In power plants and aircraft industries, power is generated by gas turbine machine. As high efficiency for gas turbines is demanded, the operating temperature of the turbine needs to be increased as well. Therefore, high temperature stability of the hot gas components of the gas turbine is required. Silicon Carbide Fiber reinforced composites are suitable for the advanced material of gas turbines because of their high reliability and excellent properties at high temperatures. However, mass reduction of products may occur due to reaction with water vapor at high temperature and oxidation reaction. This can affect the life and operation of the turbine part. Therefore, the study of the environmental coating layer is necessary. In this study, a variety of silicon based ceramic materials were selected, coated specimens were prepared by plasma spraying on the composites to replace turbine heat resistant alloys, and evaluated by thermal shock test. This aims to confirm the durability of the environmental barrier coating layer against the thermal shock that occurs during the operation of the gas turbine. After the thermal shock test, the growth behavior of cracks density of the cracks were analyzed to confirm the stability of the environmental barrier coating layer.