级环境下静叶开槽抑制附面层分离的机理研究

The mechanism of slotted stator blade controlling boundary layer separations was studied, and the transonic single-stage axial flow compressor NASA Stage 35 was selected as the research object. Based on three front slot outlet positions and two rear slot outlet positions, six double-slot schemes were designed. The numerical calculation results indicated that under small and medium mass flow rate conditions, all the schemes improved the compressor total performance. When the outlets of front slot and rear slot were located at 13%C_a (C_a was the blade tip axial chord length) and 60%C_a, the compressor total performance was the best. And without significantly reducing the design point compressor efficiency, the scheme exhibited the highest compressor efficiency improvement of 1.3% under the near stall condition. The internal flow field analysis showed that at 99% blade span, higher jet momentum and the jet direction closer to the separation vortex core better eliminated the low-energy fluids generated by the boundary layer separation. However, under the interaction of radial pressure gradient and reverse flow in the separation zone, the jet with lower velocity near the slot undersurface migrated to lower blade span and the leading edge of the blade, resulting in an increase in the thickness of the boundary layer at the lower blade span.