Abstract: In a single-shaft axial-flow gas turbine, the shaft part lying between turbine and compressor is a drum (12) which is surrounded by a drum cover (13). The annular passage (18) formed between drum and drum cover assumes the function of conducting all the rotor cooling air, tapped on the hub side behind the last moving row of the compressor, to the front end (16) of the turbine and after this to its rotor-side cooling passages. The cooling air is deflected inside the annular passage in a spin cascade (25) and accelerated to the highest possible tangential velocity. With this measure, the axial thrust of the gas turbine can be reduced on the one hand and the hitherto conventional recooler for the cooling air can be dispensed with on the other hand.

Abstract: An axial flow turbine, whose outlet rotor blades (12) are followed by a diffuser (13), has first means (8) within the retardation zone of the diffuser for swirl removal from the swirling flow.A row with adjustable guide vanes (11) is arranged between these first means for swirl removal in the form of aerodynamic ribs and the outlet rotor blades. These guide vanes (11) have a straight mean camber line with a symmetrical aerofoil section, are conically shaped in the radial direction and are twisted.In addition to a substantial improvement in the pressure recovery over a wide load range, this measure also permits the vortex usually occurring between the rotor blades and the aerodynamic ribs to be prevented.

Abstract: The cooling-air ducting of the axial flow gas turbine runs in the area of the last blading stage (9+14) radially inwards of the heat-accumulation segments (23, 24) inside the outer boundary of the rotor (4) and through blade root channels (21) in the blade roots of the last moving blade ring (9) and finally through a cooling-air blade ring (28) fixed to the rotor into the diffuser into which the cooling-air flow enters with a velocity vector which essentially corresponds to the average velocity vector of the exhaust-gas flow entering into the diffuser. This avoids the flow losses which occur when the cooling-air flow passes out into the exhaust-gas flow in the area of the last stage or stages. At the same time, the temperature difference between the rotor circumference and the last rotor disk (4), likewise cooled by tapped air from the compressor, is in this way reduced, as a result of which the thermal stresses in the rotor are also reduced.

Abstract: A rotor including a disc requiring cooling, a drum, a cover surrounding the drum so as to provide an annular space, a radial cooling air supply line, and a deflection cascade in the supply line, which cascade deflects the cooling medium in the rotational direction of the rotor and accelerates the cooling medium to the peripheral velocity of the disc.

Abstract: An air storage gas turbine having a turbine, a combustion chamber supported on the external casing of the turbine and a hot gas casing leading from the combustion chamber to the blading. The hot gas casing is surrounded by an intermediate space. An inlet casing emerging into the intermediate space is provided with main air supply lines, in each of which is located at least one control device and one rapid shut-down device. The inlet casing forms an annular chamber and is provided with radial supply openings, a vertical outlet opening and axial outlet openings. A blow-out passage communicates the vertical outlet opening with a blow-out valve.

Abstract: An air storage gas turbine which, in the thermal part, comprises: a high pressure turbine with air inlet; a low pressure turbine with a rotor which requires cooling and a vane carrier; one high pressure balance piston and one low pressure balance piston located on a common shaft for the high pressure turbine and the low pressure turbine, respectively; and an impulse turbine being connected between the air inlet of the high pressure turbine and the consumers of low pressure auxiliary air.