Abstract: A gas turbine with a shroud and labyrinth-type sealing arrangement has a casing 1 and at least one rotor 9, whose blades 2 are provided with a shroud 3. The labyrinth seal 4 is provided between the shroud 3 and the casing 1 and the shroud 3 includes at least two radially spaced and axially protruding annular fins 5, which are part of the labyrinth seal 4 At least one sealing fin 6 is provided on the casing 1 which extends essentially radially to the shroud 3 at least over a part of the circumference and at least partly in a space between the annular fins 5.

Abstract: On a platform cooling arrangement for the nozzle guide vane stator of a gas turbine arranged downstream of the combustion chamber, one or several parallel row(s) of cooling-air ejection ducts (10) are arranged continuously or in groups on the circumference. The cooling-air ejection ducts are angled relative to the axial direction at an angle (?) to produce a vortex structure on the surface of the platform (2) which, on the one hand, reduces mixing of the cooling air jets (11) with the hot gas flow (8) and, on the other hand, ensures complete cooling of the area of boundary layer separation (12) downstream of a boundary layer separation line (13) up to the suction side (14) of the adjacent nozzle guide vane (1).

Abstract: On a platform cooling arrangement for the nozzle guide vane stator of a gas turbine arranged downstream of the combustion chamber, one or several parallel row(s) of cooling-air ejection ducts (10) are arranged continuously or in groups on the circumference. The cooling-air ejection ducts are angled relative to the axial direction at an angle (?) to produce a vortex structure on the surface of the platform (2) which, on the one hand, reduces mixing of the cooling air jets (11) with the hot gas flow (8) and, on the other hand, ensures complete cooling of the area of boundary layer separation (12) downstream of a boundary layer separation line (13) up to the suction side (14) of the adjacent nozzle guide vane (1).