Gas turbine of the axial flow type

The invention relates to a gas turbine (35) of the axial flow type, comprising a rotor with alternating rows of air-cooled blades (40) and rotor heat shields, and a stator with alternating rows of air-cooled vanes (41) and stator heat shields (47) mounted on inner rings (46), whereby the stator coaxially surrounds the rotor to define a hot gas path (42) in between, such that the rows of blades (40) and stator heat shields (47), and the rows of vanes (41) and rotor heat shields are opposite to each other, respectively, and a row of vanes (41) and the next row of blades (40) in the downstream direction define a turbine stage (TS), and whereby the blades (40) of the turbine stage (TS) are each provided with a blade crown (32) at their tips and the vanes (41) of the turbine stage (TS) are each provided with an outer vane platform (38). A reduction in cooling air mass flow and an improved cooling and effective thermal protection of critical parts within the turbine stages of the turbine is achieved by adapting the stator heat shields (47) and outer vane platforms (38) within the turbine stage (TS) to one another such that air (37) leaking through the joints between the outer vane platforms (38) and the adjacent stator heat shields (47) into the hot gas path (42) is directed onto the blade crown (32) of the blades (40).