초록 ▼

The present invention relates to a combustion chamber tile of a gas turbine, where the combustion chamber tile has a plurality of effusion cooling holes and a mixing air hole provided as a flow-guiding element (chute) and projecting over the surface of the combustion chamber tile, characterized in t

The present invention relates to a combustion chamber tile of a gas turbine, where the combustion chamber tile has a plurality of effusion cooling holes and a mixing air hole provided as a flow-guiding element (chute) and projecting over the surface of the combustion chamber tile, characterized in that on the side of the mixing air hole facing away from a flow along the combustion chamber tile at least one supporting element is arranged on the combustion chamber tile and on the mixing air hole. It also relates to a method for its manufacture.

대표청구항 ▼

1. A combustion chamber of a gas turbine, comprising: a combustion chamber wall defining an interior of the combustion chamber,a tile body attached to the combustion chamber wall in the interior of the combustion chamber downstream from a head of the combustion chamber, the tile body including an in

1. A combustion chamber of a gas turbine, comprising: a combustion chamber wall defining an interior of the combustion chamber,a tile body attached to the combustion chamber wall in the interior of the combustion chamber downstream from a head of the combustion chamber, the tile body including an inner surface facing toward the interior of the combustion chamber and forming at least a portion of an interior surface of the combustion chamber wall,a plurality of effusion cooling holes provided in the tile body,a flow-guiding element provided on the tile body and projecting inwardly from the inner surface of the tile body into the interior of the combustion chamber to be positioned within a main flow through the interior of the combustion chamber along the tile body, the flow-guiding element including a mixing air hole extending through the tile body,a supporting element connecting between the tile body and the flow-guiding element, the supporting element including at least a portion that extends into the interior of the combustion chamber inwardly beyond the inner surface to be positioned within the main flow only on a side of the flow guiding element facing away from a main direction of the main flow. 2. The combustion chamber in accordance with claim 1, wherein the supporting element is a bracket structure extending from the tile body. 3. The combustion chamber in accordance with claim 1, wherein the supporting element includes an effusion cooling hole. 4. The combustion chamber in accordance with claim 1, wherein the supporting element has a maximum width in a direction transverse to the main direction of the main flow which is less than or equal to an outer diameter of the flow-guiding element positioned within the main flow. 5. The combustion chamber in accordance with claim 1, wherein the supporting element is positioned entirely within an imaginary boundary channel extending downstream of the flow-guiding element in the main direction of the main flow, a cross-section of the imaginary boundary channel transverse to the main direction of the main flow being established by an external cross-section of the flow-guiding element transverse to the main direction of the main flow. 6. A method for manufacturing a combustion chamber of a gas turbine comprising: providing a combustion chamber wall defining an interior of the combustion chamber,manufacturing a tile body attached to the combustion chamber wall in the interior of the combustion chamber downstream from a head of the combustion chamber, the tile body including an inner surface facing toward the interior of the combustion chamber and forming at least a portion of an interior surface of the combustion chamber wall,providing a plurality of effusion cooling holes in the tile body,providing a flow-guiding element on the tile body and projecting inwardly from the inner surface of the tile body into the interior of the combustion chamber to be positioned within a main flow through the interior of the combustion chamber along the tile body, the flow-guiding element including a mixing air hole extending through the tile body,manufacturing a supporting element connecting between the tile body and the flow-guiding element, the supporting element including at least a portion that extends into the interior of the combustion chamber inwardly beyond the inner surface to be positioned within the main flow only on a side of the flow guiding element facing away from a main direction of the main flow,manufacturing the tile body in a vertical direction,manufacturing the supporting element vertically below a position of the flow-guiding element,making the effusion cooling holes simultaneously or subsequently in at least one chosen from the combustion chamber tile and the supporting element. 7. The method in accordance with claim 6, and further comprising machining the mixing air hole by a calibrating drilling operation. 8. The method in accordance with claim 6, and further comprising providing the supporting element and the mixing air hole are at a same time. 9. The method in accordance with claim 6, and further comprising providing the supporting element prior to providing the mixing air hole. 10. The method in accordance with claim 6, and further comprising manufacturing the combustion chamber tile by an additive manufacturing method. 11. The method in accordance with claim 6, and further comprising removing the supporting element after completion of the mixing air hole. 12. The method in accordance with claim 6, and further comprising providing that the supporting element is positioned entirely within an imaginary boundary channel extending downstream of the flow-guiding element in the main direction of the main flow, a cross-section of the imaginary boundary channel transverse to the main direction of the main flow being established by an external cross-section of the flow-guiding element transverse to the main direction of the main flow. 13. A combustion chamber of a gas turbine, comprising: a combustion chamber wall defining an interior of the combustion chamber,a tile body attached to the combustion chamber wall in the interior of the combustion chamber downstream from a head of the combustion chamber, the tile body including an inner surface facing toward the interior of the combustion chamber and forming at least a portion of an interior surface of the combustion chamber wall,a plurality of effusion cooling holes provided in the tile body,a flow-guiding element provided on the tile body and projecting inwardly from the inner surface of the tile body into the interior of the combustion chamber to be positioned within a main flow through the interior of the combustion chamber along the tile body, the flow-guiding element including a mixing air hole extending through the tile body,a supporting element connecting between the tile body and the flow-guiding element, the supporting element including at least a portion that extends into the interior of the combustion chamber inwardly beyond the inner surface to be positioned within the main flow on a side of the flow guiding element facing away from a main direction of the main flow,wherein the supporting element has a maximum width in a direction transverse to the main direction of the main flow that is less than or equal to an outer diameter of the flow-guiding element positioned within the main flow.