Parallel Simulation of Aerodynamic Instabilities in Transonic Axial Compressor Rotor

Abstract

Although significant advances have been made in simulations of rotating stall and surge with single passage or part-annulus passages models, quite little work has been devoted to three-dimensional unsteady full-annulus simulations of the aerodynamic instabilities. In this Paper, a hierarchical domain decomposition method coupled with an artificial interface method is proposed and applied to the full-annulus simulations of three-dimensional aerodynamic instabilities in NASA rotor 35 at low flow rates. The compressor–throttle valve model and compressor–plenum chamber model are adopted to consider the effects of pipe network system on the compressor. The parallel results fit both the serial results and experimental data well, and the parallel efficiency is around 84% with 432 processor cores. With compressor–throttle valve model, rotating stall is observed in that the unsteady performance path converges to a fixed point, and the rotating speed, number, and size of stall cells vary slightly from the stall inception to the developed stall. With the compressor–plenum chamber model, mild surge is observed in that the unsteady performance path converges to a limit cycle oscillation, and low-frequency and large-amplitude axisymmetric oscillations propagate periodically along the axial direction. The occurrence of rotating stall or surge is consistent with the well-established laws of parameter .