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. Said vane wheel having a plurality of turbulators is embodied on at least one of the walls of the cooling channel, said 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: The invention relates to a temperature resistant layered structure comprising a substrate and a porous layer arranged on the substrate having a pore defined by a wall, and a ceramic coating on an interior surface of the wall. The invention also relates to a layered turbine component arrangement comprising a substrate having a cooling passage adapted to allow a cooling gas medium to pass through the substrate and a porous layer arranged on the substrate, the porous layer having cooling passages formed by gas-permeable inter-connections between pores in the porous layer.

Abstract: Layered systems in prior art are inefficient at cooling an external hot gas. The inventive layered system comprises an external porous layer, in which the pore walls of the pores have differing thicknesses. This improves the cooling action by preventing too much heat from entering the layered system.

Abstract: A coolable segment for a turbomachine such as a combustion turbine, which turbomachine is operated with a hot fluid. The segment comprises a cooling wall extending in an axial direction and in a circumferential direction orthogonal to the axial direction; a hot fluid surface to be exposed to the hot fluid. Between the wall and the surface a cooling structure is arranged which is permeable to cooling fluid and provides cooling surfaces for cooling by heat transmission through radiation. The cooling structure comprises either a netting, in particular a wire netting or a porous material.

Abstract: The invention relates to a temperature resistant layered structure comprising a substrate and a porous layer arranged on the substrate having a pore defined by a wall, and a ceramic coating on an interior surface of the wall. The invention also relates to a layered turbine component arrangement comprising a substrate having a cooling passage adapted to allow a cooling gas medium to pass through the substrate and a porous layer arranged on the substrate, the porous layer having cooling passages formed by gas-permeable inter-connections between pores in the porous layer.

Abstract: The invention pertains to a coolable segment (1) for a turbo machinery (20), which turbo machinery (20) is operated with a hot fluid (29). The segment (1) comprises a cooling wall (2) extending in an axial direction (37) and in a circumerential direction (36) orthogonal to said axial direction (37); a hot fluid surface (3) to be exposed to the hot fluid (29). Between the wall (2) and the surface (3) a cooling structure (4) is arranged which is permeable to cooling fluid (5) and provides cooling surfaces (6) for cooling by heat transmission through radiation. The cooling structure (4) comprises either a netting, in particular a wire netting or a porous material. The invention further pertains to a combustion turbine (20) comprising a coolable segment (1).