folgenden Elemente in den folgenden Gewichtsprozentbereichen aufweist: 0 bis 12 Gewichtsprozent Wolfram, 0 bis 12 Gewichtsprozent Molybdän, 0 bis 12 Gewichtsprozent Tantal, 0 bis 2 Gewichtsprozent Titan, 0 bis 2 Gewichtsprozent Niobium und 0,06 bis 0,20 Gewichtsprozent Kohlenstoff; und gewünschtenfalls die folgenden Zusatzmaterialien aufweist, die von Null bis zu den angegebenen Maximalgewichtsprozentmengen enthalten: Mangan (0,20), Phosphor (0,015), Schwefel (0,015), Silicium (0,10), Eisen (0,25), Bismut (0,00005, 0,5 ppm), Blei (0,0002, 2 ppm), Selen (0,0001, 1 ppm), Tellur (0,00005, 0,5 ppm) und Thallium (0,00005, 0,5 ppm); wobei der Rest der Superlegierung Nickel ist.
  14. Verfahren nach Anspruch 13, bei dem die Superlegierung aus einer einzigen Ofencharge unter Vakuum gegossen wurde.
  15. Verfahren nach Anspruch 14, bei dem ein Ingot der Superlegierung im Vakuum nochmals geschmolzen wird und danach unter Verwendung voll Investmentguß-Verfahren für Nickellegierungen gegossen wird.
EP94303644A 1994-05-20 1994-05-20 Oxidationsbeständige Superlegierung auf Nickelbasis Expired - Lifetime EP0683239B1 (de)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE1994616110 DE69416110T2 (de) 1994-05-20 1994-05-20 Oxidationsbeständige Superlegierung auf Nickelbasis
EP94303644A EP0683239B1 (de) 1994-05-20 1994-05-20 Oxidationsbeständige Superlegierung auf Nickelbasis
JP12211394A JP3474634B2 (ja) 1994-05-20 1994-06-03 多結晶質ニッケル超合金及びその製造方法

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP94303644A EP0683239B1 (de) 1994-05-20 1994-05-20 Oxidationsbeständige Superlegierung auf Nickelbasis
JP12211394A JP3474634B2 (ja) 1994-05-20 1994-06-03 多結晶質ニッケル超合金及びその製造方法

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EP0683239A1 EP0683239A1 (de) 1995-11-22
EP0683239B1 true EP0683239B1 (de) 1999-01-20

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2145968A1 (de) * 2008-07-14 2010-01-20 Siemens Aktiengesellschaft Gamma-Strich-verstärkte Superlegierung auf Nickelbasis
US8858873B2 (en) * 2012-11-13 2014-10-14 Honeywell International Inc. Nickel-based superalloys for use on turbine blades
US20150247220A1 (en) 2014-02-28 2015-09-03 General Electric Company Article and method for forming article
US10933469B2 (en) 2018-09-10 2021-03-02 Honeywell International Inc. Method of forming an abrasive nickel-based alloy on a turbine blade tip

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3526499A (en) * 1967-08-22 1970-09-01 Trw Inc Nickel base alloy having improved stress rupture properties
US3776704A (en) * 1968-03-01 1973-12-04 Int Nickel Co Dispersion-strengthened superalloys
US4082581A (en) * 1973-08-09 1978-04-04 Chrysler Corporation Nickel-base superalloy
US4046560A (en) * 1975-12-30 1977-09-06 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Nickel base alloy
US4719080A (en) * 1985-06-10 1988-01-12 United Technologies Corporation Advanced high strength single crystal superalloy compositions
JPH0641664A (ja) * 1992-05-28 1994-02-15 Daido Steel Co Ltd 耐熱弾性機械要素及びその製造方法

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EP0683239A1 (de) 1995-11-22
JP3474634B2 (ja) 2003-12-08

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