Method of manufacturing a component of a gas turbine engine

A system for manufacturing a component of a gas turbine engine, comprising:

• a coating apparatus configured to apply a thermal barrier coating (TBC) to a precursor component, the precursor component at least one internal cooling passage configured to receive a flow of cooling air therethrough;
• and
• processing circuitry coupled to the coating apparatus and configured to execute instructions comprising:
• estimating a predicted temperature profile for the component based on one or more operating parameters of the gas turbine engine, the predicted temperature profile indicating a predicted operating temperature of at least one gas-washed surface of the component;
• and
• determining a TBC configuration for the component based on the predicted temperature profile, comprising setting a TBC thickness to be below a threshold thickness in a region of the at least one gas-washed surface of the component based on the predicted operating temperature of the at least one gas-washed surface of the component exceeding a threshold temperature;
• wherein the coating apparatus is configured to apply a TBC to the precursor component according to the TBC configuration.