비정렬 격자를 이용한 3차원 천음속 팬 점성유동 해석

Abstract

A three dimensional viscous flow solver is developed for turbomachinery components using unstructured meshes. The numerical scheme is based on the Roe``s flux-difference splitting with an explicit Runge-Kutta time integration. A standard κ-ε turbulence model with wall function boundary condition is adopted to simulate high Reynolds number flows. To accelerate the convergence to steady state, local time stepping and implicit residual smoothing are applied. The code has been applied to calculate the performance of a transonic axial fan rotor operating both at near peak efficiency and at near stall. Blade-to-blade contour plots are compared with the experimental data to validate the present solver. Calculated Mach number distributions are compared with laser anemometer data within the blade row to quantify the accuracy of the calculations.