抄録
Thermal barrier coatings (TBC) for a 1700℃-class advanced closed-cycle gas turbine system are studied, aiming at the surface temperature of higher than 1300℃ and the allowable temperature-difference of higher than 350℃. As a result of the studies, it is showed that following processes are effective to improve the durability of TBC, i ) increasing the purity of raw powder for top-coat, ii ) using ZrO_2-Er_2O_3 as top-coat material, iii ) shaping top-coat in columnar structure by EB-PVD.
