Patent ID: 8545169
Filing Date: 2013-10-01
Classification: F01D,F05D

Abstract:
1. A turbine blade for a gas turbine, comprising: a blade root; a platform region having a transversely extending platform arranged on the blade root; a platform surface arranged on the transversely extending platform and is operatively impinged by a hot gas; a curved blade airfoil arranged upon the platform surface and which extends through an airfoil height to a blade tip, further having a leading and a trailing edge; and a cavity contained within the blade that is open on the root side and operatively exposed to a through-flow of a cooling air wherein the cooling air has a flow direction from the root side to the blade tip in the radial direction, the cavity extending through the blade root and the platform region into the blade airfoil, and which is divided into a first sub-cavity arranged adjacent to the leading edge, and a second sub-cavity arranged adjacent to the first sub-cavity, wherein the first and second sub-cavities are partially enclosed by inner walls having structural elements arranged on the face of the inner walls which influence the cooling air, wherein wherein the first and second section include a same height of at least 5% of the airfoil height calculated from the platforrn surface, and wherein in the second sub-cavity, the distance between the platform surface and the adjacent structural element which is closest to it, as seen in the radial direction, is greater than a mean minimum spacing between two directly adjacent structural elements that are provided within the blade airfoil.