Abstract: A turbine blade for a turbine of a thermal power plant, with a platform for partial delimiting of a flow passage in the turbine, wherein the platform has at least one cooling medium passage, which extends inside the platform, for guiding a cooling medium, is characterized according to the invention in that the at least one cooling medium passage emerges from the platform at at least two connecting openings, and the turbine blade has at least one supplementary component which can be fastened on the platform, with a communicating passage, which is designed for interconnecting the connecting openings in a fluid-guiding manner.

Abstract: The invention proposes a cooling system (42) for a gas turbine (1), with an annular duct extending axially in the compressor (5). In the annular duct, a ring (15) of compressor guide blades (14, 28, 33) and a ring (17) of moving blades (16) fastened to a rotor disk (19) of the rotor (3) are provided, with at least one cooling-air extraction point (34), arranged on the rotor (3), for diverting a cooling-air stream into a cooling-duct system arranged in the rotor (3), and with a turbine unit (8), in which, when the gas turbine (1) is in operation, components subjected to thermal stress by a hot gas (20) can be cooled by the divertible cooling-air stream, and also with a feed line (46) for feeding a liquid (45) into the cooling-air stream.

Abstract: The invention relates to a method for repairing components comprising a base material with an oriented microstructure, wherein the repair point comprises a correspondingly oriented microstructure as the surrounding base material. According to the inventive method, solder is applied in the region of a point which is to be repaired and is soldered to the component by means of a heating effect produced by a device. A temperature gradient, i.e., approximately a temperature characteristic, is produced during the heating effect, said temperature characteristic ranging from a high to a low temperature in the region of the point which is to be repaired.

Abstract: The invention relates a method for improving the hot-starting behavior of a turbomachine. By virtue of the setting of a radial gap formed between a brushing edge of a blade profile and a guide face lying opposite this, in which setting a guide ring forming the guide face can be acted upon with a coolant, the hot-starting behavior can be improved, in that the guide ring is cooled before the start of the machine.