Gas turbine component with a thermal barrier coating,...

Details Gas turbine component with a thermal barrier coating,... Gas turbine component with a thermal barrier coating,...

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 5/28 (2006.01)

Patent

CA 2658275

The invention relates to a gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to said base body and consists of or includes an oxide ceramic, wherein micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.

L'invention concerne un élément de turbine à gaz d'un moteur d'avion avec un corps de base constitué d'au moins un premier matériau et une couche calorifuge appliquée sur ce corps de base, la couche calorifuge étant constituée d'une céramique d'oxyde ou comportant une céramique d'oxyde. La conductivité thermique de la couche calorifuge est réduite en intégrant des microdéfauts et/ou des nanodéfauts dans la céramique d'oxyde.

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