Method of repairing a crack in a turbine component
A method of repairing a crack in a component comprising a base material, in particular in a gas turbine blade, a suspension, which comprises a carrier liquid and at least one solid in the form of nanoparticles of the same material as the base material, being applied to the location to be repaired. A heat treatment of the component is carried out, the solid in the form of nanoparticles being melted and a bond with the base material being formed. During the heat treatment, the component is exposed to a thermal shock, in which a maximum temperature which corresponds to the melting temperature of the nanoparticles is reached. The nano size of the particles in the suspension causes a lowering of the melting point of these particles to take place, so that the structure of the base material does not change even at the melting temperature of the nanoparticles.
1. A method of repairing a crack in a gas turbine component having a base material characterized by an annealing temperature, comprising:
forming a suspension comprising a carrier liquid and nanoparticles which are not soluble in the carrier liquid;
applying the suspension to penetrate into the crack to be repaired;
heating the suspension at a first temperature to evaporate carrier liquid with the nanoparticles being compacted; and
further heating the component to a more elevated temperature below the annealing temperature, wherein the elevated temperature is approximately 50 K above the first temperature and below the melting temperature of the base material, to melt the nanoparticles and form a bond between the nanoparticles and the base material, the further heating at the more elevated temperature having a duration of less than 30 minutes.
2. The method as claimed in claim 1 , wherein the nanoparticles are the same material as the base material.
3. The method as claimed in claim 2 , wherein the nanoparticles have a size of 100 nm or less.
4. The method as claimed in claim 3 , wherein the carrier liquid is an organic solution.
5. The method as claimed in claim 4 , wherein a volume fraction of the nanoparticles in the suspension is greater than 50%.
6. The method as claimed in claim 5 , wherein the suspension includes a wetting agent.
7. The method as claimed in claim 6 , wherein a mass fraction of wetting agent in the suspension is between 0.1 and 1 g/l.
8. The method as claimed in claim 7 , wherein the mass fraction of wetting agent in the suspension is between 0.2 and 0.6 g/l.
9. The method as claimed in claim 1 , wherein the more elevated temperature is between 50 K and 100 K below the melting temperature of the base material.
10. The method as claimed in claim 9 , wherein the more elevated temperature is up to 100 K above the first temperature.
11. The method as claimed in claim 10 , wherein the more elevated temperature is between 30 K and 70 K above the first temperature.
12. The method as claimed in claim 1 , wherein the further heating at the more elevated temperature has a duration between 5 minutes and 10 minutes and the more elevated temperature is 60 K below the melting temperature of the base material.
13. The method as claimed in claim 1 , wherein the gas turbine component is a blade, vane or combustion system component.