Nickel-based alloy comprising tantalum

Abstract

The invention relates to a nickel-based alloy comprising, in weight percent: 4.0 to 20.0% cobalt, 14.0 to 18.5% chromium, 1.8 to 2.6% aluminum, 1.3 to 1.9% titanium, 5.5 to 6.5% tantalum, 0.01 to 0.10% carbon, 0.003 to 0.02% boron, and 0.01 to 0.10% zirconium. A method for manufacturing a part made of the nickel-based alloy includes preparing a billet which has the same composition as that of the nickel-based alloy, shaping the part, and heat treating the part.

1 . A nickel-based alloy comprising, in weight percent:
 4.0 to 20.0% cobalt;   14.0 to 18.5% chromium;   1.8 to 2.6% aluminum;   1.3 to 1.9% titanium;   5.5 to 6.5% tantalum;   0.01 to 0.10% carbon;   0.003 to 0.02% boron; et   0.01 to 0.10% zirconium;   0 to 5.0% molybdenum;   0 to 5.0% iron;   0 to 9.0 tungsten; and   0 to 1.0% niobium.   
     
     
         2 . The nickel-based alloy according to  claim 1 , comprising, in weight percent:
 0.02 to 0.05% carbon.   
     
     
         3 . The nickel-based alloy according to  claim 1 , comprising, in weight percent:
 2.0 to 2.5% aluminum;   1.4 to 1.8% titanium; and   5.7 to 6.4% tantalum.   
     
     
         4 . A method for manufacturing a part made of a nickel-based alloy according to  claim 1 , the method comprising:
 manufacturing a billet which has the same composition as that of the nickel-based alloy;   shaping the part; and   heat treating the part.   
     
     
         5 . The method according to  claim 4 , wherein heat treating the part comprises at least one treatment among:
 a γ′ supersolvus solution heat treatment, preferably at a temperature that is 10 to 40° C. higher than the γ′ solvus; and   a γ′ subsolvus solution heat treatment, preferably at a temperature that is 10 to 40° C. lower than the γ′ solvus.   
     
     
         6 . The method according to  claim 4 , wherein the heat treatment further comprises:
 a tempering to precipitate M 23 C 6 type carbides, preferably by heating to a temperature between 825 and 870° C.; and   optionally a tempering to stabilize the populations of γ′ precipitates, preferably at a temperature between 76° and 825° C.   
     
     
         7 . An aeronautical part made of an alloy according to  claim 1 , in particular a turbine casing. 
     
     
         8 . The nickel-based alloy according to  claim 2 , comprising, in weight percent:
 2.0 to 2.5% aluminum;   1.4 to 1.8% titanium; and   5.7 to 6.4% tantalum.   
     
     
         9 . A method for manufacturing a part made of a nickel-based alloy according to  claim 2 , the method comprising:
 manufacturing a billet which has the same composition as that of the nickel-based alloy;   shaping the part; and   heat treating the part.   
     
     
         10 . A method for manufacturing a part made of a nickel-based alloy according to  claim 3 , the method comprising:
 manufacturing a billet which has the same composition as that of the nickel-based alloy;   shaping the part; and   heat treating the part.   
     
     
         11 . The method according to  claim 5 , wherein the heat treatment further comprises:
 a tempering to precipitate M 23 C 6 type carbides, preferably by heating to a temperature between 825 and 870° C.; and   optionally a tempering to stabilize the populations of γ′ precipitates, preferably at a temperature between 76° and 825° C.   
     
     
         12 . An aeronautical part made of an alloy according to  claim 2 , in particular a turbine casing. 
     
     
         13 . An aeronautical part made of an alloy according to  claim 3 , in particular a turbine casing.