Method of reconditioning a turbine blade
View Patent ↗A method of reconditioning a rotating blade ( 1 ) with a shroud ( 8 ) following the operation in a gas turbine, includes the application of a barrier ( 14 ) placed on the edge of the shroud ( 8 ) facing the edge of a shroud ( 8 ) of an adjacent blade having creep deformation. The barrier ( 14 ) prevents hot gas ingestion into a shroud cavity ( 10 ). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud ( 8 ) is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating ( 15 ) is additionally applied to the surfaces of the shroud ( 8 ) that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade ( 1 ).
1. A method of reconditioning a rotating turbine blade in a blade row following operation in a gas turbine, the turbine blade including
a blade shroud for sealing between the tip of the blade and a stationary component positioned radially opposite of the tip of the blade,
the shroud having a shroud platform, front and back knife-edges extending along the edges of the shroud platform in the circumferential direction and in the radial direction away from the shroud platform with respect to the turbine, the shroud platform, the knife-edges, and the stationary component defining a shroud cavity,
the shroud having two ends each facing a shroud of an adjacent blade in the blade row, and the shroud element including a first region having a creep deformation following operation of the blade and a second region having no deformation following the operation of the blade,
the method comprising:
applying a barrier to the edge of the second region of the shroud having no deformation where the barrier extends from the front knife-edge to the back knife-edge of the shroud and faces the shroud of the adjacent blade; and
reducing the mass of the shroud by a mass equal to or greater than the mass of the applied barrier.
2. The method according to claim 1 , further comprising:
applying a thermal barrier coating to surfaces of the shroud that are directly exposed to the hot gas of the turbine; and
wherein reducing comprises reducing the mass of the shroud by a mass equal to or greater than the mass of the barrier together with the mass of thermal barrier coating.
3. The method according to claim 1 , further comprising:
inserting a pre-fabricated barrier between the front and back knife-edges and along the edge of the second region of the shroud.
4. The method according to claim 1 , wherein applying comprises applying a barrier by layer-by-layer building-up of material.
5. The method according to claim 4 , wherein applying comprises applying the barrier by layer-by-layer welding, laser cladding, high strength diffusion brazing, or spraying.
6. The method according to claim 1 , wherein the barrier is pre-fabricated or shaped by layer-by-layer build-up of a nickel-based or cobalt-based super-alloy.
7. The method according to claim 1 , further comprising:
calculating the creep deformation of the first region of the shroud that is expected during the next operation interval of the turbine blade; and
determining the height of the barrier so that said barrier height will at least match the height of the expected creep deformation.
8. The method according to claim 1 , wherein reducing comprises reducing the mass of the shroud by reducing the thickness of the front knife-edge at least in the first region.
9. The method according to claim 1 , wherein reducing comprises reducing the mass of the shroud by reducing the thickness of the shroud platform.
10. The method according to claim 1 , wherein reducing comprises reducing the mass of the shroud element by CNC-high speed cutting, automated or manual grinding, or electro-discharge machining.
11. A method of fabricating a rotating turbine blade in a blade row intended for first operation in a gas turbine, the turbine blade including
a blade shroud for sealing between the tip of the blade and a stationary component positioned radially opposite of the tip of the blade having a shroud platform, front and back knife-edges extending along the edges of the shroud platform in the circumferential direction and in the radial direction away from the shroud platform with respect to the turbine, the shroud platform, the knife-edges, and the stationary component defining a shroud cavity,
the shroud having two ends each facing a shroud of an adjacent blade in the blade row, and the shroud including a first region oriented toward the shroud of an adjacent blade in the direction opposite the direction of the rotation of the blade row and a second region oriented toward the shroud of an adjacent blade in the direction of rotation of the blade row,
the method comprising:
applying a barrier to the edge of the second region of the shroud where the barrier extends from the front knife-edge to the back knife-edge of the shroud and faces the shroud of the adjacent blade; and
reducing the mass of the shroud by a mass equal to or greater than the mass of the applied barrier.
12. The method according to claim 11 , further comprising:
applying a thermal barrier coating to surfaces of the shroud that are directly exposed to the hot gas of the turbine; and
wherein reducing comprises reducing the mass of the shroud by a mass equal to or greater than the mass of the barrier together with the mass of thermal barrier coating.
13. The method according to claim 11 , further comprising:
inserting a pre-fabricated barrier between the front and back knife-edges and along the edge of the second region of the shroud.
14. The method according to claim 11 , wherein applying comprises applying a barrier by layer-by-layer building-up of material.
15. The method according to claim 14 , wherein applying comprises applying the barrier by layer-by-layer welding, laser cladding, high strength diffusion brazing, or spraying.
16. The method according to claim 11 , wherein the barrier is pre-fabricated or shaped by layer-by-layer build-up of a nickel-based or cobalt-based super-alloy.
17. The method according to claim 11 , further comprising:
calculating the creep deformation of the first region of the shroud that is expected during the next operation interval of the turbine blade; and
determining the height of the barrier so that said barrier height will at least match the height of the expected creep deformation.
18. The method according to claim 11 , wherein reducing comprises reducing the mass of the shroud by reducing the thickness of the front knife-edge at least in the first region.
19. The method according to claim 11 , wherein reducing comprises reducing the mass of the shroud by reducing the thickness of the shroud platform.
20. The method according to claim 11 , wherein reducing comprises reducing the mass of the shroud element by CNC-high speed cutting, automated or manual grinding, or electro-discharge machining.