초록 ▼

A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-

A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening.

대표청구항 ▼

1. A gas turbine component, comprising: a passage, opening onto an unstructured surface, for conducting a cooling medium; anda groove-like recess,wherein in the surface, close to the mouth of the passage, provision is made for the groove-like recess which is separated from the mouth by means of a di

1. A gas turbine component, comprising: a passage, opening onto an unstructured surface, for conducting a cooling medium; anda groove-like recess,wherein in the surface, close to the mouth of the passage, provision is made for the groove-like recess which is separated from the mouth by means of a dividing wall and which with regard to a stress concentration which is induced as a result of the passage effectively reduces this compared with the stress concentration without a groove-like recess, andwherein the dividing wall has a minimum wall thickness and the passage has a mouth diameter, and a ratio of minimum wall thickness to diameter lies within the range of between 0.05 and 3. 2. The component as claimed in claim 1, wherein the range is between 0.05 and 2. 3. The component as claimed in claim 1, wherein the gas turbine component is designed as a rotor disk for a gas turbine, including a plurality of retaining grooves, distributed along the periphery, to accommodate a rotor blade,wherein the walls of the retaining grooves each include the surface, andwherein the groove-like recess is arranged in each case close to a passage which opens onto the respective surface. 4. The component as claimed in claim 3, wherein the passage is formed as a bore. 5. The component as claimed in claim 3, wherein provision is made for two groove-like recesses which, in a cross-sectional view taken perpendicularly to the rotational axis of the rotor disk, are arranged on both sides of the mouth. 6. The component as claimed in claim 3, wherein the groove-like recess is formed as an endless groove which encompasses the mouth of the passage concerned. 7. The component as claimed in claim 6, wherein the endless groove is arranged in a circular manner and concentrically to the mouth of the passage concerned. 8. The component as claimed in claim 3, wherein each passage opens onto a groove base of the retaining groove concerned. 9. The component as claimed in claim 1, wherein the gas turbine component is designed as a turbine blade including a plurality of passages which open onto a surface around which hot gas can flow, of which the passage includes the groove-like recess, for reducing the stress concentration, close to its mouth in the surface. 10. The component as claimed in claim 9, wherein the recess is formed as an endless groove which encompasses the mouth of the passage concerned. 11. The component as claimed in claim 10, wherein the endless groove is arranged in a circular manner and concentrically to the mouth of the passage concerned.