Assembly, treated article, and process of treating a turbine component

1. A process of treating a turbine component after service, the turbine component comprising an article and a wear component brazed to the article, the process comprising:

applying a braze tape on at least a portion of the wear component, wherein the wear component is a pre-sintered preform; and

thermal processing the turbine component while the braze tape is on the at least a portion of the wear component to treat the turbine component;

wherein the article is a shrouded blade and the pre-sintered preform is located on a z-notch of the shrouded blade.

2. The process of claim 1 , wherein the thermal processing comprises thermally cycling the turbine component and hot isostatic pressing the turbine component.

3. The process of claim 2 , wherein the braze tape reduces or eliminates re-flow of the pre-sintered preform during the thermal cycling and during the hot isostatic pressing.

4. The process of claim 2 , wherein the thermally cycling comprises heating the turbine component to about 510° C. to about 570° C. for about 20 minutes to about 40 minutes, followed by heating to about 1040° C. to about 1090° C. for about 10 minutes to about 20 minutes, followed by heating to about 1150° C. to about 1260° C. for about three hours to about five hours, followed by removing the turbine component from the heat and allowing the turbine component to cool.

5. The process of claim 4 , wherein the braze tape reduces or eliminates re-flow of the pre-sintered preform during the thermal processing.

6. The process of claim 2 , wherein the hot isostatic pressing comprises treating the turbine component at a temperature between 1150° C. and 1260° C. and a pressure between 68.95 MPa and 137.9 MPa for 3-5 hours.

7. The process of claim 1 , wherein the pre-sintered preform is a hardface chiclet.

8. The process of claim 7 further comprising returning the turbine component to service without removing or replacing the hardface chiclet.

9. The process of claim 1 , wherein the braze tape reduces or eliminates re-flow of the pre-sintered preform during the thermal processing.

10. The process of claim 1 , wherein the article is a shroud of a stage-2 shrouded blade.

11. The process of claim 1 , wherein the pre-sintered preform comprises, by weight:

80% of a first alloy consisting essentially of a first composition, by weight, of about 16.5 to about 18.5% chromium (Cr), up to about 1.5% nickel (Ni), about 27 to about 30% molybdenum (Mo), about 3.0 to about 3.8% silicon (Si), up to about 0.08% carbon (C), and a balance of cobalt (Co) and incidental impurities, and

20% of a second alloy consisting essentially of a second composition, by weight, of about 22.5 to about 24.25% Cr, about 9.0 to about 11.0% Ni, about 6.5 to about 7.5% tungsten (W), about 3.0 to about 4.0% tantalum (Ta), about 2.0 to about 3.0% boron (B), about 0.15 to about 0.30% titanium (Ti), about 0.30 to about 0.60% zirconium (Zr), about 0.55 to about 0.65% C, and a balance of Co and incidental impurities.

12. The process of claim 1 , wherein the braze tape comprises an alloy composition of about 90% by weight of a first alloy including a first composition, by weight, of about 16.5 to about 18.5% chromium (Cr), up to about 1.5% nickel (Ni), about 27 to about 30% molybdenum (Mo), about 3.0 to about 3.8% silicon (Si), up to about 0.08% carbon (C), and a balance of cobalt (Co) and incidental impurities; and about 10% by weight of a second alloy including a second composition, by weight, of about 22.5 to about 24.25% Cr, about 9.0 to about 11.0% Ni, about 6.5 to about 7.5% tungsten (W), about 3.0 to about 4.0% tantalum (Ta), about 2.0 to about 3.0% boron (B), about 0.15 to about 0.30% titanium (Ti), about 0.30 to about 0.60% zirconium (Zr), about 0.55 to about 0.65% C, and a balance of Co and incidental impurities.

13. The process of claim 1 , wherein the braze tape comprises an alloy composition of about 95% by weight of a first alloy including a first composition, by weight, of about 16.5 to about 18.5% chromium (Cr), up to about 1.5% nickel (Ni), about 27 to about 30% molybdenum (Mo), about 3.0 to about 3.8% silicon (Si), up to about 0.08% carbon (C), and a balance of cobalt (Co) and incidental impurities; and about 5% by weight of a second alloy including a second composition, by weight, of about 22.5 to about 24.25% Cr, about 9.0 to about 11.0% Ni, about 6.5 to about 7.5% tungsten (W), about 3.0 to about 4.0% tantalum (Ta), about 2.0 to about 3.0% boron (B), about 0.15 to about 0.30% titanium (Ti), about 0.30 to about 0.60% zirconium (Zr), about 0.55 to about 0.65% C, and a balance of Co and incidental impurities.

14. An assembly comprising:

a turbine component comprising:

an article; and

a pre-sintered preform brazed to a surface of the article; and

a braze tape on at least a portion of the pre-sintered preform;

wherein the article is a shrouded blade and the pre-sintered preform is located on a z-notch of the shrouded blade.

15. The assembly of claim 14 , wherein the article is a shroud of a stage-2 shrouded blade.

16. The assembly of claim 14 , wherein the pre-sintered preform comprises, by weight:

80% of a first alloy consisting essentially of a first composition, by weight, of about 16.5 to about 18.5% chromium (Cr), up to about 1.5% nickel (Ni), about 27 to about 30% molybdenum (Mo), about 3.0 to about 3.8% silicon (Si), up to about 0.08% carbon (C), and a balance of cobalt (Co) and incidental impurities, and

20% of a second alloy consisting essentially of a second composition, by weight, of about 22.5 to about 24.25% Cr, about 9.0 to about 11.0% Ni, about 6.5 to about 7.5% tungsten (W), about 3.0 to about 4.0% tantalum (Ta), about 2.0 to about 3.0% boron (B), about 0.15 to about 0.30% titanium (Ti), about 0.30 to about 0.60% zirconium (Zr), about 0.55 to about 0.65% C, and a balance of Co and incidental impurities.

17. The assembly of claim 14 , wherein the pre-sintered preform is a hardface chiclet.

18. A treated turbine component comprising:

a treated article; and

a pre-sintered preform brazed to a surface of the treated article;

wherein the treated turbine component has been thermally processed with the pre-sintered preform being substantially free of re-flow; and

wherein the treated article is a shrouded blade and the pre-sintered preform is located on a z-notch of the shrouded blade.

19. The treated turbine component of claim 18 , wherein the pre-sintered preform is a hardface chiclet.