Abstract: In an arrangement for influencing the radial clearance of the blading of an axial-flow, highly loaded compressor which essentially comprises a rotor (1) equipped with moving blades (2) and a blade carrier (3) which is equipped with guide blades (4) and is hung in a casing (5), the blade carrier (3) has long and narrow mountings (7) for the guide blades (4), at least one hollow space (9) being arranged in the guide-blade roots (8), a hollow space (10) being present in each case in the embedded state in the peripheral direction between the guide-blade root (8), the two mountings (7) for a guide blade (4) and the blade carrier (3), a further hollow space (11) being present in each case in the peripheral direction between the blade carrier (3) and the mountings (7) for two successive guide blades (4), which hollow space (11) is defined by a plurality of segments (12) distributed over the periphery and connected to the guide-blade roots (8), and the hollow spaces (9, 10, 11) being filled with insulating material (

Abstract: An apparatus for cooling an axial-flow gas turbine of the type comprising a multi-stage turbine (1) which drives a compressor (10) arranged on a common shaft (13), involves means for removing leakage air from the space surrounding the portion of the shaft between the turbine and the compressor. In such an installation, the portion of the shaft between the turbine (1) and the compressor (10) is shaped as a drum (14) and is surrounded by a drum cover (15), which forms an annular duct (20). A labyrinth seal (21) sealing against the drum cover (15) is disposed in the annular duct (20), and the drum cover (15) together with the end face (18) of the turbine rotor (3) defines a radially directed wheel side space (19). Separate lines (22) for carrying the turbine-rotor cooling air from the compressor (10) to the end face (18) of the turbine rotor (3) are provided, and the connection between these lines (22) and the wheel side space (19) is made via at least one swirl nozzle (23).