【摘要】 对跨声速单级轴流压气机NASA Stage 35开展了静叶开槽控制附面层分离的机理研究，基于3个前槽出口位置和两个后槽出口位置，组合设计了6种双槽方案。数值结果表明：在中小质量流量工况下，6种开槽方案均提高了压气机总性能，前槽出口位于13%C_a(C_a表示叶顶轴向弦长）、后槽出口位于60%C_a处的研究方案对压气机总性能的改善效果最好，在没有明显降低设计点效率的前提下，将近失速工况压气机效率的绝对量提升了1.3%。流场分析发现：在99%叶高处，较高的射流动量和更靠近分离涡核心的射流方向能更好的消除由附面层分离产生的低能流体。但低叶高未开槽范围的叶片表面附面层厚度有所增加，这是因为在径向压力梯度和原有分离区逆向流动的双重作用下，近槽道下壁面处速度较低的射流向叶根区域和叶片前缘迁移所导致的。更多还原

【Abstract】 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.更多还原