Enhanced cooling arrangement for a turbomachine component

摘要

The invention addresses the issue of local over temperature of a turbomachine blade due to loss of protective thermal barrier coating (TBC). In predefined areas of the blade's (1) outer wall (21) recesses (73) are placed. The outer wall's thickness at the locations (72, d2) of the recesses is less than in regions (71, d1) surrounding the recess. In case of an over temperature due to a TBC loss, the thinner walls (d2) of the recess at the location of the TBC loss will melt away faster than the material of the thicker walls (d1) surrounding the recess. This will open up a hole (74) in the outer wall such that cooling fluid from the underlying core passage way can exit the blade, resulting in a film cooling effect. This cooling will protect the blade at least temporarily and guarantee a proper functioning until the next inspection.