FIELD: technological processes.
SUBSTANCE: gas turbine component having a heat insulating outer surface for exposure to combustion gas, comprising a metallic substrate, an anchoring layer built upon the substrate surface, a thermal barrier coat, a structure of protruding elements and a structure of the elements in the form of grooves. Thermal barrier coating includes an outer thermal barrier coating layer having an inner surface applied over and adhered to the anchoring layer, and an outer surface for exposure to combustion gas. Structure in the form of protruding elements has a height of protrusions ranging from 2 to 75 % of the total thickness of the thermal barrier coating layers. Structure of the elements in the form of grooves has grooves formed in the previously deposited layer of the outer heat barrier coating, along its outer surface, and penetrating into this layer. Structure of protruding elements and the structure of elements in the form of grooves are in respectively limited, separated, three-dimensional, independently aligned structures passing through the component. Another invention relates to a gas turbine engine comprising said component. In the manufacture of said gas turbine engine component, an anchoring layer is grown on the surface of the substrate and a structure of elements protruding therefrom is formed in the anchoring layer. Then a thermal barrier coating layer is formed and the structure of elements in the form of grooves is formed in the previously applied layer of the outer thermal barrier coating along its outer surface penetrating into this layer.
EFFECT: group of inventions makes it possible to increase the reliability of the coating and to enable the localisation of cracks propagating in the thermal barrier coat and caused by thermal stresses or damages by foreign objects.
14 cl, 49 dwg
