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The invention provides a high-temperature component for a turbomachine, in particular for a blade or vane having a main blade or vane part and a blade or vane root, the high-temperature component at least partially comprising, as base material, a porous material which is filled with a viscous filler

The invention provides a high-temperature component for a turbomachine, in particular for a blade or vane having a main blade or vane part and a blade or vane root, the high-temperature component at least partially comprising, as base material, a porous material which is filled with a viscous filler and is surrounded by a solid layer.

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The invention claimed is: 1. A turbine blade or vane component for use in a high temperature application, comprising: a blade or vane airfoil portion; a blade or vane root portion; a blade or vane platform portion; and a base material, wherein a portion of the base material is a porous material tha

The invention claimed is: 1. A turbine blade or vane component for use in a high temperature application, comprising: a blade or vane airfoil portion; a blade or vane root portion; a blade or vane platform portion; and a base material, wherein a portion of the base material is a porous material that is filled with a viscous filler and is surrounded by a solid layer. 2. The turbine blade or vane component as claimed in claim 1, wherein the porous material is a raw material based on a material selected from the group consisting of: silicon dioxide, aluminum oxide, zirconium oxide, magnesium oxide, and mica and aluminosilicates. 3. The turbine blade or vane component as claimed in claim 1, wherein the porous material has a porosity of at most 20%. 4. The turbine blade or vane component as claimed in claim 1, wherein the porous material has a porosity in the range of 10% to 15%. 5. The turbine blade or vane component as claimed in claim 1, wherein the porous material has a varying porosity. 6. The turbine blade or vane component as claimed in claim 1, wherein the porous material has a variable pore size. 7. The turbine blade or vane component as claimed in claim 1, wherein the base material is a granular material that forms a multiplicity of relatively small cavities. 8. The turbine blade or vane component as claimed in claim 1, wherein the viscous filler is a heat-resistant fluid. 9. The turbine blade or vane component as claimed in claim 1, wherein the viscous filler is a lubricant selected from the group consisting of: polyalkylene glycols, synthetic hydrocarbons, dicarboxylic acid and polyol esters, silicones, polyphenyl ethers, and fluorohydrocarbons. 10. The turbine blade or vane component as claimed in claim 1, wherein the viscous filler is a wax material. 11. The turbine blade or vane component as claimed in claim 1, wherein the porous material and the viscous filler are mixed in a ratio of 4 to 1, of 3 to 1 or of 2 to 1. 12. The turbine blade or vane component as claimed in claim 1, wherein the solid layer is a metal material made from a heat-resistant alloy and is substantially formed from a material selected from the group consisting of: a Ni-based material, a Co-based material, a Fe-based material, a Ti-based material, and combinations thereof. 13. The turbine blade or vane component as claimed in claim 1, wherein the solid layer has a thickness in the range of 100 μm to 1000 μm. 14. The turbine blade or vane component as claimed in claim 1, wherein the main blade or vane part and the blade or vane root are formed entirely from the porous material which is filled with the viscous filler and surrounded by the solid layer. 15. The turbine blade or vane component as claimed in claim 1, wherein the main blade or vane part has regions formed from the porous material and is filled with the viscous filler and surrounded by the solid layer. 16. The turbine blade or vane component as claimed in claim 15, wherein one third to half of the main blade or vane part is formed from the porous material and is filled with the viscous filler and surrounded by the solid layer. 17. A turbine component for use in a high temperature application, comprising: a base material, wherein a portion of the base material is a porous material that is filled with a viscous filler and is surrounded by a solid layer. 18. The turbine component as claimed in claim 17, wherein the component is a carrier element, bearing element or a ring element in a turbomachine. 19. A turbomachine, comprising: a turbine blade or vane for use in a high-temperature application; comprising: a blade or vane airfoil portion; a blade or vane root portion; a blade or vane platform portion; a base material, wherein a portion of the base material is a porous material that is filled with a viscous filler and is surrounded by a solid layer.