| 摘要 |
Disclosed is a gas turbine blade ( 1 ) having a ceramic heat-insulating layer ( 17 ). The ceramic heat-insulating layer ( 17 ) consists of 10-95% wt. % magnesium aluminate, 5-90 wt. % magnesium oxide and 0-20 wt. % aluminum oxide. Magnesium oxide particles are incorporated into a matrix made of spindle-shaped magnesium aluminate, enabling the thermal expansion coefficient of the ceramic heat-insulating layer ( 17 ) to be adapted in a particularly suitable manner to a metallic base body ( 15 ) of the gas turbine blade ( 1 ). The ceramic heat-insulating layer ( 17 ) also has a porosity which is greater that 3 vol. %, thereby guaranteeing sufficiently low heat conductivity.
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