Nickel-base superalloys and articles formed therefrom

Abstract

An article, such as a turbine engine component, formed from a nickel-base superalloy, the nickel-base superalloy containing a γ″ tetragonal phase and comprising aluminum, titanium, tantalum, niobium, chromium, molybdenum, and the balance nickel, wherein the article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100° F. in the presence of steam. The invention also includes a nickel-base superalloy for forming such and article and methods of forming the article and making the nickel-base superalloy.

1. An article formed from a nickel-base superalloy, said nickel-base superalloy containing a γ″ tetragonal phase and comprising: between about 0.05 and about 2.0 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 15 and about 25 weight percent chromium; up to about 40 weight percent iron; from about 6 to about 12 weight percent molybdenum; between about 2 and about 7 weight percent niobium; from about 2 to about 3 weight percent tantalum; up to about 2.5 weight percent titanium; and the balance nickel, wherein said article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100° F. in the presence of steam. 
     
     
       2. The article of  claim 1 , wherein said article has a yield strength of greater than 130 ksi at about 750° F. 
     
     
       3. The article of  claim 2 , wherein said article has a yield strength of greater than 146 ksi at about 750° F. 
     
     
       4. The article of  claim 3 , wherein said yield strength is at least 160 ksi at about 750° F. 
     
     
       5. The article of  claim 1 , further comprising cobalt. 
     
     
       6. The article of  claim 1 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.5 and about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       7. The article of  claim 6 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 21 weight percent chromium; about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.5 and about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.8 and about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       8. The article of  claim 7 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; about 5 weight percent cobalt; about 19 weight percent chromium; about 8 weight percent iron; about 6.4 weight percent molybdenum; about 3.5 weight percent niobium; about 3 weight percent tantalum; about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       9. The article of  claim 1 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       10. The article of  claim 9 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       11. The article of  claim 10 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; about 0.9 weight percent titanium; and a balance of nickel. 
     
     
       12. The article of  claim 1 , wherein said nickel-base superalloy further comprises: at least one element selected from the group consisting of tungsten, rhenium, and vanadium. 
     
     
       13. The article of  claim 12 , wherein said nickel-base superalloy further comprises up to about 3 weight percent tungsten. 
     
     
       14. The article of  claim 12 , wherein said nickel-base superalloy further comprises up to about 3 weight percent rhenium. 
     
     
       15. A  The article of  claim 12 , wherein said nickel-base superalloy further comprises up to about 1 weight percent vanadium. 
     
     
       16. The article of  claim 1 , wherein said nickel-base superalloy further comprises at least one element selected from the group consisting of carbon, manganese, magnesium, boron, silicon, and zirconium. 
     
     
       17. The article of  claim 1 , wherein said article has a crack propagation resistance of at least 200 hours to failure at about 1100° F. in the presence of steam. 
     
     
       18. The article of  claim 1 , wherein said article is a turbine engine component. 
     
     
       19. The article of  claim 18 , wherein said turbine engine component is a component selected from the group consisting of compressor rotors, compressor vanes, compressor stators, combustor cans, nozzles, turbine discs, turbine wheels, and buckets. 
     
     
       20. The article of  claim 18 , wherein said turbine engine component is a component in a land-based turbine engine. 
     
     
       21. The article of  claim 18 , wherein said turbine engine component is a component in an aircraft turbine engine. 
     
     
       22. A nickel-base superalloy for forming an article, said nickel-base superalloy containing a γ″ tetragonal phase and comprising: between about 0.05 and about 2.0 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 15 and about 25 weight percent chromium; up to about 40 weight percent iron; from about 6 to about 12 weight percent molybdenum; between about 2 and about 7 weight percent niobium; from about 2 to about 3 weight percent tantalum; up to about 2.5 weight percent titanium; and the balance nickel, wherein said nickel-base superalloy has a crack propagation resistance of at least 20 hours to failure at about 1100° F. in the presence of steam and a yield strength of greater than 130 ksi at about 750° F. 
     
     
       23. The nickel-base superalloy of  claim 22 , wherein said nickel-base superalloy has a yield strength of greater than 146 ksi at about 750° F. 
     
     
       24. The nickel-base superalloy of  claim 22 , wherein said yield strength is at least 160 ksi at about 750° F. 
     
     
       25. The nickel-base superalloy of  claim 22 , wherein said crack propagation resistance is at least 200 hours to failure at about 1100° F. in the presence of steam. 
     
     
       26. The nickel-base superalloy of  claim 22 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; from 3.5 to about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       27. The nickel-base superalloy of  claim 26 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 21 weight percent chromium; about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.5 and about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.8 and about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       28. The nickel-base superalloy of  claim 27 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; about 5 weight percent cobalt; about 19 weight percent chromium; about 8 weight percent iron; about 6.4 weight percent molybdenum; about 3.5 weight percent niobium; about 3 weight percent tantalum; about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       29. The nickel-base superalloy of  claim 22 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt, between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       30. The nickel-base superalloy of  claim 29 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       31. The nickel-base superalloy of  claim 30 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; about 0.9 weight percent titanium; and a balance of nickel. 
     
     
       32. An article formed from a nickel-base superalloy, the nickel-base superalloy containing a γ″ tetragonal phase and comprising between about 0.05 and about 2.0 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 15 and about 25 weight percent chromium; up to about 40 weight percent iron; from about 6 to about 12 weight percent molybdenum; between about 2 and about 7 weight percent niobium; from about 2 to about 3 weight percent tantalum; up to about 2.5 weight percent titanium; and the balance nickel, wherein said article has a time dependent crack propagation resistance of at least 20 hours to failure at about 1100° F. in the presence of steam and a yield strength of greater than 130 ksi at about 750° F. 
     
     
       33. The article of  claim 32 , wherein said article has a yield strength of greater than 146 ksi at about 750° F. 
     
     
       34. The article of  claim 32 , wherein said yield strength is at least 160 ksi at about 750° F. 
     
     
       35. The article of  claim 32 , wherein said crack propagation resistance is least 200 hours to failure at about 1100° F. in the presence of steam. 
     
     
       36. The article of  claim 32 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.5 and about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       37. The article of  claim 36 , wherein said nickel-base superalloy comprises: between about 0.1 and about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 21 weight percent chromium; about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.5 and about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.8 and about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       38. The article of  claim 37 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; about 5 weight percent cobalt; about 19 weight percent chromium; about 8 weight percent iron; about 6.4 weight percent molybdenum; about 3.5 weight percent niobium; about 3 weight percent tantalum; about 1.0 weight percent titanium; and a balance of nickel. 
     
     
       39. The article of  claim 36 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 19 and about 22 weight percent chromium; up to about 8.0 weight percent iron; between about 6 and about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       40. The article of  claim 39 , wherein said nickel-base superalloy comprises: between about 0.2 and about 0.6 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; between at least 3.6 and about 5.5 weight percent niobium; from about 2 to about 3 weight percent tantalum; between about 0.6 and about 2.0 weight percent titanium; and a balance of nickel. 
     
     
       41. The article of  claim 40 , wherein said nickel-base superalloy comprises: about 0.5 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; about 21.5 weight percent chromium; about 2.5 weight percent iron; about 9 weight percent molybdenum; about 5.1 weight percent niobium; from about 2 to about 3 weight percent tantalum; about 0.9 weight percent titanium; and a balance of nickel. 
     
     
       42. The article of  claim 32 , wherein said nickel-base superalloy further comprises at least one element selected from the group consisting of tungsten, rhenium, and vanadium. 
     
     
       43. The article of  claim 42 , wherein said nickel-base superalloy further comprises up to about 3 weight percent tungsten. 
     
     
       44. A  The article of  claim 42 , wherein said nickel-base superalloy further comprises up to about 3 weight percent rhenium. 
     
     
       45. The article of  claim 42 , wherein said nickel-base superalloy further comprises up to about 1 weight percent vanadium. 
     
     
       46. The article of  claim 32 , wherein said article is a turbine engine component. 
     
     
       47. The article of  claim 46 , wherein said turbine engine component is a component selected from the group consisting of compressor rotors, compressor vanes, compressor stators, combustor cans, nozzles, turbine discs, turbine wheels, and buckets. 
     
     
       48. The article of  claim 46 , wherein said turbine engine component is a component in a land-based turbine engine. 
     
     
       49. The article of  claim 46 , wherein said turbine engine component is a component in an aircraft turbine engine. 
     
     
       50. An article formed from a nickel-base superalloy, said nickel-base superalloy containing a γ″ tetragonal phase and comprising: between about 0.05 and about 2.0 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 15 and about 25 weight percent chromium; up to about 40 weight percent iron; from about 6 to about 12 weight percent molybdenum; between about 2 and about 7 weight percent niobium; from about 2 to about 3 weight percent tantalum; up to about 2.5 weight percent titanium; and the balance nickel, wherein said article has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100° F. in the presence of steam, and wherein said article is formed by: forming an ingot of the nickel-base superalloy; remelting the ingot a first time; remelting the ingot a second time; homogenizing the ingot by heat treating the ingot at a first temperature below a melting temperature of the nickel-base superalloy; billetizing the ingot, thereby creating a billet; hot-working the billet; and solution treating the billet at a second temperature below a solvus temperature of a high temperature phase of the superalloy to form the nickel-base superalloy article. 
     
     
       51. The article of  claim 50 , wherein the second temperature is below a δ-solvus temperature of the nickel-base superalloy. 
     
     
       52. The article of  claim 50 , wherein said article is a turbine engine component. 
     
     
       53. The article of  claim 52 , wherein said turbine engine component is a component selected from the group consisting of compressor rotors, compressor vanes, compressor stators, combustor cans, nozzles, turbine discs, turbine wheels, and buckets. 
     
     
       54. The article of  claim 52 , wherein said turbine engine component is a component in a land-based turbine engine. 
     
     
       55. The article of  claim 52 , wherein said turbine engine component is a component in an aircraft turbine engine. 
     
     
       56. The article of  claim 52 , wherein said article has a diameter of at least about 20 inches. 
     
     
       57. A nickel-base superalloy, said nickel-base superalloy containing a γ″ tetragonal phase and comprising: between about 0.05 and about 2.0 weight percent aluminum; from about 1.5 to about 5 weight percent cobalt; between about 15 and about 25 weight percent chromium; up to about 40 weight percent iron; from about 6 to about 12 weight percent molybdenum; between about 2 and about 7 weight percent niobium; from about 2 to about 3 weight percent tantalum; up to about 2.5 weight percent titanium; and the balance nickel, wherein said nickel-base superalloy has a time dependent crack propagation resistance of at least about 20 hours to failure at about 1100° F. in the presence of steam, and wherein said nickel-base superalloy is formed by: forming an ingot of the nickel-base superalloy; remelting the ingot a first time; remelting the ingot a second time; homogenizing the ingot to a first temperature below a melting temperature of the nickel-base superalloy; billetizing the ingot, thereby creating a billet; hot-working the billet; and solution treating the billet at a second temperature below a solvus temperature of a high temperature phase of the superalloy. 
     
     
       58. The nickel-base alloy of  claim 57 , wherein the second temperature is below a δ-solvus temperature of the nickel-base superalloy. 
     
     
       59. A turbine engine component formed from a nickel- base superalloy, the nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      between about  0 . 05  and about  0 . 5  percent aluminum, cobalt is present and is present in a concentration up to about  5  percent, between about  19  and  22  percent chromium, up to about  8  percent iron, between about  6  and about  9  percent molybdenum, between about  3 . 3  and about  5 . 4  percent niobium, tantalum is present and is present in a concentration of up to  3  percent, between about  0 . 2  and about  1 . 6  percent titanium and the balance nickel; and        wherein the nickel - base superalloy comprising the turbine engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.     
     
     
       60. The turbine engine component of  claim 59  wherein the nickel- base superalloy comprises:      about  0 . 5  percent aluminum, about  21 . 5  percent chromium, about  2 . 5  percent iron, about  9  percent molybdenum, about  5 . 1  percent niobium about  0 . 9  percent titanium and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  1680  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy comprising the engine component has a yield strength of at least about  160  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  177  ksi and a room temperature ultimate tensile strength of at least about  221  ksi.     
     
     
       61. The turbine engine component of  claim 60  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 ° F., the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       62. The turbine engine component of  claim 59  wherein the nickel- base superalloy comprises:      about  0 . 5  percent aluminum, about  21 . 5  percent chromium, about  2 . 5  percent iron, about  9  percent molybdenum, about  5 . 1  percent niobium about  0 . 9  percent titanium and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  1680  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy comprising the engine component has a grain size of less than about  5  microns.     
     
     
       63. The turbine engine component of  claim 62  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., and grain size is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       64. A turbine engine component formed from a nickel- base superalloy, said nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent,      about  0 . 5  percent aluminum, cobalt is present, about  19  percent chromium, about  18 . 5  percent iron, about  3  percent molybdenum, about  5 . 1  percent niobium, about  0 . 9  percent titanium, tantalum is present and is present in a concentration of up to about  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy comprising the engine component has a yield strength of at least about  146  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  164  ksi and a room temperature ultimate tensile strength of about  212  ksi.     
     
     
       65. The turbine engine component of  claim 64  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 ° F., the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       66. A turbine engine component formed from a nickel- base superalloy, said nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      about  0 . 5  percent aluminum, cobalt is present, about  19  percent chromium, about  18 . 5  percent iron, about  3  percent molybdenum, about  5 . 1  percent niobium, about  0 . 9  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the nickel - base superalloy comprising the engine component has a grain size of less than about  5  microns.     
     
     
       67. The turbine engine component of  claim 66  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., and the grain size is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       68. A turbine engine component formed from a nickel- base superalloy, said nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      about  0 . 09  percent aluminum, cobalt is present, about  20 . 9  percent chromium, about  7 . 91  percent iron, about  7 . 92  percent molybdenum, about  3 . 48  percent niobium, about  1 . 57  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  2139  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy comprising the engine component has a yield strength of at least about  163  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  177  ksi and a room temperature ultimate tensile strength of at least about  220  ksi.     
     
     
       69. The turbine engine component of  claim 68  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 ° F., the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       70. A turbine engine component formed from a nickel- base superalloy, said nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      about  0 . 09  percent aluminum, cobalt is present, about  20 . 9  percent chromium, about  7 . 91  percent iron, about  7 . 92  percent molybdenum, about  3 . 48  percent niobium, about  1 . 57  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the engine component has a crack propagation resistance of at least about  2139  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the nickel - base superalloy comprising the engine component has a grain size of less than about  28  microns.     
     
     
       71. The turbine engine component of  claim 70  wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., and grain size is achieved by first homogenizing the nickel- base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.   
     
     
       72. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, of between about  0 . 05  and about  0 . 5  percent aluminum, cobalt is present and is present in a concentration up to about  5  percent, between about  19  and  22  percent chromium, up to about  8  percent iron, between about  6  and about  9  percent molybdenum, between about  3 . 3  and about  5 . 4  percent niobium, tantalum is present and is present in a concentration of up to  3  percent, between about  0 . 2  and about  1 . 6  percent titanium and the balance nickel;        wherein the nickel - base superalloy comprising the turbine engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F. is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       73. The turbine disc of  claim 72  wherein the nickel- base superalloy comprises about  0 . 5  percent aluminum, about  21 . 5  percent chromium, about  2 . 5  percent iron, about  9  percent molybdenum, about  5 . 1  percent niobium about  0 . 9  percent titanium and the balance nickel;      wherein the nickel - base superalloy has a crack propagation resistance of at least about  1680  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy further has a yield strength of at least about  160  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  177  ksi and a room temperature ultimate tensile strength of at least about  221  ksi.     
     
     
       74. The turbine disc of  claim 72  wherein the nickel- base superalloy comprises about  0 . 5  percent aluminum, about  21 . 5  percent chromium, about  2 . 5  percent iron, about  9  percent molybdenum, about  5 . 1  percent niobium about  0 . 9  percent titanium and the balance nickel;      wherein the nickel - base superalloy has a crack propagation resistance of at least about  1680  hours to failure at  1100 ° F. in the presence of steam; and        wherein the nickel - base superalloy further has a grain size of less than about  5  microns.     
     
     
       75. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, about  0 . 5  percent aluminum, cobalt is present, about  19  percent chromium, about  18 . 5  percent iron, about  3  percent molybdenum, about  5 . 1  percent niobium, about  0 . 9  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the turbine disc has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam;        wherein the nickel - base superalloy comprising the turbine disc has a yield strength of at least about  146  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  164  ksi and a room temperature ultimate tensile strength of at least about  212  ksi; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 °, the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       76. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, about  0 . 5  percent aluminum, cobalt is present, about  19  percent chromium, about  18 . 5  percent iron, about  3  percent molybdenum, about  5 . 1  percent niobium, about  0 . 9  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the turbine disc has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.;        wherein the nickel - base superalloy comprising the turbine disc has a grain size of less than about  5  microns; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 °, the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       77. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, of about  0 . 09  percent aluminum, cobalt is present, about  20 . 9  percent chromium, about  7 . 91  percent iron, about  7 . 92  percent molybdenum, about  3 . 48  percent niobium, about  1 . 57  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the turbine disc has a crack propagation resistance of at least about  2139  hours to failure at  1100 ° F. in the presence of steam;        wherein the nickel - base superalloy comprising the turbine disc has a yield strength of at least about  163  ksi at a temperature of  750 ° F., a room temperature yield strength of at least about  177  ksi and a room temperature ultimate tensile strength of about  220  ksi; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 °, the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       78. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, of about  0 . 09  percent aluminum, cobalt is present, about  20 . 9  percent chromium, about  7 . 91  percent iron, about  7 . 92  percent molybdenum, about  3 . 48  percent niobium, about  1 . 57  percent titanium, tantalum is present and is present in a concentration of up to  3  percent and the balance nickel;        wherein the nickel - base superalloy comprising the turbine disc has a crack propagation resistance of at least about  2139  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.;        wherein the nickel - base superalloy comprising the turbine disc has a grain size of less than about  28  microns; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F., the yield strength at  750 °, the room temperature yield strength and the room temperature ultimate tensile strength is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       79. A turbine engine component formed from a nickel- base superalloy, the nickel - base superalloy including a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      between about  0 . 1  and about  0 . 6  percent aluminum, cobalt is present and is present in a concentration up to about  5  percent, between about  19  and  22  percent chromium, up to about  8  percent iron, between about  6  and about  9  percent molybdenum, between about  3 . 5  and about  5 . 1  percent niobium, tantalum is present and is present in a concentration of up to  3  percent, between about  0 . 6  and about  2 . 0  percent titanium and the balance nickel;        wherein the nickel - base alloy comprising the turbine engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F. is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       80. A turbine engine component formed from a nickel- base superalloy, the nickel - base superalloy containing a γ″ tetragonal phase, the nickel - base superalloy comprising, in weight percent:      between about  0 . 2  and about  0 . 6  percent aluminum, cobalt is present and is present in a concentration up to about  5  percent, between about  19  and  22  percent chromium, up to about  8  percent iron, between about  6  and about  9  percent molybdenum, between about  3 . 6  and about  5 . 5  percent niobium, tantalum is present and is present in a concentration of up to  3  percent, between about  0 . 6  and about  2 . 0  percent titanium and the balance nickel;        wherein the nickel - base superalloy comprising the turbine engine component has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F. is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       81. The turbine engine component of  claim 80  wherein the nickel- base superalloy includes about  21 . 5  percent chromium, about  2 . 5  percent iron and about  9  percent molybdenum.   
     
     
       82. A turbine disc for a gas turbine engine comprising:
   a nickel - base superalloy including a γ″ tetragonal phase and having a composition, in weight percent, of between about  0 . 2  and about  0 . 6  percent aluminum, cobalt is present and is present in a concentration up to about  5  percent, between about  19  and  22  percent chromium, up to about  8  percent iron, between about  6  and about  9  percent molybdenum, between about  3 . 6  and about  5 . 5  percent niobium, tantalum is present and is present in a concentration of up to  3  percent, between about  0 . 6  and about  2 . 0  percent titanium and the balance nickel;        wherein the nickel - base superalloy comprising the turbine disc has a crack propagation resistance of at least about  200  hours to failure at  1100 ° F. in the presence of steam and a yield strength of at least about  130  ksi at a temperature of  750 ° F.; and        wherein the γ″ tetragonal phase providing the crack propagation resistance at  1100 ° F. is achieved by first homogenizing the nickel - base superalloy, then shaping the superalloy at a temperature below the homogenization temperature, then solutioning the shaped superalloy at a temperature below a  δ- solvus temperature or Laves solvus temperature of the shaped superalloy to partially solution the shaped superalloy to precipitate in a matrix the phase that is primarily γ″ tetragonal.     
     
     
       83. The turbine disc of  claim 82  wherein the nickel- base superalloy includes about  21 . 5  percent chromium, about  2 . 5  percent iron and about  9  percent molybdenum.