Welding of nickel-base superalloys having a nil-ductility range

• US 5,897,801 A
• Filed: 01/22/1997
• Issued: 04/27/1999
• Est. Priority Date: 01/22/1997
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kelly, Thomas J., Snyder, John H., Smashey, Russell W., Sheranko, Ronald L.
• Primary Examiner(s): Shaw, Clifford C.
• Application Number:
  US08/787,356
• Time in Patent Office: 825 Days
• Field of Search: 219/121.14, 219/121.13, 219/121.38, 219/121.46, 219/121.64, 219/129, 219/137 WM, 219/76.15, 219/76.14, 148/524, 148/525, 148/527, 228/119
• US Class Current: 219/137.0WM
• CPC Class Codes: B23K 35/304 with Cr as the next major constituent
• CPC Class Codes: B23K 9/0026 specially adapted for particular articles or work
• CPC Class Codes: B23K 9/04 Welding for other purposes than joining, e.g. built-up welding
• CPC Class Codes: B23K 9/23 taking account of the properties of the materials to be welded
• CPC Class Codes: B23P 6/007 using only additive methods, e.g. build-up welding
• CPC Class Codes: B23P 6/045 of turbine components, e.g. moving or stationary blades, rotors, etc.
• CPC Class Codes: F01D 5/005 Repairing methods or devices

Abstract

An article made of a nickel-base superalloy having a nil-ductility range from the solidus temperature of the alloy to about 600° F. below the solidus temperature is welded, as for example in the weld repair of surface cracks, by removing foreign matter from the area to be welded, first stress relieving the article, adjusting the temperature of the article to a welding temperature of from about 1800° F. to about 2100° F., welding a preselected area in an inert atmosphere at the welding temperature, and second stress relieving the article. Welding is preferably accomplished by striking an arc in the preselected area so as to locally melt the alloy in the preselected area, providing a filler metal having the same composition as the nickel-based superalloy of the article, and feeding the filler metal into the arc so that the filler metal is melted and fused with the article to form a weldment upon solidification.

Claims

1. A method of welding a nickel-base superalloy having a nilductility range from the solidus temperature of the alloy to about 600°

F. below the solidus temperature, comprising the steps of

furnishing an article made of a nickel-base superalloy having a nil-ductility range from the solidus temperature of the alloy to about 600°

F. below the solidus temperature;

removing any foreign matter present in a welding area of the article to be welded;

first heating the article at a first stress-relieving temperature in the nil-ductility range;

adjusting the temperature of the article to a bulk-material welding temperature within the nil-ductility range, but less than the first-stress-relieving temperature;

welding the welding area of the article, in an inert atmosphere, at the welding temperature; and

second heating the article from the welding temperature to a second stress relieving temperature in the nil-ductility range, but above the welding temperature,

the steps of first heating, adjusting, welding, and second heating being accomplished without reducing the temperature of the welding area to substantially less than the bulk temperature of the article.

2. The method of claim 1, wherein the step of furnishing includes the step of

furnishing a nickel base superalloy having a composition, in weight percent, selected from the group consisting of R108, having a nominal composition of 0.07-0.10 percent carbon, 8.0-8.7 percent chromium, 9.0-10.0 percent cobalt, 0.4-0.6 percent molybdenum, 9.3-9.7 percent tungsten, 2.5-3.3 percent tantalum, 0.6-0.9 percent titanium, 5.25-5.75 percent aluminum, 0.01-0.02 percent boron, 1.3-1.7 percent hafnium, 0.1 percent maximum manganese, 0.06 percent maximum silicon, 0.01 percent maximum phosphorus, 0.004 percent maximum sulfur, 0.005-0.02 percent zirconium, 0.1 percent maximum niobium, 0.1 percent maximum vanadium, 0.1 percent maximum copper, 0.2 percent maximum iron, 0.003 percent maximum magnesium, 0.002 percent maximum oxygen, 0.002 percent maximum nitrogen, balance nickel and incidental impurities;

Mar M-246, having a nominal composition of 8.25 percent copper, 10.0 percent cobalt, 0.7 percent molybdenum, 10.0 percent tungsten, 1.0 percent titanium, 5.5 percent aluminum, 0.5 percent maximum iron, 0.15 percent carbon, 0.015 percent boron, 0.05 percent zirconium, 1.5 percent hafnium, 3.0 percent tantalum, balance nickel and incidental impurities;

Mar M-200, having a nominal composition of 0.15 percent carbon, 9 percent chromium, 10 percent cobalt, 1 percent iron, 5 percent aluminum, 0.015 percent boron, 2 percent titanium, 12.5 percent tungsten, 0.05 percent zirconium, 1 percent niobium, balance nickel and incidental impurities;

AF2-1DA, having a nominal composition of 0.35 percent carbon, 12 percent chromium, 10 percent cobalt, 3 percent molybdenum, 0.5 percent maximum iron, 4.6 percent aluminum, 0.015 percent boron, 3 percent titanium, 6 percent tungsten, 0.1 percent zirconium, 1.5 percent tantalum, balance nickel and incidental impurities;

Udimet 500, having a nominal composition of 0.1 percent carbon, 18 percent chromium, 17 percent cobalt, 4 percent molybdenum, 2 percent iron, 3 percent aluminum, 3 percent titanium, balance nickel and incidental impurities;

B1900, having a nominal composition of 0.1 percent carbon, 8 percent chromium, 10 percent cobalt, 6 percent molybdenum, 6 percent aluminum, 0.015 percent boron, 1 percent titanium, 0.1 percent zirconium, 4 percent tantalum, balance nickel and incidental impurities;

Inconel 100, having a nominal composition of 0.18 percent carbon, 9.5 percent chromium, 15 percent cobalt, 3 percent molybdenum, 5.5 percent aluminum, 0.015 percent boron, 4.2 percent titanium, 0.06 percent zirconium, 1 percent vanadium, balance nickel and incidental impurities;

Udimet 700, having a nominal composition of 0.1 percent carbon, 15 percent chromium, 18.5 percent cobalt, 5.25 percent molybdenum, 4.25 percent aluminum, 0.03 percent boron, 3.5 percent titanium, balance nickel and incidental impurities; and

Rene 80, having a nominal composition of 0.17 percent carbon, 14 percent chromium, 9.5 percent cobalt, 4 percent molybdenum, 3 percent aluminum, 0.015 percent boron, 5 percent titanium, 4 percent tungsten, 0.03 percent zirconium, balance nickel and incidental impurities.

3. The method of claim 1, wherein the step of removing includes the step of

removing foreign matter from the region of a crack in the article by grinding away material around the crack.

4. The method of claim 1, wherein the step of removing includes the step of

removing foreign matter from the region of a crack in the article by grinding away material around the crack to a width of at least about 2 times the width of the crack.

5. The method of claim 1, wherein the step of removing includes the step of

chemically cleaning the welding area.

6. The method of claim 1, wherein the step of first heating includes the step of

heating the article to a temperature of from about 2000°

F. to about 2200°

F.

7. The method of claim 1, wherein the step of adjusting the temperature includes the step of

adjusting the temperature to a welding temperature of from about 1800°

F. to about 2100°

F.

8. The method of claim 1, wherein the step of welding includes the step of

striking an arc in the welding area so as to locally melt the alloy in the welding area.

9. The method of claim 1, wherein the step of welding includes the step of

providing a filler metal having the same composition as the nickel-based superalloy of the article.

10. The method of claim 1, wherein the step of second heating includes the step of

heating the article to a temperature of from about 2000°

F. to about 2200°

F.

11. The method of claim 1, wherein there is no step of hot isostatic pressing at any time in the processing.

12. A method of welding a nickel-base superalloy having a nil-ductility range from the solidus temperature of the alloy to about 600°

F. below the solidus temperature, comprising the steps of

furnishing an article made of a nickel-base superalloy having a nil-ductility range from the solidus temperature of the alloy to about 600°

F. below the solidus temperature;

removing any foreign matter present in a welding area of the article to be welded;

first heating the article to a temperature of from about 2000°

F. to about 2200°

F.;

adjusting the temperature of the article to a bulk-material welding temperature of from about 1800°

F. to about 2100°

F.; and

welding the welding area of the article, in an inert atmosphere, at the bulk-material welding temperature, the step of welding including the steps of

striking an arc in the welding area so as to locally melt the alloy in the welding area,

providing a filler metal, and

feeding the filler metal into the arc so that the filler metal is melted and fused with the article; and

second heating the article from the bulk-material welding temperature to a temperature of from about 2000°

F. to about 2200°

F., the steps of first heating, adjusting, welding, and second heating being accomplished without reducing the temperature of the welding area to substantially less than the bulk temperature of the article.

13. The method of claim 12, wherein the step of furnishing includes the step of

furnishing a nickel base superalloy having a composition, in weight percent, selected from the group consisting of R108, having a nominal composition of 0.07-0.10 percent carbon, 8.0-8.7 percent chromium, 9.0-10.0 percent cobalt, 0.4-0.6 percent molybdenum, 9.3-9.7 percent tungsten, 2.5-3.3 percent tantalum, 0.6-0.9 percent titanium, 5.25-5.75 percent aluminum, 0.010.02 percent boron, 1.3-1.7 percent hafnium, 0.1 percent maximum manganese, 0.06 percent maximum silicon, 0.01 percent maximum phosphorus, 0.004 percent maximum sulfur, 0.005-0.02 percent zirconium, 0.1 percent maximum niobium, 0.1 percent maximum vanadium, 0.1 percent maximum copper, 0.2 percent maximum iron, 0.003 percent maximum magnesium, 0.002 percent maximum oxygen, 0.002 percent maximum nitrogen, balance nickel and incidental impurities;

Mar M-246, having a nominal composition of 8.25 percent copper, 10.0 percent cobalt, 0.7 percent molybdenum, 10.0 percent tungsten, 1.0 percent titanium, 5.5 percent aluminum, 0.5 percent maximum iron, 0.15 percent carbon, 0.015 percent boron, 0.05 percent zirconium, 1.5 percent hafnium, 3.0 percent tantalum, balance nickel and incidental impurities;

Mar M200, having a nominal composition of 0.15 percent carbon, 9 percent chromium, 10 percent cobalt, 1 percent iron, 5 percent aluminum, 0.015 percent boron, 2 percent titanium, 12.5 percent tungsten, 0.05 percent zirconium. 1 percent niobium, balance nickel and incidental impurities;

AF2-1DA, having a nominal composition of 0.35 percent carbon, 12 percent chromium, 10 percent cobalt, 3 percent molybdenum, 0.5 percent maximum iron, 4.6 percent aluminum, 0.015 percent boron, 3 percent titanium, 6 percent tungsten, 0.1 percent zirconium, 1.5 percent tantalum, balance nickel and incidental impurities;

Udimet 500, having a nominal composition of 0.1 percent carbon, 18 percent chromium, 17 percent cobalt, 4 percent molybdenum, 2 percent iron, 3 percent aluminum, 3 percent titanium, balance nickel and incidental impurities;

B1900, having a nominal composition of 0.1 percent carbon, 8 percent chromium, 10 percent cobalt, 6 percent molybdenum, 6 percent aluminum, 0.015 percent boron, 1 percent titanium, 0.1 percent zirconium, 4 percent tantalum, balance nickel and incidental impurities;

Inconel 100, having a nominal composition of 0.18 percent carbon, 9.5 percent chromium, 15 percent cobalt, 3 percent molybdenum, 5.5 percent aluminum, 0.015 percent boron, 4.2 percent titanium, 0.06 percent zirconium, 1 percent vanadium, balance nickel and incidental impurities;

Udimet 700, having a nominal composition of 0.1 percent carbon, 15 percent chromium, 18.5 percent cobalt, 5.25 percent molybdenum, 4.25 percent aluminum, 0.03 percent boron, 3.5 percent titanium, balance nickel and incidental impurities; and

Rene 80, having a nominal composition of 0.17 percent carbon, 14 percent chromium, 9.5 percent cobalt, 4 percent molybdenum, 3 percent aluminum, 0.015 percent boron, 5 percent titanium, 4 percent tungsten, 0.03 percent zirconium, balance nickel and incidental impurities.

14. The method of claim 12, wherein the step of providing includes the step of

providing a filler metal having the same composition as the nickel-based superalloy of the article.

15. The method of claim 12, wherein the step of removing includes the step of

removing foreign matter from the region of a crack in the article by grinding away material around the crack.

16. The method of claim 12, wherein the step of removing includes the step of

removing foreign matter from the region of a crack in the article by grinding away material around the crack to a width of at least about 2 times the width of the crack.

17. The method of claim 12, wherein the step of removing includes the step of

chemically cleaning the welding area.