关键词: 非定常干扰；附面层转捩；尾迹；压气机

Abstract: In order to reveal the unsteady flow mechanism of compressor blade boundary layer under rotor/stator aerodynamic interaction，numerical simulation was applied to investigate the unsteady boundary layer flow of the stator at the mid-span in a high loading transonic fan stage. Critical parameters，including skin friction，turbulence kinetic energy and static pressure fluctuation on the blade surface，were analyzed in detail to describe the unsteady effects of the high loaded stator boundary layer based on the model of rotor wake/potential-stator boundary layer interaction. The numerical results show that the bypass transition would occur in the stator boundary layer during the impinging of the rotor wake. And also，a pressure fluctuation would propagate with the speed of sound along the blade boundary layer after the leading edge was impinged by the wake. The distribution of the pressure and friction along the whole pressure side and the leading edge of the suction side were affected by the pressure fluctuation propagation. The pressure fluctuation effect was determined by the pressure gradient and the blade surface shape.

Key words: Unsteady interaction；Boundary layer transition；Wake；Compressor