Low temperature diffusion braze repair of single crystal components
The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).
1. A process for repairing cracks in a component, said process comprising the steps of:
providing a component with at least one crack;
applying a repair alloy composition consisting of from 5 to 50 wt % of a single crystal nickel based material, from 40 to 60 wt % of a first nickel based braze alloy, and from 10 to 35 wt % of a second nickel based braze alloy to the at least one crack; and
subjecting said component with said repair alloy composition to a thermal cycle to diffuse the braze alloy composition into said at least one crack and repair said component.
2. The process according to claim 1 , wherein said component providing step comprises providing a component formed from a single crystal nickel based alloy.
3. The process according to claim 1 , wherein said component providing step comprises providing a component formed from a single crystal nickel based alloy having a composition containing from 5 to 10 wt % chromium, from 5 to 10 wt % cobalt, from 5 to 6.2 wt % aluminum, up to 1.9 wt % molybdenum, from 4 to 6 wt % tungsten, from 8 to 12 wt % tantalum, up to 0.35 wt % hafnium, up to 3.0 wt % rhenium, and the balance nickel.
4. The process according to claim 1 , wherein said repair alloy composition applying step comprises applying a repair alloy containing a single crystal nickel based material consisting of from 5 to 10 wt % chromium, from 5 to 10 wt % cobalt, from 1.5 to 3.5 wt % titanium, from 4.2 to 6.2 wt % aluminum, up to 1.9 wt % molybdenum, from 4 to 6 wt % tungsten, from 4.8 to 12 wt % tantalum, up to 0.5 wt % columbium, up to 0.35 wt % hafnium, up to 0.004 wt % boron, up to 3.0 wt % rhenium, up to 0.013 wt % yttrium, and the balance nickel, a first nickel based braze alloy consisting of 14 wt % chromium, 10 wt % cobalt, 3.5 wt % aluminum, 2.5 wt % tantalum, 2.75 wt % boron, 0.1 wt% yttrium, and the balance nickel, and a second nickel based braze alloy consisting of 14.75 wt% chromium, less than 0.05 wt % carbon, 3.63 wt % boron, less than 1.5 wt % iron and the balance nickel.
5. The process according to claim 1 , wherein said subjecting step comprises placing said component with said applied repair alloy composition into a furnace;
heating said component with said applied repair alloy composition to a temperature in the range of from 1950 to 2065° F. for a desired time period; cooling said component with said applied repair alloy composition to a temperature in the range of from 1950 to 2025° F. for a time period in the range of from 5 to 20 hours.
6. The process according to claim 5 , applying a vacuum of 5 ×10 −4 Torr or lower during said subjecting step.
7. The process according to claim 5 , further comprising cooling said repair component.
8. The process according to claim 7 , wherein said cooling step comprises cooling said repair component at a rate of 35° F./ minute.
9. The process according to claim 7 , wherein said cooling step comprises cooling said repair component at a rate faster than 35° F/minute.
10. The process according to claim 1 , wherein said component providing step comprises providing a component formed from a single crystal nickel based alloy having a composition consisting of from 5 to 10 wt % chromium, from 5 to 10 wt % cobalt, from 5 to 6.2 wt % aluminum, up to 1.9 wt % molybdenum, from 4 to 6 wt % tungsten, from 8 to 12 wt % tantalum, up to 0.35 wt % hafnium, up to 3.0 wt % rhenium, and the balance nickel.