Abstract: A blade for a turbine blade includes a suction-side side wall and a pressure-side side wall that enclose a cavity at least partially in a manner which extends along a profile centre line from a common front edge to a common rear edge and in a span width direction from a root-side end to a tip-side end. A first perforated impingement cooling wall which is provided with openings for the impingement cooling of the front edge and at least one further perforated impingement cooling wall for the impingement cooling of a section of the suction-side and/or pressure-side side wall are provided in the interior along the span width. The impingement cooling openings of the first impingement cooling wall and the at least one second impingement cooling wall are connected in series in terms of flow.

Abstract: A blade for a turbine blade includes a suction-side side wall and a pressure-side side wall that enclose a cavity at least partially in a manner which extends along a profile centre line from a common front edge to a common rear edge and in a span width direction from a root-side end to a tip-side end. A first perforated impingement cooling wall which is provided with openings for the impingement cooling of the front edge and at least one further perforated impingement cooling wall for the impingement cooling of a section of the suction-side and/or pressure-side side wall are provided in the interior along the span width. The impingement cooling openings of the first impingement cooling wall and the at least one second impingement cooling wall are connected in series in terms of flow.

Abstract: A turbine blade comprising at least one cooling element, a cooling duct for conducting a cooling medium, and a leading edge is provided. The cooling element is located within the flow of the cooling medium and is designed in a cog-shaped manner. The cooling duct is formed within the turbine blade for conducting a cooling air flow and extends along the flow attacking edge in at least some sections. The cooling elements are successively arranged in a stationary manner inside the cooling duct in the longitudinal direction. Each individual cooling element has a cooling capacity that is adapted to a predefined cooling requirement for the leading edge in the vicinity of the cooling element.

Abstract: A turbine blade comprising a plurality of ribs arranged one after the other in a cooling channel extending along a leading edge is provided. The plurality of ribs is split into pairs of ribs formed by two ribs arranged in the form of a skating step.

Abstract: A cooled turbine rotor blade for a gas turbine which is traversed axially by flow and is equipped with an attachment area and an airfoil profile is provided. Meandering cooling channels with interposed deflecting regions are provided in the interior of the airfoil profile. In the deflecting regions, it is possible to prevent dead water regions, which are generated in the prior art, by virtue of at least one of the ribs running so as to curve towards the leading edge or towards the trailing edge in the region of the airfoil tip. At the same time, an opening is provided in the curvature of the rib. Through this opening a part of the coolant flows in the deflecting region and can pass over into the adjacent cooling duct.

Abstract: Even a layer system, provided with a protective coating and used in a hot gas atmosphere needs to be cooled. However, said cooling is often insufficient, as far as cooling pipes are arranged relatively far from the external surface of said layer system. In order to solve the problem, the inventive coolable layer system consists of intersecting cooling pipes.

Abstract: The invention relates to a turbine blade which has a nose cavity in the region of a leading edge, it being possible for the leading edge to be cooled by impingement cooling, which has an inner cavity at least partly of meander-shaped design, and which has a crown pocket as cavity in the region of the blade tip, which crown pocket is connected to the nose cavity, so that the cooling of the turbine blade is improved.

Abstract: A turbine blade or vane for use in a gas turbine is to have as long a service life as possible at high strength. To this end, the turbine blade or vane, according to the invention, has a basic body which is formed from a strengthened cast ceramic material and in which a number of reinforcing elements are placed.

Abstract: The invention relates to a turbine blade which has a nose cavity in the region of a trailing edge, it being possible for the trailing edge to be cooled by impingement cooling, which has an inner cavity at least partly of meander-shaped design, and which has a crown pocket as cavity in the region of the blade tip, which crown pocket is connected to the nose cavity, so that the cooling of the turbine blade is improved.

Abstract: A structural part of a gas turbine plant is cooled by branching off a partial mass air stream, after being compressed by a compressor of the gas turbine plant, from a main mass air stream. The cooling partial mass air stream is ducted in a closed duct to the structural part to be cooled. At the same time, the partial mass air stream undergoes, independently of the main mass air stream, additional compression which is carried out by utilizing the rotational energy of a turbomachine shaft of the gas turbine plant. The novel gas turbine plant therefore is provided with a secondary compressor. The invention is suitable particularly for use in stationary gas turbine plants.

Abstract: A structural part of a gas turbine plant is cooled by branching off a partial mass air stream, after being compressed by a compressor of the gas turbine plant, from a main mass air stream. The cooling partial mass air stream is ducted in a closed duct to the structural part to be cooled. At the same time, the partial mass air stream undergoes, independently of the main mass air stream, additional compression which is carried out by utilizing the rotational energy of a turbomachine shaft of the gas turbine plant. The novel gas turbine plant therefore is provided with a secondary compressor. The invention is suitable particularly for use in stationary gas turbine plants.

Abstract: A heat-shield component with a cooling-fluid return, a hot-gas wall to be cooled, an inlet duct for conducting a cooling fluid and an outlet duct for returning the cooling fluid. The inlet duct is directed towards the hot-gas wall and widens in a direction of the hot-gas wall. Furthermore, the invention relates to a heat-shield configuration which lines a component directing a hot gas, in particular a combustion chamber of a gas-turbine plant. The heat-shield configuration and has a plurality of the heat-shield components.