The operating temperature of the combustion chamber of heavy-duty gas turbines has been continually increased in order to improve engine power and efficiency. Part of this improvement is due to the use of ceramic thermal barrier coatings (TBCs), which reduce thermal flow from the combustion gas to the metallic structural part of the components. The most traditional deposition technique for bond coats on combustion chamber components is Air Plasma Spray; whereas this technology is the optimum one for ceramic coatings, due to air entrapment in the plasma jet significant oxidation of Al is produced during bond coats deposition. The thermal design of a thick porous TBC able to reduce the heat flow to the minimum allowable by the materials temperature limits is performed. Paper includes a German-language abstract.