Metal joining and strengthening methods utilizing microstructural enhancement
A method for joining first and second metal portions includes welding together the portions such that a weld nugget joins them, compressively stressing the weld nugget throughout its volume, and heat treating the compressively stressed weld nugget to recrystallize metal therein. A method for strengthening a metal element includes imparting compressive stress within a region of the metal element, and heat treating it such that metal of the region recrystallizes with a finer grain structure than was present in the region before the step of imparting the compressive stress. A repaired metal part includes a first, original section made of metal alloy, and a second, repair section of metal alloy joined to the original section by a recrystallized metal weld having crystals within +/−3 ASTM-112 grain sizes of the size of the crystals of the original and repair sections.
1. A method for repairing a metal rotor blade, comprising:
welding a metal patch to a portion of a metal rotor blade to form a weld nugget joining the metal patch and the portion of the metal rotor blade;
compressively stressing the weld nugget throughout its volume while maintaining shape of at least a section of the metal patch and the metal rotor blade away from the weld nugget; and
heat treating the compressively stressed weld nugget to recrystallize metal therein.
2. The method of claim 1 , further comprising overlapping the portion of the metal rotor blade with a flange of the metal patch before the welding.
3. The method of claim 2 , wherein welding comprises utilizing one of an electron beam and a laser beam, and the flange acts as a beam stop during the welding.
4. The method of claim 1 , the welding comprising generating an as-welded structure having at least one dimension that exceeds a desired dimension of a corresponding portion of the metal rotor blade after completing repair of the metal rotor blade.
5. The method of claim 1 , the step of welding, the metal patch and the portion of the metal rotor blade being formed of a similar alloy that is one of a titanium-based alloy and a nickel-based alloy.
6. The method of claim 1 , the heat treating comprising heating at least the weld nugget to a temperature sufficient to recrystallize metal thereof.
7. The method of claim 1 , the heat treating comprising heating at least the weld nugget to a temperature that, in combination with the compressively stressing, is sufficient to recrystallize metal thereof to a parent metallurgical state of the metal patch and the portion of the metal rotor blade.
8. The method of claim 1 , further comprising maintaining a substantially constant force pressing together the metal patch and the portion of the metal rotor blade, to keep the metal patch and the portion of the metal rotor blade in intimate contact during the step of welding while allowing for thermal expansion of at least one of the metal patch and the metal rotor blade.
9. The method of claim 1 , the compressively stressing comprising indenting the weld nugget with a series of overlapping indentations.
10. The method of claim 9 , the compressively stressing further comprising indenting a heat affected zone adjacent to the weld nugget with a series of overlapping indentations.
11. The method of claim 10 , the compressively stressing comprising forming each of the overlapping indentations with a primary dimension such that each of the indentations overlaps an adjacent one of the indentations by 10% to 50% of the primary dimension.
12. The method of claim 1 , further comprising compressively stressing the weld nugget subsequent to the step of heat treating.
13. The method of claim 12 , further comprising compressively stressing a heat affected zone adjacent to the weld nugget subsequent to the step of heat treating.
14. The method of claim 1 , in the step of welding the metal patch and the portion of the metal rotor blade being formed of a nickel-based alloy, the method further comprising:
preheating a preheat zone that includes overlap sections of each of the metal patch and the portion of the metal rotor blade, to a preheat temperature substantially close to one of a gamma prime solvus temperature and a gamma double prime solvus temperature of the nickel-based alloy forming the metal patch and the portion of the metal rotor blade, before the welding; and
wherein the welding comprises performing the welding while the preheat zone remains substantially at the preheat temperature, and the step of compressively stressing comprises forging the preheat zone.
15. The method of claim 14 , the welding comprising performing the welding with equipment utilized for the preheating, and wherein the equipment performs the welding within 10 seconds of discontinuing the preheating.
16. The method of claim 15 , the welding comprising performing the welding with equipment utilized for the preheating, and wherein the equipment performs the welding within one second of discontinuing the preheating.
17. The method of claim 14 , the welding comprising performing the welding while maintaining the preheat zone at the preheat temperature.
18. The method of claim 14 , the preheating comprising heating the preheat zone to a temperature within a range of 300 degrees Fahrenheit below the one of the gamma prime and the gamma double prime solvus temperatures, to the respective gamma prime or gamma double prime solvus temperature.
19. The method of claim 18 , the preheating comprising heating the preheat zone to a temperature within a range of 150 degrees Fahrenheit below the one of the gamma prime and the gamma double prime solvus temperature, to the respective gamma prime or gamma double prime solvus temperature.
20. The method of claim 14 , further comprising cooling the preheat zone in a controlled manner after the welding.
21. The method of claim 20 , the cooling comprising lowering a temperature of the preheat zone at a rate of 500 degrees Fahrenheit, or less, per minute.
22. The method of claim 1 , the portion of the metal rotor blade being part of an integrally bladed rotor.