Patent ID: 7044710

Claim:
A gas turbine arrangement, comprising: a rotor; a hot-gas passage, through which hot gases flow while the gas turbine is operating; at least one first row of turbine blades or vanes, which blades or vanes each have a platform and an airfoil with a suction side and a pressure side; at least one second row of turbine blades or vanes arranged upstream of the at least one first row of turbine blades or vanes in the direction of the hot-gas stream and in the axial direction of the rotor, each blade or vane of said at least one second row of turbine blades or vanes including a platform; at least one seal configured and arranged so that a cooling air leakage stream emerges therethrough while the gas turbine is operating, the at least one seal positioned between the first row of turbine blades or vanes and the second row of turbine blades or vanes in the region of the respective platforms; and means for guiding the leakage stream of cooling air along the surface of the platform to the pressure side of the first row of turbine blades or vanes.