Multi-passage time-resolved CFD analysis of rotor tip stall inception and passive control in a highly-loaded axial compressor

摘要

Casing treatment is a known design technique for improving the stability of operation of high-speed aircraft engines.Although many different casing treatment concepts have been investigated in the literature, widespread consensus ona standard design for axial compressors is not established.One reason for this could be the component efficiency penalty caused by some casing treatments. The time dependentsimulation in this work show that the flow structure breakdown follows the formation of reversed flow at blade leading edge. This paper aims to achieve an increase in the rotor operating range by using the recirculation type casing treatment. Unlike other known casing treatments like an axisymmetric square groove, higher improvement in the stall margin is expected by generating flow. The steady state numerical simulations have shown a useful extensionof the rotor operating range by using this recirculation type treatment, without the adiabatic efficiency penalty of othertreatments, reported in previous work.