| 摘要 |
The invention relates to a heat-insulating layer system for metallic structural components, especially for structural components of a gas turbine such as an aircraft engine. The heat-insulating layer system ( 13 ) comprises an inner contact layer ( 14 ) and an outer cover layer ( 15 ), whereby the inner contact layer ( 14 ) is applied onto a surface ( 11 ) of a gas turbine structural component ( 10 ) with intermediate arrangement of an adhesion promoting layer ( 12 ). According to the invention, the inner contact layer ( 14 ) is formed of a zirconium oxide partially stabilized with yttrium or yttrium oxide, the outer cover layer ( 15 ) is formed of lanthanum hexaaluminate.
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