低雷诺数下附面层组合抽吸方案对压气机特性影响的研究  

Effect of integration suction scheme on the characteristic of compressor at low Reynolds number

作　　者：周敏[1] 李航航[1] 唐侃平[1] 

机构地区：[1]北京航空工程技术研究中心,北京100076

出　　处：《应用力学学报》2012年第1期27-31,115,共5页Chinese Journal of Applied Mechanics

摘　　要：为了分析附面层抽吸流动控制对低雷诺数下压气机特性的影响,本文采用数值方法模拟了低雷诺数下附面层组合抽吸方案对NASA Rotor 37跨音速压气机性能和稳定性的影响特点及作用机理。通过在该压气机转子叶片吸力面和机匣上分别设计附面层抽吸槽,探讨了组合抽吸方案对低雷诺数下(H=20km)压气机性能和稳定性的影响。结果表明:采用组合抽吸方案后,压气机峰值效率提高约1.3%;压气机最大增压比提高约2.5%;压气机转子的近失速点流量减小约14.6%。进一步分析作用机理发现,组合抽吸槽有效抑制了附面层径向涡向叶顶的运动和聚集,使叶顶附面层分离区减少约70%从而有效改善了压气机的流场特性。To analyze the effect of suction flow control on compressor characteristic at low Reynolds number,the effect of integration suction scheme on transonic axial-flow compressor performance and stability at low Reynolds number and its physical mechanisms is studied numerically.The first phase of the work involves the design of suction slots on the blade suction surface and shroud,and numerical simulation of integration suction flow control on compressor performance and stability.The numerical results obtained show that the relative increase of peak efficiency and maximum pressure ratio are 1.3% and 2.5%,respectively,and the relative reduction of flow rate at near stall condition is 14.6%.The mechanism studied shows that the movement and convergence of boundary layer radial vortex are effectively controlled by integration suction slot,and the boundary layer separation zone is reduced about 70%.Therefore,the flow field characteristic of compressor is improved.

关 键 词：跨音速压气机 低雷诺数 附面层抽吸 

分 类 号：V231.9[航空宇航科学与技术—航空宇航推进理论与工程]