Gas turbine thermal shroud with improved durability
View Patent ↗Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.
1. Shroud device for thermally protecting a gas turbine blade, the shroud device comprising:
a ceramic layer; and
a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer configured to engage with a plurality of cavities located in the ceramic layer, such that a gap will exist between the cavities and the protrusions at a predetermined ambient temperature, the gap disappearing at a higher temperature operation of the gas turbine, the protrusions being then locked into the cavities,
wherein the fixation device is configured such that the protrusions of the metallic layer, that are located in the cavities in the ceramic layer, are perpendicular to each other along the rotational axis of the turbine.
2. Shroud device according to claim 1 , wherein the fixation device is configured to allow the ceramic layer to follow a directional movement in a direction of insertion and retrieval of the ceramic layer into/out of the metallic layer, the shroud device comprising:
a blocking device defining an installed position of the ceramic layer and restraining movement of the ceramic layer along the directional movement, this directional movement being parallel to a shear movement applied by a gas turbine blade when rotating.
3. Shroud device according to claim 1 , wherein the ceramic layer comprises:
ceramic foam.
4. Shroud device according to claim 1 , wherein the ceramic layer comprises:
alumina.
5. Shroud device according to claim 1 , wherein the ceramic layer comprises:
zirconia stabilized with yttria, calcia, magnesia or any combination thereof.
6. Shroud device according to claim 1 , wherein a porosity of material in the ceramic layer ranges between 20% and 80%.
7. Shroud device according to claim 1 , wherein the porosity of the material in the ceramic layer ranges between 30% and 50%.
8. Shroud device according to claim 1 , wherein a porosity grade in the ceramic layer is obtained with a fugitive material, by introducing fugitive pore formers or by direct foaming of slurry.
9. Shroud device according to claim 1 , wherein the ceramic layer is covered by an extra ceramic layer made of a material with a porosity of less than 30%.
10. Gas turbine comprising:
at least one gas turbine blade; and
a shroud device according to claim 1 .
11. Shroud device according to claim 2 , wherein the ceramic layer comprises:
ceramic foam.
12. Shroud device according to claim 2 , wherein the ceramic layer comprises:
alumina.
13. Shroud device according to claim 2 , wherein the porosity of the material in the ceramic layer ranges between 30% and 50%.
14. Shroud device according to claim 13 , wherein a porosity grade in the ceramic layer is obtained with a fugitive material, by introducing fugitive pore formers or by direct foaming of slurry.
15. Shroud device according to claim 14 , wherein the ceramic layer is covered by an extra ceramic layer made of a material with a porosity of less than 30%.
16. Shroud device for thermally protecting a gas turbine blade, the shroud device comprising:
a ceramic layer; and
a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer configured to engage with a plurality of cavities located in the ceramic layer, such that a gap will exist between the cavities and the protrusions at a predetermined ambient temperature, the gap disappearing at a higher temperature operation of the gas turbine, the protrusions being then locked into the cavities,
wherein the protrusions extending from the metallic layer form an angle of 45° with respect to the metallic layer and the ceramic layer.
17. Shroud device according to claim 16 , wherein the fixation device is configured such that the protrusions in the metallic layer, matching with the cavities in the ceramic layer, are parallel to each other.