Patent ID: 9163515
Filing Date: 2015-10-20
Classification: F01D,F05D

Abstract:
1. A gas turbine arrangement comprising: an annulus, which is axially delimited between a rotor unit, rotatable around a rotor axis, and at least one stationary component; a plurality of cooling medium outlet openings, from which a cooling medium flow can be discharged, lead into the annulus, from the at least one stationary component, the cooling medium flows proportionately into cooling medium inlet openings, provided in the rotor unit in a flow direction of the cooling medium flow, that propagates through the annulus, radially to the annulus, at least one inner cavity which is delimited by the rotor unit and by the at least one stationary component, the at least one inner cavity is pressurized with a purging gas, and is fluidically connected to the annulus, wherein the at least one stationary component and the rotor unit comprise a constriction by which the at least one inner cavity is separated from the radially outer annulus and via which the at least one inner cavity is fluidically connected to the radially outer annulus, and wherein flow guides, which are fastened on the at least one stationary component on one side and extend from the radially innermost portion of the at least one stationary component, project into the constriction and guide a purging gas flow, the flow guides have a profile of a design which extends in a curved manner in the axial direction, and the flow guides have throughflow sections which extend in a curved manner from an axial inlet to an axial outlet.