Abstract: Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions extending from the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.

Abstract: The invention refers to a method for applying heat resistant protection components onto the surface of a heat exposed component. The method including providing at least two separate heat protection components, and joining the at least two separate heat protection components onto their top surface and/or bottom surface and/or at least one side surface by flexible means for obtaining an integrally handable entity. The method further includes fixing the integrally handable entity by applying and brazing the surface of each heat protection component on the surface of the heat exposed component. The materials of the flexible means and for joining the flexible means on the separate heat protection components are selected such that the materials withstand brazing being performed under protective atmosphere, i.e. an atmosphere without or with reduced amount of oxygen, at process temperatures between 700° C. and 1200° C., and that the materials are burned out after brazing during a following oxidizing thermal step.

Abstract: The invention refers to a method for applying heat resistant protection components onto the surface of a heat exposed component. The method including providing at least two separate heat protection components, and joining the at least two separate heat protection components onto their top surface and/or bottom surface and/or at least one side surface by flexible means for obtaining an integrally handable entity. The method further includes fixing the integrally handable entity by applying and brazing the surface of each heat protection component on the surface of the heat exposed component. The materials of the flexible means and for joining the flexible means on the separate heat protection components are selected such that the materials withstand brazing being performed under protective atmosphere, i.e. an atmosphere without or with reduced amount of oxygen, at process temperatures between 700° C. and 1200° C., and that the materials are burned out after brazing during a following oxidizing thermal step.

Abstract: Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions located in the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities.