Superalloy test pieces for three different typical forms of cooling laminated configurations were designed and processed. High working temperature of cooled turbine blades in real engine was simulated; the thermal fatigue life of each type of cooling laminated configuration by thermal cycling loading was studied experimently; the reasons for its destruction and damage locations were analyzed

and the data were compared with the numerical results. The results show that thermal fatigue cracks in each configuration occur near the film holes of exhaust plate and extend along longitudinal direction of film hole. The cracks extention at inner surface is greater than that at outer surface. 211-type has the shortest thermal fatigue life among three cooling laminated configurations

and the thermal fatigue lifes of 161-and 141-type cooling laminated configurations are on the same level.