항공기용 가스터빈 엔진의 고압터빈에서 열유동 특성해석을 위한 전산해석기법 연구

Abstract

In this study, a numerical analysis methodology is studied to predict thermal and flow characteristics of C3X vane withinternal cooling. Effects of turbulence models, transition models and viscous work term on temperature and pressuredistributions on the vane surface are investigated. These optional terms have few effects on the pressure distributions over thevane surface. However, they have great influence on prediction of the temperature distributions on the vane surface. Thecombination of k-ω based SST turbulence model, γ transition model and viscous work term are better than RSM turbulencemodel on prediction of the surface temperature. The average temperature difference between CFD results and experimentalresults is calculated 2 % at the pressure side and 1 % at the suction side. Furthermore computing time of this combination ishalf of the RSM turbulence model. When k-ω based SST turbulence model and γ transition model with viscous work term areapplied, more accurate predictions of thermal and internal flow characteristics of high pressure turbine are expected.