내부냉각노즐의 열차폐코팅을 위한 복합열전달 해석기법 연구

Abstract

In this study, a conjugate heat transfer analysis methodology was studied for TBC application using NASA C3X Vane. Two methodologies were compared. First was physically modeling a real TBC structure and second was numerically modeling heat resistance on the vane surface. 0.1mm, 0.2mm and 0.3mm thickness were modeled for TBC layer utilizing 20mol.% YSZ. Surface pressure showed almost the same for all cases. Vane surface temperature for both methodology appeared the same. As the TBC layer thickness was increased by 0.1mm, the average vane surface temperature was decreased by 3-4K. The temperature change when TBC is applied was small compared to other studies. The reason is due to thick vane walls and low temperature difference of the main fluid and coolant fluid. The numerical TBC can be used to alter physical TBC to save analysis cost.