Method for producing and restoring ceramic heat insulation coatings in gas turbines and associated gas turbine
Through the use of different ceramic heat insulation coatings ( 7, 13 ) on turbine blades, it is possible to produce or restore different configurations of gas turbines, which are then optimized for a respective baseload operation application or peak load operation application. Differences in the sprayed-on heat insulation coatings ( 7, 13 ) can be generated by means of a different material composition of the powder, for example zirconium oxide, by means of a different number of layers ( 10 ), by means of different coating thicknesses and/or by means of different porosities.
1. A process for operating a second gas turbine using first turbine blades or vanes of a first gas turbine comprising:
providing first turbine blades or vanes of the first gas turbine having either a single-layer first ceramic thermal barrier coating previously operated at peak load operations or a two-layer first ceramic thermal barrier coating previously operated at base load operations,
removing the first ceramic thermal barrier coating from the first turbine blades or vanes of the first gas turbine to produce uncoated first turbine blades or vanes;
applying a second ceramic thermal barrier coating to the uncoated first turbine blades or vanes to produce second turbine blades or vanes;
operating the second turbine blades or vanes at base load operations with a bottom layer having a porosity of 12% to 16% and a top layer having a porosity of 18%±4%, or the bottom layer having a porosity of 18%±4% and the top layer having a porosity of 25%±4%, when the removed first ceramic thermal barrier coating was the single-layer ceramic barrier coating configured for peak load operations,
wherein, when applied, at least the top layer is comprised of partially stabilized zirconium oxide,
operating the second turbine blades or vanes at peak load operations with a uniform porosity of 18%±4% when the removed first ceramic thermal barrier coating was a two-layer first ceramic thermal barrier coating configured for base load operations.
2. The process as claimed in claim 1 , wherein the absolute difference in the porosity of the bottom and the top layers is at least 2%, when the two-layer second ceramic thermal barrier coating is applied,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.
3. The process as claimed in claim 1 , wherein, when applied, the bottom layer of the applied two-layer second ceramic thermal barrier coating is thinner than the top layer thereof; and
the bottom layer of the applied two-layer second ceramic thermal barrier coating has a thickness of 75 μm to 150 μm,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.
4. The process as claimed in claim 1 , wherein the bottom layer is comprised of partially stabilized zirconium oxide.
5. The process as claimed in claim 1 , wherein the zirconium oxide is sprayed with a powder having a monoclinic proportion of less than 3%.
6. The process as claimed in claim 4 , wherein a tetragonal proportion has the greatest proportion of zirconium oxide.
7. The process as claimed in claim 5 , further comprising applying a heat treatment to reduce the monoclinic proportion of the zirconium oxide powder to be sprayed by at least 50%.
8. The process as claimed in claim 1 , wherein, when applied, the applied two-layer second ceramic thermal barrier coating is applied by spraying a bottom layer without a polymer and spraying a top layer with a polymer,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.
9. The process as claimed in claim 1 , wherein, when applied, the top layer of the applied two-layer second ceramic thermal barrier coating has pores with a mean pore diameter and the bottom ceramic layer has pores with a mean pore diameter, and the mean pore diameter of the top layer is greater than the mean pore diameter of the bottom layer.
10. The process as claimed in claim 1 , wherein, when applied, a same powder with a same composition and a same grain size distribution is used in applying the two-layer second ceramic thermal barrier coating,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.
11. The process as claimed in claim 1 , wherein, when applied, the bottom ceramic layer and the top ceramic layer of the applied two-layer second ceramic thermal barrier coating are comprised of different materials,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.
12. The process as claimed in claim 2 , wherein the absolute difference in the porosity of the top and the bottom layers is at most 4%,
wherein the first turbine blades or vanes have a single layer first ceramic thermal barrier coating.