항공기용 고압 터빈의 정상 및 비정상 수치해석

초록

In a gas turbine engine, the vane and blade of the high pressure turbine are exposed to exceptionally complicate flow, because of the so-called the secondary flow phenomenon. This introduces the pressure and temperature gradients in the turbine rotor blade, which an unresolved phenomenon. In order to minimize the secondary flow loss in the turbine rotor blade redesign process steady and unsteady CFD analysis for the nozzle and the rotor blade passage of the axial flow turbine has been investigated. The governing equations are the RANS(Reynolds Averaged Navier Stokes) equations and the turbulent model is k-ω based SST(Shear Stress Transport) model for the better numerical simulation of the flow separations and shear stresses near the wall. This study has allowed a deeper analysis of the unsteady flow characteristics data.

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