Development of a Thermal Shock Resistance Evaluation Device for Coatings in Aviation

In this study, a test device was developed to evaluate the thermal shock resistance performance of thermal barrier coatings, which are being developed for application in aviation engines.To simulate the combustion conditions of an aviation engine, compressed air and aviation fuel were burned to generate a high-temperature jet flow, which was used to heat the front surface of the thermal barrier coating.At the same time, cooling air was injected onto the rear surface to create a thermal gradient in the test specimen.The developed device was capable of generating a jet flow with a mass flow rate of 32 g/s, a temperature of 1200°C, and a velocity of 300 m/s, demonstrating high operational reliability within a temperature deviation of 10°C.Through thermal shock testing on the developed combustion and turbine coatings, the test device was verified to be suitable for evaluating long-term durability as well. 초 록본 연구에서는 항공 엔진 적용을 목표로 개발되고