Directionally solidified eutectic superalloys for elevated temperature applications

Abstract

A measurement device for measuring and displaying a physical quantity such as a heartbeat, an atmospheric pressure or temperature, or the like, includes a clock for counting time, a physical quantity measuring device for measuring the physical quantity to be displayed, a processor for determining a plurality of values based on the measured physical quantity and the counted time, a first display for simultaneously displaying the plurality of values and a second display for magnifying at least one of the values and displaying the magnified value.

1 . An alloy, comprising: 
 a Ni-based matrix comprising, on a weight basis, about 5-7% Al, up to about 0.025% B, about 0.1-0.5% C, about 3-13% Co, about 2-7% Cr, up to about 5% Mo, up to about 1% Nb, about 2-7% Re, about 10-13% Ta, up to about 1.8% Ti, about 4-7% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.    
     
     
         2 . The alloy of  claim 1 , wherein the Ni-based matrix comprises, on a weight basis, about 0.8-1.8% Ti.  
     
     
         3 . The alloy of  claim 1 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6% Al, up to about 0.01% B, about 0.15-0.3% C, about 11-13% Co, about 3-5% Cr, about 0.8-1.8% Mo, about 4.5-5.6% Re, about 10-12% Ta, about 5-6% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         4 . The alloy of  claim 1 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6.1% Al, up to about 0.01% B, about 0.15-0.3%C, about 6.25-7.25% Co, about 2-3.1% Cr, up to about 1.1% Mo, about 0.1-1% Nb, about 4.75-5.9% Re, about 9-11% Ta, about 0.5-1.5% Ti, about 5.5-6.8% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         5 . The alloy of  claim 1 , further comprising an aligned eutectic reinforcing fibrous phase disposed within the Ni-based matrix, the aligned eutectic reinforcing fibrous phase comprising a carbide.  
     
     
         6 . The alloy of  claim 5 , wherein the carbide comprises substantially TaC.  
     
     
         7 . A directionally solidified eutectic superalloy, comprising: 
 a Ni-based matrix comprising, on a weight basis, about 5-7% Al, up to about 0.025% B, about 0.1-0.5% C, about 3-13% Co, about 2-7% Cr, up to about 5% Mo, up to about 1% Nb, about 2-7% Re, about 10-13% Ta, up to about 1.8% Ti, about 4-7% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities; and    an aligned eutectic reinforcing fibrous phase disposed within the Ni-based matrix, the aligned eutectic reinforcing fibrous phase comprising a carbide.    
     
     
         8 . The directionally solidified eutectic superalloy of  claim 7 , wherein the Ni-based matrix comprises, on a weight basis, about 0.8-1.8% Ti.  
     
     
         9 . The directionally solidified eutectic superalloy of  claim 7 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6% Al, up to about 0.01% B, about 0.15-0.3% C, about 11-13% Co, about 3-5% Cr, about 0.8-1.8% Mo, about 4.5-5.6% Re, about 10-12% Ta, about 5-6% W, up to about 1% V, up to about 0.2% Hf. and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         10 . The directionally solidified eutectic superalloy of  claim 7 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6.1% Al, up to about 0.01% B, about 0.15-0.3%C, about 6.25-7.25% Co, about 2-3.1% Cr, up to about 1.1%-Mo, about 0.1-1% Nb, about 4.75-5.9% Re, about 9-11% Ta, about 0.5-1.5% Ti, about 5.5-6.8% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         11 . The directionally solidified eutectic superalloy of  claim 7 , wherein the carbide comprises substantially TaC.  
     
     
         12 . An article of manufacture comprising an alloy, the alloy comprising: 
 a Ni-based matrix comprising, on a weight basis, about 5-7% Al, up to about 0.025% B, about 0.1-0.5% C, about 3-13% Co, about 2-7% Cr, up to about 5% Mo, up to about 1% Nb, about 2-7% Re, about 10-13% Ta, up to about 1.8% Ti, about 4-7% W, up to about 1% V, up to about 0.2% Hf, and up to about 0. 1% Zr, the balance being essentially Ni and incidental impurities.    
     
     
         13 . The article of manufacture of  claim 12 , wherein the Ni-based matrix comprises, on a weight basis, about 0.8-1.8% Ti.  
     
     
         14 . The article of manufacture of  claim 12 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6% Al, up to about 0.01% B, about 0.15-0.3% C, about 11-13% Co, about 3-5% Cr, about 0.8-1.8% Mo, about 4.5-5.6% Re, about 10-12% Ta, about 5-6% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         15 . The article of manufacture of  claim 12 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6.1% Al, up to about 0.01% B, about 0.15-0.3% C, about 6.25-7.25% Co, about 2-3.1% Cr, up to about 1.1% Mo, about 0.1-1% Nb, about 4.75-5.9% Re, about 9-11% Ta, about 0.5-1.5% Ti, about 5.5-6.8% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         16 . The article of manufacture of  claim 12 , wherein the alloy further comprises an aligned eutectic reinforcing fibrous phase disposed within the Ni-based matrix, the aligned eutectic reinforcing fibrous phase comprising a carbide.  
     
     
         17 . The article of manufacture of  claim 16 , wherein the carbide comprises substantially TaC.  
     
     
         18 . The article of manufacture of  claim 12 , wherein the article of manufacture comprises a gas turbine engine component.  
     
     
         19 . The article of manufacture of  claim 18 , wherein the gas turbine engine component comprises a turbine airfoil.  
     
     
         20 . An article of manufacture comprising a directionally solidified eutectic superalloy, the directionally solidified eutectic superalloy comprising: 
 a Ni-based matrix comprising, on a weight basis, about 5-7% Al, up to about 0.025% B, about 0.1-0.5% C, about 3-13% Co, about 2-7% Cr, up to about 5% Mo, up to about 1% Nb, about 2-7% Re, about 10-13% Ta, up to about 1.8% Ti, about 4-7% W, up to about 1% V, up to about 0.2% Hf. and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities; and    an aligned eutectic reinforcing fibrous phase disposed within the Ni-based matrix, the aligned eutectic reinforcing fibrous phase comprising a carbide.    
     
     
         21 . The article of manufacture of  claim 20 , wherein the Ni-based matrix comprises, on a weight basis, about 0.8-1.8% Ti.  
     
     
         22 . The article of manufacture of  claim 20 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6% Al, up to about 0.01% B, about 0.15-0.3% C, about 11-13% Co, about 3-5% Cr, about 0.8-1.8% Mo, about 4.5-5.6% Re, about 10-12% Ta, about 5-6% W, up to about 1% V, up to about 0.2% Hf. and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         23 . The article of manufacture of  claim 20 , wherein the Ni-based matrix comprises, on a weight basis, about 5-6.1% Al, up to about 0.01% B, about 0.15-0.3% C, about 6.25-7.25% Co, about 2-3.1% Cr, up to about 1.1% Mo, about 0.1-1% Nb, about 4.75-5.9% Re, about 9-11% Ta, about 0.5-1.5% Ti, about 5.5-6.8% W, up to about 1% V, up to about 0.2% Hf, and up to about 0.1% Zr, the balance being essentially Ni and incidental impurities.  
     
     
         24 . The article of manufacture of  claim 20 , wherein the carbide comprises substantially TaC.  
     
     
         25 . The article of manufacture of  claim 20 , wherein the article of manufacture comprises a gas turbine engine component.  
     
     
         26 . The article of manufacture of  claim 25 , wherein the gas turbine engine component comprises a turbine airfoil.