Abstract: A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.

Abstract: A rotor for a gas turbine comprises a multiplicity of rotor blades of which each comprises a blade airfoil, a blade root and a platform arranged between blade airfoil and blade root and each of which, together with the blade root, is pushed into an axial location slot, which is arranged on the outer periphery of a rotor disk, and is releasably retained there in such a way that hollow spaces are formed between the platform and the peripheral surface of the rotor disk, and each of which is supplied, for cooling purposes, with cooling air through at least one cooling air supply passage extending in the rotor disk and emerging into the location slot, which cooling air is fed through the blade root to within the blade airfoil.

Abstract: A cooled component, such as a turbine blade for gas turbines is provided, having efficient internal cooling, with an interior cooling passageway having a round cross-section. A row of feeding holes for the coolant are arranged spaced from each other in the direction of the longitudinal axis of the cooling passageway and originating from a common coolant channel. Each of the feeding holes intersects the cooling passageway tangentially. The ease of manufacturing the cooling component is improved in that the majority of the feeding holes have a hole diameter that is smaller than half of the hydraulic diameter of the cooling passageway, and selected feeding holes have a hole diameter that is greater than half of the hydraulic diameter of the cooling channel.

Abstract: The devices according to the invention serve to direct a cooling fluid 230 in a cooled blade 210 of a turbomachine, in particular a gas turbine. In this case, the blade 210 has at least one cooling channel 213 running in the blade. According to the invention, at least one drawer 220 is arranged in at least one slot 221 of the blade 210. In a preferred embodiment of the invention, the drawer 220 arranged in the slot 221 is directly adjacent to the cover wall 212 and/or at least one side wall 211 of the blade. Furthermore, arranged in the drawer is at least one flow channel 222, which is preferably formed from a groove arranged in the drawer 220 and from the directly adjacent cover wall 212 and/or side wall 211. The flow channel 222 is connected to the cooling channel 213 by means of at least one opening 223. In addition, the cooling fluid 230 fed to the flow channel 222 flows off through a passage opening 224 in the cover wall 212 and/or the side wall 211 into the main flow flowing around the blade.

Abstract: A blade component of a gas turbine is disclosed around the outside of which hot air flows. The blade component is constructed as a hollow profile having outside walls and a tip cover, and having guiding walls arranged between the outside walls and connecting said outside walls. The blade component is cooled on the inside by cooling air flowing through cooling channels between the outside walls and the guiding walls. Cooling air flows through deflection areas in which the cooling air is deflected into flow stagnation zones. An efficient cooling of the blade component in the area of the stagnation zones is obtained in the area of the flow stagnation zones which are located at the outer corner of the deflection area. At least one drilled opening is provided in the outside wall through which drilled opening cooling air is able to flow at the stagnation zone from the cooling channel onto the outside of the blade component.

Abstract: In an air-cooled turbine blade (10) which has a shroud-band element (11) at the blade tip, the shroud-band element (11) extending transversely to the blade longitudinal axis, hollow spaces (16, 16′, 17, 17′) for cooling being provided in the interior of the shroud-band element (11), which hollow spaces (16, 16′, 17, 17′) are connected on the inlet side to at least one cooling-air passage (18) passing through the turbine blade (10) to the blade tip and open on the outlet side into the exterior space surrounding the turbine blade (10), the hollow spaces (16, 16′, 17, 17′) and the shroud-band element (11) are matched to one another in shape and dimensions in order to reduce the weight of the shroud-band element (11).