Process for restoring a turbine blade
The restoring process machines out a crack in the platform of a turbine blade to form a pocket that then receives a plug of compatible material. The plug is brazed in place and the blade is the machined and cleaned to present a clean fresh surface where the plug is inserted. The plug has a lower coefficient of thermal expansion so that the plug area has less compressive stresses in the repaired area.
1. A process for restoring a turbine blade having a crack on a side of a platform thereof; said process comprising the steps of
forming a pocket of predetermined length in said platform to obliterate the crack therein;
inserting a plug having a length greater than said predetermined length into said pocket to completely fill said pocket while having a portion projecting therefrom;
brazing the plug into said pocket with a braze material; and
thereafter working said plug and said braze material to remove said portion of said plug projecting from said pocket to match the length of said plug to said predetermined length and to match the surfaces of the platform.
2. A process as set forth in claim 1 wherein said pocket and said plug have matching shapes.
3. A process as set forth in claim 2 wherein said plug has a first section with a rectangular portion and a semicircular portion extending therefrom and a second section with a rectangular portion and a semicircular portion extending therefrom, said second section being of smaller size than said first section and overlying said first section.
4. A process as set forth in claim 1 wherein said step of forming a pocket includes machining of said platform to remove material therefrom to form said pocket.
5. A process as set forth in claim 1 wherein said step of brazing includes an application of nickel braze to said pocket prior to inserting of said plug into said pocket.
6. A process as set forth in claim 1 wherein said plug is made of a material with a coefficient of thermal expansion compatible with said platform to preclude said plug from expanding outside said pocket.
7. A process as set forth in claim 6 wherein said plug is made of a Ni—Cr—W—Mo alloy.
8. A process for restoring a turbine blade having a crack on a side of a platform thereof; said process comprising the steps of
forming a rocket in said platform to obliterate the crack therein;
inserting a plug into said rocket to completely fill said pocket;
brazing the plug into said pocket with a braze material;
thereafter working said plug and said braze material to match the surfaces of the platform; and
grit cleaning the blade after said step of blending said plug and said braze material to match the surfaces of the turbine blade.
9. A process for restoring a turbine blade having a crack on a concave side of a platform thereof; said process comprising the steps of
machining material from said platform from about said crack to form a pocket of predetermined length in said platform to obliterate the crack therein;
applying a nickel braze to said pocket;
thereafter inserting a plug having a length greater than said predetermined length into said pocket to fill said pocket while having a portion projecting therefrom;
applying a nickel braze to the surfaces of said plug and said turbine blade;
subjecting the turbine blade and plug to a vacuum brazing heat treatment to braze the plug into said pocket; and
thereafter working said plug and said braze material to remove said portion of said plug projecting from said pocket to match the length of said plug to said predetermined length and to match the surfaces of the turbine blade.
10. A process as set forth in claim 9 wherein a vane extends from the platform and said pocket has a cross-sectional shape for retaining said plug therein in a direction of said vane.
11. A process as set forth in claim 9 wherein said plug has a first section with a rectangular portion and a semicircular portion extending therefrom and a second section with a rectangular portion and a semicircular portion extending therefrom, said second section being of smaller size than said first section and overlying said first section.
12. A process as set forth in claim 9 further comprising the step of heating the turbine blade prior to said step of applying a nickel braze to said pocket to a degree sufficient to bake out oils and penetrant therein.
13. A process as set forth in claim 9 further comprising the step of tack welding said plug in said pocket prior to said step of vacuum brazing heat treatment.
14. A process as set forth in claim 9 further comprising the step of inserting a pin between said plug and said pocket.
15. A process as set forth in claim 9 further comprising the step of grit cleaning the blade after said step of working said plug and said braze material to match the surfaces of the turbine blade.
16. A process as set forth in claim 9 further comprising the step of subjecting the turbine blade to an X-ray and Zyglo inspection to ensure blade penetration.
17. A process as set forth in claim 9 wherein said plug is made of one of a nickel alloy and a nickel cobalt alloy.
18. A plug for repairing a turbine blade, said plug having a first section with a rectangular portion and a semicircular portion extending therefrom and a second section with a rectangular portion and a semicircular portion extending therefrom, said second section being of smaller size than said first section and overlying said first section to define a T-shaped cross-section.
19. A plug as set forth in claim 18 made of Ni—Cr—W—Mo alloy.