GAS TURBINE SYSTEM

摘要

The invention relates to a gas turbine system which comprises a rotor, a hot gas channel through which a hot gas flow (12) flows during operation of the gas turbine, at least one row of turbine blades (1), comprising a vane (3) with a suction and a pressure side (11, 10) and a platform (4), and at least one second row of turbine blades (2) which in the axial direction of the rotor and in the direction of the hot gases (12) are disposed in front of the first row of turbine blades (1) and likewise comprise a platform (4). Between the first row of turbine blades (1) and the second row of turbine blades (2), in the area of the respective platforms (4), there is at least one seal (5, 6) through which a cooling air leakage flow (7) emerges during operation of the gas turbine. Means (8, 9) are provided which guide the leakage flow (7) of the cooling air along the surface of the platform (4) to the pressure side (10) of the first row of turbine blades (1).