Patent ID: 8926285
Filing Date: 2015-01-06
Classification: F01D,F05D

Abstract:
1. A turbine blade fastening, comprising: a blade root; a blade airfoil; and a blade groove, wherein the blade root is arranged in the blade groove, wherein the blade root comprises at least two anchoring teeth which are designed for fitting into corresponding recesses in a rotor, wherein the blade root has a blade root tip formed at the end in relation to a rotational axis of the rotor, wherein the at least two anchoring teeth are arranged in series along an extent pointing towards the blade root tip, wherein the height of the anchoring teeth increases towards the blade root tip, wherein an anchoring tooth has a flank between an anchoring-tooth trough apex and an anchoring-tooth apex, wherein an outer notch radius is formed between the flank and the anchoring-tooth apex, wherein an inner notch radius is formed between the anchoring-tooth trough apex and the anchoring-tooth apex, wherein the outer notch radius is smaller than the inner notch radius, and wherein a load-bearing flank clearance is formed between the flank and a corresponding load-bearing flank in the blade groove, and wherein there is basically no load-bearing flank clearance on the anchoring tooth which is closest to the blade root tip, and the load-bearing flank clearances between a plurality of further flanks and corresponding load-bearing flanks increase towards the blade airfoil.