Nickel base superalloy compositions and superalloy articles

Abstract

A superalloy composition comprising, in weight percent: about 6.2-6.6 Al, about 6.5-7.0 Ta, about 6.0-7.0 Cr, about 6.25-7.0 W, about 1.5-2.5 Mo, about 0.15-0.60 Hf, 0.0-1.0 Re, 6.5-9.0 Co, optionally, 0.03-0.06 C, optionally, up to about 0.004 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, such that the superalloy composition exhibits a stress rupture capability improvement of at least 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 Hf, 0.0 Re, 7.5 Co. Articles incorporating the superalloy composition include a gas turbine engine component such as a high pressure turbine nozzle or nozzle segment.

1 . A superalloy composition comprising, 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 Hf, 0.0 Re, 7.5 Co, balance nickel. 
     
     
         2 . The superalloy composition according to  claim 1  comprising not more than about 0.5 weight percent rhenium. 
     
     
         3 . The superalloy composition according to  claim 1  comprising substantially 0 weight percent rhenium. 
     
     
         4 . The superalloy composition according to  claim 1  comprising about 0.5 weight percent rhenium. 
     
     
         6 . The superalloy composition according to  claim 2  comprising from 6.5 to about 6.6 weight percent tantalum. 
     
     
         7 . A superalloy composition consisting 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. 
     
     
         8 . The superalloy composition according to  claim 7  consisting of about 6.5 to about 6.6 weight percent tantalum. 
     
     
         9 . The superalloy composition according to  claim 7  consisting of substantially 0 weight percent rhenium. 
     
     
         10 . The superalloy composition according to  claim 7  consisting of about 0.5 weight percent rhenium. 
     
     
         11 . The superalloy composition according to  claim 7 , consisting of, in weight percent: about 6.3 aluminum (Al), about 6.5 tantalum (Ta), about 6.0 chromium (Cr), from about 6.25 to about 7 tungsten (W), about 2.0 molybdenum (Mo), about 0.60 hafnium (Hf), substantially 0.0 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 and incidental impurities. 
     
     
         12 . An article formed of a superalloy composition according to  claim 1 . 
     
     
         13 . The article according to  claim 12  comprising a gas turbine engine component. 
     
     
         14 . The article according to  claim 13  comprising a high pressure turbine nozzle or nozzle segment. 
     
     
         15 . An article formed of a superalloy composition according to  claim 7 . 
     
     
         16 . The article according to  claim 15  comprising a gas turbine engine component. 
     
     
         17 . The article according to  claim 16  comprising a high pressure turbine nozzle or nozzle segment. 
     
     
         18 . An article formed of a superalloy composition according to  claim 11 . 
     
     
         19 . The article according to  claim 18  comprising a gas turbine engine component. 
     
     
         20 . The article according to  claim 19  comprising a high pressure turbine nozzle or nozzle segment.