EP2045345A1 - A nickel based superalloy - Google Patents

A nickel based superalloy Download PDF

Info

Publication number
EP2045345A1
EP2045345A1 EP08252916A EP08252916A EP2045345A1 EP 2045345 A1 EP2045345 A1 EP 2045345A1 EP 08252916 A EP08252916 A EP 08252916A EP 08252916 A EP08252916 A EP 08252916A EP 2045345 A1 EP2045345 A1 EP 2045345A1
Authority
EP
European Patent Office
Prior art keywords
base superalloy
nickel base
titanium
nickel
cobalt
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
EP08252916A
Other languages
German (de)
French (fr)
Other versions
EP2045345B1 (en
Inventor
Robert John Mitchell
Mark Christopher Hardy
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP2045345A1 publication Critical patent/EP2045345A1/en
Application granted granted Critical
Publication of EP2045345B1 publication Critical patent/EP2045345B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0433—Nickel- or cobalt-based alloys
    • 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
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/047—Making non-ferrous alloys by powder metallurgy comprising intermetallic compounds
    • 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
    • C22C19/07—Alloys based on nickel or cobalt based on cobalt
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent

Definitions

  • the present invention relates to a nickel base superalloy.
  • cobalt and titanium increases the temperature and flow stress capability. It is known that cobalt modifies the solubility of the gamma prime phase in the gamma phase, raises the solidus temperature, lowers the gamma prime solvus temperature and lowers the stacking fault energy.
  • the addition of titanium increases the volume fraction of gamma prime phase by forming Co 3 Ti with the same crystal structure as Ni 3 Al.
  • Nickel base superalloys containing high levels of refractory elements such as molybdenum, niobium, tantalum, tungsten etc, are difficult to process by conventional cast and wrought processing routes. This is due to the macro-segregation that occurs between atomic species, including aluminium and titanium, leading to variable microstructures and mechanical properties.
  • Udimet 720Li is produced by the cast and wrought processing route, although it may be produced in a powder metallurgy form. Processing by the powder metallurgy route, although considered more expensive, allows for a greater degree of alloying additions to be made and eliminates macro-segregation, limiting segregation to the micro/nano-scale.
  • the present invention seeks to provide a novel nickel base superalloy.
  • the present invention provides a nickel base superalloy consisting of 23 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities.
  • the present invention provides a nickel base superalloy consisting of 23.5 to 30wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 1wt% silicon and the balance nickel plus incidental impurities.
  • the present invention provides a nickel base superalloy consisting of 23.5 to 28wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • the present invention provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027 to 0.03wt% carbon, 0.015 to 0.02wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • the present invention provides a nickel base superalloy consisting of 46.34wt% nickel, 24wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.03wt% carbon, 0.02wt% boron.
  • the present invention provides a nickel base superalloy consisting of 43.35wt% nickel, 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027wt% carbon, 0.015wt% boron.
  • the present invention also provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • the precipitated gamma prime phase comprises a (Ni/Co) 3 (Al/Ti/Ta).
  • the precipitated gamma prime phase comprises a (Ni/Co) 3 (Al/Ti/Ta/Nb).
  • the precipitated gamma prime phases comprises Co 3 Ta and/or Co 3 Ti.
  • a turbofan gas turbine engine 10 as shown in figure 1 , comprises in axial flow series an inlet 12, a fan section 14, a compressor section 16, a combustion section 18, a turbine section 20 and an exhaust 22.
  • the turbofan gas turbine engine 10 is quite conventional and will not be discussed further.
  • the turbine section 20 comprises one or more turbine discs 24, shown more clearly in figure 2 , comprising a nickel base superalloy according to the present invention.
  • the present invention seeks to provide a nickel base superalloy which is a high strength alloy capable of use for applications at 750°C and above and which is stable.
  • the nickel base superalloy consists of 23 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities.
  • the nickel base superalloy consists of 23.5 to 30wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 1wt% silicon and the balance nickel plus incidental impurities.
  • the nickel base superalloy consists of 23.5 to 28wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • the nickel base superalloy consists of 24 to 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027 to 0.03wt% carbon, 0.015 to 0.02wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • One preferred nickel base superalloy consists of 46.34wt% nickel, 24wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.03wt% carbon, 0.02wt% boron.
  • Another preferred nickel base superalloy consists of 43.35wt% nickel, 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027wt% carbon, 0.015wt% boron.
  • the present invention also provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • the starting chemistry for a nickel base superalloy according to the present invention is RR1000 nickel base superalloy.
  • the RR1000 nickel base superalloy is a gamma/gamma prime strengthened superalloy, which has a gamma prime composition of Ni 3 (Al/Ti/Ta/Hf) and an increased volume fraction of gamma prime over Udimet 720Li.
  • the addition of cobalt and titanium to the RR1000 nickel base superalloy increases the gamma prime volume fraction further and changes the gamma prime chemistry to (Ni/Co) 3 (Al/Ti/Ta).
  • Co 3 Ta phase and/or Co 3 Ti phase is precipitation of a Co 3 Ta phase and/or Co 3 Ti phase.
  • cobalt and titanium may be added to other advanced nickel base superalloys, e.g. Rene95, ME3, Alloy10 or LSHR, to provide similar nickel base superalloys.
  • advanced nickel base superalloys e.g. Rene95, ME3, Alloy10 or LSHR
  • the gamma prime chemistry changes to (Ni/Co) 3 (Al/Ti/Ta/Nb).
  • the nickel base superalloys of the present invention are only capable of processing by the powder metallurgy route due to the high content of refractory elements. This allows for a wider range of elemental additions to be incorporated into the final nickel base superalloy composition.
  • Table 1 shows the compositions of Udimet 720Li and some advanced powder metallurgy nickel base superalloys and shows how the advanced powder metallurgy nickel base superalloys have sought to optimise gamma prime volume fraction. It is clear that the level of the gamma prime forming elements, in terms of at%, is increased as well as the level of tantalum and niobium to change the chemistry of the gamma prime phase precipitated to (Ni/Co) 3 (Al/Ti/Ta/Nb).
  • Table 2 shows the compositions of alloys according to the present invention and the prior art alloy RR1000.
  • Table 2 wt% Alloy Invention Broad Preferred RR1000 A B Range Range Ni 52.3 46.34 43.35 Balance Balance Co 18.5 24 27 23 to 40 24 to 27 Cr 15 14.5 14.5 10 to 15 10 to 15 Mo 5 5 5 3 to 6 3 to 6 W 0 0 0 0 to 5 0 to 5 Al 3 3 3 3 2.5 to 4 2.5 to 4 Ti 3.6 4.5 4.5 3.4 to 5 3.4 to 5 Ta 2 2 2 1.35 to 2.5 1.35 to 2.5 Nb 0 0 0 0 to 2 0 Hf 0.5 0.55 0.55 0.5 to 1 0.5 to 1 Zr 0.06 0.06 0.06 0 to 0.1 0 to 0.1 C 0.027 0.03 0.027 0.01 to 0.05 0.01 to 0.05 B 0.015 0.02 0.015 0.01 to 0.05 0.01 to 0.05 Si 0 0 0 0 to 2 0 to 0.2
  • TCP phase forming elements in particular chromium
  • TCP phase forming elements in particular chromium
  • gamma prime forming elements there is a requirement to increase the levels of gamma prime forming elements to greater than 12at%, but increases of gamma prime forming elements above 13at% are likely to increase the propensity for processing problems, such as forgeability, quench cracking etc.
  • the addition of large amounts of titanium to a nickel base superalloy make it liable to the formation of TCP phases, in particular the eta phase, which is detrimental to the mechanical properties of the nickel base superalloy.
  • the nickel base superalloy has an increase in the volume fraction of the gamma prime phase, the precipitation of gamma prime phase with a Co 3 (Ta/Nb) chemistry, powder metallurgy processing route eliminates macro-segregation and allows more alloying additions.
  • the nickel base superalloy has lower density than conventional nickel base superalloys due to the increased level of cobalt.
  • the level of gamma prime forming elements is not too high. There is a reduced tendency for formation of TCP phases by control of chromium, titanium and the aluminium to titanium ratio.
  • the level of cobalt is determined using the fact that it is known to generate a minimum stacking fault energy promoting planar deformation when there is at least 15wt% cobalt. Cobalt is also considered to reduce fatigue crack growth rates as less damage accumulation occurs in planar slip, due to the ease of slip reversal. Addition of more than 20wt% cobalt increases the volume fraction of gamma prime precipitates and substitutes for nickel. Higher levels of cobalt reduce the gamma prime solvus temperature.
  • the level of chromium is controlled to balance a requirement for reduced fatigue crack propagation rates, e.g. higher levels of chromium, and greater propensity for TCP phase formation, e.g. lower levels of chromium.
  • Molybdenum and tungsten are both beneficial for creep properties.
  • the beneficial effects on tensile strength and ductility at high temperatures through solid solution strengthening are balanced against the propensity to form TCP phases.
  • Tantalum is controlled at a level to reduce crack growth and stabilise the MC carbide. Tantalum controls the volume fraction of gamma prime phase with aluminium and titanium.
  • Titanium is controlled with levels of tantalum to provide volume fraction of gamma prime phase. Additional titanium lowers the gamma prime solvus temperature. The maximum amount of titanium is controlled to prevent excessive formation of TCP phases.
  • Aluminium is controlled with the levels of tantalum and titanium to optimise strength.
  • nickel base superalloy there is no niobium in the nickel base superalloy and/or that there is no tungsten in the nickel base superalloy.
  • a feature of the nickel base superalloys according to the present invention is their ability to be processed at temperatures either below or above the gamma prime solvus temperature. Thus, they are capable of being produced in a fine grain size, typically 5 to 10 micrometers, or coarse grain size, typically greater than 30 micrometers.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A nickel base superalloy consisting of 20 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities. The gamma prime phase comprises (Ni/Co)3(Al/Ti/Ta).

Description

  • The present invention relates to a nickel base superalloy.
  • It is proposed to add cobalt and titanium to Udimet 720Li as disclosed in "Microstructure and Yield Strength of Udimet 720Li Alloyed with Co-16.9wt% Ti" C Cui, Y Gu, H Harada and A Sato, Metallurgical and Materials Transactions A, Volume 36A, November 2005, pp2921-2927 and "New Ni-Co-Base Disk Superalloys with Higher Strength and Creep Resistance" Y Gu, H Harada, C Cui, D Ping, A Sato and J Fujioka, Scripta Materialia, Volume 55, Issue 9, November 2006, pp815-818.
  • The addition of cobalt and titanium to Udimet 720Li increases the temperature and flow stress capability. It is known that cobalt modifies the solubility of the gamma prime phase in the gamma phase, raises the solidus temperature, lowers the gamma prime solvus temperature and lowers the stacking fault energy. The addition of titanium increases the volume fraction of gamma prime phase by forming Co3Ti with the same crystal structure as Ni3Al.
  • The addition of higher levels of cobalt and titanium to Udimet 720Li make the superalloy more prone to macro segregation during the casting process, suggesting a powder metallurgy process is more suitable for manufacturing large articles and limiting segregation to the nano-scale. The addition of large amounts of titanium to a nickel base superalloy, when coupled with high levels of cobalt, make it liable to the formation of Topologically Close Packed (TCP) phases, in particular the eta phase, a phenomonen excarbated due to cast and wrought processing. The TCP phases are detrimental to mechanical properties of the superalloy article. The TCP phases form during the initial processing, ageing heat treatment and/or during long-term exposure to heat in service. The papers mentioned above only consider the production of the superalloy using cast and wrought processing.
  • Nickel base superalloys containing high levels of refractory elements such as molybdenum, niobium, tantalum, tungsten etc, are difficult to process by conventional cast and wrought processing routes. This is due to the macro-segregation that occurs between atomic species, including aluminium and titanium, leading to variable microstructures and mechanical properties. Udimet 720Li is produced by the cast and wrought processing route, although it may be produced in a powder metallurgy form. Processing by the powder metallurgy route, although considered more expensive, allows for a greater degree of alloying additions to be made and eliminates macro-segregation, limiting segregation to the micro/nano-scale.
  • Accordingly the present invention seeks to provide a novel nickel base superalloy.
  • Accordingly the present invention provides a nickel base superalloy consisting of 23 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities.
  • Preferably the present invention provides a nickel base superalloy consisting of 23.5 to 30wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 1wt% silicon and the balance nickel plus incidental impurities.
  • Preferably the present invention provides a nickel base superalloy consisting of 23.5 to 28wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • Preferably the present invention provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027 to 0.03wt% carbon, 0.015 to 0.02wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • The present invention provides a nickel base superalloy consisting of 46.34wt% nickel, 24wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.03wt% carbon, 0.02wt% boron.
  • The present invention provides a nickel base superalloy consisting of 43.35wt% nickel, 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027wt% carbon, 0.015wt% boron.
  • The present invention also provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • Preferably the precipitated gamma prime phase comprises a (Ni/Co)3(Al/Ti/Ta).
  • Alternatively the precipitated gamma prime phase comprises a (Ni/Co)3(Al/Ti/Ta/Nb).
  • Preferably the precipitated gamma prime phases comprises Co3Ta and/or Co3Ti.
  • The present invention will be more fully described by way of example with reference to the accompanying drawings in which:-
    • Figure 1 shows a turbofan gas turbine engine having a turbine disc comprising a nickel base superalloy according to the present invention.
    • Figure 2 shows an enlarged view of turbine disc comprising a nickel base superalloy according to the present invention.
  • A turbofan gas turbine engine 10, as shown in figure 1, comprises in axial flow series an inlet 12, a fan section 14, a compressor section 16, a combustion section 18, a turbine section 20 and an exhaust 22. The turbofan gas turbine engine 10 is quite conventional and will not be discussed further.
  • The turbine section 20 comprises one or more turbine discs 24, shown more clearly in figure 2, comprising a nickel base superalloy according to the present invention. The present invention seeks to provide a nickel base superalloy which is a high strength alloy capable of use for applications at 750°C and above and which is stable.
  • The nickel base superalloy consists of 23 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities.
  • Preferably the nickel base superalloy consists of 23.5 to 30wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 1wt% silicon and the balance nickel plus incidental impurities.
  • More preferably the nickel base superalloy consists of 23.5 to 28wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • More preferably the nickel base superalloy consists of 24 to 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027 to 0.03wt% carbon, 0.015 to 0.02wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • One preferred nickel base superalloy consists of 46.34wt% nickel, 24wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.03wt% carbon, 0.02wt% boron.
  • Another preferred nickel base superalloy consists of 43.35wt% nickel, 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027wt% carbon, 0.015wt% boron.
  • The present invention also provides a nickel base superalloy consisting of 24 to 27wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  • The starting chemistry for a nickel base superalloy according to the present invention is RR1000 nickel base superalloy. The RR1000 nickel base superalloy is a gamma/gamma prime strengthened superalloy, which has a gamma prime composition of Ni3(Al/Ti/Ta/Hf) and an increased volume fraction of gamma prime over Udimet 720Li. The addition of cobalt and titanium to the RR1000 nickel base superalloy increases the gamma prime volume fraction further and changes the gamma prime chemistry to (Ni/Co)3(Al/Ti/Ta). In addition there is precipitation of a Co3Ta phase and/or Co3Ti phase. Alternatively cobalt and titanium may be added to other advanced nickel base superalloys, e.g. Rene95, ME3, Alloy10 or LSHR, to provide similar nickel base superalloys. In the case with nickel base superalloys containing niobium the gamma prime chemistry changes to (Ni/Co)3(Al/Ti/Ta/Nb).
  • The nickel base superalloys of the present invention are only capable of processing by the powder metallurgy route due to the high content of refractory elements. This allows for a wider range of elemental additions to be incorporated into the final nickel base superalloy composition. Table 1
    wt% Alloy
    720Li RR1000 Rene95 Rene 88DT ME3 Alloy 10 LSHR
    Ni bal bal bal bal bal bal bal
    Co 15 18.5 8.12 13.1 20.6 17.93 20.8
    Cr 16 15 12.94 15.8 13 10.46 12.7
    Mo 3 5 3.45 4 3.8 2.52 2.74
    W 1.25 0 3.43 3.9 2.1 4.74 4.37
    Al 2.5 3 3.42 2 3.4 3.53 3.48
    Ti 5 3.6 2.44 3.7 3.7 3.79 3.47
    Ta 0 2 0 0 2.4 1.61 1.65
    Nb 0 0 3.37 0.7 0 0.97 0
    Hf 0 0.5 0 0 0 0 0
    Zr 0 0.06 0.05 0.045 0.05 0.07 0.049
    C 0.015 0.027 0.07 0.05 0.04 0.027 0.024
    B 0.015 0.015 0.012 0.016 0.03 0.028 0.028
    Gamma prime formers (Ti+Ta+Al+Nb)
    7.5 8.6 9.23 6.4 9.5 9.9 8.6
    TCP formers (Mo+Cr+W)
    20.25 20 19.82 23.7 18.9 17.72 19.81
  • Table 1 shows the compositions of Udimet 720Li and some advanced powder metallurgy nickel base superalloys and shows how the advanced powder metallurgy nickel base superalloys have sought to optimise gamma prime volume fraction. It is clear that the level of the gamma prime forming elements, in terms of at%, is increased as well as the level of tantalum and niobium to change the chemistry of the gamma prime phase precipitated to (Ni/Co)3(Al/Ti/Ta/Nb).
  • Table 2 shows the compositions of alloys according to the present invention and the prior art alloy RR1000. Table 2
    wt% Alloy Invention Broad Preferred
    RR1000 A B Range Range
    Ni 52.3 46.34 43.35 Balance Balance
    Co 18.5 24 27 23 to 40 24 to 27
    Cr 15 14.5 14.5 10 to 15 10 to 15
    Mo 5 5 5 3 to 6 3 to 6
    W 0 0 0 0 to 5 0 to 5
    Al 3 3 3 2.5 to 4 2.5 to 4
    Ti 3.6 4.5 4.5 3.4 to 5 3.4 to 5
    Ta 2 2 2 1.35 to 2.5 1.35 to 2.5
    Nb 0 0 0 0 to 2 0
    Hf 0.5 0.55 0.55 0.5 to 1 0.5 to 1
    Zr 0.06 0.06 0.06 0 to 0.1 0 to 0.1
    C 0.027 0.03 0.027 0.01 to 0.05 0.01 to 0.05
    B 0.015 0.02 0.015 0.01 to 0.05 0.01 to 0.05
    Si 0 0 0 0 to 2 0 to 0.2
  • There is a requirement to reduce the levels of TCP phase forming elements, in particular chromium, in order to reduce the propensity for TCP phase formation during long term exposure at high temperatures. There is a requirement to increase the levels of gamma prime forming elements to greater than 12at%, but increases of gamma prime forming elements above 13at% are likely to increase the propensity for processing problems, such as forgeability, quench cracking etc. The addition of large amounts of titanium to a nickel base superalloy make it liable to the formation of TCP phases, in particular the eta phase, which is detrimental to the mechanical properties of the nickel base superalloy.
  • The advantages of the present invention is that the nickel base superalloy has an increase in the volume fraction of the gamma prime phase, the precipitation of gamma prime phase with a Co3(Ta/Nb) chemistry, powder metallurgy processing route eliminates macro-segregation and allows more alloying additions. The nickel base superalloy has lower density than conventional nickel base superalloys due to the increased level of cobalt. The level of gamma prime forming elements is not too high. There is a reduced tendency for formation of TCP phases by control of chromium, titanium and the aluminium to titanium ratio.
  • The level of cobalt is determined using the fact that it is known to generate a minimum stacking fault energy promoting planar deformation when there is at least 15wt% cobalt. Cobalt is also considered to reduce fatigue crack growth rates as less damage accumulation occurs in planar slip, due to the ease of slip reversal. Addition of more than 20wt% cobalt increases the volume fraction of gamma prime precipitates and substitutes for nickel. Higher levels of cobalt reduce the gamma prime solvus temperature.
  • The level of chromium is controlled to balance a requirement for reduced fatigue crack propagation rates, e.g. higher levels of chromium, and greater propensity for TCP phase formation, e.g. lower levels of chromium.
  • Molybdenum and tungsten are both beneficial for creep properties. The beneficial effects on tensile strength and ductility at high temperatures through solid solution strengthening are balanced against the propensity to form TCP phases.
  • Tantalum is controlled at a level to reduce crack growth and stabilise the MC carbide. Tantalum controls the volume fraction of gamma prime phase with aluminium and titanium.
  • Titanium is controlled with levels of tantalum to provide volume fraction of gamma prime phase. Additional titanium lowers the gamma prime solvus temperature. The maximum amount of titanium is controlled to prevent excessive formation of TCP phases.
  • Aluminium is controlled with the levels of tantalum and titanium to optimise strength.
  • Other elemental additions are niobium, boron, carbon, zirconium, hafnium, rhenium, yttrium and silicon.
  • It is preferred that there is no niobium in the nickel base superalloy and/or that there is no tungsten in the nickel base superalloy.
  • A feature of the nickel base superalloys according to the present invention is their ability to be processed at temperatures either below or above the gamma prime solvus temperature. Thus, they are capable of being produced in a fine grain size, typically 5 to 10 micrometers, or coarse grain size, typically greater than 30 micrometers.

Claims (12)

  1. A nickel base superalloy consisting of 23 to 40wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 2wt% silicon and the balance nickel plus incidental impurities.
  2. A nickel base superalloy as claimed in claim 1 consisting of 23.5 to 30wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0 to 2wt% niobium, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 1wt% silicon and the balance nickel plus incidental impurities.
  3. A nickel base superalloy as claimed in claim 1 or claim 2 consisting of 23.5 to 28wt% cobalt, 10 to 15wt% chromium, 3 to 6wt% molybdenum, 0 to 5wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  4. A nickel base superalloy as claimed in claim 3 consisting of 24 to 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027 to 0.03wt% carbon, 0.015 to 0.02wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  5. A nickel base superalloy as claimed in claim 4 consisting of 46.34wt% nickel, 24wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.03wt% carbon, 0.02wt% boron.
  6. A nickel base superalloy as claimed in claim 4 consisting of 43.35wt% nickel, 27wt% cobalt, 14.5wt% chromium, 5wt% molybdenum, 3wt% aluminium, 4.5wt% titanium, 2wt% tantalum, 0.55wt% hafnium, 0.06wt% zirconium, 0.027wt% carbon, 0.015wt% boron.
  7. A nickel base superalloy as claimed in claim 3 consisting of 24 to 27wt% cobalt, 10 to 15wt% chromium, 2 to 6wt% molybdenum, 0 to 5 wt% tungsten, 2.5 to 4wt% aluminium, 3.4 to 5 wt% titanium, 1.35 to 2.5wt% tantalum, 0.5 to 1wt% hafnium, 0 to 0.1wt% zirconium, 0.01 to 0.05wt% carbon, 0.01 to 0.05wt% boron, 0 to 0.2wt% silicon and the balance nickel plus incidental impurities.
  8. A nickel base superalloy as claimed in any of claims 1 to 7 wherein the precipitated gamma prime phase comprises a (Ni/Co)3(Al/Ti/Ta).
  9. A nickel base superalloy as claimed in any of claims 1 to 7 wherein the precipitated gamma prime phase comprises a (Ni/Co)3(Al/Ti/Ta/Nb).
  10. A nickel base superalloy as claimed in any of claims 1 to 7 wherein the precipitated gamma prime phases comprises Co3Ta and/or Co3Ti.
  11. A gas turbine engine component comprising a nickel base superalloy as claimed in any of claims 1 to 10.
  12. A gas turbine engine component as claimed in claim 11 wherein the component is a turbine disc or a compressor disc.
EP08252916A 2007-10-02 2008-09-02 A nickel based superalloy Expired - Fee Related EP2045345B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GBGB0719195.0A GB0719195D0 (en) 2007-10-02 2007-10-02 A nickel base superalloy

Publications (2)

Publication Number Publication Date
EP2045345A1 true EP2045345A1 (en) 2009-04-08
EP2045345B1 EP2045345B1 (en) 2011-07-06

Family

ID=38738976

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08252916A Expired - Fee Related EP2045345B1 (en) 2007-10-02 2008-09-02 A nickel based superalloy

Country Status (4)

Country Link
US (2) US20090087338A1 (en)
EP (1) EP2045345B1 (en)
JP (1) JP2009097094A (en)
GB (1) GB0719195D0 (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110088817A1 (en) * 2009-10-15 2011-04-21 Rolls-Royce Plc Method of forging a nickel base superalloy
EP2383356A1 (en) * 2010-04-29 2011-11-02 General Electric Company Cobalt-Nickel Superalloys, and Related Articles
EP2503013A1 (en) * 2009-11-19 2012-09-26 National Institute for Materials Science Heat-resistant superalloy
CN102816953A (en) * 2011-06-09 2012-12-12 通用电气公司 Alumina-Forming Cobalt-Nickel Base Alloy and Method of Making an Article Therefrom
CN102816965A (en) * 2011-06-09 2012-12-12 通用电气公司 Cobalt-nickel base alloy and method of making an article therefrom
EP2602336A1 (en) * 2010-11-10 2013-06-12 Honda Motor Co., Ltd. Nickel alloy
EP2620594A1 (en) * 2012-01-27 2013-07-31 Honeywell International Inc. Multi-material turbine components
WO2016016437A3 (en) * 2014-08-01 2016-04-07 Friedrich-Alexander-Universität Erlangen-Nürnberg Cobalt-based super alloy
CN107960109A (en) * 2015-04-01 2018-04-24 牛津大学创新有限公司 Nickel-base alloy
US10138534B2 (en) 2015-01-07 2018-11-27 Rolls-Royce Plc Nickel alloy
US10266919B2 (en) 2015-07-03 2019-04-23 Rolls-Royce Plc Nickel-base superalloy
DE102018208736A1 (en) * 2018-06-04 2019-12-05 Siemens Aktiengesellschaft Y, Y 'hardened cobalt-nickel base alloy, powder, component and process
DE102018208737A1 (en) * 2018-06-04 2019-12-05 Siemens Aktiengesellschaft Y, Y` hardened cobalt-nickel base alloy, powder, component and process

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8349250B2 (en) * 2009-05-14 2013-01-08 General Electric Company Cobalt-nickel superalloys, and related articles
CN102549182A (en) 2009-09-14 2012-07-04 公立大学法人大阪府立大学 W Ni3(Si, ti)-based intermetallic compound and method for producing the same
JP2012107269A (en) * 2010-11-15 2012-06-07 National Institute For Materials Science Nickel-based heat-resistant superalloy and heat-resistant superalloy member
GB2497128A (en) * 2011-12-02 2013-06-05 Rolls Royce Plc Nickel-based alloys comprising 0.2-0.6 % by weight silicon
US9540714B2 (en) 2013-03-15 2017-01-10 Ut-Battelle, Llc High strength alloys for high temperature service in liquid-salt cooled energy systems
US9377245B2 (en) 2013-03-15 2016-06-28 Ut-Battelle, Llc Heat exchanger life extension via in-situ reconditioning
US10017842B2 (en) 2013-08-05 2018-07-10 Ut-Battelle, Llc Creep-resistant, cobalt-containing alloys for high temperature, liquid-salt heat exchanger systems
US9435011B2 (en) 2013-08-08 2016-09-06 Ut-Battelle, Llc Creep-resistant, cobalt-free alloys for high temperature, liquid-salt heat exchanger systems
GB201400352D0 (en) 2014-01-09 2014-02-26 Rolls Royce Plc A nickel based alloy composition
US9683280B2 (en) 2014-01-10 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
CN104894434B (en) * 2014-03-04 2018-04-27 中国科学院金属研究所 A kind of corrosion and heat resistant nickel base superalloy of tissue stabilization
US9683279B2 (en) 2014-05-15 2017-06-20 Ut-Battelle, Llc Intermediate strength alloys for high temperature service in liquid-salt cooled energy systems
US9605565B2 (en) 2014-06-18 2017-03-28 Ut-Battelle, Llc Low-cost Fe—Ni—Cr alloys for high temperature valve applications
US10563293B2 (en) * 2015-12-07 2020-02-18 Ati Properties Llc Methods for processing nickel-base alloys
US20200010930A1 (en) * 2017-02-21 2020-01-09 Hitachi Metals, Ltd. Ni-based super heat-resistant alloy and method for manufacturing same
BR112019021654A2 (en) * 2017-04-21 2020-05-12 Crs Holdings, Inc. SUPERCALINATE BASED ON CLEAN-NICKEL HARDENING BY PRECIPITATION AND ITEM MANUFACTURED FROM THE SUPERLIGA ON COBALT-NICKEL BASED BY PRECIPITATION
WO2018216067A1 (en) * 2017-05-22 2018-11-29 川崎重工業株式会社 High temperature component and method for producing same
US11787105B2 (en) * 2019-11-14 2023-10-17 Rolls-Royce Corporation Fused filament fabrication of components including predetermined yield points based on composition functions
CN114262822B (en) * 2021-12-28 2022-05-31 北京钢研高纳科技股份有限公司 Nickel-based powder superalloy and preparation method and application thereof

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2101536A5 (en) * 1970-07-06 1972-03-31 Int Nickel Ltd
EP0248757A1 (en) * 1986-06-02 1987-12-09 United Technologies Corporation Nickel base superalloy articles and method for making
US5370497A (en) * 1991-10-24 1994-12-06 Hitachi, Ltd. Gas turbine and gas turbine nozzle
EP1195446A1 (en) * 2000-10-04 2002-04-10 General Electric Company Ni based superalloy and its use as gas turbine disks, shafts, and impellers
US6521175B1 (en) * 1998-02-09 2003-02-18 General Electric Co. Superalloy optimized for high-temperature performance in high-pressure turbine disks

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3146136A (en) * 1961-01-24 1964-08-25 Rolls Royce Method of heat treating nickel base alloys
US4908069A (en) * 1987-10-19 1990-03-13 Sps Technologies, Inc. Alloys containing gamma prime phase and process for forming same
US5476555A (en) * 1992-08-31 1995-12-19 Sps Technologies, Inc. Nickel-cobalt based alloys
EP1842934B1 (en) * 2004-12-02 2011-10-19 National Institute for Materials Science Heat-resistant superalloy

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2101536A5 (en) * 1970-07-06 1972-03-31 Int Nickel Ltd
EP0248757A1 (en) * 1986-06-02 1987-12-09 United Technologies Corporation Nickel base superalloy articles and method for making
US5370497A (en) * 1991-10-24 1994-12-06 Hitachi, Ltd. Gas turbine and gas turbine nozzle
US6521175B1 (en) * 1998-02-09 2003-02-18 General Electric Co. Superalloy optimized for high-temperature performance in high-pressure turbine disks
EP1195446A1 (en) * 2000-10-04 2002-04-10 General Electric Company Ni based superalloy and its use as gas turbine disks, shafts, and impellers

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
C CUI ET AL.: "Microstructure and Yield Strength of Udimet 720Li Alloyed with Co-16.9wt% Ti", METALLURGICAL AND MATERIALS TRANSACTIONS A, vol. 36A, November 2005 (2005-11-01), pages 2921 - 2927
Y GU ET AL., NEW NI-CO-BASE DISK SUPERALLOYS WITH HIGHER STRENGTH AND CREEP RESISTANCE, vol. 55, no. 9, November 2006 (2006-11-01), pages 815 - 818

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110088817A1 (en) * 2009-10-15 2011-04-21 Rolls-Royce Plc Method of forging a nickel base superalloy
EP2503013A1 (en) * 2009-11-19 2012-09-26 National Institute for Materials Science Heat-resistant superalloy
EP2503013A4 (en) * 2009-11-19 2016-04-06 Nat Inst For Materials Science Heat-resistant superalloy
EP2383356A1 (en) * 2010-04-29 2011-11-02 General Electric Company Cobalt-Nickel Superalloys, and Related Articles
CN102234732A (en) * 2010-04-29 2011-11-09 通用电气公司 Cobalt-nickel superalloys, and related articles
EP2602336A4 (en) * 2010-11-10 2014-02-19 Honda Motor Co Ltd Nickel alloy
US8961646B2 (en) 2010-11-10 2015-02-24 Honda Motor Co., Ltd. Nickel alloy
EP2602336A1 (en) * 2010-11-10 2013-06-12 Honda Motor Co., Ltd. Nickel alloy
CN102816965A (en) * 2011-06-09 2012-12-12 通用电气公司 Cobalt-nickel base alloy and method of making an article therefrom
EP2532761A1 (en) * 2011-06-09 2012-12-12 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
CN102816953A (en) * 2011-06-09 2012-12-12 通用电气公司 Alumina-Forming Cobalt-Nickel Base Alloy and Method of Making an Article Therefrom
US10227678B2 (en) 2011-06-09 2019-03-12 General Electric Company Cobalt-nickel base alloy and method of making an article therefrom
EP2620594A1 (en) * 2012-01-27 2013-07-31 Honeywell International Inc. Multi-material turbine components
US9266170B2 (en) 2012-01-27 2016-02-23 Honeywell International Inc. Multi-material turbine components
WO2016016437A3 (en) * 2014-08-01 2016-04-07 Friedrich-Alexander-Universität Erlangen-Nürnberg Cobalt-based super alloy
US10138534B2 (en) 2015-01-07 2018-11-27 Rolls-Royce Plc Nickel alloy
CN107960109A (en) * 2015-04-01 2018-04-24 牛津大学创新有限公司 Nickel-base alloy
US10358701B2 (en) 2015-04-01 2019-07-23 Oxford University Innovation Limited Nickel-based alloy
US10266919B2 (en) 2015-07-03 2019-04-23 Rolls-Royce Plc Nickel-base superalloy
US10422024B2 (en) 2015-07-03 2019-09-24 Rolls-Royce Plc Nickel-base superalloy
DE102018208736A1 (en) * 2018-06-04 2019-12-05 Siemens Aktiengesellschaft Y, Y 'hardened cobalt-nickel base alloy, powder, component and process
DE102018208737A1 (en) * 2018-06-04 2019-12-05 Siemens Aktiengesellschaft Y, Y` hardened cobalt-nickel base alloy, powder, component and process

Also Published As

Publication number Publication date
US20120269646A1 (en) 2012-10-25
GB0719195D0 (en) 2007-11-14
JP2009097094A (en) 2009-05-07
US20090087338A1 (en) 2009-04-02
EP2045345B1 (en) 2011-07-06

Similar Documents

Publication Publication Date Title
EP2045345B1 (en) A nickel based superalloy
US9945019B2 (en) Nickel-based heat-resistant superalloy
EP2503013B1 (en) Heat-resistant superalloy
EP1842934B1 (en) Heat-resistant superalloy
JP5177559B2 (en) Ni-based single crystal superalloy
EP2006402B1 (en) Ni-BASE SUPERALLOY AND METHOD FOR PRODUCING SAME
EP2076616B1 (en) Nickel-base superalloys
US7169241B2 (en) Ni-based superalloy having high oxidation resistance and gas turbine part
JP3814662B2 (en) Ni-based single crystal superalloy
US8764919B2 (en) High-temperature-resistant cobalt-base superalloy
WO2012026354A1 (en) Co-based alloy
EP1433865B2 (en) High-strength Ni-base superalloy and gas turbine blades
US6071470A (en) Refractory superalloys
CN105543568B (en) A kind of platiniferous non-rhenium nickel base single crystal superalloy and its preparation method and application
JP2009149976A (en) Ternary nickel eutectic alloy
EP1927669B1 (en) Low-density directionally solidified single-crystal superalloys
WO2006104059A1 (en) COBALT-FREE Ni BASE SUPERALLOY
US6159314A (en) Nickel-base single-crystal superalloys, method for manufacturing the same, and gas turbine parts prepared therefrom
EP3042973B1 (en) A nickel alloy
EP3833793B1 (en) Nickel based alloy
EP3121298B1 (en) Ni-base alloy for structural applications
JP2014051698A (en) Ni-BASED FORGING ALLOY, AND GAS TURBINE USING THE SAME
JP7324254B2 (en) Co-Based Alloy Material, Co-Based Alloy Product, and Method for Making Same
KR20240017621A (en) Ni-based super heat resisting alloy and manufacturing method thereof
WO2017154809A1 (en) Ni-BASED UNIDIRECTIONALLY SOLIDIFIED ALLOY

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

17P Request for examination filed

Effective date: 20090319

17Q First examination report despatched

Effective date: 20090518

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602008008077

Country of ref document: DE

Effective date: 20110825

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20110706

26N No opposition filed

Effective date: 20120411

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602008008077

Country of ref document: DE

Effective date: 20120411

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20120925

Year of fee payment: 5

Ref country code: SE

Payment date: 20120927

Year of fee payment: 5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20121001

Year of fee payment: 5

Ref country code: ES

Payment date: 20120926

Year of fee payment: 5

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20120927

Year of fee payment: 5

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20111017

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130903

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20130902

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 602008008077

Country of ref document: DE

Effective date: 20140401

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140530

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130902

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130930

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140401

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20221001

Year of fee payment: 5