Method and apparatus for improving turbine blade sealing in a gas turbine engine
A system and method for improving sealing at a turbine blade tip shroud, while reducing weight associated with the improved sealing is disclosed. The gas turbine blade incorporates a tip shroud having one or more pockets located therein, where the one or more pockets remove weight from the shroud, thus reducing load on the blade attachment generated by additional sealing at the turbine blade shroud. Methods for incorporating the one or more tip shrouds in a new turbine blade or a repaired turbine blade are also disclosed.
1. A method for repairing a pre-casted turbine blade and improving sealing of a blade tip region comprising:
providing the pre-casted turbine blade having an airfoil, a tip shroud, and a knife edge extending radially outward from the tip shroud;
adding material to an outer surface of the tip shroud to form an additional knife edge; and,
placing a pocket in at least a portion of the tip shroud;
wherein:
a weight of the pre-casted turbine blade is reduced after forming the additional knife edge and placing the pocket in the tip shroud; and
a curvature and a shape of the pocket adheres to a curvature and a shape of each of the tip shroud and the airfoil.
2. The method of claim 1 , wherein the pocket is placed in the tip shroud by an EDM process.
3. The method of claim 1 , wherein the pocket extends into a portion of the airfoil.
4. The method of claim 1 , wherein the pocket surrounds one or more cooling holes extending into the tip shroud.
5. The method of claim 4 , wherein the pocket distributes cooling flow from the one or more cooling holes to the tip shroud.
6. The method of claim 1 , wherein the second knife edge is added by brazing a strip of material to the outer surface of the tip shroud.
7. The method of claim 1 , wherein the second knife edge is added by an additive manufacturing process.
8. A method of retrofitting a pre-cast turbine blade to reduce airflow passing around a tip of the turbine blade comprising:
providing the pre-cast turbine blade having an airfoil, a tip shroud, and a knife edge extending radially outward from the tip shroud;
forming at least one additional knife edge extending radially outward from the tip shroud of the pre-cast turbine blade, the at least one additional knife edge added to the tip shroud in a first subsequent manufacturing process; and
forming at least one pocket in the tip shroud of the pre-cast turbine blade, the at least one pocket being formed in the tip shroud in a second subsequent manufacturing process;
wherein:
a weight of the pre-cast turbine blade is reduced after forming the at least one additional knife edge and forming the at least one pocket in the tip shroud; and
a curvature and a shape of the at least one pocket adheres to a curvature and a shape of the tip shroud.
9. The method of claim 8 , wherein the at least one additional knife edge is added to the tip shroud by an additive manufacturing process.
10. The method of claim 8 , wherein the at least one additional knife edge is added to the tip shroud by brazing material to an outer surface of the tip shroud.
11. A method of retrofitting a pre-cast turbine blade to reduce airflow passing around a tip of the turbine blade comprising:
providing the pre-cast turbine blade having an airfoil, a tip shroud, and a knife edge extending radially outward from the tip shroud;
forming at least one additional knife edge extending radially outward from the tip shroud of the pre-cast turbine blade, the at least one additional knife edge added to the tip shroud in a first subsequent manufacturing process; and
forming at least one pocket in the tip shroud of the pre-cast turbine blade, the at least one pocket being formed in the tip shroud in a second subsequent manufacturing process;
wherein, a curvature and a shape of the at least one pocket adheres to a curvature and a shape of the tip shroud.
12. The method of claim 11 , wherein the at least one pocket is between the knife edge and the at least one additional knife edge.
13. The method of claim 11 , wherein the at least one pocket distributes cooling flow from a cooling hole to the tip shroud.