Patent ID: 11859287
Assignee: HONEYWELL INTERNATIONAL INC.
Field: Materials, metallurgy (Chemistry)
Classification: CPC C  F  Y | IPC C  F

Claim 0:
1. A protective coating system comprising:
a turbine engine component substrate formed of a ceramic matrix composite material;
an environmental barrier coating layer comprising a rare earth disilicate material formed directly on the substrate; and
a thermal barrier coating layer comprising a porous rare earth monosilicate material formed directly on the environmental barrier coating layer by decomposition or conversion of the rare earth disilicate material to produce a chemical transition between the environmental barrier coating layer and the thermal barrier coating layer, wherein the porous rare earth monosilicate material has a metal silicate material infiltrated within at least a portion of the pores, wherein the thermal barrier coating layer has a thickness of between 5 and 25 microns, wherein the thermal barrier coating layer has a porosity gradient such that first portions of the thermal barrier coating layer adjacent to the environmental barrier coating layer have a lower porosity than second portions of the thermal barrier coating layer further from the environmental barrier coating layer.