Abstract: A machine train includes a drive unit, preferably a steam turbine with axial exhaust flow, a geared turbine machine, and an additional compressor. The geared turbine machine has an integrated gear train with a drive pinion for driving turbine machine rotors via a large gear, and an output pinion of a rotational speed reduction power gear for driving the additional compressor.

Abstract: A machine train includes a drive unit, preferably a steam turbine with axial exhaust flow, a geared turbine machine, and an additional compressor. The geared turbine machine has an integrated gear train with a drive pinion for driving turbine machine rotors via a large gear, and an output pinion of a rotational speed reduction power gear for driving the additional compressor.

Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Abstract: A symmetrical component of a turbine unit, whose wall is exposed to a hot medium on one side and is subject to nonuniform thermal stress over the circumference, is cooled by a flow of cooling air being guided along the other side of the component. A ring (5) is provided with slots (7) or other openings for the passage of the cooling air. The ring (5) protrudes into the flow of the cooling air. The overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to the higher stress is larger than the overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to a lower stress.

Abstract: A device for sealing between the guide vanes (1) and the rotor (17) of turbomachines, especially gas turbines has inner rings (3) suspended on the vane footing (14) of the guide vanes (1) in a thermally elastic manner with soldered honeycomb seal (4) and labyrinth tips (5) arranged on the rotor (17). First flow channels, which are connected to the cavities (21) of the cooled guide vanes (1), through which said cavities cooling air flows, are led through the vane footings (14). The first flow channels are connected to at least one of second flow channels led through the inner ring (3) to the vicinity of the honeycomb seal (4). The second flow channels open into at least one of third flow channels that are open at the rear edge of the inner ring (3) or are led to an annular groove (10) open toward the honeycomb seal (4) on the underside of the inner ring (3).

Abstract: A symmetrical component of a turbine unit, whose wall is exposed to a hot medium on one side and is subject to nonuniform thermal stress over the circumference, is cooled by a flow of cooling air being guided along the other side of the component. A ring (5) is provided with slots (7) or other openings for the passage of the cooling air. The ring (5) protrudes into the flow of the cooling air. The overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to the higher stress is larger than the overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to a lower stress.