Patent ID: 6638012
Filing Date: 2003-10-28
Classification: F01D

Abstract:
A platform arrangement of an axial-throughflow gas turbine comprises:alternately arranged rows of stationary guide vanes and rotating moving blades in an annular flow channel, the guide vanes being connected to the stator housing of the gas turbine via vane carriers, and these vane carriers having platforms determining the inner contour of the annular flow channel and exposed to a hot gas flow, and the moving blades being equipped with shroud elements which on their top side have sealing ribs oriented in the direction of movement of the blade and running against sealing strips on an inner wall of the flow channel, wherein the platforms are arranged so as to be spaced from the stator housing and form at least predominantly the inner contour of the flow channel, said platforms having prolonged platform portions on both sides and transitional regions between the platforms of adjacent guide vane rows are arranged within the cavity formed by the continuous sealing ribs of the shroud of the moving blade row located in each case between them; wherein each of the guide vane carriers is designed as a hollow profile, consisting of a platform forming the contour of the flow channel and of two essentially parallel side walls which are connected positively to the stator housing; wherein cooling air acts on the voids enclosed by the guide vane carriers and/or the void enclosed between the prolonged platform portions and the stator housing; and wherein a joint between adjacent platforms has overflow orifices for overflowing cooling air from the void into the cavity.