| 摘要 |
Shroud device (10) thermally protecting a gas turbine blade, comprising a ceramic layer (11) and a metallic layer (12), the metallic layer (12) being thermally protected by the ceramic layer (11), the ceramic layer (11) being mechanically joined to the metallic layer (12) by a fixation device (20) comprising a plurality of protrusions (21) located in the metallic layer (12) designed so as to engage with a plurality of cavities (22) located in the ceramic layer (11), such that there exists a gap (50) between the cavities (22) and the protrusions (21) at ambient temperature, the gap (50) disappearing at high temperature operation of the gas turbine, the protrusions (21) being then locked into the cavities (22). |
