This article presents issues concerning the relationship between the degradation of the coating of gas turbine blades and changes in the color of its surface. Conclusions were preceded by the determination of parameters characterizing changes in the technical condition of protective coatings made based on a metallographic examination that defined the morphological modifications of the microstructure of the coating, chemical composition of oxides, and roughness parameters. Most of gas turbine performances evolving coatings on combustion chambers because of its high temperature withstand ability improves combustion process. As a part of this some works which is considerable for improving performances stage wise compressor blades also coming in to consideration. Deterioration of blades also affects total performance of turbine, this leads to engine performances depended on gas turbine efficiency. In order to stream line minimum gaps occurred in long life cycles of gas turbine linked engines thermal stresses on blades also becoming a needful factor of research. Coatings are frequently applied on gas turbine components in order to restrict surface degradation such as corrosion and oxidation of the structural material or to thermally insulate the structural material against the hot environment, thereby increasing the efficiency of the turbine. However, in order to obtain accurate lifetime expectancies and performance of the coatings system it is necessary to have a reliable understanding of the mechanical properties and failure mechanisms of the coatings.

Gas Turbine, coating on blades, corrosion and oxidation.