EP2449140A1 - Superlegierungszusammensetzungen auf nickelbasis und superlegierungsartikel - Google Patents

Superlegierungszusammensetzungen auf nickelbasis und superlegierungsartikel

Info

Publication number
EP2449140A1
EP2449140A1 EP10727610A EP10727610A EP2449140A1 EP 2449140 A1 EP2449140 A1 EP 2449140A1 EP 10727610 A EP10727610 A EP 10727610A EP 10727610 A EP10727610 A EP 10727610A EP 2449140 A1 EP2449140 A1 EP 2449140A1
Authority
EP
European Patent Office
Prior art keywords
weight percent
optionally
superalloy composition
superalloy
rhenium
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10727610A
Other languages
English (en)
French (fr)
Other versions
EP2449140B1 (de
Inventor
Joshua Leigh Miller
Brian Thomas Hazel
Douglas Gerard Konitzer
Paul John Fink
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2449140A1 publication Critical patent/EP2449140A1/de
Application granted granted Critical
Publication of EP2449140B1 publication Critical patent/EP2449140B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Definitions

  • This invention relates generally to nickel-base superalloy compositions and superalloy articles and more particularly to such alloys for use in high pressure turbine (HPT) nozzle applications.
  • HPT high pressure turbine
  • no-rhenium superalloys may exhibit inadequate stress rupture capability.
  • Other known superalloys that provide desired stress rupture capability may include relatively high amounts of rhenium. It is desirable to provide an alloy able to provide sufficient stress rupture capability with a reduced rhenium level.
  • exemplary embodiments that provide nickel-base superalloy compositions for use in high temperature applications.
  • Exemplary embodiments exhibit sufficient stress rupture capability, at relatively low- or no- rhenium levels.
  • a superalloy composition comprises, in weight percent: about 6.2-6.6 aluminum (Al), about 6.5-7.0 tantalum (Ta), about 6.0-7.0 chromium (Cr), about 6.25-7.0 tungsten (W), about 1.5-2.5 molybdenum (Mo), about 0.15-0.60 hafnium (Hf), 0.0-1.0 rhenium (Re), 6.5-9.0 cobalt (Co), optionally, 0.03-0.06 carbon (C), optionally, up to about 0.004 boron (B,) optionally up to about 0.03 total of one or more rare earth elements selected from yttrium (Y), lanthanum (La), or cerium (Ce), balance nickel (Ni), such that the superalloy composition exhibits a stress rupture capability improvement of at least about 15% over a base stress rupture capability of a base composition nominally comprising, in weight percent: 6.5 Al, 6.6 Ta, 6.0 Cr, 6.25 W, 1.5 Mo, 0.15 H
  • a superalloy composition consists of, in weight percent: about 6.2-6.6 aluminum (Al), about 6.5-7.0 tantalum (Ta), about 6.0 chromium (Cr), about 6.25-7.0 tungsten (W), about 2.0 molybdenum (Mo), about 0.6 hafnium (Hf), from 0.0 to 0.5 rhenium (Re), about 7.5 cobalt (Co), optionally, 0.03-0.06 carbon (C), optionally, up to about 0.004 boron (B), optionally up to about 0.03 total of one or more rare earth elements selected from yttrium (Y), lanthanum (La), or cerium (Ce), and a balance of nickel (Ni) and incidental impurities.
  • an article formed from an exemplary superalloy composition is provided.
  • the article may be a high pressure turbine nozzle, nozzle segment, or other gas turbine engine component.
  • FIG. 1 is a perspective view of a component article such as a gas turbine engine high pressure turbine (HPT) nozzle segment.
  • HPT high pressure turbine
  • FIG. 1 depicts an HPT nozzle segment 10 including at least one vane 12.
  • the nozzle segment 10 comprises a single crystal nickel-base superalloy composition as disclosed herein.
  • Articles incorporating the disclosed superalloy composition include HPT nozzles or nozzle segments and may include other gas turbine engine components.
  • Exemplary nickel-base superalloy composition comprise reduced levels of rhenium (Re), defined herein as being from 0 up to about 0.5 weight %.
  • Increased amounts of other strengthening alloying elements such as tantalum (Ta), tungsten (W) and molybdenum (Mo) may be utilized to offset the lower levels of Re.
  • tantalum may be present in amounts from about 6.5 to about 7.0 weight %
  • molybdenum may be present in amounts from about 1.5 to about 2.5 weight %
  • tungsten may be present in amounts from about 6.25 to about 7.0 weight %.
  • tantalum may be present at levels of from about 6.5 to about 6.6 weight %. All percentages presented herein are percentages by weight, unless noted otherwise.
  • Table 1 provides a series of exemplary compositions. A theoretical stress rupture prediction generated by computer modeling for the compositions was compared with the predicted stress rupture (in hours) of a base, no-rhenium superalloy composition. As evidenced in Table 1, each of the enumerated compositions provided an improved predicted stress rupture, presented as % improvement.
  • compositions presented in Table 1 are highlighted. These exemplary compositions exhibit excellent improvement in the predicted stress rupture as compared to the Base composition. These exemplary compositions may provide desired outcomes with reduced rhenium levels (0.0-0.5 weight %). Other exemplary compositions include rhenium in levels up to about 1.0 weight %.
  • Alloys 25 and 27 listed in Table 1 are provided as comparative examples and include about 1.5 weight % rhenium. Exemplary embodiments disclosed herein consider the contributions of various alloying elements to the thermal mechanical properties and oxidation resistance of the superalloy composition. 58-2
  • Certain exemplary embodiments disclosed herein include from about 6.2 to about 6.6 weight percent aluminum. In other exemplary embodiments, the aluminum may be present in amounts from about 6.3 to about 6.5 percent.
  • Certain embodiments disclosed herein include at least about 6 to about 7 weight % chromium (Cr) sufficient to provide hot corrosion resistance, but not high enough to detrimentally lead to TCP phase instability and poor cyclic oxidation resistance.
  • Certain embodiments disclosed herein include from about 6.5% to about 9%, and more preferably about 7% to about 8% cobalt (Co). Lower amounts of cobalt may reduce alloy stability. Greater amounts may reduce the gamma prime solvus temperature thus impacting high temperature strength and oxidation resistance.
  • Mo molybdenum
  • the minimum value is sufficient to impart solid solution strengthening. Amounts exceeding the maximum may lead to surface instability. Greater amounts of Mo may also negatively impact both hot corrosion and oxidation resistance.
  • Certain embodiments disclosed herein include tungsten (W) in amounts from about 6.25 to about 7.0 weight %. Lower amounts of W may decrease strength. Higher amounts may produce instability with respect to TCP phase formation. Higher amounts may also reduce oxidation capability.
  • Certain embodiments disclosed herein provide reduced levels of rhenium, preferably from 0.0 to about 1.0 weight percent, and more preferably not greater than about 0.5 weight %. It is contemplated that some or all of the rhenium may be provided as revert from scrap material. Compositions 25 and 27 illustrate significant improvement in predicted stress rupture capability with the addition of 1.5 weight % rhenium. It is desired to provide improved performance at reduced rhenium levels.
  • Hafnium (Hf) may be included at relatively low levels of about 0.15 weight % up to higher levels of about 0.6 weight %. Hafnium can improve oxidation resistance and the adherence of thermal barrier coatings when utilized. However, hafnium can degrade the corrosion resistance of uncoated alloys. Hafnium additions of about 0.7% can be satisfactory, but additions of greater than about 1% adversely impact stress rupture properties and the incipient melting temperature.
  • Optional additions may include about 0.03-0.06 weight % carbon (C), up to about 0.004 weight % boron (B), or up to about 0.03 weight% of one or more rare earth elements such as yttrium (Y), lanthanum (La), and cesium (Ce).
  • C carbon
  • B boron
  • Y yttrium
  • La lanthanum
  • Ce cesium
  • Boron provides strength for low angle boundaries and enhanced acceptability limits for components having low angle grain boundaries.
  • the lower limit for carbon provides sufficient carbon to improve alloy cleanliness since carbon provides de-oxidation. Beyond the upper 0.06% amount, the carbide volume fraction increases, reducing fatigue life.
  • Rare earth additions i.e., yttrium (Y), lanthanum (La), and cerium (Ce), may be provided in certain embodiments in amounts up to about 0.03%. These additions may improve oxidation resistance by enhancing the retention of the protective alumina scale. Greater amounts may promote mold/metal reaction at the casting surface, increasing the component inclusion content.
  • Exemplary embodiments disclosed herein include each of the enumerated compositions in Table 1 with the exception of the base composition, and comparative alloys 25 and 27. Additionally, exemplary embodiments disclosed herein include compositions employing the endpoints of disclosed ranges and all intermediate values. For example, a range of aluminum from about 6.2 to about 6.6 weight percent is defined to include 6.2 weight percent, 6.6 weight percent, and any intervening percentage between 6.2 and 6.6 weight percent.
  • Exemplary embodiments disclosed herein provide improved stress rupture capability of at least 15% as compared to a base stress rupture capability of a base
  • composition nominally comprising, in weight percent: 6.5 Al, 6.6 Ta, 6.0 Cr, 6.25 W, 1.5 Mo, 0.15 Hf, 0.0 Re, 7.5Co, balance Ni, identified as "Base” in Table 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP20100727610 2009-06-30 2010-06-15 Zusammensetzungen von superlegierungen auf basis von nickel und bauteile daraus Active EP2449140B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US22194609P 2009-06-30 2009-06-30
US12/794,244 US20100329921A1 (en) 2009-06-30 2010-06-04 Nickel base superalloy compositions and superalloy articles
PCT/US2010/038640 WO2011002605A1 (en) 2009-06-30 2010-06-15 Nickel base superalloy compositions and superalloy articles

Publications (2)

Publication Number Publication Date
EP2449140A1 true EP2449140A1 (de) 2012-05-09
EP2449140B1 EP2449140B1 (de) 2015-05-20

Family

ID=43380980

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20100727610 Active EP2449140B1 (de) 2009-06-30 2010-06-15 Zusammensetzungen von superlegierungen auf basis von nickel und bauteile daraus

Country Status (5)

Country Link
US (1) US20100329921A1 (de)
EP (1) EP2449140B1 (de)
JP (1) JP5763062B2 (de)
CA (1) CA2766552A1 (de)
WO (1) WO2011002605A1 (de)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014093826A2 (en) 2012-12-14 2014-06-19 United Technologies Corporation Multi-shot casting
EP3513889B1 (de) * 2012-12-14 2021-04-14 Raytheon Technologies Corporation Legierung und hybridturbinenschaufel für verbesserte motorleistung oder -architektur
RU2519075C1 (ru) * 2013-02-05 2014-06-10 Открытое акционерное общество "Научно-производственное объединение "Сатурн" Жаропрочный сплав на основе никеля для литья деталей горячего тракта газотурбинных установок

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EP1054072B1 (de) * 1999-05-20 2003-04-02 ALSTOM (Switzerland) Ltd Nickel-Basis-Superlegierung
US6444057B1 (en) * 1999-05-26 2002-09-03 General Electric Company Compositions and single-crystal articles of hafnium-modified and/or zirconium-modified nickel-base superalloys
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Also Published As

Publication number Publication date
CA2766552A1 (en) 2011-01-06
JP5763062B2 (ja) 2015-08-12
US20100329921A1 (en) 2010-12-30
WO2011002605A1 (en) 2011-01-06
JP2012532250A (ja) 2012-12-13
EP2449140B1 (de) 2015-05-20

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