Heat insulation protection component useful as heat shield or turbine blade of combustion chamber of stationary gas turbine or aircraft engine on substrate, comprises tributyl citrate-heat insulation layer and/or ethylbenzyl chloride layer

摘要

The heat insulation protection component on a substrate, comprises a tributyl citrate-heat insulation layer and/or an ethylbenzyl chloride layer on hot-gas side and a ceramic carboxy methyl cellulose-composite material on substrate-side. The heat insulation protection component is made of oxide ceramics. The layers and the ceramic carboxy methyl cellulose-composite material contain infrared-reflecting metal components, which consist of metal foils (1), metal flakes (2), metal particles (3), metal powder and/or metal fibers (4) on the hot-gas side and/or substrate-side. The heat insulation protection component on a substrate, comprises a tributyl citrate-heat insulation layer and/or an ethylbenzyl chloride layer on hot-gas side and a ceramic carboxy methyl cellulose-composite material on substrate-side. The heat insulation protection component is made of oxide ceramics. The layers and the ceramic carboxy methyl cellulose-composite material contain infrared-reflecting metal components, which consist of metal foils (1), metal flakes (2), metal particles (3), metal powder and/or metal fibers (4) on the hot-gas side and/or substrate-side on the surface of the metal components. The heat insulation protection component has oxidic fibers (5), whose surfaces are partially or completely coated with the infrared-reflecting metal components. The mass of the metal components is less than 1% related to the mass of the heat insulation protection component. The tributyl citrate-heat insulation layers and/or the ethylbenzyl chloride layers have a thickness of 10-1000 mu m. The substrate comprises a turbine blade with optionally an adhesive mediator layer. An independent claim is included for a method for producing a heat insulation protection component.