Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: A component which can be subjected to hot gas for a gas turbine, the component having at least one wall, which includes a first surface as far as an edge, the first surface for delimiting a hot gas flow path of the gas turbine, and which includes a second surface, which adjoins the edge and is arranged transversely to the first surface. A groove for receiving a sealing element is arranged in the second surface and extends at least partially along the edge at a distance from the edge. The groove includes a groove base lying opposite the groove opening and two mutually facing side walls which adjoin the groove base and extend along the edge. At least one of the side walls has at least one groove-shaped recess.

Abstract: A turbine blade, including: an airfoil and a platform, which has an upper face on which the airfoil is arranged; and at least one lateral face, the lateral face including a slot for insertion of a sealing strip. The transition between the upper face of the platform and the at least one lateral face includes a stepped portion and a beveled portion is provided.

Abstract: A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.

Abstract: A guide vane for a gas turbine with a vane base body which is of single-piece design and comprises a profiled vane blade extending between a vane root and a cover plate and also the vane root formed integrally with the vane blade and the cover plate formed integrally with the vane blade, is intended, in a relatively simple way to be able to be matched to the individual conditions of use with especially little outlay on apparatus and logistics. For this purpose, according to the invention, a flow-routing body with an advance guide blade that is connected upstream of the vane blade as seen in the direction of flow of the working medium of the gas turbine is joined to the vane base body.

Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

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: An axial turbine for a gas turbine including a rotor blade cascade is provided. The rotor blade cascade is formed from rotor blades each including, a front edge, a blade tip, and an annular space wall that surrounds the rotor blade cascade and includes an annular space inner side, enabling the annular space wall to be arranged directly adjacent to the blade tip forming a radial gap between the covering of the blade tip and the annual space inner side. When the turbine is in operation, the area of the blade tip with the highest pressure load is disposed in the region of the front edges, and the rotor blades in the region of their front edges include a radial projection and the annular space wall includes on the annular space inner side, a peripheral radial recess that interacts with the radial projections such that a minimum is established in the direction of the main through-flow of the turbine.

Abstract: A turbine blade with an aerodynamically profiled blade leaf which is produced from two assembled shell elements is provided. The shell elements forming the suction-side and the pressure-side blade leaf wall have been assembled by a high-temperature and high-pressure bonding process. In the region of the blade leaf tip, a cramp is provided which hooks the two blade walls together with one another with a form fit.

Abstract: There is described a vane wheel of a turbine comprising at least one vane, the footing thereof being held on a wheel disk. At least one cooling channel is arranged between the wheel disk and the vane footing. The vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, the turbulators being configured in such a way that the turbulence and thus the heat transfer of a cooling fluid flowing through the cooling channel are increased.

Abstract: A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure.

Abstract: The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element.

Abstract: A turbine blade (2), with a root section (4), with a tip section (6) and with a blade leaf (12) which is provided with a number of coolant ducts (22) through which a coolant (K) is capable of flowing, outlet ducts (34) which issue in outlet ports (24) branching off, in the leading edge region (28) of the blade leaf (12), from a coolant duct (22) running essentially in the longitudinal direction (L) of the turbine blade (2) and spaced apart from the leading edge (14), the outlet ports (24) being arranged along at least two rows oriented essentially parallel to the leading edge (14), and the outlet ducts (34) being oriented, in the region of their respective outlet port (24), obliquely with respect to the longitudinal direction (L) of the turbine blade (2), in such a way that the coolant (K) flowing out in a root-side subsection (38) of each row possesses, in the region of the outlet ports (24), a velocity component pointing toward the tip section (6) of the turbine blade (2), and the coolant (K) flowing out in