Abstract: A turbine vane, especially a turbine vane of the last stages, respectively includes a lower area which is radially and externally arranged, an upper area which is radially and internally arranged, and a radial cooling air channel extending between the upper area and the lower area. Cooling air can be introduced into the channel via an inlet in the lower area, and can be at least partially discharged via an outlet in the upper area. The cooling channel includes a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel which is adjacent to the inner channel on the circumferential side thereof. The outer channel communicates with the inner channel and includes an outlet which is arranged in the lower area. Part of the cooling air flows back in the direction of the lower area via the outer channel and emerges via the outlet.

Abstract: A turbine blade through which cooling liquid flows, comprises several flow channels that are adjacently arranged in the flowing-off direction of the working fluid. The flow channels extend between inflow openings, which are located on a radially inner blade foot, and out-flow openings, which are situated opposite the blade foot in a more radially outer manner. The flow channels extend such that the local radial flow components of the resulting cooling fluid stream are directed outward in a, for the most part, predominately radial manner. A flow channel, which is in the front when viewing in the flowing-off direction, is provided whose outflow openings are placed inside a touching edge of the turbine blade. In addition, at least one rear edge channel is provided whose associated resulting cooling fluid stream additionally comprises local cross-flow components and whose outflow openings are placed inside a rear edge of the turbine blade.

Abstract: A moving turbine blade includes a blade profile with inner cooling which extends out from a blade platform adjoined by a blade foot, the blade foot engaging with a turbine disk and having a radial cross-section with an area whose width increases towards the blade platform. A moving turbine blade of this type is configured in such a way as to enable the moving blade profile to be lengthened. To this end, the blade foot has a hollowed-out section which opens out in the direction facing away from the platform side and which has a widened cross section in the area of the blade foot whose width increases.

Abstract: A turbine blade arrangement includes rotating blades respectively provided with a leg which can be respectively inserted into a groove on the outer circumference of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section which has a lateral platform located in an end area on the side of the disk. At least one part of the platform is joined to the turbine disk by way of a retaining element which is independent from the leg of the blades in order to extend the profiled sections of the rotating blades.

Abstract: A component can be subjected to hot gas. At least one duct is provided which can be subjected to a cooling fluid. The duct is bounded by two first walls opposite to one another. The walls include turbulators with the same direction of inclination. In order to avoid constrictions, the turbulators of the first wall have a different angle of inclination relative to a flow direction of the cooling fluid to the turbulators of the second wall.

Abstract: The invention relates to a turbine vane (1), especially a turbine vane of the last stages, respectively comprising a lower area (2) which is radially and externally arranged, an upper area (3) which is radially and internally arranged, and a radial cooling air channel (4) extending between the upper area and the lower area. Cooling air (23) can be introduced into said channel via an inlet (36) in the lower area, and can be at least partially discharged via an outlet (35) in the upper area. The cooling air channel comprises a radial inner channel through which the cooling air flows from the lower area to the upper area, and an outer channel (9) which is adjacent to the inner channel and which at least partially surrounds the inner channel on the circumferential side thereof. Said outer channel communicates with the inner channel and comprises an outlet (12) which is arranged in the lower area.

Abstract: The invention relates to a turbine blade (1) through which cooling liquid flows and which comprises several flow channels (4, 5, 6) that are adjacently arranged in the flowing-off direction (2) of the working fluid (3). Said flow channels (4, 5, 6) extend between inflow openings (7, 8, 9), which are located on a radially inner blade foot (10), and outflow openings (11, 12, 13), which are situated opposite the blade foot in a more radially outer manner. The flow channels (4,5,6) extend such that the local radial flow components (15) of the resulting cooling fluid stream (14) are directed outward in a, for the most part, predominantly radial manner. A flow channel (4), which is in the front when viewing in the flowing-off direction (2), is provided whose outflow openings (11) are placed inside a touching edge (16) of the turbine blade (1).

Abstract: The invention relates to a moving turbine blade comprising a blade profile (1) with inner cooling which extends out from a blade platform (2) adjoined by a blade foot (4), said blade foot engaging with a turbine disk (3) and having a radial cross-section with an area (5) whose width (6′) increases towards the blade platform (2). The aim of the invention is to configure a moving turbine blade of this type in such a way as to enable the moving blade profile to be lengthened. To this end, the blade foot (4) has a hollowed-out section (7) which opens out in the direction facing away from the platform, which comes to a dead end on the platform side and which has a widened cross section in the area (5) of the blade foot (4) whose width (6) increases.

Abstract: The invention relates to a turbine blade arrangement consisting of rotating blades (4) respectively provided with a leg (8) which can be respectively inserted into a groove (9) on the outer circumference (2) of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section (5) which has a lateral platform (6) located in an end area on the side of the disk. According to the invention, at least one part (10) of the platform is joined to the turbine disk by means of a retaining element (11) which is independent from the leg (8) of the blades in order to extend the profiled sections of the rotating blades.