Optimized nickel-based superalloy

Abstract

A nickel-based alloy for high-temperature applications, in particular for use in turbomachines, which has a chemical composition as set forth in the claims, wherein the ratio of the fractions of Ta to Al in percent by weight is greater than or equal to 1 and less than or equal to 2, and wherein the ratio of the fractions of Co to W in percent by weight is greater than or equal to 2 and less than or equal to 5.

What is claimed is: 
     
         1 . A nickel-based alloy for high-temperature applications, wherein the alloy has a chemical composition which comprises, in % by weight:
 Al from 3.7 to 7.0   Co from 10 to 20   Cr from 2.1 to 7.2   Mo from 1.1 to 3.0   Re from 5.7 to 9.2   Ru from 3.1 to 8.5   Ta from 4.1 to 11.9   Ti from 0 to 3.3   from 2.1 to 4.9   from 0 to 0.05   Si from 0 to 0.1   Mn from 0 to 0.05   from 0 to 0.015   S from 0 to 0.001   from 0 to 0.003   Cu from 0 to 0.05   Fe from 0 to 0.15   from 0 to 0.15   Zr from 0 to 0.015   from 0 to 0.001   remainder nickel and unavoidable impurities, and wherein a ratio of fractions of Ta to Al in percent by weight is greater than or equal to 1 and less than or equal to 2, and a ratio of fractions of Co to W in percent by weight is greater than or equal to 2 and less than or equal to 5.   
     
     
         2 . The nickel-based alloy of  claim 1 , wherein the ratio of the fractions of Co to W in percent by weight is less than or equal to 4. 
     
     
         3 . The nickel-based alloy of  claim 1 , wherein a ratio of fractions of W to Mo in percent by weight is greater than or equal to 1 and less than or equal to 4. 
     
     
         4 . The nickel-based alloy of  claim 1 , wherein a ratio of fractions of Co to Re in percent by weight is greater than or equal to 1 and less than or equal to 2. 
     
     
         5 . The nickel-based alloy of  claim 1 , wherein the alloy comprises, in percent by weight:
 from 5.0 to 7.0% Al and/or   from 10.5 to 15.0% Co and/or   from 4.0 to 6.0% Cr and/or   from 1.1 to 2.5% Mo and/or   from 5.5 to 7.0% Re and/or   from 3.1 to 5.5% Ru and/or   from 5.0 to 9.0% Ta and/or   from 0 to 2.0% Ti and/or   from 3.0 to 4.5% W.   
     
     
         6 . The nickel-based alloy of  claim 1 , wherein the alloy comprises, in percent by weight:
 from 5.5 to 6.0% Al and/or   from 11.0 to 12.0% Co and/or   from 4.5 to 5.5% Cr and/or   from 1.1 to 2.0% Mo and/or   from 5.7 to 6.5% Re and/or   from 3.3 to 5.0% Ru and/or   from 5.5 to 8.0% Ta and/or   from 0.5 to 2.0% Ti, and/or   from 3.5 to 4.5% W.   
     
     
         7 . The nickel-based alloy of  claim 5 , wherein the alloy comprises, in percent by weight:
 from 5.5 to 6.0% Al and/or   from 11.0 to 12.0% Co and/or   from 4.5 to 5.5% Cr and/or   from 1.1 to 2.0% Mo and/or   from 5.7 to 6.5% Re and/or   from 3.3 to 5.0% Ru and/or   from 5.5 to 8.0% Ta and/or   from 0.5 to 2.0% Ti, and/or   from 3.5 to 4.5% W.   
     
     
         8 . The nickel-based alloy of  claim 6 , wherein the alloy comprises from 1.1 to 1.7% Ti. 
     
     
         9 . The nickel-based alloy of  claim 7 , wherein the alloy comprises from 1.1 to 1.7% Ti. 
     
     
         10 . The nickel-based alloy of  claim 1 , wherein a density of the alloy is less than or equal to 9.09 g/cm 3 . 
     
     
         11 . The nickel-based alloy of  claim 10 , wherein the density of the alloy is less than or equal to 8.94 g/cm 3 . 
     
     
         12 . The nickel-based alloy of  claim 10 , wherein the density of the alloy is less than or equal to 8.85 g/cm 3 . 
     
     
         13 . The nickel-based alloy of  claim 10 , wherein the density of the alloy is less than or equal to 8.80 g/cm 3 . 
     
     
         14 . The nickel-based alloy of  claim 1 , wherein the alloy comprises a γ matrix and γ′-precipitates, a fraction of W and/or Mo in the γ matrix being greater than in the γ′-precipitates. 
     
     
         15 . A component of a turbomachine, wherein the turbomachine comprises the nickel-based alloy of  claim 1 . 
     
     
         16 . The component of  claim 15 , wherein the nickel-based alloy is formed as a single crystal. 
     
     
         17 . The component of  claim 15 , wherein the nickel-based alloy is formed by directed solidification. 
     
     
         18 . A process for making a component of a turbomachine, wherein the process comprises forming the component or a part thereof from the alloy of  claim 1 .