METHOD FOR FORMING THERMAL BARRIER COATING ON HOT-GAS-PATH COMPONENTS OF GAS TURBINE DURING OPERATION

摘要

PURPOSE: A method for forming a thermal barrier coating on hot-gas-path components of a gas turbine is provided to do a thermal barrier coating without stopping the gas turbine. CONSTITUTION: A method of the thermal barrier coating layer during the operation of the gas turbine comprises: a step of adding the organic compound which contain in the fuel the silicon under the first condition; and a step of adding the organic compound which contain in the fuel the silicon under the second condition. A base layer and a porous layer include silicon dioxide which becomes with the reaction of the organic compound and fuel gas. The thickness of the base layer 1 ~ 5μm The porosity of the porous layer 60%, and the thickness more than 5μm.