Numerical investigation of the effect of stator clocking on blade boundary layer flow in compressor

Numerical simulation is applied to investigate the unsteady flow fields at the mid-span of a two-stage low-speed compressor. Detailed analysis of blade unsteady boundary layer flow of rotor-stator interaction condition is presented by the analysis model of rotor wake and stator boundary layer interaction under typical clocking positions of the second stator row. The skin friction of suction side and turbulence kinetic energy close to the suction side are presented to analyze the effect of stator clocking on blade boundary layer flow. Results of the research on the second stator boundary layer show that stator clocking alters the transportation character of the wakes in the stator flowfield, reduces the skin friction and turbulence kinetic energy close to the wall as well as the maximum unsteady fluctuations. And it also affects the calmed region width behind the rotor wakes in the stator blade suction side boundary layer. Under unsteady condition, the stator laminar flow can be induced to turbulent flow in local wake disturbance region (wake-induced transition), and the wake disturbance with high turbulence intension is able to control the boundary layer separation flow under negative pressure gradient and to extend the range of laminar region.