Patent ID: 7520719

Claim:
A method for the cooling of outer shrouds of rotor blades of a gas turbine which are subject to a hot-gas flow downstream of stator blades of the gas turbine and which are passively cooled with cooling air supplied by a compressor via a turbine casing, comprising: introducing a multitude of cooling-air flows distributed equally on a circumference of a respective turbine stage downstream of the stator blades directly into the hot-gas flow in a defined direction, wherein the cooling-air flows, in dependence of applicable aerodynamic and geometrical conditions, are positioned and angularly orientated such that the cooling air primarily and essentially hits substantially all of a bottom surface of the outer shrouds of the rotor blades; wherein a blow-out rate, as a quotient of a product of density and velocity of both the cooling air and the hot gas, is approximately 1.5.