Cooled constructional element for a gas turbine
View Patent ↗A cooled constructional element for a gas turbine includes a wall having a front and a rear side. The front side is configured to be thermally loaded during operation of the turbine, and the rear side has a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element. A device is configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement.
1. A cooled constructional element for a gas turbine comprising:
a wall including a front side and a rear side, the front side being configured to be thermally loaded during operation of the turbine and the rear side having a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the cooled constructional element than in the remaining regions of the cooled constructional element; and
an impingement cooling plate having a plurality of impingement cooling holes in a distributed arrangement and configured to create jets of a cooling medium that are directed onto the rear side of the wall in a region of the plurality of pins so as to cool the rear side of the wall by impingement, the impingement cooling plate being disposed essentially parallel at a distance to the rear side of the wall and the distributed arrangement of the plurality of cooling holes corresponding to the two-dimensional distribution of the plurality of pins such that, in a direction perpendicular to the impingement cooling plate, the plurality of cooling holes are respectively disposed between the plurality of pins.
2. The cooled constructional element as recited in claim 1 , wherein a density of the plurality of impingement cooling holes is locally the same as a density of the plurality of pins.
3. The cooled constructional element as recited in claim 1 , wherein the cooled constructional element is a stator blade including a blade airfoil extending in a longitudinal direction, wherein the wall is a base of a platform adjoining the blade airfoil and extending transversely to the longitudinal direction, and wherein the critical zone is an area of the rear side of the wall toward a concavity that is disposed at a transition between the blade airfoil and the platform.
4. A stator blade for a gas turbine comprising:
a blade airfoil extending in a longitudinal direction;
a platform adjoining the blade airfoil and extending transversely to the longitudinal direction, the platform including a base having a front side and a rear side, the front side being configured to be thermally loaded during operation of the turbine and the rear side having a plurality of pins projecting therefrom in a two-dimensional distribution, the two-dimensional distribution including a higher density distribution of pins in a critical zone of the stator blade than in the remaining regions of the stator blade; and
an impingement cooling plate configured to create jets of a cooling medium that are directed onto the rear side of the base in a region of the plurality of pins so as to cool the rear side of the base by impingement, the impingement cooling plate being disposed essentially parallel at a distance to the rear side of the base and the distributed arrangement of the plurality of cooling holes corresponding to the two-dimensional distribution of the plurality of pins such that, in a direction perpendicular to the impingement cooling plate, the plurality of cooling holes are respectively disposed between the plurality of pins.
5. The stator blade as recited in claim 4 , wherein a density of the plurality of impingement cooling holes is locally the same as a density of the plurality of pins.