Patent ID: 7467922

Claim:
A turbine blade or vane for a gas turbine, comprising: a blade or vane root that is successively adjoined by a platform region with a transversely extending platform and then a blade profile that is curved in the longitudinal direction; a platform surface that is provided at the platform and exposed to hot gas; and at least one cavity that is open on the root side, through which a coolant can flow and which extends through the blade or vane root and at least into the platform region and is surrounded by an inner wall, and having a contour that extends in the platform region and is set back with respect to a contour extending in the blade or vane root so as to form a recess that widens the cavity, wherein the recess that widens the cavity extends into the region below the platform surface to form an at least partially hollow platform and in that there is at least one means for diverting the coolant into the partial cavity, wherein at least one outlet opening, through which the coolant can flow out of the partial cavity, is provided in the partial cavity for guiding the coolant, wherein the outlet opening opens out into the platform surface or into an end side of the platform, and wherein a pin is located in the cavity and extends from the blade or vane root at least into the platform region, is provided as means for guiding the coolant.