Patent ID: 9051841
Filing Date: 2015-06-09
Classification: F01D,F05D,Y02T

Abstract:
1. A cooled turbine blade for a gas-turbine engine, comprising: at least one cooling duct extending radially, relative to a rotary axis of the gas-turbine engine, inside an airfoil of the turbine blade, the at least one cooling duct extending into a root of the blade at least two nozzle-shaped air-supply ducts in an area of the blade root issuing into the at least one cooling duct tangentially or with a tangential velocity component to generate a cooling air flow close to a wall of the at least one cooling duct, the cooling airflow being generated to have a circumferential velocity to move radially through the at least one cooling duct in a helical manner; the at least two nozzle-shaped air-supply ducts tangentially issuing into the at least one cooling duct in opposite directions and offset from one another by a diameter of the at least one cooling duct.