항공기용 가스터빈 엔진의 고압터빈에서 열유동 특성해석을 위한 전산해석기법 연구

Abstract

In order to investigate thermal and flow characteristics of high pressure turbine, the numerical analysis methodology was set up using the k-ω based SST turbulent model with transition scheme. To validate the numerical methodology, C3X vane was selected. The surface pressure was not influenced by the viscous work term and transition models. However the surface temperature was affected by the viscous work term and transition models. We recommend γ transition model with viscous work term.