Cooling of a gas turbine component designed as a rotor disk or turbine blade

摘要

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.

主权项

1. A gas turbine component, comprising:
a passage, opening onto an unstructured surface, for conducting a cooling medium; and a 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, and wherein 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.