Surge Improvement in an Isolated Rotor with Enhanced Airfoil

Every compressor works in a limited operational range. As one of the sources of this limitation, surge, has been studied for many years. In this research, an isolated rotor blade row compressor is numerically modeled and solved by a CFD code. In order to improve operational limit and postpone the surge, a stepped blade of RAF6E with higher stall angle is used to investigate the near stall flow behavior. In this study, several locations of step on blades are tried and the results are compared with the case with no step on blades. It is shown that, as the step moves toward the leading edge of blades, the effect of delay on surge is reduced and even efficiency is decreased significantly. By moving the step towards the trailing edge, surge is delayed due to the reattachment of flow after the step. Efficiency is also decreased but lower than previous case

کلیدواژه ها:

compressor performance ، efficiency ، stable operational margin ، stepped airfoil ، surge improvement