Patent ID: 9341078
Filing Date: 2016-05-17
CPC Classification: F01D,F05D

Claim Text:
1. Blade for a turbomachine, comprising: an airfoil and a root portion, both being unitary to said blade; said airfoil having a cooler arranged inside the airfoil; said a root portion having two narrow sides and two broad sides; a cooling air supply passage in the root portion that guides cooling air into the cooler; and a cooling air bleed arranged in the root portion and in fluid connection with the cooling air supply passage; wherein the cooling air bleed comprises a nozzle on one of the narrow sides of the root portion, and wherein the nozzle is formed by a hole, wherein the blade root portion comprises an upper blade platform and a lower blade platform, wherein the upper blade platform and the lower blade platform are embodied as parts of a labyrinth-sealing when assembled in the turbomachine, and wherein the nozzle is arranged between the upper blade platform and the lower blade platform, and wherein an axial direction of the hole is inclined upward between 92° and 135° with respect to a longitudinal direction of the blade.